Basic avionics module design for general aviation aircraft

TABLE 3.2-3 BAM CONNECTOR LIST PART NO.

P1-P7, P9 . MS 3106A-10SL-3S J1-J7, J9 MS 3101A-10SL-3P J10, Jll 50 PIN RIBBON CROSSOVER RECEPTACLE P10, Pll 50 PIN RIBBON CONNECTOR J12 UG492A BULKHEAD ADAPTER P12 UG88B/U COAX PLUG J13 DB-25S RS232C CONNECTOR P13 DB-25P RS232C PLUG J14 34 PIN RIBBON CROSSOVER RECEPTACLE P14 34 PIN RIBBON CONNECTOR 015 20 PIN RIBBON CROSSOVER RECEPTACLE P15 20 PIN RIBBON CONNECTOR J16 IEEE 488 INTERFACE CONNECTOR The autopilot actuator interfaces with the DMC using a cable consisting of a shielded twisted pair terminated in a Bendix connector. The internal wiring is via a shielded twisted pair cable connected to the Analog module with PC connectors which interfaces to the MN562 digital to analog converter (which is a 24 pin DIP) on the module. The MN562 has 12 bits resolution, converts in 1.5 microsec with an accuracy of .012% of full scale. If the full scale aileron deflection is 20 deg this corresponds to an accuracy of .0024 deg of aileron.

The three microcomputers are interconnected via the IEEE 488 parallel bus using the three digital I/O modules. The bus is implemented using a smart 488 bus chip (the MC 69488) which includes all the bus protocol and provides for defining the bus interface as a controller, talker, and listener. The controller function is assigned to microcomputer #3 (digital I/O module #3). The IEEE 488 bus interface for each microcomputer can be assigned as either a talker of listener with the assignment changeable. Microcomputer 12 is mainly a listener, and 13 is both a talker and listener as well as being the controller. An IEEE 488 bus connector is brought to the back of the DMC chassis so that other IEEE 488 devices can access the bus during simultaion. Internally the IEEE 488 bus connections are made to the three digital I/O modules using ribbon cable and PC connectors on the modules.

A pair of ribbon cables containing 50 conductors each terminated by two ribbon chassis connectors are used for each of the three nvaigation radios (two VOR/LOC receivers and one ADF receiver). Internally the connections are made to the digital I/O #3 module via two ribbon connectors. It would be highly desirable to put each of the navigation radios on the IEEE 488 bus which would reduce the amount of aircraft cabling from 96 wires to 16 wires, however, this would mean a special IEEE 488 bus interface at the radios.

The dual microfloppy diskette drive is connected to the DMC via a ribbon cable to the PL connector on the disk driver module located in microcomputer #3.

The 55 key keyboard as well as the 16 key telephone keyboard are connected to the DMC via an RS232C cable terminated in an RS232C connector. The internal connections is via a ribbon cable to a connector on the CPU/APU module. Each CPU/APU module has a RS232C interface, however the only one utilized is that on microcomputer #3.

The video for the 9" TV CRT display uses a shielded video cable connected to a BNC connector.

The SR-59 calculator is connected to the DMC from an 11 wire shielded cable from the cockpit to a Bendix connector on the DMC. The internal connection is via a ribbon connecter. A special ribbon cable from the SR-59 to a PC connector on the control panel is used to connect from the SR-59 printer interface to the calculator. The SR-59 is used to enter flight plan data into the DMC using a magnetic card entered into the SR-59.

4 . 0 SOFTWARE M O D U L E S The work breakdown structure of BAM software is shown in figure 4.0-1.

The software is broken down into those modules which are operational a n d those m o d u l e s w h i c h a r e I / O o r i e n t a t e d .

The p r e l i m i n a r y BAM s o f t w a r e is s u m m a r i z e d in f i g u r e 4 . 0 - 2 . The application software addressed during the BAM design used NORTHSTAR BASIC. A floating point board with floating point BASIC was acquired but not used for the BAM preliminary software. The BAM operational software will be updated to MICROPOLIS extended BASIC. Also a FORTRANIV and PASCAL compiler are available to generate compiled code executable by t h e 8085 m i c r o p r o c e s s o r .

ihe support s o f t w a r e is a v a i l a b l e s o f t w a r e compatible w i t h the Micropolis disk drive and provides for both higher order language and a s s e m b l y l a n g u a g e p r o g r a m m i n g .

The common software modules are used by all three microcomputers of the DMC and i n c l u d e : o A P U F l o a t i n g P o i n t M A t h R o u t i n e s This module includes a number of assembly language subroutines callable by BASIC .which execute the AM 9511 a r i t h m e t i c processor 32 bit f l o a t i n g commands i n c l u d i n g a d d , s u b t r a c t , m u l t i p l y , and the transcendental functions (log, exponentiation, sin, cos, e t c . ) . The floating point math utilizes the direct interface between the 8085 CPU and the 9511 APU with the results available on an interrupt basis. A growth feature can provide DMA control of the floating point APU to enhance the computational throughput should this prove to be desorable.

This f e a t u r e can be added by another w i r e wrap m o d u l e w i t h a DMA c o n t r o l l e r c h i p .

o I E E E 488 Bus C o n t r o l and Access This module includes a number of I/O s u b r o u t i n e s c a l l a b l e by BASIC w h i c h p r o v i d e f o r : o A c c e s s i n g d a t a f r o n t h e b u s o S e n d i n g d a t a t o t h e b u s The 488 bus protocol is implemented on an MC 68488 chip which is programmed to provide the controller function for microcomputer #3 and provides the t a l k e r l i s t e n e r f u n c t i o n s as r e q u i r e d by the DMC.

o M i c r o c o m p u t e r Self Test This module includes subroutines callable by BASIC which provide for testing all memory cells, I/O ports, and performing checks of other m i c r o c o m p u t e r e l e m e n t s .

The MILCO software development system is showm in figure 4.0-3. MILCO has recently acquired a FORTRAN IV Compiler which compiles into machine c o d e . H o w e v e r , t h e c o m p i l e r w a s n o t used o n BAM.

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A detailed breakdown of the BAM software modules is presented in table 4.0-1 w h i c h s u m m a r i z e s the status on the p r e l i m i n a r y BAM s o f t w a r e relative to the workbreakdown structure defined in f i g u r e 4.0-1. It should be noted that 100% complete means coded and v a l i d a t e d using North Star BASIC. A modest conversion e f f o r t is required to convert to t h e m o r e p o w e r f u l M i c r o p o l i s e x t e n d e d B A S I C .

T A B L E 4.0-1 B A M SOFTWARE S T A T U S R E L A T I V E T O W O R K B R E A K D O W N S T R U C T U R E P R O G R A M %

WBSf NAME MNEMONIC COMPLETE

1010 BAM SOFTWARE WORK BREAKDOWN STRUCTURE

2010 BAM I/O SOFTWARE

3010 NAVIGATION RADIO I/O MODULE

3011 VOR/LOC TUNING -MODULE 0%

3012 VOR/LOC BEARING MODULE 0%

3013 ADF TUNING MODULE 0%

3014 ADF BEARING MODULE 0%

3020 SENSOR I/O MODULE

3021 ANALOG INPUT MODULE 0%

3022 PULSE RATE INPUT MODULE 0%

3023 PARALLEL DIGITAL INPUT MODULE 0%

3030 PILOT ADVISORY & WARINING MODULE

2020 BAM OPERATIONS SOFTWARE

3040 SUPPORT SOFTWARE

3041 EXTENDED BASIC VERSION 4.0 BASIC 100%

3042.1 MICROPOLIS DISK OPERATING SYSTEM MDOS 100%

3043 8085 ASSEMBLER & LINE EDITOR 100%

3042.2 CP/M DISK OPERATING SYSTEM CP/M 100%

3044 FORTRAN IV COMPILER F80 100%

3045 UCSD PASCAL COMPILER AVAILABLE

APPLICATION SOFTWARE MODULES

3050 FLIGHT MANAGEMENT MODULES

3051.1 CHECKLIST CHCKLST 100%

3051.2 IFR CHECKLIST IFRCHKL 100%

3052 WEIGHT AND BALANCE WT&BAL 100%

3053.1 FLIGHT PLAN FLTPLN2 100%

3053.2 FLIGHT PLAN UPDATE FLTPLNUP 80%

3054 RESERVES RESERVES 0%

3055. FLIGHT PARAMETERS FLTPAR 0%

3056.1 AIRCRAFT PERFORMANCE (TAKE OFF) TOPRF 100%

TABLE 4.0-1 BAM SOFTWARE STATUS RELATIVE TO WORK BREAKDOWN STRUCTURE (CONT) CLBPRF 100% 3056.2 AIRCRAFT PERFORMANCE (CLIMB) 100% 3056.3 AIRCRAFT PERFORMANCE (LAND) LNDPRF 3060 NAVIGATION MODULES 0% 3061 POSITION INITIALIZATION 0% 3062 POSITION RESET 0% 3063 DISPLAY NAVIGATION DATA VORFIX 95% 3064.1 VOR RNAV VORRNAV 0% 3064.2 VOR RNAV 3065 ILS APPROACH 0% 3070 LATERAL FLIGHT CONTROL MODULES 3071 HOLD HEADING 0% 0% 3072 TURN LEFT OR RIGHT 100% 3073 RNAV COUPLING FLTCTRL 0% 3074 LOCALIZER COUPLING 0% 3075 TURN TO SELECTED HEADING 3076 ADF COUPLING 0% 3077 VOR COUPLING 0% 3078 AUTOPILOT OUTPUT 0% 3080 NAVIGATION MAP MODULES PARTIAL 3081 ENTER NAV MAP DATA BASE 3082 UPDATE NAV MAP DATA BASE 0% 3083 ACCESS NAV MAP DATA BASE (USED IN FLTPLN) 90% 3084 DISPLAY NAV MAP FORMATS (GROWTH FUNCTION) 3090 COMMON MODULES 3091 APU FLOATING POINT ROUTINES (NO LISTINGS AVAILABLE) 10% 3092 IEEE 488 I/O 0% 3093 MICROCOMPUTER SELF TEST (NO LISTINGS AVAIL.) MEMTEST 10% 5.0 .BAM SOFTWARE LISTINGS The source listings for preliminary BAM software sdhown completed in table 4.0-1 are included in this section. The source listings are well documented with REM (remark) statements to explain their operation, The listings are in the same order as table 4.0-1 with the WBS# shown on the listing for cross reference.

An additional listing of the BAM operational software including data files is shown in table 5.0-1.

TABLE 5.0-1 BAM OPERATIONAL SOFTWARE DESCRIPTION NAME ADDR LEN TYP MASTER MENU PROGRAM MASTER 4 4 .— » VORFIX 8 18 POSITION UPDATE BY MULTI. VOR PROGRAM POSITION 26 18 2 DATA FILE FOR POSITION IN LAT/LNG FLIGHT MANAGEMENT MENU PROGRAM MENU 27 4 3 31 17 2 VFR CHECK LIST PROGRAM CHECKLST IFRCHKL 48 40 2 IFR CHECK LIST PROGRAM WT&BAL 88 10 2 WEIGHT AND BALANCE PROGRAM FLTPLN2 98 41 2 FLIGHT PLANNING PROGRAM 0422 139 15 MAP DATA BASE FOR MAP SEGMENT 0422 FPDATA 154 4 3 DATA COMPUTED BY FLTPLN2 PROGRAM TOPRF 158 6 2 TAKE OFF PERFORMANCE PROGRAM CLBPRF 154 12 2 CLIMB PERFORMANCE PROGRAM LNDPRF 176 4 2 LANDING PERFORMANCE PROGRAM RESERVES 180 3 2 RESERVES CALCULATING PROGRAM FLTPAR 183 3 2 FLIGHT PARAMETER DISPLAY PROGRAM FLTCTRL 190 29 2 LATERAL FLIGHT CONTROL PROGRAM ADDR <= Sector number of program beginning on disk.

Disk has 350 sectors, 219 have been used so far.

LEN = Program length in 256 byte blocks TYP = Type of file: 2 = program 3 = data 5.1 MASTER MENU PROGRAM FIGURE 5.1-1 BAM FLOW CHART FOR MASTER MENU MASTER and MENU are program select routines which merely allow the operator to choose from a displayed selection of programs. The logic for both programs is simple: /DISPLAY PROGRAM SELECTION / r , y INPUT SELECTION/ CHAIN PROGRAM 1 CHAIN PROGRAM 2 CHAIN PROGRAM N ERROR!/ The display format is similar for both menu programs, which consists of a selection description, followed by a number, and, if the selection is not yet operational, a lower case V.

MILCO INTERNATIONAL. INC.

WBS# 3050.1 10 REM***** MASTER PROGRAM 5/31/78 20 A = C A L L ( 1 0 6 0 8 , 2 5 ) \ A = C A L L ( 1 0 6 0 8 , 1 1 ) 30 REM MASTER MENU PROGRAM 5/26/78 40 ! TAB (10) /'MASTER M E N U " 50 !

60 !"FUNCTION: E N T E R : " 70 ! "NAVIGATION 1 n" 80 ' " F L I G H T MANAGEMENT 2" 90 ! "NAVIGATION MAP 3 n " 100 !" LATERAL FLIGHT CONTROL 4 n" 110 !

120 ] " W H I C H FUNCTION ?" ,\B=CALL (10608 , 29) 130 INPUT " " , A $ 140 B=CALL (10608, 29) 150 IF A $ > " 9 " THEN 220 160 A = V A L ( A $ ) 170 IF A02 THEN 220 180 IF A=l THEN CHAIN "NAVMENU" 190 IF A=2 THEN CHAIN " M E N U " 200 IF A=3 THEN CHAIN "MAPMENU" 210 IF A=4 THEN CHAIN "CTLMENU" 220 !"RE-ENTER FUNCTION" 230 B=CALL (10608 , 31 )\A=CALL (10608,31) 240 GOTO 120 WBS# 3050.2 10 A=CALL (10608 , 25 )\A=CALL (10608 ,11) REM FLIGHT MANAGMENT MENU 5/26/78 30 ! TAB (10) /'FLIGHT MANAGEMENT MENU" i {"FUNCTION: E N T E R : " ! "CHECKLIST 1" 70 !"WEIGHT AND BALANCE 2" !" FLIGHT PLAN 3" !" RESERVES 4 n" !"FLIGHT PARAMETERS 5 n" 110 !"AIRCRAFT PERFORMANCE 6" 120 ! "WHICH FUNCTION ? " ,\A=CALL (10608 , 29) 130 INPUT " " , A $ \ I F A$="/" THEN CHAIN "MASTER" 140 IF A$="M" THEN CHAIN "MASTER" 150 A = V A L ( A $ ) 160 B = C A L L ( 1 0 6 0 8 , 2 9 ) 170 IF A=l THEN CHAIN "CHECKLST" 180 IF A=2 THEN CHAIN "WT&BAL" IF THEN CHAIN 190 A=3 "FLTPLN2" 200 IF A=4 THEN CHAIN "RESERVES" IF THEN 210 A=5 CHAIN "FLTPAR" 220 IF A=6 THEN CHAIN "TOPRF" 230 !"RE-ENTER FUNCTION" 240 A=CALL (10608, 31 )\A=CALL (10608 , 31) 250 GOTO 120 5.2 CHECKLIST PROGRAMS FIGURE 5.2-1 CHECK LIST FLOW DIAGRAM WBS# 3051.1 i—

I

DISPLAY CHECK LIST SELECTION MENU

i

>/INPUT / SELECTION -*-GOTO "EXTERIOR INSPECTION LIST" IS ->-GOTO "BEFORE STARTING ENGINE LIST" .SELECTION: IS

SELECTION: ->-GOTO "STARTING ENGINE LIST"

J?

"BEFORE TAKE OFF LIST" -^GOTO"NORMAL TAKE OFF LIST" TO IFR CHECK LIST MENU CHAIN TO FLT MGMT MENU "7 ERROR / WBS# 3051.1 10 DIM A l * ( l > , A 2 * ( 1 ) , A 3 * ( 1 ) , A 4 * ( 1 ) , A 5 * < 1 ) , A 6 $ ( 1 ) , A 7 * ( 1 > , A 8 * ( 1 ) , A 9 * < 1 ) 20 REM CHECKLST PROGRAM 5/31/78 30 A=CALL(10608,25)\A=CALL(10608,11) 40 !"CHECKLIST MENU" 50 !

60 !"FUNCTION: ENTER:" 70 !A1*,TAB(3),"EXTERIOR INSPECTION 1 " SO ! A2*, TAB(3), "BEFORE STARTING ENGINE 2" 90 !A3*,TAB<3),"STARTING ENGINE 3" 100 ! A4$, TAB(3), "BEFORE TAKEOFF 4" 110 ! A5*, TAB<3), "NORMAL TAKEOFF 5" 120 !A6*,TAB(3),"MAX IMUM PERFORMANCE TAKEOFF 6 " 130!A7*,TAB(3), "CLIMB 7" 140! AS'*, TAB(3) , "CRUISING 8" 150!A9*,TAB<3), "IFR CHECKLIST 9" 160 ! A9*, TAB(3), "CHECK LIST COMPLETE 10" 170 ."'WHICH FUNCTON ? ", 180 INPUT "",Q* 190 IF Q*="/"THEN CHAIN "MENU" 200 IF Q*="" THEN GOTO 330 210 Q=VAL(Q*> 220 IF Q =1 THEN 370 230 IF Q =2 THEN 690 240 IF Q =3 THEN 790 250 IF Q =4THEN 930 260 IF Q =5 THEN 1110 270 IF Q =6 THEN 1220 280 IF Q =7 THEN 1340 290 IF Q =8 THEN 1430 300 IF Q =9 THEN INPUT"INSERT DISK #302 THEN HIT RETURN"7C 310 IF Q =9 THEN CHAIN "IFRCHKL" 320 IF Q =10 THEN CHAIN "MENU" 330 !"RE-ENTER FUNCTION" 340 A=CALL(10608, 31) 350 A=CALL(10608,31) 360 GOTO 170 370 A=CALL(10608,25)\A=CALL(10608, 11 ) 380 !"EXTERIOR INSPECTION CHECKLIST" 390 !" REMOVE CONTROL WHEEL LOCK" 400 !" CHECK IGNITION SWITCH OFF" 410 f" TURN ON MASTER SWITCH, CHECK FUEL, TURN OFF MASTER SWITCH" 420 !" FUEL SELECT VALVE ON BOTH" 430 !" CHECK BAGGAGE DOOR" 440 !" REMOVE RUDDER GUST LOCK" 450 !" UNTIE TAIL" 460 !" CHECK RUDDER AND ELEVATOR" 470 !" CHECK AILERON" 480 !" UNTIE WINGS" 490 !" CHECK TIRE INFLATION" 500 !" VISUALLY CHECK FUEL, FILLER CAP" 510 !" CHECK OIL LEVEL, 6 GTS MINIMUM" 520 !" PULL FUEL STRAINER-DRAIN" 530 !" CHECK PROP AND SPINNER" 540 !" CHECK LANDING LIGHT" 550 !" CHECK NOSE GEAR STRUT" 560 !" CHECK STATIC SOURCE FOR STOPPAGE" 570 !" REMOVE COVER AND INSPECT PI TOT TUBE" 530 !" CHECK FUEL TANK VENT FOR STOPPAGE" 590 !" CHECK STALL WARNING VENT FOR STOPPAGE" 600 !" CHECK AILERON" 610 Z=22 620 A1*="*" 630 FOR R=l TO Z \A=CALL<10608,31)\NEXT R : 640 FOR R=l TO Z 650 INPUT "#",A* 660 NEXT R 670 A=CALL(1060S,25)\A=CALL(10608,11) 680 GOTO 20 690 A=CALL(10608,25)\A=CALL(10608,11) "BEFORE STARTING ENGINE" 11 1 720 SEATS, SEAT BELTS—ADJUST AND SECURE 730 " FUEL SLECTOR—BOTH" " BRAKES—TEST AND SET" 11 1 750 RADIOS AND ELECTRICAL EQUIPMENT—OFF 760 Z=4 770 A^2*="*" 780 GOTO 630 790 A=CALL(10608,25)\A=CALL(10608,11) 800 !"STARTING ENGINE" 810 !

820 !" MIXTURE—RICH" 830 !" CARB HEAT—COLD" 840 !" PRIMER—2 TO 6 STROKES, NONE IF WARM. CLOSE AND LOCK PRIMER 850 !" THROTTLE—OPEN 1/8 INCH" 360 !" MASTER SWITCH—ON" 870 !" PROPELLER AREA—CLEAR" 830 !" IGNITION SWITCH—START (RELEASE WHEN ENGINE STARTS)" 890 !" OIL PRESSURE—CHECK" 900 A3*="*" 910 Z=8 920 GOTO 630 930 A=CALL(10608,25)\A=CALL(10608,11) 940 !"BEFORE TAKE-OFF" 950 !

