This paper studies the online trajectory planning method of the rocket vertical landing under the condition of high thrust-to-weight ratio (HTWR). This is common for most of the existing rockets which are configured with high-thrust engines but only few are installed. The HTWR leads to a substantial reduction in the physical feasible region of the optimal solution. Moreover, the traditional fuel optimal strategy has the characteristics of bang-bang control, which makes the rocket weak adaptability to disturbance or model deviation in the state of maximum or minimum thrust. Thus the online planning could be unsolvable or violate the feasible boundary. This paper first describes the equations of motion and constraints during the landing process, and then the influence of the HTWR is analyzed from the perspectives of physical feasible region and deviation adaptability. In this paper, an optimal objective function with larger feasible region is proposed, so that the online planning trajectory under the condition of HTWR can be far from the boundary of the feasible region. The nonlinearity of the problem is reduced by the method of compensation model, and a second-order cone programming problem with free terminal time suitable for the primal dual interior point method is constructed. The simulation results show that the landing trajectory planned by the proposed algorithm is adaptive to the model uncertainty and disturbances, and is more robust to achieving a safe landing with a HTWR.
Trajectory Planning for Landing Phase of Reusable Rocket with High Thrust-to-Weight Ratio
Lect. Notes Electrical Eng.
2021-10-30
13 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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