BUG-14

BUG-14 amplifier unit for the IKV-1 inertial reference system

BUG-14 is an aircraft electronic unit used as part of the IKV-1 strapdown inertial attitude and heading reference system. The designation is commonly interpreted as “gyro sensor amplifier unit.” The block processes electrical signals from gyroscopic sensors and prepares them for further use by the aircraft navigation and flight-control equipment. In the IKV-1 system architecture, BUG-14 supports the generation and correction of attitude and heading information used by onboard systems and cockpit indication.

Function of the BUG-14 gyro sensor amplifier block

The main function of BUG-14 is amplification and phase-sensitive rectification of signals received from gyro sensor elements. These signals are used in the inertial reference channel to support aircraft attitude, roll, pitch and heading information. The unit works as an analog signal-processing block and forms part of the signal chain between gyroscopic sensing elements and correction / output units. Its operation is continuous during flight, because the inertial reference system must maintain stable navigation and spatial orientation data from power-up through aircraft operation.

BUG-14 in the IKV-1 system

Within the IKV-1 inertial attitude and heading system, BUG-14 works together with related blocks and control units. The system context includes the KV-1 attitude and heading unit, BK-20 correction block, PND-1 or PU-38 initial data input panel, and magnetic heading correction components such as ID-6 and KM-2. BUG-14 is not a standalone navigation instrument. It is a functional module inside a larger inertial reference system, so interchangeability, testing and replacement must be checked according to the IKV-1 technical documentation and aircraft maintenance manual.

Aircraft application of BUG-14

The IKV-1 system and its associated blocks were used on a number of Soviet and Russian military aircraft. Source context indicates use on MiG-29 aircraft. Since military avionics installations may differ by aircraft modification, avionics package and modernization status, BUG-14 applicability should be confirmed by the aircraft equipment list, maintenance documentation and installed IKV-1 configuration. For procurement purposes, the requested series, documentation set and frame requirement should be specified before quotation.

BUG-14 Series 1 and Series 2

BUG-14 is commonly encountered on the aviation technical property market in Series 1 and Series 2 versions. The exact series is important because mounting, electrical compatibility, documentation and test procedures may differ. The unit is installed in a dedicated shock-mounted frame, with RA-5 Series 1 mentioned in the source context for BUG-14 Series 2. When ordering or replacing the unit, the buyer should indicate whether BUG-14 Series 1 or BUG-14 Series 2 is required and whether the RA-5 frame must be supplied together with the block.

Maintenance, testing and ordering of BUG-14

BUG-14 is a military avionics module, and full technical parameters, adjustment procedures, connector pin assignments and test methods are usually defined in technical specifications and aircraft maintenance documentation. Open sources normally provide only general function, system relation and basic physical data. For maintenance or procurement, the required condition should be stated clearly: new old stock, serviceable, overhauled or repairable. It is also important to confirm passport availability, storage history, test status and compatibility with the customer’s IKV-1 system.

Product Type: Gyro sensor amplifier unit / avionics signal-processing block
Designation: BUG-14
Alternative Designations: BUG 14, BUG-14 Series 1, BUG-14 Series 2, БУГ-14, БУГ-14 серия 1, БУГ-14 серия 2
Designation Meaning: Gyro Sensor Amplifier Unit / Блок усилителей гиродатчика
Parent System: IKV-1 strapdown inertial attitude and heading reference system
Function: Amplification and phase-sensitive rectification of gyro sensor signals
Signal Role: Processing of gyro sensor signals for attitude, roll, pitch and heading correction channels
Operating Mode: Continuous operation during aircraft flight
Typical Channels: Independent channels for roll, pitch and heading signal processing, according to source context
Associated Equipment: KV-1, BK-20, PND-1, PU-38, ID-6, KM-2, according to IKV-1 system context
Mounting Frame: RA-5 Series 1 shock-mounted frame, according to source context
Application / Where Used: Military aircraft avionics inertial reference system
Compatible Aircraft / Equipment: MiG-29 and other aircraft fitted with IKV-1, depending on documentation
Power Supply: 27 V DC and 36 V AC 400 Hz, according to source context
Electrical Connection: Low-frequency cylindrical aircraft connectors, according to source context
Construction: Monoblock aircraft electronic module
Approximate Dimensions: About 140 × 160 × 280 mm, according to source context
Approximate Weight: Not more than 3.5–4.0 kg, according to source context
Operating Temperature Range: −60 °C to +60 °C, according to source context
Environmental Context: Designed for aircraft vibration, maneuvering loads and reduced atmospheric pressure conditions
Series / Modifications: Series 1 and Series 2
Condition: New / As-Stored / Overhauled / Serviceable, depending on availability
Technical Documentation: Product passport, test report, storage records and IKV-1 system documentation if available

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