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Direct collocation method has been widely used for trajectory optimization. In this paper, the application of direct
optimization method (direct collocation method & nonlinear programming (NLP)) to lunar probe soft-landing trajectory
optimization is introduced. Firstly, the model of trajectory optimization control problem to lunar probe soft landing
trajectory is established and the equations of motion are simplified respectively based on some reasonable hypotheses.
Performance is selected to minimize the fuel consumption. The control variables are thrust attack angle and thrust of
engine. Terminal state variable constraints are velocity and altitude constraints. Then, the optimal control problem is
transformed into nonlinear programming problem using direct collocation method. The state variables and control
variables are selected as optimal parameters at all nodes and collocation nodes. Parameter optimization problem is solved
using the SNOPT software package. The simulation results demonstrate that the direct collocation method is not
sensitive to lunar soft landing initial conditions; they also show that the optimal solutions of trajectory optimization
problem are fairly good in real-time. Therefore, the direct collocation method is a viable approach to lunar probe soft
landing trajectory optimization problem.
Lianghui Tu,Jianping Yuan,Jianjun Luo,Xin Ning, andRuiwu Zhou
"Lunar soft landing rapid trajectory optimization using direct
collocation method and nonlinear programming", Proc. SPIE 6795, Second International Conference on Space Information Technology, 67954T (10 November 2007); https://doi.org/10.1117/12.774978
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Lianghui Tu, Jianping Yuan, Jianjun Luo, Xin Ning, Ruiwu Zhou, "Lunar soft landing rapid trajectory optimization using direct collocation method and nonlinear programming," Proc. SPIE 6795, Second International Conference on Space Information Technology, 67954T (10 November 2007); https://doi.org/10.1117/12.774978