1、MIL-D-70LI87 12 I 7779906 0355115 T MIL-D-70487 (AR) 30 June 1983 MI LI TARY SPEC IF ICAT ION DETECTOR, WIND DIRECTION, SPEED, AND TEMPERATURE, FIRE AND FLIGHT AIR DATA SUBSYSTEM, HELICOPTER ARAMAMENT: M143 This specification is approved for use by the US Army Armament, Munitions and Chemical Comman
2、d, and is available for use by all Departments and Agencies of the Department of Defense. 1. SCOPE. 1.1 Scope. This specification contains performance and environmental requirements, quality assurance provisions, and packaging for delivery for the Detector, Wind Direction, Speed, and Temperature, Fi
3、re and Flight Air Data Subsystem, Helicopter Armament: M143. 2 . APPLICABLE DOCUMENTS. 2.1 Government documents. Unless otherwise specified, the following Specifications and Standards of the issue listed in that issue of the Department of Defense Index of Specifications and this specification to the
4、 extent specified herein. ! Standards (DoDISS) specified in the solicitation, form a part of SPECIFICATIONS MILITARY MIL-E-5400 Electronic Equipment, Airborne, General Specification for MIL-E-6051 Electromagnetic Compatibility Requirements Systems MIL-1-8500 Interchangeability and Replaceability of
5、Components Parts for Aircraft and Missiles FSC 1270 Beneficial commenta (recommendatiom, additiona, deletiona) and any pertinent data which may be of une in impro- tbia document ohould be adreaaed to. Commander, US Army hament Reaearch and Development Center. Attax AMSMC-Qa, Dorer, New Jemy 07801-1
6、by u- the .eif-addre#ed Standardization Document Improvement Propood (DD Porn 1426) appeufnl at the end of thio document or by letter. - PAGES - _ - - - -, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-70487 (AR) MIL-F-13926 MIL-M-38510 MIL-S
7、-45743 MIL-S-46844 STANDARDS MILITARY DOD-STD-10 O MIL- STD- 1 O 5 MIL-STD-46 1 MIL-STD- 7 O 4 MIL-STD-781 MIL-STD-810C Fire Control Materials: General Specification Governing the Manufacture and inspection of Microcircuits, General Specification for Soldering, Manual Type, High Reliability Electric
8、al, Electronic, Instrument, Communication and Radar for Aerospace and Control Systems, Procedure for Solder Bath, Soldering and Printed Wiring Assemblies, Automatic Machine Type Engineering Drawing Practices Sampling Procedures and Tables for Inspection by Attributes Electromagnetic Interference Cha
9、racteristics Requirements for Equipment Electric Power, Aircraft, Characteristcs and Utilization of Reliability Design Qualification and Production Acceptance Tests: Exponential Distribution Environmental Test Methods 2.1.2 Other qovernment documents, drawings, and publications. The following other
10、Government documents, drawings, and publications form a part of this specification to the extent specified hrein. DRAWINGS US ARMY ARMAMENT, RESEARCH AND DEVELOPMENT CENTER (ARDC) P 1 1 11776800 1776800 ,1776801 11776813 11776858 11776864 11776869 11776877 Preservation and Packaging Data .Sheet Dete
11、ctor, Wind Direction Speed and Temperature Tail Assembly Neck Assembly Cover and Dowel Assembly Body and Plug Assembly Plate and Connector Assembly Head Assembly I- f 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- I MIL-D-70q7 12 9977906 0355327
12、3 MIL-D-70487 (AR) (Copies of specifications, 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.) 2.2 Other publications. The followin
13、g documents form a part of this specification to the extent specified herein: American Society for Testing and Materials (ASTM) ASTM-D3951 - Standard Practice for Commercial Packaging. 2.3 Order of precedence. In the event of a conflict of this specificatron and the references cited herein, the text
14、 of this specification shall take precedence. 3. REQUIREMENTS 3.1 Materials. Materials shall be in accordance with the - - applicable drawings, specifications, and standards. 3.2 Parts. All parts shall comply with the applicable drawings, specifications, and standards. 3.3 Air Data System Airspeed a
15、nd Direction Sensor (AADS). The AADS shall comply with all requirements specified on Drawing (DWG) 11776800, all associated drawings, and with all requirements specified in applicable specifications and standards. The AADS shall consist of a pitotstatic pressure head supported on a gimbal arrangemen
16、t, caused to point into the local airflow by a finned tail. Total and static pressures shall be sensed by the head which is aligned with the local resultant airflow, and shall not suffer from incidence errors. Air pressure shall be conveyed via the axles of the gimbal to aircraft plumbing. Movement
