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Integrated guidance and autopilot design for a chasing UAV via high-order sliding modes. (English) Zbl 1254.93059

Summary: Integrated Guidance and Control (IGC) approaches exploit the synergy between guidance and control designs. This study focuses on the integrated guidance and control (autopilot) design for a chasing Uninhabited Aerial Vehicle (UAV) against a target aircraft. A second-order sliding structure with a Second-Order Sliding Mode (SOSM) including a High-Order Sliding Mode (HOSM) observer for the estimation of the uncertain sliding surfaces is selected to develop an integrated guidance and autopilot scheme. In order to make the design synthesis easier, intermediate control variables for partial derivatives of a sliding surface are carefully selected. The resulting sliding surface structure is simple and sufficient to relate the actuator input to the sliding surface. The potential of the proposed method is demonstrated through an aircraft application by comparing its simulation performance, number of tuning parameters used, and information needed for its implementation with an approach where the guidance law and the controller are designed separately.

MSC:

93B12 Variable structure systems
70P05 Variable mass, rockets
93C15 Control/observation systems governed by ordinary differential equations
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[1] Zarchan, P., Tactical and strategic missile guidance—fifth edition, progress in astronautics and aeronautic, vol. 219, (2007), AIAA
[2] Lu, P.; Doman, D.B.; Schierman, J.D., Adaptive terminal guidance for hypervelocity impact in specified direction, AIAA journal of guidance, control and dynamics, 29, 2, 269-278, (2006)
[3] Kim, B.S.; Lee, J.G.; Han, H.S., Biased PNG law for impact with angular constraint, IEEE transactions on aerospace and electronic systems, 34, 1, 277-288, (1998)
[4] Smith, A.L., Proportional navigation with adaptive terminal guidance for aircraft rendezvous, AIAA journal of guidance, control and dynamics, 31, 6, 1832-1835, (2008)
[5] Machol, R.E.; Tanner, W.P.; Alexander, S.N., (), (Chapter 19 Guidance)
[6] T. Yamasaki, K. Enomoto, H. Takano, Y. Baba, S.N. Balakrishnan, Advanced pure pursuit guidance via sliding mode approach for chase UAV, in: Proceedings of the AIAA Guidance, Navigation and Control Conference, Chicago, AIAA 2009-6298, 2009.
[7] N. Harl, S.N. Balakrishnan, Coordinated rendezvous of unmanned air vehicles to a formation: a sliding mode approach, in: Proceedings of the AIAA Guidance, Navigation and Control Conference, Honolulu, Hawaii, AIAA 2008-6318, 2008.
[8] D. Galzi, Y. Shtessel, UAV formations control using high order sliding modes, in: Proceedings of the 2006 American Control Conference, Minneapolis, 2006, pp. 4249-4254.
[9] Shima, T.; Idan, M.; Golan, O.M., Sliding mode control for integrated missile autopilot-guidance, AIAA journal of guidance, control and dynamics, 29, 2, 250-260, (2006)
[10] Shkolnikov, I.A.; Shtessel, Y.B., Aircraft nonminimum phase control in dynamic sliding manifolds, AIAA journal of guidance, control, and dynamics, 24, 3, 566-572, (2001)
[11] Levant, A., Quasi-continuous high-order sliding mode controllers, Transactions on aeronautical control, 50, 11, 1812-1816, (2005) · Zbl 1365.93072
[12] Shtessel, Y.; Shkolnikov, I.A.; Levant, A., Guidance and control of missile interceptor using second-order sliding modes, IEEE transactions on aerospace and electrical systems, 45, 1, 110-124, (2009)
[13] N. Harl, S.N. Balakrishnan, C. Phillips, Sliding modes integrated missile guidance and control, in: Proceedings of the AIAA Guidance, Navigation, and Control Conference, Toronto, AIAA 2010-7741, 2010.
[14] Harl, N.; Balakrishnan, S.N., Reentry terminal guidance through sliding mode control, AIAA journal of guidance, control, and dynamics, 33, 1, 186-189, (2010)
[15] Levant, A., Robust exact differentiation via sliding mode technique, Automatica, 34, 3, 379-384, (1998) · Zbl 0915.93013
[16] W.P. Gilbert, L.T. Nguyen, R.W. Van Gunst, Simulator Study of the Effectiveness of an Automatic Control System Designed to Improve the High-Angle-of-Attack Characteristics of a Fighter Airplane NASA TN D-8176, 1976.
This reference list is based on information provided by the publisher or from digital mathematics libraries. Its items are heuristically matched to zbMATH identifiers and may contain data conversion errors. It attempts to reflect the references listed in the original paper as accurately as possible without claiming the completeness or perfect precision of the matching.