A novel biased proportional navigation guidance law for close approach phase

Su, Wenshan; Dangnai, Yao; Li, Kebo; Chen, Lei

doi:10.1016/j.cja.2015.12.014

Cited by 14 publications

(8 citation statements)

References 24 publications

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“…This is a modification of the proportional navigation guidance law with a bias command b added such that , but is often expressed in the alternative form , by making the substitution . Typically, the bias command b is used to modify the agent’s underlying targeting response so as to accomplish some other objective, such as optimizing the control efficiency of a rocket [20], causing a missile to attain a required impact angle [21], guiding an autonomous vehicle along a specified path [22], or meeting specific rendezvous conditions in spaceflight [23]. Many different variants of biased proportional navigation have been proposed, with bias commands that may be engaged in either a continuous or discontinuous fashion, and that may be specified in either open or closed loop [24].…”

Section: Experimental Designmentioning

confidence: 99%

Obstacle avoidance in aerial pursuit

Brighton

Kempton

France

et al. 2023

Preprint

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Pursuing prey through clutter is a complex and risky activity requiring integration of guidance subsystems for obstacle avoidance and target pursuit. The unobstructed pursuit trajectories of Harris' hawks Parabuteo unicinctus are well modelled by a mixed guidance law feeding back target deviation angle and line-of-sight rate. Here we ask how their closed-loop pursuit behavior is modified in response to obstacles, using high-speed motion capture to reconstruct flight trajectories recorded during obstructed pursuit of maneuvering targets. We find that their trajectories are well modelled by the same mixed guidance law identified previously, which produces a tail-chasing behavior that promotes implicit obstacle avoidance when led by a target that is itself avoiding clutter. When presented with obstacles blocking their path, hawks resolve the pursuit-avoidance conflict by applying a bias command that is well modelled as an open-loop steering correction aiming at a clearance of one wing length from an upcoming obstacle.

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Section: Experimental Designmentioning

confidence: 99%

Obstacle avoidance in aerial pursuit

Brighton

Kempton

France

et al. 2023

Preprint

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“…There are two collision conditions that are possible for every point within the kill zone against higher speed constant velocity targets. 8 One can be achieved by using a positive navigation constant [23][24][25] (i.e., PPN), the other uses a negative navigation constant (i.e., RPN). In this work, the RPN guidance law is implemented to determine the missile command acceleration.…”

Section: Analysis Of Capture Conditionsmentioning

confidence: 99%

A novel capture region of retro proportional navigation guidance law for intercepting high-speed nonmaneuvering targets

Wang

Lei

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, the capturability of retro proportional navigation against high-speed nonmaneuvering targets is analyzed. By using a modified polar coordinate, the equations describing the relative dynamics of the guidance problem become simple. The novel capture region of retro proportional navigation, which is the necessary and sufficient conditions for the interception, is derived by utilizing an auxiliary function. A new constraint condition is added to the derivation of the capture region, which can guarantee capture high-speed targets successfully. Meanwhile, the optimal aiming and the optimal position of interceptor are derived which are used to acquire the excellent initial conditions to capture the high-speed targets. The results show that the capture region of retro proportional navigation is larger compared with pure proportional navigation. Additionally, initial constraint conditions of interceptor in the case of planar engagement are described based on the capture region of retro proportional navigation, which can provide a reference for midcourse trajectory planning. Finally, simulation is performed to verify the feasibility of the initial conditions of the interceptor.

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“…However, the cross-coupling effects between the two planes are neglected in this simplified method, which will make the guidance precision reduce. [1][2][3] Therefore, to improve the guidance performance of the missile system, various guidance techniques in three-dimensional space have been investigated, such as proportional navigation guidance law, 4,5 optimal guidance law, 6 feedback linearisation-based guidance law 7 and nonlinear guidance law. 8,9 Li et al 9 designed a novel finite-time three-dimensional nonlinear terminal guidance law for intercepting manoeuvring targets by using the theory of finite-time input-to-state stability.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional impact angles constrained integral sliding mode guidance law for missiles with input saturation

Qian

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper proposes the three-dimensional impact angles constrained integral sliding mode guidance laws for the missile with the constraint of the input saturation. To solve the problem of the input constraint, an integral sliding mode surface is given for the first time by using the saturation function. The first three-dimensional integral sliding mode guidance law can solve the impact angle constraint and the target accelerations with known upper bound, while the second one can solve the impact angle constraint, input saturation, and the target accelerations with unknown upper bound simultaneously. Finally, numerical simulations are used to verify the effectiveness of the guidance laws.

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A novel biased proportional navigation guidance law for close approach phase

Cited by 14 publications

References 24 publications

Obstacle avoidance in aerial pursuit

Obstacle avoidance in aerial pursuit

A novel capture region of retro proportional navigation guidance law for intercepting high-speed nonmaneuvering targets

Three-dimensional impact angles constrained integral sliding mode guidance law for missiles with input saturation

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