Digital signal processing capability can be added to a missile homing guidance system to provide a broad system decision capability against a complex threat. This processing may be on the ground or in the missile. Wherever it occurs, it introduces additional dynamics into the guidance loop which can degrade system performance. In fact, the influence of digitization is so important that it must be included at the outset in order to ensure that a guidance system design will work. One of the most significant effects is the introduction of a sample and hold in the guidance attitude loop. This paper discusses the influence of digital processing on system relative stability and performance. A variety of techniques for improving system performance are introduced and tradeoff curves are presented indicating how major subsystem parameters, such as seeker stabilization loop gain or autopilot time constant, may be specified. The results show the tradeoffs between a robust set of guidance subsystem specifications and acceptable performance when digital guidance is used.
[1]
H. W. Bode,et al.
Network analysis and feedback amplifier design
,
1945
.
[2]
Paul Zarchan,et al.
Hardware-software trade-offs for digital flight control of guided missiles
,
1982
.
[3]
F. William Nesline.
Missile Guidance for Low-Altitude Air Defense
,
1979
.
[4]
H. Nyquist,et al.
The Regeneration Theory
,
1954,
Journal of Fluids Engineering.
[5]
L.I. Slafer,et al.
Sampled-Data Control System Analysis Using the Poisson Summation Rule
,
1974,
IEEE Transactions on Aerospace and Electronic Systems.
[6]
Paul Zarchan,et al.
A New Look at Classical vs Modern Homing Missile Guidance
,
1981
.
[7]
F. Nesline,et al.
Missile guidance design tradeoffs for high-altitude air defense
,
1983
.
[8]
G.M. Siouris,et al.
Guided weapon control systems
,
1983,
Proceedings of the IEEE.