ARMY MIL-P-70444-1983 PROCESSOR SIGNAL SIGHT HELICOPTER HEAD UP SUBSYSTEM M76《M76式直升机平视显示子系统信号处理器》.pdf

1、c MIL -E-5 40 O Electronic Equipment, Airborne, General Specification for MIL -E-60 51 Electromagnet i c C anpa t i bi 1 i ty Requ i remen t s , Systems MIL-1-8500 L- Interchangeability and Replaceability of Components Parts for Aircraft and Missiles MIL-Q-985 8 Quality Control Requirements MIL-F- 1

2、3 926 Fire Control Materials: General Specification Governing the Manufacture and inspection of FSC 1270 MIL-P-70444 (AR) 30 November 1983 MILITARY SPECIFICATION PROCESSOR, SIGNAL, SIGHT, HELICOPTER HEAD Up SUBSYSTEM: M76 This specification is approved for use by the U.S. Army Armament, . Munitions

3、and Chemical Command, and is available for use by all Departments and Agencies of the D.epar tment of Defense. 1. SCOPE. 1.1 Scope, This specification contains quality assurance provisions and preparation for delivery for the Processor, Signal, Sight, Helicopter, Head Up Subsystem: M76. 2 APPLICABLE

4、 DOCUMENTS. 2.1 Government documents. - 2.1.1 Specifications and standards. Unless otherwise specified, the following specifications and standards of the issue listed in that issue of-the Department of Defense index of Specifications and Standards (DoDISS) specified in the solicitation, form a part

5、of this specification to the extent specified herein. SPECIFICATIONS MIL ITARY Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Commander. US Arm Armament Research and Development Center, Attn. D

6、RSMC-QA, Dover, New Jersey 07801 by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document or by letter. THIS DOCUMENT CONTAINS 3 PAGES, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-

7、,-,-NIL-P-704LILI LE = 7777706 035LI467 3 MIL-0-13830 MIL-L-25467 MIL-M-38510 MIL-S-45743 MIL-S-46844 MIL-W- 63150 MIL- S- 7 O 4 4 2 STANDARDS MILITARY DOD- STD- 10 0 MIL- STD- 1 O 5 MIL-STD- 461 MIL-STD- 704 MIL- STD- 7 81 MIL-STD-810 MIL-P-70444 (AR) Optical Component for Fire Control Instrument,

8、General Specification Governing Assembly and Inspection of Lighting, Integral Aircraft Instrument, General Specification for Microcircuits, General Specification for Soldering, Manual Type, High Reliability Electrical, Electronic, Instrument, Communication and Radar for Aerospace and Control Systems

9、, Procedure for Solder Bath, Soldering of Printed Wiring Assemblies, Automatic Machine Type Weapons and Support Material, Standard Quality Assurance Provisions for Sight, Helicopter, Head-Up Subsystem: M76 Engineering Drawing Practices Sampling Procedures and Tables for Inspect ion by At t r i bu te

10、s Electromagnetic Interference Character- istics Requirements for Equipment Electric Power, Aircraft, Characteristics and Utilization of Reliability Design Qualification and Production Acceptance Tests: Exponential Dis t r ibut ion Env ironmenta 1 Test Methods 2.1.2 Other Government documents, drawi

11、ngs and publications. The following other Government documents, drawings and publications form a part of this specification to the extent specified herein. DRAWINGS US ARMY ARMAMENT RESEARCH AND DEVELOPMENT COMMAND (ARRADCOM) 11780002 Signal Processor 17780014 Functional Block Diagram (Copies of spe

12、cifications, standards, handbooks, drawings, and publications required by manufacturers in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting officer.) 2 Provided by IHSNot for ResaleNo reproduction or networking permitte

13、d without license from IHS-,-,-MIL-P-70Ll44 12 7799906 0354Llb 5 _. _- MIL-P-70444 (AR) 2.1.3 Order of precedence. In the event of a conflict between the text ofThis specification and the reference cited herein, the text of this specification shall take precedence. 2.2 Other publications. The follow

14、ing documents form a part of this spec%f ioation to khe extent specified herein: American Society for Testing and Materials. (ASTM). ASTM - D3951 - Standard Practice for Commercial Packaging. 3. REQUIREMENTS. 3.1 Materials. Materials shall be in accordance with the applicable drawings, specification

15、s and standards. 3.2 Parts. A11 parts shall comply with applicable drawings, specifications, and standards. 3.3 Head up display signal processor (SP). The SP shall comply with all requirements specified on Drawing (Dwg) li.780002, all associated drawings, and with all requirements specified in appli

16、cable specifications and standards. The Sp covered by this specification shall be configured for use on the AH-1S series helicopter and is part of MIL-S-70442 (Sight, Helicopter, Head-Up Subsystem: M76). The SP shall process input signals from the AH-1 helicopter . The processed- signals shall then

