Three-dimensional robust diving guidance for hypersonic vehicle

Zhu, J.; Liu, Luhua; Tang, Guojian; Bao, Weimin

doi:10.1016/j.asr.2015.10.037

Cited by 11 publications

(3 citation statements)

References 20 publications

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Section: Other Robust Control Schemesmentioning

confidence: 99%

“…In addition to the aforementioned robust algorithms, other robust control schemes have also been applied in the design of spacecraft guidance and control systems [49,[61][62][63]. Examples include the fault tolerant control-based guidance scheme 465 proposed in [64] and the H ∞ -based guidance algorithm developed in [61]. Besides, in 2016, Bandyopadhyay et al[62] developed an attitude control strategy, together with a nonlinear tracking controller, for spacecrafts carrying a large object.…”

Section: Other Robust Control Schemesmentioning

confidence: 99%

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Review of advanced guidance and control algorithms for space/aerospace vehicles

Chai

Tsourdos

Chai

et al. 2021

Progress in Aerospace Sciences

122

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Section: Other Robust Control Schemesmentioning

confidence: 99%

Section: Other Robust Control Schemesmentioning

confidence: 99%

Review of advanced guidance and control algorithms for space/aerospace vehicles

Chai

Tsourdos

Chai

et al. 2021

Progress in Aerospace Sciences

122

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“…The radar seeker of an interceptor is susceptible to the ground clutter and multipath effects when detecting and tracking the low-altitude target, and measurement noise is easily generated. Current researches on seeker's measurement noise mainly focus on three aspects, that is, filtering [15], measurement model [16], and noise estimation [17]. However, the seeker is only regarded as an independent measurement system in the above methods, and the influence of seeker's measurement noise of the whole interception system is not considered.…”

Section: Introductionmentioning

confidence: 99%

A Composite Guidance Law for Suppressing Measurement Noise of LOS Angular Rate

Feng

2019

Mathematical Problems in Engineering

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To effectively intercept a low-altitude target in clutter background, a nonsingular fast terminal sliding mode guidance law is designed. The designed guidance law can fully exploit the fast convergence characteristics of linear sliding mode control and the finite-time-convergent characteristics of terminal sliding mode control to ensure that the line-of-sight (LOS) angle converges to a desired angle in a limited time at a faster rate. Utilizing the smooth switching characteristics of the hyperbolic tangent function similar to the saturation function, a finite-time-convergent differentiator is designed. Meanwhile, a new finite-time-convergent disturbance observer designed on the tracking differentiator can effectively track the ideal LOS angular rate, suppress the measurement noise, and make a smooth estimation of the target maneuvering acceleration in clutter background. Combining the estimated value of the disturbance observer, the sign function with switch coefficient is introduced to design a composite nonsingular fast terminal sliding mode guidance law. The simulation results show that the composite guidance law can not only effectively suppress the measurement noise of the LOS angular rate and improve the accuracy of low-altitude target intercepting, but also greatly reduce the energy consumption in the interception process.

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