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Maneuver control of the hypersonic gliding vehicle with a scissored pair of control moment gyros

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Abstract

A maneuver control approach using a scissored pair of control moment gyros is proposed to improve the penetration ability of a hypersonic gliding vehicle (HGV) with a relatively high lift-drag ratio. Then, a multivariable strong coupling nonlinear bank-to-turn dynamical model is established for the case of lateral maneuvering of an HGV equipped with a scissored pair of control moment gyros. According to the requirement of coordinated turning of the HGV in a lateral maneuver, a decoupling controller based on feedback linearization and a linear quadratic optimal algorithm is designed. Finally, the large airspace maneuvering trajectories of the HGV including S-shaped, cycloid and spiral maneuvering modes are designed by applying overload control technology. Simulations demonstrate that the designed maneuvering trajectory significantly increases the airspace range and flexibility of the vehicle. The coordinated turn control system achieves an accurate and rapid tracking of the maneuvering trajectories in large airspace.

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Authors and Affiliations

  1. School of Astronautics, Harbin Institute of Technology, Harbin, 150001, China

    Kun Zhao, DengQing Cao & WenHu Huang

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  1. Kun Zhao
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  2. DengQing Cao
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  3. WenHu Huang
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Correspondence to DengQing Cao.

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Zhao, K., Cao, D. & Huang, W. Maneuver control of the hypersonic gliding vehicle with a scissored pair of control moment gyros. Sci. China Technol. Sci. 61, 1150–1160 (2018). https://doi.org/10.1007/s11431-017-9164-6

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  • DOI: https://doi.org/10.1007/s11431-017-9164-6

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