960 !" PARKING BRAKE—SET" 970 !" FLIGHT CONTROLS—CHECK FOR FREE AND CORRECT MOVEMENT" 930 !" FUEL SELECTOR—BOTH" 990 !" ELEVATOR TRIM—TAKEOFF SETTING" 1000 !" THROTTLE—1700RPM" 1010 !" ENGINE INST AND AMMETER—CHECK" 1020 !" SUCTION GAUGE—4.6 TO 5.4" 1030 !" MAGNETOS—CHECK EACH, RPM LOSS LESS THAN 125 RPM 1040 !" CARB HEAT—CHECK OPERATION" 1050 !" FLIGHT INSTRUMENTS AND RADIOS—SET" 1 <V-.O !" AUTOPILOT—OFF" *'' • 1070 !" CABIN DOORS AND WINDOW—LOCKED" 1080 A4$="#" 1090 Z=12 1100 GOTO 630 1110 A=CALL(10608,25)\A=CALL <10608,11) 1120 .'"NORMAL TAKE-OFF" 1130 !

1140 !" WING FLAPS— 0"" 1150 !" CARB HEAT—COLD" 1160 !" POWER—FULL THROTTLE" 1170 !" ELEVATOR—LIFT NOSE WHEEL AT 60 MPH" 1180 !" CLIMB SPEED—75 TO 85 MPH" 1190 Z=5 1200 A5*="*" 1210 GOTO 630 1220 A=CALL(10608,25)\A=CALL(10608,11) 1230 !"MAX IMUM PERFORMANCE TAKEOFF" 1240 !

1250 !" WING FLAPS- 0"" 1260 !" CARB HEAT—COLD" 1270 !" BRAKES—APPLY" 1280 !" POWER—FULL THROTTLE" 1290 !" BRAKES—RELEASE" 1300 !" AIRPLANE ATTITUDE—SLIGHTLY TAIL LOW" 1310 Z=6 1320 A6*="*" 1330 GOTO 630 1340 A=CALL(10608,25)\A=CALL(10608,11) CLIMB" AIRSPEED—80 TO 90 MPH" 1380 POWER—FULL THROTTLE" MIXTURE—FULL RICH (MAY BE LEANED ABOVE 3000 FEET) 1400 Z=3 1410 A7*="*" 1420 GOTO 630 1430 A=CALL(10608,25)\A=CALL <10608,11) 1440 !" CRUISING" 1450 !

1460 !" POWER—2200 TO 2700 RPM" 1470 !" ELEVATOR TRIM—ADJUST" 1480 !" MIXTURELEAN FOR MAXIMUM RPM" 1490 Z=3 1500 A8*="*" 1510 GOTO 630 FIGURE 5.2-2 IFR CHECK LIST WBS# 3051.2 'DISPLAY IFR CHECK LIST MENU I INPUT SELECTION ->-GOTO IFR PRESTART LIST EXTERIOR LIST •>-GOTO ENGINE STARTING LIST CHAIN TO FLT MGMT MENU ERROR WBS# 3051.2 REM ***** THIS IS THE IFR CHECKLIST SUBROUTINE CALLED FROM CHECKLST 20 REM IFRCHKL 30 DIM A*<14> !CHR*(12) PRINT" IFR CHECKLIST MENU 1.2.9" '\PRINT\PRINT 60 PRINT" 70 PRINT"FUNCTION: ENTER: SO PRINT !A*(1,1),TAB(3> IFR PRESTART 1 !A*(2,2),TAB<3) "EXTERIOR : !A*(3,3> "TAXI & SHUT DOWN 3" 110 ) TAB( 120 !A*(4,4),TAB(3), "MISSED APPCH SEGMENT 4" 130 "FINAL APPCH SEGMENT 5" !A*(5,5),TAB(3), 140 INTERMEDIATE SEGMENT 6" !A*(6,6),TAB(3), 150 !A*(7,7),TAB(3), "INITIAL APPCH SEGMENT 7" 160 !A*(8,8),TAB(3), "TRANSITION 8" 170 !A*(9,9),TAB<3), "LANDING ENROUTE 9" !A*(10,10),TAB(3), ENROUTE 10" ISO 190 !A*(11,11),TAB< 3) . TAKE OFF / CLIMB OUT 11" 200 !A*(12,12),TAB(3), RUN UP 12" !A*(13,13),TAB(3), PRETAXI AND TAXI 13" 220 !A*(14,14),TAB(3), ENGINE STARTING 14" 230 !" RETURN TO FLIGHT MGMT MENU.. 15" 240 INPUT "WHICH FUNCTION 250 THEN GOTO 490 IF F=l THEN IF F=2 730 260 GOTO — •"•» 270 THEN IF F GOTO 950 — O 230 THEN IF F=4 GOTO 1200 290 THEN IF F=5 GOTO 1350 300 THEN IF F=6 GOTO 1530 310 THEN IF F=7 GOTO 1680 320 THEN IF F=8 GOTO 1880 THEN IF F=9 330 GOTO 2070 340 THEN IF F=10 GOTO 2330 350 THEN IF F=ll GOTO 2590 THEN IF F=12 GOTO 2760 370 THEN IF F=13 GOTO 3130 THEN IF F=14 GGTO 380 3400 390 THEN IF F=15 INPUT"INSERT DISK #203 THEN HIT RETURN ,S* 400 THEN IF F=15 CHAIN "MENU" 410 TO Z FOR R=l 420 !CHR*(31)t 430 NEXT R 440 FOR R=l TO Z INPUT "*",B* 460 NEXT R 470 !CHR*(12) 480 GOTO 40 490 !CHR*(12) 500 PRINT IFR PRESTART CHECKLIST" 510 PRINT" AIRCRAFT DOCUMENTS ON BOARD" 550 CHARTS,PLATES,LOG,WX,ORGANIZED" 560 AIRSPEED INDICATOR ZERO" 570 ALTIMETER (SET TO FIELD ELEVATION)" 580 CLOCK (WIND S< SET TO GMT)" ENGINE INSTRUMENTS (ON ZERO)" 600 DG UNCAGED" 610 MAG COMPASS FULL OF FLUID" 620 VOR ACCURACY LOGGED" A/C LOG BOOK CHECKED" 640 SUCTION GAUGE ZERO" TURN & BANK CENTERED ?< FULL OF FLUID" VERTICAL SPEED INDICATOR ON ZERO" SET COMM FREQS."

NAV #2 (ILS) SET DEP. ARPT. APPCH" 690 SET ENROUTE VOR" NAV #1 Z=16 710 A*(l)="#" 720 GOTO 410 730 !CHR*(12) 740 PRINT " EXTERIOR CHECKLIST 750 PRINT " 770 " INSIDE MAG OFF, MASTER OFF, FLAPS DOWN, BRAKE ON" 780 " INSIDE CONTROLS FREE, PRIME" 790 " RWING FLAP, AILERON, TIP, LIGHTS, LEADING EDGE, FUEL" 800 " RWING VENTS, GEAR 22/4, DRAIN, TIEDOWN, DRAIN FUEL" 810 " ENGINE SECURE R COWLING, GEN BELT, PULL PROP,AIR FLOW" 820 " ENGINE OIL 9, BRAKE FLUID,SECURE L COWLING" 830 " LWING FUEL, GEAR, VENT, DRAIN,TIEDOWN, STALL WARNING" 840 " LWING PITOT TUBE, LEADING EDGE, TIP, LIGHTS" 850 " LWING AILERON, FLAP" 860 " FUS/TAIL STATIC PORT, ANTENNAS, STABILATOR, RUDDER, LIGHT" 870 " FUS/TAIL TIEDOWN, UNDERSIDE, STATIC PORT, STOW TOW BAR" 880 " FUS/TAIL BAGGAGE DOOR" 890 " INSIDE SWITCH TANKS, MASTER ON, PITOT HEAT ON, FLAPS UP" 900 " INSIDE MASTER OFF, PITOT HEAT OFF" 910 " OUTSIDE DRAIN FUEL, PITOT HEAT, CLOSE FUEL DRAIN DOOR" 920 Z=15 930 A*(2)="#" 940 GOTO 410 950 !CHR*(12) 960 PRINT" TAXI & SHUT DOWN" 970 PRINT" \PRINT 980 !" FLAPS UP" 990 !" MK 7 ON (OFF)" 1000 !" MK 5 OFF (ON)" i 1010 ADF OFF" i 1020 NAV 122 OFF" !

1 030 XPDR OFF" i 1 040 FUEL PUMP OFF" i 1 050 STROBE OFF" i 1 060 REMOTE COMPASS OFF" i 1070 LANDING LIGHTS (AS NEEDED)" i 1080 PITOT HEAT OFF" i 1 090 CARB HEAT OFF" i 1100 TURN & BANK OFF" t 1 1 1 0 CLOSE FLIGHT PLAN (NO TOWER) i 1120 RADIOS OFF, IDLE MAG CHECK" !

1130 RPM 1000 12000, MIXTURE IDLE CUT OFF" !

BEACON OFF, MAGS OFF, MASTER OFF" i 1 1 50 LOG TIME, SECURE CONTROL SURFACES" !

1160 TIE DOWN AIRCRAFT, LOCK DOOR" Z=19 1 1 70 Z 1180 A A*(3)="*" 1190 G GOTO 410 1 200 R REM i 1210 !CHR*(12) !

1220 MISSED APPCH SEGMENT i 1 230 !

1 240 !

1250 TURN TIME TWIST THROTTLE TALK TRACK" i 1260 GUMP" i NO TURN BEFORE MAP" i CHECK MISSED APPCH ALT & HDG" i 1290 REPORT TO TWR" i 1300 LANDING LIGHTS OFF" t 1310 CONTACT APPROACH CONTROL" 1320 Z 1330 A A*(4)="*" 1340 GI GOTO 410 REM 1350 Rl ! i 1360 !CHR*(12) 1370 PI PRINT" IFR FINAL APPCH SEGMENT PRINT" 1380 PI i !

TURN-TIME-TWIST-THROTTLE-TALK-TRACK i 1410 START CLOCKS AT FAF" !

1420 REPORT FAF" !

1430 GUMP" !

SCAN ALT/MDA" i 1450 SCAN TIME/MAT" i DESCEND TO MDA/DH" i 1470 SMALL CORRECTIONS" i 1480 FIELD IN SIGHT" i FLAPS AS NEEDED" 1500 2 Z=10 1510 A$<5)="*" GOTO 410 1530 REM 1540 !CHR*(12) 1550 PRINT" IFR INTERMEDIATE SEGMENT PRINT" 1580 TURN-TIME-TWIST-THROTTLE-TALK-TRACK" 1590 DESCEND TO IFR ALT."

1600 GUMP" 1610 LANDING LIGHTS ON" 1620 SCAN APPCH PLATE" 1630 MAINTAIN APPCH SPEED" 1640 CONTACT TOWER" 1650 2=7 1660 A*<6)="*" 1670 GOTO 410 1630 REM 1690 !CHR*(12) 1700 PRINT" IFR INITIAL APPCH SEGMENT PRINT- 1730 TURN-TIME-TWIST-THROTTLE-TALK-TRACK' 1740 SLOW TO APPCH SPEED" 1750 DESCEND TO IFR ALT."

1760 SCAN APPCH PLATE" 1770 TIME LEGS" 1780 SET ADI" 1790 SET DG BY COMPASS" 1800 LOAD HP25 MDA & TIME TO MAP" 1810 SET REMOTE COMPASS POINTER" SET ILS OBS CRS" SET ALTIMETER" ii 1840 CHECK OAT" 1850 Z=12 1870 GOTO 410 1830 REM 1390 !CHR$(12) 1900 PRINT" IFR TRANSITION SEGMENT" 1910 PRINT" TURN-TIME-TWIST-THROTTLE-TALK-TRACK' 1940 DESCEND TO IFR ALT" SCAN APPCH PLATE" 1960 STUDY FINAL APPCH CRS" STUDY TIME TO MAP " 1980 STUDY MDA OR DH" 1990 STUDY AIRPORT DIAGRAM" 2000 STUDY MISSED APPCH" 2010 !" PITOT HEAT AS NEEDED" 2020 !" COPY APPCH CLEARANCE" 2030 !" CARB HEAT AS NEEDED" 2040 Z=ll 2050 A*(3)="*" 2060 GOTO 410 2070 REM 2080 !CHR»(12)i 2090 PRINT" IFR LANDING ENROUTE CHECKLIST" 2100 PRINT" " 2110 !

2120 !" WX (ATIS) OBTAIN" 2130 !" SCAN APPCH. PLATE" 2140 !" GROUNDSPEED ON FINAL DETERMINED" 2150 !" TIME FAF TO MAP DETERMINED" 2160 !" TIME TO START DESCENT" 2170 !" SET DG BY COMPASS" 2180 !" CHECK OAT" 2190 !" SEAT BELTS FASTENED" 2200 !" SELECT FULLEST TANK" 2210 !" DEFROSTER AS NEEDED" 2220 !" RESET CLOCK SECOND HAND" 2230 !" MKR BCN SPKR ON (TEST)" 2240 ! " TUNE VOR & IDENT" 2250 !" TUNE ILS & IDENT" 2260 !" TUNE ADF & IDENT" 2270 !" TUNE TWR #2 RADIO" 2280 !" PITOT HEAT AS NEEDED" 2290 !" SET ALTIMETER" 2300 Z=18 2310 A*(9)="*" 2320 GOTO 410 2330 REM 2340 !CHR*(12) 2350 PRINT" IFR ENROUTE CHECKLIST" 2360 PRINT" "\PRINT 2370 !" CRUISE POWER SET" 2380 !" MIXTURE / EGT SET" 2390 !" CARB HEAT AS NEEDED" 2400 !" OAT CHECKED" 2410 !" FUEL MGMT" 2420 !" PITOT HEAT AS NEEDED" 2430 !" SET DG BY COMPASS" 2440 !" OIL PRESSURE / TEMP NORMAL" 2450 !" FUEL PRESSURE NORMAL" 2460 !" FUEL PUMP OFF" 2470 !" GENERATOR CHARGING" 2480 !" SUCTION 4-5 IN. " 2490 !" SET ALTIMETER" 2500 !" RUDDER TRIM BALL CENTERED" 2510 !" INDENT VORS" 2520 !" FCST / CURRENT WX REPORTS" 2530 !" REPORTS TO ATC" 2540 !" MAINTAIN MEA / MOCA" 2550 !" COM FAILURE SEE FAR 91.127" 2560 Z=19 2570 A*(10)="*" 2580 GOTO 410 2590 REM 2600 !CHR*(12) 2610 PRINT" TAKE OFF / CLIMB OUT CHECKLIST" 2620 PRINT " " \ PR I NT \PR I NT 2630 !" DG SET TO RUNWAY HEADING" 2640 !" ADI WINGS LEVEL" 2650 !" ROTATE AT SG KTS" 2660 !" RETRACT GEAR" 2670 !" NORMAL CLIMB 90 KTS" 2680 !" Vx = 70 KTS, VY = 80 KTS" 2690 !" REDUCE POWER 24"'-' 2400 RPM" 2700 !" XPDR ON" 2710 !" CONTACT DEPARTURE" 2720 .'" RETURN TO TOWER (NEGATIVE CONTACT)" 2730 Z=10 2740 A*(l !) = "•»" 2750 GOTO 410 2760 REM 2770 !CHR*(12), 2780 PRINT" RUN UP CHECKLIST" 2790 PRINT" " 2800 !" BRAKE ON " 2810 !" SWITCH TANKS" 2820 !" SET 1700 RPM" 2830 !" CHECK MIXTURE CONTROL" 2840 !" CHECK CARB HEAT" 2850 !" SET 2000 RPM" 2860 !" CHECK MAG DROP" 2870 .'" FULL IDLE-THEN 1000-15000 RPM" 2380 !" SET TRIM TAB" 2890 !" AUTO PILOT OFF" 2900 !" CHECK CONTROL SURFACES (FLAPS UP)" 2910 !" DOOR CLOSED & LOCKED" 2920 !" SEAT BELTS" 2930 ! " FUEL PUMP ON" 2940 !" EMERGENCY GEAR HANDLE CLEAR" 2950 !" RECEIVE CLEARANCE" 2960 !" XPNDR SET- ON" 2970 !" COM FREQ SET " 2980 !" TWR FOR TAKE OFF CLEARANCE" 2990 !" RECORD TIME" 3000 !" STROBE ON" 3010 !" BRAKE OFF", 3020 2=22 3030 A*(12)="*" 3040 FOR R=l TO Z 3050 !CHR*(31), 3060 NEXT R 3070 !

3030 FOR R=l TO Z 3090 INPUT "#",B* 3100 NEXT R 3110 !CHR*<12) 3120 GOTO 40 3130 REM 3140 !CHR*(12) 3150 PRINT" PRETAX I AND TAXI CHECKLIST" 3160 PRINT" 3170 PRINT 3180 !" RADIOS ON, XPDR STBY" 3190 !" ROTATING BEACON ON" 3200 ! " TURN & BANK ON" 3210 !" GENERATOR CHARGING" 3220 !" XMTRS CHECKED" 3230 !" OBTAIN ATIS INFORMATION" 3240 !" OBTAIN TAXI CLEARANCE" 3250 !" SET DO / WET" 3260 !" SET ADI LEVEL" 3270 !" SET ALTIMETER (ERROR < 75FT>" 3230 !" ADF POINTS TO LOCAL NDB" 3290 !" NAV SET FOR IFR APPCH" 3300 !" TEST AUTO PILOT OPERATION" 3310 !" BRAKE OFF" 3320 ! " CHECK TURN ?< BANK" 3330 !" CHECK DG" 3340 !" CHECK ADI" 3350 !" CHECK ADF" 3360 !" VOR ACCURACY CHECK" 3370 Z=19 3380 A*(13)="*" 3390 GOTO 410 3400 REM 3410 !CHR*<12), 3420 PRINT" ENGINE STARTING CHECKLIST" 3430 PRINT" ' 3440 !

3450 !" BRAKE ON, RADIOS OFF" 3460 !" RADIOS OFF" 3470 !" CIRCUIT BREAKERS IN" 3480 !" GEAR SWITHC DOWN" 3490 !" EMPTIEST TANK" 3500 !" CARB HEAT OFF" 3510 PROP IN" MIXTURE RICH" MASTER SWITCH ON " 3540 FUEL PUMP ON " CHECK FUEL PRESSURE" 3560 PRIME, FUEL PUMP OFF" THROTTLE (1/4'")" 35SO MAGS ON, CLEAR PROP" 3590 START ENGINE (LOG TIME)" MAGS BOTH, 1000 RPM" OIL PRESSURE CHECKED" VACUUM 4-5 IN" FUEL GAUGES CHECKED" 3640 GEN CHARGING AT 1500 RPM" 3650 SEATS BELTS ON", 3660 Z=21 A*(14)="#' 3680 GOTO 3040 5.3 WEIGHT AND BALANCE PROGRAM TABLE 5.3-1 is a list of symbols for weight and balance, FIGURE 5.3-1 WEIGHT AND BALANCE FLOW DIAGRAM INITIALIZE CONSTANTS INPUT PASSENGER WEIGHTS, FUEL COMPUTE MOMENT ARM COMPUTE WEIGHT COMPUTE AFT C.G. LIMIT COMPUTE FWD C.G. LIMIT PRINT MOMENT ENVELOPE, AIRCRAFT C.G.

SYMBOLS FOR W&B FLOW CHARTS, TABLE 5.3-1 A Dummy for cursor control B Baggage lever arm Cl Pilot weight, pounds C2 Copilot weight, pounds C3 Passenger weight, pounds C4 Passenger weight, pounds C5 Fuel weight, pounds C6 Baggage, pounds E Empty weight of airplane F Fuel lever arm Gl Fuel, gallons M2 Moment of loaded plane M Moment used for plotting Ml Moment of empty plane P Passenger (rear) lever arm Pi Pilot (front seat) lever arm R Loop variable W Weight of loaded plane Wl Weight used for plotting W9 Weight (plotting) loop Y Aft C. G. limit Yl Forward C. G. limit WBS# 3052 10 A=CALL (10608, 25 )\A=CALL (10608,11) 20 REM ** WEIGHT AND BALANCE, DATA FOR CESSNA 172 30 E=1364 \REM EMPTY WT OF AIRPLANE 40 F=48.25\REM FUEL LEVER ARM 50 P l = 3 7 . 5 \REM PILOT LEVER ARM 60 P=73.00 \REM REAR SEAT LEVER ARM 70 B =95.0 \REM BAGGAGE LEVER ARM 80 M l = 5 1 . 7 \REM MOMENT OF EMPTY PLANE/1000 90 !"WEIGHT AND BALANCE" 100 J 110 !"WEIGHT OF PILOT: LBS " , 120 GOSUB 450 130 C 1 = V A L ( A $ ) 140 OUT 2 , 2 9 150 ! TAB ( 3 0 ) / ' C O P I L O T : LBS ", 160 GOSUB 450 170 C 2 = V A L ( A $ ) 180 OUT 2 , 2 9 190 !

