Finite-Time Spacecraft’s Soft Landing on Asteroids Using PD and Nonsingular Terminal Sliding Mode Control

Finite-Time Spacecraft’s Soft Landing on Asteroids Using PD and Nonsingular Terminal Sliding Mode Control

This paper presents a continuous control law of probe, which consists of PD (proportional-derivative) controller and nonsingular terminal sliding mode controller for probe descending and landing phases, respectively, in the case of the asteroid irregular shape and low gravity. The probe dynamic mode...

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Main Authors: Keping Liu, Fengxia Liu, Shenquan Wang, Yuanchun Li
Format: Article
Language:English
Published: Hindawi Limited 2015-01-01
Series:Mathematical Problems in Engineering
Online Access:http://dx.doi.org/10.1155/2015/510618
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spelling doaj-11ede34a7f0c4d3aa65a94bd3d2642572020-11-25T01:00:58ZengHindawi LimitedMathematical Problems in Engineering1024-123X1563-51472015-01-01201510.1155/2015/510618510618Finite-Time Spacecraft’s Soft Landing on Asteroids Using PD and Nonsingular Terminal Sliding Mode ControlKeping Liu0Fengxia Liu1Shenquan Wang2Yuanchun Li3College of Electrical and Electronic Engineering, Changchun University of Technology, Changchun 130000, ChinaCollege of Electrical and Electronic Engineering, Changchun University of Technology, Changchun 130000, ChinaCollege of Electrical and Electronic Engineering, Changchun University of Technology, Changchun 130000, ChinaCollege of Electrical and Electronic Engineering, Changchun University of Technology, Changchun 130000, ChinaThis paper presents a continuous control law of probe, which consists of PD (proportional-derivative) controller and nonsingular terminal sliding mode controller for probe descending and landing phases, respectively, in the case of the asteroid irregular shape and low gravity. The probe dynamic model is deduced in the landing site coordinate system firstly. Then the reference trajectory based on optimal polynomial in open-loop state is designed, with the suboptimal fuel consumption. Taking into account different characteristics of phases, PD controller and nonsingular terminal sliding mode controller can be employed in the descending phase and the landing phase, respectively, to track the designed reference trajectory. The controller which used the corresponding control methods can meet the motion characteristics and requirements of each stage. Finally simulation experiments are carried out to demonstrate the effectiveness of the proposed method, which can ensure the safe landing of probe and achieve continuous control.http://dx.doi.org/10.1155/2015/510618
collection DOAJ
language English
format Article
sources DOAJ
author Keping Liu
Fengxia Liu
Shenquan Wang
Yuanchun Li
spellingShingle Keping Liu
Fengxia Liu
Shenquan Wang
Yuanchun Li
Finite-Time Spacecraft’s Soft Landing on Asteroids Using PD and Nonsingular Terminal Sliding Mode Control
Mathematical Problems in Engineering
author_facet Keping Liu
Fengxia Liu
Shenquan Wang
Yuanchun Li
author_sort Keping Liu
title Finite-Time Spacecraft’s Soft Landing on Asteroids Using PD and Nonsingular Terminal Sliding Mode Control
title_short Finite-Time Spacecraft’s Soft Landing on Asteroids Using PD and Nonsingular Terminal Sliding Mode Control
title_full Finite-Time Spacecraft’s Soft Landing on Asteroids Using PD and Nonsingular Terminal Sliding Mode Control
title_fullStr Finite-Time Spacecraft’s Soft Landing on Asteroids Using PD and Nonsingular Terminal Sliding Mode Control
title_full_unstemmed Finite-Time Spacecraft’s Soft Landing on Asteroids Using PD and Nonsingular Terminal Sliding Mode Control
title_sort finite-time spacecraft’s soft landing on asteroids using pd and nonsingular terminal sliding mode control
publisher Hindawi Limited
series Mathematical Problems in Engineering
issn 1024-123X
1563-5147
publishDate 2015-01-01
description This paper presents a continuous control law of probe, which consists of PD (proportional-derivative) controller and nonsingular terminal sliding mode controller for probe descending and landing phases, respectively, in the case of the asteroid irregular shape and low gravity. The probe dynamic model is deduced in the landing site coordinate system firstly. Then the reference trajectory based on optimal polynomial in open-loop state is designed, with the suboptimal fuel consumption. Taking into account different characteristics of phases, PD controller and nonsingular terminal sliding mode controller can be employed in the descending phase and the landing phase, respectively, to track the designed reference trajectory. The controller which used the corresponding control methods can meet the motion characteristics and requirements of each stage. Finally simulation experiments are carried out to demonstrate the effectiveness of the proposed method, which can ensure the safe landing of probe and achieve continuous control.
url http://dx.doi.org/10.1155/2015/510618
work_keys_str_mv AT kepingliu finitetimespacecraftssoftlandingonasteroidsusingpdandnonsingularterminalslidingmodecontrol
AT fengxialiu finitetimespacecraftssoftlandingonasteroidsusingpdandnonsingularterminalslidingmodecontrol
AT shenquanwang finitetimespacecraftssoftlandingonasteroidsusingpdandnonsingularterminalslidingmodecontrol
AT yuanchunli finitetimespacecraftssoftlandingonasteroidsusingpdandnonsingularterminalslidingmodecontrol
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