GA-2M

GA-2M gyro unit for attitude and heading systems

GA-2M is an aircraft gyro unit used as a central element of compact gyro-vertical systems and aircraft navigation systems such as GMK-1. The unit is intended to determine and transmit aircraft roll and pitch angles relative to the true horizon. It can also support heading reference functions, including storage of true or orthodromic heading, depending on the system configuration. GA-2M is used as part of a broader navigation and attitude reference system and is not normally considered a standalone cockpit indicator.

Function of the GA-2M gyro unit

The main function of the GA-2M gyro unit is continuous measurement of aircraft attitude in roll and pitch. The unit converts gyro position data into electrical signals for remote transmission to cockpit attitude indicators, automatic flight control equipment and onboard computing or navigation units. These signals allow the aircraft systems to receive stable attitude information during flight, maneuvering and route navigation. The unit also participates in heading reference operation where it is installed as part of GMK-type heading systems.

GA-2M correction and stabilization principles

GA-2M uses gyro-based attitude reference principles with correction circuits that reduce accumulated errors. The source context refers to liquid pendulum switches used to correct gyro drift caused by Earth rotation and internal friction. The system may also include latitude correction, normal correction and fast synchronization modes depending on the aircraft installation. These functions help maintain usable attitude and heading reference data during sustained operation, while avoiding excessive influence from short-term aircraft oscillations.

Use of GA-2M in MGV and GMK systems

The GA-2M gyro unit is associated with compact gyro-vertical equipment and heading systems such as GMK-1AE and GMK-1G. In such systems, it can operate together with other blocks, cockpit controls, heading sensors and remote transmission circuits. The system configuration may include two gyros, or the unit may work in a paired arrangement with another half-set for mutual correction. For replacement or procurement, the exact aircraft system configuration and modification should be confirmed against the technical documentation.

Aircraft application of the GA-2M gyro unit

GA-2M is used on Soviet and Russian aircraft and helicopters where compact gyro-vertical and heading reference systems are installed. Source context indicates application on Mi-8 and Mi-24 family helicopters and aircraft such as An-24, An-26 and Yak-40, depending on the installed navigation system. Since avionics packages may differ by aircraft modification, overhaul history and modernization status, applicability must be checked through the aircraft equipment list and the relevant GMK / gyro-vertical system documentation.

Maintenance and ordering of GA-2M

When ordering GA-2M, it is important to specify the required modification, condition, documentation and mounting configuration. The unit may require a damping or shock-mounted base because gyro instruments are sensitive to vibration and mechanical impact. Before removal, maintenance personnel must observe gyro run-down time after power-off. For supply purposes, the buyer should confirm whether the requirement is for the gyro unit only, the unit with mounting base, or a tested set for a specific navigation system.

Product Type: Aircraft gyro unit / gyro-vertical system unit
Designation: GA-2M
Alternative Designations: GA 2M, GA-2M gyro unit, ГА-2М, гироагрегат ГА-2М
Function: Measurement and output of aircraft roll and pitch angles
Additional Function: Heading reference / storage of true or orthodromic heading depending on system configuration
Parent Systems: Compact gyro-vertical system, GMK-1, GMK-1AE, GMK-1G according to source context
Application / Where Used: Aircraft attitude and heading reference systems
Compatible Aircraft / Equipment: Mi-8, Mi-24, An-24, An-26, Yak-40 and other aircraft depending on installed system documentation
Measured Parameters: Roll angle, pitch angle and heading reference data depending on configuration
Signal Output: Electrical remote transmission signals to attitude indicators, autopilot and onboard navigation equipment
Gyro Configuration: Two three-degree gyros or paired half-set arrangement, according to source context
Correction Elements: Liquid pendulum switches for gyro drift correction, according to source context
AC Power Supply: Three-phase 36 V ±10%, 400 Hz ±2%
DC Power Supply: 27 V ±10%
Gyro Start-Up Time: Up to 5 minutes
Rotor Run-Down Time After Power-Off: Not less than 10–15 minutes, according to source context
Gyro Drift in DG Mode: Not more than ±1° to ±2° per hour, according to source context
Remote Heading Transmission Error: Not more than ±0.5°
Roll / Pitch Output Error: Within ±1° in stabilized straight flight, according to source context
Fast Synchronization Rate: Approximately 2° to 4° per second
Normal Correction Rate: Approximately 2° to 3° per minute
Approximate Dimensions: About 250 × 230 × 240 mm with mounting base, according to source context
Approximate Weight: Not more than 7.5–8.5 kg depending on modification and mounting frame
Operating Temperature Range: −60 °C to +60 °C
Heating: Built-in heating element and thermostat, according to source context
Mounting: Damped / shock-mounted platform for vibration protection
Condition: New / As-Stored / Overhauled / Serviceable, depending on availability
Technical Documentation: Product passport, test report, storage records and aircraft system documentation if available

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Returns & Changes (Restocking Fee)
For selected items, a RESTOCKING FEE of 10% may apply in case of return, order cancellation, or changes to the order specifications. This condition applies only to certain products and is confirmed at the order approval stage.

Warranty
All products are covered by a standard 6-month warranty.
Extended warranty is available upon request and is agreed individually; it may affect the final product price.