Some aspects of a realistic three-dimensional pursuit-evasion game

Imado, Fumiaki

doi:10.2514/3.21002

Cited by 38 publications

(22 citation statements)

References 7 publications

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“…For the purpose of simulations, the following data as taken from [33]- [35] is considered. The missile has initial mass of 165 kg including 15 kg of propellants.…”

Section: B Simulations With Varying Missile Velocitymentioning

confidence: 99%

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Sliding Mode and Inertial Delay Control Based Missile Guidance

Phadke

Talole

2012

IEEE Trans. Aerosp. Electron. Syst.

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A novel formulation of sliding mode control (SMC) based proportional navigation (PN) guidance law is presented. Unlike conventional SMC-based guidance laws, the law presented here does not need any knowledge of bounds of target acceleration. The target acceleration is estimated using the so-called inertial delay control (IDC). Closed-loop stability for the guidance loop is established. Simulations are carried out by considering highly-maneuvering targets and constant as well as varying missile velocity and the results are presented to demonstrate the effectiveness of the proposed formulation.

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“…For the purpose of simulations, the following data as taken from [33]- [35] is considered. The missile has initial mass of 165 kg including 15 kg of propellants.…”

Section: B Simulations With Varying Missile Velocitymentioning

confidence: 99%

“…Next we take a more realistic approach [31][32][33][34][35][36][37][38][39] by considering the effect of thrust and drag when the propulsion system is on and only drag otherwise. To this end, the equations (1) are augmented by…”

Section: B Simulations With Varying Missile Velocitymentioning

confidence: 99%

Sliding Mode and Inertial Delay Control Based Missile Guidance

Phadke

Talole

2012

IEEE Trans. Aerosp. Electron. Syst.

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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%

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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“…[13][14][15][16][17][18][19][20] A three-dimensional pursuit-evasion game between a realistic missile and an aircraft is studied in Imado 13 employing point-mass models for both vehicles. The nonlinear dynamic characteristics of pursuit situation in the three-dimensional space were taken into account to analyze the performance and capturability of PPN law.…”

Section: Introductionmentioning

confidence: 99%

A generalized design method for three-dimensional guidance laws

Zhou

Teo

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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The true proportional navigation guidance law, the augmented proportional navigation guidance law, or the adaptive sliding-mode guidance law, is designed based on the planar target-to-missile relative motion dynamics. By a proper construction of a nonlinear Lyapunov function for the line-of-sight angular rates in the three-dimensional guidance dynamics, it is shown that the three guidance laws mentioned above are able to ensure the asymptotic convergence of the angular rates as they are directly applied to the three-dimensional guidance environment. Furthermore, considering the missile autopilot dynamics as a first-order lag, we design three-dimensional nonlinear guidance laws by using the backstepping technique for three cases: (1) the target does not maneuver; (2) the information of target acceleration can be acquired; and (3) the target acceleration is not available but its bound is known a priori. In the first step of the backstepping design of the control law, there is no need to cancel the nonlinear coupling terms in the three-dimensional guidance dynamics in such way that the final expressions of the proposed guidance laws are significantly simplified. Thus, the proposed nonlinear Lyapunov function for the line-of-sight angular rates is a generalized function for designing three-dimensional guidance laws. Simulation results of a missile interception mission show that the proposed guidance laws are highly effective.

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Some aspects of a realistic three-dimensional pursuit-evasion game

Cited by 38 publications

References 7 publications

Sliding Mode and Inertial Delay Control Based Missile Guidance

Sliding Mode and Inertial Delay Control Based Missile Guidance

Engagement Tactics for Two Missiles Against an Optimally Maneuvering Aircraft

A generalized design method for three-dimensional guidance laws

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