ARMY ADS-62-SP-2001 DATA AND TEST REQUIREMENTS FOR AIRWORTHINESS RELEASE FOR HELICOPTER SENSOR DATA AND TESTING REQUIREMENTS IN DEVELOPMENT STAGE《直升机传感器的适航签放数据和实验要求以及其开发阶段的数据和测试要求》.pdf

《ARMY ADS-62-SP-2001 DATA AND TEST REQUIREMENTS FOR AIRWORTHINESS RELEASE FOR HELICOPTER SENSOR DATA AND TESTING REQUIREMENTS IN DEVELOPMENT STAGE《直升机传感器的适航签放数据和实验要求以及其开发阶段的数据和测试要求》.pdf》由会员分享，可在线阅读，更多相关《ARMY ADS-62-SP-2001 DATA AND TEST REQUIREMENTS FOR AIRWORTHINESS RELEASE FOR HELICOPTER SENSOR DATA AND TESTING REQUIREMENTS IN DEVELOPMENT STAGE《直升机传感器的适航签放数据和实验要求以及其开发阶段的数据和测试要求》.pdf（10页珍藏版）》请在麦多课文档分享上搜索。

1、 ADS-62-SP 29 June 2001 CAGE Code 18876 AERONAUTICS DESIGN STANDARD STANDARD PRACTICE DATA AND TEST REQUIREMENTS FOR AIRWORTHINESS RELEASE FOR HELICOPTER SENSOR DATA AND TESTING REQUIREMENTS IN DEVELOPMENT STAGE AMSC N/A DISTRIBUTION STATEMENT A. Approved for public release, distribution is unlimite

2、d. FOOT-POUND Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ii Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-iii Provided by IHSNot for ResaleNo reproduction or networking permitted without licens

3、e from IHS-,-,-ADS-62-SP iv CONTENTS PARAGRAPH PAGE 1.0 SCOPE. 1 2.0 APPLICABLE DOCUMENTS. 1 2.1 General 1 2.2 Government documents 1 2.3 Non-Government publications 1 2.4 Order of precedence . 2 3.0 DEFINITIONS. 2 3.1 Acronyms 2 4.0 GENERAL REQUIREMENTS 2 4.1 Sensor package description and installa

4、tion 2 4.2 Location of sensor package 3 4.3 Equipment furnished to contractor 3 4.4 Analysis requirements 3 4.4.1 Safety statement/hazard analysis 3 4.4.2 Aircraft strike analysis . 3 4.4.3 Mechanical load analysis 3 4.4.4 Weights and balance report 3 4.4.5 Stress analysis 3 4.4.6 Preliminary dynami

5、c analysis. 4 4.4.7 Electrical load analysis. 4 4.4.8 Clearance analysis 4 4.4.9 Blast overpressure analysis. 4 4.4.10 Preliminary human engineering analysis 4 4.4.11 Electromagnetic design and analysis 4 5.0 DETAILED REQUIREMENTS. 4 5.1 Test specifications 4 5.2 Explosive atmosphere 4 5.3 Pilotage

6、night vision systems . 4 5.4 The laser rangefinder/designator system. 4 5.5 Limited vibration . 5 5.6 High and low temperature testing . 5 5.7 Electromagnetic interference/compatibility testing . 5 6.0 NOTES 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from

7、IHS-,-,-ADS-62-SP 1 1.0 SCOPE. This standard establishes design and documentation requirements which shall be completed prior to issue of a Flight Release or Airworthiness Release (AWR) to conduct helicopter Flight Testing on Pilotage and Target Acquisition/Designator System Sensors. It includes sta

8、tements, analyses and preliminary analyses presenting the Pilotage and Target Acquisition Designation System/subsystem and guarantees a certain safety standard. The requirements may be tailored for each test. 2.0 APPLICABLE DOCUMENTS. 2.1 General. The documents listed in this section are specified i

9、n sections 3, 4, and 5 of this standard. This section does not include documents cited in other sections of this standard or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they must me

10、et all specified requirements documents cited in sections 3, 4, and 5 of this standard, whether or not they are listed. 2.2 Government documents. 2.2.1 Specifications, standards, and handbooks. The following specifications, standards, and handbooks form a part of this document to the extent specifie

11、d herein. Unless otherwise specified, the issues of these documents are those listed in the issue of the Department of Defense Index of Specifications and Standards (DoDISS) and supplement thereto, cited in the solicitation. MIL-STD-461 Requirements for the Control of Electromagnetic Interference Ch

12、aracteristics of Subsystems and Equipment MIL-STD-464 Electromagnetic Environmental Effects Requirements for Systems MIL-STD-810 Environmental Engineering Considerations and Tests MIL-STD-1425 Military Lasers and Associated Support Equipment, Safety Design Requirements for MIL-STD-1472 Human Enginee

