3D unified approach to missile guidance laws

Autonomous aerial hard docking is the process where an aircraft approaches and forms a rigid connection with another aircraft. After the docking process is complete, it is not necessary for the lift and propulsion system of the docked aircraft to be operating. Docking allows the larger aircraft to carry the small aircraft outside its airframe, thereby extending the range of endurance of the smaller aircraft. In this paper, we investigate specific scenario where docking occurs between a rotary wing aircraft and a fixed wing aircraft. To perform the above procedure, a guidance system on each platform has to ensure interception while satisfying the primary interception condition of velocity vector co-linearity at the moment of intercept of the two trajectories or flight paths. Pursuit guidance and proportional navigation were assessed as candidates for further development for the terminal docking phase. Since the platforms are in quasi-perfect knowledge of each other, the pursuer evader scenario is replaced by the pursuer-pursuer scenario. The novelty of this work lies in the formulation of terminal constraints, as well as the findings obtained. This paper concludes that contrary to the missile guidance scenario, pursuit based guidance laws provide superior baseline laws from which AAHD guidance and navigation laws can be developed.

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Two composite guidance laws based on the backstepping control and disturbance observers with autopilot lag

Transactions of the Institute of Measurement and Control ◽

10.1177/0142331218821422 ◽

2019 ◽

Vol 41 (10) ◽

pp. 2957-2969 ◽

Cited By ~ 2

Author(s):

Chaoyuan Man ◽

Zhenxing Zhang ◽

Shihua Li

Keyword(s):

Disturbance Observer ◽

Three Dimensional ◽

Simulation Studies ◽

Missile Guidance ◽

Nonlinear Disturbance Observer ◽

First Order ◽

Guidance Law ◽

Control Scheme ◽

Backstepping Controller ◽

Guidance Laws

A composite three-dimensional (3D) missile guidance law is proposed for manoeuvering targets with the consideration of the first-order autopilot dynamics without any linearization. This guidance law consists of a backstepping controller and a feedforward compensation based on disturbance observers. In this control scheme, the unknown target acceleration is regarded as part of the lumped disturbance, estimated by a disturbance observer, and then feedforward compensated. The backstepping controller is introduced to deal with unmatched disturbances. Moreover, both the nonlinear disturbance observer (NDOB) and the generalized proportional integral observer (GPIO) are employed in the derivation. Simulation studies demonstrate the effectiveness of the proposed guidance law, and compare the guidance performance of the two composite guidance laws with different disturbance observers.

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Multiobjective Evolutionary Algorithm for Designing Fuzzy-Based Missile Guidance Laws

Journal of Aerospace Engineering ◽

10.1061/(asce)as.1943-5525.0000057 ◽

2011 ◽

Vol 24 (1) ◽

pp. 89-94 ◽

Cited By ~ 1

Author(s):

Hanafy M. Omar ◽

M. A. Abido

Keyword(s):

Evolutionary Algorithm ◽

Missile Guidance ◽

Multiobjective Evolutionary Algorithm ◽

Guidance Laws

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Nonlinear Control for Missile Terminal Guidance

Journal of Dynamic Systems Measurement and Control ◽

10.1115/1.1316796 ◽

2000 ◽

Vol 122 (4) ◽

pp. 663-668 ◽

Cited By ~ 27

Author(s):

Der-Cherng Liaw ◽

Yew-Wen Liang ◽

Chiz-Chung Cheng

Keyword(s):

Nonlinear Control ◽

Design Procedure ◽

Variable Structure Control ◽

Variable Structure ◽

Missile Guidance ◽

Proportional Navigation ◽

Structure Control ◽

Guidance Laws ◽

Terminal Guidance

Variable Structure Control (VSC) technique is applied to the design of robust homing missile guidance laws. In the design procedure, the target’s maneuver is assumed to be unpredictable and is considered as disturbances. Guidance laws are then proposed to achieve the interception performance for both cases of longitude-axis control being available and unavailable. The proposed guidance laws are continuous which alleviate chattering drawback by classic VSC design. Results are obtained and compared with those by realistic true proportional navigation design to illustrate the benefits of the proposed design. [S0022-0434(00)00604-3]

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