1、ML-DE70443 (AR) 30 November 1983 MILITARY SPECIFICATION DISPLAY UNIT, SIGHT, HELICOPTER HEAD UP SUBSYSTEM: M76 Munitions and Chemical Canmand, and is available for use by all Departments and Agencies of the Depar tmet of Defense. This specification is approved for use by the U.S. Army Armament, 1. S
2、COPE. 1.1 Scope. This specification contains quality assurance provisions and preparation for delivery for the Display Unit, Sight, Helicopter, Head Up Subsystem: M76. 2. APPLICABLE DOCUMENTS. 2.1 Government documents. - 2.1.1 Specifications and standards. Unless otherwise specified, the following s
3、pecifications ana 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 of this specification to the extent specified herein. SPECIFICATIONS . e. MILITARY MIL-E-5400 MIL -E -6 O 5 1 MIL-I -85
4、0 O MIL-Q-9 85 8 MIL-F- 13 926 MIL-O- 13 830 Electronic Equipment, Airborne, General Specification for Electromagnetic Canpatibility Requirements, Systems interchangeability and Replaceability of Cmponents Parts for Aircraft and Missiles Quality Control Requirements Fire Control Materials: General S
5、pecification Governing the Manufacture and inspection of Optical Canponent for Fire Control Instrument, General Specification Governing Assembly and Inspection of FSC 1270 Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this documen
6、t should be addressed to: Commander, US Arm Armament Research and Development Center, Attn. DRSMC-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 DOCUMEMT CONTAINS PAGES. - /
7、- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-70443 32 m 373930b 0354430 7 m MIL-D-70443 (AR) MIL-C-148 06 MIL-L-25467 M IL-M- 3 8 5 10 MIL-S- 457 4 3 MIL-S-46844 MIL-W-63150 MIL-S-70442 STANDARDS MILITARY DOD-STD-LOO MIL- STD- 10 5 MIL- ST
8、D- 4 6 1 MIL- STD- 7 0 4 MIL-STD-781 MIL- STD- 8 1 O Coating, Reflection Reducing, for Instrument Cover Glasses and Lighting Wedges Lighting, Integral Aircraft Instrument, General Specification for Microcircuits, General Specification for Soldering, Manual Type, High Reliability Electrical, Electron
9、ic, Instrument, Communication and Radar for Aerospace and Control Systems, 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 P
10、ractices Sampling Procedures and Tables for Inspection by Attributes Electromagnetic Interference Characteristics Requirements for Equipment Electric Power, Aircraft, Characteristics and Utilization of Reliability Design Qualification and Production Acceptance Tests: Exponential Distribution Environ
11、mental Test Methods 2.1.2 Other Government documents, drawings and publications. The followina other other Government documents, drawings and publicationsdform a part of this specification to the extent specified herein. DRAWINGS us ARMY ARMAMENT RESEARCH AND DEVELOPMENT COMMAND (ARRADCOM) 1178001 D
12、isplay Unit, Sight, Helicopter Head-Up 11780731 HUD Block Diagram Subsystem (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 c
13、ontracting officer.) i 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. MIL-D-70443 12 W 777770b 0354LI1L 7 W MIL-D- 70 4 4 3 (AR) 2.1.3 Order of .precedence. In the event of a conflict between the text of this specification and the reference cite
14、d herein, the text of this specification shall take precedence. this specification to the extent specified herein: 2.2 Other publications. The following documents form a part of American Society for Testing and Materials (ASTM). ASTM - D3951 - Standard Practice for Commercial Packaging. 3. ReQUIREME
15、NTS. 3.1 Materials. Materials shall be in accordance with the applicable drawings, specifications and standards. 3.2 Parts. All parts shall comply with applicable drawings, specifications, and standards. 3.3 Head up display (HUI). The HD shall comply with all requirements specified on Drawing (Dwg)
16、11780001, all associated drawings, and with all requirements specified in applicable specifications and standards. The HD 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 HUD shall di
17、splay a visual presentation of flight and fire control data to the pilot during day and night missions utilizing a four inch optics aperature. The data shall be collimated and superimposed on the pilots image of the real world by means of a partially reflective optical image combiner. The displayed
18、data shall be as commanded from the Signal Processor (SP) Dwg. 11780002. For a functional block diagram that shows the general signal flow for the HD unit see Dwg. 11780731. C 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-70443 32 W 9799906
