CORBA Support for Missile Guidance

Earlier stress studies under laboratory conditions show that heart rates from 100 to 110 bpm are associated with significant decrements in missile-tracking performance. Data from real missile tracking by 8 operators with no stress deliberately induced indicate, however, that performance is unaffected up to 135 bpm, and only moderately affected in the 135- to 170-bpm region. The disagreement between the two sets of results highlights the difficulties in generalizing from stress experiments.

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Sampling-based path planning: a new tool for missile guidance

IFAC Proceedings Volumes ◽

10.3182/20130902-5-de-2040.00091 ◽

2013 ◽

Vol 46 (19) ◽

pp. 131-136 ◽

Cited By ~ 3

Author(s):

P. Pharpatara ◽

B. Hérissé ◽

R. Pepy ◽

Y. Bestaoui

Keyword(s):

Path Planning ◽

Missile Guidance

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Development of an educational interactive hardware-in-the-loop missile guidance system simulator

Computer Applications in Engineering Education ◽

10.1002/cae.21888 ◽

2017 ◽

Vol 26 (2) ◽

pp. 341-355 ◽

Cited By ~ 1

Author(s):

Zhongyuan Chen ◽

Wanchun Chen ◽

Xiaoming Liu ◽

Chuang Song

Keyword(s):

Guidance System ◽

Hardware In The Loop ◽

Missile Guidance

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Missile Guidance Algorithm Design Using Particle Swarm Optimization

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.284-287.2411 ◽

2013 ◽

Vol 284-287 ◽

pp. 2411-2415

Author(s):

Chien Chun Kung ◽

Kuei Yi Chen

Keyword(s):

Objective Function ◽

Fitness Function ◽

Equations Of Motion ◽

Algorithm Design ◽

Solution Space ◽

Pso Algorithm ◽

Local Optimum ◽

Missile Guidance ◽

Pursuit Evasion ◽

Guidance Algorithm

This paper presents a technique to design a PSO guidance algorithm for the nonlinear and dynamic pursuit-evasion optimization problem. In the PSO guidance algorithm, the particle positions of the swarm are initialized randomly within the guidance command solution space. With the particle positions to be guidance commands, we predict and record missiles’ behavior by solving point-mass equations of motion during a defined short-range period. Taking relative distance to be the objective function, the fitness function is then evaluated according to the objective function. As the PSO algorithm proceeds, these guidance commands will migrate to a local optimum until the global optimum is reached. This paper implements the PSO guidance algorithm in two pursuit-evasion scenarios and the simulation results show that the proposed design technique is able to generate a missile guidance law which has satisfied performance in execution time, terminal miss distance, time of interception and robust pursuit capability.

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