Modern guidance systems are generally accepted to yield better performance than classical proporticmal navigation systems. However, it is not always recognized that this better performance carries with it certain costs in inproved components or additional instruments. This paper compares a modern guiasnce system, MGS, to a classical proportional navigationai, PIV , homing misslle guidance system in terms of perforuance, robustness, and ease of implementation. Q aan titative first order m i s s distances are compared to show that MGS has the smallest miss if component tolerances can be met, but as component tolerances or measurement errors degrade, M G S degrades faster than P N until, at relatively large component or measurement erl-ors, P N has less miss distance than MGS.
A b s t r a c t T h i s paper p r e s e n t s an a n a l y s i s of radome induced m i s s d i s t a n c e i n aerodynamically c o n t r o l l e d homing m i s s i l e s . The s t a b i l i t y of t h e m i s s i l e guiflance system is analyzed and c o r r e l a t e d with miss d i s t a n c e e f f e c t s . Nondimensionalized c u r v e s of miss d i s t a n c e v e r s u s t h e important parameters a r e p r e s e n t e d and used t o show p o s s i b l e t r a d e -o f f s between radome k s i g n and 3ero:lynamic d e s i g n . Such t r a d e -o f f s a r e important i n p r e l i m i n a r y d e s i g n t o i n s u r e proper balance between aerodynamic and radome design and t o i n s u r e t h a t t h e system w i l l dork over t h e range of parameter t o l e r a n c e s t h a t w i l l be encountered i n p r a c t i c e . I n t r o d u c t i o n A l l radar guided homing m i s s i l e s have radomes t h a t a r e 'designed t o p r o t e c t t h e ~i e e k e r antenna mechanically and t h e r m a l l y while p a s s i n g t h e radar energy r e q u i r e d t o develop guidance s i g n a l s . The radome l e n g t h is a compromise. The longer t h e r a d~m e , t h e l o s s aerodynamic ,drag on t h e m i s s i l e . The s h o r t e r t h e radome, t h e l e s s r e f r a c t i o n of t h e raclar wave a t the radome. Radorne r e f r a c t i m c r ea t e s a f a l s e l i n e of s i g h t r a t e when t h e m i s s i l e p i t c h e s , which m u s t be accounted f o r i n t h e m i s s i l e system d e s i g n because it changes t h e m i s s i l e ' s miss d i s t a n c e . I n t h i s paper t h e r a d m e induced m i s s d i s t a n c e e f f e c t i s analyzed by i n v e s t i g a t i n g t h e p o l e d i s t r i b u t i o n of t h e t r a n s f e r f u n c t i o n of t h e m i s s i l e and c o n s t r u c t i n g m i s s d i s t a n c e curves f o r a l l t h e major s o u r c e s of m i s s . The c u r v e s a r e nondimensionalized using t h r e e parameters, N ' , t h e VCR e f f e c t i v e n a v i g a t i o n r a t i o , -, t h e c l o s i n g vel-VM o c i t y t o m i s s i l e v e l o c i t y r a t i o times t h e radome r e f r a c t i o n s l o p e , and Q/TG, t h e m i s s i l e t u r n i n g r a t e time c o n s t a n t t o guidance system time c o n s t a n t r a t i o s . The nondimensionalized c u r v e s can be used t o p r e d i c t m i s s d i s t a n c e f o r a l l p r a c t i c a l ranges of t h e s e parameters. I t is shown t h a t radome e f f e c t s i n t e r a c t with aerodynamic e f f e c t s and t h e c a n b i n a t i o n p l a c e s a c o n s t r a i n t on t h e minimum a c h i e v a b l e guidance time c o n s t a n t . A r a d a r homing missile uses an antenna o r d i s h , mounted i n t h e m i s s i l e ' s nose, t o c o l l e c t t h e r e f l e c t e d e l e c t r o m a g n e t i c energy from t h e t a r g e t . ( l ) The d i s h i s p r o t e c t e d from t h e a i r f l o w by a radome. The f u n c t i o n of t h e radome is t o t r a n s m i t t h e incomin...
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