200 !"REAR SEAT PASSENGER: LBS ", 210 GOSUB 450 220 C 3 = V A L ( A $ ) 230 OUT 2 , 2 9 240 !TAB ( 3 0 ) /'PASSENGER: LBS ", 250 GOSUB 450 260 C 4 = V A L ( A $ ) 270 OUT 2 , 2 9 280 !

290 !

300 !"FUEL: GAL " , 310 GOSUB 450 320 G 1 = V A L ( A $ ) 330 OUT 2 , 2 9 340 ! TAB ( 3 0 ) /'BAGGAGE: LBS ", 350 GOSUB 450 360 C6=VAL(A$) 370 OUT 2 , 2 9 380 !

390 C5=G1*6 \REM F U E L WT IN LBS 400 M = ( ( C 1 + C 2 ) * P 1 + ( C 3 + C 4 ) * P + C 5 * F + C 6 * B ) / 1 0 0 0 + M l 410 W=C1+C2+C3+C4+C5+C6-136 420 Y=.0475*W+71 430 IF W>450 THEN Yl=.059375*W+42 ELSE Y l = 3 . 4 4 4 4 4 4 E - 0 2 * W + 5 2 . 5 440 GOTO 490 450 FOR R=l TO 4\A=CALL (10608,8 )\NEXT R 460 I N P U T 1 " " , A $ 470 IF A$="M" THEN CHAIN "MENU" 480 RETURN 490 W1=W+E+151 500 M=M/1.6 510 A=CALL (10608, 25 )\A=CALL (10608 ,11) 520 !" C.G. FORWARD / C.G. OK / C.G. AFT" 530 FOR W9=2500 TO 2350 STEP -50 540 IF WKW9 AND Wl>W9-50 THEN ! "ERROR OVER GROSS" ,TAB (M/l. 5) ,"* "ELS E!

550 NEXT W9 n 560 ! T A B ( 5 6 ) , " 570 FOR W9=2300 TO 1950 STEP -50 580 Yl=.059375*(W9-1515)+42 590 Y1=Y1/1.6 600 Y = . 0 4 7 5 * ( W 9 - 1 5 1 5 ) + 7 1 610 Y=Y/1.6 620 IF Y>79 THEN Y=79 630 IF WK=W9-50 OR Wl> W9 THEN 680 640 IF YKM AND M<Y THEN 720 650 IF Y1>M THEN 700 660 !"ERROR AFT CG" , TAB ( Y l ) , " / " , TAB ( Y l ) ,"/", TAB (M) ,"*" 670 GOTO 730 680 ! W 9 , T A B ( Y 1 ) ,"/" , T A B ( Y ) ,"/" 690 GOTO 730 700 ! "CALL FAT-SO'S ANONYMOUS! " , TAB (M) ,"*", TAB ( Y l ) , " / " , TAB (Y ) , " / ' 7.10 GOTO 730 720 !"WT & BAL 0. K" TAB ( Y l ) ,"/" , T A B ( M ) , "* " , TAB (Y ) ,"/" f 730 NEXT W9 740 FOR W9=1900 TO 1400 STEP -50 750 Y l = 3 . 4 4 4 4 4 E - 2 * ( W 9 - 1 5 1 5 ) + 5 2 . 5 760 Y1=Y1/1.6 770 Y = .0475*(W9-1515)+71 780 Y=Y/1.6 790 IF W9<1951 AND W9>1849 THEN Y1=Y1-1 800 IF W9=1950 THEN Y=Y-1 810 IF WKW9-50 OR W1>W9 THEN 860 820 IF YKM AND M<Y THEN 900 830 IF Y1>M THEN 880 840 !"ERROR AFT CG" , TAB ( Y l ) , " / " , TAB (Y ) , " / " , TAB (M) ,"*" 850 GOTO 910 860 ! W 9 , T A B ( Y 1 ) ,"/" , T A B ( Y ) ,"/" 870 GOTO 910 880 !"ERROR HELIUM IN BAGGAGE" , TAB (M) ,"*" ,TAB ( Y l ) , " / " , TAB (Y ) , "/" 890 GOTO 910 900 !"WT & BAL 0. K" ,TAB (Y 1) ,"/" , T A B ( M ) , " * " , T A B ( Y ) ,"/" 910 NEXT W9 920 ! T A B ( 3 0 ) , " " 930 !"1 ANOTHER WEIGHT & BALANCE" 940 !"2 RETURN TO MENU" 950 INPUT "WHICH FUNCTION ? " ,A 960 IF A=2 THEN CHAIN "MENU" 970 GOTO 10 5.4 FLIGHT PLAN PROGRAM FIGURE 5.4-1 FLTPLN FLOWCHART . . .FLIGHT PLAN FLOW CHART ALL VARIABLES = 0 BEFORE INITIALIZE VARIABLES & DEFINE USER FUNCTIONS THEY ARE 1ST USED /INPUT AIRPORT TEMP., INPUT WINDS ALOFT FLIGHT PLAN FLOW CHART #1 FLIGHT PLAN FLOW CHART #2 MILCO INTERNATIONAL. INC.

GET NAME GET NAME GET NAME GET LAT/LNG LAT/LNG LAT/LNG LAT/ MEA MEA MEA MEA | 1- \ /PRINT WAYPOINT NAME/ /INPUT ENROUTE ALT/ /PRINT "DES "CLB / /FLASH MEA/ /P "LND /

T

U CONVERT LAT/LNG TO RADIAN

i

COMPUTE COURSE TO WAYPOINT /PRINT FROM,TO/ COMPUTE DISTANCE FIND SPEED USING FLIGHT PLAN CLIMB PERF. ALGORITHMS FLOW CHART #3 MILCO INTERNATIONAL. INC.

COMPUTE SPEED CORRECT HEADING & GROUND SPEED FOR WIND

I

FIND G.P.H.

RESERVES

I

/ PRINT COMPUTED D/ DATA / FLIGHT PLAN FLOW CHART #4 INTERNATIONAL. INC.

FLIGHT PLAN SYMBOL TABLE 5.4-1 A DUMMY FOR CURSOR CONTROL A* AIRPORT NAME FROM DISK AS NUMBER OF LAST WAYPOINT A9 WAYPOINT POINTER A@ AIRPORT PARAMETER ARRAY B* NDB NAME FROM DISK Bl INPUT FORMAT TAB VARIABLE B2 INPUT FORMAT TAB VARIABLE B3 INPUT FORMAT TAB VARIABLE B@ NDB PARAMETER ARRAY C$ ALTITUDE MNEMONIC C2 MEA INDICATOR Ce ALTITUDE INPUT Dl WINDS ALOFT DIRECTION D@ WAYPOINT NUMBER INPUT E ALT < MEA ERROR FLAG E$ INPUT VARIABLE E2 ESTIMATED TIME ENROUTE E3 ESTIMATED TOTAL TIME Fl NUMBER OF VOR ON MAP F2 NUMBER OF INTERSECTIONS ON MAP F3 NUMBER OF AIRPORTS ON MAP F4 NUMBER OF ILS ON MAP F5 NUMBER OF N.D.B. ON MAP G* WAYPOINT MNEMONIC Gl INITIAL FUEL G2 GPH HI TEMP AT AIRPORT H3 DIST FROM WPT(A9) TO (A9+1) H9 TOTAL DISTANCE OF FLIGHT I* ILS NAME FROM DISK I@ ILS PARAMETER ARRAY •J2 USED IN COURSE COMPUTATION J3 SAME J4 SAME J5 SAME J6 SAME J7 SAME J7 MAGNETIC HEADING JS SAME J9 TRUE COURSE K2 RADIAN LAT ARRAY K@ WAYPOINT LATITUDE ARRAY L2 RADIAN LNG ARRAY L@ WAYPOINT LONGITUDE ARRAY M@ MAGNETIC VARIATION FOR MAP SEC N* INTERSECTION NAME FROM DISK N@ INTERSECTION PARAMETER ARRAY 0* CURRENT MAP SECTOR NUMBER FLIGHT PLAN SYMBOL TABLE 5.4-1 (CONT.)

P PI HR 3.14159 ; P$ INITIAL MAP SECTOR NUMBER PI NUMBER OF VOR ON MAP P2 NUMBER OF INTERSECTION PARAMET P3 NUMBER OF AIRPORT PARAMETERS P4 NUMBER OF ILS PARAMETERS- PS NUMBER OF N.D.B. PARAMETERS R LOOP VARIABLE R* STRING OF ALL INTER. NAMES Rl REMAINING FUEL R2 TIME RESERVES S* STRING OF ALL AIRPORT NAMES T* STRING OF ALL ILS NAMES Tl CRUISE POWER SETTING ( 7 . ) T2 ESTIMATED TIME OF DEPARTURE T4 AIRSPEED U* STRING OF ALL NDB NAMES V* VOR NAME AS READ FROM DISK V@ VOR PARAMETER ARRAY W LOOP VARIABLE Wl WINDS ALOFT WINDSPEED X LOOP VARIABLE X DUMMY FOR DEC TO RAD CONVERSIO Y DECIMAL LAT Y DUMMY FOR ARCSIN FUNCTION Yl DECIMAL LAT OF NEXT WAYPOINT Z* STRING OF ALL VOR NAMES WBS# 3 53>1 10 REM FLTPLN 8/31/78 ° 20 I C H R $ ( 1 2 ) 30 OPEN #2,"FPDATA" 40 REM FNS(X) RETURNS ARCS IN (X) 50 DBF FNS (X) 60 Y=1.5707288-.2121144*X+.074261*X~2-.0187293*X~3 70 Y=3.l41592654/2-SQRT(l-X)*Y 80 RETURN Y 90 FNEND 100 DEF FNR(X)=X*3.141592654/180 110 DIM D(20) ,C(20) ,K(20) ,L(20) 120 REM *********** INPUT INITIAL FUEL ******************** 130 !"INIT FUEL: GG", 140 !CHR$(29), 150 FOR R=l TO 2 \ A = C A L L ( 1 0 6 0 8 , 8 ) \ N E X T R n 160 INPUT1 " , E $ 170 ! C H R $ ( 2 9 ) , 180 IF E$="M" THEN CHAIN "MENU" 190 IF E$0"E" THEN 210 200 !\!CHR$(31),\GOTO 130 210 G1=VAL(E$) 220 1" gal",TAB(30), 230 REM ************* INPUT AIRPORT OAT ******************* 240 !"TEMP 'C AT AIRPORT: CC" , 250 FOR R=l TO 2\! CHR$ (8) ANEXT R 260 I N P U T l " " E $ f 270 ! C H R $ ( 2 9 ) , 280 IF E$="M" THEN CHAIN "MENU" 290 IF E$0"E" THEN 310 300 !\!CHR$(31),\GOTO 130 310 H1=VAL(E$) 320 !"'" 330 REM ************** INPUT FORCAST WINDS ALOFT ************** 340 !"WIND: DEC KTS", 350 FOR R=l TO 9\! CHR$ (8 ) , \NEXT R 360 INPUT1"",E$ 370 IF E$="M"THEN CHAIN "MENU" 380 IF E$0"E" THEN 420 390 ! \ ! C H R $ ( 3 1 ) , \ ! C H R $ ( 2 9 ) ,\!CHR$(31) , 400 FOR R=l TO 28\! CHR$ (28) ,\NEXT 410 GOTO 240 420 D1=VAL(E$)-180 430 IF DKO THEN D1=VAL (E$)+180 440 !'"", 450 FOR R = ( 5 - L E N ( E $ ) ) TO 1 STEP -1 460 J" ", 470 NEXT R 480 INPUT1 " " , E $ 490 ! C H R $ ( 2 9 ) , 500 IF E$="M" THEN CHAIN "MENU" 510 IF E$0"E"THEN 540 520 !\!CHR$(31), 530 GOTO 340 540 W1=VAL(E$) 550 1" kts", 560 FOR R=l TO 12-LEN ( E $ ) \ ! " ",\NEXT R 570 REN ****************** INPUT CRUISE POWER SETTING ***************** 580 J " C R U I S E % BHP: PP ", 590 J C H R $ ( 8 ) , 600 ] C H R $ ( 8 ) f 610 I C H R $ ( 8 ) / 620 INPUT1"",E$ 630 ! C H R $ ( 2 9 ) f 640 IF E$="M" THEN CHAIN "MENU" n 650 IF E$0"E THEN 710 660 !\!CHR$(31), 670 FOR R=l TO 12\! CHR$ (28) ,\NEXT 680 !"KTS" ,\!CHR$(29) , 690 FOR R=l TO 3\! CHR$ (8 ) ,\NEXT 700 GOTO 480 710 T1=VAL(E$) 720 !"%" 730 REM ************** INPUT ETD *********************** 7 4 0 J " E T D : H H . M M " , 750 FOR R=l TO 5\! CHR$ (8 ) ,\NEXT 760 I N P U T 1 " " , E $ 770 IF E$="M"THEN CHAIN "MENU" 780 IF E$0"E THEN 820 790 !\!CHR$(31) ,\!CHR$ ( 2 9 ) ,\!CHR$ (31) , 800 FOR R=l TO 28\! CHR$ (28) \NEXT f 810 GOTO 580 820 T 2 = V A L ( E $ ) 830 !" hrs" 840 !

850 A9=0 860 B1=10\B2=20\B3=30 870 REM ************* INPUT INITIAL MAP # ******************** 880 !"INITIAL MAP f: NNNN",\FOR R=l TO 4 \ A = C A L L ( 1 0 6 0 8 , 8 ) \ N E X T R 890 INPUT"",P$ 900 A=CALL (10608,11) 910 IF P$="M" THEN CHAIN "MENU" 920 IF P$=0$ THEN 1010 930 IF P$<>"E" THEN 960 94 0 A=CALL (10608 , 31 )\A=CALL (10608 , 29) \A=CALL (10608 , 31 )\A=CALL (10608 , 31) 950 A=CALL (10608, 29)\GOTO 740 960 IF P$>"3500"THEN 2820 970 IF P$<"0099"THEN 2820 n 980 IF P $ O 0 4 2 2 " T H E N 2820 \REM REMOVE WHEN MORE MAPS ARE ON FILE 990 GOTO 1440 \REM ****** LOAD MAP DATA BASE 1000 REM *************** INPUT WAYPT, ALT ***************** 1010 !"MAP#", T A B ( B l ) , " W A Y P T * " , T A B ( B 2 ) , " W A Y P T " , T A B ( B 3 ) , " A L T . X 1000 ft" 1020 ! P $ , T A B ( B 1 ) , A 9 , T A B ( B 2 ) , \ A = C A L L ( 1 0 6 0 8 , 2 9 ) \ I N P U T 1 E$ 1030 IF E$="M" THEN CHAIN "MENU" 1040 IF E$O"E"THEN 1070 1050 1\FOR R=l TO 3\A=CALL (10608 , 31 )\A=CALL (10608 , 29) \NEXT R 1060 GOTO 880 1070 D(0)=VAL(E$) 1080 FOR R=0 TO LEN (E$)\A=CALL (10608 , 8)\NEXT R\A=CALL (10608 ,11) 1090 GOSUB 1940 1100 IF A0999 THEN 1130 1110 A=0 1120 GOTO 1020 1130 !G$,\FOR R=l TO 10-LEN ( G $ ) \ ! " ",\NEXT R 1140 REM ************* INPUT ALTITUDE IN 1000 ' ******************* 1150 INPUT1 E$ 1160 IF E$="M" THEN CHAIN "MENU" 1170 IF E$O"E" THEN 1190 1180 !\A=CALL(10608,31)\GOTO 1020 1190 C ( A 9 ) = V A L ( E $ ) * 1 0 0 0 1200 GOSUB 2430 1210 A9=A9+1 1220 JP$,TAB(B1) , A 9 , T A B ( B 2 ) ,\A=CALL (10608,29)\INPUT1 E$ 1230 IF E$="M" THEN CHAIN "MENU" 1240 IF E$O"E" THEN 1290 1250 J\A=CALL (10608 , 31)\A=CALL (10608 , 29) \A=CALL (10608 , 31) 1260 FOR R=l TO B3\A=CALL (10608 , 28)\NEXT R\A=CALL (10608 , 29) 1270 A9=A9-1 1280 IF A9=0 THEN 1150 ELSE 1350 1290 D(A9)=VAL(E$) 1300 GOSUB 1940 1310 IF AO999 THEN 1330 1320 GOTO 1220 1330 FOR R=0 TO LEN (E$)\A=CALL (10608 , 8 )\NEXT R\A=CALL (10608 ,11) 1340 !G$,\FOR R=l 0 10-LEN (G $) \ ! " ",\NEXT R T 1350 INPUT1 E$ 1360 IF E$="M" THEN CHAIN "MENU" 1370 IF E$O"E" THEN 1400 1380 !\A=CALL(10608,31)\A=CALL(10608,29) 1390 GOTO 1220 1400 C ( A 9 ) = V A L ( E $ ) * 1 0 0 0 1410 IF C ( A 9 ) < C 2 THEN E=l 1420 GOTO 1200 1430 REM *************** LOAD MAP DATA BASE ********************** 1440 OPEN #0,P$ 1450 WRITE #2,G1,H1,D1,W1,T1,T2,P$ 1460 0$=P$ 1470 READ # 0 , M ( A 9 ) , P 1 , F 1 \ REM LOAD VOR DATA,MAGYAR 1480 DIM V(P1-1,F1) ,V$ (3) ,Z$(F1*3) 1490 FOR W=l TO Fl 1500 READ #0,V$ 1510 Z$=V$+Z$ 1520 FOR X=l TO Pl-1 1530 READ # 0 , V ( X , W ) 1540 NEXT X 1550 NEXT W 1560 READ # 0 , P 2 , F 2 \ REM LOAD INTERSECTION DATA 1570 DIM N ( P 2 - 1 , F 2 ) , N $ ( 5 ) , R $ ( F 2 * 5 ) 1580 FOR W=l TO F2 1590 READ # 0 , N $ 1600 R$=N$+R$ 1610 FOR X=l TO P2-1 1620 READ # 0 , N ( X , W ) 1630 NEXT X 1640 NEXT W 1650 READ # 0 , P 3 , F 3 \ REM LOAD AIRPORT DATA 1660 DIM A(P3-1,F3) , A $ ( 6 ) ,S$(F3*6) 1670 FOR W=l TO F3 1680 READ # 0 , A $ 1690 S$=A$+S$ 1700 FOR X=l TO P3-1 1710 READ # 0 , A ( X , W ) 1720 NEXT X 1730 NEXT W 1740 READ # 0 , P 4 , F 4 \ REM LOAD ILS DATA 1750 DIM I ( P 4 , F 4 ) , I $ ( 4 ) ,T$(F4*4) 1760 FOR W=l TO F4 1770 READ # 0 , 1 $ 1780 T$=I$+T$ 1790 FOR X=l TO P4-1 1800 READ # 0 , I ( X , W ) 1810 NEXT X 1820 NEXT W 1830 READ # 0 , P 5 , F 5 \ REM LOAD NDB DATA 1840 DIM B(P5-1,F5) , B $ ( 4 ) , U $ ( F 5 * 4 ) 1850 FOR W=l TO F5 1860 READ # 0 , B $ 1870 U$=B$+U$ 1880 FOR X=l TO P5-1 1890 READ # 0 , B ( X , W ) 1900 NEXT X 1910 NEXT W 1920 CLOSE #0\GOTO 1010 1930 REM ************** GET WAYPT MNEMONIC, LAT/LNG, MEA ************* 1940 IF D ( A 9 ) < 1 0 0 0 THEN 2340 \REM WAYPT IS A VOR 1950 IF D ( A 9 ) < 1 0 0 0 0 THEN 2050 \REM WAYPT IS NDB OR ILS 1960 IF D ( A 9 ) < 1 0 0 0 0 0 THEN 2250 \REM WAYPT IS AN INTRSECTION 1970 FOR W=0 TO F3-1 \REM WAYPT IS AN AIRPORT 1980 IF A ( 1 , W + 1 ) = D ( A 9 ) THEN 2010 1990 NEXT W 2000 GOTO 2750 2010 G$=S$ (6*(F3-W)-5,6*(F3-W) ) 2020 K ( A 9 ) = A ( 3 , W + 1 ) \REM ASSIGN LAT 2030 L ( A 9 ) = A ( 4 , W + 1 ) \REM ASSIGN LONG 2040 RETURN 2050 IF D(A9)<5000 THEN 2140 2060 FOR W=0 TO F5-1 \ REM WYPT IS NDB 2070 IF B(1,W+1)=D(A9)THEN 2100 2080 NEXT W 2090 GOTO 2750 2100 G$=U$(4*(F5-W)-3,4*(F5-W) ) 2110 K ( A 9 ) = B ( 3 , W + 1 ) \REM ASSIGN LAT 2120 L ( A 9 ) = B ( 4 , W + 1 ) \REM ASSIGN LONG 2130 RETURN 2140 IF D ( A 9 ) > 4 0 0 0 THEN 2170 2150 REM B IS A NDB 2160 GOTO 2060 2170 FOR W=0 TO F4-1 \REM WAYPT IS AN ILS 2180 IF I ( 1 , W + 1 ) = D ( A 9 ) THEN 2210 2190 NEXT W 2200 GOTO 2750 2210 G $ = T $ ( 4 * ( F 4 - W ) - 3 , 4 * ( F 4 - W ) ) 2220 K(A9)=I(3,W+1) \REM ASSIGN LAT 2230 L(A9)=I(4,W+1) \REM ASSIGN LONG 2240 RETURN 2250 FOR W=0 TO F2-1 \REM WAUPT IS AN INTERSECTION 2260 IF N(1,W+1)=D (A9) THEN 2290 2270 NEXT W 2280 GOTO 2750 2290 G$=R$(5*(F2-W)-4,5*(F2-W) ) 2300 L(A9)=N(4,W+1) \REM ASSIGN LNG 2310 K(A9)=N(3,W+1) \REM ASSIGN LAT 2320 C2=N (2,W-H)*100 2330 RETURN 2340 FOR W=0 TO Fl-1 \ REM WYPT IS VOR 2350 IF V(1,W+1)=D(A9) THEN 2380 2360 NEXT W 2370 GOTO 2750 2380 G $ = Z $ ( 3 * ( F 1 - W ) - 2 , 3 * ( F 1 - W ) ) 2390 K ( A 9 ) = V ( 3 , W + 1 ) \REM ASSIGN LAT 2400 L ( A 9 ) = V ( 4 , W + 1 ) \REM ASSIGN LONG 2410 RETURN 2420 REM *********** ALT MNEMONICS, ERROR MSGS **************** 2430 IF E=l THEN 2590 2440 ! \REM AND ALT 2450 A=CALL (10608, 29) 2460 A=CALL(10608,31) 2470 IF C ( A 9 ) = 2 5 2 0 0 0 THEN C$="CLB " ELSE 2490 2480 GOTO 2550 2490 IF C(A9)=337000 THEN C$="DES " ELSE 2510 2500 GOTO 2550 2510 IF C ( A 9 ) = 5 6 3 0 0 0 THEN C$="LND " ELSE 2530 2520 GOTO 2850 2530 ! P $ , T A B ( B 1 ) , A 9 , T A B ( B 2 ) , G $ , T A B ( B 3 ) , C ( A 9 ) , 2 5 4 0 GOTO 2560 2550 ! P $ , T A B ( B 1 ) , A 9 , T A B ( B 2 ) , G $ , T A B ( B 3 + 1 ) , C $ , 2560 A = C A L L ( 1 0 6 0 8 , 2 9 ) 2570 !

