NAVY MIL-D-81641-1972 DISPLAY HEAD-UP GENERAL SPECIFICATION FOR《平视显示器总说明书》.pdf

1、MILITARY SPECIFICATION DISPLAY, HEAD-UP, GENERAL SPECIFICATION FOR This specification has been approved by the Naval Air Systems Command, Department of the Navy 1. SCOPE li 1 Scope - This specification covers the general design, performance, and test requirements for procurement of all fixed wing ai

2、rcraft Head-Up Displays. 1.2 Classification - The equipment covered by this specification shall con- sist of the.following items: - item Type Designation Applicable Paragaph Pilots Display Unit (PDU) (1) 3.5.2 Electronics Unit (EU) (1) 3.5;3 Control Panel (Optional) (CP) (1) 3.3.4 Display Unit M0un.

3、t (DUM) (i) 3.5 5, 1.3 Associated equipment - This equipment shall operate wtn the associated equipment listed in 6.8, 2. APPLICABLE DOCUMENTS 2.1 General - The following documents of the issue in effect on the date of invitation for bids form a part of this specification to the extent specified her

4、ein: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Cases; Bases, Mounting, and Mounts, Vibration (for use with Electronic Equipment in Aircraft) Wiring, Aircraft, Installation of Electronic Equipment, Aircraft, General Specification for Control Pan

5、el; Aircraft Equipment, Rack or Console Mounted Meter, Time Totalizing Optical Components for Fire Control Instruments; General Specification Governing the Manufacture, Assembly, and Inspection of Coating, Reflection Reducing, for Instrument Cover Glasses and Lighting Wedges Electronic and Electrica

6、l Equipment and Associated Repair Parts, Preparation or Delivery of Test Procedures; Preproduction Acceptance, and Life for Aircraft Electronic Equipment, Format for Nomenclature and Nameplates for Aeronautical Electronic and Associated Equipment Thermal Performance E valuation, Airborne Electronic

7、Equipment, General Requirements for 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SPECIFICATIONS (Contld) MGC-25050 MIEC-25516 MIEC-26482 M IL-I- 8 12 19 Naval Air Systems Command AR- 5 AR-8 AR-9 AR- 10 AR-34 STANDARDS Militarv Microelectronic De

8、vices Used in Avionics Equipment, Procedures for Selection and Approval of Versatile Avionic Shop Test System, Avionic System Compatibility, General Requirements for VAST Test Programs, General Requirements for Maintainability of Avionics Equipment and Systems, General Requirements for Failure Class

9、ification for Reliability Testing, General Requirements for MIESTD-203 MIL-STD-210 MILSTD-461 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Measurement of Electric Power, Aircraft, Characteristics and Utilization of Reliability Tests, Exponential D

10、istribution J MIL-STD-794 1 MIE STD-8 10 MIE STD- 133 3 MI E STD- 1472 Aircrew Station Geometry for Military Aircraft Human Engineering Design Criteria for MS 3311 I Reliability Program for in the Take-off/NAV mode the flight director symbol shall show navigation fly-to information when the airspeed

11、 is greater than the rotaion airspeed plus 50 hots (See Figure 2). 14 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-3643 66 7779906 0343446 3 W MIL-D-8 1641 (AS) 3.5.1.3.3 Breakaway - The breakaway symbol, an llXfl, shall indicate need for im

12、mediate pull-up of the aircraft. Upon data input command, the symbol shall appear and commence blinking at a rate of four flashes per second with a duty cycle of O. 5 (See Figure 16). 3.5.1.3.4 Warning indicator - The warning indicator shall display a warning of critical airplane. conditions in all

13、modes. The indicator shall be controlled by a minimum of five parallel sensor inputs (discretes). The inputs shall be: 1. Designated by the detailed specification for the individual air craft HUD . 2. Hydraulic pressure warning, 3. Oil pressure warning. 4. Engine temperature warning. 5. Fire warning

14、. The warning indicator shall be a I1W1? flashing four times a second with a duty time of 0.5 (See Figure 17). 3.5.1.3.5 Horizon line - The horizon line shall represent the true horizon. Movement of the horizon line shall be in a direct one-to-one correspondence with the roll and pitch of the aircra

15、ft. The horizon line shall not overlie any part of the tape symbols (See Figure 4). 3.5.1.3.6 Pitch lines - The pitch lines shall represent the aircraft attitude and shall.move in a direct one-to-one correspondence with the pitch and roll of the aircraft. The pitch lines shall be parallel to the hor

16、izon line and shall be spaced at 5“ intervals from the horizon line up to +90“ and down to -90“. The pitch degree number of the pitch line shall be written at the extreme ends of the pitch lines every ten degrees starting at -90“. The pitch lines shall not overlie the tape symbols (See Figure 4), 3.

