BDG-26 Variant 1

BDG-26 Variant 1 damping gyroscope block

BDG-26 Variant 1 is an aircraft damping gyroscope block used to measure angular velocity of an aircraft or moving object along one control axis. Depending on installation, the block can be assigned to roll, heading or pitch channels. It generates an electrical signal proportional to angular rate and sends this signal to automatic flight control systems, damping circuits and onboard stabilization equipment.

Function of the BDG-26 angular rate block

The main function of BDG-26 is to provide angular rate feedback for aircraft control and damping systems. The block measures angular velocity within its working range and helps suppress unwanted oscillations in the controlled axis. In automatic control systems, this signal is used to improve aircraft stability, reduce short-period movements and support smoother operation of autopilot or flight-control channels.

BDG-26 in SAU and ABSU systems

BDG-26 blocks are used in Soviet and Russian automatic control systems, including SAU and ABSU-type systems. In aircraft such as Tu-154, the source context describes installation of several independent blocks for separate roll, heading and pitch channels. Each block is mounted according to the aircraft structural axes, so the measured angular velocity corresponds to the assigned control channel. The exact system role depends on the aircraft type and automatic control system documentation.

Internal composition of BDG-26 Variant 1

According to the source context, the BDG-26 block includes a DUSU2 unified angular rate sensor, a pulse transformer block and a gyro motor rotation control block. This internal composition allows the unit to measure angular velocity, form the required electrical output and monitor gyro motor operation. The block works as a dedicated aviation control sensor rather than as a cockpit display or navigation indicator.

Aircraft application of BDG-26

BDG-26 is associated with automatic control and stabilization systems of civil, transport, military and special aircraft. The source context mentions Tu-154, Il-76, An-124 Ruslan, Su-27, MiG-29 and Mi-26 helicopters. Actual applicability must be confirmed by aircraft modification, installed SAU / ABSU system and maintenance documentation. The same designation may appear in different channels or configurations depending on the aircraft system architecture.

Installation and ordering of BDG-26

BDG-26 blocks are installed rigidly on aircraft structural elements, with orientation aligned to the aircraft construction axes. They are normally located in technical compartments, avionics racks or equipment bays, not on the cockpit panel. When ordering BDG-26 Variant 1, the buyer should specify the required variant, control channel, aircraft type, condition, documentation package and test status. Product passport, repair certificate, storage records and bench test confirmation are important for aviation supply.

Product Type: Damping gyroscope block / aircraft angular-rate sensor block
Designation: BDG-26 Variant 1
Alternative Designations: BDG-26 ver.1, BDG-26 version 1, БДГ-26 вариант 1, БДГ-26 исп.1
Designation Meaning: Damping Gyroscope Block / Блок демпфирующих гироскопов
Function: Measurement of angular velocity and output of proportional electrical signal
Measured Axis: Roll, heading or pitch depending on installation channel
Angular Rate Measurement Range: ±6°/s
Application / Where Used: SAU / ABSU automatic flight-control and stabilization systems
Compatible Aircraft / Equipment: Tu-154, Il-76, An-124, Su-27, MiG-29, Mi-26 and other aircraft depending on documentation
Internal Sensor: DUSU2 unified angular-rate sensor, according to source context
Internal Blocks: Pulse transformer block and gyro motor rotation monitoring block, according to source context
Gyro Motor Power Supply: 36 V AC, 400 Hz
Potentiometer Power Supply: 27 V DC; source context also indicates 27 ±7 V DC
Consumed AC Current: Not more than 0.75 A per phase total, according to source context
Readiness Time: Not more than 1 second according to the provided final specification; other source context also mentions up to 60 seconds
Measurement Error Reference: 1–3% of scale in the operating range, according to source context
Operating Temperature Range: −60 °C to +60 °C
Weight: Not more than 2.3 kg
Mounting: Rigid installation on fuselage structural elements, aligned with aircraft construction axes
Installation Area: Technical compartments, avionics racks or automatic control system equipment areas depending on aircraft type
Condition: New / As-Stored / Overhauled / Serviceable, depending on availability
Technical Documentation: Product passport, test report, storage records, repair certificate and SAU / ABSU system documentation if available

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