Adaptive control for feedback-linearized missiles with uncertainties

A robust adaptive control scheme is proposed that can be applied to a practical autopilot design for feedback-linearized skid-to-turn (STT) missiles with aerodynamic uncertainties. The approach is to add a robust adaptive controller to a feedback-linearizing controller in order to reduce the influence of the aerodynamic uncertainties. The proposed robust adaptive control scheme is based on a sliding mode control technique with an adaptive law for estimating the unknown upper bounds of uncertain parameters. A feature of the proposed scheme is that missile systems with aerodynamic uncertainties can be controlled effectively over a wide operating range of flight conditions. It is shown, using Lyapunov stability theory, that the proposed scheme can give sufficient tracking capability and stability for a feedback-linearized STT missile with aerodynamic uncertainties. The six-degree-of-freedom nonlinear simulation results also show that good performance for several uncertainty models and engagement scenarios can be achieved by the proposed scheme in practical night conditions.

[1]  R. Walker,et al.  Nonlinear flight test trajectory controllers for aircraft , 1987 .

[2]  Sahjendra N. Singh,et al.  Adaptive Control of Feedback Linearizable Nonlinear Systems With Application to Flight Control , 1996 .

[3]  Jae-Hyuk Oh,et al.  A new approach to autopilot design for highly nonlinear missiles , 1996 .

[4]  S. A. Snell.  Preliminary assessment of the robustness of dynamic inversion based flight control laws , 1992 .

[5]  Jae-Hyuk Oh,et al.  Missile autopilot design via functional inversion and time-scaled transformation , 1997 .

[6]  J. Huang,et al.  Sliding Mode Control of HAVE DASH II Missile Systems , 1993, 1993 American Control Conference.

[7]  Weiping Li,et al.  Applied Nonlinear Control , 1991 .

[8]  William L. Garrard,et al.  Nonlinear inversion flight control for a supermaneuverable aircraft , 1992 .

[9]  Ching-Fang Lin,et al.  Advanced Control Systems Design , 1993 .

[10]  S. Shankar Sastry,et al.  Nonlinear control design for slightly non-minimum phase systems: Application to V/STOL aircraft , 1992, Autom..

[11]  Min-Jea Tahk,et al.  Applications of plant inversion via state feedback to missile autopilot design , 1988, Proceedings of the 27th IEEE Conference on Decision and Control.

[12]  John H. Blakelock,et al.  Automatic control of aircraft and missiles , 1965 .

[13]  Zhihua Qu,et al.  Dynamic robust recursive control design and its application to a nonlinear missile autopilot , 1997, Proceedings of the 1997 American Control Conference (Cat. No.97CH36041).

[14]  Zhihua Qu,et al.  Design and evaluation of robust nonlinear missile autopilots from a performance perspective , 1995, Proceedings of 1995 American Control Conference - ACC'95.

[15]  Li-Chen Fu,et al.  Nonlinear autopilot and guidance for a highly maneuverable missile , 1994, Proceedings of 1994 American Control Conference - ACC '94.

[16]  Alberto Isidori,et al.  Nonlinear control systems: an introduction (2nd ed.) , 1989 .

[17]  Gary J. Balas,et al.  Flight control design using robust dynamic inversion and time-scale separation , 1996, Autom..

[18]  J.R. Cloutier,et al.  Robust feedback linearization approach to autopilot design , 1992, [Proceedings 1992] The First IEEE Conference on Control Applications.

[19]  Robert F. Stengel,et al.  Flight Control Design using Nonlinear Inverse Dynamics , 1986, 1986 American Control Conference.

[20]  S. A. Snell,et al.  Robust control of angle of attack using dynamic inversion combined with quantitative feedback theory , 1996 .

[21]  Ching-Fang Lin,et al.  Modern Navigation, Guidance, And Control Processing , 1991 .

[22]  Mikhail Goman,et al.  ROBUST NONLINEAR DYNAMIC INVERSION METHOD FOR AN AIRCRAFT MOTION CONTROL , 1998 .