Near-Optimal Missile Avoidance Trajectories via Receding Horizon Control

Karelahti, Janne; Virtanen, Kai; Raivio, Tuomas

doi:10.2514/1.26024

Cited by 45 publications

(21 citation statements)

References 24 publications

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“…In a oneon-one engagement, and supposing one has achieved an advantageous position to another and has caught the enemy in his lethal cone, he has to employ his missiles most effectively. Many studies have appeared about optimal missile avoidance by an aircraft [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20], however, only a few papers have treated avoiding multiple missiles [12,18]. The reason for this could be that it is difficult for an aircraft to avoid even one missile, therefore avoiding two missiles is not realistic.…”

Section: Introductionmentioning

confidence: 99%

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Engagement Tactics for Two Missiles Against an Optimally Maneuvering Aircraft

Imado

Kuroda

2011

Journal of Guidance, Control, and Dynamics

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The engagement tactics for two missiles to attack an aircraft are studied. A tail chase scenario between two aircraft is assumed where the attacker tries to kill the evader with two missiles, while the evader employs optimal maneuvers for avoiding two missiles. The algorithm to solve this optimal control problem is first developed. For the aircraft, in order to simultaneously maximize the miss distances against two missiles, a special type of performance index is introduced and the problems are solved by the solver based on the steepest ascent method. The result shows that the aircraft optimal maneuvers are divided into three patterns. Next, the optimal timing for the attacker to launch the two missiles, in order to minimize both miss distances against the aircraft is studied. The effect of their taking trajectory shaping is also studied. Nomenclature= missile navigation gain n = power of penalty function p = penalty function for the first missile r = slant range between missile and aircraft r 12 = initial distance between two missiles r 1a = reference value of the slant range between the first missile and aircraft r 1f , r 2f = closest ranges (miss distances) between the aircraft and the first and second missiles, respectively r m = the mean miss distance between two missiles, r 1f :r 2f 1 2 S = reference area T = thrust t = time t e = sustainer burning time t f = interception time t w1 , t w2 = start time and end time of window function u = control vector v = velocity v c = closing velocity w = window function x, y = longitudinal and lateral coordinates x = state vector , 0 = angle-of-attack and zero-lift angle, respectively = adjoint vector = air density , = line-of-sight and azimuth angles, respectively = missile time constant = performance index for minimizing both miss distances = stopping condition = terminal constraints = time derivative Subscripts a = aircraft c = command signal i = ith missile m = missile max, min = maximum and minimum values, respectively

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Section: Introductionmentioning

confidence: 99%

“… 19. Vehicle trajectories and aircraft control history by using type 3 maneuver for r 12 of 250 m (with trajectory shaping).…”

mentioning

confidence: 99%

Engagement Tactics for Two Missiles Against an Optimally Maneuvering Aircraft

Imado

Kuroda

2011

Journal of Guidance, Control, and Dynamics

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“…Thus, it is constructed as a worst-case no-escape envelope. In [8], the no-escape firingenvelope concept, which was developed originally for offensive purposes, was used to analyze near-optimal missile avoidance trajectories. The analysis included defensive envelope construction, with respect to a missile that is about to be launched, for different performance measures (e.g., capture time, closing velocity, miss distance, and control effort).…”

Section: Introductionmentioning

confidence: 99%

Game-Based Safe Aircraft Navigation in the Presence of Energy-Bleeding Coasting Missile

Alkaher

Moshaiov

2016

Journal of Guidance, Control, and Dynamics

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Tactical-flight scenarios of modern combat aircraft are often executed in the presence of air-to-air or ground-to-air missile threats. One such scenario deals with a navigating aircraft that aims to intercept a nonaggressive adversary aircraft, in the presence of an energy-bleeding coasting missile that was or is launched toward the navigator. When launching of an adversary missile has been detected, the pilot is faced with a constrained optimization problem of closing the distance to the target, while avoiding the threatening missile. Here, the problem is formulated as a twoteam zero-sum differential-game model between the navigator and an adversary coalition of the target and the missile. Solving this game provides an optimal controller, in a closed-loop form, which results in a safe-navigation strategy for the aircraft. The game formulation is based on modeling the missile as a dynamic shrinking obstacle. Both time and range horizons are incorporated to postpone early avoidance from the missile. The proposed approach is tested using a simulated problem. The results demonstrate the strength of the proposed method, which can support the development of an onboard real-time safe-navigation system for tactical-flight scenarios. Nomenclature

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“…Initial value of velocity, flight path and heading angle are determined applying the result of equation (10) in equation (9).…”

Section: Initializationmentioning

confidence: 99%

Air-to-Air Missile Tracking and Guidance Law Identification Based on CKF

Wu¹,

Wang²,

Yang³

et al. 2018

Proceedings of the 2017 4th International Conference on Machinery, Materials and Computer (MACMC 2017)

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An air-to-air missile tracking and guidance law identification method based on CKF is proposed. A precise air-to-air missile model is constructed with drag force taken into consideration. With CKF method and preprocessing, guidance law filter is designed for missile tracking and estimation of guidance law, gravity compensation and drag constant. Simulation results indicate the rapidness and accuracy of this method.

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Near-Optimal Missile Avoidance Trajectories via Receding Horizon Control

Cited by 45 publications

References 24 publications

Engagement Tactics for Two Missiles Against an Optimally Maneuvering Aircraft

Engagement Tactics for Two Missiles Against an Optimally Maneuvering Aircraft

Game-Based Safe Aircraft Navigation in the Presence of Energy-Bleeding Coasting Missile

Air-to-Air Missile Tracking and Guidance Law Identification Based on CKF

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