BDG-26 Variant 2
damping gyroscope block
Description
BDG-26 Variant 2 damping gyroscope block
BDG-26 Variant 2 is an aircraft damping gyroscope block used to measure angular velocity of an aircraft or helicopter around one of its coordinate axes. Depending on installation, the unit can operate in roll, heading / yaw or pitch channels. It converts angular motion of the aircraft body into proportional electrical signals that are transmitted to the automatic flight-control system, autopilot or stabilization equipment.
Full descriptionCollapse description
Function of the BDG-26 angular-rate block
The main function of BDG-26 Variant 2 is to provide angular-rate feedback for flight-control damping. When the aircraft begins to rotate around the measured axis, the gyroscopic sensing element detects this motion and forms an electrical signal proportional to angular velocity. The automatic control system uses this signal to reduce oscillations and improve dynamic stability. The unit is not a cockpit indicator; it is a sensor block inside the aircraft control loop.
BDG-26 Variant 2 internal construction
BDG-26 Variant 2 is built around the DUSU-2 unified angular-rate sensor. The block may also include signal-conditioning elements, interference filtering circuits and gyro motor operation monitoring, depending on the configuration. The unit forms a feedback signal for stabilization channels and can be checked on specialized ground equipment. The source context mentions PP-25 as a checking panel used for technical inspection of BDG-type blocks.
Use in automatic control systems
BDG-26 Variant 2 is installed in aircraft automatic control systems, autopilots, stability augmentation systems and flight-navigation complexes. It is used in systems of manual-assisted and automatic control where angular-rate information is required for damping. Since each channel depends on physical orientation, the block must be installed according to the assigned aircraft axis and system documentation.
Installation of BDG-26 Variant 2
The unit is mounted on a rigid base or frame inside an avionics compartment, technical bay or automatic-control equipment area. According to the source context, the block is fixed by four screws. Correct alignment with the aircraft construction axes is important because the measured axis is defined by the installation position. Vibration resistance and operation over a wide temperature range allow the unit to work in typical aircraft onboard conditions.
Ordering and replacement of BDG-26 Variant 2
When ordering BDG-26 Variant 2, the buyer should specify the exact variant, aircraft type, measured channel and automatic control system where the unit will be installed. It is also important to confirm required condition, passport availability, repair certificate, storage records and test status. For maintenance or bench checking, wiring data, connector pinout, permissible error limits and PP-25 test procedure may be required.
Technical details
- Product Type
- Damping gyroscope block / aircraft angular-rate sensor block
- Designation
- BDG-26 Variant 2
- Alternative Designations
- BDG-26 var.2, BDG-26 version 2, БДГ-26 вариант 2, БДГ-26 вар.2, БДГ-26 исп.2
- Designation Meaning
- Damping Gyroscope Block / Блок демпфирующих гироскопов
- Function
- Measurement of angular velocity and output of proportional electrical signal
All specificationsCollapse specifications
- Measured Axis
- Roll, heading / yaw or pitch depending on installation channel
- Signal Role
- Angular-rate feedback for damping and automatic control channels
- Application / Where Used
- SAU / autopilot systems, stabilization systems, flight-navigation complexes and automatic control equipment
- Sensitive Element
- DUSU-2 unified angular-rate sensor
- Operating Principle
- Gyroscopic sensing of angular motion with conversion into an electrical output signal
- Checking Equipment
- PP-25 checking panel, according to source context
- Gyro Motor Power Supply
- 36 V AC
- Power Supply Frequency
- 400 Hz
- Potentiometer Power Supply
- 27 V ±7 V DC
- Consumed AC Current
- Not more than 0.75 A per phase total, according to source context
- Start-Up Current Reference
- Up to 0.5 A per phase in start mode, according to source context
- Readiness Time
- Not more than 1 second according to the provided final specification; another supplied fragment mentions up to 3 minutes
- Output Signal
- DC or AC electrical voltage proportional to angular velocity, depending on system circuit
- Operating Temperature Range
- −60 °C to +60 °C
- Dimensions
- 142 × 175 × 166 mm, according to source context
- Weight
- Not more than 2.3 kg according to the provided final specification
- Mounting
- Rigid base / frame mounting with four screws
- Environmental Context
- Aircraft vibration and onboard operating loads
- Technical Documentation
- Product passport, repair certificate, test report, storage records, connector pinout and SAU / autopilot system documentation if available
Payment & delivery
Orders ship from our hub in Dubai. Partner stock is first transferred to Dubai, then shipped to you.
Dubai stock: 100% before dispatch. Partner stock (Remote stock) and Pre-order: 50% advance payment to start the order and 50% before shipment from Dubai to you.
Availability, lead time, delivery cost and payment terms are confirmed for your order before payment.
Payment & delivery terms