Advanced stabilization system algorithms of launch vehicle's first stage with attack and sliding angles control

2009 ◽  
Vol 15 (4) ◽  
pp. 72-78
Author(s):  
A.N. Kalnoguz ◽  
◽  
V.M. Tykhovskiy ◽  
V.A. Bataev ◽  
V.N. Pilguy ◽  
...  
Keyword(s):  
2020 ◽  
Vol 8 (3) ◽  
pp. 189-197
Author(s):  
Andrey Teteryatnikov ◽  
Alexey Rybakov ◽  
Nikolay Vybornov ◽  
Dmitry Starov

2017 ◽  
Vol 73 (9) ◽  
Author(s):  
Maria A. Smirnova ◽  
Mikhail N. Smirnov ◽  
Tatyana E. Smirnova ◽  
Nikolay V. Smirnov

Symmetry ◽  
2021 ◽  
Vol 13 (2) ◽  
pp. 336
Author(s):  
Askhat Diveev ◽  
Elizaveta Shmalko

This article presents a study devoted to the emerging method of synthesized optimal control. This is a new type of control based on changing the position of a stable equilibrium point. The object stabilization system forces the object to move towards the equilibrium point, and by changing its position over time, it is possible to bring the object to the desired terminal state with the optimal value of the quality criterion. The implementation of such control requires the construction of two control contours. The first contour ensures the stability of the control object relative to some point in the state space. Methods of symbolic regression are applied for numerical synthesis of a stabilization system. The second contour provides optimal control of the stable equilibrium point position. The present paper provides a study of various approaches to find the optimal location of equilibrium points. A new problem statement with the search of function for optimal location of the equilibrium points in the second stage of the synthesized optimal control approach is formulated. Symbolic regression methods of solving the stated problem are discussed. In the presented numerical example, a piece-wise linear function is applied to approximate the location of equilibrium points.


Author(s):  
Pavel V. Kovalenko ◽  
Vasilina V. Kovalenko ◽  
Sergei F. Stepanov ◽  
Ivan I. Artyukhov ◽  
Ekaterina E. Mirgorodskaya ◽  
...  

Aerospace ◽  
2021 ◽  
Vol 8 (2) ◽  
pp. 48
Author(s):  
Witold Bużantowicz

A description is given of an application of a linear-quadratic regulator (LQR) for stabilizing the characteristics of an anti-aircraft missile, and an analytical method of selecting the weighting elements of the gain matrix in feedback loop is proposed. A novel method of LQR tuning via a single parameter ς was proposed and tested. The article supplements and develops the topics addressed in the author’s previous work. Its added value includes the observation that the solutions obtained are symmetric pairs, and that the tuning parameter ς proposed for the designed linear-quadratic regulator enables the selection of suitable parameters for the airframe stabilizing loop for the majority of the analytical solutions of the considered Riccati equation.


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