N~VIGATION COM· Submitted to AFHQ/ AMTS/CAE/DIE-Eng/ 1E3-3 Royal Canadian Airforce Ottawa Ontario .COMPUTING DEVICES OF CANADA LIMIT ED -r I , ' 9201/7601 / R 1 TERMINATION REPORT THE ASTRA - 1 NAVIGATION COMPUTER Submitted to AFHQ/ AMTS/CAE/DIE-Eng / 1E3-3 Royal Canadian Airforce Cl .. Ottawa, Ontario ass1hcation cancelled/changed to •••-.m11••••••••••••••••s by a 1thority of ....................... (date) ... s ·anat ". .. - ·- -- nk .... .. .... ...... ..... ,., By Computing Devices of Canada Limited, P.O. Box 508, Ottawa 4, Ontario. Author 31 March 1959 . 1 TABLE OF CONTENTS SECTION TITLE PAGE 1 .. 11 1 INTRODUCTION 2 SPECIFIED REQUIREMENTS 2. 1 GENERAL DESCRIP.TION 3 GENERAL SYSTEM DESCRIPTION 3o 1 SYSTEM COMPONENTS 3. 2 FUNCTION 4 DETAILED SYSTEM DESCRIPTION 4.1 OPERATION 4. 2 UNIT FUNCTIONS 5 . OPERATIONAL PROCEDURES 5.1 COMPUTER ·ZEROING 5. 2 AIRCRAFT POSITION FIXING 5. 3 TARGET POSITION AND VELOCITY FIXING 5. 4 SELECTION OF CLOSE CONTROL (C. C.) or MODIFIED CLOSE .C.ONTROL (M. C. C.) 5.5 USE OF A.D.F. 5. 6 EMERGENCY PROCEDURES 3 3 5 5 5 7 7 8 15 15 16 18 19 20 20 6 ENVIRONMENTAL TESTS 23 6. 1 HIGH TEMPERA TU~E - SEA LEVEL 23 6. 2 HIGH ALTITUDE 24 6. 3 LOW TEMPERATURE - SEA LEVEL . (ALL UNITS) 25 6. 4 CONDENSATION (ALL UNITS) 25 6. 5 VIBRATION 25 6. 6 SHOCK 27 6. 7 VOLTAGE VARIATION AND FREQUENCY 28 7 ACCURACY REQUIREMENTS 29 7. 1 SYSTEM 29 7.2 WIND DATA DISPLAY 29 7 o 3 TARGET AND DISPLAY 29 7. 4 DESTINATION INDICATOR DISPLAYS 30 7 .. 5 OUTPUT SIGNALS 31 9201/7601/Rl ' Confidential TABLE OF CONTENTS ( Continued} SECTION TITLE 8 ACCURACY 9 8. 1 ROOM TEMPERATURE 8. 2 EFFECTS OF ENVIRONMENTAL TESTING PROBLEM AREAS 9. 1 RELAYS PAGE 33 33 34 39 39 9. 2 TEMPERATURE EFFECTS ON AMPLIFIER GAIN 40 10 11 STATE OF DESIGN CONCLUSIONS 9201/7601/Rl 43 45 ... 111 FIGURE Frontispiece l 2 3 4 5 6 7 8 9 l O - l 1 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 2·1 30 31 32 33 34 35 36 lV . Confidential l..1IST OF ILLUSTRATIONS TITLE Astra 1 Cornputer Astra 1 Computer Destination Indicator and Wind Data Display Destination Indicator - Face Destination Indicator - Exploded View Destination Indicator - Outline Drawing Wind Data Display - Face Wind Data Display - Internal View Wind Data Display - Outline Drawing Target Data Display Target Data Display - Face Target Data Display - Internal Target Data Display - Internal Target Data Display - Internal Target Data Display - Outline Drawing Control Units Pilot's Destination Indicator Control - Face Pilot's Destination Indicator Control - Outline Drawing Navigation Computer Control - Face Navigation Computer Control - Internal Navigation Computer Control - Outline Drawing Dead Reckoner Units Ground Speed Computer - Internal Ground Spe e d Computer - Internal Ground Speed Integrator - Internal Ground Spe~d Integrator - Internal Computer and R.elay Unit - Internal Computer and Relay Unit - Internal Dead Reckoner Mounting Tray Dead R.eck~)nc:1.: M :::n1nting Tray Dead Reckoner Mounting Tray - Outline Drawing Interc e ptor Grid Target Interception Return to Base Block and Flow Diagram Symbols Block Diagram Information Flow Diagram PAC;E Vl 47 49 51 53 55 57 59 61 63 65 67 69 71 73 75 77 79 81 83 85 87 89 91 93 95 97 99 101 l 0 l 103 105 107 109 111 113 115 9201/7601/Rl Confidential FIGURE 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 9201/7601/Rl I LIST OF ILLUSTRATIONS (Continued) TITLE Inte-rceptor Position Computation and Correction Target in Relation to G.C.I. and Computing Grids Target Interception Return to Base Destination Indicator Information Flow Diagram Wind Data Display Information Flow Diagram (Normal) Wind Data Display Information Flow Diagram (Flux Valve, Failed) Wind Data Display Information Flow Diagram Diagram (Flux Valve Only) Target Data Display Information Flow Diagram Pilot's Destination Indicator Control Flow Diagram Navigation Computer Control Information Flow Diagram Ground Speed Computer Information Flow Diagram Ground Speed Integrator Information Flow Diagram Computer and Relay Unit Information Flow Diagram Electro-Mechanical Schematic Diagram - Sheet 1 Electro-Mechanical Schematic Diagram - Sheet 2 Electro-Mechanic.al Schematic Diagram - Sheet 3 PAGE 117 119 121 123 125 127 129 131 133 135 137 139 141 143 145 147 149 V SECTION 2 SPECIFIED REQUIREMENTS 2.1 GENERAL DESCRIPTION The Astra Airborne Navigation Computer shall have the capability of operating in conjunction with a ground environment system and of function ing in all phases of operation of the interceptor including interception, return-to-base and ferry missions. It shall be capable at all times of in dicating the present position of the interceptor. Computations shall be in plane geometry and all input angles, distances, and speeds except true airspeed shall be . treated as being in the geometrical plane of the com putation. The Navigation Computer shall receive ground speed and drift angle information from Doppler radar; heading f ram the heading reference; horizontal true airspeed from the Air Data Computer. The Navigation Computer shall also receive target velocity and position either automatic ally via Data-Link or by manual insertion. By processing this data, the Navigation Computer shall be capable of supplying the distance bearing and course to · any one of five pre-selected bases; the distance, bearing and collision course to a 1noving target and a suitable steering signal for the Automatic Flight Control System. The computer shall also indicate time-to ga to the interception point, or base. The Navigation Computer shall perform the required functions to the accuracy called for in Section 7 and under the environmental conditions set down in Section 6. 9201/7601/Rl 3 I SECTION 3 GENERAL SYSTEM DESCRIPTION 3.1 SYSTEM COMPONENTS (Figure 1) In its final form the Astra Computer consisted of the ten units listed below. 3.1.1 Displays (Figures 2-14): Pilot's Destination Indicator (P.D.I.) - Pilot's Cockpit Observer's Destination Indicator (0. D. I.) - Observer's Cockpit Wind Data Display (W. D. D.,) - Observer's Cockpit Target Data Display (T. D. D.) - Observer's Cockpit 3.1.2 Control Units (Figures 15-20) Pilot' s Destination Indicator Control (P.D.I.C.) Navigation Computer Control (N. C .. C.) 3.1.3 Dead Reckoner (Figures 21-30) Ground Speed Computer (G.S.C.) Ground Speed Integrator (G .S.I.) Computer and Relay Unit (C.R. U .) Mounting tray for these three units 3.2 FUNCTION - Pilot' s Cockpit - Observer's Cockpit Electronics Bay The Astra Computer will perform the following functions: 3.2.1 General (Figure 31): 3 .2 .1.1 Compute the interceptor position in a rectangular grid system (hereafter referred to as the Computer grid) by dead reckoning techniques. 3.2.1.2 Allow the computed interceptor position to be corrected at any time in accordance with a fix without interfering with an intercep t i o n in progress. 9201/7601/Rl 5 I Section 3 C onfidential 3.2.2 Interception Mode (Figure 32) 3.2.2.1 Accept target position and velocity fixes as available from G.C.I. stations or other ground environment and compute the target position in the Computer grid. 3 .2 .2 .2 Display the distance and bearing of the target from the interceptor and the time-to-go to the collision point. 3 .2 .2 .3 Display the interceptor heading for collision with the target, and supply a signal to the Autopilot to acquire and maintain this heading. 3.2.3 Return-to-Base Mode (Figure 33) 3 .2 .3 .1 Display the distance and bearing from the interceptor to any one of several pre-selected bases or G.C.I. stations, (or to any selected ground point whose co-ordinates are k,own to the observer) and the time-to-go to the selected point. 