17、be sent to the Head-Up Dispaly (HUD) Dwg 11780001 for pilt use. The symblogy displayed shall be in accordance with Table I (Symbology VS. Operating Mode). For functional block diagram of the SP that shows the general signal fow of the CP, see Dwg 11780014. 3.3.1 Major components list. Major componen

18、ts of the SI? are as follows: Nmenclature Drawing Chassis Assembly, SP 11780i83 CCA, CPU 11780151 CCA, Input Processor 11780162 CCA, Output Processor 11780178 Power Supply, Low Voltage 117 80 208 3.4 - Characteristics, 3.4,l Electrical. 3.4.1.- -Electrical signal interface. The HUD signal interface

19、with the AH-1 series helicopter shairbe as defined in Appendix A. 3.4.1.2 Electrical powel:. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-70444 12 7777706 0354467 7 MIL-P-70444 (AR) 3.4.1.2.1 Steady state. The electrical service conditions

20、 will be in accordance with MIL-STD-704, Category “B“ utilization equipment, except that the transient frequency limit of Figure 5, limit 4 in MIL-STD-704 shall be 240 Hz. The equipment shall meet specified requirements of MIL-STD-704 for the types of power specified herein, and shall give specified

21、 performance when supplied with electrical power having these characteristics and limits. a. 28 V dc for SP primary operating power, maximum available power shall be 76 watts for test and 70 watts for normal operation. b. 115 V ac 400 Hz signal phase for SP cooling fan and HUDS elapsed time indicato

22、rs; maximum available power shall be 15 volt-amperes. 3.4.1.2.2 Electrical power interruptions. Manentary power interruptions to the SP will be experienced when external primary power is switched to helicopter power or when switching from one helicopter power bus to another. requirements of this spe

23、cification within 5 seconds after such momentary power interruption as defined in MIL-STD-704. The SP shall return to specified performance within fifteen seconds (10 seconds desired) after any similar momentary longer term , interrupt ion . 3.4.1.2.3 Polarity reversal. Canponents that receive dc pr

24、imary or instrument power shall not be damaged when subjected to a polarity reversal due to inadvertant polarity reversal of the dc power. SP operation shall return to normal after normal polarity is restored, within the constraints specified for electrical power interruptions specified in 3.4.1.2.2

25、. The SP shall meet the performance 3.4.1.2.4 Power factor. The power factor for 115 V ac HUDC operating power shall be greater than 0.95. 3 . 4 . 2 3.4.2.1 Operation. The SP is used to process data received from the AH-1 helicopter in conjunction with the settings on the HD front panel switches. Th

26、e SP processes data for armament aiming and flight information. Perf ormance. 3.4.2.2 Power control modes. The following power control modes shall be provided to the SP: 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-a MIL-P-70444 12 = 9Ob 0354470

27、 3 MIL-P-70444 (AR) -. a. - OFF. The SP shall not be operational; all electrical power shall be removed from SP circuits. b. STANDBY. All necessary power shall be applied for SP operations, the Bright Up output blanked. c. 7 ON. The SP shall be fully operational. 3.4.2.3 Operational modes. When the

28、SP is in the “ON“ power control mode, the SP shall have the following selectable operating modes. shall be in accordancewith Table I. “STAD“ mode, the Stadiametric Reticle (SMR) shall be output. The SMR shall be a backup reticle that is selected for display in the event of primary failure in the SPs

29、 interface, processor, or main program memory circuitry. output when the SP is in “NORMAL“ mode and the appropriate control signals are received as specified in Table I, reference symbol serves as the HUDS display reference, shall always be present during the “ON“ power control mode. The data suppli

30、ed and symbols displayed within each mode 3.4.2.3.1 Stadiametric mode. Whenever the SP is placed in the 3.4.2.3.2 Normal mode. The following data and symbols shall be 3.4.2.3.2.1 Boresiqht reference symbol. The boresight 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without

31、license from IHS-,-,-MIL-P-70444 12 m 777770b 0354473 5 m MIL-P-70444 (AR) c O -4 rn al 4 U c al rn 4 U al m o 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-7044i 12 = 7777706 0354472 7 M MIL-P-70444 (AR) 3.4.2.3.2.2 Normal data. The follow

32、ing alpha numeric data shall always be provided when the data exists at the SP interface with the condition that the FCC operation is valid. a. Range b. Engine torque c. Magnetic heading - d. Radar altitude If the FCC operation is invalid, the raw laser range shall be output and so indicated. The ra

33、dar altitude high/low symbols shall be output when these discrete commands from the radar altimeter exists at the SP interface. 3.4.2.3.2.3 Fire control symbol. A fire control reticle (see Figures 1 i.e., “fail“ indications when no fault exists, 3i4.2.8.1.2 Fault detection and isolation capability.