17、of the gimbal shall position two angular resolvers to generate electrical signals which represent the movement of the pitot head in pitch and yaw axes relative to the aircraft. These signals, together with the pressure signals, shall be used by the ADS EPU to compute helicopter airspeed and directio
18、n. A gimbal arrangement shall permit total angular freedom in pitch and +60 in yaw to allow the head to sense accurately the local Pitot and static pressures for helicopter foward and lateral airspeeds. The pressure head shall be equipped with a heating element. The AADS shall incorporate an Air Tem
19、perature Sensor (ATS) which does not interfere with airflow over the pressure head or pick up heated air from the head. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-D-70LI87 12 7777906 0355118 5 I MIL-D-70487 (AR) 3.3.1 Major component list
20、. -I Nomenclat Ure Drawing Head Assembly 11776877 Plate and Connector Assembly 11776869 Body and Plug Assembly 11776864 Cover and Dowel Assembly 11776858 Neck Assembly 11776813 Tail Assembly 11776801 3.4 Characteristics. 1_- 3.4.1 Electrical. 3.4.1.1 Signal interface. The AADS signal interface with
21、the EPU shall be as defined in Appendix A to this specification and drawing 11776300. 3.4.1.2 Electrical power. - 3.4.1.2.1 Steady state. The electrical service conditions will - be in accordance with MIL-STD-704, Category “B“ utilization equipment, except that the transient frequency limit of Figur
22、e 5, limit 4 in MIL-STD-704 shall be 240Hz. The equipment shall meet all specified requirements of MIL-STD-704 for the types of power specified herein, and shall give specified performance when supplied with electrical power having these characteristics and limits. The power required shall not excee
23、d the amounts specified below: a. 115/200 Volts, 400Hz, 1-phase grounded neutral 200 Volt amperes (anti-icing). 3.4.1.2.2 Electrical power interruptions. Momentary power interruptions to the equipment will be experienced when external primary power is switched to helicopter power or when switching f
24、rom one helicopter power bus to another. The ADS shall meet the performance requirements of this specification after such momentary power interruptions have been experienced. The ADS shall return automatically to specified performance within 5 seconds after any power interruption. 3.4.1.3 Mechanical
25、 interface. The maximum envelope dimensions and mounting provisions of the AADS shall conform to drawing 11776806. 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-707 12 m 777770b 0355119 7 m MIL-D-70487 (AR) 3.4.1.4 Interfacing components. T
26、he AADS shall interface with the ADS EPU and pitot head heater control and pitot static plumbing on drawing 11776300. 3.4.2 Performance. 3.4.2.1 Input/output parameter range. The AADS shall have input/output characteristics over the ranqe and within the toerancec specified in Table 1. - 3.4.2.2 Accu
27、racy. The AADS accuracy values shown in Table I shall be defined as 95 percent confidence values. AADS measured accuracy shall be within the specified accuracies in at least 19 out of each 20 separate measurements within the ADS performance envelope specified in Table I. 3.4.2.3 Anti-icing provision
28、s. The AADS shall contain an anti-icing subsystem. The anti-icing subsystem shall use 115 Vac, 400Hz, single phase helicopter power for the heating function. 3.4.2.4 Mechanical alignment. The AADS shall have a reference plane or mounting points with respect to which the sensor shall be tested for di
29、rectional airspeed accuracy. Mounting provisions shall be in accordance with 11776806. 3.4.2.5 Orthogonality. AADS pitch and yaw eiectrical outputs shall be such that the equivalent measurement axes are mutually perpendicular within 1 degree. 3.4.2.6 System turn-on time. The ADDS response time from
30、power-on actuation to ready state shall not exceed 5 seconds. 3.4.2.7 Air leakage. Air leakage within the AADS from the pitot and static lines shall not cause an equivalent error of greater than 0.5 knot in the dynamic pressure sensed by the AADS. This shall apply for any point within performance en
31、velope of the ADS, and for the environmental conditions specified herein. 3.4.2.8 - Freedom of movement. The pitot/static sensing assembly shall have adequate freedom of movement to accurately sense the parameters listed in Table 1. 5 Provided by IHSNot for ResaleNo reproduction or networking permit
32、ted without license from IHS-,-,-MIL-D-70487 (AR) 3.4.3 Physical characteristics. 3.4.3.1 Dimensions. Dimensional requirements applicable to envelop size, mounting and mating shall be in accordance with drawing 11776806. 3.4.3.2 Weiqht. The maximum weight of the AADS shall be 2 pounds 7 ounces. 3.4.
