Research of De-Couple Control System for near Space Vehicle with High Maneuver and Couple

Shao Bo Ni; Wei Jun Hu; Song Xiong

doi:10.4028/www.scientific.net/AMM.128-129.979

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 128-129Research of De-Couple Control System for near...

Research of De-Couple Control System for near Space Vehicle with High Maneuver and Couple

Abstract:

A de-couple control method with information feedback from other control channel and a method with double control loops were present for the hypersonic vehicle with non-linear, couple and lateral maneuver. The whole controller was divided into two parts: the computation of actuator which deal with control couple and design of control law which solve the problem of movement and aerodynamic couple. The time-varying controller parameter method and robust control law were present to solve the problem of quick time-varying model parameter and non-linear. Finally these two methods were analyzed contrastively; the simulation result show that these two methods present above can achieve the quick dynamic and high precise track of command. But the latter was better.

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Periodical:

Applied Mechanics and Materials (Volumes 128-129)

Pages:

979-984

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.128-129.979

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Online since:

October 2011

Authors:

Shao Bo Ni, Wei Jun Hu, Song Xiong

Keywords:

Decouple Control, Hypersonic Vehicle, Robust Control

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References

[1] An Xian-yu, Wang Xiao-hu. Research of Dynamic Inversion Decoupling Tracking Control Method for Hypersonic Sliding Vehicle [J]. Journal of system Simulaton, Vol. 22(1).

Google Scholar

[2] Marrison, C T Stengel. R.F. Synthesis of robust control systems for a hypersonic aireraft Decision and Control [J]. In: 33rd IEEE Conference, Lake Buena, (1994).

DOI: 10.1109/cdc.1994.411649

Google Scholar

[3] Wang Qian, Stengel, Robert F. Robust nonlinear control of a hypersonic aircraft [J]. AIAA Guidance, Navigation，and Control Conference and Exhibit. Portland, (1999).

DOI: 10.2514/6.1999-4000

Google Scholar

[4] Pan Yan-peng, Hu Wei-jun, etc. Adaptive Attitude Decoupling Control for High-dynamic Near Space Flying Vehicles [J]. Computer Simulation, Vol. 27(4).

Google Scholar

[5] Zhu Min-xiong, Song Qing. Decoupling Sliding Mode Control in a Nonlinear Spacecraft System {J}. Journal of Beijing University of Aeronautics and Astronautics, Vol. 26(5).

Google Scholar

[6] Li Ke-feng, Ren Zhang. Study on Robust Variable Structure Control for Hypersonic Missile in Reentry [J}. Control Technology of Tactics Missiles, No. 3, (2006).

Google Scholar

[7] Liu Yang. Design of Multi-surfaces Fighter Flight Control System [J]. Computer Measurement & Control, Vol. 16(3), (2008).

Google Scholar