Change of Satellite Orbit Plane by Aerodynamic Maneuvering

M a n e u v e r s in which t h e o rb i t a l p l a n e of a n e a r t h sa te l l i te is changed b y m e a n s of a e r o d y n a m i c forces d u r i n g one or m o r e skips i n to a n d o u t of t h e a t m o s p h e r e a r e ana lyzed . T h e cha r ac te r i s t ic veloci t ies r equ i r ed of r o c k e t s t o deflect t h e vehic le i n to t h e a t m o s p h e r e in i t ia l ly a n d t o reacce le ra te i t t o o rb i t a l speed af ter l eav ing t h e a t m o s p h e r e a r e ca lcu la ted as func t ions of t h e change in inc l ina t ion , t h e l i f t -drag r a t io , a n d t h e e n t r y angle , a n d a r e c o m p a r e d w i t h t h e c h a r a c t e r i s t i c veloci t ies r equ i red for p u r e l y e x t r a a t m o s p h e r i c rocke t m a n e u v e r s . I n add i t i on , a e r o d y n a m i c h e a t i n g , acce le ra t ions , a n d t i m e t o c a r t y ou t t h e m a n e u v e r s a r e e s t i m a t e d .