Acceleration autopilot design for gliding guided projectiles with less measurement information

Xu, Qiuping; Chang, Sijiang; Wang, Zhongyuan

doi:10.1016/j.ast.2018.03.007

Cited by 11 publications

(1 citation statement)

References 14 publications

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“…Spinning motion, which can offset the effect of missile misalignment and eccentric mass and decrease the free flight distribution, is widely applied [1][2][3][4][5][6][7] in the design of various missiles. However, unlike nonspinning missiles, spinning missiles suffer from strong aerodynamic and control cross-coupling between the yaw and pitch channels.…”

Section: Introductionmentioning

confidence: 99%

Coning motion stability and decoupling methods analysis of spinning missiles with angle‐of‐attack feedback autopilot

Wang

et al. 2022

Asian Journal of Control

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The angle-of-attack (AOA) three-loop feedback autopilot is an improved three-loop autopilot that has been widely employed in missile control systems. For spinning missiles, however, unstable coning motion can be induced by the cross-couple effect. For spinning missiles with an AOA feedback autopilot, this paper analyzes the coning motion stability with the consideration of the augmentation loop and the position of the accelerometer and compares the performance of three decoupling methods. First, a novel double-channel actuator AOA three-loop autopilot is established, and the sufficient and necessary condition of coning motion stability is proposed analytically on account of the complex system equations. The stability condition shows that the stable region of the design parameters for the autopilot shrinks as a result of the spinning condition. Moreover, methods associated with actuator dynamics, control coupling, static stability, and the decoupling method of setting the lead angle to the control system are presented to improve the stability of spinning missiles. Numerical simulations are implemented to demonstrate the accuracy of the proposed methods, whose results illustrate that the stability conditions can guide AOA autopilot design for the flight stabilization of spinning missiles.

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Section: Introductionmentioning

confidence: 99%

Coning motion stability and decoupling methods analysis of spinning missiles with angle‐of‐attack feedback autopilot

Wang

et al. 2022

Asian Journal of Control

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UDE-Based Robust Optimal Autopilot Design for Gliding-Guided Projectiles Subjected to Coupling Input Magnitude and Rate Saturation

Zhang

2021

Int. J. Aeronaut. Space Sci.

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Integrated guidance and control design for the hypersonic interceptor based on adaptive incremental backstepping technique

Chang

Guo

Cieslak

et al. 2019

Aerospace Science and Technology

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Acceleration autopilot design for gliding guided projectiles with less measurement information

Cited by 11 publications

References 14 publications

Coning motion stability and decoupling methods analysis of spinning missiles with angle‐of‐attack feedback autopilot

Coning motion stability and decoupling methods analysis of spinning missiles with angle‐of‐attack feedback autopilot

UDE-Based Robust Optimal Autopilot Design for Gliding-Guided Projectiles Subjected to Coupling Input Magnitude and Rate Saturation

Integrated guidance and control design for the hypersonic interceptor based on adaptive incremental backstepping technique

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