2580 RETURN 2590 REM THIS CAUSES FLASHING OF THE CORRECT 2600 REM MINIMUM ENROUTE ALTITUDE FOR 10 SECONDS 2610 C ( A 9 ) = C 2 2620 FOR R=0 TO LEN (E$) \A=CALL (10608 , 8 ) \NEXT R 2630 A = C A L L ( 1 0 6 0 8 , 2 9 ) 2640 C $ = S T R $ ( C 2 ) 2650 FOR R6=l TO 5 2660 FOR R=l TO 500\NEXT R 2670 A=CALL(10608,11) 2680 FOR R=l TO 50\NEXT R 2690 !C$, 2700 FOR R=l TO L E N ( C $ ) \ A = C A L L ( 1 0 6 0 8 , 8 ) \ N E X T R 2710 NEXT R6 2720 E=0 2730 !

2740 RETURN 2750 !

2760 !"*******ERROR WAYPT NOT ON FILE*******" 2770 A=CALL (10608 , 31 )\A=CALL (10608 , 31) 2780 A = C A L L ( 1 0 6 0 8 , 2 9 ) 2790 A=999 2800 RETURN 2810 GOTO 1090 2820 !"****** ERROR ILLEGAL MAP* ****** 2830 A=CALL (10608 , 31 )\A=CALL (10608 , 31)\A=CALL (10608 , 2) 2840 GOTO 880 2850 !P$,TAB(B1) , A 9 , T A B ( B 2 ) ,G$,TAB (B3-KL) ,C$, 2860 OUT 2,29 2870 !

2880 !"DESTINATION ", 2890 OUT 2,31 n 2900 i " 9 9 2910 A8=A9 2920 FOR R=l TO 1200 2930 NEXT 2940 A=CALL(10608, 25) 2950 A=CALL (10608,11) *********************** 2960 REM ************** BEGINNING OF CALCULATION 2970 !"DEPART FROM ETD INITIAL FUEL/GAL" 2980 A9=0 2990 GOSUB 1940 3000 ! G $ , T A B ( 2 8 ) , %#5F2, T2,TAB (47 ) ,%#4F1,G1 3010 I 3020 !"FROM TO COURSE DIST HDG ETER EGS ALT RESERVES" 3030 1" DDD NN.N DDD H.MM KTS FT. GAL HRS" 3040 P=3.14159265 \REM P= PI 3050 DIM K2(19) ,L2(19) 3060 REM **************** CHANGE LAT & LNG TO RADIANS & DECIMAL ********** 3070 FOR A9=0 TO A8 3080 IF K ( A 9 ) = 0 THEN 4130 3090 K 2 ( A 9 ) = I N T ( K (A9) ) + (K ( A 9 ) - I N T (K ( A 9 ) ) ) / . 6 \REM RADIAN LAT 3100 K 2 ( A 9 ) = K 2 (A9)*P/180 3110 L 2 ( A 9 ) = I N T ( L ( A 9 ) ) + ( L ( A 9 ) - I N T (L ( A 9 ) ) ) / . 6 \REM DECIMAL LNG 3120 NEXT A9 3130 A9=-l 3140 A9=A9+1 3150 IF A9=A8 THEN 4130 3160 REM ************ FIND COURSE FROM WAYPOINT A9 TO A9+1 ************ 3170 J 2 = L 2 ( A 9 ) - L 2 ( A 9 + 1 ) 3180 J 3 = P / 4 + K 2 ( A 9 + l ) / 2 3190 J 4 = P / 4 + K 2 ( A 9 ) / 2 3200 J5=LOG(SIN (J3)/COS ( J 3 ) ) - L O G (SIN (J4)/COS ( J 4 ) ) 3210 J 6 = A B S ( ( P * J 2 ) / ( 1 8 0 * J 5 ) ) 3220 J8=ATN (J6) 3230 J7=180*J8/P \REM GIVES TRUE HDG IN DEG 3240 J9=J7 \REM J9=TRUE COURSE 3250 J 7 = J 7 + M ( 0 ) \REM J7=MAG HDG 3260 REM ************ CORRECT COURSE ANGLE FOR EACH QUADRANT *********** 3270 IF K ( A 9 ) < K ( A 9 + 1 ) AND L ( A 9 ) > L ( A 9 + 1 ) THEN 3370 3280 IF K ( A 9 ) > K ( A 9 + 1 ) AND L ( A 9 ) < L ( A 9 + 1 ) THEN 3330 3290 IF K ( A 9 ) > K ( A 9 + 1 ) AND L ( A 9 ) > L ( A 9 + 1 ) THEN 3420 3300 REM ***** HDG NE 3310 IF J7<0 THEN J7=360+J7 3320 GOTO 3450 3330 REM ***** HDG SE 3340 J7=180-J7+2*M(0) 3350 J9=180-J9 3360 GOTO 3450 3370 REM ***** HDG NW 3380 J7=360-J7+2*M(0) 3390 IF J7>360 THEN J7=J7-360 3400 J9=360-J9 3410 GOTO 3450 3420 REM ***** HDG SW 3430 J7=J7+180 3440 J9=J9+180 3450 J 7 = I N T ( J 7 + . 5 ) 3460 REM *********** PRINT FROM & TO WAYPTS, MAG COURSE ************ 3470 !G$,TAB(8 ), \REM OUTPUT "FROM" WAYPT 3480 A9=A9+1 3490 D = D ( A 9 ) 3500 GOSUB 1940 \REM OUTPUT "TO" WAYPT AND 3510 A9=A9-1 3520 !G$,TAB(17) , %#3I, J7 T A B ( 2 0 ) , f 3530 REM *********** FIND DIST FROM WAYPT A9 TO A9+1 *************** 3540 IF J9=270 OR J9=90 THEN 3410 \REM IS TRUE COURSE E OR W?

3550 Y=K2(A9)*180/P \REM Y=DECIMAL LAT 3560 Y1=K2(A9+1)*180/P 3570 H3=60*(Y1-Y)/COS (FNR ( J 8 ) ) \REM DIST = H3 IF C O S ( J 8 ) < > 0 3580 GOTO 3600 3590 H3=60*(L2(A9+1)-L2(A9))*COS ( K 2 ( A 9 ) ) \REM DIST=H3 IF COS(J8)=0 3600 H3=ABS(H3) 3610 H3=INT(10*H3)/10 \REM ROUND DIST TO 1/10 3620 H9=H9+H3 \REM SUM DIST 3630 IF H9>1000 THEN 4340 3640 ! % # 6 F l , H 3 T A B ( 2 9 ) , f 3650 REM ********** SELECT CLB, CRUISE OR DESCEND ROUTINES ********* 3660 IF C ( A 9 ) < > 2 5 2 0 0 0 THEN 3770 3670 REM ********* INSERT CLIMB PERFORMANCE ALGORITHMS HERE ******** n 3680 C$="CLB 3690 T4=80 3700 GOSUB 3930 3710 G 2 = 2 2 3720 GOSUB 4050 3 7 3 0 ! % # 3 I , J 8 , T A B ( 3 6 ) , % | 4 F 2 , E 2 , T A B ( 4 2 ) , % # 3 I , T 3 , T A B ( 4 8 ) , C $ , T A B ( 5 4 ) , % # 4 F 1 , R 1 , 3740 ! T A B ( 6 0 ) , % # 5 F 2 , R 2 3750 WRITE # 2 , D ( A 9 ) ,D ( A 9 + 1 ) , J 7 , H 3 , J 8 , E 2 , T 3 , C ( A 9 ) , R 1 , R 2 , T4 3760 GOTO 3140 3770 IF C ( A 9 ) < > 3 3 7 0 0 0 AND C{A9+1)O563000 THEN 3840 3780 REM ********* INSERT DESCENT PERFORMANCE ALGRITHMS HERE ********** 3790 C$="DES" 3800 IF C(A9+1)=563000 THEN T4=100 ELSE T4=120 3810 GOSUB 3930 3820 GOSUB 4020 3830 GOTO 3730 3840 REM ****************** LEVEL FLIGHT *************************** 3850 GOSUB 3900 3860 GOSUB 4010 3870 ! % # 3 I , J 8 , T A B ( 3 6 ) , % # 4 F 2 , E 2 , T A B ( 4 2 ) , % # 3 I , T 3 , T A B ( 4 7 ) , % # 5 I , C ( A 9 ) , T A B ( 5 4 ) , 3880 ! % # 4 F 1 , R 1 , T A B ( 6 0 ) , % # 5 F 2 , R 2 3890 WRITE # 2 , D ( A 9 ) , D ( A 9 + 1 ) , J 7 , H 3 , J 8 E 2 T 3 , C ( A 9 ) , R l , R 2 , T4 f f 3900 REM ********* CRUISE PERFORMANCE ROUTINE ********************** 3910 T4=128+.00111*C(A9)+(T1-64.4)*1.1 \REM T3=TAS AT 2400RPM,30"MAP 3920 REM ********** CORRECT HDG & GS FOR WIND *********************** 3930 J8=J7+FNS (W1/T4) *180/P*SIN (FNR (D1-J7) ) 3940 T3=T4*COS (FNR (J8-J7))-W1*COS (FNR (D1-J7)) 3950 J 8 = I N T ( J 8 + . S ) 3960 E2=H3/T3 \REM E2 = ETER 3970 E3=E3+E2 \REM E3=ETT FOR TRIP 3980 E 2 = I N T ( E 2 ) + ( E 2 - I N T ( E 2 ) ) * . 6 \REM E2=HRS.MIN 3990 E 2 = I N T ( E 2 * 1 0 0 + . 5 ) / 1 0 0 4000 RETURN 4010 REM ************** FIND GPH, RESERVES ***************************** 4020 IF TK68 THEN K=.1545 \REM T1=CRUISE %BHP 4030 IF Tl>=68 THEN K = . 1 5 4 5 + ( . 0 0 4 5 * ( T l - 6 8 ) ) 4040 G2=K*T1 \REM G2=GPH 4050 R1=G1-(G2*E3) \REM R1=GAL REMAINING 4060 IF Rl<=0 THEN 4260 \REM CHECK FOR NO FUEL 4070 R2=R1/G2 4080 R 2 = I N T ( R 2 ) + (R2-INT ( R 2 ) ) *0 . 6 \REM HRS,MIN RESERVE 4090 R2=INT(100*R2)/100 4100 R1=INT(R1*10)/10 4110 T3=INT(T3) 4120 RETURN 4130 !

4140 CLOSE #2 4150 !"DESTINATION TDIST ETA FINAL RES/GAL RES/HRS" 4160 T 2 = I N T ( T 2 ) + (T2-INT ( T 2 ) ) / . 6 4170 H9=INT(10*H9)/10 \REM H9=TOTAL DIST IN MM.m 4180 E3=E3+T2 \REM E3=ETA, OR ETT+ETD 4190 E3=INT(E3) + (E3-INT (E3)) * .6 \REM E3=HRS.MIN 4200 E 3 = I N T ( E 3 * 1 0 0 ) / 1 0 0 \REM CORRECTION FOR E3 IN MIN ONLY 4210 !G$,TAB(21) , %#5F1, H9,TAB (28) , %#5F2, E3, TAB (48 ) ,%#4F1, Rl, 4220 ! T A B { 5 6 ) , % # 5 F 2 , R 2 4230 !\!\!"DO YOU WISH TO TRY ANOTHER R O U T E ? ( 1 = Y E S , 0 = N O ) : ", n n 4 2 4 0 INPUT , Z 9 \ I F Z9=0 THEN CHAIN "MENU" 4250 CHAIN "FLTPLNUP" 4260 !

4270 !

4280 i"********* ERROR INSUFFICIENT FUEL*********** " 4290 ! "RE-INPUT I N I T . F U E L : ", 4300 INPUT " " , G 9 4310 IF G9>G1 THEN 2940 4320 !"ILLEGAL ENTRY" 4330 GOTO 4290 4340 !

4350 !

4360 i"********* ERROR DIST EXCEEDS MAX RANGE **********" 4370 !"TRY A G A I N ! ! " 4380 CHAIN "FLTPLN" 5.5 FLIGHT PLAN UPDATE PROGRAM FIGURE 5.5-1 FLT PLN UP ... FLIGHT PLAN UPDATE FLOW CHART READ EXISTING FLTPLN

i FROM F.P. DATA

i } PRINT/ r \ /EDIT / / FLTPLN/ f i COMPUTE ALL DATA AS IN FLTPLN MILCO INTERNATIONAL. INC.

10 REM FLTPLNUP PROGRAM 20 REM PROGRAM FOR UPDATING FLIGHTPLAN 30 A=CALL ( 1 0 6 0 8 , 2 5 ) \ A = C A L L ( 1 0 5 0 8 , 1 1 ) 40 A9=0 50 B1=15\B2=33\B3=50 60 OPEN # 2 , " F P D A T A " 70 DIM D( 2 0 ) , C ( 2 0 ) , K ( 2 0 ) , L ( 20 ) , Y (1 9) , Yl (1 9) , H3 (20 ) 80 DIM F ( 2 0 , l l ) 90 READ # 2 , G 1 , H 1 , D 1 , W 1 , T 1 , T 2 , P $ 100 FOR R=0 TO 20 \REM LOAD O R I G I N A L FLIGHT PLAN 110 FOR R l = l TO 11 120 READ # 2 , F ( R , R 1 ) 130 NEXT Rl 140 IF T Y P ( 2 ) = 0 THEN 160 150 NEXT R 160 GOTO 2070 \REM *** GO LOAD MAP DATA BASE *** 170 REM************* THIS SECTION MAY NOT BE USED **************** 180 1 " I N I T F U E L : G G " , 190 A = C A L L ( 1 0 6 0 8 , 2 9 ) 200 FOR R=l TO 2\A=CALL (10608 , 8 ) \ N E X T R 210 I N P U T 1 "" ,E$ 220 IF E$="M" THEN CHAIN " M E N U " 230 IF E $ O " E " THEN 250 240 ! \ A = C A L L ( 1 0 6 0 8 , 3 1 ) \ G O T O 180 250 G 1 = V A L ( E $ ) 260 !" g a l " , T A B ( 3 0 ) , 270 !"TEMP 'C AT AIRPORT: CC", 280 FOR R=l TO 2\A=CALL (10608 , 8 )\NEXT R 290 I N P U T 1 " " , E $ 300 A=CALL ( 1 0 6 0 8 , 2 9 ) 310 IF E$="M" THEN CHAIN "MENU" 320 IF E$O"E" THEN 340 330 !\A=CALL(10608,31)\GOTO 180 340 H1=VAL(E$) 350 !"'" 360 !"WIND: DEC KTS", 370 FOR R=l TO 9\A=CALL ( 1 0 6 0 8 , 8 ) \ N E X T R 380 I N P U T 1 " " , E $ 390 IF E$="M"THEN CHAIN "MENU" 400 IF E$0"E" THEN 440 410 1\A=CALL (10608 , 31 )\A=CALL (10608 , 2 9 ) \ A = C A L L (10608,31) 420 FOR R=l TO 28\A=CALL (10608 , 28) \NEXT R 430 GOTO 270 440 D1=VAL(E$)-180 450 IF DKO THEN D1=VAL (E$ )+180 460 !"'", 470 FOR R = ( 5 - L E N ( E $ ) ) TO 1 STEP -1 480 !" ", 490 NEXT R n n 5 0 0 INPUT1 , E $ 510 A = C A L L ( 1 0 6 0 8 , 2 9 ) 520 IF E$="M" THEN CHAIN " M E N U " 530 IF E$0"E"THEN 560 540 !\A=CALL (10608 ,31) 550 GOTO 360 560 W 1 = V A L ( E $ ) 570 !" kts", 580 FOR R=l TO 12-LEN ( E $ ) \ ! " " ,\NEXT R 590 !"CRUISE % BHP: PP ", 6 0 0 A = C A L L ( 1 0 6 0 8 , 8 ) 610 A=CALL (10608,8) 620 A=CALL (10608, 8) n 630 I N P U T l " , E $ 640 A=CALL ( 1 0 6 0 8 , 2 9 ) 650 IF E$="M" THEN CHAIN " M E N U " 660 IF E $ O " E " THEN 720 670 ! \ A=CALL (10608,31) 680 FOR R=l TO 12\A=CALL (10608 , 28)\NEXT R 690 !"KTS",\A=CALL(10608,29) 700 FOR R=l TO 3\A=CALL (10608 , 8 ) \NEXT R 710 GOTO 500 720 T1=VAL(E$) 730 !"%" 740 !"ETD: HH.MM", 750 FOR R=l TO 5\A=CALL (10608 , 8 ) \NEXT R 760 I N P U T 1 " " , E $ 770 IF E$="M"THEN CHAIN "MENU" 780 IF E$O"E" THEN 820 790 !\A=CALL (10608 , 31) \A=CALL (10608 , 29) \A=CALL (10608 , 31) 800 FOR R=l TO 28\A=CALL (10608 , 28 ) \NEXT R 810 GOTO 590 820 T 2 = V A L ( E $ ) 830 1" hrs" 840 1 850 A9=0 860 B1=10\B2=20\B3=30 870 !" I N I T I A L MAP #: NNNN" ,\FOR R=l TO 4\A=CALL (10608 , 8 ) \NEXT R 880 I N P U T " " , P $ 890 A=CALL(10608,11) 900 IF P$="M" THEN CHAIN "MENU" 910 IF P$=0$ THEN 1000 920 IF P$O"E" THEN 950 930 A=CALL (10608, 31 )\A=CALL (10608, 29 )\A=CALL (10608, 31 )\A=CALL (10608, 31) 940 A=CALL ( 1 0 6 0 8 , 2 9 ) \ G O T O 740 950 IF P$>"3500"THEN 3430 960 IF P$<"0099"THEN 3430 970 IF P $ 0 " 0 4 2 2 " T H E N 3430 \REM REMOVE WHEN MORE MAPS ARE ON FILE 980 GOTO 2070 990 REM ****************** END OF MAY NOT BE USED SECTION *********** 1000 PRINT "EXISTING FLIGHT PLAN UPDATED FLIGHT PLAN" 1010 PRINT "WAYPOINT ALT. WAYPOINT A L T . " 1020 PRINT 1030 REM ****************** PRINT OUT OLD WAYPOINTS ****************** 1040 FOR Rl=0 TO R 1050 D ( A 9 ) = F ( R 1 , 1 ) \REM GET MNEMONIC 1060 GOSUB 2560 1070 IF Rl=0 THEN G1$=G$ \REM SAVE WAYPOINT 0 MNEMONIC 1080 ! G $ , T A B ( B 1 ) , 1090 IF F(R1,8)0252000 THEN 1120 1100 !" CLB" 1110 GOTO 1190 1120 IF F ( R 1 , 8 ) 0 3 3 7 0 0 0 THEN 1150 1130 !" DES" 1140 GOTO 1190 1150 IF F(R1,8)0563000 THEN 1180 1160 !" LND" 1170 GOTO 1190 1180 ! F ( R 1 , 8 ) 1190 N E X T Rl 1200 FOR Rl=0 TO R 1210 A=CALL (10608, 31) \REM REPOSITION CURSOR UP NEXT Rl 1230 FOR Rl=l TO B2 1240 A=CALL (10608, 28) \REM MOVE CURSOR OUT 1250 NEXT Rl INPUT NEW WAYPOINTS ********************** \REM PRINT AIRPORT N A M E , WILL NOT CHANGE 1270 !G1$, 1280 FOR R1=LEN ( G l $ ) TO A=CALL (10608, 28) \REM MOVE CURSOR OUT NEXT Rl 1310 \REM WILL ALWAYS CLB OUT FROM AIRPORT!