13、ring MIL-E-7016 Electrical Load and Power Source Capacity, Aircraft, Analysis of MIL-STD-7080 Selection and Installation of Aircraft Electronic Equipment MIL-A-8591 Airborne Stores, Suspension Equipment and Aircraft Store Interface (Carriage Phase); General Criteria for 2.2.2 Other Government docume

14、nts, drawings, and publications. The following other Government documents, drawings, and publications form a part of this document to the extent specified herein. Unless otherwise specified, the issues are those cited in the solicitation. ADS-37-PRF Electromagnetic Environmental Effects (E3) Mangeme

15、nt, Design, and Test Requirements AMCP 706-203 Engineering Design Handbook - Helicopter Engineering Part Three Quality Assurance 2.3 Non-Government publications. The following documents form a part of this document to the extent specified herein. Unless otherwise specified, the issues of the documen

16、ts which are DoD adopted are those listed in the issue of DoDISS cited in the solicitation. Unless otherwise specified, the issues of the documents not listed in DoDISS are the issues of the documents cited in the solicitation. Provided by IHSNot for ResaleNo reproduction or networking permitted wit

17、hout license from IHS-,-,-ADS-62-SP 2 SAE-AS-50881 Wiring, Aerospace Vehicle SAWE-RP7 Weight and Balance Control Data (for Airplanes and Helicopters) 2.4 Order of precedence. In the event of a conflict between the text of this document and the references cited herein, the text of this document takes

18、 precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3.0 DEFINITIONS. 3.1 Acronyms use in this standard. The acronyms used in this standard are defined as follows: ADS Aeronautic Design Standard AMCP Army Material C

19、ommand Pamphlet AWR Airworthiness Release CFE Contractor Furnished Equipment DoDISS Department of Defense Index of Specifications and Standards EMI Electromagnetic Interference FLIR Forward Looking Infra-red GFE Government Furnished Equipment NOE nap of the earth SAE Society of Automotive Engineers

20、SAWE Society of Allied Weight Engineers 4.0 GENERAL REQUIREMENTS. Electro-optical drawings, optical schematics, and systems performance data shall be provided according to the following : 4.1 Sensor package description and installation. Drawings, schematics, and performance data shall describe all i

21、tems of the entire sensor systems/subsystems. The data shall identify by Governmental nomenclature, each item of the system/subsystem and shall include the functional relationship and purpose of the items. The interconnections to systems, such as structural mounting surface, electrical, and optical

22、requirements shall be provided. Structural attachment details of the sensor turret system (Pilotage and Target Acquisition/ Designator) to the aircraft shall be shown. The structural attachment details shall be provided and all loaded joints clearly shown. Mounting details depicting the system/subsy

23、stem to brackets or pallets or rack attachments to the aircraft shall be provided. Electro-optical and optical description/analysis/diagrams shall be provided to indicate the performance requirements for safety are met ( Pilotage/Laser subsystem). Electrical schematics and wire diagrams internal to

24、the system/subsystem and wire diagrams/cable connections shall be provided. Electrical schematics/cable connectors, and wire run diagrams shall be provided using SAE-AS-50881and MIL-STD-7080 as guides. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-

25、ADS-62-SP 3 4.2 Location of sensor package. Equipment installations and arrangement drawings showing the location of all major items of the sensor equipment for which provisions has been made and any exterior equipment shall be provided. 4.3 Equipment furnished to contractor. Contractor-furnished-eq

26、uipment (CFE) sensor design/analysis/test design data, shall be required when such equipment is furnished as CFE Sensor equipment systems/subsystems, or if modification of the Government-Furnished Equipment (GFE) is made. 4.4 Analysis Requirements. 4.4.1 Safety statement/hazard analysis. Analysis of

27、 the helicopter design shall assure that all provided Pilotage/ Target Acquisition/Designation System/Subsystem are in accordance with the safety criteria of AMCP 706-203. Hazard analyses shall be prepared and submitted. This analysis data shall include, but not be limited to: 4.4.1.1 Pilotage night

28、 vision systems. Pilotage night vision systems such as Forward Looking Infra-red (FLIR) coupled to a helmet mounted display or helmet mounted night vision goggle with a pointing Fire Control System in the aircraft shall be designed and evaluated by analysis. The analysis shall provide sufficient fie

29、ld of view and resolution to allow safe flying of the aircraft in marginal light conditions and marginal weather and at nap of the earth (NOE) or above altitudes. 4.4.1.2 Laser rangefinder/designator system. The laser rangefinder/designator system in a stabilized turret shall be designed to meet the

30、 U.S. Army Laser Safety Office criteria. Laser systems installed on aircraft shall meet the safety requirements specified in MIL-STD-1425 and MIL-STD-1472. A safety analysis shall be performed to include, but not be limited to the following : a) Laser beam divergence, and power for the 1.06 micron a

31、nd Eye Safe selectable mode. The Eye Safe Mode must pass an safety analysis. b) Safety interlocks on the high voltage laser electronics unit box (usually mounted off gimbal). Weight on wheels helicopter switch for disabling the possibility that the 1.06 micron laser may fire when near maintenance pe

