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## Gasodynamic control system for guided missile

### Piotr Bunia

#### Abstract

In this study a model of the missile controlled by gasodynamic method is described. The missile control is realized by single-use impulse control engines. They are mounted around the center of gravity of the missile. The correcting impulses are perpendicular to the main symmetry axis, thus they influence directly on the center of gravity and velocity vector, changing the trajectory of the missile. Every engine can be fired only once in a selected radial direction. The decision when the correcting engine should be fired depends on the value of the control error. The time to fire depends on position of engine and angular speed along the main axis of the missile. In the first part of this study the methods of navigation and guidance of missiles are presented. In the next step, equations of motion of the missile are derived. These equations are obtained from Newton’s second low of motion for rigid body with six degrees of freedom: three linear and three rotational velocity components. The missile equations are obtained by summing up the loads acting on the missile: inertia , gravity, aerodynamic and loads from correction engines. The equations are combined with the missile control system, which calculates the control signal and choose the proper correction engine. In this system, one channel is used to control the missile in horizontal and vertical plane. The missile is using pure pursuit guidance system. The target is detected by mosaic detector, fixed to the rotating missile. The control error is defined by the angle between main axis of the missile and the line connecting target with missile. The main objective is to make this value equal to zero. The trajectory of the missile is corrected by control signal which is based on the control error. The correction engine is fired after receiving the control signal from the controller. In the last part of this study the results of the Matlab-Simulink simulations are shown.
Record ID
WUT210d30d11c5d4133abbb1174ddb74b43
Diploma type
Master of Science
Author
Piotr Bunia (FPAE/IAAM) Piotr Bunia,, The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)Faculty of Power and Aeronautical Engineering (FPAE)
Title in Polish
Supervisor
Robert Głębocki (FPAE/IAAM) Robert Głębocki,, The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)Faculty of Power and Aeronautical Engineering (FPAE)
Certifying unit
Faculty of Power and Aeronautical Engineering (FPAE)
Affiliation unit
The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)
Study subject / specialization
, Lotnictwo i Kosmonautyka
Language
(pl) Polish
Status
Finished
Defense Date
02-02-2012
Issue date (year)
2012
Pages
76
Internal identifier
MEL; PD-1680
Reviewers
Robert Głębocki (FPAE/IAAM) Robert Głębocki,, The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)Faculty of Power and Aeronautical Engineering (FPAE) Elżbieta Jarzębowska (FPAE/IAAM) Elżbieta Jarzębowska,, The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)Faculty of Power and Aeronautical Engineering (FPAE)
Keywords in Polish
układ automatycznego sterowania, pocisk, dynamika pocisku
Abstract in Polish
urn:pw-repo:WUT210d30d11c5d4133abbb1174ddb74b43