![](/assets/images/picto-drapeau-france-3a76576a5d60a512053b4612ab58dae5.png)
3. Conclusion
This article presents the two main problems involved in positioning an electrically propelled satellite, and the methods used to solve them.
For the positioning of satellites in high orbit, the objective is to ascend the perigee and apogee while minimizing the transfer time. The optimal control problem can be reduced to an unconstrained minimization with four angular variables taking values close to zero. The use of a gradient-free algorithm avoids the usual numerical difficulties (sensitivity to initial adjoint, integration accuracy). This method enables rapid resolution for all transfer configurations (initial orbit, illumination), taking eclipse transits into account.
When positioning satellites in low-Earth orbit, the aim is to change the orbital plane while minimizing power consumption. The optimum solution is to use a drift orbit to...
Exclusive to subscribers. 97% yet to be discovered!
You do not have access to this resource.
Click here to request your free trial access!
Already subscribed? Log in!
![](/assets/images/logo-eti-286623ed91fa802ce039246e516e5852.png)
The Ultimate Scientific and Technical Reference
This article is included in
Systèmes aéronautiques et spatiaux
This offer includes:
Knowledge Base
Updated and enriched with articles validated by our scientific committees
Services
A set of exclusive tools to complement the resources
Practical Path
Operational and didactic, to guarantee the acquisition of transversal skills
Doc & Quiz
Interactive articles with quizzes, for constructive reading
Conclusion
Bibliography
Exclusive to subscribers. 97% yet to be discovered!
You do not have access to this resource.
Click here to request your free trial access!
Already subscribed? Log in!
![](/assets/images/logo-eti-286623ed91fa802ce039246e516e5852.png)
The Ultimate Scientific and Technical Reference