3 .2 .3 .2 Upon selection of a destination, display the heading for homing to the selected point and supply a signal to the Autopilot to acquire and main tain this heading. 3 .2 .3 .3 Although the function outlined in paragraph 3 .2 .3 .1 will normally be carried out after the interception, it can be carried out at any time. 6 9201/7601/Rl SECTION 4 DETAILED SYSTEM DESCRIPTION The following section describes in detail the operation of the Computer and indicates the specific function of each of the units listed above. See Figures 35 and 36, for the System Block Diagram and the Information Flow Diagram. 4.1 OPERATION 4.1.1 Interceptor Position Computation and Correction (Figure 37) 4.1.1.1 The Computer accepts inputs of grid heading, true airspeed, climb angle, Doppler ground speed and Doppler drift. From these signals it com putes the interceptor position in the Computer grid and the wind velocity. The mechanism used to compute wind velocity filters out small random fluctuations . in the Doppler output signals. 4.1.1.2 Duringperiods ~£Doppler inactivitydue to interceptor manoeuvers, the latest value of wind velocity is automatically used. Also, in the event of Doppler failure, the latest value of wind velocity is automatically used, unless it is desirable to insertanewvalne, which may be done at any time. 4 .1.1.3 The computed interceptor position may be corrected at any time if a fix can be obtained. Upon receipt of a distance and bearing fix with res pect to a base whose designation appears on a Base Selector unit, a simple procedure allows correction of the computed position to the actual value. This procedure does not interfere with the progress of an interception. 4.1.1.4 Fixes with respect to G.C.I. stations appearing on a G.C.I. Selector unit, may also be used. In fact, any ground point can be used as a fix point, so long as its position is known to the observer. 4.1.2 Interception Mode (Figure 38, 39) 4.1.2.1 The Computer _ accepts target velocity and position fixes with res pect to one of the G.C.I. stations designated on a G.C.I. Selector unit. These fixes may be automatically inserted from a Data-Link receiver, or may be inserted manually when received by 'voice radio' from the G.C.I. station. The G.C.I. station need not operate in the same grid system as the 9201/760 l / R 1 7 Section 4 Confid ential interceptor . During the tim e between f ix es , the t a r g e t ' s pos i tion 1s extra polated by the Computer. 4.1.2.2 The Computer can also accept target position fixes with respect to the interceptor position. These fixes are manually inserted. 4 .1.2 .3 The required heading for the interceptor to collide with the target (command heading) is computed, and displayed on the Destination Indicators. This heading may be flown manually by reference to the Destination Indi cator, or may be acquired and maintained by the Autopilot. 4.1.2.4 The distance and bearing of the target from the interceptor are computed, and displayed on the Destination Indicators. In addition, the time-to-go to collision is computed, and displayed on the Target Data Display. 4 .1.3 Return-to-Base Mode (Figure 40) 4.1.3.1 The bearing, distance and command heading to a selected destination are computed, and displayed on the Destination Indicators. The time-to-go is computed, and displayed on the Target Data Display. The command heading may be flown manually, or by Autopilot. The destination may be any one of the following:- 4. l .3. l .l A base designated on one of the Base Selectors carried by the interceptor. 4.1.3.1.2 A G.C.I. station designated on one of the G .C.I. Selectors carried by the interceptor. 4.1.3.1.3 Any point whose co-ordinates are known, inG.C.I. grid reference, with respect to one of the G.C.I. stations designated on a G.C.I. Selector. 4.1.3.1.4 Any point whose co-ordinate ~ are i nserted into the Computer, from the ground, by Data-Link. 4.2 UNIT FUNCTIONS 4 .2 .1 Displays 8 9201/7601/Rl C onf iden tial Se ction 4 4.2.1.1 Destination Indicators (Pilot's and Observer's) (Figures 2, 5 , 41) These units, which are identical, operate as repeater-type instru ments and display the following information:- 4 .2 .1.1.1 Interceptor grid or magnetic heading is displayed on a compass card read against the lubber line. Selection of heading reference for both Indicators is made by the Heading switch on the Pilot's Destination Indicator Control. 4 .2 .1.1.2 Bearing of target, G .C .I. station or base is applied to a pointer which read against the lubber line gives relative bearing and against the compass card gives bearing. 4.2.1.1.3 Command heading for collision with target or homing on selected point. The command heading is applied to a pointer which read against the lubber line gives heading error and against the compass card gives com_ mand heading. The interceptor is normally flown to align this pointer ~ith the lubber line. 4.2.1.1.4 Distance of target, G.C.I. station or base is displayed on a three digit, 0-999 mile counter. 4.2.1.2 Wind Data Display (Figures 2, 6-8, 42-44) This unit displays the following information:- 4.2 .l .2. l Wind Direction - displayed on a pointer read against a fixed dial. 4.2.1.2.2 Wind Speed 4.2.1.2.3 Grivation - displayed on a three-digit, 0-250 knot counter. - displayed on a two-digit, 89 ° E-O-896 W counter. 4 .2 .1 .2 .4 Grid Heading - displayed on a three-digit 0 0-360 counter. This unit also carries the following controls:- 4 .2 .1.2 .5 Wind direction and wind speed manual setting knobs . 4.2 .1.2 .6 Grivation manual setting knob. 4.2 .1.2. 7 An emergency switch, to be operated in the event of flux valve failure. 9201 /760 l /Rl 9 > Section 4 (>)nfid'elltial 4 .2 .1.2 .8 Stable Platform manual alignment push-buttons. 4.2.1.2.9 There is in addition a Doppler mode lamp which 1s illuminated when Doppler is inactive. 4.2.1.2.10 The circuits contained in this unit operate in conjunction with the Ground Speed Computer and Doppler to con1pute wind speed and direc tion. In addition, grid and magnetic headings are combined in such a way as to produce grivation, and also supply a stabilized magnetic heading for the Destination Indicators. 4.2 .1.3 Target Data Display (Figure 3, 9-14, 45) This unit displays the following information:- 4.2.1.3.1 Target distance from G.C.I. station - displayed on a three-digit, 0-999 mile counter. 4.2.1.3.2 Target bearing from G.C.I. station - displayed on a pointer read against a fixed dial. 4.2.1.3.3 Target speed - displayed on a four-digit, 0-1500 knot counter. 4.2.1.3.4 Target track - displayed on a pointer read against a fixed dial. 4.2.1.3.5 Time-to-go to destination - displayed on a three-digit, 0-99.9 minute counter. This unit also carries the following controls:- 4 .2 .1.3 .6 Manual setting knobs - for target distance, bearing, speed and track. 4.2.1.3.7 Target Data switch - for insertion of different types of target fix information. 4 .2 .1.3 .8 Mark push-button - for establishing the zero time for a manually inserted targe t fix. 4.2.1.3 .9 Heading-Hold-Off push-button - which releases the Autopilot signal from the heading hold condition. There a re in addition:- 10 9201/7601/Rl I Confidential Section 4 4.2.1.3.10 Data-Link mode identification lamps - (two). 4 .2 .1.3 .11 Heading-Hold lamp - which is illuminated when the output signal to the Autopilot is held constant to maintain a constant heading. 4.2.1.3.12 This unit contains the circuitry required to convert the cartesian target data information to polar information, to compute the time-to-go, and to perform switching functions associated with the insertion of target information. 