32、rsonnel. An override on the switch allows ground testing of laser functions provided all personnel has laser goggle protection (optical density of 4.0 or better). c) A fail-safe switch shall be provided for selection of either 1.06 or 1.57 micron eye safe beam. A feedback sensor shall be used to det

33、ermine if the correct selection switch has been activated. d) A software inhibit shall control the laser field of regard (FOR) so the beam will not fire into any helicopter or turret obstruction. Laser energy shall not be reflected back into the pilots eyes. e) The laser shall not randomly fire due

34、to electromagnetic interference (EMI). 4.4.2 Aircraft strike analysis. Analysis shall demonstrate that crashworthiness has not been degraded below the requirements, or levels appropriate to the particular aircraft. (The hazards are defined within the airworthiness qualifications specifications (AQS)

35、 and Safety Assessment for each aircraft.) The analysis shall demonstrate that hazards do not exist because of potential strike areas due to sensor turret structure or any egress blockage by the sensor installation. 4.4.3 Mechanical load analysis. The mechanical load analysis shall demonstrate the s

36、tructural integrity of the sensor turret itself and supporting structure on the aircraft. The expected loads shall not exceed critical limits and shall meet the requirements of AMCP 706-203. 4.4.4 Weights and balance report. This report shall show accurate and complete weight and balance calculation

37、s of the sensor system. Tables shall include the weight, moment of inertia, and center of gravity (c.g.) for the sensor system and sub systems, as well as weights empty, gross weights, and c.g. for the aircraft. Reporting shall be in accordance with SAWE-RP7. 4.4.5 Stress analysis. The stress analys

38、is shall be performed in accordance with MIL-A-8591 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-62-SP 4 for all critical conditions throughout the aircraft/sensor operational envelope, including takeoff and landing, This analysis shall consid

39、er the structural loading effects of the sensor system and mounting bracket on the aircraft , and the effects of the aircraft and mounting bracket on the sensor function. 4.4.6 Preliminary dynamic analysis. A preliminary dynamic analysis shall be performed to determine the fundamental dynamic proper

40、ties of the sensor system/subsystem. These properties shall include, as a minimum, but not be limited to: (1) the resonant frequencies, damping, and the mode shapes of the installed system; (2) the forced response of the installed system with the forcing frequencies of the host equal to the primary

41、forcing frequencies of 1P, nP, 2nP, 3nP, and 4nP (where n= number of blades, P= rotor angular velocity; and (3) the installed system dynamic effect on the weapon and host system. 4.4.7 Electrical load analysis. An electrical load and power source capacity analysis shall be prepared in accordance wit

42、h MIL-E-7016. This analysis shall determine for each electrical system that adequate electrical sources are present for all system loading conditions under all operating conditions. 4.4.8 Clearance analysis. A clearance analysis shall prove that there is sufficient clearance between the rotors and t

43、he sensor packages and between the sensor system and the weapons trajectories. During landing operations in all environmental conditions the sensor package shall be provided necessary ground clearance to prevent any collision accidents. 4.4.9 Blast overpressure analysis. The blast overpressure analy

44、sis shall describe the effects on the sensor system/subsystems due to blast overpressure from firing the armament systems/subsystems. The launch effects from smoke, flames, and temperature deltas on the visual/infrared optics in the sensor system also shall be characterized to determine any operatio

45、nal effects on mission. 4.4.10 Preliminary human engineering analysis. This preliminary human engineering analysis shall give a prognosis of all affects which could impair the crew, their sight and ability to fly safely, concerning or caused by blast overpressure, noise, toxic emissions, and expecte

46、d gas concentration in the cockpit. Consideration shall also be given to Man-Machine-Interface (MMI) and ease of operation for crew and maintenance personnel. 4.4.11 Electromagnetic design and analysis. The sensor package shall be designed and analyzed per the requirements of Aeronautical Design Sta

47、ndard (ADS) 37-PRF for electromagnetic interference and electromagnetic compatibility. 5.0 DETAIL REQUIREMENTS 5.1 Test specifications. The test specifications shall include a test plan to describe in detail how tests will be conducted and define also criteria for a suitable documentation of all rea

48、lized tested The design handbook, AMCP 706-203, shall be used as a guide for specifying data collection, analysis, instrumentation, and test equipment in the test specification. 5.2 Explosive atmosphere. The test for an explosive atmosphere per MIL-STD-810 shall be performed on the new sensor boxes

49、such as the laser high voltage system to prevent any possible ignition of gaseous aircraft fuel vapors in the close quarters of the storage areas in the helicopter. 5.3 Pilotage night vision systems. such as Forward Looking Infra-red (FLIR) with a helmet mounted display system or a helmet or body mounted night vision goggle, or helmet mounted displays (HMDs) alone shall be lab