• Home
• Optical Tracking
  • Super Radot Tracking System
  • Cine-Sextant Tracking Mount
  • MMTS Tracking Mount
  • Compact Tracking Mount (CTM)
  • Mini-Sextant Tracking Mount
  • Nano-Sextant Tracking Mount
  • Argus Instrument Control System
• Airborne Cameras
  • HUD and Airborne Video Home Page
  • Head-Up Display (HUD) Cameras
    • Alpha Jet HUD Camera (2 LRU's)
    • Alpha Jet Video System
    • A/OA-10C Video Camera
    • A-4M HUD Camera
    • AV-8B Night Attack Replacement Camera
    • F-15CD MSIP HUD Camera
    • F-16A/B/ADF HUD Camera
    • F-16C/D Cockpit Camera (CCAM)
    • F/A-18A/B HUD Camera
    • F/A-18C/D/E/F/G HUD Camera
    • Integrated HUD Camera
    • T-45C HUD Camera
  • Multi-Purpose Ruggedized Equipment
    • Remote-Head Camera
• Video Gallery
• News Items
• Company Information
  • Request Additional Information
  • AS9100 Certificate
  • Calendar of Events
  • Engineering Services
  • Equipment Service
  • Purchase Order Terms and Conditions
  • Warranty Policy
  • Company History and Milestones
  • Map to Facility
  • Employment
  • Links
• Contact Us

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.

FEATURES

●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.

GENERAL SPECIFICATIONS

●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

ENVIRONMENTAL SPECIFICATIONS*

● 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

OPTICAL SPECIFICATIONS

© 2018 Photo-Sonics, Inc.