4.2.1.3.13 This unit also carries the following Selector units:- 4.2.1.3.13.1 G.C.I. Selector This removable unit carries five push-buttons, each of which, when operated, inserts into the Computer the grid coordinates of a G.C.I. station, together with the orie1J.tation of the G.C.I. station's grid with res- pect to the Computer grid. This allows target information given with respect to a G.C.I. station to be converted into information relative to the Computer . grid. Other units, set for differentG.C.I. stations may be inter changed with the unit in use at any time. 4 .2 .1.3 .13 .2 Base Selector This removable unit carries five push-buttons,eachofwhich, whenqperated, inserts into the Computer the grid coordinates of a . base. Other units, set for different bases, may be interchanged with the unit in use at any time. 4 .2 .2 Control Units 4.2.2.1 Pilot's Destination Indicator Control (Figures 15-17, 46) This unit carries two switches, the Heading switch and the Bearing switch. 4.2.2.1.1 Heading Switch This three-position switch selects the heading references for the observer's and pilot's Destination Indicators. The switch positions are:- 9201/7601/Rl 1 1 Section 4 4.2.2.1.1.1 Normal 4.2.2.1.1.2 Grid 4 .2 .2 .1.1.3 Flux Valve Only Pilot ' s refer ence is Observer's reference Pilot's reference Observer's reference magnetic. 1s grid. lS . 16 grid. grid . Pilot's reference is magnetic. Observer I s reference is magnetic. The last two positions are intended for emergency use in case of failure of the Flux Valve or the Stable Platform, respectively, but may be used under normal conditions. 4.2.2.1.2 Bearing Switch This three-position switch selects the distance, bearing and com mand heading signals to be displayed on the Pilot's Destination Indicator. The switch positions are:- 4 .2.2.1.2.l Normal 4.2.2.1.2.2 ADF (LF/MF) ADF (UHF) The Indicator displays the dist ance, bearing and command head ing to the target or to some ground point, as selected by the observer. The Indicator displays bearing to an ADF station. 4.2.2.2 Navigation Computer Control (Figures 15, 18-20, 47) This unit carries a Computer power switch, a Doppler power switch, a Bearing switch and interceptor position reset push-buttons. 4.2.2.2.1 Power Switch This switch is the power on/ off switch for the Navigation Com puter. 12 9201/7601/Rl Confidential Section 4 4 .2 .2 .2 .2 Doppler Power Switch This switch is the power switch for the Doppler Radar. It has three positions - off, standby and on. 4.2.2.2.3 Bearing Switch The Bearing Switch selects the bearing, distance and command heading signals to be displayed on the observer's Destination Indicator. The positions are:- 4 .2 .2 .2 .3 .1 Normal 4.2.2.2.3.2 ADF (LF/MF) 4 .2 .2 .2 .3 .3 ADF (UHF) 4.2.2.2.3.4 Set Indicator 4.2.2.2.3.4 Reset Switches Bearing, distance and command heading of the target, or of some ground point, as selected by the observer on the Target Data Dis play. Bearing of an ADF station. Bearing of an ADF station. Identical to Normal position, ex cept that circuit connections are made to allow insertion of a pos ition fix. The position reset push-buttons allow the observer, when the bearing switch is in the Set Indicator position, to correct the computed interceptor position by slewing his Destination Indicator readings to the fix values. 4 .2 .3 Dead Reckoner Units (Figures 21- 30, 48- 50) The Ground Speed Computer, Ground Speed Integrator, and Computer and Relay Unit perform most of the computations required in the operation of the Computer. These units carry no displays or controls, and require no attention in flight. 9201/7601/Rl 13 SECTION 5 OPERATIONAL PROCEDURES This section describes the control settings required in the operational use of the C~mputer. 5.1 COMPUTER ZEROING Before take-off, the Computer must be 'zeroed'. This is done in the following manner:- 5.1.l Correct Aircraft Position 5.1.1 .. 1 Operate push-button corresponding to the base where the interceptor is located. The Heading-Hold lamp on the T .. D.D. will come on. 5.1.1.2 Turn the N.C.C. Bearing switch to the Set-Indicator position. 5 .1 .1.3 Operate the appropriate push- button on the N .C .C. to set the dis tance on the Destination Indicators to zero. 5 .1.1.4 Turn the N .C .C. Bearing switch to the Normal position. 5 . 1 . 2 R ~ set Storage 5 .1.2 .1 Turn the Target Data switch on the T .D.D, to the Relative-To Aircraft position. 5.1.~.2 Operate the Mark push-button on the T .D.D. 5 .1.2 .3 After :ipproximately ten seconds, operate the Heading Hold Off push-button on the T .D.D. The Heading-Hold lamp on the T .D.D. will go out. The Computer is now prepc1,red for take-off. 9201/7601/Rl 15 Section 5 5 .2 AIRCRAFT POSITION FIXING NOTE In the following description it is to be noted that whenever the 1-Ieading-Hold lamp is on, the interceptor heading is held con- stant. This applies, of course, only if the Computer output is controlling the inter ceptor heading. 5 . 2 . 1 Over a Bas e If the interceptor flies over a base designated on the Base Selector unit, the computed interceptor position may be corrected by the following procedure:- 5 .2 .1.1 At the moment the interceptor is over the base, turn the N .C .C. Bearing Switch to the Set Indicator position. The Heading-Hold lamp on the T .D.D. will come on. 5 .2 .1.2 Select the appropriate base on the Base Selector unit. 5.2.1.3 Set the distance on the Destination Indicator to zero by operating the appropriate push-button on the N .C .C. 5.2.1.4 Turn the N.C.C. Bearing switch to the Normal position. 5.2.1.5 Operate the Heading-Hold-Off push-button · on the T.D.D. The Heading-Hold lamp will go out. 5 .2 .2 Position Fix From a Base If the interceptor receives a position fix with respect to a base desig nated on the Base Selector unit, the computed interceptor position may be corrected by the following procedure:- 5 .2 .2 .1 At the moment the Mark signal is received from the ground, des ignating the time at which the fix is correct, turn the N .C .C. Bearing switch to the Set Indicator position. The Heading-Hold lamp on the T .D.D. will come on. 16 9201/7601/Rl • idential ~ Section 5 5 .2 .2 .2 Proceed as in Section 5 .2 .1, but set the distance and bearing on the Destination Indicators to the values transmitted to the interceptor using the N.C.C. push-buttons. NOTE The fix must be in Computer grid co ordinates. 5.2.3 Over a G.C.I. Station If the interceptor flies over a G.C.I. station designated on the G.C.I. Selector unit, the computed interceptor position may be corrected by the following procedure:- 5.2.3.1 At the moment the interceptor is over the. G.C.I. station, turn the N .C.C. Bearing switch to the Set Indicator position. The Heading-Hold lamp on the T .D.D. will come on. 5.2.3.2 Select the appropriate G.C.I. station on the G.C.I. Selector. 5 .2 .3 .3 Set the target distance counter on the T .D.D. to zero, using the appropriate knob. 5 .2 .3 .4 Operate the appropriate push-button on the N .C .C. to set the dis tance on the Destination Indicators to zero. 5.2.3.5 Turn the N.C.C. Bearing switch to the Normal position. 5.2.3.6 Reset the target distance on the T.D.D. to its original value. 5.2.3.7 Operate the Heading-Hold-Off push-button on the T .D.D. The Heading Hold lamp will go off. 5.2.4 Position Fix from a G.C.I. Station If the interceptor receives a position fix with respect to a G.C.I. station designated on the G.C.I. Selector unit, the computed interceptor position may be corrected by the following procedure:- 5.2.4.1 At the moment the Mark signal is received from the ground, des ignating the time at ~hich the fix is correct, turn the N .C.C. Bearing switch to the Set Indicator position. 