17、5.1.3.7 Tape symbology on the left, right, and top - The tape symbology (i. e. Vertical Velocity, Airspeed, Mach Number, Heading, Barometric Altitude, Radar Altitude and Closure) on the left, right, and top of the field of view shall have the same method of display. Each group of symbols shall consi

18、st of a moving tape scale. The actual flight parameter-indicator shall be a fixed line segment which points to the center of the tape. The command flight parameter indicator shall be a pointer which points to the tape. The command flight para- meter indicator shall remain in view within one degree o

19、f the scale when the - 15 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-command parameter is beyond the range of the tape. When the command flight parameter indicator is centered in the pointer of the actual flight parameter indica- tor, the comman

20、d flight parameter is satisfied. 3 5, I . 3.7 . I Heading - The heading symbols shall show magne tic heading and command maghetic heading on a moving tape scale at the top of the field of view. The scale shall be in five degree increments. Every ten degree incre- ment shall be numbered with the last

21、 digit zero omitted. The scale shall be continuous, i.e. O“ shall follow 355“ on the scale (See Figure 5). 3.5.1.3.7.2 Vertical velocity - The vertical velocity symbols shall show vertical velocity and command vertical velocity from -10,000 ft/min to +lo, O00 ft/min on a moving tape scale on the lef

22、t side of the observers field of view. The tape shall be divided into 100 ft/min increments. The 500 ft/min increments shall be numbered with the last two zero digits omitted (See Figure 7). 3.5.1.3.7.3 Airspeed - The airspeed symbols shall show airspeed and command airspeed from O to 600 knots on a

23、 moving tape scale on the left side of the field of view. The tape shall be divided into ten knot increments. Every 50 knot increment shall be numbered with the last zero digit omitted (See Figure 7) . 3.5.1.3.7.4 Mach number - The mach number symbols shall show mach number and command mach number f

24、rom O to 4 on a moving tape scale on the left side of the field of view. The tape shall be divided into O. 1 mach increments, Every O. 5 mach increment shall be numbered (See Figure 7). 3.5.1. 3.7.5 Altitude - The altitude symbols shall show barometric or radar altitude and command altitude on a mov

25、ing tape scale on the right side of the field of view. Barometric altitude shall be shown from (minus) -1000 feet to an altitude to be designated by the detailed specification of the Head-Up Display for a particular aircraft. %dar altitude shall be shown from O feet to a radar altitude to be designa

26、ted by the detailed specification of the Head-Up Display for a particular aircraft. The tape shall be divided into 100 foot increments. Every 500 foot increment shall be numbered with the last two zero digits omitted (See Figure 8). of the selected missile target from +lo00 knots to -1000 knots. The

27、 symbology shall consist of an electronically displayed moving tape on the right of the field of view. The line segmenta on the tape shall consist of 20knot increments. Every 100 knot increment shall be numbered starting at -1000 knots with the last zero digit omitted (See Figure 19). 3.5.1.3.7.6 Cl

28、osure rate - The olosure rate symbols shall give closure 3.5.1.3.8 Range - - The range symbology shall display range to target in the Guns, Rockets, and Boresight Missiles and Missile Modes. The range symbolog Provided by IHSNot for ResaleNo reproduction or networking permitted without license from

29、IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-BLbLIL bb H 47777Ob OLY3LIY7 7 MIL-D-8164J(AS) release cue passes the center of the flight path marker, a release will occur. The angular difference between the velocity vector and first o

30、ptimum weapon release cue shall be scaled such that one degree of difference displayed on the HUD represents five degrees in real world measurement (See Figure 14). 3.5. 1.3.9.4 Second optimum weapon release cue - The second optimum weapon release cue shall represent the upper solution of a bomb del

31、ivery. Scaling of this cue shall be the same as the first optimum weapon release cue. The upper solution is used in hi-loft and over-the-shoulder weapons deliveries (See Figure 14). 3.5,l. 3.9.5 Pull-up anticipation cue - The pull-up anticipation cue shall be used to indicate an approaching pull-up

32、requirement, (See Figure 15). 3.5.1. 3.10 Terrain carpet - The terrain carpet shall be a perspective rendition of the topography in front of the aircraft, The terrain carpet shall indicate the elevation angles to peak terrain elements with five range gates. Each range gate or elevation line shall be

