ARMY ADS-65-HDBK-2004 AIRWORTHINESS QUALIFICATION AND VERIFICATION GUIDANCE FOR ELECTRO-OPTICAL AND SENSOR SYSTEMS《电光传感器系统的适航资格及验证准则》.pdf

《ARMY ADS-65-HDBK-2004 AIRWORTHINESS QUALIFICATION AND VERIFICATION GUIDANCE FOR ELECTRO-OPTICAL AND SENSOR SYSTEMS《电光传感器系统的适航资格及验证准则》.pdf》由会员分享，可在线阅读，更多相关《ARMY ADS-65-HDBK-2004 AIRWORTHINESS QUALIFICATION AND VERIFICATION GUIDANCE FOR ELECTRO-OPTICAL AND SENSOR SYSTEMS《电光传感器系统的适航资格及验证准则》.pdf（29页珍藏版）》请在麦多课文档分享上搜索。

1、ADS-65-HDBK 17 February 2004 CAGE Code 81996 AERONAUTICAL DESIGN STANDARD HANDBOOK AIRWORTHINESS QUALIFICATION AND VERIFICATION GUIDANCE FOR ELECTRO-OPTICAL AND SENSOR SYSTEMS AMSC N/A DISTRIBUTION STATEMENT A. Approved for public release, distribution is unlimited. Provided by IHSNot for ResaleNo r

2、eproduction or networking permitted without license from IHS-,-,-ADS-65-HDBK ii Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-65-HDBK iii Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-65-H

3、DBK iv CONTENTS PARAGRAPH PAGE 1.0 SCOPE 1 2.0 Applicable Documents. 1 2.1 General 1 2.2 Government Documents. 1 2.3 Order of Precedence 2 3.0 ACRONYMS . 2 4.0 General Requirements . 3 4.1 A irworthiness Qualification 3 4.2 Methods of Verification 4 4.3 Verification Categories 5 4.4 Inspection Condi

4、tions 5 4.5 System Safety 5 4.6 Reliability, Availability and Maintainability 5 5.0 Detailed Requirements . . 5 5.1 Engineering Analyses/Simulations 6 5.2 Component Qualification. 9 5.3 Survey/Tests 13 5.4 Software Qualification. 20 5.5 Requirements For Demonstrations On Sensor System. 22 6.0 NOTES.

5、 24 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-65-HDBK 1 AIRWORTHINESS QUALIFICATION AND VERIFICATION GUIDANCE FOR ELECTRO-OPTICAL AND SENSOR SYSTEMS 1.0 SCOPE. This document establishes the guidance for airworthiness qualification and discu

6、sses the methods of verification for Electro-Optical (EO) and Sensor Systems (SS), mission sensor group, and any other targeting/pilotage systems installed on U.S. Army aircraft. It also establishes the guidance for ancillary equipment, including displays, lasers and targeting systems. The sensors a

7、nd system-related EO equipment are collectively referred to as a “sensor system” in this document. A combination of analyses and testing is used to verify the design, installation and operation of the sensor system and to support airworthiness qualification. 2.0 APPLICABLE DOCUMENTS. 2.1 General. Th

8、is section lists references that are cited in this document. 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 specified herein. It is recommended that the latest versions be used

9、 unless otherwise stated within the specification. AMCP 706-203 Engineering Design Handbook, Helicopter Engineering Part III, Qualification Assurance JSSG-2010-5 Joint Services Crew Systems Aircraft Lighting Handbook JSSG-2010-7 Crash Protection Handbook JSSG-2010-11 Emergency Egress Handbook MIL-E-

10、7016 Electrical Load and Power Source Capacity Aircraft, Analyses for MIL-L-85762 Aviators Night Vision Imaging System (ANVIS ) MIL-STD-461 Electromagnetic Interference Characteristics Requirements for Equipment Subsystem and System Provided by IHSNot for ResaleNo reproduction or networking permitte

11、d without license from IHS-,-,-ADS-65-HDBK 2 MIL-STD-464 Electromagnetic Environmental Effects Requirements for Systems MIL-STD-704 Aircraft Electrical Power Characteristics MIL-STD-810 Environmental Test Methods and Engineering Guidelines MIL-STD-882 System Safety Program Requirements MIL-STD-1472

12、Human Engineering MIL-STD-1787 Aircraft Display Symbology MIL-STD-2525 Common Warfighting Symbology MIL-STD-3009 Lighting, Aircraft, Night Vision Imaging System (NVIS) Compatible MIL-HDBK-781 Handbook for Reliability Test Methods, Plans and Environments for Engineering, Development, Qualification an