9201/7601/Rl 17 Section 5 5 ,2 ,4 .2 If the fix is in Computer gr id c oordinates proc e e d a s i n Section 5 .2 .3, but set the distance and bearing on the Destin ation Indic ators to the values transmitted to the interceptor,using the N .C. C. push-buttons . 5.2.4.3 If the fix is in G.C .I. station coordinates, proceed as in Section 5.2.3, but set the target distance and bearing on the T .D.D. to the values transmitted to the interceptor, using the appropriate T .D.D. knobs. 5.3 TARGET POSITION AND VELOCITY FIXING Target position and velocity fixing can be carried out in the following three ways:- 5.3.1 Automatic Fix Insertion by Data-Link To select automatic insertion of target position and velocity infor mation into the Computer from Data-Link, the following procedure is used:- 5.3.1.1 Turn the Target Data switch on the T.D.D. to the Data-Link position. The Heading-Hold lamp on the T ·.D.D. will come on. 5.3.1.2 Operate the appropriate push-button on the G.C.I. Selector · unit to select the G.C.I. station from which the target information is to be received. 5.3.1.3 Wait for a fix to be inserted into the Computer. This will be in dicated by a movement of the target position and velocity displays on the T.D.D. 5.3.1.4 Operate the Heading-Hold-Off push-button on the T.D.D. The Heading-Hold lamp will go out. 5 .3 .2 Manual Fix Insertion To insert target velocity and position information transmitted by voice from the ground, into the Computer, the following procedure is used:- 5.3.2.l Turn the Target Data switch on the T.D.D. to the Relative-To-G.C.I. position. The Heading-Hold lamp on the T .D.D. will come on . . 5.3.2.2 Operate the appropriate push-button on the G.C.I. Selector Unit to select the G.C.I. station from which the target information is to be re ceived. 18 9201/7601/Rl Section 5 5.3.2.3 Insert the fix transmitted from the ground into the Computer by operating the appropriate knobs on the T .D.D. 5.3.2.4 At the moment the Mark signal is received from the grour: 1, des ignating the time at which the fix is correct, operate the Mark push-button on the T .D.D. 5 .3 .2 .5 After a period of approximately five seconds, operate the Heading Hold-Off push-button on the T .D.D. The Heading-Hold lamp on the T .D.D. will go out. NOTE Operations 5.3.2.3 and 5.3.2.4 may be interchanged depending on whether the Mark signal is received before or after the fix information. 5 .3 .3 Relative-To-Aircraft Manual Insertion If the target position trans:r1.itted by voice from the ground is given with respect to the interceptor, rather than a G.C.I. station, a similar procedure to Section 5.3.2 is used. In ·this case, however, the Target Data switch is operated to the Relative-To-Aircraft position and the Heading Hold-Off push-button is not to be operated until approximately ten seconds after the Mark push-button is pressed. 5.4 SEl.iECTION OF CLOSE CONTROL (C.C.) OR MODIFIED CLOS.E CONTROL (M.C.C.) 5.4 . 1 With the Target Data switch in the Data-Link position, the interceptor operates in the C.C. or M.C.C. mode as .dictated by the Data-Link trans missions. In the C.C. mode, the ·interceptor is steered by the Data-Link transmissions. Data- Link control of the interceptor may be removed by turning the Target Data Switch off the Data-Link position. 5.4.2 With the Target Data switch on the T .D.D. in the Relative-To-G.C.I. or Relative-To-Aircraft position, the interceptor operates in M.C .C. mode, with the interceptor being steered in accordance with the heading command output from the Computer. 9201/7601/Rl 19 Section 5 Confidential In this mode, the interceptor may be held to the command heading automatically by the Automatic Flight Control System, or may be manually steered by the pilot. In either case the hea.ding is maintained so as to bring the command heading pointer coincident with the lubber line on the Destin ation Indicators. 5.5 USE OF A.D.F. 5.5.1 The bearing of an ADF station can be displayed on the Pilot's or Observer's Destination Indicator, by operating the Bearing switch on the PDIC or NCC, respectively, to the appropriate position. This can be done in either C.C. or M.C.C. mode. 5 .5 .2 To home on the ADF station, the heading must b_e maintained so as to bring the Relative Bearing pointer into coincidence with the lubber line. This can be done on M.C.C. mode only. (See Section 5.4) 5.6 EMERGENCY PROCEDURES 5.6.1 Flux-Valve Failure In the event of Flux- Valve failure, the Flux- Valve switch on the W .D.D. rnust be operated to the Failed Position. 5.6.1.l If magnetic heading is to be displayed on the Pilot's Destination Indicator, the assumed value of grivation must be manually set on the W.D.D"' and the Heading switch on the P.D.I.C. must be in the Normal • +. pos1l,1on. 5.6.1.2 If grid heading 1s to be displayed on the P.D.I., two alternatives exist: 5.6.1.2.l The P.D.I.C. Heading switch is operated to the Grid position. 5 .6 .1.2 .2 The P .D .I.C. Heading switch is operated to the Normal position, and the grivation is manual ly set to zero on the W .D.D. 5 .6 .2 Stable Platform Failure In the event of Stable Platform failure, the Heading svvitch on the P.D.I.C. must be operated to the Flux-Valve Only position. Both Des tination Indicators will then display magnetic heading. 20 9201/7601/Rl Confidential Section 5 5 .6 .2. 1 If grid heading is to be displayed on the W .D .D., the grivation must be set to the assumed correct value. 5 .6 .2 .2 If magnetic heading is to be displayed on the W .D .D., the gri va tion must be set to zero. 5 .6 .3 Power Failure In the event of power failure, the Computer is inoperative except for the sections concerned in providing for display on the following functions:- Grid Heading (W.D.D. and O.D.I.) Magnetic Heading (PDI) Grivation (WDD) ADF Bearing (ODI, PDI) 9201/7601/Rl 21 SECTION 6 ENVIRONMENTAL TESTS The Computer shall be subjected to the following environmental conditions:- High Temperature High Altitude Low Temperature Condensation Vibration Shock Sea level Sea level Voltage and frequency variation 6.1 HIGH TEMPERATURE - SEA LEVEL 6 . 1 . 1 Non - Opera ting Subject the equipment to an ambient temperature of + 85°C (relative humidity not more than 5%) for two hours after it has stabilized at this temperatur~. Then inspect the equipment for deterioration, mechanical failure or corrosion of any internal or external components, which could in any way prevent the equipment from meeting operational require ments during service life . 6 .1.2 Operating (Ducted or Directed Air-Cooled Equipment) (Dead-Reckoner Units) 6 .1.2 .1 The equipment shall be stabilised in an ambient temperature of +7 I 0 c in an off condition with no cooling air . 6.1.2.2 After stabilisation the equipment shall be turned on at the maximum specified input voltage, (Section 6.7) and cooling air shall be supplied in accordance with Table 1 (R.C .A. Spee. 8954602). The equipment shall then be operated for four hours maintaining the ambient temperature between +71 °c and +57°C. During this period the equipment shall be switched through a minimum of three operational cycles. 6.1.2.3 The equipment shall then be inspected for deterioration of per formance outside the limits quoted in Section 7 .0. 9201/7601/Rl 23 Section 6 6.1.3 Operating (Ambient Air-Cooled Equipment) (All units except Dead-Reckoner Units) Confidential 6 .1.3 .1 The equipment shall be stabilised at an ambient tempera ~ure of +71 °c in an off condition. 6.1.3.2 After stabilisation the chamber temperature shall be changed to 43°c and the equipment shall be turned on at the maximum specified volt2.ee. (Sect10n 6.7) The equipment shall be operated in this condition for four hours. During this period the equipment shall be switched through a minimum of three -operational cycles. 