i" CLB" FOR R l = l TO B2 1330 A=CALL (10608, 28) \REM MOVE CURSOR OUT NEXT R l 1350 R=l 1360 A9=l 1370 A = C A L L ( 1 0 6 0 8 , 8 ) \REM BS 1380 INPUT WAYPOINT REM * * * * * * * * * * * 1390 INPUT1 E$ IF E$="M" THEN CHAIN " M E N U " 1410 IF E$0"E" THEN 1590 1420 IF A 9 O O THEN 1480 1430 A = C A L L ( 1 0 6 0 8 , 7 ) \REM B U Z Z A = C A L L ( 1 0 6 0 8 , 8 ) \REM BS 1450 A = C A L L ( 1 0 6 0 8 , 8 ) \REM BS A=CALL (10608, 29) \REM ERASE 1470 GOTO 1380 1480 REM ***** RE-POSITION R E - I N P U T LAST ALT ***** CURSOR TO 1490 A = C A L L ( 1 0 6 0 8 , 8 ) \REM BS 1500 A=CALL ( 1 0 6 0 8 , 8 ) \REM BS A = C A L L ( 1 0 6 0 8 , 2 9 ) \REM ERASE 1520 FOR Rl=l TO 17 A=CALL ( 1 0 6 0 8 , 2 8 ) \REM SPACE OUT 1540 NEXT Rl 1550 A=CALL (10608, 31) UP SPACE \REM 1560 A=CALL (10608, 29) \REM ERASE OLD ALT 1570 A9=A9-1 1580 GOTO 1850 \REM RE-INPUT OLD ALT 1590 IF E $ < > " " THEN 1700 1600 D ( A 9 ) = F ( R , 1 ) \REM NO WAYPOINT CHANGE 1610 A = C A L L ( 1 0 6 0 8 , 8 ) 1620 GOSUB 2560 \REM GET WAYPOINT MNEMONIC 1640 FOR R 1 = L E N ( G $ ) TO 17 1650 A=CALL ( 1 0 6 0 8 , 2 8 ) \REM SPACE OUT 1660 NEXT R*l 1670 ! F ( R , 8 ) 1680 R=R+1 1690 GOTO 2010 \ R E M REPOSITION CURSOR 1700 IF E $ ( l , l ) = "/" THEN 1730 1710 R=R+1 1720 GOTO 1750 1730 E$=E$ ( 2 , L E N ( E $ ) ) 1740 A = C A L L ( 1 0 6 0 8 , 8 ) 1750 D ( A 9 ) = V A L ( E $ ) 1760 GOSUB 2560 \REM GET WAYPOINT MNEMONIC FOR R 1 = L E N ( E $ ) TO 0 STEP -1 A=CALL ( 1 0 6 0 8 , 8 ) NEXT Rl 1800 A=CALL (10608, 29) 1810 !" ",G$, 1820 FOR Rl = L E N ( G $ ) TO 17 1830 A=CALL(10608,28) 1840 NEXT Rl 1850 REM ***** INPUT ALTITUDE ***** 1860 INPUTl E$ 1870 IF E$="M" THEN CHAIN " M E N U " 1880 IF E$O"E" THEN 1940 1890 FOR Rl=17 TO 1 STEP -1 1900 A = C A L L ( 1 0 6 0 8 , 8 ) 1910 NEXT Rl 1920 A = C A L L ( 1 0 6 0 8 , 2 9 ) 1930 GOTO 1380 \REM CHANGE LAST WAYPOINT 1940 C ( A 9 ) = V A L ( E $ ) * 1 0 0 0 1950 IF C ( A 9 ) < C 2 THEN ERROR \REM CHECK FOR ALT<MEA 1960 IF C ( A 9 ) = 5 6 3 0 0 0 THEN COMPUTE FLIGHTPLAN 1970 FOR R l = L E N ( E $ ) TO 0 STEP -1 1980 A=CALL ( 1 0 6 0 8 , 8 ) \REM BS 1990 NEXT Rl 2000 ! C ( A 9 ) 2010 REM ***** REPOSITION CURSOR, GET READY FOR NEXT WP ************* 2020 A9=A9+1 2030 FOR Rl=l TO B2 2 0 4 0 A=CALL (10608, 28) 2050 NEXT Rl 2060 GOTO 1370 \REM GO GET NEXT WAYPOINT 2070 REM ******************** LOAD MAP DATA BASE ******************* 2080 OPEN # 0 , P $ 2090 0$=P$ 2100 READ # 0 , M ( A 9 ) , P 1 , F 1 \ REM LOAD VOR DATA,MAGYAR 2110 DIM V(P1-1,F1) , V $ ( 3 ) ,2$ (Fl*3) 2120 FOR W=l TO Fl 2130 READ # 0 , V $ 2140 Z$=V$+Z$ 2150 FOR X=l TO Pl-1 2160 READ # 0 , V ( X , W ) 2170 NEXT X 2180 NEXT W 2190 READ # 0 , P 2 , F 2 \ REM LOAD INTERSECTION DATA 2200 DIM N ( P 2 - 1 , F 2 ) ,N$ (5) , R $ ( F 2 * 5 ) 2210 FOR W=l TO F2 2220 READ # 0 , N $ 2230 R$=N$+R$ 2240 FOR X=l TO P2-1 2250 READ #0,N(X,W) 2260 NEXT X 2270 NEXT W 2280 READ # 0 , P 3 , F 3 \ REM LOAD AIRPORT DATA 2290 DIM A ( P 3 - 1 , F 3 ) ,A$ (6) ,S$ (F3*6) 2300 FOR W=l TO F3 2310 READ #0,A$ 2320 S$=A$+S$ 2330 FOR X=l TO P3-1 2340 READ # 0 , A ( X , W ) 2350 NEXT X 2360 NEXT W 2370 READ # 0 , P 4 , F 4 \ REM LOAD ILS DATA 2380 DIM I ( P 4 , F 4 ) ,1$ (4) ,T$ ( F 4 * 4 ) 2390 FOR W=l TO F4 2400 READ #0,1$ 2410 T$=I$+T$ 2420 FOR X=l TO P4-1 2430 READ #0,1 (X,W) 2 4 4 0 NEXT X 2450 NEXT W 2460 READ #0,P5,F5 \ REM LOAD NDB DATA 2470 DIM B(P5-1,F5) , B $ { 4 ) , U $ ( F 5 * 4 ) 2480 FOR W=l TO F5 2490 READ # 0 , B $ 2500 U$=B$+U$ 2510 FOR X=l TO P5-1 2520 READ # 0 , B ( X , W ) 2530 NEXT X 2540 NEXT W 2550 CLOSE #0\GOTO 1000 2560 IF D(A9)<1000 THEN 2960 \REM WAYPT IS A VOR 2570 IF D ( A 9 ) < 1 0 0 0 0 THEN 2670 \REM WAYPT IS NDB OR ILS 2580 IF D ( A 9 ) < 1 0 0 0 0 0 THEN 2870 \REM WAYPT IS AN INTRSECTION 2590 FOR W=0 TO F3-1 \REM WAYPT IS AN AIRPORT 2600 IF A ( 1 , W + 1 ) = D ( A 9 ) THEN 2630 2610 NEXT W 2620 GOTO 3360 2630 G$=S$ (6*(F3-W)-5 6*(F3-W) ) f 2640 K ( A 9 ) = A ( 3 , W + 1 ) \REM ASSIGN LAT 2650 L ( A 9 ) = A ( 4 , W + 1 ) \REM ASSIGN LONG 2660 RETURN 2670 IF D ( A 9 ) < 5 0 0 0 THEN 2760 2680 FOR W=0 TO F5-1 \ REM WYPT IS NDB 2690 IF B ( 1 , W + 1 ) = D ( A 9 J T H E N 2720 2700 NEXT W 2710 GOTO 3360 2720 G $ = U $ ( 4 * ( F 5 - W ) - 3 , 4 * ( F 5 - W ) ) 2730 K(A9)=B(3,W+1) \REM ASSIGN LAT 2740 L(A9)=B(4,W+1) \REM ASSIGN LONG 2750 RETURN 2760 IF D ( A 9 ) > 4 0 0 0 THEN 2790 2770 REM B IS A NDB 2780 GOTO 2680 2790 FOR W=0 TO F4-1 \REM WAYPT IS AN ILS 2800 IF I(1,W+1)=D(A9) THEN 2830 2810 NEXT W 2820 GOTO 3360 2830 G$=T$ ( 4 * ( F 4 - W ) - 3 , 4 * ( F 4 - W ) ) 2840 K (A9) = I (3,W+1) \REM ASSIGN LAT 2850 L ( A 9 ) = I ( 4 , W + 1 ) \REM ASSIGN LONG 2860 RETURN 2870 FOR W=0 TO F2-1 \REM WAUPT IS AN INTERSECTION 2880 IF N(1,W-H)=D (A9) THEN 2910 2890 NEXT W 2900 GOTO 3360 2910 G$=R$ (5*(F2-W)-4,5*(F2-W)) 2920 L (A9)=N (4,W+1) \REM ASSIGN LNG 2930 K ( A 9 ) = N ( 3 , W + 1 ) \REM ASSIGN LAT 2940 C2=N (2,W+1)*100 2950 RETURN 2960 FOR W=0 TO Fl-1 \ REM WYPT IS VOR 2970 IF V ( 1 , W + 1 ) = D ( A 9 ) THEN 3000 2980 NEXT W 2990 GOTO 3360 3000 G $ = Z $ ( 3 * ( F l - W ) - 2 , 3*(F1-W) ) 3010 K(A9)=V(3 W+l) \REM ASSIGN LAT f 3020 L (A9)=V(4,W+1) \REM ASSIGN LONG 3030 RETURN 3040 IF E=l THEN 3200

3050 ! \REM AND ALT

3060 A=CALL (10608, 29) 3070 A=CALL(10608,31) 3080 IF C ( A 9 ) = 2 5 2 0 0 0 THEN C$="CLB " ELSE 3100 3090 GOTO 3160 3100 IF C ( A 9 ) = 3 3 7 0 0 0 THEN C$="DES " ELSE 3120 3110 GOTO 3160 3120 IF C ( A 9 ) = 5 6 3 0 0 0 THEN C$="LND " ELSE 3140 3130 GOTO 3460 3140 IP$,TAB(B1),A9,TAB(B2),G$,TAB(B3),C(A9), 3150 GOTO 3170 3160 ! P $ , T A B ( B 1 ) , A 9 , T A B ( B 2 ) , G $ , T A B ( B 3 + 1 ) , C $ , 3170 A=CALL ( 1 0 6 0 8 , 2 9 ) 3180 !

3190 RETURN 3200 REM THIS CAUSES FLASHING OF THE CORRECT 3210 REM M I N I M U M ENROUTE ALTITUDE FOR 10 SECONDS 3220 C ( A 9 ) = C 2 3230 FOR R=0 TO LEN (E$)\A=CALL (10608,8)\NEXT R 3240 A=CALL (10608, 29) 3250 C $ = S T R $ ( C 2 ) 3260 FOR R6=l TO 5 3270 FOR R=l TO 500\NEXT R 3280 A=CALL(10608,11) 3290 FOR R=l TO 50\NEXT R 3300 !C$, 3310 FOR R=l TO L E N ( C $ ) \ A = C A L L ( 1 0 6 0 8 , 8 ) \ N E X T R 3320 NEXT R6 3330 E=0 3340 !

3350 RETURN 3360 !

3370 !"*******ERROR WAYPT NOT ON FILE*******" 3380 A=CALL (10608 , 31 )\A=CALL (10608 , 31) 3390 A=CALL (10608, 29) 3400 A=999 3410 RETURN 3420 GOTO 1150 3430 !"****** ERROR ILLEGAL MAP# *****" 3440 A=CALL (10608, 31 )\A=CALL (10608, 31 )\A=CALL (10608, 2) 3450 GOTO 870 3 4 6 0 ! P $ , T A B ( B 1 ) , A 9 , T A B ( B 2 ) , G $ , T A B ( B 3 + 1 ) , C $ , 3470 OUT 2 , 2 9 3480 !

3490 !"DESTINATION ", 3500 OUT 2,31 3510 !"99" 3520 A8=A9-1 3530 OUT 2,13 3540 GOTO 4180 3550 END 3560 !"DEPART FROM ETD INITIAL FUEL/GAL" 3570 A9=0 3580 GOSUB 2560 3590 ! G $ , T A B ( 2 8 ) , %#5F2, T2, TAB (47 ) , % # 4 F 1 , G 1 3600 !

RESERVES" 3610 !"FROM TO COURSE DIST HDG ETER EGS ALT GAL HRS" !" ODD N N . N ODD H . M M KTS FT.

3630 P=3.14159265 \REM P= PI 3640 D I M K 2 ( 1 9 ) , L 2 ( 1 9 ) A9=-l 3660 FOR R=l TO 2 3670 A9=A9+1 IF K ( A 9 ) = 0 THEN 4690 \REM RADIAN LAT K 2 ( A 9 ) = I N T ( K ( A 9 ) ) + ( K ( A 9 ) - I N T ( K ( A 9 ) ) K 2 ( A 9 ) = K 2 ( A 9 ) * P / 1 8 0 \REM RADIAN LNG 3710 L 2 ( A 9 ) = I N T ( L ( A 9 ) ) + ( L ( A 9 ) - I N T ( L ( A 9 ) ) NEXT R 3730 THIS IS THE HP-65 RHUMBF A9=A9-1 \REM 3740 ROUTINE MODIFIED FOR RADIAN TRIG J 2 = L 2 ( A 9 ) - L 2 ( A 9 + 1 ) \REM J 3 = P / 4 + K 2 ( A 9 + l ) / 2 j 4 = P / 4 + K 2 ( A 9 ) / 2 3770 J 5 = L O G ( S I N (J3)/COS (J3 ) ) - L O G (SIN (J 4 )/COS (J 4 ) ) J 6 = A B S ( ( P * J 2 ) / ( 1 8 0 * J 5 ) ) 3790 J 9 = ( J 6 - 1 ) / ( J 6 + 1 ) 3800 J8=ATN ( J 6 ) 3810 \REM GIVES TRUE HDG IN DEC J7=180*J8/P IF K ( A 9 ) > K (A9+1) THEN 3840 3830 ELSE 3900 \REM COURSE<90 IF L ( A 9 ) > L ( A 9 + 1 ) THEN 3870 3840 IF L ( A 9 ) > L ( A 9 + 1 ) THEN 3890 3850 \REM 180>COURSE>90 J7=180-J7 3860 GOTO 3900 3870 \REM 360>COURSE>270 J7=360-J7 3880 GOTO 3900 3890 J7=J7+180 REM MAG COURSE=J7+MAG VAR 3910 J 9 = J 7 \REM J9=TRUE COURSE 3920 J 7 = J 7 + M ( 0 ) 3930 IF H 2 > . 5 THEN 3960 \REM ROUND OFF MAG HDG 3940 J 7 = I N T ( J 7 ) 3950 GOTO 3970 3960 J 7 = 1 + I N T ( J 7 ) 3970 ! G $ , T A B ( 8 ) , \REM OUTPUT "FROM" WAYPT 3980 A9=A9+1 D = D ( A 9 ) 4000 GOSUB 2560 \REM OUTPUT "TO" WAYPT AND ! G $ , T A B ( 1 7 ) , % # 3 I , J 7 , T A B ( 2 0 ) , 4020 IF J 7 - M ( 0 ) = 2 7 0 THEN 4070 \REM IS TRUE COURSE E OR W?

4030 Y ( A 9 ) = K 2 ( A 9 ) * 1 8 0 / P \REM Y ( A 9 ) = D E C I M A L LAT Y (A9-1)=K2(A9-1)*180/P 4050 H 3 = 6 0 * ( Y ( A 9 ) - Y (A9-1))/COS (J8) \REM DIST = H3 IF C O S ( J 8 ) < > 0 4060 GOTO 4100 Y l ( A 9 ) = L 2 ( A 9 ) * 1 8 0 / P \REM Y l ( A 9 ) = D E C I M A L LNG 4080 Yl ( A 9 - 1 ) = L 2 ( A 9 - 1 ) *180/P 4090 H 3 = 6 0 * ( Y 1 ( A 9 ) - Y 1 ( A 9 - 1 ) ) * C O S ( K 2 ( A 9 ) ) \REM DIST=H3 IF C O S ( J 8 ) = 0 4100 H 3 ( A 9 - 1 ) = H 3 4110 H3=ABS (H3) H3=INT(10*H3)/10 \REM ROUND DIST TO 1/10 4130 H9=H9+H3 \REM SUM DIST 4140 IF H9>1000 THEN 4960 4150 ! % t 6 F l , H 3 , T A B ( 2 9 ) , 4160 GOTO 4230 !"ARRRGH! I Q U I T ! ! ! " 4180 FOR R=l TO 900 4190 NEXT R 4200 OUT 2 , 2 5 4210 OUT 2,11 4220 GOTO 3560 4230 A9=A9-1 4 2 4 0 IF C ( A 9 ) = 2 5 2 0 0 0 THEN C$="CLB " ELSE 4310 4250 T3=100 4260 GOSUB 4460 4 2 7 0 ! % f 3 I , J 7 , T A B ( 3 6 ) , % # 4 F 2 , E2, TAB (42 ) , %#3I , T 3 , T A B ( 4 8 ) , C $ , T A B ( 5 4 ) , % # 4 F 1 , R 1 , 4280 ! T A B ( 6 0 ) , % # 5 F 2 , R 2 4290 WRITE # 2 , D ( A 9 ) , D ( A 9 + 1 ) , J 7 , H 3 , J 7 , E 2 , T 3 , C ( A 9 ) , R 1 , R 2 4300 GOTO 4680 4310 IF C ( A 9 ) = 3 3 7 0 0 0 THEN C$="DES " ELSE 4370 4320 IF C ( A 9 + 1 ) = 5 6 3 0 0 0 THEN T3=100 ELSE 4350 4330 GOSUB 4410 4 3 4 0 GOTO 4 2 7 0 4350 GOSUB 4410 4360 GOT04270 4370 IF C ( A 9 + 1 } = 5 6 3 0 0 0 THEN T3=100 4380 GOSUB 4 4 0 0 4390 GOTO 4 6 4 0 4 4 0 0 T3=128+.00111*C(A9)+ ( T l - 6 4 . 4 ) * ! . 1 \REM T3=TAS AT 2 4 0 0 R P M , 30 "MAP 4410 R6=W1/T3 4 4 2 0 R 6 = l . 5707288-.2121144*R6+.074261*R6~2-.0187293*R6~3 4 4 3 0 J7=J7+(P/2-SQRT (1-W1/T3) *R6) *SIN ((D1-J9)/180*P ) 4 4 4 0 T3=T3*COS ((J9-J7-M (0 ) ) / I 80 *P )-Wl*COS ((D1-J9)/180*P ) 4450 J 7 = I N T (J7) 4 4 6 0 E2=H3/T3 \REM E2 = ETER 4 4 7 0 E 3 = E 3 + E 2 \REM E3=ETT FOR TRIP 4480 E 2 = I N T ( E 2 ) + (E2-INT ( E 2 ) ) * . 6 \REM E2=HRS.MIN 4490 IF E 2 - I N T ( E 2 * 1 0 0 ) / 1 0 0 > = . 0 0 5 THEN 4520 4500 E 2 = I N T (E2*100)/100 4510 GOTO 4530 4520 E2=INT{E2*100)/100+.01 4530 IF TK68 THEN K=.1545 4540 IF Tl>=68 THEN K = . 1 5 4 5 + ( . 0 0 4 5 * ( T l - 6 8 ) ) 4550 G2=K*T1 \REM G2=GPH 4560 R 1 = G 1 - ( G 2 * E 3 ) \REM R1=GAL REMAINING 4570 IF R l < = 0 THEN 4840 \REM CHECK FOR NO FUEL 4580 R2=R1/G2 4590 R 2 = I N T ( R 2 ) + (R2-INT ( R 2 ) ) *0 . 6 \REM HRS,MIN RESERVE 4600 R2=INT(100*R2)/100 4610 R1=INT(R1*10)/10 4620 T3=INT(T3) 4630 RETURN 4 6 4 0 ! % # 3 I , J 7 , T A B ( 3 6 ) , % # 4 F 2 , E2, TAB (42 ) ,%f 31 , T 3 , T A B ( 4 7 ) ,%|5I C ( A 9 ) , T A B ( 5 4 ) , f 4650 ! % # 4 F 1 , R 1 , 4660 ! T A B ( 6 0 ) , % # 5 F 2 , R 2 4670 WRITE # 2 , D ( A 9 ) , D ( A 9 + 1 ) , J 7 , H 3 , J 7 , E 2 , T 3 , C ( A 9 ) , R 1 , R 2 4680 GOTO 3660 4690 !