19、 0354432 O W MIL-D-70443 (AR) 3.3.1 Major components list. Major components of the HUD are as follows: Nomenclature Drawinq CCA , X-D e f lec t ion 11780024 CCA, Y-Deflection 11780060 CCA, Bright-Up Amp1 11780011 CRT Assy 11780036 Chassis Assy, HUD 11780064 3.4 Characteristics. 3.4.1 Electrical. 3.4
20、.1.1 Electrical signal interface. The HUD signal interface 3.4.1.2 Electrical power. with the AH-1 series helicopter shall be as defined in Appendix A. 3.4.1.2.1 Steady state. The electrical service shall be supplied to the HUD from the Signal Processor (SP). Edge Lit Panel power shall be supplied f
21、rom aircraft. The following powers shall be supplied: Signal Nominal Maximum Continuous % Regulations Name Voltage (22%) Current 10% to Full Load Filament PWR _ +9v 0.55A 6% HVPS PWR +26 . 5V O. 75A 3% 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-
22、,-MIL-D-70443 32 9 7799906 0354433 2 W MIL-D-70443 (AR) Signal Nominal Maximum Continuous % Regulations Name Voltage (52%) Current 10% to Full Load O Deflection Boost PWR .4OV O . 10A 3% Deflection PWR +16V 0.4A 3% Deflection PWR +16V 0.4A 3% %-Amp PWR +8 5V 0.04A 3% !ST;L41NTS 8 Provided by IHSNot
23、for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-D-70943 22 779770b 0354437 T M MIL-D-70443 (AR) 3.4.2.3 Data characteristics. 3.4.2.3.1 Data definition. Data signal characteristics supplied to the HUD are as stated in Table I. O 3.4.2.3.2 Symbol and reticle line w
24、idth. The observed line width of the HUD reticles or symbol shall be 1.0 mr with a tolerance of +0.5 mr at the 50 apercent line intensity point for a display brightness setting in the range of 10 foot-lambert to 1000 foot- lamberts. 3.4.2.3.2.1 Displayed data color. The color of the displayed data s
25、hall be consistent with the human factor and visual interface requirements of this specification. 3.4.2.3.3 Briqhtness. 3.4.2.3.3.1 Displayed data briqhtness. The line brightness of all displayed data shall be such that the images shall be clearly visible against a 10,000 foot-lambert background bir
26、ghtness, and in the presence of direct sunlight penetration in the cockpit. The minimum contrast ratio (C) under the conditions, shall be 1.15. The contrast ratio (C) is defined as: c = Ba + B1 B1 Where: B2 is the apparent brightness of the symbology as viewed through the combiner. BJ is the apparen
27、t brightness of the background as viewed through the combiner . The projected image shall be clearly defined with no visible breaks or irregularities when viewed from a normal operating position in a darkened area or against a bright sky. 3.4.2.3.3.2 Briqhtness control ranqe. The displayed data brig
28、htness shall be adjustable by controls and/or filtering to accommodate and ambient brightness range of 1 x 10-4 (1x105 desired to 10,000 foot-lamberts in two ranges if necessary. For ambient brightness below 1.0 foot-lambert, AN/PVS-5 goggles may be worn by the pilot. Symbol brightness shall vary no
29、n-linearly with adjustment of the manual brightness control on the HUD display unit, such that the control sensitivity at a given contrast is approxi- mately constant over the ambient brightness range. 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-
30、,-I MIL-D-70443 (AR) Table I. Data Characteristics MIL-D-30443 32 m 777770b 0354438 1 M Signal Parameters Deflection X + Input impedance 3.9K ohm, differential, Deflection X - Volt signal each line, + 10 Volts analog signal (horizontal -axis) . t 5 differential. deflection (183,259 mr) + 1OV di?f =
31、t10.50 Deflection Y + , Input impedance 3.9K ohm, differential, Deflection Y - analog signal (elevation axis). + 5 Volt signal each line, + 10 Volts- differential. + 10V diff = - +10.50 deflection (1831259 mr) + 5 V dc = Bright-up, O V d.c = Cut-off Bright-up + Input impedance 680 ohm Bright-up - In
32、put impedance 680 ohm O V dc = Bright-up, + 5 V dc = Cut-off , 10 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-70443 12 m 9999906 0354419 3 W MIL-D-70443 (AR) 3.4.2.3.3.3 Brishtness uniformity. For a given brightness setting, the average lin
33、e brightness of symbols shall not vary more than 25 percent over the FOV of the BUD. Brightness variation is defined as follows: Where: . B max = maximum symbol line. brightness B min = minimum symbol line brightness . . 3.4.2.3.3.4 Automatic brishtness control (ABC). A light sensor and control syst
34、em which autmatically adjusts the brightness of the HUD and symbology in response to the outside ambient light level shall be incorporated in the HUD. permits the pilot to enable or defeat the automatic control. The ABC shall operate within the brightness range of the symbols and for an ambient rang