33、 positioned vertically in the field of view at the highest elevation angle for the terrain within the five range increments, O to 1 nautical miles (nmi), 1 to 2 nmi, 3 to 4.3 nmi, and 4.3 to 6 nmi. The connection of these ive elevation lines with the side Unes results in the per- spective representa

34、tion of the terrain. When one or several range gates are in the shadow of closer terrain, they shall be blanked (See Figure 12). 3.5,1,3,11 Ordnance type and number - The ordnance type and number shall consist of one or two letters to identify the particular missile, or guns, or rockets. Underneath

35、these identification letters shall be a one or two digit number which shall show, in the missile modes, the number of missiles which are ready or number of rounds in the hundreds in the gun submode, or number of rockets in the tens in the rocket submode. A small flashing X over the ordnance type and

36、 number alphanumerics shall indicate that the Master Arm Switch has not been activated, The X shall flash four times a second, The on and off portions of the flash cycle shall be approximately equal duration (See Figure 23). 3,5.1.3.J2 Aiming reticle - The aiming reticle shall be movable and shall d

37、esignate the computed weapon impact point at target range in any position in the field of view (See Figure 22), 3.5.1.3.12. J Armament datum line (boresight) - The armament datum line shall be fixed at HUD boresight in the boresight mode, and boresight weapons mode, which will allow the symbol to be

38、 used to align the HUD in the aircraft. Preferably, the boresight would be within a four degree angle measured on a vertical arc through the center of the eld of the optics. The letters BS shall appear in .e weapon ID area of the field of view when the movable reticle is fixed at boresight (See Figu

39、re 30). Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-Lb4L bb M 7777706 OLLi3450 5 M MIL-D-81641 (AS) 3.5.1.3.13 Missile target - The missile target symbols shall be provided to enable the pilot to locate and track a target. The symbol shall

40、be slaved to and track the target. if the aircraft is capable of simultaneous multi-missile delivery, fYailsff shall appear on each diamond when each target is in range, and the ID number of the missile assigned to eaoh individua target shall appear to the left of the diamond when the missile is loc

41、ked in and ready (See Figure 21). 3.5.1.3.14 Angle of attack error - The angle of attack error shall be a fly-to command symbol. When the left wing of the velocity vector is centered in the middle of the IVf, the command angle of attack is satisfied. The distance from the top line of the Wff to the

42、bottom line of the tCft shall-represent four angle of attack units. The W“ shall move in a path perpendicular to the left “wing“ of the velocity vector (See Figure 3). 3.5.1.3.15 Runway - The runway symbol shall represent the center line and aimpoint of a 700 by 70 foot runway with an aimpoint 330 f

43、eet from the ramp, The runway shall overlie the actual runway in the outside world. The runway symbol shall show perspective length and width of a runway in a one-to-one correlation to the actual runway at any angle and distance of one nautical mile or closer from the actual runway. At a distance of

44、 greater than one nautical mile from the actual runway the runway symbol shall change angular perspective shape, but shall maintain the size of a runway at a distance of one nautical mile (See Figure 9). 3.5. i. 3.16 Aircraft reticle - The aircraft reticle symbol shall represent an extension of the

45、fuselage reference line. The aircraft reticle symbol shall indicate the pitch angle of the aircraft fuselage as compared to the pitch lines or to the command angle of rotation of the aircraft (the flight director). The aircraft reticle shall disappear when the airspeed is greater than the rotation a

46、irspeed plus 50 knots (See Figure 11). 3.5. I. 3.17 Test pattern - A. test pattern shall show a fixed design of symbology. The misalignment or absence of parts of this pattern shall show that there is a defect in the HUD. 3.5. I. 3.18 Standby-reticle image - Thistandby reticle image- shall be as sho

47、wn in Figure 31. 3.5.2 Pilotfs display unit - The Pilots Display Unit (PDU) shall project virtual images of the symbology which is generated on the face of a cathode ray tube by signals from the electronics unt. The display unit shall also. generate and project a virtud image of a standby reticle. T

48、he display unit shall sense the brightness of the real world background in the observers field of view. The display unit shall be capable of recording with a camera the symbology and the real world background. ,a- 19 . Provided by IHSNot for ResaleNo reproduction or networking permitted without lice

49、nse from IHS-,-,-MIL-D-Lb43 bb 49499Ob 0343453 7 MfL-D-81641(AS) 3,5.2. Y Pilots display unit components - The Pilots Display Unit shall con- sist of a cathode ray tube or a laser, electron beadlight beam deflection circui- try, collimating optics, a combining glass, a standby reticle, a light brightness detector and a film camera and its associated optics. 8.5,2.3,3 Cathode ray tube - T