Dual-control missile guidance: a simulation study

• Autorzy: Bużantowicz W. , Pietrasieński J.

Identyfikatory

DOI

10.15632/jtam-pl.56.3.727

• Języki publikacji: EN

Abstrakty

EN

Theoretical considerations and a simulation study concerning description and analysis of new autopilot structures and issues relating to conversion of guidance commands into deflections of a complex system of control surfaces aimed at minimizing the miss distance value are presented in this paper. Due to nonlinear and nonstationary nature of the phenomena associated with the guidance process, a significant role is assigned to simulation studies. A comparative analysis has been made of the guidance processes of three models of a dual-control missile, which differ in terms of formulae implemented in the control command converters.

Słowa kluczowe

EN

dual-control missile; autopilot; guidance; miss distance

• Wydawca: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
• Czasopismo: Journal of Theoretical and Applied Mechanics
• Rocznik: 2018
• Tom: Vol. 56 nr 3
• Strony: 727--739
• Opis fizyczny: Bibliogr. 16 poz., rys., tab.

Twórcy

autor

Bużantowicz W.

• Military University of Technology, Faculty of Mechatronics and Aerospace, Warsaw, Poland

autor

Pietrasieński J.

• Military University of Technology, Faculty of Mechatronics and Aerospace, Warsaw, Poland

Bibliografia

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• 2. Grycewicz H., Mosiewicz R., Pietrasieński J., 1984, Radio Control Systems (in Polish), Military University of Technology, Warsaw
• 3. Hua W.H., Meng Q.L., Zhang J.P., Zhang Y.J., 2016, Differential game guidance law for dual and bounded controlled missiles, Journal of Beijing University of Aeronautics and Astronautics, 42, 9, 1851-1856
• 4. Hull D.G., Speyer J.L., Burris D.B., 1990, Linear-quadratic guidance law for dual control of homing missiles, Journal of Guidance, Control and Dynamics, 13, 1, 137-144 5. Ibarrondo F.B., Sanz-Ar´anguez P., 2016, Integrated versus two-loop guidance-autopilot for a dual control missile with high-order aerodynamic model, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 230, 1, 60-76
• 6. Idan M., Shima T., Golan O.M., 2007, Integrated sliding mode autopilot-guidance for dual control missiles, Journal of Guidance, Control and Dynamics, 30, 4, 1081-1089
• 7. Ochi Y., 2003, Design of a normal acceleration and angle of attack control system for a missile having front and rear control surfaces, Transactions of the Japan Society for Aeronautical and Space Sciences, 51, 598, 621-627
• 8. Ochi Y., Kanai K., Saka N., Imado F., Kuroda T., 1991, A design method of normal acceleration control system for a missile with front and rear control surfaces, Proceedings of Navigation and Control Conference, New Orleans LA, USA, 196-207
• 9. Schroeder W., 2001, Dual-control scheme for improved missile maneuverability, Patent No. US RE37,331 E
• 10. Shima T., Golan O.M., 2006, Bounded differential games guidance law for dual-controlled missiles, IEEE Transactions on Control Systems Technology, 14, 4, 719-724
• 11. Shima T., Golan O.M., 2007, Linear quadratic differential games guidance law for dual controlled missiles, IEEE Transactions on Aerospace and Electronic Systems, 43, 3, 834-842
• 12. Shtessel Y.B., Tournes C.H., 2009, Integrated higher-order sliding mode guidance and autopilot for dual-control missiles, Journal of Guidance, Control and Dynamics, 32, 1, 79-94
• 13. Siouris G.M., 2004, Missile Guidance and Control Systems, Springer, New York
• 14. Yan H., Ji H., 2012, Integrated guidance and control for dual-control missiles based on small-gain theorem, Automatica, 48, 10, 2686-2692
• 15. Yanushevsky R., 2007, Modern Missile Guidance, 1st Edition, CRC Press, New York
• 16. Zarchan P., 2012, Tactical and Strategic Missile Guidance, 6th Edition, AIAA, Reston

Uwagi

PL

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2018).