34、BIT shall provide the crew with a minimum of 95 percent confidence level that no failure-which would result in a loss of function or mode in flight will occur. 3.4.2.8.1.3 - BIT reliability. BIT shall be designed so that any failure of the BIT circuitry will not inherently cause failure or degradati

35、on of the SP primary performance as defined herein. 3 . 4.2.8 . 1.4 Malfunction indication. An equipment status indicator shall be provided for the SP. The equipment status indicator shall be a go/no-go device and shall be such as to hold the last result if power is interrupted or removed, and shall

36、 be on the surface of the SP. 25 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I MIL-P-70qqq 12 m 9999906 0354491 O E I MIL-P-70444 (AR) 3.4.2.8.1.5 BIT output. The BIT circuitry shall provide a HUDS go/no-go output, defined in Appendix A, upon req

37、uest from either the SP or the HUD. It shall also provide an SP Fail Line to the HlJD in order to hold the HUD BIT indicator from false tripping. 3.4.2.9 Internal power supplies. Internal power supplies shall have overvoltage protection. Trip point shall be less than the minimum voltage rating of th

38、e devices supplied by the internal power supplies. 3.4.2.10 Ranqe data interface. Two sources of range data shall be accepted by the SP for the display of digital range data. These two sources shall be as follows: a. Fire Control Canputer Range b. Laser Range 3.4.2.10.1 Range display precedence. Ran

39、ge shall be displayed fran one of two sources, with the following priority, respectively. a. FCC Ranqe. Displayed when a valid FCC GOOD discrete is b. Laser Range. Displayed when a false FCC GOOD discrete is present at the SP interface. present at the SP interface and valid laser range word is avail

40、able at the SP interface. 3.4.2.10.2 Depressed reticle solution. The fire control reticle for backup rocket (see Figure 2) shall be used as depressed reticle for rockets when the FCC fails (FCC Good discrete is false). When this occurs, the range data being used for range output by the SP shall also

41、 be processed for depressing/elevating the symbol in accordance with an exponential curve fit for rockets. 3.4.3 Physical characteristics. 3.4.3.1 Dimensions, Dimensional requirements applicable to envelope size, mounting and mating shall be in accordance with Dwg 11780003. 3.4.3.2 Weight, SP weight

42、 shall be 11.25 pounds maximum. 3.4.4- Preconditioninq (burn-in), Each SP procured under this specification shall be subjected to a burn-in test as defined in Appendix B. - 26 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-VIL-p-7aqqq 12 m 3797306 0

43、35q472 2 m MIL-P-70444 (AR) 3.4.5 Environmental conditions (first article testing only). The SP shall operate and meet the performance requirements of 3.4.2 under any of the environmental conditions, or a reasonable combination of these conditions I as specified herein. withstand storage in the envi

44、ronments specified herein. 3.4.5.11 Natural environment. The SP shall operate and 3.4.5.1.1 Atitude. Operating: O-20,000 feet; nonoperating and storage: O-50,000 feet. 3.4.5.1.2 Temperature. Operating nonoperating, and storage: -500 to t71OC. 3.4.5.1.3 Humidit . Operation while being subjected to In

45、 Step 6, measurements shall be taken during the last five hours of the last test cycle. 3.4.5.1.4 Sand and dust. Operation after being subjected to MIL-STD-810, Method 510.1, Procedure I, except that the air velocity in Steps 1, 2, and 3 shal.1 be 200 + 100 fpn. Step 3 may proceed immediately after

46、stabilization in-Step 2, if desired. MIL-STD-810, Method 509,l. Operation of the SP shall not be required and failure criteria shall be limited to corrosion of finished and metals only. Such corrosion shall be defined as visible degradation of the equipment surfaces that can be attributed to flakey,

47、 pitted, blistered, or otherwise loosened finish or metal surf ace. MIL-STD-810, Met -F-d o 5 7.1, Procedure TI. 3.4.5.1.5 Salt atmosphere. Operation after being subjected to 3.4.5.1.6 Fungus. No evidence of viable fungus on any surfaces after being subjected to MIL-STD-810, Method 508. 3.4.5.1.7 Ex

48、plosive atmosphere. Osration after being subjected to MIL-STD-810, Method 511.1, Procedure I, except test to be limited to a maximum altitude of 20,000 feet. 3.4.5.1.8 Rain. Operation after being subjected to MIL-STD-810, Me- 506.1, Procedure I, During each thirty minute rain period, the wind shall

49、be maintained for fifteen minutes, commencing five minutes after the start of the period as specified in the procedures. The SP shall be operated during the last ten minutes of the thirty minute period. 27 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-70444 12 U 7777706 0354473 4 MIL-P-70444 (AR) 3.4.5.2 Service environment. T