Suboptimal Midcourse Guidance with Terminal-Angle Constraint for Hypersonic Target Interception

Wan, Shizheng; Chang, Xiaofei; Li, Quancheng; Yan, Jie

doi:10.1155/2019/6161032

Cited by 7 publications

(4 citation statements)

References 26 publications

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“…Simulation results are depicted in Figures 3-6. The LOS rate _ θ is regulated to zero within a period of 4 to 6 seconds as shown in Figures 3(a), 4(a), and 5(a), which leads the ZEM to zero according to Equation (17). Meanwhile, Figures 3(b), 4(b), and 5(b) show that a negative _ r is maintained to ensure that the relative distance between the interceptor and the target decreases.…”

Section: Hypersonic Target Interception In Various Engagementmentioning

confidence: 99%

“…Thus, the application and improvement of modern guidance laws for hypersonic target interception has been investigated. Suboptimal midcourse guidance with a terminal-angle constraint for interceptors against near-space hypersonic targets was introduced in [17], which can provide handover conditions for intercepting hypersonic targets. The results of [18] exploited a fourth-order sliding mode controller in an augmented integrated guidance and control model using an arbitrary order robust exact differentiator to estimate the highorder derivatives of the sliding manifold.…”

Section: Introductionmentioning

confidence: 99%

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Predictive Differential Game Guidance Approach for Hypersonic Target Interception Based on CQPSO

Chen

Bao

2022

International Journal of Aerospace Engineering

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In the descent phase of the hypersonic target flight trajectory, the hypersonic speed of the target makes the reaction time shorter. Due to overload restrictions, it is challenging for the interceptor to achieve successful interception. To address this problem, a predictive differential game guidance approach based on dynamic optimization algorithm is proposed to relax the interceptor acceleration requirements. Two-dimensional kinematics and dynamics engagement mode for hypersonic target interception is formulated as a nonlinear differential control model in the presence of matched uncertainties. The nonlinear differential model is transformed into a differential game model by combining a performance index. The performance index is positively correlated with the Line-Of-Sight (LOS) rate and control effort of interceptor and negatively correlated with the target maneuver. The Chaotic Quantum Particle Swarm Optimization (CQPSO) algorithm is utilized to address the nonlinear differential game problem to generate the instantaneous and predicted guidance commands for the interceptor and target. Numerical examples are given to verify the performance of the proposed guidance law in various engagement scenarios, including different target maneuvers, initial heading angles and target overload. Moreover, the performance of the algorithm is validated comparing with traditional and state-of-the-art guidance laws.

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Section: Hypersonic Target Interception In Various Engagementmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Predictive Differential Game Guidance Approach for Hypersonic Target Interception Based on CQPSO

Chen

Bao

2022

International Journal of Aerospace Engineering

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“…However, in the midcourse guidance, the accurate information of the high-speed target is difficult, which will lead to the larger calculation error of the sight line [4]. To solve this problem, Wan et al [5] used the model predictive static programming method to give a suboptimal guidance law with terminal angle constraints. Ebrahimi et al [6] proposed a new generalized model predictive extended control technology, which smoothed the control signal.…”

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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“…Guidance refers to the process of issuing commands for the interceptor to adjust its position and orientation to fly toward its target while satisfying several constraints [18,19] and demonstrating the optimal performance [20,21]. Many researchers have investigated the interception of hypersonic vehicles and designed various forms of guidance laws [22][23][24][25][26]. Depending on the number of interceptors, the existing guidance laws for intercepting hypersonic vehicles can be categorised as single-interceptor guidance laws or multi-interceptor cooperative guidance laws [27].…”

Section: Introductionmentioning

confidence: 99%

Bulletin of the Polish Academy of Sciences: Technical Sciences

Liu,

Yan

et al. 2022

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The conditions for accurately intercepting hypersonic vehicles by low-speed interceptors in the terminal guidance process are examined, considering the general form of a guidance scheme. First, based on the concept of the engagement geometry, three interception scenarios are established considering different manoeuvring configurations of the interceptors and hypersonic vehicle. Second, the boundary conditions for intercepting hypersonic vehicles (with speeds higher than those of the interceptors) are specified for the three scenarios, considering several factors: the speed, path angle, line-of-sight angle, and available overload of the interceptor; path angle and manoeuvrability of the hypersonic vehicle; and relative distance between the interceptor and vehicle. A series of simulations are performed to clarify the influence of each factor on the Interception performance in the three interception scenarios. The challenges associated with accurately intercepting hypersonic vehicles by low-speed interceptors are summarised, and several recommendations for designing guidance laws are presented.

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Suboptimal Midcourse Guidance with Terminal-Angle Constraint for Hypersonic Target Interception

Cited by 7 publications

References 26 publications

Predictive Differential Game Guidance Approach for Hypersonic Target Interception Based on CQPSO

Predictive Differential Game Guidance Approach for Hypersonic Target Interception Based on CQPSO

Fast Trajectory Generation Method for Midcourse Guidance Based on Convex Optimization

Bulletin of the Polish Academy of Sciences: Technical Sciences

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