13、d Production MIL-HDBK-87213 Electronically/Optically Generated Airborne Displays 2.2.2 Other Government documents, drawings, and publications. The following documents, drawings, and publications form a part of this document to the extent specified herein. ADS-37A-PRF Electromagnetic Environmental Ef

14、fects, Performance and Verification Requirements ADS-62-SP Data and Test Requirements for Airworthiness Release for Helicopter Sensor Data and Testing Requirements 2.2.3 Non-Government publications. The following documents form a part of this document to the extent specified herein. International So

15、ciety of Allied Weight Engineers SAWE RP7 Weight and Balance Control Data (for Airplanes andHelicopters) Society of Allied Weight Engineers Recommended Practice 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-65-HDBK 3 2.3 Order of precedence.

16、In the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3.0 ACRONYMS ADS Aeronautical Design

17、Standard A display of sensor FOVs and sensor switching timelines including electronic zoom FOVs; sensor FOR limits; sector search; fixed forward gimbal cage operation; helmet slaved operation; hand control operation for manual and aided/automatic target acquisition and manual tracking; auto target t

18、racking (including multi-target track capability); internal boresight and boresight retention; laser to gyro boresight algorithm. b. Survey performance that is dependent on the helicopter being airborne against the system specification requirements. Manual and aided/automatic target acquisition at a

19、 hover and on the move with FLIR and TV/I2TV sensors; prepoint, laser designation; laser ranging (tactical laser and eye-safe), auto target tracking (including multitarget track capability); target location and hand-off accuracy; man-in-the-loop target acquisition and engagement timeline capability

20、for operation at a hover and on the move; operational impact of EOCCM protection including manual override. Surveyed performance should address operation in/over low contrast environments; The electro-optical target acquisition sensors should be characterized for end-to-end (at the aircraft display)

21、 MRT/MRC in each of the operational sensor FOVs prior to conducting the TAS survey. c. The TAS survey should conduct an airborne laser designation Total Pointing Error (TPE) survey. A laser spot scoring system should be used. The laser spot scoring system should also be used to measure TAS stabiliza

22、tion, tracking accuracy, boresight, and boresight retention with and without gunfire. d. Target Acquisition/Designation Subsytem. Turret optical jitter, slew rates, acceleration, position accuracy, gimbal field of regard throughout the specified angular coverage, and Laser characteristics should be

23、determined. Measurements for tracker qualification should include determination of the capability to track targets in various environmental conditions including clutter, obscurants, target multiplicity, and varying target spacing. Provided by IHSNot for ResaleNo reproduction or networking permitted

24、without license from IHS-,-,-ADS-65-HDBK 17 e. Tracking and Laser Designation. The TAS should perform all tracking, sighting, and fire control functions with accuracies consistent with weapon requirements. Laser designation performance should enable laser terminal homing weapons probabilities of hit

25、 to be met at ranges and target maneuver conditions. Pulse A-Code and Pulse Repetition Frequency (PRF) coding should meet laser terminal homing weapons requirements. Day and Night zoom available within each of the sensor FOVs. During the zoom mode the display reticle size should be unaffected. The L

26、aser designator should be capable of continuous operation at its highest required pulse rate without degradation in power output, beam divergence, or boresight retention with a continuous duty cycle. There should be no vignetting, FOV cutoff, or obscurations of the EO sensors. Laser pulse initiation

27、 should be synchronized to rotoblade position to minimize obscuration and loss of coded laser pulses. f. Boresight Subsystem. Operation and accuracy of boresight subsystem with the sensor system should be verified. Boresight tests are performed to ensure that the optical alignment among the various

28、sensor and designator subsystems of the targeting system is within specification requirements and the internal boresighting equipment provides the required boresight accuracy. g. Target Acquisition/Designation Subsystem Pointing. Target acquisition/designation subsystem day/night pointing throughout

29、 the gimbal field of regard and flight envelope should be verified. The minimum set of military targets against which the TAS should perform acquisition functions includes moving and stationary tracked and wheeled vehicles, and rotary and fixed wing aircraft. This test should include boresight reten

30、tion. h. Target Acquisition/Designation Subsystem Handover. Target acquisition/designation subsystem handover both air-to-air and ground-to-air should be verified. 5.3.4 Pilotage System Survey. A survey of the pilotage system should be conducted to verify the design. The survey should include: a. Th

