When an aerodynamically controlled missile is used in a homing application, the transfer function of the vehicle becomes part of an overall homing an attitude control feedback loop. Therefore, the missile must be designed so that its aerodynamics meet the constraints required to accomplish homing successfully. For radar homing, these constaints are stringent enough to require an autopilot that controls the aerodynamic transfer function using body instruments and internal fedback loops. Even with an autopilot, there are limits on the aerodynamic moment parameters such as M alpha und M that must be considered at the very beginning of the missile system design. This paper explores the nature and sources of these limits and presents numerical examples to illustrate what kinds of numbers are required.
How autopilot requirements constrain the aerodynamic design of homing missiles
Der Einfluss der Autopilot-Anforderungen auf die aerodynamische Entwicklung von gelenkten Flugkoerpern
Proc. of the 1984 American Control Conf. ; 2 ; 716-730
1984
15 Seiten, 23 Bilder, 1 Tabelle, 8 Quellen
Aufsatz (Konferenz)
Englisch
Autopilot design for modern missiles
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