Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1993-08-27
1995-07-25
Lobo, Ian J.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
36442401, F41G 700, F42B 1501
Patent
active
054355036
ABSTRACT:
A weak Hamiltonian finite element method is used for iterative computation of missile guidance acceleration commands for maximizing a missile's terminal velocity while satisfying control authority limits and terminal attitude constraints. The guidance acceleration commands include commands for controlling the angle of attack (.alpha.) and the bank angle (.phi.) of the missile. The angle of attack (.alpha.) and bank angle (.phi.) are related to a set of virtual control variables selected to avoid convergence problems when the angle of attack is approximately zero. The preferred control variables are .beta..sub.2 and .beta..sub.3 such that .beta..sub.2 =cos.phi.tan.alpha. and .beta..sub.3 =sin.phi.tan.alpha.. Iterative convergence is facilitated when control inequality constraint parameters are reached by adjusting iterative solutions between iterations toward satisfaction of the constraints. An approximation to an optimal trajectory is calculated at each guidance cycle during missile flight using data which are revised during each guidance cycle. The revised data include current position data for the target and the current position for the missile. The revised data are taken from the most reliable source currently available, such as on-board target-seeking radar when the target-seeking radar is locked onto the target, uplink data from ground or airborne tracking radar when an uplink is operational, or inertial guidance data. Extracted from the optimal trajectory is an optimal acceleration command for optimally controlling the angle of attack and bank angle of the missile.
REFERENCES:
patent: 5253823 (1993-10-01), Lawrence
patent: 5259569 (1993-11-01), Waymeyer et al.
Hodges et al., "Weak Hamiltonian Finite Element Method for Optimal Control Problems," Journal of Guidance Control, and Dynamics, vol. 14, No. 1, Jan.-Feb. 1991, American Institute Aeronautics and Astronautics, pp. 148-156.
Bless et al., "Finite Element Solution of Optimal Control Problems with Inequality Constraints," Proceedings of the 1990 American Control Conference, San Diego, California, May 23-25, 1990, vol. 1, American Automatic Control Conference, pp. 242-247.
CRC Handbook of Mathematical Tables, 1980, Chemical Rubber Company Press Inc., Boca Raton, Florida, pp. 43-44.
McGraw-Hill Encyclopedia of Science & Technology, vol. 8, 1992, McGraw-Hill, Inc., New York, N.Y., pp. 307-310.
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Robert R. Bless, "Time-Domain Finite Elements in Optimal Control With Application to Launch-Vehicle Guidance," NASA Contract Report 4376, National Aeronautics and Space Administration, 1991.
Haskins Glenn T.
Hodges Dewey H.
Johnson, Jr. Malvin G.
Lobo Ian J.
Loral Vought Systems Corp.
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