Trajectory Optimization for Powered Descent and Landing of Reusable Rockets with Restartable Engines
- Paper number
IAC-18,D2,IP,5,x44659
- Author
Dr. Lin Ma, China, Zhejiang University
- Coauthor
Dr. Kexin Wang, China, Zhejiang University
- Coauthor
Prof. Zuhua Xu, China, Zhejiang University
- Coauthor
Prof.Dr. Zhijiang SHAO, China, Zhejiang University
- Coauthor
Prof. Zhengyu Song, China, China Academy of Launch Vehicle Technology (CALT)
- Year
2018
- Abstract
Reusable rockets will begin a new era in spaceflight, and the scheme of vertical takeoff and landing has become a promising way to recover rockets. This study presents a direct trajectory optimization framework for powered descent and landing of reusable rockets with restartable engines. The rocket engine is throttleable, but the number of engine restart is limited. Given the engine characteristics, a unified problem formulation with a multi-phase structure is established. The simultaneous collocation is utilized to transcribe the established problem into a nonlinear programming problem solved by interior-point optimizer. An initialization strategy is designed in the proposed framework to generate a good guess of initial value for the trajectory optimization problem. Simulation results illustrate that the presented direct trajectory optimization framework exhibits unification and adaptability to effectively deal with trajectory optimization problems of reusable rockets with limitedly restartable engines.
- Abstract document
- Manuscript document
IAC-18,D2,IP,5,x44659.pdf (🔒 authorized access only).
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