New parametric affine modeling and control for skid-to-turn missiles

This paper presents a new practical autopilot design approach to acceleration control for tail-controlled STT (skid-to-turn) missiles. The approach is novel in that the proposed parametric affine missile model adopts acceleration as the controlled output and considers the couplings between the forces as well as the moments and control fin deflections. The aerodynamic coefficients in the proposed model are expressed in a closed form with fittable parameters over the whole operating range. The parameters are fitted from aerodynamic coefficient look-up tables by the function approximation technique, which is based on the combination of local parametric models through curve fitting using the corresponding influence functions. In this paper, in order to employ the results of parametric affine modeling in the autopilot controller design, we derived a parametric affine missile model and designed a feedback linearizing controller for the obtained model. Stability analysis for the overall closed loop system is provided, considering the uncertainties arising from approximation errors. The validity of the proposed modeling and control approach is demonstrated through simulations for an STT missile.

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

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

[3]  Dongkyoung Chwa,et al.  New parametric affine modeling and control for skid-to-turn missiles , 2001, IEEE Trans. Control. Syst. Technol..

[4]  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).

[5]  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.

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

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

[8]  Sahjendra N. Singh,et al.  I-O map inversion, zero dynamics and flight control , 1990 .

[9]  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.

[10]  J. Munkres,et al.  Calculus on Manifolds , 1965 .

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

[12]  Arjan van der Schaft,et al.  Non-linear dynamical control systems , 1990 .

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

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

[15]  V. Cheng,et al.  Practical design methodologies for robust nonlinear flight control , 1996 .

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

[17]  Michael J Hemsch,et al.  Tactical Missile Aerodynamics , 1986 .