Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1990-02-16
1991-11-12
Hellner, Mark
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
364462, 364435, G05D 108
Patent
active
050641417
ABSTRACT:
A guidance system for a homing missile having an observer filter which utilizes signals representative of range, range rate, acceleration normal to the line-of-sight of the missile, acceleration along the line-of-sight of the missile, and line-of-sight rate of the missile to a target is described. The filter includes means, responsive to a lateral acceleration signal, a measured range rate signal and a range signal for providing an estimated line-of-sight rate signal. The measured line-of-sight rate signal and the estimated line-of-sight rate signal are used to produce a difference output signal. The difference output signal is used to produce an error signal which is applied to the providing means to minimize the difference output signal. The estimated line-of-sight rate signal provides a more accurate estimate of the actual line-of-sight rate of the missile to the target than that which can be obtained with a standard proportional navigation system.
REFERENCES:
patent: 4037202 (1977-07-01), Terzian
patent: 4529151 (1985-07-01), Skarman
patent: 4783744 (1988-11-01), Yueh
patent: 4791573 (1988-12-01), Zemany et al.
Thomas Kailath, Linear Systems, "Asymptotic Observers and Compensator Design," 1980, by Prentice-Hall, Inc., Chapter 4, pp. 259-313.
David G. Luenberger, "An Introduction to Observers," IEEE Transactions on Automatic Control, vol. AC-16, No. 6, Dec. 1971, pp. 596-602.
Hellner Mark
Mofford Donald F.
Raytheon Company
Sharkansky Richard M.
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