33、4 Precondition burn in. Each AADS procured under this specification shall be subjected to a burn-in test as defined in Figure 1. 3.4.5 Environment conditions. The AADS shall operate and meet the performance requirements of 3.4.2 under any of the environmental conditions, or a reasonable combination
34、of these conditions, as specified herein. TABLE I. Input/output parameter ranqe and characteristics input/ Par ame t er Units Nom. Value/ To1 er ance output Ranqe (Plus or Minus) Output A ir Temperatur e Ohms 367 thru 617 2 ohm/OC Input Pitot Head Heater 400 Hz 115. O 5. O S encor Input Resolver Sup
35、ply Volts AC 19. o 2.0 Output Angle (Pitch) (o() degrees O thru 360 2. o Output Ang 1 e (P i tc h-Y aw ) (A-B 1 deqrees O thru 360 2. o 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-u I O 1 O +7loC OC L- -54O MIL-D-70Y7 12 = 777770b 0355121 5 1 M
36、IL-D- 7 04 8 7 (AR) 4 Q om cicm b Q 8 VOLTAGE 7 OLTAGE VOLTAGE HEATING HIGH TEMP 8 3 PERIOD PERIOD A .% I I l I I I I I I l 1 I I l 1 I I i COOLING 4 PERIOD A A 0 STABILIZE TEMPERATURE 0 MOMENTARY OFF EQUIPMENT ON - - EQUIPMENT OFF TIME - HOURS FIGURE 1. Typical temperature cycle - electronic and av
37、ionic equipment - continued 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-70487 32 m 777770b 0355322 7 m MIL-D-70487 (AR) NOTES : 1. 2. 3. 4. 5. 6. 7. During the cooling period, the chamber temperature shall not be lower than -60%. Once eve
38、ry 24 hours at O%, moisture shall be injected until the equipment being tested is coated with frost. One temperature cycle shall start with the equipment stabilized at the low temperature, heated and stabilized at the high temperature, maintained at the high temperature for 2 hours, then end with th
39、e equipment cooled and stabilized at the low temperature. During the temperature cycle, the equipment shall be operated in accordance with its normal duty cycle. Equipment ON; input voltage at 110% and 90%, respectively during each 1/3 of the total time of heating period plus high temperature period
40、; momentarily OFF between input voltage changes. Equ ipmen t OFF . Vibration -2.2g 510% peak acceleration value at any nonresonant frequency between 20 and 60 Hz measured at the mounting points of the equipment. The vibration shall be a- least 10 minutes during each hour of operating time. Transitio
41、n rate between temperature levels shall average 5% per minute. FIGURE 1. Typical temperature cycle - electronic and avionic equipment 8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. MIL-D-70q7 32 W 7779906 0355323 7 W MIL-D-70487 (AR) 3.4.5.1 Nat
42、ural environment. The AADS shall operate and withstand storage in the environment described in MIL-E-5400 exceDt - - as noted herein. 3.4.5.1.1 Altitude. Operating, 0-20,000 feet. Nonoperating and storage 0-50,000 feet. . 3.4.5.1.2 Temperature. Operating, nonoperating, and storage -54OC to +71OC, 3.
43、4.5.1.3 Humidity. Operation while being subjected to MIL-STD-810, Method 507.1, Procedure II. In 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
44、air velocity in Steps 1, 2, and 3 shall be 200 + 100 fpm. Step 3 may proceed immediately after stabilization in-Step 2, if desired. 3.4.5.1.5 Salt atmosphere. Operation after being subjected to MIL-STD-810, Method 509.1. Operation of the AADS shall not be required and failure criteria shall be limit
45、ed to corrosion of finishes and metals only. Such corrosion shall be defined as visible degradation of the equipment surfaces that can be attributed to flakey, pitted, blistered, or otherwise loosened finish or metal surf ace. 3.4.5.1.6 Fungus. No evidence of viable fungus on any surfaces after bein
46、g subjected to MIL-STD-810, Method 508.1. 3.4.5.1.7 Explosive atmosphere. Operation 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, Method 506.1, Procedure
47、 I. During each thirty minute rain period, the wind shall be maintained for fifteen minutes, commencing five minutes after the start of the period as specified in the procedures. The AADS shall be operated during the last ten minutes of the thirty minute period. 3.4.5.2 Service environment. The AADS
48、 shall withstand the -Id service environment as specified in MIL-E-5400 for Class 2 equipment, except as noted in paragraphs 3.4.5.1.1 thru 3.4.5.1.8. 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-70487 12 H 7977906 035512LI O H MIL-D-70487
49、 (AR) 3.4.5.2.1 Bench handling. The AADS shall withstand shock environments encountered in maintenance and servicing. 3 . 4 . 5 . 3 Induced environment. 3.4.5.3.1 Vibration. The AADS shall not sustain damage or subsequently fail to provide specified performance when subjected to the vibratipn environment defined by Figure 2, except that the maximum double ampl
