F-15CD MSIP HUD Camera

  The F-15C/D Multi Stage Improvement Program (MSIP) , Head Up Display (HUD) camera is a new configuration working in conjunction with Video Improvement TCTO 1F-15-1481.  
  The camera looks directly into the HUD-combining glasses and accurately records the HUD symbology and outside world, permitting accurate recording of precisely what the “pilot sees”
with no boresighting errors.
  Automatic Lens/Iris Exposure Control for Flickerless HUD Symbology Recording.
Increases resolution and color separation.
NO Over-the-Nose Vision Blockage compared to existing HUD camera.
Large Dynamic Light Range - 26.5 f-stops.
Extended low light level recording (.35 LUX).
Intended low-light level coverage including night recording.
Automatic Gain Control, S/N Ratio increases to –18dB, (6 full f-stops).
No mechanical changes to the aircraft, uses MSIP camera mounting.
Extended coverage of Field of View, 321 milliradians
Aircraft glare shield provided as part of camera.
Minimum changes to the aircraft.
  Automatic Exposure Control with lens iris
Large Dynamic Light Level Range
NO damage when looking directly at the sun
Input Power— +28 VDC.
Power Consumption less than 15 Watts
Pickup device: Interline-transfer hyper HAD CCD, 1/2”
Horizontal resolution:
        ◊ NTSC: 470 TV lines
Picture elements:
        ◊ NTSC: 768(h) x 494(v)
S/N ratio:
        ◊ NTSC: >48dB
Sensitivity: 2000 Lux at f/5.6
AGC: on/off (automatic), increases by 6 f-stops
Minimum sensitivity: 0.35 Lux AGC-ON
Shutter speeds: 1/60th second, 1/100,000 second,
   flickerless, and CCD iris (AEC), Off for F-15 MSIP
Gamma: 0.45/1
White balance: ATW, 3200K, 5600K, and Manual
Video formats: Y/C component and NTSC
   composite (NTSC used on this configuration)
Weight: 2 lb 6 oz
18 month warranty
  Vibration (non-gunfire) random/sine low frequency region V-FF-3. Perform vibration. Equipment was operating and
   monitored during testing.
Vibration (gunfire) sine test schedule (total time each axis – 150 min)
Vibration (gunfire) sine test levels. Perform sine vibration. Total time in each axis was 150 minutes.
Vibration (non-gunfire) random test levels. Perform endurance levels 120 minutes each axis. Equipment was  
   operating and monitored during testing.
Service shock (longitudinal, vertical and lateral). Perform 6 total shocks, 3 in each direction for each test.
   Figure 4-3.2: Service shock test requirements / Shock response spectrum region S-FF-2.
Crash safety (Perform crash safety per Fig 4-5). Crash test requirements / All shock regions.
Thermal non-operating thermal cycling: -57°C. Dwell for a period of 2 hrs. Raise the temperature to +125°C and dwell 
   for 16 hrs.
Operating thermal cycling: -40°C. Dwell for a period of 2 hrs. Raise the temperature to +71°C and dwell for 16 hrs. 
   Raise the chamber temperature to +85°C and dwell for 30 minutes.
Thermal shock: Perform thermal shock per MIL-STD-810C Method 503.1. Three thermal cycles from +71°C to –57°C 
   with a 5 minute maximum transfer time and a 4 hr dwell at each temperature plateau.
Altitude: Normal operating – test per MIL-STD-810F, Procedure 2. Reduce pressure at a rate not to exceed 2,000 
    Ft/min to an altitude of 50,000 ft. Dwell for a period of 1 hr.
Explosive decompression: Test per MIL-STD-810F, Procedure 4. Reduce chamber pressure to 2,437 m (8,000 ft), then 
   in <0.1 seconds reduce pressure to an altitude of 12,192 m (40,000 ft). Maintain this pressure for 10 minutes.
Salt and fog: Test per MIL-STD-810F, Method 509.4. Perform 2 cycles of Salt fog of 24 hrs and 24 hrs drying per cycle.
Explosive atmosphere: Test per MIL-STD-810F, Method 511.4, Procedure 1 (operation in explosive atmosphere).

Based on similarity to tests conducted on F/A-18/C/D/E/F
Lens Focal Length FOV Horizontal Degrees Vertical FOV Horizontal Milliradians Vertical Application
14.77mm, f1.4 24.45 18.46 426.7 322.1 HUD-Special
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