Near-Optimal Midcourse Guidance for Velocity Maximization with Constrained Arrival Angle

Li, Hongyan; He, Shaoming; Wang, Jiang; Shin, Hyo‐Sang; Tsourdos, Antonios

doi:10.2514/1.g005250

Cited by 13 publications

(3 citation statements)

References 28 publications

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“…Optimal-control-based midcourse guidance laws were also studied in [14]- [17] without considering the physical dependencies of aerodynamics on flight altitude. More recently, methods for maximisation of final speed were developed in [18] based on online sequential convex programming and in [19] based on the combination of offline trajectory optimisation and waypoint guidance for online implementation.…”

Section: Introductionmentioning

confidence: 99%

Three-Dimensional Guidance Method With Course Modification for Altitude Shaping in Endoatmospheric Interception

Cho

2023

IEEE Trans. Aerosp. Electron. Syst.

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Section: Introductionmentioning

confidence: 99%

Three-Dimensional Guidance Method With Course Modification for Altitude Shaping in Endoatmospheric Interception

Cho

2023

IEEE Trans. Aerosp. Electron. Syst.

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“…Du et al [16] presented a semianalytical method for solving the exoatmospheric midcourse guidance problem with minimum velocity increment. Li et al [17] designed an angleconstrained midcourse guidance trajectory according to the offline optimized trajectory information. But the trajectory generation efficiency of the above method is not ideal for intercepting 3d maneuverable high-speed target.…”

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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“…It is therefore worth it to compare the proposed approach with similar approaches that do not use fuzzy logic but indeed share the same paradigm of guidance toward a target by shaping the approach trajectory in closed loop. Several approaches for guidance with a constraint on the angle of arrival exist [20][21][22] but these are designed specifically for missile application, and thus for intercept, they do not pose much attention to the shape of the obtained trajectory, but more on the feasibility of it withstanding the performance limit of the missile, and for all these reasons, modifications to achieve rendezvous may be very difficult. Modifications of missile guidances for rendezvous were proposed [13,14], but cannot handle a large set of possible initial conditions.…”

Section: Introductionmentioning

confidence: 99%

A Fuzzy Guidance System for Rendezvous and Pursuit of Moving Targets

2020

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This article presents the development of a fuzzy guidance system (FGS) for unmanned aerial vehicles capable of pursuing and performing rendezvous with static and mobile targets. The system is designed to allow the vehicle to approach a maneuvering target from a desired direction of arrival and to terminate the rendezvous at a constant distance from the target. In order to perform a rendezvous with a maneuvering target, the desired direction of arrival is adjusted over time to always approach the target from behind, so that the aircraft and target velocity vectors become aligned. The proposed guidance system assumes the presence of an autopilot and uses a set of Takagi–Sugeno fuzzy controllers to generate the orientation and speed references for the velocity and heading control loops, given the relative position and velocity between the aircraft and the target. The FGS treats the target as a mobile waypoint in a 4-D space (position in 2-dimensions, desired crossing heading and speed) and guides the aircraft on suitable trajectories towards the target. Only when the vehicle is close enough to the rendezvous point, the guidance law is complemented with an additional linear controller to manage the terminal formation keeping phase. The capabilities of the proposed rendezvous-FGS are verified in simulation on both maneuvering and non-maneuvering targets. Finally, experimental results using a multi-rotor aerial system are presented for both fixed and accelerating targets.

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Near-Optimal Midcourse Guidance for Velocity Maximization with Constrained Arrival Angle

Cited by 13 publications

References 28 publications

Three-Dimensional Guidance Method With Course Modification for Altitude Shaping in Endoatmospheric Interception

Three-Dimensional Guidance Method With Course Modification for Altitude Shaping in Endoatmospheric Interception

Fast Trajectory Generation Method for Midcourse Guidance Based on Convex Optimization

A Fuzzy Guidance System for Rendezvous and Pursuit of Moving Targets

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