6.1.3.3 The equipment shal-i then be inspected for deterioration of per formance outside the limits quoted in Section 7 .0. 6.2 HIGH ALTITUDE 6.2.1 (Ducted or Directed Air Cooled Equipn:ient) - (Dead-Reckoner Units) 6 .2 .1 .1 The equipment shall be placed ir. a test chamber and shall be maintained in an off condition until the chamber altitude is increased to 70,000 feet. 6.2.1.2 The equipment shall then be ·operated for thirty minutes after the specified minimum warm-up period. Cooling shall be provided sufficient to maintain safe equipment operating temperatures. During this period, the equipment shall be switched through a minimum of three operational cycles. 6.2.1.3 No arcing, flash over, corona or similar discharge shall occur during this test. 6 .2. ~ .4 The equipment shall then be inspected for deterioration of perform ance outside the limits quoted in Section .7 .0. 6.2.2 (Ambient Air-Cooled Equipment) (All Units except Dead-Reckoner Units) 6 .2 .2 .1 The equipment shall be stabilised in an ambient temperature of +43°C and an altitude of 70,000 feet in an off condition. 24 9201/7601 / R 1 Con£ idential Section 6 6 .2 .2 .2 The equipment shall then be operated in this condition for four hours. During this period, the equipment shall be switched through a minimum of three operational cycles . 6 .2 .2 .3 No arcing, flashover, corona, or similar discharge shall occur during this test. 6 .2 .2 .4 The equipment shall then be inspected for deterioration of per formance outside the limits quoted in Section 7 .0. 6.3 LOW TEMPERATURE - SEA LEVEL (ALL UNITS) 6 .3 .1 The equipment shall be maintained in an ambient of - 55 °c in an off condition for a period of twenty-four hours, or until temperature stab ilisation has occured (whichever is longer). 6 .3 .2 The equipment and cooling air as applicable in accordance with Table 1 (R.C.A Spee. 8954602) shall then be turned on at the minimum specified voltage (Section 6. 7). 6 .3 .3 The equipment shall then be inspected for deterioration of perform ance outside the limits quoted in Section 7 .0. 6.4 CONDENSATION (ALL UNITS) 6 .4.1 The equipment shall be stabilised in an off condition at -10°C at sea level pressure . 6.4.2 The test chamber door shall then be opened and shall remain open until the frost has melted, but shall be closed before the moisture evap orates. 6 .4 .3 The equipment shall then be switched onQ 6 .4 .4 The equipment shall be inspected for deterioration of performance outside the limits quoted in Section 7. 0. 6.5 VIBRATION 6 .5 .1 Equipment with Isolators 9201/7601/Rl 25 Section 6 Confidential 6 .5 .1.1 Equipment normally isolated shall be subjected to ·vibrati o~ isolators in place, in each of the three planes, according to the schedule below. This test shall apply also to vibration and shock rac ks with dummy loads (or equipment) installed. CPS 5-55-5 55-500-55 DOUBLE AMPL. 0.036" MAX. ACCLN. 10 g SWEEP TIME 1-3 . min. 15-20 min. TEST TIME 15 min. 75 min. RESONANCE TEST TIME 15 min. 15 min. 6.5.1.2 The equipment then shall be inspected for deterioration of per formance outside the limits quoted in Section 7 ~O. 6.5.2 Equipment with Isolators (Alternative Procedure) 6 .5 .2 .1 If vibration and shock racks are not available, the individual units shall be vibrated without isolators in each of the. three planes according to the following schedule. CPS 5-16-5 16-500-16 DOUBLE AMPL. . 150" MAX. ACCLN. 2 g SWEEP TIME 1-3 min. 15-20 min. TEST TIME 10 min . 90 min . RESONANCE TEST TIME 15 min. 15 min. 6 .5 .2 .2 The equipment shall then be inspected for deterioration of p er formance outside the limits quoted in Se ction 7 .0 . 6 .5 .3 Equipment without Isolators 6.5.3.1 Equipment mounted to the airframe without isolators shall be sub jected to vibration in each of the three planes according t~ the following schedule. CPS 5-55-5 55-500-55 26 DOUBLE AMPL. 0 .036" MAX . ACCLN. 5 g SWEEP TIME 1-3 . min. 15-20 min. TEST TIME 15 min . 75 min . RESONANCE TEST TIME 15 min. 15 min. 9 20l/7601 / R l ,,.-,...., ' 9nfidential Section 6 6 .5 .3 .2 The equipment shall then be inspected for deterioration of per formance outside the limits quoted in Section 7 .0. 6.6 SHOCK 6.6.l Equipment with Isolators 6 .6 .1.1 Equipment normally isolated shall be subjected to shock testing with isolators in place. This equipment shall be subjected to 18-impact shocks of 10g consisting of three shocks in opposite directions along each of three axes, each shock impulse having a time duration of 11 ± l milliseconds. The 'g' value shall be within ± 10 percent when measured with a 100 cps filter and the maximum 'g' value shall occur at approximately 5 1/2 milli seconds. 6.6.1.2 The equipment shall riot suffer damage, come loose from mounting base nor subsequently fail to µrovide the performance specified in RCA (Camden) Spee. 8951017. 6.6.2 Equipment with Isolators (Alternative Procedure) 6.6.2.l This test may be performed in lieu of paragraph 6.6.1 for in dependent testing of units normally mounted on a common isolation rack with other units, if all units in each rack are not available concurrently. 6.6.2.2 The equipment shall be subjected toshocktesting without isolators. The equipment shall be subjected to 18-impact shocks of 20g consisting of three shocks in opposite directions along each of three axes, each shock impulse having a time duration of 25 ± 3 milliseconds. The 'g' value shall be within ± 10 percent when measured with a 100 cps filter, and the max imum 'g' shall occur at approximately 12 1/2 milliseconds. 6 .6 .2 .3 The equipment shall not suffer damage nor subsequently fail to pro vide the performance specified in Section 7 .0. 6 .6 .3 Equipment without Isolators 6 .6 .3 .1 Equipment mounted to the airframe without isolators shall be sub jected • to shock testing according to the procedure in paragraph 6 .6 .2. 6 .6 .3 .2 The equipment shall not suffer damage nor subsequently fail to provide the performance specified in Section 7 .0. 9201/7601/Rl 27 Section 6 Confidential 6.7 VOLTAGE VARIATION AND FREQUENCY 6.7 .1 The equipment shall be subjected to voltage and frequency variation over the following ranges: A.C. Voltage D.C. Voltage 115 Volts 400 c/ s 28 Volts 108 to 121 volts 396 to 404 c/ s 26 to 30 volts The D.C. voltage shall have ripple contents as follows:- 400 cps 1200 cps Total less than lOo/o peak to peak. less than 0 .2% less than 1.5% 6. 7 .2 The equipment shall' be inspected for deterioration of performance outside the limits quoted in Section 7 .0. 6.8 The for .egoing environmental tests have been extracted from R.C.A. (Camden) Spee. 8954602. 28 9201/7601/Rl o:d.f 'den tial SECTION 7 ACCURACY REQUIREMENTS The Computer shall perform to the limits of accuracy set down in RCA Specification 8951017. These limits are as follows: 7 .1 SYSTEM The Navigation Computer error shall not exceed a value of two miles per hour + 1/2% of distance travelled. This error does not include display errors of the Destination Indicators. 7.2 WIND DATA DISPLAY 7 .2 .1 Grid Heading Interceptor grid heading shall be displayed with an accuracy of ± 1/2 degree. 7.3 TARGET DATA DISPLAY 7 .3 .1 Target Distance Display 7.3.1.1 Automatic Input Target distance as inserted automatically by the Data-Link Coupler shall have an accuracy of display of ± 1 nautical mile. 7.3.1.2 Manual Input Target distance as inserted manually shall have an accuracy of display of ± ' 1 nautical mile. 7 .3 .2 Target Bearing Dispaly 7.3.2.1 Automatic Input Target bearing as inserted automatically by the Data-Link Coupler shall have accuracy of display of ± 1 degree. 9201/7601 / R 1 29 Section 7 7 .3 .2 .2 Manual Input Target bearing as inserted manually shall have an accuracy of display ± 1 degree. 