Controlling lunar lander in powered descending phase

Xiaofei Chang; Weiwei Yu; Jie Yan

doi:10.1109/VPPC.2009.5289555

Controlling lunar lander in powered descending phase

Xiaofei Chang
, Weiwei Yu
, Jie Yan

School of Astronautics

Northwestern Polytechnical University Xian

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

Abstract

The requirement for controlling lunar lander in the powered descending phase is analyzed in the paper. With sub-optimal minimum fuel considered first, the expected non-iterative calculation formulas of the attitude angles are accquired. The explicit guidance project in relevance with the state variables and terminal restrict are deduced. According to deflection between the real attitude angles and the desired attitude angles, the attitude tracking system is designed by adopting the method of exponent reaching law and chattering reducing of boundary layers based on variable structure control with sliding mode. The simulation results show that the control system can complete flying mission in the powered descending phase, and has good robustness and adaptability as well.

Original language	English
Title of host publication	5th IEEE Vehicle Power and Propulsion Conference, VPPC '09
Pages	1506-1510
Number of pages	5
DOIs	https://doi.org/10.1109/VPPC.2009.5289555
State	Published - 2009
Event	5th IEEE Vehicle Power and Propulsion Conference, VPPC '09 - Dearborn, MI, United States Duration: 7 Sep 2009 → 10 Sep 2009

Publication series

Name	5th IEEE Vehicle Power and Propulsion Conference, VPPC '09

Conference

Conference	5th IEEE Vehicle Power and Propulsion Conference, VPPC '09
Country/Territory	United States
City	Dearborn, MI
Period	7/09/09 → 10/09/09

Keywords

Explicit guidance law
Lunar lander
Powered descension phase
Variable structure control

Access to Document

10.1109/VPPC.2009.5289555

Cite this

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title = "Controlling lunar lander in powered descending phase",

abstract = "The requirement for controlling lunar lander in the powered descending phase is analyzed in the paper. With sub-optimal minimum fuel considered first, the expected non-iterative calculation formulas of the attitude angles are accquired. The explicit guidance project in relevance with the state variables and terminal restrict are deduced. According to deflection between the real attitude angles and the desired attitude angles, the attitude tracking system is designed by adopting the method of exponent reaching law and chattering reducing of boundary layers based on variable structure control with sliding mode. The simulation results show that the control system can complete flying mission in the powered descending phase, and has good robustness and adaptability as well.",

keywords = "Explicit guidance law, Lunar lander, Powered descension phase, Variable structure control",

author = "Xiaofei Chang and Weiwei Yu and Jie Yan",

year = "2009",

doi = "10.1109/VPPC.2009.5289555",

language = "英语",

isbn = "9781424426003",

series = "5th IEEE Vehicle Power and Propulsion Conference, VPPC '09",

pages = "1506--1510",

booktitle = "5th IEEE Vehicle Power and Propulsion Conference, VPPC '09",

note = "5th IEEE Vehicle Power and Propulsion Conference, VPPC '09 ; Conference date: 07-09-2009 Through 10-09-2009",

}

Chang, X, Yu, W & Yan, J 2009, Controlling lunar lander in powered descending phase. in 5th IEEE Vehicle Power and Propulsion Conference, VPPC '09., 5289555, 5th IEEE Vehicle Power and Propulsion Conference, VPPC '09, pp. 1506-1510, 5th IEEE Vehicle Power and Propulsion Conference, VPPC '09, Dearborn, MI, United States, 7/09/09. https://doi.org/10.1109/VPPC.2009.5289555

TY - GEN

T1 - Controlling lunar lander in powered descending phase

AU - Chang, Xiaofei

AU - Yu, Weiwei

AU - Yan, Jie

PY - 2009

Y1 - 2009

N2 - The requirement for controlling lunar lander in the powered descending phase is analyzed in the paper. With sub-optimal minimum fuel considered first, the expected non-iterative calculation formulas of the attitude angles are accquired. The explicit guidance project in relevance with the state variables and terminal restrict are deduced. According to deflection between the real attitude angles and the desired attitude angles, the attitude tracking system is designed by adopting the method of exponent reaching law and chattering reducing of boundary layers based on variable structure control with sliding mode. The simulation results show that the control system can complete flying mission in the powered descending phase, and has good robustness and adaptability as well.

AB - The requirement for controlling lunar lander in the powered descending phase is analyzed in the paper. With sub-optimal minimum fuel considered first, the expected non-iterative calculation formulas of the attitude angles are accquired. The explicit guidance project in relevance with the state variables and terminal restrict are deduced. According to deflection between the real attitude angles and the desired attitude angles, the attitude tracking system is designed by adopting the method of exponent reaching law and chattering reducing of boundary layers based on variable structure control with sliding mode. The simulation results show that the control system can complete flying mission in the powered descending phase, and has good robustness and adaptability as well.

KW - Explicit guidance law

KW - Lunar lander

KW - Powered descension phase

KW - Variable structure control

UR - https://www.scopus.com/pages/publications/72149104329

U2 - 10.1109/VPPC.2009.5289555

DO - 10.1109/VPPC.2009.5289555

M3 - 会议稿件

AN - SCOPUS:72149104329

SN - 9781424426003

T3 - 5th IEEE Vehicle Power and Propulsion Conference, VPPC '09

SP - 1506

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BT - 5th IEEE Vehicle Power and Propulsion Conference, VPPC '09

T2 - 5th IEEE Vehicle Power and Propulsion Conference, VPPC '09

Y2 - 7 September 2009 through 10 September 2009

ER -

Controlling lunar lander in powered descending phase

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