Optimal Control and Output Feedback Considerations for Missile with Blended Aero-fin and Lateral Impulsive Thrust

For the missile with blended aero-fin and lateral impulsive thrust, a blended control autopilot is designed, which comprises an optimal controller and a control allocation module. The combined optimal/classical approach is applied to designing the optimal controller to determine the virtual controls, and the control allocation module is used to distribute the desired virtual controls onto the redundant control effectors. The autopilot holds some attractive characteristics, such as simple structure, good tracking performance and robustness; moreover the actual constraints of the control effectors can be taken into account. Based on this blended control autopilot, it is found that the conflict between stability and fast tracking performance is serious when using the total acceleration as feedback. In order to avoid this problem, the transient factors in total acceleration are eliminated, so the acceleration caused only by angle of attack is used as feedback, and obvious improvement is shown. Finally, how to get reasonable acceleration feedback is discussed, and conclusion is presented that after passing the low-pass filter, the total acceleration can also be used as feedback, and satisfied tracking performance can be obtained.

[1]  Kevin Wise,et al.  Robust Stability Analysis of Adaptive Missile Autopilots , 2008 .

[2]  Shunji Manabe,et al.  Autopilot Design for a Missile with Reaction-Jet Using Coefficient Diagram Method , 2001 .

[3]  Todd Fanciullo,et al.  Dual Aero/Propulsive Missile Control - Optimal Control and Control Allocation , 2006 .

[4]  Yuri B. Shtessel,et al.  Guidance and Autopilot for Missiles Steered by Aerodynamic Lift and Divert Thrusters Using Second Order Sliding Mode Control , 2006 .

[5]  D. Ridgely,et al.  Missile Longitudinal Autopilots: Connections Between Optimal Control and Classical Topologies , 2005 .

[6]  Mario Innocenti,et al.  Simultaneous reaction jet and aerodynamic control of missile systems , 1993 .

[7]  Yuri B. Shtessel,et al.  Autopilot for Missiles Steered by Aerodynamic Lift and Divert Thrusters using Nonlinear Dynamic Sliding Manifolds , 2005 .

[8]  Curtis Mracek,et al.  Optimal Control Solution for Dual (Tail and Canard) Controlled Missiles , 2006 .

[9]  Yin Xing-liang.  Design Three-loop Autopilot for BTT Missile Using Combined Optimal/Classical Approach , 2008 .

[10]  T. Johansen,et al.  Efficient Optimal Constrained Control Allocation via Multiparametric Programming , 2005 .

[11]  William R. Chadwick.  Augmentation of High-Altitude Maneuver Performance of a Tail-Controlled Missile Using Lateral Thrust, , 1995 .

[12]  Yin Xing-liang.  Dynamic Analysis and Control Design for a Spinning Missile with Impulsive Attitude Control Motors , 2008 .

[13]  Kai Liu,et al.  An appropriate application of fuzzy logic: a missile autopilot for dual control implementation , 1994, Proceedings of 1994 9th IEEE International Symposium on Intelligent Control.

[14]  Li Xin,et al.  Design of autopilot for Aerodynamic/Reaction-jet Multiple control missile using variable structure control , 2008, 2008 27th Chinese Control Conference.

[15]  Yin Xing-liang.  Modeling and control of a spinning missile with blended aero-fin and lateral impulsive thrust , 2005 .