7 .3 .3 Target Speed Display 7 .3 .3 .1 Automatic Input Target speed as inserted automatically by the Data-Link Coupler shall have an accuracy of display of ± 1 knot. 7 .3 .3 .2 Manual Input Target speed as inserted manually shall have an accuracy of display of ± 1 knot. 7 .3 .4 Target Track Display 7 .3.4.1 Automatic Input Target track as inserted automatically by the Data-Link Coupler shall have an accuracy of display of ± 1 degree. 7 .3 .4 .2 Manual Input Target track as inserted manually shall have an accuracy of display of ± 1 degree. 7 .3.5 Time-To-Go 'Time-to-go' shall be displayed with an accuracy of± l percent of full scale. 7.4 DESTINATION INDICATOR DISPLAYS 30 9201/7601 / R 1 r ,. Confidential , Section 7 7 .4 .1 Aircraft Heading Interceptor grid or magnetic heading shall be displayed with an accuracy of ± 1/2 degree. 7 .4 .2 Distance to Target or Destination Distance to target or destination shall be displayed with an accuracy of ± 1 nautical mile. 7 .4 .3 Bearing to Target, Destination or A.D.F. Station Bearing to target, destination or A.D.F. Station shall be displayed with an accuracy of ± 1/2 degree. 7 .4 .4 Heading Error Heading error shall be displayed with an accuracy of ± 1 degree. 7 .5 OUTPUT SIGNALS 7 .5 .1 N/S Di~tance from Grid Zero N/S distance from grid zero shall be transmitted with an accuracy of ± 8 .5 nautical miles. 7 .5 .2 N/S and E/W Ground Speed N/S and E/W ground speed shall be transmitted with an accuracy of ± 10 knots. 7 .6 The foregoing accuracy figures do not cover every Computer display or output signal. The figures quoted ~ave been extracted from R.C.A. (Camden) Spee. 8951017. 9201/7601 / R l 31 SECTION 8 ACCURACY The following para.graphs will deal with the Computer accuracy at room tempera~ure and will then mention the effects of environrnental testing. Since environmental testing of the Navigation Computer was not very far advanced at tern1ination, none of the units was co1npletely tested .under the environmental conditions listed in Section 6 . 8 .1 ROOM TEMPERATURE 8.1.1 - Interceptor grid heading display on W.1).D. - the required accuracy of ± 1/2 degree "vas obtained. 8.1.2 Target distance display - the requir~d accuracy of ± 1 nautical 1nile was obtained.. 8 .1 .3 Target bearing display - the required accuracy of ± 1 degree was obtained. 8 .1 ~4 Target speed display - the required· accuracy of ± 1 knot was obtained. 8.1.5 Target track display - the required accuracy of± 1 degree ,vas obtained. 8.1.6 Time-to-go display - the required accuracy of ± 1% of full scale was obtained. 8.1.7 Interceptor heading display (on D.I.) - the required accuracy of± 1/2 degrre was not obtained. (See paragraph 8.2.3). 8 .1.8 Target or destination dista·nce display - the required accuracy of ± 1 nautical mile was obtained. 8.1.9 Target destination or A.D.F. bearing display - the required. accuracy of ± 1/2 degree was obtained. ~.l .10 Heading error display - the required accuracy of± 1/2 degree \Vas not obtained. (See paragraph 8.2.3). Section 8 8 .1 .11 N/S distance from grid zero - the requi red a ccuracy of ± 8 .5 naut ical miles was obtained. 8.1.12 N/S and E/W ground speed - the required accuracy of± 10 knots was obtained. 8.1.13 The inaccuracies at room temperature mentioned 1n paragraphs 8.1.7 and 8.1.10 were caused by torsional wind-up in c erta in gear passes . This fault was apparent in the first two systems only, as subsequent re design eliminated this difficulty. 8.2 EFFECTS OF ENVIRONMENTAL TESTING This section will deal with accuracy figures on a unit basis. 8 .2 .1 Wind Data Display This unit displays the Interceptor grid heading mentioned 1. n para graph 8.1.1. 0 8 .2 .1.1 Low-Temperature Test -55 C This unit has not been subjected to a low-temperature test. 8 .2 .1.2 High-Temperature Test+ 71 °c This test was carried out before R.C.A. changed the temperature figure to +43 °c. This test did not effect the heading accuracy figure of ± 1/2 degree. 8.2.1.3 High-Altitude Test - 70,000 feet This test did not affect the heading accuracy figure of ± 1/2 degree. 8 .2 .1.4 Condensation Test This unit has not been subjected to a condensation test. 34 9 20 l / 7 60 l / R l Confidential Section 8 • 8.2.1.5 Vibration Test This unit was not operational during the vibration test. After the test was completed the unit was switched on and the heading accuracy was found to be to the required standard. 8.2.1.6 Shock Test This unit has not been subjected to a shock test. 8 .2 .2 Target Data Display This unit displays the following data:- Target distance Target bearing Target speed Target track Time-to-go 8.2.2.1 Low-Temperature -55°C (Para. 8.1.2) (Para. 8,1.3) (Para. 8.1.4) (Para. 8.1.5) (Para. 8.1.6) This unit has not been subjected to a low-temperature test. 8 .2 .2 .2 High-Temperature Test+ 43°C This unit has not been subjected to a high-temperature test. 8.2.2.3 High-Altitude Test - 70,000 feet This unit has not been subjected to a high-altitude test. 8 .2 .2 .4 Condensation Test This unit has not been subjected to a condensation test. 920 l /760 l /Rl 35 Section 8 8 . 2 . 2 . 5 Vibration Test This unit was not operational during the vibration test. After the test was completed the unit was switched on and the accuracies were found to be within the limits required. 8.2.3 Destination Indicators These units display the following data: Interceptor heading (para. 8.1.7) Target or destination distance (para. 8.1.8) Target, destination or A.D.F. bearing {para. 8.1.9) Heading error (para. 8 .1.10). 0 8 .2 .3 .1 Low-Temperature Test - 55 C This unit displays Interceptor heading, bearing and heading error to the required accuracy down to -10°C, and the target or destination dis tance down to -30°C. To obtain the required accuracy down to -55°C minor redesign of gear passes, (to preserve mechanical freedom at low temperature) would be required. 8.2 .3 .2 High-Temperature+ 71 °c This test was carried out before R.C .A. changed the temperature figure to +43°C. This test· did not cause the Indicators to lose their required ac- curacy. 8.2.3.3 High-Altitude Test - 70,000 feet This test did not cause the Indicators to lose their required ac- curacy. 36 9201/7601 / R 1 Section 8 C8n!id e n ial 8.2.3.4 Condensation Test These units have not been subjected to a condensation test. 8 .2 .3 .5 Vibration Test These units were not operational during the vibration test. After the test was completed the units were switched on and the accuracy of the displays was found to be to the required standard. 8.2.3.6 Shock Test These units were not subjected to a shock test. 8 .2 .4 Ground Speed Integrator This unit provides the following outputs: N/S distance from grid zero (para. 8.1.11) N/S and E/W ground speed (para. 8.1.12) 0 8.2.4.l Low-Temperature Test -55 C The integrator held the required accuracy down to -50°C. To ob tain the required accuracy at -55 °C the amplifier gain will need to be increased . 8.2 .4.2 High-Temperature Test +71 °c This test did not cause the Integrator to lose its required accuracy . 8.2.4.3 High-Altidude Test - 70,000 feet This test did not cause the Integrator to lose its required accuracy. 8.2.4.4 Condensation Test This unit has not been subjected to a condensation test. 9201/7601/Rl 37 Section 8 Confidential 8.2.4.5 Vibration Tests This test did not cause the Integrator to lose its required accuracy. 8.2.4.6 Shock Test This unit has not been subjected to a shock test. 8 .2 .5 System The required system accuracy figurP of two miles per hour + l/2o/o of distance travelled has never been checked under environ1nental con ditions. 38 9 20 l / 7 60 l / R 1 C • n1tq e:µtial SECTION 9 PROBLEM AREAS Several problems were encountered during the development of the Astra Computer. These problems involved the following components. 