Part Number 93 - 2040 - 501       NSN 5821-01-662-2657       MX-10403A/AXQ
Part Number 93 - 2040 - 502       NSN 5821-01-662-2666       MX-10403B/AXQ

Features

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 camera.

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

General Specifications

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)

Switches on camera to control VCR

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, 1/100,000 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

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 2,437m (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

FOV Horizontal	Degrees Vertical	FOV Horizontal	Milliradians Vertical	Application
22.06	16.63	384.9	290.3	HUD Special Boresighted to all US Navy requirements

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