4700 CLOSE #2 4710 ! "DESTINATION TDIST ETA FINAL RES/GAL RES/HRS" 4720 T 2 = I N T ( T 2 ) + (T2-INT ( T 2 ) ) / . 6 4730 H9=INT(10*H9)/10 \REM H9=TOTAL DIST IN MM.m 4 7 4 0 E3=E3+T2 \REM E3=ETA, OR ETT+ETD 4750 E 3 = I N T ( E 3 ) + (E3-INT ( E 3 ) ) * . 6 \REM E 3 = H R S . M I N 4760 E3=INT(E3*100)/100 \REM CORRECTION FOR E3 IN MIN ONLY 4770 ! G $ , T A B ( 2 1 ) , %#5F1, H9, TAB (28 ) , % # 5 F 2 , E3, TAB (48 ) , % # 4 F 1 , R 1 , 4780 ! T A B ( 5 6 ) , % # 5 F 2 , R 2 4790 WRITE # 2 , 0 , 0 , 0 , 0 , 0 , 0 , 0 , 0 , 0 , 0 4800 CLOSE #2 4810/!\!\!"DO YOU WISH TO TRY ANOTHER ROUTE? (1=YES, 0 = N O ) : " , 4820 INPUT " " , Z 9 \ I F Z9=0 THEN CHAIN "MENU" 4830 A=CALL (10608, 25 )\A=CALL (10608,11 )\GOTO 180 4 8 4 0 !

4850 !

4860 I"********* ERROR INSUFFICIENT FUEL*********** " 4870 ""RE-INPUT I N I T . F U E L : ", n 4880 INPUT " , G 9 4890 IF G9>G1 THEN 4180 4900 .'"ILLEGAL ENTRY" 4910 OUT 2,31 4920 OUT 2,31 4930 OUT 2,31 4940 OUT 2 , 2 9 4950 GOTO 4870 4960 I 4970 !

4980 i"********* ERROR DIST EXCEEDS MAX RANGE **********" 4990 FOR R=l TO 600 5000 NEXT R 5010 OUT 2 , 2 5 5020 OUT 2,11 5030 GOTO 760 5040 END 5050 ! TAB ( 2 9 ) , E2,TAB ( 3 5 ) , T 3 , T A B ( 4 1 ) ,C( A9) *100 , TAB (47 ) , R 1 , T A B ( 5 6 ) ,R2 5 0 6 0 ! % # 4 F 2 , E 2 , T A B ( 3 5 ) , %|6F2, T3, TAB (42 ) , % | 5 I , C ( A 9 ) * 1 0 0 , T A B ( 5 0 ) , % # 4 F 1 , R 1 5.6 AIRCRAFT PERFORMANCE PROGRAMS FIGURE 5.6-1 AIRCRAFT PERFORMANCE PROGRAM HIERARCHY FLOW DIAGRAM MENU CLB PRF LND PRF CRS PRF EACH MODULE IS FULLY SELF DOCUMENTED, EXHIBITING STRAIGHT THRU PROGRAMMING. FLOW CHARTS FOR ALL ARE SIMILAR: /INPUT DATA/ COMPUTE / PRINT ~7 MILCO INTERNATIONAL. INC.

WBS# 3056 10 REM CLBPRF 6/1/78 20 A=CALL (10608, 25 )\A=CALL (10608,11) 30 PRINT "CLIMB PERFORMANCE M E N U " 40 PRINT " " 50 PRINT 60 PRINT"RATE OF CLIMB AT SELECTED ALT 1" 70 PRINT"TIME/DISTANCE TO CLIMB 2" 8 0 PR INT" FUE L TO C LIMB 3 " 90 INPUT X$\IF X$="M" THEN CHAIN "MENU" ELSE X=VAL(X$) 100 IF X=l THEN GOTO 130 110 IF X=2 THEN GOTO 450 120 IF X=3 THEN GOTO 870 130 A=CALL(10608,25)\A=CALL (10608,11) 140 PRINT "RATE OF CLIMB AT SELECTED ALT" 150 PRINT " " 160 PRINT"ASSUME: FULL THROTTLE, FLAPS U P , M I X LEANED AT 3000 FT" 170 PRINT\PRINT 180 PRINT "ENTER DATA:" 190 PRINT 200 INPUT"ALTITUDE, FT ",A1 210 PRINT 220 INPUT"OAT AT ALT, DEC C ",0 230 PRINT 240 INPUT "AIRCRAFT WEIGHT, LBS ",W 250 PRINT 260 V1=2319-.731667*W 270 V2=-.078533+.00001617*W 280 V3=0-15+.002*A1 290 R=V1+V2*A1+V3*1.8 300 R=INT (R) 310 PRINT "RATE OF CLIMB AT ",A1," FT = " , R , " FT PER M I N " 320 PRINT\PRINT\PRINT 330 PRINT "CHOOSE FUNCTION: ENTER:" 340 PRINT 350 PRINT"RETURN TO CLIMB PERFORMANCE MENU 1" 360 PRINT "RETURN TO AIRCRAFT PERFORMANCE MENU 2" 370 PR INT" COMPUTE ANOTHER ROC CASE 3" 380 P R I N T " R E T U R N TO MASTER MENU 4" 390 INPUT X\PRINT\PRINT 400 IF X=l THEN GOTO 20 410 IF X=2 THEN CHAIN "TOPRF" 420 IF X=3 THEN GOTO 130 430 IF X=4 THEN CHAIN "MASTER" 440 GOTO 330 450 PRINT 460 PRINT"TIME/DISTANCE TO CLIMB TO ALTITUDE" 470 PRINT " " 480 PRINT 490 PRINT "INPUT DATA:"\!\!

500 INPUT " I N I T I A L ALT, FT ",A1 510 PRINT 520 INPUT "FINAL ALT, FT " ,A2 530 PRINT 540 INPUT "OAT, DEC C ",01 550 PRINT 560 INPUT "AIRCRAFT WEIGHT, LBS ",W 570 V1=2319-.731667*W 580 V2=-.078533+.00001617*W 590 V3=01-15+.002*A1 600 02=01-.002*A2+.002*A1 610 V4=02-15+.002*A2 620 R1=V1+V2*A1-V3*1.8 630 R2=V1+V2*A2-V4*1.8 R3=R1+R2 650 R4=R3/2 660 T1=A2-A1 670 T=T1/R4 680 T2=T/60 690 V5=47.417+.01375*W D=T2*V5 710 T=INT (T)\D=INT (D) 720 PRINT FROM ",A1," FT TO ",A2,"FT = ",T," MIN" 730 PRINT "TIME TO CLIMB 740 PRINT 750 ,D," N. MI." PRINT"DISTANCE TO CLIMB = 760 PRINT\PRINT ENTER:" 770 PRINT "CHOOSE FUNCTION: 780 PRINT 790 PRINT"RETURN TO AIRCRAFT PERFORMANCE MENU 1" 800 P R I N T " R E T U R N TO CLIMB PERFORMANCE MENU 2" PRINT" RETURN TO MASTER MENU 3" 820 INPUT X\PRINT\PRINT 830 IF X=l THEN CHAIN "TOPRF" 840 IF X=2 THEN GOTO 20 850 IF X=3 THEN CHAIN "MASTER" 860 GOTO 770 870 PRINT PRINT "FUEL TO C L I M B " 890 PRINT " " PRINT\PRINT PRINT "INPUT DATA:" 920 PRINT INPUT " I N I T I A L ALT, FT ",A1 940 PRINT 950 INPUT "FINAL ALT, FT " ,A2 960 PRINT 970 INPUT "AIRCRAFT WEIGHT, LBS ",W PRINT 990 PRINT "ENTER: 1 = FROM TAKEOFF 2 = ENROUTE CHANGE" INPUT Cl 1010 PRINT 1020 V l = - . 0 0 0 0 7 9 3 6 + . 0 0 0 0 0 0 1 0 2 * W 1030 V2=V1*A1 1040 V3=V1*A2 1050 F1=1.06*2.71828~V2 1060 F2=1.06*2.71828~V3 1070 F=F2-F1 1080 F3=F*100 1090 F 3 = I N T ( F 3 ) F4=F3/10 1110 F 4 = I N T ( F 4 ) 1120 F=F4/10 IF Cl=l THEN F=F+1 1140 PRINT 1150 PRINT "FUEL TO CLIMB FROM " , A 1 , " FT TO " , A 2 , " FT = ",F," GALS" 1160 PRINTXPRINT 1170 PRINT "CHOOSE FUNCTION: ENTER:" 1180 PRINT PRINT "RETURN TO AIRCRAFT PERFORMANCE MENU 1" PRINT "RETURN TO CLIMB PERFORMANCE MENU 2" 1210 PRINT "RETURN TO MASTER MENU 1220 INPUT X\PRINT\PRINT 1230 IF X=l THEN CHAIN "TOPRF" 1240 IF X=2 THEN GOTO 20 1250 IF X=3 THEN CHAIN "MASTER" 1260 GOTO 1170 WBS# 3056.1 10 REM***** TOPRF PROGRAM 5/31/78 20 A=CALL (10608 , 25 ) \A=CALL (10608 , 11) 30 PRINT "AIRCRAFT PERFORMANCE M E N U " 40 PRINT" " 50 PRINT PRINT "TAKE OFF PERFORMANCE 1" 70 PRINT "CLIMB PERFORMANCE 2" 80 PRINT "CRUISE PERFORMANCE 3" 90 PRINT "LANDING PERFORMANCE 4" 100 PRINT INPUT X$\PRINT\PRINT 120 IF X$="M"THEN CHAIN "MENU"ELSE X = V A L ( X $ ) 130 IF X=2 THEN CHAIN "CLBPRF" IF X=3 THEN CHAIN "CRSPRF" 150 IF X=4 THEN CHAIN "LNDPRF" 160 A=CALL (10608, 25 ) \A=CALL (10608 , 11) 170 TAKE OFF PERFORMANCE" PRINT 180 PRINT 190 PRINT PRINT "HARD SURFACE RUNWAY — WITH FLAPS UP" PRINT INPUT "OUTSIDE AIR TEMP, DEC C ,0 PRINT INPUT "AIRPORT A L T , FT.

250 P R I N T INPUT "TAKE OFF WEIGHT, LBS 270 PRINT INPUT KNOTS ,W2 "HEAD W I N D , 290 K=1.0-.0215*W2 A1=(0-15)+.002*P A2=A1/14.9 320 A3=A2*.1+1 A4=K*A3 340 B1=-1184+1.14*W 350 A5=A4*B1 360 V l = - . 0 0 0 0 6 2 0 + . 0 0 0 0 0 0 0 7 9 * W 370 V2=V1*P 380 B 2 = 2 . 7 1 8 2 8 2 ~ V 2 390 A6=A5*B2 400 A 6 = I N T ( A 6 ) 410 P R I N T 420 PRINT P R I N T "TAKE OFF DISTANCE TO CLEAR 50 FT. OBSTACLE = " , A 6 , " FT.

440 PRINT PRINT\PRINT 460 PRINT CHOOSE FUNCTION: ENTER: 470 PRINT "RETURN 480 PRINT TO AIRCRAFT PERFORMANCE MENU 1" "RETURN 490 PRINT TO MASTER MENU 2" 500 PRINT "RETURN TO TAKE OFF PERFORMANCE 3" 510 INPUT X\PRINT\PRINT THEN GOTO 20 520 IF X=l 530 IF X=2 THEN CHAIN "MASTER" 540 IF X=3 THEN GOTO 160 550 GOTO 460 WBS# 3056.2 A=CALL (10608, 25 )\A=CALL (10608,11) 20 PRINT PRINT" CRUISE PERFORMANCE" 40 PRINT " " PRINT\PRINT 60 PRINT"ASSUME: GROSS WEIGHT = 2300" 70 PRINT" STANDARD T E M P . " 80 PRINT" LEAN MIXTURE" 90 PRINT 100 "INPUT DATA: "\PRINT PRINT 110 "CRUISE A L T I T U D E , FT INPUT 120 PRINT 130 "ENGINE RPM INPUT 140 PRINT 150 V1=-104.60+.07225*R V3=-.00002168*A1 170 V 2 = 2 . 1 7 8 2 8 ~ V 3 180 B=V1*V2 190 B = I N T ( B ) 200 Tl=-25.92+.0525*R 210 E = 2 . 7 1 8 2 8 220 T 1 = I N T ( T 1 ) 230 U1=.0009862*R 240 U2=.000150*R 250 U 3 = E ~ U 1 260 U 4 = E ~ U 2 270 U 5 = . 0 0 0 0 0 0 4 3 5 * U 4 280 U 6 = E ~ - U 5 290 G = .7085*U3*U6 300 G1=G*100 310 G 1 = I N T ( G 1 ) G2=G1/10 330 G 2 = I N T ( G 2 ) 340 G3=G2/10 PRINT "% BRAKE HORSEPOWER = ",B," %" 360 PRINT 370 PRINT"TRUE AIR SPEED = ",T1," KNOTS" 380 PRINT 390 PRINT "GALLONS PER HOUR = ",G3 400 PRINT\PRINT PRINT "CHOOSE FUNCTION: 410 ENTER,: " 420 PRINT 4 3 0 PRINT "TO RETURN TO AIRCRAFT PERFORMANCE MENU , 1" PRINT 440 "TO RETURN TO CLIMB PERFORMANCE MENU 2" PRINT 450 "TO CALCULATE ANOTHER CRUISE PERFORMANCE. 3" 460 PRINT "TO RETURN TO MASTER MENU 4" 470 INPUT X\PRINT\PRINT IF X=l 480 THEN CHAIN "TOPRF" IF X=2 THEN CHAIN "CLBPRF" 500 IF X=3 THEN GOTO 20 IF X=4 THEN CHAIN "MASTER" GOTO 400 WBS# 3056.3 10 PRINT 20 PRINT "LANDING PERFORMANCE" 30 PRINT " " 40 PRINT\PRINT 50 PRINT "ASSUMES: 40 DEC FLAPS" 60 PRINT " POWER OFF" 70 PRINT " GROSS WEIGHT = 2300 LBS" 80 PRINT " APPROACH =60 KNOTS IAS" 90 PRINT 100 PRINT "INPUT DATA:" 110 PRINT 120 INPUT "AIRPORT ELEVATION, FT " , E 130 PRINT 140 INPUT " H E A D W I N D , KNOTS ",H 150 E l = 2 . 1 7 8 2 8 160 V1=1-.02*H 170 V 2 = . 0 0 0 0 2 0 4 5 * E 180 V3=V1*1248.3 190 V4=E1~V2 200 F=V3*V4 210 F=INT (F) 220 PRINT 230 PR INT "LAND ING DISTANCE OVER 50 FT OBSTACLE = " F , " FT" / 240 PRINT\PRINT 250 PRINT"CHOOSE FUNCTION: E N T E R : " 260 PRINT 270 PRINT"TO RETURN TO AIRCRAFT PERFORMANCE MENU 1" 280 PRINT"TO RETURN TO CLIMB PERFORMANCE MENU 2" 290 PRINT"TO CALCULATE ANOTHER LANDING PERFORMANCE .. 3" 300 PRINT" TO RETURN TO MASTER MENU 4" 310 INPUT X\PRINT\PRINT 320 IF X=l THEN CHAIN "TOPRF" 330 IF X=2 THEN CHAIN "CLBPRF" 340 IF X=3 THEN GOTO 10 350 IF X=4 THEN CHAIN "MASTER" 360 GOTO 240 5.7 VORFIX PROGRAM FIGURE 5.7-1 FLOW CHART FOR VORFIX ALL VARIABLES SET TO ZERO INITIALIZE VARIABLES AND BEFORE THEY ARE USED DEFINE USER FUNCTIONS READ ALL VOR DATA FROM DATA BASE

C

NOTE: IN DEMONSTRATION READ CURRENT D .R. A PROGRAM POSITION MAY ALSO BE POSITION

C

INPUT BY PILOT IF VOR IS OUT OF RANGE, QUADRANT IS ZERO th Q(R)iIS QUADRANT THE R VOR IS IN, WITH AIRPLANE AT ORIGIN VOR FIX FLOW CHART #1 MILCO INTER NATIONAL, INC.

DON'T DO IF VOR IS OUT OF RANGE COMPUTE TRUE BEARING . VOR * D.R.

COMPUTE DISTANCE VOR FIX VOR + D.R.

FLOW CHART #2 VOR FIX FLOW CHART #3 R >(# of VORs) X N THIS THIS THIS THIS ROUTINE ROUTINE ROUTINE ROUTINE \ Y BEEN DONE BEEN DONE BEEN DONE BEEN DONE BEFORE BEFORE BEFORE BEFORE TUNE VOR / TUNE VOR TUNE VOR TUNE VOR GET BEARING/ GET BEARING GET BEARING GET BEARIN FIND DIST.

FIND DIST.

FIND DIST. FIND DIST.

NORTH, EAST NORTH, EAST NORTH, EAST NORTH, EAST FROM D.R. FROM D.R.

FROM D.R.

FROM D.R.

I

COMPUTE A MOST PROBABLE POSITION (UP TO 4 M.P.P.)

I I I (ALL M.P.P. + D.R.)

I

NEW D.R. = AVERAGE ALL POSITIONS (#MPP + 1) FOR UPDATE /WRITE NEW D.R.

\JO "POSITION" FILE VOR FIX FLOW CHART #4 WBS# 3064.1 10 REM VORFIX 20 REM UPDATE POSITION BY 2 VOR BEARINGS 30 REM 40 REM PLAN 50 REM 1. LOAD ALL VORS FROM MAP DATA BASE.

