Optimal Control Strategy at the Main Reduction Process for Lunar Spacecraft Soft Landing

Xue Yuan Zhang

doi:10.4028/www.scientific.net/AMM.775.334

Paper Titles

Effect of Correcting the Electro-Hydraulic Servo Drive on the Stability and Controllability of an Airplane
p.314

Study on Iterative Learning Control of Mobile Robot
p.319

Analytical Study of Piezoelectric Effect on Curvature and Mechanical Sensitivity in Large Deflection of Pre-Stressed Layered Plate Including a Piezoelectric Layer
p.324

Catastrophic Results for Equipment and Machine Driving Systems when High Impact during Operation Occurs
p.329

Optimal Control Strategy at the Main Reduction Process for Lunar Spacecraft Soft Landing
p.334

New Results on PID Stabilization of Integral Process with Time Delay
p.339

Multi-Objective Optimization of Nonlinear Controller for Untripped Rollover Prevention of an 8-dof Vehicle Dynamic Model
p.347

A Gear Micropump without Bearings Production
p.352

Design and Research of a Novel Fast Connecting and Separating Modular Space Manipulator
p.357

HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 775Optimal Control Strategy at the Main Reduction...

Optimal Control Strategy at the Main Reduction Process for Lunar Spacecraft Soft Landing

Abstract:

According to the law of energy conservation and the second law of Kepler, this paper obtains the spacecraft velocity in perilune and apolune. Based on trajectory inversion thought, this paper obtains position and velocity direction in the perilune and apolune. For the five sub stages of soft landing, this paper discusses the optimal control strategy: establishing optimization model of genetic algorithm for the main deceleration section, the terminal constraint condition is reflected on the fitness function through the penalty function, combined with linear iterative thought, the winner engine thrust and direction angle are obtained. Aiming at the rapid adjustment period, the spacecraft angle change is done equivalent decomposition and discrete linear, so the thrust can be obtained through the angle change provided by adjusting attitude engine and combined with rigid body motion law.

You might also be interested in these eBooks

Engineering Solutions for Industrial Production

View Preview

Info:

Periodical:

Applied Mechanics and Materials (Volume 775)

Pages:

334-338

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.775.334

Citation:

Cite this paper

Online since:

July 2015

Authors:

Xue Yuan Zhang*

Keywords:

Genetic Algorithm, Iteration Method, Penalty Function Threshold

Export:

RIS, BibTeX

Price:

Permissions CCC:

Request Permissions

Permissions PLS:

Request Permissions

Сopyright:

Citation:

* - Corresponding Author

References

[1] J.F. Zhu, S.J. Xu. Lunar soft landing trajectory optimization based on adaptive simulated annealing genetic algorithm. Journal of aviation, 2012, 28(4): 56-59.

Google Scholar

[2] S.K. Si, X.J. Sun. Genetic algorithms. Beijing: National Defense Industry Press, 2011: 305-307.

Google Scholar

[3] G. Chen, Z.M. Wan, M. Xu. Research on parameter and constraint handling method of aircraft trajectory optimization using genetic algorithm. Journal of system simulation, 2012, 17(11): 23-26.

Google Scholar

[4] Timothy J. Cole, Julie Bassler, Scott Cooper, Vince Stephens. The challenges of designing a lightweight spacecraft structure for landing on the lunar surface. Acta Astronautica, 2012, 71(1): 83-91.

DOI: 10.1016/j.actaastro.2011.08.003

Google Scholar

[5] Xiaohui Wei, Qing Lin, Hong Nie, Ming Zhang. Investigation on soft-landing dynamics of four-legged lunar lander. Acta Astronautica, 2014, 101(8): 55-66.

DOI: 10.1016/j.actaastro.2014.04.001

Google Scholar

[6] Yuriy Shkuratov, Vadym Kaydash, Xenija Sysolyatina. Lunar surface traces of engine jets of Soviet sample return probes: The enigma of the Luna-23 and Luna-24 landing sites. Planetary and Space Science, 2013, 75(1): 28-36.

DOI: 10.1016/j.pss.2012.10.016

Google Scholar

[7] J.B. Chen, H. Nie. Overloading of Landing Based on the Deformation of the Lunar Lander. Chinese Journal of Aeronautics, 2012, 21(1): 43-47.

DOI: 10.1016/s1000-9361(08)60006-0

Google Scholar

[8] F. Zhang, G.R. Duan. Integrated translational and rotational control for the terminal landing phase of a lunar module. Aerospace Science and Technology, 2013, 27(1): 112-126.

DOI: 10.1016/j.ast.2012.07.003

Google Scholar

[9] Lars Witte. Duan. Stochastic modeling of a hazard detection and avoidance maneuver-The planetary landing case. Reliability Engineering & System Safety, 2013, 119(12): 259-269.

DOI: 10.1016/j.ress.2013.06.033

Google Scholar