MATHEMATICAL MODELING OF THE OPERATION OF AN AIRCRAFT GYROSCOPE
Abstract
A dynamically tuned gyroscope used in a compact gyroscopic angular velocity vector meter of an aircraft is considered. Guided missile inclination methods are analyzed. Mathematical models of the gyroscope rotor motion on a fixed base and the angular motion of the aircraft missile gyroscope itself are presented.
Keywords
missile, drone, flight, system, guidance, homing, angular motion.
References
- Topilskaya S.V., Borodulin D.S., Kornyukhin A.V. Experimental assessment of permissible mechanical effects on a dynamically tuned gyroscope. Bulletin of Bauman Moscow State Technical University. Series: Instrument Engineering. 2018. No. 4, pp. 69-71.
- Novikov L.Z., Shatalov M.Yu. Mechanics of dynamically tuned gyroscopes. Moscow, Nauka Publ., 1985. 245 p.
- Losin, A. A. Mathematical model of the homing system of an anti-tank guided missile. Izvestiya Tula State University. Technical sciences. 2018. Issue 11, pp. 337–340.
- Patent 1473893 Germany, MKI G01c, NKI 42c, 25/51. Federal Trial Code. Priority 1970.
- A.s. 282956 USSR. Gyroscopic device / V. Ya. Raspopov, Yu. N. Oskin (USSR). Priority 1988.
- US Patent 3,225,609, IPC G01c, NKI 74-5.7. Two-axis Gyroscope. Priority 1962.
- US Patent 3,417,627, IPC G01c, NKI 74-5.6. Free-rotor gyro. Priority 1966.
- Raspopov V. Ya. Theory of Gyroscopic Systems. Inertial Sensors. Tula: Tula State University Press, 2012. 256 p.
Downloads
Download data is not yet available.