Reentry trajectory optimization for hypersonic vehicle satisfying complex constraints

Zhao, Jiang; Zhou, Rui

doi:10.1016/j.cja.2013.10.009

Cited by 112 publications

(44 citation statements)

References 10 publications

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“…It is found that with more than sixty LG points [54], the GPM can basically lead to an error less than 5% between the ODE trajectory and approximated trajectory. Based on the multiphase technique, some extensions of the standard GPM were also proposed to optimize the reference trajectory of hypersonic vehicles with complex geographic constraints [58,59].…”

Section: Gpmmentioning

confidence: 99%

Progress in reentry trajectory planning for hypersonic vehicle

Zhao

Zhou

Jin

2014

J. of Syst. Eng. Electron.

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The reentry trajectory planning for hypersonic vehicles is critical and challenging in the presence of numerous nonlinear equations of motion and path constraints, as well as guaranteed satisfaction of accuracy in meeting all the specified boundary conditions. In the last ten years, many researchers have investigated various strategies to generate a feasible or optimal constrained reentry trajectory for hypersonic vehicles. This paper briefly reviews the new research efforts to promote the capability of reentry trajectory planning. The progress of the onboard reentry trajectory planning, reentry trajectory optimization, and landing footprint is summarized. The main challenges of reentry trajectory planning for hypersonic vehicles are analyzed, focusing on the rapid reentry trajectory optimization, complex geographic constraints, and cooperative strategies.

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Section: Gpmmentioning

confidence: 99%

Progress in reentry trajectory planning for hypersonic vehicle

Zhao

Zhou

Jin

2014

J. of Syst. Eng. Electron.

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“…Recently, many researchers start on the development of the cooperative guidance laws for the salvo attack of multiple missiles, which may have better performance than the individual missile system in detecting the maneuvering targets, penetrating the defense systems, and surviving the threats [7][8][9]. In this case, it is more difficult to achieve a simultaneous attack against the target in the light of different initial conditions as well as the communication limitation between each missile [10][11][12][13].…”

Section: Introductionmentioning

confidence: 99%

Unified approach to cooperative guidance laws against stationary and maneuvering targets

2015

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This paper presents the unified cooperative strategies for the salvo attack of multiple missiles on the basis of the traditional proportional navigation (PN) algorithm. The cooperative guidance laws are developed in a quite simple formulation consisting of a PN component for target capture and a coordination component for simultaneous arrival. The centralized coordination algorithms have better performance when the global information of time-to-go can be obtained by each missile, whereas the decentralized coordination algorithms come into effect when the group member is only able to collect information from its neighbors. The cooperative strategies can achieve a simultaneous attack against both stationary and maneuvering targets. Numerical simulations are used to demonstrate that the proposed approaches are feasible and flexible for the salvo attack of multiple missiles. The capturability analyses of the cooperative guidance laws are also performed by discussing the selection of gain parameters.

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“…However, in some papers [17,25] the attack angle is not a constant and the two control variables can change at the same time to a large degree.…”

Section: Hgv Aerodynamic Modelmentioning

confidence: 99%

A Cost-Effective Tracking Algorithm for Hypersonic Glide Vehicle Maneuver Based on Modified Aerodynamic Model

2016

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Abstract:In order to defend the hypersonic glide vehicle (HGV), a cost-effective single-model tracking algorithm using Cubature Kalman filter (CKF) is proposed in this paper based on modified aerodynamic model (MAM) as process equation and radar measurement model as measurement equation. In the existing aerodynamic model, the two control variables attack angle and bank angle cannot be measured by the existing radar equipment and their control laws cannot be known by defenders. To establish the process equation, the MAM for HGV tracking is proposed by using additive white noise to model the rates of change of the two control variables. For the ease of comparison several multiple model algorithms based on CKF are presented, including interacting multiple model (IMM) algorithm, adaptive grid interacting multiple model (AGIMM) algorithm and hybrid grid multiple model (HGMM) algorithm. The performances of these algorithms are compared and analyzed according to the simulation results. The simulation results indicate that the proposed tracking algorithm based on modified aerodynamic model has the best tracking performance with the best accuracy and least computational cost among all tracking algorithms in this paper. The proposed algorithm is cost-effective for HGV tracking.

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Reentry trajectory optimization for hypersonic vehicle satisfying complex constraints

Cited by 112 publications

References 10 publications

Progress in reentry trajectory planning for hypersonic vehicle

Progress in reentry trajectory planning for hypersonic vehicle

Unified approach to cooperative guidance laws against stationary and maneuvering targets

A Cost-Effective Tracking Algorithm for Hypersonic Glide Vehicle Maneuver Based on Modified Aerodynamic Model

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