Core Avionics Computer (CAC) SU-30MKM

DARE took up the development and delivery in quantities of Mission
Computers, Display Processors and Radar Computers for the Su 30
avionics upgrade. The requirements were analysed and instead of
building three different computers DARE developed nine functional
modules. The chassis was also common across the computers. These
modules use state of the art processors. They are designed as
independent modules to do a specific function such as generating
computer generated imagery for display on HUD or MFD. But they are able
to communicate with the main processor module through high speed Dual
Ported RAMs. This makes development of software for these specific
functions as independent activities. Also, HW changes in one module
does not affect the other modules. Hence this approach reaps the
benefits of Open System Architectures to the full. Later when proposals
for upgrade of the MiG 27 aircraft came up, DARE could respond with a
ready solution by configuring the Display Processor of the Su30
avionics.

Su 30 Computer consists of the following modules : Main Processor
Module ,1553B interface Module, Colour Symbol Gen. Module, Stroke
Symbol Gen. Module, Discrete Interface Module, Power Supply Module,
Chassis Aircraft Specific Modules (for CAC only), Video Switching
Module and Analog / Synchro Interface Module.

The Core Avionics Computer (CAC) developed by DARE is housed in a
aircraft industry standard 3/4 th ATR chassis with an option rear mount
ARINC 404 connector or front mounted 38999 series connectors. The tray
is mounted in the equipment bay/rack of the aircraft and the computer
is plugged in to the tray. It is forced air cooled and weighs less than
8 Kg. It works on both 115V 400Hz AC and 28V DC aircraft power supplies
and consumes less than 80 W of power.

CAC Functions The following are the functions of various modules of the CAC

a) Through the CPU module:

Control of the 1553B interface

• Primary mission, navigation and weapon computations
• Air Data Computations
• Control of the UFCP for avionics system moding and data insertion and data readout.
• Management of the display system (MFDs and HUD)
• Management of the Stores (weapons) system
• Reading and writing of mission data from the Data Loader Flash Disk.
• Coordination of LDP and FLIR for navigation and targetting functions
• Auto-pilot function

b) Through the Colour Symbol Generator and Monochrome Symbol Generator Modules:

i) Raster mode writing on the MFDs in colour (mixing with external sensor video)
ii) Stroke Mode writing on the HUD in monochrome.

c) Through the Intelligent Dual channel 1553B interface board:
Provide for the exchange of data among avionics subsystems in the
primary and reversionary modes; Control of the ARINC 429 channels;
Interface air data system, hand controller etc through the analog
inputs.

• Through Discrete Interface Module Interface aircraft discretes
  including the HOTAS switches to the CPU board and Interface the CAC’s
  discrete outputs to the stores management system.

e) Through Synchro and Analog output Module interface the automatic flight control system and Crash Data recorder system.

f) Through the Video switching module provide for switching the
video signals in the avionics system to the MFD, HUD and the Video Tape
Recorder.