Optimal diving maneuver strategy considering guidance accuracy for hypersonic vehicle

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

doi:10.1016/j.actaastro.2014.07.026

Cited by 15 publications

(10 citation statements)

References 17 publications

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“…The traditional relative dynamics for dive guidance design between the target and the hypersonic vehicle generally divide the diving motion into longitudinal and lateral sub-planes. 9,16 In Liu et al. 9 and Zhu et al.…”

Section: Dive Guidance Schemementioning

confidence: 99%

“…9 and Zhu et al. 16 the authors analyzed the couplings between these two sub-planes based on the intuitionistic geometry relationship between the LOS and the velocity vector of the hypersonic vehicle. However, the inherent dynamics of the relative motion has not been exposit yet.…”

Section: Dive Guidance Schemementioning

confidence: 99%

“…The last question is that the three-dimensional (3D) relative dynamics between the target and the hypersonic vehicle described in the public papers generally divide the diving motion into longitudinal and lateral sub-planes, 15 or be implemented based on the intuitionistic geometry relationships between the LOS and the velocity vector of the hypersonic vehicle. 16 Note that the dynamical and kinematical models of the hypersonic vehicle are more complex and coupling, and the high-precision navigation is more difficult to be realized, so it will be very necessary and essential to analyze and implement the dive guidance schemes considering the model uncertainties, the aerodynamic uncertainties, the navigation errors, and the measurement noise.…”

Section: Introductionmentioning

confidence: 99%

“…9 The first aspect converts the guidance design process into a control problem of the firstorder derivatives of angles of the line-of-sight (LOS) between the target and the hypersonic vehicle. Modern control theories such as the feedback control method, 1,9 optimal control method, 10,16 and sliding mode control approach, 2,15,11 have been well employed and verified in the design of the dive guidance scheme of hypersonic vehicles. The second aspect is called the trajectory tracking method, the reference trajectories should be firstly designed, and then the classical perturbation theory is usually adopted to implement the guidance missions.…”

Section: Introductionmentioning

confidence: 99%

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A fast robust guidance scheme for a hypersonic vehicle in the diving phase

Wang

Liu

Wang

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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A fast robust dive guidance scheme for a hypersonic vehicle is proposed based on the extended state observer and sliding mode observer. The three-degree-of-freedom centroid dynamical and kinematical equations containing model and aerodynamic uncertainties are established. A novel three-dimensional coupling relative dynamical model is described based on exact coordinate transformations. The fast robust dive guidance scheme considering navigation errors and uncertainties is derived with the help of extended state observer and sliding mode observer. An optimal control allocation is adopted and the actual commands of the angle of attack and bank angle are obtained via the second order actuator model. Finally, the performance and robustness of the novel dive guidance scheme is verified and validated via an air-breathing generic hypersonic vehicle.

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Section: Dive Guidance Schemementioning

confidence: 99%

Section: Dive Guidance Schemementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

A fast robust guidance scheme for a hypersonic vehicle in the diving phase

Wang

Liu

Wang

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…In recent years, the optimal guidance law is investigated intensively based on optimal control theory [7]. The different forms of guidance law can be achieved by different performance indexes, such as the minimum miss distance, the minimum consumption, and the minimum time.…”

Section: Introductionmentioning

confidence: 99%

A Terminal Guidance Law Based on Motion Camouflage Strategy of Air-to-Ground Missiles

Gao¹,

Wu-xing³

2016

International Journal of Aerospace Engineering

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A guidance law for attacking ground target based on motion camouflage strategy is proposed in this paper. According to the relative position between missile and target, the dual second-order dynamics model is derived. The missile guidance condition is given by analyzing the characteristic of motion camouflage strategy. Then, the terminal guidance law is derived by using the relative motion of missile and target and the guidance condition. In the process of derivation, the three-dimensional guidance law could be designed in a two-dimensional plane and the difficulty of guidance law design is reduced. A two-dimensional guidance law for three-dimensional space is derived by bringing the estimation for target maneuver. Finally, simulation for the proposed guidance law is taken and compared with pure proportional navigation. The simulation results demonstrate that the proposed guidance law can be applied to air-to-ground missiles.

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