KV-2NM

KV-2NM course-vertical gyro unit

KV-2NM is an aircraft gyroscopic unit / course-vertical instrument used in flight-navigation complexes of Soviet fighter aircraft. In the supplied context, the unit is associated with MiG-23 and MiG-25 aircraft and with the SKV-2N course-vertical system. KV-2NM continuously measures and transmits aircraft attitude and heading parameters to onboard consumers, including the autopilot, navigation complex and cockpit indication equipment.

Function of the KV-2NM course-vertical

The main function of KV-2NM is to provide aircraft heading, roll and pitch data. The unit measures the aircraft’s angular position relative to the horizon and heading reference, then issues electrical signals to connected systems. These signals can be used for flight control, attitude indication, navigation calculations and stabilization. Unlike a simple directional gyro, a course-vertical unit combines heading and vertical reference functions in one gyroscopic assembly.

KV-2NM in MiG-23 and MiG-25 avionics

In the source context, KV-2NM is linked to Soviet fighter aircraft, especially MiG-23 and MiG-25. It is used as part of onboard pilot-navigation equipment where attitude and heading data must be available to several consumers at the same time. The unit can feed the automatic flight-control system, navigation equipment and cockpit indicators. Actual installation and interchangeability depend on the aircraft modification, SKV system version and maintenance documentation.

Electromechanical gyro-stabilized construction

KV-2NM belongs to the class of platform or indicator gyroscopic systems. It is a classical electromechanical device rather than a modern strapdown inertial system. The source context describes its operation as based on a gyroscopic stabilizer with mechanical rotor gyros, dynamically tuned gyros and pendulum correction for maintaining the horizon plane. This construction allows the unit to provide analog attitude and heading information in aircraft systems built around electromechanical avionics.

Signal output and correction of KV-2NM

KV-2NM transmits data to onboard consumers through electromechanical sensors such as sine-cosine rotating transformers. These devices generate analog AC signals proportional to the sine and cosine of the measured angle. In heading operation, the unit can work in gyroscopic semi-compass mode and may also receive correction from an external induction heading sensor, depending on the system configuration. This correction reduces gyro drift and improves heading accuracy.

Ordering and replacement of KV-2NM

When ordering KV-2NM, the buyer should specify the exact designation, aircraft type, installed SKV system, condition and documentation requirements. The unit may be required for MiG-23, MiG-25 or related aircraft equipment depending on the configuration. Before replacement, compatibility with the aircraft wiring, mounting provisions, signal outputs and correction circuits should be checked. Product passport, repair certificate, test report and storage records should be confirmed before supply.

Product Type: Course-vertical gyro unit / aircraft gyroscopic unit
Designation: KV-2NM
Alternative Designations: KV 2NM, KV-2NM gyro unit, КВ-2НМ, курсовертикаль КВ-2НМ
Function: Measurement and output of aircraft heading, roll and pitch data
System Role: Gyroscopic attitude and heading reference unit in pilot-navigation systems
Parent System: SKV-2N course-vertical system according to source context
Application / Where Used: Autopilot, navigation complex, cockpit indicators and flight-control systems
Compatible Aircraft / Equipment: MiG-23, MiG-25 and other aircraft depending on installed documentation
Measured Parameters: Gyroscopic or true heading, roll angle and pitch angle
Heading Mode: Gyroscopic semi-compass mode according to source context
Heading Correction: Gyromagnetic correction with ID-3 induction heading sensor, according to source context
Course Error in GPK Mode: Not more than ±1.5° per hour, according to source context
Gyromagnetic Heading Error: About ±1° when operating with induction heading sensor, according to source context
Static Roll / Pitch Error: Within ±0.5°, according to source context
Dynamic Error: May increase temporarily during deep maneuvers and energetic turns, according to source context
Roll Tracking Range: 360°
Pitch Tracking Range: Up to approximately ±75° to ±85°, according to source context
Readiness / Alignment Time: Up to 5 minutes in normal conditions
Sensitive Elements: Indicator gyro stabilizer based on dynamically tuned gyros, according to source context
Signal Pick-Off: Sine-cosine rotating transformers
Output Signal Type: Analog AC signal proportional to sine / cosine of measured angle
AC Power Supply 1: Three-phase 36 V, 400 Hz
AC Power Supply 2: Single-phase 115 V, 400 Hz
Power Use: Gyro motors, frame follow-up systems, correction circuits and coupling transformers depending on circuit configuration
Construction Type: Classical electromechanical platform / indicator gyroscopic system
Correction Elements: Pendulum correction for horizon reference, according to source context
Condition: New / As-Stored / Overhauled / Serviceable, depending on availability
Technical Documentation: Product passport, repair certificate, test report, storage records and aircraft SKV system documentation if available

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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.