Midcourse Guidance for Exoatmospheric Interception Using Response Surface Based Trajectory Shaping

Ann, Sungjun; Lee, Seok-Won; Kim, Youdan; Ahn, Ji-Whan

doi:10.1109/taes.2020.2976084

Cited by 15 publications

(4 citation statements)

References 12 publications

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“…The proposed switching threshold method can effectively save fuel when the threshold of the first stage is ε 1 = 0 m/s and the threshold of the second stage is ε 2 = 70 m/s. Compared with the methods of regenerating optimal trajectories based on the target's maneuver in documents [6][7][8][9][10][11][12][13][14][15][16][17], the method in this paper does not need to regenerate the optimal trajectory based on the updated PIP of the target, which avoids the huge computational cost brought by re-optimization. In addition, compared with the methods in documents [18][19][20][21][22][23][24][25][26][27], the correction algorithm in this paper is not limited to the original trajectory.…”

Section: Discussionmentioning

confidence: 99%

“…The first type is to re-optimize a trajectory for the interceptor, and some researchers propose the method of the online re-optimization trajectory according to the changes of state and constraint. In [6], an improved zero effort miss and zero effort velocity (ZEM/ZEV) guidance law was proposed for the guidance of anti-ballistic missiles outside the atmosphere. According to the updated terminal conditions, a flight trajectory was re-optimized.…”

Section: Introductionmentioning

confidence: 99%

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Correction Strategy of Online Midcourse Guidance for High-Speed Gliding Target Interceptor

et al. 2023

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During the interception of a high-speed gliding vehicle (HGV), the predicted intercept point (PIP) is updated many times, so the interceptor must continuously adjust its trajectory. In this paper, we propose an online guidance correction algorithm for the interceptor, which can effectively meet the position constraints and energy management of the guidance process. Firstly, we simplify the interceptor’s maneuvering problem to a two-body orbital transfer problem. The Lambert orbit transfer method is used to enable the interceptor to maneuver towards the target’s PIP. Secondly, by comparing the target’s high probability existence area (THPEA) with the interceptor-interceptable area (IIA), the engine start threshold is set in stages to avoid frequent redundancy maneuvers caused by frequent engine starting during missile correction. This approach achieves energy management. Simulation results show that our midcourse guidance strategy is effective.

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Section: Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Correction Strategy of Online Midcourse Guidance for High-Speed Gliding Target Interceptor

et al. 2023

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“…But there is no study on precise analytical solution to ascent trajectory. The existing ascent guidance laws in an analytic manner ignore the aerodynamic force, which results in large prediction error as for the endoatmospheric trajectory [39,40]. In endoatmospheric ascent phase, the variations in velocity, altitude, and flight-path angle are much great, which leads to the great difference in a flight environment.…”

Section: Introductionmentioning

confidence: 99%

Endoatmospheric Ascent Optimal Guidance with Analytical Nonlinear Trajectory Prediction

Zhao

Chen

Yang

2022

International Journal of Aerospace Engineering

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In this paper, an endoatmospheric ascent optimal guidance law with terminal constraint is proposed, which is under the framework of predictor-corrector algorithm. Firstly, a precise analytical nonlinear trajectory prediction with arbitrary Angle of Attack (AOA) profile is derived. This derivation process is divided into two steps. The first step is to derive the analytical trajectory with zero AOA using a regular perturbation method. The other step is to employ pseudospectral collocation scheme and regular perturbation method to solve the increment equation so as to derive the analytical solution with arbitrary AOA profile. The increment equation is formulated by Taylor expansion around the trajectory with zero AOA which remains the second order increment terms. Therefore, the resulting analytical solutions are the nonlinear functions of high order terms of arbitrary AOA values discretized in Chebyshev-Gauss-Legendre points, which has high accuracy. Secondly, an iterative correction scheme using analytical gradient is proposed to solve the endoatmospheric ascent optimal guidance problem, in which the dynamical constraint is enforced by the resulting analytical solutions. It only takes a fraction of a second to get the guidance command. Nominal simulations, Monte Carlo simulations, and optimality verification are carried out to test the performance of the proposed guidance law. The results show that it not only performs well in providing the optimal guidance command, but also has great applicability, high guidance accuracy and computational efficiency. Moreover, it has great robustness even in large dispersions and uncertainties.

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“…But during the intercept, there may be no guarantee that the interceptor meets some path restrictions. Ann et al [7] combined zero effort trajectory with minimum time trajectory to predict intercept points. Liu et al [8] proposed a midcourse guidance law considering the influence of random interference, detection range constraint, and target capture probability.…”

Section: Introductionmentioning

confidence: 99%

Fast Trajectory Generation Method for Midcourse Guidance Based on Convex Optimization

Zhang

Zhou

et al. 2022

International Journal of Aerospace Engineering

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To generate the midcourse guidance trajectory for intercepting the high-speed and high maneuvering target, which is a strongly nonlinear and strongly constrained problem, a two-stage convex optimization method is proposed to solve the optimal trajectory quickly. In the first stage, an initial trajectory generation method is proposed, by which the trajectory’s terminal state is close to the terminal position. And the generated trajectory is used as the initial solution of the convex optimization method. In the second stage, the original nonconvex optimization problem is transformed into a convex optimization problem by linearization and relaxation methods and then solved discretely. In the numerical simulation, the effectiveness of the proposed method is verified, and the robustness of the method is verified in different initial and terminal states. Then, several ablation experiments are operated to verify the advantage of the rapid initial trajectory generation method in the first stage. Finally, compared with the gauss pseudospectral method (GPM), the proposed method is proved to be efficient and has the potential of online trajectory generation.

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Midcourse Guidance for Exoatmospheric Interception Using Response Surface Based Trajectory Shaping

Cited by 15 publications

References 12 publications

Correction Strategy of Online Midcourse Guidance for High-Speed Gliding Target Interceptor

Correction Strategy of Online Midcourse Guidance for High-Speed Gliding Target Interceptor

Endoatmospheric Ascent Optimal Guidance with Analytical Nonlinear Trajectory Prediction

Fast Trajectory Generation Method for Midcourse Guidance Based on Convex Optimization

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