60 REM 2. SELECT ALL VORS WHICH ARE WITHIN 1'LAT & 1'LNG OF 70 REM BELEIVED POSITION.

80 REM 3. COMPUTE BEARING FROM VOR TO DR POSITION.

90 REM 4. CORRECT BEARING FOR WHICH QUADRANT THE VOR IS IN 100 REM WITH RESPECT TO THE DR POSITION.

110 REM 5. COMPUTE DIST FROM VOR TO DR POSITION.

120 REM 6. SELECT VOR FOR EACH QUADRANT, ONLY ONE PER QUADRANT.

130 REM 7. TUNE RADIOS, GET ACTUAL BEARING FROM VOR.

140 REM 8. COMPUTE DISTANCE OFF COURSE, DIST NORTH, DIST EAST.

150 REM 9. AVERAGE LAT & LNG UPDATES FOR NEW DR POSITION, WRITE 160 REM TO DISK, CHAIN TO A MENU OR FLTCTRL 170 DEF FNR<X)=X*3.141592654/180 130 DEF FND(X)=X*180/3.141592654 190 DEF FNT(X)=SIN(X)/COS(X) 200 REM ********** LOAD VORS FROM MAP DATA BASE *************** 210 OPEN #0,"0422" 220 READ #0,M,P,N \REM MAG VAR, # OF VOR PARAMETERS, # OF VORS 230 DIM V(P-1,N),V*(N*3) 240 FOR W=l TO N 250 READ #0,X* \REM GET VOR NAME 260 V$=V*+X* 270 FOR X=l TO P-l 230 READ #0,V(X,L) \REM GET VOR PARAMETERS 290 NEXT X 300 NEXT W 310 N1=N 320 CLOSE #0 330 REM VOR PARAMETERS ARE, 340 REM #CODE,FREQ,LAT,LNG 350 REM ********* SELECT VORS WITHIN 1'LAT AND 1'LNG *********** 360 OPEN #0 POSITION 370 READ #0, L,N 330 FOR R=l TO Nl 390 IF V(3,RXL-1 OR V(3,R)>L+1 THEN 470 400 IF V(4,RXN-1 OR V(4,R»N+1 THEN 470 410 S=S+1 420 REM **#**#** Q(R) IS QUADRANT VOR IS IN W/RESPECT TO DR 430 IF V(3,R)>L AND V(4,R)>N THEN Q(R)=1 440 IF V(3,RXL AND V(4,R)>N THEN Q(R)=2 450 IF V(3,RXL AND V(4,RXN THEN Q(R)=3 460 IF V(3,R)>L AND V(4,RXN THEN Q(R)=4 470 NEXT 480 FOR R=l TO Nl 490 IF Q(R)=0 THEN 670 500 REM * * * * * * * * B(R) IS BEARING FROM VOR TO DR ************ 510 .J2=V(4,R)-N 520 J3=P/4+FNR(L)/2 530 J4=P/4+FNR < V < 3 , R » /2 540 J5=LOG ( FNT ( J3 ) ) -LOG ( FNT ( J4 ) ) 550 J6=ATN ( ABS ( FNR (-J2/J5 ) ) ) 560 J7=FND ( J6 ) 570 IF Q(R)=1 THEN B(R)=J7+180 530 IF Q(R)=2 THEN B(R)=360-.J7 590 IF Q(R)=3 THEN B(R)=.J7 600 IF Q(R)=4 THEN B(R)=1SO-J7 610 REM ******** D(R) IS DIST FOR VOR TO DR **************** 620 IF B(R)=270 OR B(R)=90 THEN 650 630 D ( R ) =60* ( L-V ( 3 1 R ) ) /COS ( FNR ( J6 > ) 640 GOTO 660 650 D ( R ) =60* ( N- V ( 4 , R ) ) *COS ( FNR ( L ) ) 660 D(R)=ABS(D(R) ) 670 NEXT R 630 FOR R=l TO Nl 690 IF Q(R)=0 THEN 710 700 ON Q < R ) GOSUB 730 , 830 , 930 , 1 030 710 NEXT R 720 GOTO 1190 730 REM ********** VOR IN 1ST QUAD ************ 740 IF Q100 THEN RETURN 750 Ql=l \REM ONLY 1 VOR / QUAD 760 U=U-H 770 GOSUB 1150 730 T=A-B(R) 790 D1=D(R)*SIN(FNR(T) ) 300 D2= D1*SIN(FNR(A-180) ) \REM DIST NORTH 810 D3=-D1*COS(FNR(A-180) ) \REM DIST EAST 320 GOTO 1120 330 REM ********** VOR IN 2ND QUAEi ************ 340 IF Q200 THEN RETURN 350 Q2=l \REM ONLY 1 VOR / QUAD 360 U=U+1 S7O GOSUB 1150 380 T=A-B(R) 890 D1=D(R)*SIN(FNR(T) ) 900 D2= D1*SIN(FNR(A-180) ) \REM DIST NORTH 910 D3= D1*COS(FNR(A-180) ) \REM DIST EAST 920 GOTO 1120 930 REM ********** VOR IN 3RD QUAD ************ 940 IF Q3OO THEN RETURN 950 Q3=l \REM ONLY 1 VOR / QUAD 960 U=U+1 970 GOSUB 1150 980 T=A-B(R) 990 D1=D(R)*SIN(FNR(T» 1000 D2=-D1*SIN(FNR(A-180) ) \REM DIST NORTH D3= D 1 * COS ( FNR ( A - 1 80 ) ) \REM DIST EAST 1 020 GOTO 1120 •fr*****"****** REM ##•»•*#•»•»#**• VOR IN 4TH QUAD 1 030 1 040 IF Q4OO THEN RETURN 1 050 \REM ONLY 1 VOR / QUAD Q4=l 1 060 U=U+1 1070 GOSUB 1150 1 080 T=A-B(R) 1 090 D1=D(R)#SIN(FNR(T) ) 1 1 00 \REM DIST NORTH D2=-D1*SIN(FNR(A-180) ) 1110 D3=-D 1 #COS ( FNR ( A- 1 80 ) ) \REM DIST EAST 1120 L(U)=L+D2/60 1130 N ( U > =N+ ( D3 / 60 > *COS ( FNR ( L ) ) 1140 RETURN 1150 !" COMPUTED BEARING FRM VOR IS " ,B(R) 1160 ."'COMPUTED DISTANCE TO VOR IS " , D ( R ) INPUT "ACTUAL BEARING FROM VOR ? ",A 1180 RETURN 1190 FOR R=l TO U L1=L1+L(U) N1=N1+N(U) 1220 NEXT 1230 L1=L1/U \REM UPDATE LAT 1 240 N1=N1/U \REM UPDATE LNG 1 250 OPEN #0, POSITION 1 260 WRITE #0, L1,N1 ! "UPDATED LAT 1270 UPDATED LNG" 1280 ! INT (LI )+<Ll-INT(Ll ) )* .6, " 'MNT(N1 < N l - I N T ( N l . 6 1290 REM #*# PUT A CHAIN HERE 5.8 LATERAL FLIGHT CONTROL . FLIGHT CONTROL FLOW CHART FIGURE 5.8-1 FLTCTRL FLOW CHART . . .

DEFINE USER FUNCTIONS INITIALIZE VARIABLES /READ FLTPLAN I FROM DISK FILE

*

LOAD INTO ARRAYS READ D MAP DATA, ^V MAG . VAR. )

I

LOAD LAT/LNG OF WAYPOINTS IN ARRAY INITIALIZE GUIDANCE CONSTANTS INPUT INITIAL HEADING PRINT INITIAL LAT/LNG AUTOPILOT LOOP SEE DETAIL PRINT PLOT OF FLIGHT PATH AUTO PILOT LOOP DETAIL COMPUTE CONVERGENCE ANGLE, RATE

I

COMPUTE DESIRED CONVERGENCE ANGLE, RATE LIMIT CONVERG. ANGLE TO 45 degrees MAX

I

COMPUTE DESIRED TRUE HEADING COMPUTE DESIRED BANK ANGLE

I

/ COMMAND AILERON COMPUTE ACTUAL BANK ANGLE COMPUTE DIST.

TRAVELED NORTH

I

UPDATE LAT COMPUTE DIST.

TRAVELED EAST UPDATE LNG AUTO PILOT LOOP DETAIL (CONT.)

Q

GET NEXT WAYPOINT COMPUTE DIST.

OFF COURSE COMPUTE NEW HEADING SAVE DIST.

OFF COURSE FOR PLOT

I

/PRINT ALL COMPUTED DATA/

^

MILCO INTERNATIONAL. INC.

WBS# 3073 10 REM FLTCTRL 20 REM LATERAL GUIDANCE FOR BAM 30 LINE 80 40 A=CALL (10508, 25 )\A=CALL (10608,11) 50 K l = . 0 2 60 K 2 = 2 \REM 2'BANK/DEC HDG ERROR 70 K4=l \REM AILERON GAIN 80 K5=3600 \REM DEG/HR AILERON RESPONSE 90 Pl=3.141592654 100 REM CONVERT DEG.MIN -> DECIML DEC 110 DEF FND (X) = I N T ( X ) + (X-INT (X ) )/. 6 120 REM ARCS IN FUNCTION 130 DEF FNS (S ) 140 X=l. 5707288-. 2121144*S + . 0742610*S~2-.0187293*S~3

150 x=p 1/2-SQRT (i-s)*x

160 RETURN X 170 FNEND 180 REM CONVERT DEGREES -> RADIANS 190 DEF FNR (X)=X*P1/180 200 REM TANGENT 210 DEF FNT (X)=SIN (X)/COS (X) 220 REM ROUND TO 3 DECIMAL PLACES 230 DEF F N F ( X ) = INT (X*1000 + . 5)/1000 240 B1=15\B2=33\B3=50 250 OPEN #2,"FPDATA" 2 6 0 D I M L ( 2 0 ) , N ( 2 0 ) , Y ( 5 0 ) 2 7 0 D I M F ( 2 0 , l l ) 280 REM ******************** LOAD FLT PLN AS ENTERED ****************** 290 REM G1=INIT FUEL\H1=OAT AT AIRPORT\D1=WIND DIRECTON\W1=WINDSPEED 300 REM T1=CRUISE %BHP\T2=ETD\P $=INIT MAP f 310 READ # 2 , G 1 , H 1 , D 1 , W 1 , T 1 , T 2 , P $ 320 REM F ( R , R 1 ) IS FLIGHT PLAN AS ENTERED IN FLTPLN & FLTPLNUP 330 REM R ( R , 1 ) = FROM WAYPOINT CODE 340 REM F ( R , 2 ) = TO WAYPOINT CODE 350 REM F ( R , 3 ) = MAG COURSE 360 REM F ( R , 4 ) = DIST NT. MI 370 REM F ( R , 5 ) = MAG HEADING (WIND CORRECTED COURSE) 380 REM F ( R , 6 ) = ETER HOURS 390 REM F ( R , 7 ) = EGS KNOTS (WIND CORRECTED TAS) 400 REM F ( R , 8 ) = ALT FEET 410 REM F ( R , 9 ) = RESERVES GAL 420 REM F ( R , 1 0 ) = RESERVES HRS 430 REM F ( R , 1 1 ) = TAS KNOTS 440 FOR R=0 TO 20 \REM LOAD ORIGINAL FLIGHT PLAN 450 FOR Rl=l TO 11 460 READ # 2 , F ( R , R 1 ) 470 NEXT Rl 480 IF T Y P ( 2 ) = 0 THEN 500 490 NEXT R \REM NOTE R IS THE NUMBER OF WAYPOINTS 500 REM ******************** LOAD MAP DATA BASE ******************* 510 OPEN # 0 , P $ 520 0$=P$ 530 READ f O , M , M l , F l \ REM LOAD VOR DATA,MAGVAR 540 DIM V(M1-1,F1) ,V$ (3) ,Z$ (Fl*3) 550 FOR W=l TO Fl 560 READ # 0 , V $ 570 Z$=V$+Z$ 580 FOR X=l TO Ml-1 590 READ | O V ( X , W ) f 600 NEXT X 610 NEXT W 620 READ # 0 , P 2 , F 2 \ REM LOAD INTERSECTION DATA 6 3 0 D I M T ( P 2 - 1 , F 2 ) , N $ ( 5 ) , R $ ( F 2 * 5 ) 640 FOR W=l TO F2 650 READ # 0 , N $ 660 R$=N$+R$ 670 FOR X=l TO P2-1 680 READ # 0 , T ( X , W ) 690 NEXT X 700 NEXT W 710 READ # 0 , P 3 , F 3 \ REM LOAD AIRPORT DATA 720 DIM A ( P 3 - 1 , F 3 ) ,A$ (6) ,S$ (F3*6) 730 FOR W=l TO F3 740 READ # 0 , A $ 750 S$=A$+S$ 760 FOR X=l TO P3-1 770 READ # 0 , A ( X , W ) 780 NEXT X 790 NEXT W 800 READ # 0 , P 4 , F 4 \ REM LOAD ILS DATA 810 DIM I ( P 4 , F 4 ) ,1$ (4) ,T$ ( F 4 * 4 ) 820 FOR W=l TO F4 830 READ #0,1$ 840 T$=I$+T$ 850 FOR X=l TO P4-1 860 READ # 0 , 1 ( X , W ) 870 NEXT X 880 NEXT W 890 READ # 0 , P 5 , F 5 \ REM LOAD NDB DATA 900 DIM B ( P 5 - 1 , F 5 ) ,B$ (4) , U $ ( F 5 * 4 ) 910 FOR W=l TO F5 920 READ # 0 , B $ 930 U$=B$+U$ 940 FOR X=l TO P5-1 950 READ # 0 , B ( X , W ) 960 NEXT X 970 NEXT W 980 CLOSE #0 990 REM *************** END OF MAP LOAD *********************** 1000 REM ****GET FLIGHT PATH FROM WAYPOINT N TO WAYPOINT N+l**** 1010 FOR N=0 TO R 1020 GOSUB 1050 \REM LOAD LAT & LNG ARRAYS 1030 NEXT N 1040 GOTO 1590 1050 REM ************** SELECT WHAT WAYPOINT IS ******************** 1060 IF F(N,1)<1000 THEN 1460 \REM WAYPT IS A VOR 1070 IF F(N,1)<10000 THEN 1170 \REM WAYPT IS NDB OR ILS 1080 IF F(N,1)<100000 THEN 1370 \REM WAYPT IS AN INTRSECTION 1090 FOR W=0 TO F3-1 \REM WAYPT IS AN AIRPORT 1100 IF A(1,W+1)=F(N,1)THEN 1130 1110 NEXT W 1120 GOTO 1540 1130 G$=S$(6*(F3-W)-5,6*(F3-W)) 1140 L ( N ) = A ( 3 , W + 1 ) \REM ASSIGN LAT 1150 N ( N ) = A ( 4 , W + 1 ) \REM ASSIGN LONG 1160 RETURN 1170 IF F ( N , 1 ) < 5 0 0 0 THEN 1260 1180 FOR W=0 TO F5-1 \ REM WYPT IS NDB 1190 IF B ( 1 , W + 1 ) = F ( N , 1 ) T H E N 1220 1200 NEXT W GOTO 1540 1220 G $=U $ (4 * ( F5-W) -3 , 4 * ( F5-W) ) L ( N ) = B ( 3 , W + 1 ) \REM ASSIGN LAT N ( N ) = B ( 4 , W + 1 ) \ R E M ASSIGN LONG 1250 RETURN 1260 IF F ( N , 1 ) > 4 0 0 0 THEN 1290 1270 REM B IS A NDB GOTO 1180 FOR W=0 TO F4-1 \REM WAYPT IS AN ILS IF I a , W + l ) = F ( N , l ) T H E N 1330 NEXT W GOTO 1540 G$=T$ ( 4 * ( F 4 - W ) ~ 3 , 4 * ( F 4 - W ) ) L (N) = I ( 3 W + l ) \REM ASSIGN LAT f N (N) = I ( 4 , W + 1 ) \REM ASSIGN LONG 1360 RETURN FOR W=0 TO F2-1 \REM WAUPT IS AN INTERSECTION IF T ( 1 , W + 1 ) = F ( N , 1 ) T H E N 1410 NEXT W GOTO 1540 G$=R$ ( 5 * ( F 2 - W ) - 4 , 5 * ( F 2 - W ) ) L ( N ) = T (3,W+1) \REM ASSIGN LAT N ( N ) = T ( 4 , W + 1 ) \REM ASSIGN LNG C 2 = T ( 2 W + l ) * 1 0 0 f RETURN FOR W=0 TO Fl-1 \ REM WYPT IS VOR IF V ( 1 , W + 1 ) = F ( N , 1 ) T H E N 1500 NEXT W GOTO 1540 G$=Z$ (3*(F1-W)-2,3*(F1-W) ) L ( N ) = V ( 3 , W + 1 ) \REM ASSIGN LAT N ( N ) = V ( 4 , W + 1 ) \REM ASSIGN LONG 1530 RETURN i !"*******ERROR WAYPT NOT ON FILE*******" !"BOMBING OUT! CHECK WAYPOINT CODE!!

1580 END ************* REM ************* BEGIN GUIDANCE AT WAYPOINT #0 B3=0 \REM BANK ANGLE INITIALLY 0 G=69552 \REM ACELLERATION OF GRAVITY, MI/HR~2 1620 T=l/3600 \REM 1 SEC IN HOURS 1630 W=0 \REM W=FROM WAYPOINT NUMBER 1.640 L=FND (L (W) ) \REM INIT DECIML LAT N=FND (N (W) ) \REM INIT LNG DECIML 1660 L1=FND (L ( W + l ) ) \REM LAT NEXT DECIML N1=FND(N ( W + l ) ) \REM LNG DECIML NEXT C 1 = F ( W , 3 ) \REM MAG COURSE C=C1-M \REM TRUE COURSE D = F ( W , 4 ) \REM DIST FROM W ( W ) TO W ( W + 1 ) 1710 S = F ( W , 1 1 ) \REM TAS B1=ATN (3*S/19 \REM MAX BANK ANGLE 2) B1=B1*180/P1 \REM IN DEGREES IF B l > 4 5 THEN Bl=45 INPUT " I N I T HDG " , H 1760 ! "INIT LAT FINAL LAT FINAL L N G ' INIT LNG ! L , " " , N , 1780 IF W>0 THEN 1790 Y=0 \REM AT AIRPORT, Y=0 GOTO 1840 1810 GOSUB 2410 \REM GET COURSE ( C 3 ) AND DIST (D) 1820 C2=C3-C \REM ANGLE OFF COURSE 1830 Y=D*SIN (FNR ( C 2 ) ) \REM Y=DIST OFF COURSE !"INIT DIST OFF COURSE = ",Y .'"MAX BANK ANGL = ",B1 1860 ! " H D G " , T A B ( 1 0 ) , " A CONV A" , TAB (20 ) ," A CONV R" , TAB (30 ) , "D CONV A" ! T A B ( 4 0 ) " Y " , T A B ( 5 0 ) , " D B A N K " , T A B ( 6 0 ) , " B A N K C " , T A B ( 7 0 ) , f 1880 ] " B A N K " ******* BEGIN MINOR LOOP 1890 FOR Q=l TO 50 \REM ACTUAL CONVERGENCE ANGLE H9=H-C \REM 1910 ACTUAL CONVERGENCE RATE Y1=-S*SIN (FNR ( H 9 ) ) \ R E M 1920 DESIRED CONVERGENCE RATE Y2=-YA1 \REM 1930 CONVERGENCE ANGLE DESIRED H8=FNS (-Y2/S) \ R E M 1940 CONV ANGLE IN DEGREES DESIRED H8=H8*180/P1 \REM 1950 IF H8>45 THEN H8=45 1960 DESIRED TRUE HEADING H1=H8+C \REM 1970 DESIRED BANK ANGLE B = K 2 * ( H 8 - H 9 ) \REM 1980 IF B>B1 THEN B=B1 1990 B 9 = K 4 * ( B - B 3 ) \REM AILERON DEFLECTION COMMAND IF B9>15 THEN B9=15 2010 B3=B3+K5*B9*T \REM ACTUAL BANK ANGLE D1=S*COS (FNR ( H ) ) * T 2030 L=L+D1/60 \REM UPDATE LAT 2040 D2=S*SIN (FNR ( H ) ) * T 2050 N=N-D1/(60*COS (FNR ( L ) ) ) 2060 IF A B S ( L - L 1 ) < . 0 0 1 AND ABS ( N - N l ) < . 0 0 1 THEN EXIT 2330 2070 Y=Y+Y1*T \REM NEW DIST OFF COURSE 2080 REM NEW HDG 2090 H = H + ( G / S ) * F N T ( F N R (B3 )) *T*1 80/P1 2100 Y ( Q ) = Y \REM SAVE DIST OFF COURSE FOR PLOT D=D-S*T 2120 ! I N T ( H ) , T A B ( 1 0 ) , INT (H9*100 ) /100 , TAB (20 ) , F N F ( Y 1 ) , TAB ( 3 0 ) , F N F ( H 8 ) , 2130 ! T A B ( 4 0 ) , F N F ( Y ) , T A B ( 5 0 ) , INT (B*10 }/10 , TAB (60 ) , INT (B9*10)/10, 2140 ! TAB ( 7 0 ) ,INT(B3*10)/10 2150 NEXT Q \REM ******* END MINOR LOOP ******* 2160 !"END MINOR LOOPS" 2170 LINE 80 X = Y ( 1 ) \REM FIND MAX DIST OFF COURSE 2190 FOR 0=2 TO 50 I F A B S ( X ) < A B S ( Y ( Q ) ) THEN X = Y ( Q ) 2210 NEXT Q 2220 IF X=0 THEN 2240 2230 E = 7 9 / ( X * 2 ) \REM TAB FACTOR TO XPAND PLOT FULL SCREEN 2240 FOR Q=l TO 50 \REM PLOT DIST OFF COURSE 2250 IF Y ( Q ) * E > - 1 A N D Y ( Q ) * E < 0 THEN Y (Q)=Y (Q)-1/E ii* n 2260 IF Y ( Q ) > 0 THEN PRINT TAB (4 0 ) , " : " ,TAB (Y (Q ) *E+4 0 ) 2270 I F Y ( Q ) < 0 THEN PRINT T A B ( 4 0 - Y ( Q ) * E ) , "* " , TAB (4 0 ) n* n 2280 IF Y ( Q ) = 0 THEN PRINT TAB ( 4 0 ) 2290 NEXT Q 2300 ! " L A T = " , L 2310 ! " L N G = " , N 2320 GOTO 1890 2330 W=W+1 2340 GOSUB 1050 2350 PRINT "FROM ,G$, TO 2360 W=W+1 2370 GOSUB 1050 2380 !G$ W=W-1 GOTO 1660 2410 REM FIND COURSE BETWEEN TWO LAT/LNG COORDINATES 2420 J 2 = P l / 4 + F N R ( L l ) / 2 2430 J 3 = P l / 4 + F N R ( L ) / 2 2 4 4 0 J4=FNR ( N ) - F N R ( N l ) 2450 J5=LOG (FNT (J2 ) ) - L O G (FNT (J3 ) ) 2460 J 6 = A B S ( J 4 / J 5 ) 2470 J8=ATN ( J 6 ) 2480 C=J8*180/P1 \REM RETURN TRUE COURSE 2490 IF L>L1 AND N>N1 THEN C=180-C 2500 IF L > L 1 AND N < N 1 THEN C=180+C 2510 IF L<L1 AND N < N 1 THEN C=360-C 2520 REM FIND DIST BETWEEN TWO LAT/LNG COORDINATES 2530 REM NOTE THIS ROUTINE MUST BE DONE AFTER THE 40000 ROUTINE 2540 D = 6 0 * ( L - L 1 ) / C O S (J8) 2550 RETURN 6.0 CONCLUSIONS AND RECOMMENDATIONS The BAM design for General Aviation A i r c r a f t has verified that a low cost, microprocessor based avionics system can be defined to aid the single pilot d u r i n g IFR c o n d i t i o n s in the low end of the General A v i a t i o n A i r c r a f t s p e c t r u m .

