DocumentCode :
2636960
Title :
Optimization design and analysis of spacecraft formations on elliptic orbits
Author :
An, Xueying ; Yang, Leping ; Xi, Xiaoning
Author_Institution :
Coll. of Aerosp. & Mater. Eng., Nat. Univ. of Defense Technol., Changsha
fYear :
2008
fDate :
10-12 Dec. 2008
Firstpage :
1
Lastpage :
5
Abstract :
The differential J2 influence is a big challenge to design periodic relative motion between two spacecrafts on neighboring eccentric orbits. A linearized time-variant equation is presented to describe the formation dynamics in the presence of J2 disturbances. For five kinds of basic formation configurations, numerical simulations show that the spacecrafts will not separate over time, when the initial inclination, initial argument of perigee and initial mean anomaly of the reference orbit are set to be special values. Some simple results can be demonstrated with the theory of mean orbit elements, but iteration need to be used for the others. Therefore, an optimization design involving the above osculating orbital elements is proposed to reduce relative orbit drifts due to J2 effects. The results indicate that, the optimal formation can avoid considerable in-plane relative motion drifts and provide substantial fuel savings for formation maintenance.
Keywords :
aerospace control; iterative methods; optimisation; position control; space vehicles; J2 disturbances; elliptic orbits; formation dynamics; fuel savings; iteration; linearized time-variant equation; neighboring eccentric orbits; numerical simulations; optimization design; periodic relative motion; relative orbit drifts; spacecraft formations; Aerodynamics; Aerospace engineering; Aerospace materials; Aircraft manufacture; Design optimization; Equations; Motion analysis; Orbits; Space technology; Space vehicles;
fLanguage :
English
Publisher :
ieee
Conference_Titel :
Systems and Control in Aerospace and Astronautics, 2008. ISSCAA 2008. 2nd International Symposium on
Conference_Location :
Shenzhen
Print_ISBN :
978-1-4244-3908-9
Electronic_ISBN :
978-1-4244-2386-6
Type :
conf
DOI :
10.1109/ISSCAA.2008.4776223
Filename :
4776223
Link To Document :
بازگشت