Research Papers

A Guidance Law With Terminal Impact Angle Constraint Accounting for Missile Autopilot

[+] Author and Article Information
Di Zhou

Department of Control Science and Engineering,
Harbin Institute of Technology,
Mailbox 327,
Harbin 150001, China
e-mail: zhoud@hit.edu.cn

Pingping Qu

Department of Control Science and Engineering,
Harbin Institute of Technology,
Mailbox 327,
Harbin 150001, China;
The School of Electronics
and Information Engineering,
Shenyang Aerospace University,
Shenyang 110136, China

Sheng Sun

Department of Control Science and Engineering,
Harbin Institute of Technology,
Mailbox 327,
Harbin 150001, China

Contributed by the Dynamic Systems Division of ASME for publication in the Journal of Dynamic Systems, Measurement, and Control. Manuscript received May 18, 2012; final manuscript received March 29, 2013; published online June 6, 2013. Assoc. Editor: Yang Shi.

J. Dyn. Sys., Meas., Control 135(5), 051009 (Jun 06, 2013) (10 pages) Paper No: DS-12-1144; doi: 10.1115/1.4024202 History: Received May 18, 2012; Revised March 29, 2013

A sliding-mode guidance (SMG) law is designed to intercept maneuvering targets with impact angle constrained flight trajectories under the assumption of ideal missile autopilot. Furthermore, accounting for the autopilot as second-order dynamics, a new guidance law with terminal impact angle constraint is designed using the dynamic surface control method. Some first-order low-pass filters are introduced into the designing process to avoid the occurrence of high-order derivatives of the line of sight (LOS) angle in the expression of the guidance law such that the guidance law can be implemented in practical applications. The proposed guidance law is effective in compensating for the second-order autopilot lag. Simulation results show that it is able to guide a missile to impact a maneuvering target with a desired angle and a small miss distance.

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Ratnoo, A., and Ghose, D., 2008, “Impact Angle Constrained Interception of Stationary Targets,” J. Guid. Control Dyn., 31(6), pp. 1816–1821. [CrossRef]
Kim, M., and Grider, K. V., 1973, “Terminal Guidance for Impact Attitude Angle Constrained Flight Trajectories,” IEEE Trans. Aerosp. Electron. Syst., 9(6), pp. 852–859. [CrossRef]
Song, T. L., and Shin, S. J., 1999, “Time-Optimal Impact Angle Control for Vertical Plane Engagements,” IEEE Trans. Aerosp. Electron. Syst., 35(2), pp. 738–742. [CrossRef]
Manchester, I. R., and Savkin, A. V., 2004, “Circular Navigation Missile Guidance With Incomplete Information and Uncertain Autopilot Model,” J. Guid. Control Dyn., 27(6), pp. 1078–1083. [CrossRef]
Manchester, I. R., and Savkin, A. V., 2006, “Circular-Navigation-Guidance Law for Precision Missile/Target Engagements,” J. Guid. Control Dyn., 29(2), pp. 314–320. [CrossRef]
Jeon, I. S., Lee, J. I., and Tahk, M. J., 2006, “Impact-Time-Control Guidance Law for Anti-Ship Missiles,” IEEE Trans. Control Syst. Technol., 14(2), pp. 260–266. [CrossRef]
Lee, J. I., Jeon, I. S., and Tahk, M. J., 2007, “Guidance Law to Control Impact Time and Angle,” IEEE Trans. Aerosp. Electron. Syst., 43(1), pp. 301–310. [CrossRef]
Kim, B. S., Lee, J. G., and Han, H. S., 1998, “Biased PNC Law for Impact With Angular Constraint,” IEEE Trans. Aerosp. Electron. Syst., 34(1), pp. 277–288. [CrossRef]
Idan, M., Golan, O. M., and Guelman, M., 1995, “Optimal Planar Interception With Terminal Constraint,” J. Guid. Control Dyn., 18(6), pp. 1078–1083. [CrossRef]
Song, T. L., Shin, S. J., and Cho, H., 1999, “Impact Angle Control for Planar Engagements,” IEEE Trans. Aerosp. Electron. Syst., 35(4), pp. 1439–1444. [CrossRef]
Zhou, D., Mu, C. D., and Xu, W. L., 1999, “Adaptive Sliding-Mode Guidance of a Homing Missile,” J. Guid. Control Dyn., 22(4), pp. 589–594. [CrossRef]
Rusnak, I., and Meirt, L., 1990, “Modern Guidance Law for High-Order Autopilot,” J. Guid. Control Dyn., 14(5), pp. 1056–1058. [CrossRef]
Yoo, S. J., Park, J. B., and Choi, Y. H., 2006, “Adaptive Dynamic Surface Control of Flexible-Joint Robots Using Self-Recurrent Wavelet Neural Networks,” IEEE Trans. Syst., Man, Cybern., Part B: Cybern., 36(6), pp. 1342–1355. [CrossRef]
Xiong, G. L., Xie, Z. W., Huang, J. B., Liu, H., Jiang, Z.-N., and Sun, K., 2010, “Dynamic Surface Control-Backstepping Based Impedance Control for 5-DOF Flexible Joint Robots,” J. Cent. South Univ. Technol., 17(4), pp. 807–815. [CrossRef]
Hou, M. Z., and Duan, G. R., 2011, “Adaptive Dynamic Surface Control for Integrated Missile Guidance and Autopilot,” Int. J. Autom. Comput., 8(1), pp. 122–127. [CrossRef]
Swaroop, D., Hedrick, J. K., Yip, P. P., and Gerdes, J. C., 2000, “Dynamic Surface Control for a Class of Nonlinear Systems,” IEEE Trans. Autom. Control, 45(10), pp. 1893–1899. [CrossRef]
Swaroop, D., Gerdes, J. C., Yip, P. P., and Hedrick, J. K., 1997, “Dynamic Surface Control of Nonlinear Systems,” American Control Conference, Albuquerque, New Mexico, pp. 3028–3034.
Zhou, D., Sun, S., and Teo, K. L., 2009, “Guidance Laws With Finite Time Convergence,” J. Guid. Control Dyn., 32(6), pp. 1838–1846. [CrossRef]
Chwa, D. Y., and Choi, J. Y., 2003, “Adaptive Nonlinear Guidance Law Considering Control Loop Dynamics,” IEEE Trans. Aerosp. Electron. Syst., 39(4), pp. 1134–1143. [CrossRef]


Grahic Jump Location
Fig. 1

Planar relative motion of missile and target

Grahic Jump Location
Fig. 2

Simulation results in the elevation loop for case 1

Grahic Jump Location
Fig. 3

Simulation results in the elevation loop for case 2

Grahic Jump Location
Fig. 4

Simulation results for case 3 in the elevation loop

Grahic Jump Location
Fig. 5

Simulation results for case 3 in the azimuth loop




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