The design study has v a l i d a t e d the concept of a n a v i g a t i o n system utilizing waypoints stored in a navigation map data base. The concept of an area n a v i g a t i o n system using dead reckoning updated by a n a v i g a t i o n aid such as dual VOR has been shown to be sound. Such a concept for which the update method is t r a n s p a r e n t to the pilot provides a sound basis for f u t u r e upgrades of the US n a v i g a t i o n f a c i l i t i e s s u c h a s t h e i n t r o d u c t i o n o f NAVSTAR/GPS.

Considerable work remains to integrate all of the BAM software into an operationally usable system. This BAM study has been a start in that d i r e c t i o n with some of the c r i t i c a l s o f t w a r e modules addressed.

A number of the software modules r e q u i r e a dynamic simulation environment to validate, which was beyond the scope of the BAM study.

For example the VOR update requires a dynamic simulation to complete the VOR RNAV module. A critical module used for VOR RNAV is the VORFIX m o d u l e w h i c h w a s c o m p l e t e d d u r i n g t h e B A M s t u d y .

The navigation map display used a graphics module with 128 x 128 r e s o l u t i o n display f o r m a t without h i g h resolution alphanumerics superimposed. The study showed this format to be unsatisfactory. A 512 x 512 resolution g r a p h i c s mode with superimposed a l p h a n u m e r i c s is n e c e s s a r y f o r a n a c c e p t a b l e N A V M A P d i s p l a y .

The programming in BASIC using an interpreter loaded into RAM proved to be an e f f e c t i v e way to develop the BAM demonstration software r a p i d l y . Making changes is very easy. The disadvantage is the excessive memory used and the relatively slow execution time caused by t h e i n t e r p r e t e r c o m p a r e d t o a c o m p i l e d p r o g r a m f o r e x a m p l e .

I m p l e m e n t i n g t h e RNAV o u t e r loop g u i d a n c e i n t h e d i s t r i b u t e d microcomputer (DMC) appears to be a reasonable approach. The short period dutch roll dynamics were not included in the closed loop d e m o n s t r a t i o n s , however, it is not believed that including these dynamics would change the results since the natural frequency of the outer loop guidance mode is considerable lower frequency than the dutch r o l l . The DMC commands an a i l e r o n d e f l e c t o r to s a t i s f y the lateral flight control equations. An analog yaw rate loop is closed i n t h e o f f t h e shelf a u t o p i l o t t o p r o v i d e t u r n c o o r d i n a t i o n .

Both the handbook checklists and IFR checklists were included in the BAM preliminary software. It appears that having the additional IFR checklists would be helpful to the single pilot during IFR to prompt him on procedures that a copilot would otherwise help him to remember.

The BAM a c t s as a s u r r o g a t e c o p i l o t .

The following recommendations are offered as a result of the BAM design s t u d y : 1. . The hardware for the NASA Langley simulation and flight test R&D can use the type of microcomputer hardware utilized by MILCO for software development provided: a. A suitable DC power supply is incorporated in the DMC b. Provision is made to constrain the cards in the DMC card cage with some appropriate mechanical means.

2. The mounting of a 9 inch TV in the cockpit poses a difficult installation problem which could be costly. It is recommended that the TV be mounted on a slanted bracket located near the center of the control panel console. The TV longitudinal axis would be about 60 deg relative to the horizontal with the TV display pointing up towards the pilot. The ADCC "telephone" keyboard data entry panel can be mounted near by.

3. A dual floppy disk should be used for storing the NAV MAP data base and application programs during the NASA Langley R&D program The data base and programs can be stored on EPROMs to eliminate the need to fly the floppy disks during the mature stages of the R&D program. However, there should be no problems in flying the floppy disks. The advantage of using floppy disks is the ease of making software changes during the R&D. The use of EPROMs makes changes much more difficult.

4. The operational software should be written in a higher order language such as FORTRAN IV which has an efficient microcomputer oriented compiler. The compiler should be resident in the 8085 microcomputer rather than use a cross compiler. MILCO has acquired a true FORTRAN IV compiler from MICROSOFT which will operate on the MILCO 8085 microcomputer, however the compiler was not used during the BAM design program. The translation of BASIC into FORTRAN IV is a fairly straight forward process.

5. The low cost electropneumatic sensors developed by NASA Langley are recommended for the BAM dead reckoning sensors. The availability of a good low cost true airspeed sensor significantly simplifies the sensor computations. MILCO presented and alternate method based on absolute and differential pressure transducers and OAT transducer to compute TAS in the midterm briefing.

6. A parallel data bus is recommended rather than a serial bus in order to have a moderate byte data rate without using very high serial bit rates. MILCO has found that components to implement the IEEE 488 bus are currently more available and considerably cheaper than the components to implement the 1553 bus.

7. It is recommended that the three navigation radios be placed on the IEEE 488 bus to redice the number of wires from the navigation radios from 96 to 16 wires. This would require building a IEEE 488 bus interface unit located adjacent to the radios.

8. It is recommended that the BAM be implemented for simulation and flight test by NASA Langley as a cost effective avionics research tool.

APPENDIX A LATERAL DIRECTIONAL TRANSFER FUNCTIONS FOR AIRPLANE "A"

The lateal directional transfer functions for airplane "A" presented in

this section can be used for point stability analyses of the flight

control equations presented in section 2.5. The level of e f f o r t on the

BAM d e s i g n did not p e r m i t a detailed s t a b i l i t y d e s i g n of the BAM

l a t e r a l f l i g h t c o n t r o l s y s t e m .

Figure A-l and A-2 presents the lateral transfer functions in terms of

t h e a i r c r a f t s t a b i l i t y .

The numerical values for a i r c r a f t A stability derivatives at two flight

conditions: cruise at 5000 feet and approach are taken from reference 1

and a t t a c h e d f o r r e f e r e n c e a s t a b l e s A-10, A-12, a n d A-14.

a: UJ «o a z CQ z

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a: on Table A 10 Aerodynamic, Geometric and ( n e r t i a l C h a r a c t e r i s t i c s of A i r p l a n e A. Flight C o n d i t i o n : 5,000 ft, 219 f t / s e c I N P U T W I N G A R E A , S Q . F T . 1 7 4 . 0 0 W E I G H T / I B S . 2 6 4 5 . 0 0 W I N G S P A N , F T . 3 5 . 8 0 0 0 4.9000 M E A N A E R O D Y N A M I C CHORD, F T .

A I R S P E E D , F T . / S E C . 219.00 D E N S I T Y , S L U G S / C U . F T . O . C 0 2 0 5 C O O 0.

.. I N I T I A L T H E T A , 8 A O _ . _ I Y Y , S L U G - S O . F T . 1 3 4 6 .

9 4 8 .

I X X , S L U G - S O . F T .

I Z Z , S L U G - S O . F T . 1967.

I X Z , S L U G - S O . F T . 0.

0 . 3 1 0 0 C L 1 , C D 1 , 0 . 0 3 1 0 C T X 1 , 0.0310 c?n .

0- C M T 1 , 0.

D I M E N S I O N A , D E R I V A T I V E S N O N O I M E N S I O N A L D E R I V A T I V E S L O N G I T U D I N A L D E R I V A T I V E S MU , R A O / F r /StC U.

• MA ,RAD/ScC/SEC.

C M A D , i M A D , R A D / S E C / - 5 . 2 0 0 0 -1.8115 -4.3197 " 1 C m *»UUU MO , RAO/_SE.C_/ C M T U , 0. M T U , R A D / F T /SEC o".

C M T A , i 0. M T A , R A D / S E C / S E C ...o.

. ZU ,RAO/SEC/ -0.2946 / Art nn H. oUUU ZA ,FT /SEC/SE_C_ i81 .8540_ C L A O / 1.7000 ZAD,FT /SEC/ -1.9788 _- -5397_

. vuuu ZO ,FT / S E C /

1 V nn 0 . I J 00 XA ,FT / S E C / S E C 7289 . XU ,RAD/SEC/ 0295

_-o

C T X U * -0.0930 X T U , R A O / S E C / 0147' -0

C L D E , - — . ZDE,FT /SEC/SEC 7 4 14 •44 0.4300 C O D E , - — - X O £ , F T /SEC/SEC 0.0600 2430' -6 C N D E , -1.2800 I MOE,RAO/SEC/_S_E_C_ -39.8586 L A T E R A L - D I R E C T I O N A L D E R I V A T I V E S C L B , / R A b " -0.0390 L9, L9,RAD/SEC/SEC -28.7492 L P , R A D / S E C / S E C C L P , / R A O -0.4700 L P , •12.4092 C L R , / R A D O.C960 L R , L R , R A O / S E C / S E C 2.5346 C L D , / R A O L D , L D , R A D / S E C / S E C 57.4984 0. 1780 N9. 10.1194" C N B , / R A D 0.0650 N9,PAD/SEC/SEC C N P , / R A D NP, -0.0300 N P , R A D / S E C / S E C -0.331 7 M R , -1.2597 C N R , / R A D -0.0990 M R , R A O / S E C / S E C N O , C N O , / R A D -0.0530 N O , R A D / S E C / S E C -8.2512 C Y 3 , / R A D Y 5 , , F T / S E C / S E C •32.2554 -0. 3100 Y P , _-0.3147 C Y P , / R A D - 0 . 0 3 7 0 , F T / S E C / S E C C Y R , / R AD Y R , , F T / S E C / S E C 1.7859" 0.2100 Y D , C Y D , / R A O 0. F T / S E C / S E C 0.

Table A.12 Dynamic S t a b i l i t y Characteristics

of Airplane A. ( A p p r o a c h ) "

L O N G I T U D I N A L R O O T N O . R E A L P A R T _ I M A G . P A R T ONE - 0 . 2 0 9 2 E - 0 1 0 . 1 7 9 7 E 00 TWO - 0 . 4 1 3 0 E OJ 0 . 4 3 9 0 E 01_ " T H R E E "~~ " -o. 2092E-01 " " - 0 . 1 7 9 7 E ob F O U R - 0 . 4 1 3 0 E 01 - 0 . 4 3 9 0 E 01 U N D A M P E D N A T U R A L F R E O U E N C Y < F N > C Y C L E S / S E C _ 0 . 0 2 9 U N D A M P E D N A T U R A L F R E 3 U E N C Y , 0 « E G A ( N ) , R A D / S E C 0.131 T I M E TO H A L F AMP_L...IJUO E.*OSjC _MOO E/J E_C 3_?_--?JL D A M P I N G R A T I O ~ 0.116 U N D A M P E D N A T U R A L F R E Q U E N C Y ( F N ) C Y C L E S / S E C J3.960.

U N D A M P E D N A T U R A L F R E O U E N C Y / O M E G A ( N ) * R A D / S E C 6 . 0 2 7 T I M E TO H A L F AMPL UUDE r O S C . MOD l S.E.C _P«17 f D A M P I N G R A T I O 0 . 6 8 5 T H E C H A R A C T E R I S T I C E Q U A T I O N I N F A C T O R E D F O R 1 ( S « S + 0 . 4 1 8 3 9 E - 0 1 S + 0 . 3 2 7 2 0 E - 0 1 ) ( S * S + 0 . 8 2 6 0 7 E 0 1 S + 0 . 3 6 3 2 8 E 0 2 J = 0 T W O P A I R S O F C O M P L E X C O N J U G A T E S S E C O N D MODE A B O V E I S S H O R T P E R I O D W I T H T H E S E F E A T U R E S L O A D F A C T O R / A N G L E OF ATT A_CJC JG^UNJ T_S/JRAD 14 . 5 _ f O M E b A S U U A R t D / N / A L P H A " <T.!>03 L A T E R A L - D I R E C T I O N A L R O O T NO. R E A L P A R T I M A G . P A R T ONE -0. 1095E-01 "0."

TWO _ _ - 0 . 6 3 5 8 E 00__; 0 . 3 3 0 6 E 01 T H R E E " - 0 . 1 2 4 3 E 0 2 "~-0.3213E-iT FOUR - 0 . 6 8 5 8 E 00 -0.3306E 01 T I M E C O N S T A N T ^ S E C ?_L-318 UNDAMPED N A T U R A L FREQ'uENC Y »0"«EGA*( N) / R A D / S E C 3 . 3 7 7 " U N D A M P E D N A T U R A L F R E Q U E N C Y , F N / C Y C L E S / S E C " " 0 ^ 5 3 8 D A M P I N G R A T I O ; P - 2 0 3 Z T D « O M N D = d".6858 O S C I L L A T O R Y P H I / B E T A R A T I O 0.69 O M E G A ( N ) S O U A R E D X PHI / BE T A,1 / S EC / S'EC 7 . 9 1 ~ ~ ~ T I M E C O N S T A N T , S E C _ 0.080 ' THE F I R S T T I M E CO N S T A N T "l S "THE SP I R AL."~w'HiuE THE S E C O N D " IS THE R O L L TIME C O N S T A N T _

" T I M E TO DOUBLE THE A M P L I T U D E I"N~~T~HE S'PIR'AL >i6bExS~EC, 6 3 . 0 0 9

T H E C H A R A C T E R I S T I C E Q U A T I O N "IN" F A C T O R E D " F O R M

CS+ 0.10951E-01 ) C S * 0 . 1 2 4 3 4 E 0 2 ) ( S « S * 0 . 1 3 7 1 7 E 0 1 S + 0.1U03E 0 2 ) T'WO R O O T S A R E R E A L A N D T W O ROOTS A R E C O M P L E X C O N J U G A T E S Table A.1*t Transfer Functions for Airplane A.

Flight Condition: Cruise, 5,000ft, 219 ft/sec

T R A N S F E R F U N C T I O N P O L Y N O M I A L C O E F F I C I E N T S . T H E . C O E F F I C I E N T S 0 F. TH E. L O N G I T U O I N AL C H A R A C T E R I S T I C E Q U A T I O N ^ A= 0 . 2 2 0 9 3 E . 0 3 . 9 = 0 . 1 8 3 4 7 E . 0 4 C = O . S 1 1 1 2 E . . 0 4 0= 0 . 3 9 5 5 9 E 03 E= 0 . 2 6 2 6 6 E 03 . T H E C O E F F I C I E N T S . F O R .THE N U K E S A T O R . U ( S . ) _ . A R E . .

A U = - 0 . 1 3 7 9 6 E . 0 4 . B U = - 0 . 1 2 2 3 1 E . . D 5 _ . _ C U = . . 0 . 6 6 9 6 J E _ 0 5 . _ . O J = _ _ 0 . 5 7 8 9 4 E . _ 0 _ 6 _ .

T H E C O E F F I C I E N T S F O R T H E N U M E R A T Q R A L P H A ( S ) A R E .

A A = - 0 . 4 4 7 4 1 E 02 B A = - 0 . 8 7 4 1 5 E 04 C A = - 0 . 3 7 3 3 0 E 03 DA =-0. 3 7 7 7 6 E .!) 3 THE. C O E F F I C 1 EN T S..F..OR-T H E __NU !*E R A TO R._T.H E T A ( S )_AR_E .

.A T = -0. 8726.9E_0_4 9T_=-0 . 1 8355JL.Q5 CT = - 0 . 1 0 6 4 7 E 34 S T A N O A R O F O R M A T .FO R_J.ONG I TU 01 N A L _ _ T R ANS.FE.R _F UNC TJ_O.N.S_ /n PI T 4 - p f « \ _ rn ccc f rj c ni T c A o e m K U D E = 2 2 0 0 . 7 0 3 _ TU1 = M 6 . 5 9 8 7 3 TU2 = 1/ _ 9 . 1 8 2 2 4 _ OMN = 0.18089 OMN s 6 . 0 2 7 2 3 Z T = 0 . 1 1 5 6 5 ZT = 0 . 6 8 5 2 8 A L P H A ( S ) / O E L T A - E ( S ) C O E F F I C I E N T S A R E K A L P H A O E = - 1 . 4 3 8 T A L P H A = 1 / 1 9 5 . 3 3 5 4 7 OMN A L P H A = 0.20790 Z E T A A L P H A = 0._103.I7_ OMN = 0.18089 OMN = 6 . 0 2 7 2 3 _ Z E T A = 0 . 1 1 5 6 5 Z E T A = 0 . 6 8 5 2 8 T H £ T A ( S ) / O E L T A - E ( S ) C O E F F I C I E N T S A R E K T H E T A O E = - 4 . 0 5 4 T T H E T 4 1 = 1 / 2 . 0 4 3 5 7 T T H E T A 2 = 1 / 0 . 0 5 9 7 0 O'lN = 0 . 1 3 C 3 9 O.'iN = 6 . 0 2 7 2 3 Z ? T A = 0 . 1 1 5 6 5 Z E T A = 0 . 6 8 5 2 8 1 Table A.lA (cont'd) Transfer Functions for Airplane A.

Flight Condition; Cruise, 5.000 ft, 219 ft/sec

_THE. COLEF/_I.C.I.EMT_S_Oi_.TH E...L A T ER A L - 0 I R E C T j ONAL C H A R A C T E R I S T I C E Q U A T I O N ' A = . . 0 . 2 1 9 0 0 E 03 8=. 0 . 3 0 2 5 7 E 04 C=. 0 . 6 2 6 5 3 E JD4 0 = Q.3 111 7E .05 E » .0.34001 E..03 .

T H E C O E F F I C I E N T S F O R T H E B E T A ( S ) - D U E T O A I L E R O N S - P O L Y N O M I A L A R E .

AB» 0... BB= 0 . 1 7 7 4 2 E 04 CB = 0 . 2 3 3 4 2 E 05 03= 0. 1 6 5 7 6 E 0_4 THE C O E F F I C I E N T S . FOR T HE PH I ( S ) - 0 UE _TO .AI LE RONS-..POL Y NOM I A_L._A_R E_.

AF = 0.12.5?l.E_p5 _8F«_0.J.3137_E._P5 CF= 0 . 7 6 5 2 1 E OS THE .COEFFI CIENT.S..F.OR.TH£_PSICS). jr.OUE _rO_.A I LE RONS-_ .POL r NOMI AL_AR_E, 1S070E 04 __B S=-0. 2 7 4 9 7£ 05 _ .C.SjL~0. 4J.1_9J E..04 OS^._0...1.1 088E._0_5_ S T A N D A R D F O R N A T _ F O R L A T E R A L D I R E C T I O N A L L"A N SFER_F UNC (DUE TO A I L E R O N S ) BETA(S)/DELTA-A(S) C O E F F I C I E N T S A R E K B E T A D E L T A - A » 4.875 T B E T A A1 » 1/ 16.1989?

T SETA A2 = 1/ 0.05768

TS = I/ 0.01095

TR =T/'12.4335 7

OMNO = 3.37678

Z E T A O = 0.20311 P H I ( S ) / D E L T A - A ( S ) C O E F F I C I E N T S A R E K PHI O E L T A - A a 2 2 5 . 0 5 5 OMN PHI A » 2 . 4 6 5 1 3 Z E T A PHI A s 0.21161 TS = 1/ 0.01095 TR « 1/ 12.4335_7 OMND » 3 . 3 7 6 7 8 Z E T A D > 0.20311 P S I ( S ) / D E L T A - A < S ) C O E F F I C I E N T S A R E < PSI D E L T A - A * 32.611 T PSI A = 1/ 0 . 7 3 4 3 7 O.MN PSI A = 0.

Z E T A P S I A s 0 .

TS = 1/ 0 . 0 1 0 9 5 T R = J /_1 2 . 4 3 3 5 7 O M N D = " 3 . 3 7 6 7 8 Z E F A D - 0 . 2 0 3 1 1