35、e of 100 to 6000 foot-lamberts. A switch on the HUD front panel 3.4.2.4 Accuracy. Within the environmental conditions specified herein, the HUD shall not exceed 1.7 mr error, one signma, in each axis of azimuth and elevation for the FCS retical. switch for the use of power control mounted on its fro
36、nt panel. 3.4.2.5 Power control modes. The HUD shall have a toggle a. - OFF. This shall be the down position. OFF shall cause the HUDS to have no power on its circuits. b. STANDBY. This shall be the middle position. STANDBY shall invoke the SP to supply power to all circuits and blank the Cathode Ra
37、y Tube (CRT). c. - ON. This shall be the up position. ON shall cause the SP 3.4.2.5.1 Operational modes. The HUD shall have a toggle to render the HUDS system totally operational. switch for the use of mode selection mounted on its front panel. The switch shall have three positions as listed below:
38、the SP to suppy appropriate signals to the HUD for display of normal mode symbology. a. NORMAL. This shall be the up position. NORMAL shall cause 11 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- - MIL-D-70443 12 M 977770b 0354420 T I MIL-D-70443 (
39、AR) b. - TEST. This shallbe the middle position. TEST shall command the SP to supply appropriate signals to the HUD for displaying the test pattern. c. - STAD. This shall be the down position. STAD shall induce the SP to supply appropriate signals to the HUD for displaying the Statiametric Reticle (
40、SMR) . 3.4.2.5.2 Automatic briqhtness control switch. The Automatic Brightness Control (ABC) circuitry shall be controlled by a two position toggle switch on the HUD front pannel. shall initiate the ABC. The down position shall defeat ABC. adjustment for adjusting display birghtness in an out of the
41、 ABC mode. HUD as viewed by the pilot. The up position 3.4.2.5.3 Briqhtness control. This shall be a potentiometer The potentiometer shall be located on the left side of the 3.4.2.5.4 Direct/indirect fire mode. The HUD shall incorporate a two position toggle switch which shall be a part of the HUD c
42、ontrols for use in helicopter fire control circuits. 3.4.2.5.5 Niqht filter. The night filter is for use in conjunction with the brightness control potentiometer for night flying and use with AN/PVS-5 night vision goggles. control shall be a knob, located behind the Brightness Control knob on the le
43、ft hand side of the HUD as viewed by the pilot. The night filter 3.4.2.6 Display charactersitics. 3.4.2.6.1 Ambient light reflections. The HUD optics shall be designed to avoid ambient light reflections from the combining glass and HUD optics. consideration given to minimizing sunlight reflected int
44、o the pilots eyes. images shall be less than 3 percent of the primary image brightness over the total FOV and for head locations anywhere within the head motion box indicated in Figure 2. 3.4.2.6.3 Reflector/combiner plate. The combiner glass shall The HUD optics shall be positioned with 3.4.2.6.2 S
45、econdary imaqes., Brightness levels of any secondary conform to MIL-0-13830. 12 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- - MIL-D-70443 I2 m 777990b 035LI42L L m MIL-D-70443 (AR) 3.4.2.6.4 Niqht symbol color. To accomodate night operation with
46、out the AN/PVS-5 night vision goggles, it is required that the symbols displayed on the HUD shall be red in color in accordance with MIL-L-25467. 3.4.2.7 Built-in-test equipment (BITE). 3.4.2.7.1 Fault detection/location. The HUD shall have a Built-In-Test (BIT) capability of checking its operationa
47、l status. BUT shall obviate the need for any external test equipment for the performance of preflight or in-flight testing of the HUD unit. 3.4.2.7.1.1 Test accuracy. The accuracy of BIT stimuli and measurements shall be designed to preclude false pass/fail indications. When the equipment is operate
48、d within the environmental and service conditions specified herein, less than 2.0 percent of all “fail“ indications shall occur when no fault exists. 3.4.2.7.1.2 Fault detection and isolation capability. BIT shall provide the crew with a minimum of 95 percent confidence level that no failure which w
49、ould result in a loss of function or mode in flight would occur. 3.4.2.7.1.3 BIT reliability. BIT shall be designed so that any failure of the BIT circuitry will not inherently cause failure or degradation of the HUDs primary performance as defined herein. indicator shall be provided for the HUD. The equipment status indictor shall be a go/no-go device and shall be such as
