F/A-18C/D/E/F and E/A-18G HUD Camera
The F/A-18C/D/E/F and E/A-18G,
Head Up Display (HUD) camera is a new configuration operating on Lot
XII and higher series F/A-18's.
Part Number 93 - 2040 - 400
The input connector to the
camera utilizes the same connector type and the same pin function as
the legacy camera.
● The body of the camera is the same size and utilizes the same mechanical mounting provisions used on the legacy
● The GO indicator lamp is Night Vision Goggle (NVG) compatible.
● The camera looks into the HUD-combining glasses and accurately records the HUD symbology and outside world,
permitting accurate recording of “what the pilot saw.”
● The new camera has been flown by the US Navy and the following enhanced features were noted:
◊ Better color and higher resolution
◊ FOV extended coverage including recording of all the azimuth heading numerics and the complete
roll angle information in the Navigation mode.
◊ Intended low-light level coverage including night recording
◊ Two Built-In Test (BIT) features
Automatic Exposure Control
with lens iris
● Adjustable air-to-ground exposure lock (0-10 sec)
● Visual event mark, completion of GRD
● 115 VAC, 85 to 265 VAC, 47-440 Hz, Single Phase “C”
● Pickup device: Interline-transfer hyper HAD CCD, 1/3”
● Horizontal resolution:
◊ NTSC: 470 TV lines
● Picture elements:
◊ NTSC: 768(h) x 494(v)
● S/N ratio:
◊ NTSC: >-48dB
Sensitivity: 2000 Lux at f/11.00
● Automatic AGC
● Minimum sensitivity: 0.975 Lux AGC-On
● Shutter speeds: 1/60th second, flickerless,
and CCD iris (AEC), Off for F-18
● Gamma: 0.45/1
● White balance: ATW
● Video formats: Y/C component and NTSC composite
(NTSC used on F-18)
● Weight: 2 lb 6 oz
● 12 month warranty
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).
● EMI: RE-102, CE-102, RS-103 including video during radiation.
© 2018 Photo-Sonics, Inc.