9.1 RELAYS 9.1.1 Intermittent Pin Contact Intermittent pin contact was a major source of trouble. This fault was attributable to the fact that contact pressure between pin a~d socket was insufficient to remove the oxide film on the socket when the relay was inserted into the holder. This fault was overcome in two ways:- ( 1) Gold-plated socket contacts were obtained. These contacts exhibited a marked improvement in perform ance since the amount of oxide formed was negligible. (2) Sockets produced by a different manufacturer, having higher contact pressure, were used. 9 . 1.2 Current Leakage Current leakage was detected in relays of a particular manufacturer. This fault manifested itself as a leakage path (less than SOOK) across relay contacts which were required to be open-circuited during certain modes of operation. When the relay contacts were placed in the input signal lines to a summing amplifier, the effect of the small current flowing across the relay contacts was to modify the signal input. This caused the servo-loop to drive to an incorrect null position. Errors of up to eight miles in range have been noticed due to this condition. It was not possible in all cases to remedy this condition by circuit changes. Where possible however, amplifier signal input lines not used during a particular mode of operation were grounded for the duration of the mode. This condition was eliminated by changing to relays of a different manufacturer. 9201/7601/Rl 39 Section 9 In a number of circuits in the Computer , the slider voltage of a potentiometer is compared with that from another potentiometer connected across the output winding of a resolver. Without compensation the changing phase-shift of the resolver, due to changing temperature, results in a decrease in sensitivity of the servo-loop and also an increase in the temp erature of the motor. It was found that if a temperature- sensitive net work having a suitable negative rate-of-change is connected in series with the resolver input, then partial compensation is achieved, and the phase of the resolver output remains approximately constant over the temperature range stated above. A thermistor network having approximately this char acteristic is used in series with each resolver in the Astra system. The in-phase input to each servo-loop includes a phase-lead capacitor adjusted to give a good null at the summing junction of the amplifier, which remains good over a temperature range O 0 c to 60 °c. In the ' interests of interchangeability a standard thermistor network has to be applied to each resolver, giving a first-order approximation to perfect compensation. In a .. 1 individual application where a thermistor network can be tailored to a particular resolver, a reasonably accurate degree of compensation can be achieved over a temperature range -50°C to +50 °c. A rod type thermistor was used in Astra, and was mounted remote from the resolver concerned. During initial warm-up the thermistor reached a thermal steady-state long before the associated resolver. During this period errors in servo outputs up to O .3 or O .4% of full scale were noticed. A change to a wafer type thermistor mounted directly on the res olver was envisaged which would ensure that the thermistor and resolver ambient temperatures remain identical at all times. This change was implemented on similar circuits 1n other equipment and was found to be quite satisfactory. 9. 2 TEMPERATURE EFFECTS ON AMPLIFIER GAIN The gain of the amplifiers used in the Astra Computer is constant over a temperature range o0 c to +20°C. As the temperature increases to+ so 0 c the gain increases by 3.5 db. As the temperature decreases to -55°C the gain decreases by 12 db. In addition, the phase shift of voltage through the amplifiers is approx imately 90 ° in the range 0°C + 80°C, falling to approximately 45° at -55°C. The effect of this change is equivalent to a change in · gain of approx- imately 3 db. , 40 9201/7601/Rl Confidential Sec t ion 9 The effect of these two conditions is to decrease the sensitivity of the amplifier at low temperatures, and to increase the sensitivity at high temperatures. If the gain is increased to offset the de c rease in sensitivity at low temperatures, then the associated servo-loop hunts at high temp eratures. It was intended to increase the overall gain by adding a preamplifier and also to incorporate a thermistor network at the input of the amplifier. This network would hold the overall gain approximately constant with temp erature. No compensation for phase- shift was considered necessary as its effect on the overall gain was comparatively small. 9201/7601/Rl 41 SECTION 10 STATE OF DESIGN 10.1 The state of design of the Astra-Navigation Computer was well ad vanced at termination. This is evident from the following facts:- 10.1.1 R.C.A. (Montreal) had completed acceptance tests on two systems. 10.1.2 A roof-test on one system at Camden, N.J. was well under way. 10 .2 System design was virtually complete. It remained only to incorporate the Aircraft Relative Fix facility. This facility would not have been re qu_ired until the £if th sys tern. 10 .3 The remaining design problems were limited to ensuring that' indiv idual units passed the environmental tests listed in Section 6 .0. 9201/7601/Rl 43 Confidential SECTION 11 CONCLUSIONS 11.1 Although the Astra-Navigation Computer was designed to be compatible with the Arrow and the Astra fire control system, it possesses the follow ing £ea tures which make its immediate uBe with other systems practicable:- 11.1.1 It is a self-contained navigation system requiring only the usual in puts as set down in Section 2.0. 11.1.2 Since the Computer consists of several small units ( 1.2 cubic f eet total volume) its incorporation into other aircraft should present no prob lem. In addition three of the largest units require no attention in flight and can therefore be located in any_ convenient position. 11.1 .3 The overall weight of th<:: Computer is only 80 pounds. 11.1.4 The maximum power requirements of the Computer are:- 9201/7601/Rl 120 watts of 400 cps at 115 volts 110 watts of D.C. at 28 volts. 45 ti~ . Figure 1. Astra l Computer 9201/7601/Rl 47 Confidential Figur e 2. Destina t ion Indicator and Wind Data Display 9201/7601/Rl 49 ;nfid·e.nti Figure 3 o Des tin ation Indicator - Face 920 l / 760 l / Rl 51 ential Figure 4. Destination Indicator - Exploded View 9201/760 l / R 1 53 Figure 5 9201/7601/Rl -t- ' I tJ:i-~'~ --- // • -- - -- 3~ ------- - --- •-I PAN~f-- C.UTOUT 55 // 64- D IA fRoN'T' 01' PIINEt. r-- 64 .. - - ---- - - - ro ~,-,cF o,- Rccc,,:,r,qc1.~ t "( h /e .. I ~ r(l . ~::::,1-,e P"<~-( ~"roe_ ~0'2.\.- 1e,-'!:,'2- P,..J 0 QI 0 vi&J \..) c:-.eE.<;::.to..) ~ b..::!.~ WEIGHT- 3LB., 2oz. Figure 20 Figure 20 - Navigation Computer Control - Outline Drawing 85 85 Figure 21. Dead Reckoner Units 9201/7601/Rl 87 Figure 22. Ground Speed Computer - Internal 9 20 l / 7 60 l / R l 89 I . ~ • < . ~ . .~.-:...,. "· -~ . Figure 24. Ground Speed Integrator - Internal 9201/7601/Rl 93 Confidential Figure Z 5. Ground Speed Integrator - Internal 9201/7601/BJ 95 9201/7601/Rl ~ . ...,., ,~t>~')· . .,.:4 ~"i,' \~'!'{-.. "·>< ·~~~: .. -. ~\. ·. f.., .. ► .. ~, .. -,& ' f ." :;. . .rt_~:~K\~ • . . ) t '\ =~ _.,. •· .. .. Figure 26. Computer and R e lay Unit - Internal 97 Con£ idential I I I I I I Figure 27. Computer and Relay Unit - Internal I 9201/7601/Rl 99 I Figure 28. Dead Reckoner Mounting Tray ________ ,, ________________________________ __, Figure 29. 