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
© 2018 Photo-Sonics, Inc.