Missile Guidance Laws Based on Singular Perturbation Methodology

1980 ◽  
Vol 3 (2) ◽  
pp. 158-165 ◽  
Author(s):  
B. Sridhar ◽  
N.K. Gupta
Keyword(s):  
Singular Perturbation ◽  
Missile Guidance ◽  
Guidance Laws

Investigation into Air Interception Guidance Algorithms for Autonomous Aerial Hard Docking of Dissimilar Platforms

2014 ◽  
Vol 629 ◽  
pp. 214-218
Author(s):  
Omar Kassim Ariff ◽  
E. Salami ◽  
M.T. Ahmad ◽  
T.H. Go
Keyword(s):  
Guidance System ◽  
Missile Guidance ◽  
Proportional Navigation ◽  
Terminal Constraints ◽  
Rigid Connection ◽  
The Moment ◽  
Further Development ◽  
Rotary Wing ◽  
Guidance Laws ◽  
Specific Scenario

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.

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

2019 ◽  
Vol 41 (10) ◽  
pp. 2957-2969 ◽  
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.

Nonlinear Control for Missile Terminal Guidance

2000 ◽  
Vol 122 (4) ◽  
pp. 663-668 ◽  
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]

Missile guidance laws based on pursuit–evasion game formulations

Automatica ◽  
2003 ◽  
Vol 39 (4) ◽  
pp. 607-618 ◽  
Author(s):  
Vladimir Turetsky ◽  
Josef Shinar
Keyword(s):  
Missile Guidance ◽  
Pursuit Evasion ◽  
Evasion Game ◽  
Guidance Laws

APPLICATION OF THE TAGUCHI QUALITY METHOD TO DESIGN NAVIGATION CONSTANTS THAT ARE ROBUST TO TARGET MANEUVERS

2013 ◽  
Vol 37 (2) ◽  
pp. 231-246
Author(s):  
Chien-Chun Kung ◽  
Feng-Lung Chiang ◽  
Ciann-Dong Yang
Keyword(s):  
Quality Control ◽  
Missile Guidance ◽  
Time Constants ◽  
Control Approach ◽  
Guidance Law ◽  
Simulation Results ◽  
Noise Factors ◽  
Guidance Laws

The object of this paper is to present a quality control approach to design the navigation constants for missile guidance law that are robust for target’s maneuverability and missile’s performance. Target’s maneuvers and missile's time constants are considered to be noise factors and Taguchi Quality Method (TQM) is used to conduct matrix experiments and determine the robust navigation constants. From the simulation results for three kinds of guidance laws, we find that robust navigation constants have a greater ability to enhance the interception of targets that are performing uncertain maneuvers with less interception time and smaller miss distances in the hitting phase.

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