TM 1-1510-262-10
Figure 4-6. Electro-Optic Missile Sensor
Table 4-5.
Electronic Control Unit Features
ITEM #
FEATURE
DESCRIPTION
1
Mounting Holes (4 places)
Used to secure EOMS to platform.
2
Optical Aperture (120 FOV)
Collects ultraviolet (UV) emissions.
3
BIT Lamp
Active during BIT as UV source.
4
J1 connector
Power and data interface with the ECU.
(4) Coarse/Acquisition - Miniature Integrated GPS/INS Tactical System (C-MIGITS). The C-MIGITSTM
III Global Positioning System (GPS) and Inertial Navigation System (INS) provides essential three dimensional po-
sition, velocity, precise time, attitude, heading, angular rate, and acceleration. An Inertial Measurement Unit (IMU)
measures angular rates and translational accelerations using accelerometers and gyroscopes. The C-MIGITSTM
III operates from +28 Vdc provided by an EGI Power Supply. The CMWS on the RC-12 platform can operate in
the pseudo INS mode without the GPS/INS components by installing a jumper cable that changes the aircraft ID
for the ECU. The aircraft ID jumper cable is installed between the wiring harness PP902 and ECU J2 when not
using the C-MIGITS III. This change in aircraft ID indicates which software will be used by the ECU during startup.
Integral to the C-MIGITS are the RS-232 to RS-422 converter and EGI Power Supply. The RS-232 to RS-422 Data
Converter provides bi-directional data transfer between the C-MIGITSTM III and the ECU. EGI Power Supply, this
Power Supply unit regulates and ilters the +28 Vdc aircraft power and is used to supply power to the C-MIGITSTM
III module and the Data Converter.
4-11