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' /./ ( BLOCK 6. lN FOR b1ATlON FLOW DiAGRAMS LIST OF SYMBOLS FIGURE:34 Figure 34 - Block and Flow Diagram Symbols - ·-- 111 6 F~Or<1 0oPPLER \(J 60 F,.c,,-, O..L.C. llal r"o"' c,i:.u Ya6S1n~ ... ., _Vca6 '4S l'tl:<9 AIRCRAFT e Vo.6 WIND SOLUTION GRID HEADING 8r GRIVATION SOLUTION COMMAND HEADING SOLUTION ~--,---,xi------- ·TARGET DATA SOLUTION AIRCRAFT TO TARGET OISTANC.E & BEARING SOLUTION J'A-.Gf.T Tot,,C.IC' T~tt J( Sf~VOi-+l---41 lOOP t VtC> / I I I T4~C.E.'I" Si=>EE.D TA~C.l!.T Ol~TAN<:I!. 8"-SL 5€l!"'r-..,...--~ TOR 1eo•-Te tajF'lilOM • C.,'1-<./, __ S_t_'"Cj ~0:0M C..~.---1 + l---+'"-+--+--+--1--' ( ie.o•- r,;, , 9 ) X'la. SLEWIN SIGNAL TO STABLE PLATFORM 1----4--:CHc::a.:::.:..:..-n FR.OM n U lC VAL-Ve. I ~~'l' · "a..q l - 1- - / ~ .-" / , . .., , POi :H.LOW 1~'2. '("r-.iaTS.16r'4QL ,:-~0"1 A-0-C. - PUSH BUTTON Ho..q c.. Dat :::>051nor1 ------------J UP FIGURE 41 DISPLAY I ' 7' ) I I ASTRA CO~t1PUTER - lf'1FORMATtON FLOY/ OIAGRA~.t FOR DESTINATION INDICATORS ( P IL OT 1S 8 OBSER\/ER 1 S ! Figure 42 Figure 41 - Destination Indicator Information Flow Diag-ram !25 125 9201/7601/Rl .P.R. ~tRVO RI!) EA.DIN 1 ► FOllO'rl ~ ~ ~- 2 Bts 0 llP • . - G H 6 ' ~. u x-Vr-;1.ve. S!~VO GRIVATIOM ' ~~ - FoLLck/ • + . --}r--{~- l~ t,5J-~ .. UP I .. - 0 Hfllv!)St.T I •• ~ - l .4ct.rn To -,Syr.Jc,'l~i;-1 ----!,," _ _ P,D-I.C. , SIi? &, cos o;: (1/09 -Hct9} -----------;.tc... - --- ----.:.l j~5 Sin _(rl'l)c:,- l-/ et..9 ) FRot1 6.s.c. --;,,~------------------'-------- Poi, il ' Wsc..os ( wD9- licz..9 -==rc:.;;ll· •J ro G .s . c. . •. ~../D9 F'~OM 6,5 ,C., (HtlD col'ISTtv-17 11v DaP P. o~ ·11aTJE) 8EloW 132 KNCJT StuNAI. r ► r~OM R,l), C, l SERVO } ' ... MOrOii: I . - I , .. FIGURE: 42 W IN!) 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G ,e1!) /"JoJ>c - 1-10.q ~t.ux Vtrt\le orvt.V rJoDE- ;,fq,m OP£J;J.r;r£S ·A• co,vrJ:Jc,s 1r1 J:/..<./;( V~L.vG Or-lt.f 1"7o])E t:'/H'/ON!: O.C-tJ/E 3- tNP~r S1(;,v,9LS ·ASTRA COMPUTER INFORMATION FLOW DIAGRAM FOR PILOTS DESTINATION l~JDICATOR COt-JTROL '-------------------------------- -----------~----------------------- - - -------------- Figure 46 Figu r e 46 -Pilot' s Destinati on Indicator Control Flow Diagram. 9201/7601/Rl 135 135 Confidential ~ y,( ___,,.. -: --"T ~ f. (l t,, • -.;,.:_· ~ - -------- -------------- - --~-- -- iJ :, '-YI 0 - ... --· :; Figure 47 9201/7601/Rl ., ADJ:-: /Lt=/t1~) BEA~IH~ FRQt"7 R~N·6 ·1s To 0-DJ ! . ~ • w1TCH11---------~-~1NrE"R / Ha..9-Sto..9/ /:ROt-1 D,l.,C, ~ ( NO~/"JAL i, s~r 11'/DICATO~) -=.:! ==~ I · /ND/C, ' '26 Vet<: ---~~-----1sw, rc!f ; It-, --i:5'--1 ~s St.cw;+-_ -~-To c R,ll Con/ Tli-;vl. ' 2b Vczc A \I-"! I L.~ B! f 0"''!..j t/Y T,Lf ~ S ;: ... I .... ,.,.., ,,.. '' .... . "':::, _.,_._,,_..., "i::: '-.. ,/ I 1 ~ ,... , .. I ..,pi ,• I / ._.,. ~ .,-- . /4 '28 V, DC .C,VA! L~ sis,\ ( OtvL'j / ,V TI-!= ) \ 4DF "..,?o!)ES ASTRA COMPUTER IN FOR~1iATION F LOV/ D l AG RA ~j NAVIGATION CO rvlPUTER CONTR OL Figure 4 7 - Navigation Computer Control In.formation Flow Diagram 137 137 - 9201/7601/Rl OPPlEle ., .. 6' F,:ore IM$6'1f:r10N C.Ru.tieS if/G'S~ /"J!:MOR.~es To BE DE-ErvE 1!flG,1$£7) Figure 49 141 FIGURE 49 r- ............. "-. , _, -, --r-"\ (, ''--, ' ;-- -· =- r< INFORMATION FLOvV DIAGRAM FOR. GROUND SPEED INTEGRATOR Figure 49 - Ground Speed Integrator Information Flow Diagram. 141 9201/7601/Rl - ~ • • ... (, - +' r-• { tf -1-__<)i ) ( a +ll '-1 Bjaq) - O.t'] G.S,C,. I - ... Sel!!Vo H-_ ,-,+, ... + ... . I - LOOP - ♦ I - I Btc:t.01 _ {,i 4, - I - • I +· -H - I I -L u.saL\la - cos I!, , , ~ . . .. . H~ '?c~ Ha.CJ) To OD1/Px,z VIA DLC ct9c -Het.c;) TO ltFCS ( /1UTOPIJ.OT j cos A ;o r.v.7:J ~ S11, /3 Jt: • V t G 51"~ - .. Sl!l?VO _ . ' . 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Ol.9.S Ya.qs, FIGURE 50 ASTRA CO~APUTER - INF FOR COMPUTER 8t' OR~AATION FLOW DIAGRAM E.LAY UNIT R Figure 50 - Computer and R elay Unit Information F low Diagram 143 REVISION DESCRIPTIONS APPROVAL THESE DRAWINGS AND SPECIFICATIONS ARE THE PROPERTY Of RADIO CORPORATION OF AMERICA, AND SHAH NOT RE REPRODUCED, Oi COPIED. OR USED AS THE BASIS FOR THE MANUFACTURE OR SALE OF APPARATUS WITHOUT PERMISSION, PLATFORM «UÛN-MEWT 28 V, EMER |E> 0 ' CTC tCflSl «40! FÎR40» W(N/C; Hog; FROM grm pu=aro RM J402-K imm J40I-H K401 FLUX l/VRLUE. SET GF?^ NORM AU M 5 \y (EMER.) ER. è K 401-0 IZOODH ^FWAmON J4ÛI-P tfarn HAKJP SET GUP, <5WP, H&MP -SET W'fNlfP SFEEC? t CrOOO’A f WfMP PlRECTlOXl HflMD T £216 VCI042! J4CN-S r4U- GMP d"‘ "s" \OOOC 2S V/ " ^ N4 O, " mv* -AAA MC U CLASSIFICATION TITLE- UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES RADIO CORPORATION^ AMERICA A-Ol' *• CAM SEN. N. J.V TOLERANCES ON 3 PLACE DECIMALS 2 PLACE DECIMALS BASIC DIMENSIONS ALL EXTERNAL THREADS TO K CLASS 2A BEFORE PATINO AND CLASS 2 AFTER PLATING* AU INTERNAL THREADS TO BE CLASS 28, UNLESS OTHERWISE SPECIFIED. / MAT’l,, FIN., & HT. TREAT. AS NOTED ANGULAR DIMENSIONS ±'ft see fHiRcn: SPEC.1 FOR STOCK, TOEERAN SHEET FOR MFO. SPEC. SEE DWG. APK-A-TEX 10! J. H. WEIL CO.. PHILA. PA «CA »4*!2-B7-700 PP'WTHO IN U S. A KfOO. REQ.'D. REQ-O. REQ0. ITEM ' OR SYMBOL PART NUMBER DESCRIPTION — .■■•«*— 504 503 502 501 LIST OP MATERIAL %J* . . *4—! pHfe-—Æ UP TO 6 ±,Q2 ABOVE 6 TO 24 ±.03 ABOVE 24 ±.06 T~ DRAFTSMAN c:jP>C ■ n ■ ■< ■ 1 • » ---f- DATE JAf-- p'7 DESIGNER ■ ' - - CHECKER v " -V-- ENGINEER , ' I; V ■ ' t GPOGP Oft PART NEXT ASS'Y. USED ON NEXT ASS’Y, FINAL ASS Y. APPUp ATION QTY. REQ'D. • / . APPROVAL REVISION DESCRIPTIONS GND • -f-Wv - | R SI i J LVv\- 50K ; î-.GO KL^OTlk vyt3 HAN O C e -r AA/V UlMeçj. w -VVArXSÛÎA TfV t CV.C -rj. 5K r,Ms CA'-.C wwy » t&mmmm ——nwwjiiMiywrni smita ITEM OR SYMBOL CLASSIFICATION DATE /A- j DRAFTSMAN UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES RADIO CORPORATION OF. AMERICA CAMDEN, N X. TOLERANCES ON DESIGNER 3 PLACE DECIMALS 2 PLACE DECIMALS BASIC DIMENSIONS CHECKER ENGINEER All EXTERNAL THREADS TO BE CIASS 2A BEFORE PIATING AND CLASS 2 AFTER PLATING» ALL INTERNAL THREADS TO BE CLASS 2B, UNLESS OTHERWISE SPECIFIED. DWG. NO. MAT'L., FIN-, & HT. TREAT. AS NOTED ANGULAR DIMENSIONS ± % SEE PURÇH. SPEC. FOR STOCK TOLERANCE SEE DWG. 96400 J. H. WEIL CO.. PHILA.. PA KEQ'D. REO'D REQD. REQ D. 504 503 502 501 UP TO 6 ±.02 ABOVE 6 TO 24 ±.03 f ABOVE 24 ±.06 PART NUMBER DESCRIPTION LIST OF MATERIAL rHr—tr^— ZONE REV. p~ -r-y ~ • - / De-} 1 4 < — r-* .1 .; __ . ... \ csoi ■-- Vv J - &A1 f . G >■ ■■■-. ; ■ ■■ y. il T 7^—r L 1 : ? . 1 . .. / ;.yÿ. ■ —, ... i i i • T T 1 A S5o4 C5I3 i '■CSC.LOASÏ • Jj T ’ A.T?. ]±O' 'i ■ —. 4 • - ——- —- - ——~ : • T :; "'f’ & A . 1 .. ; • t *V ÿ ï 1 fe-±*ï ■ T U ! ■ : •• . .. . ' . - ■ t GROUP OR PART NEXT ASS'Y. USED ON NEXT ASS'Y. FINAL ASS'Y. APPLICATION QTY. REQ'D. REVISION DESCRIPTIONS APPROVAL ZONE DtAwfi&s AND SPECIFICATIONS ARE THE PROPERTY or RADIO CORPORATION OF AMERICA, AND SHALL NOT RE DUCED, OR COPIED, OR USED AS THE BASIS FOR THE MANUFACTURE OR SALE OF APPARATUS WITHOUT PERMISSION. o/-é> W-PD - -84 03 OS C- JB 202 /fs v //su a 60/ (SM£*, err • U J? 6 O 4L CT CAMDEN, M. j. P.ftO-3 /OAS C/Of’ TOLERANCES ON 3 PLACE DECIMALS 2 PLACE DECIMA'LS BASIC DIMENSIONS ü&svsnessE All EXTERNAL THREADS TO BE CLASS 2A BEFORE PLATING AND CLASS 2 AFTER PLATING, ALL INTERNAL THREADS TO BE CLASS 2B, UNLESS OTHERWISE SPECIFIED. DWG. NO MAT'L., FIN., & HT. TREAT. AS NOTED ANGULAR DIMENSIONS ± % SEE RURCH. SPEC FOB STOCK TOLERANCE SHEET FOR MFG. SPEC SEE DWG. 96400 J. H. WEIL CO.. PHIL.A.. PA REQ'D. REQ'D REQ'D. REQ'D. 504 503 502 501 UP TO 6 ±.02 ABOVE 6 TO 24 ±.03 ABOVE 24 ±.06 ■ r - - i/.'/S /" 1/r/A? A AY o sot? W , . t '< T ' FS. k A! ” " 2i4 i os>o t 1 Y DRAFTSMAN CS-P

Termination report: the ASTRA-1 navigation computer. Report 9201/7601/R1

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