31、e pilotage System Survey should have image quality, uniformity of sensors (primary and backup), MRT of the thermal sensors. Data should be collected end-to-end, i.e., at the HMD and should be measured across the entire design Field of View (FOV). b. I2TV performance. The I2TV should not be damaged b

32、y exposure to bright lights or to lasers outside the 0.6 0.9 micron waveband. The I2TV should be designed to provide imagery that is Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-65-HDBK 18 registered with the FLIR imagery, and is capable of fu

33、sion with same. The I2TV should be capable of operation in urban terrain with little/no image saturation due to blooming from cultural lighting. The I2TV should incorporate protection from inadvertent solar disk imaging. c. Image fused performance. Image fusion should be provided to fuse video from

34、the FLIR sensor and the I2TV sensor into a single optimized video image. The system should provide additive fusion or feature-level fusion of the I2TV and FLIR Imagery, in all FOVs, with the capability to automatically or manually adjust the ratio of fusion of the FLIR and I2TV video. The sensor ima

35、gery, FLIR, and I2TV combined with symbology, should interface and be viewable on either, or both crewmembers displays. d. The pilotage System Survey should have automatic features to include signal and image processing and the manual overrides. e. The pilotage System Survey should have sensor compa

36、tibility with display (MFD and HMD) to include FOV, flight symbology for visual cues, such as definition of horizon and other system indicators. f. The pilotage System Survey should have the capability for performing day and night precision maneuvers, and general mission tasks such as NOE and contou

37、r flight. g. The pilotage System Survey should be interface to other aircraft subsystems. h. Operational impact of EOCCM insertion. All of the sensor equipment should provide the maximum degree of survivability, IAW system specification requirement, in an electronic warfare environment with out sacr

38、ificing or degrading the mission requirements on either a temporary or permanent basis. The Sensor should be hardened against electronic countermeasures (in according to the Performance Specification). The Sensor should provide, as a minimum, multiple spectral filters to meet the requirements of the

39、 classified Performance Specification. The time to switch between adjacent filter positions in response to an aircraft filter command should not exceed 2.0 seconds. The FLIR should not require refocusing or re-boresighting when the filter position is changed. i. The pilotage system survey should ver

40、ify pilotage system functional capabilities and operating modes. j. Survey performance, that is by specification independent on the aircraft, may be verified on the ground or airborne (horizontal and vertical FOV), field-of-vision, and Field-Provided by IHSNot for ResaleNo reproduction or networking

41、 permitted without license from IHS-,-,-ADS-65-HDBK 19 of-Regard (FOR), pilot and copilot head movement tracking rate and acceleration capability, resistance to image blur and vignetting, and registration error) during ground tests or using the aircraft. Effect of naturally occurring obscurants (rai

42、n, fog, and so on), insofar as available, and artificially produced or simulated obscurants (smoke, dust, and so on) should be surveyed. k. Survey performance that is verified by specification dependent on the helicopter should be airborne (such as support of stationkeeping, hover, and terminal area

43、 maneuver) should be verified during ground and flight tests. Vibration and temperature data should be collected to support analysis to be performed to substantiate performance required by the system specification. Effects of natural and artificially produced obscurants should be evaluated. Testing

44、should begin with daylight, visual meteorological conditions (VMC) and progress to nighttime, degraded visibility conditions. l. Data should be obtained at the lowest accurate level (component bench test, Software Integration Lab (SIL) or aircraft) and surveyed at subsequent levels to verify that in

45、tegration has not degraded allocated performance. 5.3.4.1 Pilotage Subsystems Testing. Testing of the NVPS or pilotage should be conducted to verify the design. The analysis should include but not be limited to: a. Image quality, uniformity of sensors (primary and backup), MRT of the thermal sensors

46、 Note :( Data should be collected end-to-end and should be measured across the entire design Field of View (FOV). Measurements for I2/TV subsystems include fields of view, noise, automatic light control (ALC) performance, shading characteristics, screen blemishes, signal level, distortion, field-of-

47、view alignment, and MTF.) b. Automatic features to include signal and image processing and the manual overrides c. Sensor compatibility with display to include FOV, flight symbology for visual cues, such as definition of horizon and other system indicators d. Capability for performing day and night

48、precision maneuvers defined in ADS-46 (draft, dated 1 June 1998), and general mission tasks such as NOE and contour flight e. Interfaces to other aircraft subsystems f. Pilotage modes including terrain avoidance warnings g. Operational impact of electro-optical counter-counter measures (EOCCM) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ADS-65-HDBK 20 h. Determine the accuracies of helmet-tracked, manually slewed and fixed forward controls Note: A survey test plan and report should be submitted for government approv