Research on Attitude Law of Mass Moment Missile Based on Mulriple Control

Peng Wu; Qi Chao Chen; Jiao Ding Ning

doi:10.4028/www.scientific.net/AMR.181-182.919

Paper Titles

Study on a Sewage Heat Exchanger with On-Line Hydraulic Removing Fouling Technology
p.896

A Subblock Matrix Approach to Data-Reduction in Gait Recognition
p.902

Research on a Removing Fouling Technology for the Sewage Heat Exchanger
p.908

Acoustic Reconstructing Method in Prolate Spheroidal Coordinate System
p.914

Research on Attitude Law of Mass Moment Missile Based on Mulriple Control
p.919

Condition Number of Acoustic Infinite Element
p.926

Matrix Assembly Method for Insulating Glass Sound Transmission
p.932

A Modified Particle Swarm Optimization Algorithm Based on Proportional Distribution of Particles
p.937

Algorithm Research and System Development on Free-Form Surface CNC Processing Parameters Automatically Determination/Equipment Selection/Process Management
p.943

HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 181-182Research on Attitude Law of Mass Moment Missile...

Research on Attitude Law of Mass Moment Missile Based on Mulriple Control

Abstract:

Aimed at characteristics of mass moment of missiles in exo-atmosphere, it’s inferred that 6-DOF mathematical model based on mass moment controlling stabilities on three axes. Considering the problem of harmoniously controlling two moving masses, moving mass based non-linear theorem was used to solve a series of problems met in attitude control system design. In order to weaken the chattering of the system, a saturation function is introduced to substitute for Sign function to improve the variable structure control law so that the chattering can be depressed. The simulation results illustrate the efficiency of this method.

You might also be interested in these eBooks

Advanced Materials Science and Technology, ICMST 2010

View Preview

Info:

Periodical:

Advanced Materials Research (Volumes 181-182)

Pages:

919-925

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.181-182.919

Citation:

Cite this paper

Online since:

January 2011

Authors:

Peng Wu, Qi Chao Chen, Jiao Ding Ning

Keywords:

Attitude Control, Mass Moment Missile, Variable Structure Control (VSC)

Export:

RIS, BibTeX

Price:

Permissions CCC:

Request Permissions

Permissions PLS:

Request Permissions

Сopyright:

Citation:

References

[1] P. K Menon. Integrated guidance and control moving mass actuated kinetic energy kill vehicles, OPTIMAL SYNTHESIS INC, (LOSALTOS, CA). (2001).

Google Scholar

[2] Raymond H B, Rush D R, Moving mass trim control system design, AIAA-96-3826-CP. (1996).

Google Scholar

[3] C R. D. Robinet, B. Rainwater, Moving mass trim control for aerospace vehicles, Journal of Guidance, Control and Dynamics, 1996, 19(5): 1064-1079.

Google Scholar

[4] HE You-zhi, ZHANG Xiao-yu, Design of three moving mass missile system based on the fuzzy variable structure control, Systems Engineering and Electronics, 2005, 27(2): 292-334.

Google Scholar

[5] GUO Qing, YANG Ming, WANG Zi-cai, Combined control of miss moment interceptors in terminal guidance phase, Journal of Nanjing University of Science and Technology (Natural Science), 2008, 32(3): 337-341.

Google Scholar

[6] LIAO Guo-bin, YU Ben-shui, YANG Yu-guang, Study on the theory and simplified equations of mass moment control missile, Systems Engineering and Electronics, 2004, 26(11): 1635-1639.

Google Scholar

[7] HU Zheng-dong, LI Jian, CAI Hong, Research on Reentry Simulation of Moving-Mass Actuated Kinetic Warheads, FLIGHT DYNAMICS, 2007, 25(2): 57-60.

Google Scholar

[8] Jin Wen tao, Wei Ming ying. Study on the Design Methods of the Interceptor's Attitude Control System Based on Fuzzy Control, Systems Engineering and Electronics, 2005, 27(4): 696-699.

Google Scholar