Efficiency of the Invariant Control of Atmospheric Flight*

2021 ◽  
Author(s):  
B. N. Kiforenko ◽  
Ya. V. Tkachenko
Keyword(s):  
Invariant Control

Invariant control of vehicle descent into atmosphere

1976 ◽  
Vol 3 (5-6) ◽  
pp. 357-367 ◽  
Author(s):  
M. Khrustalev ◽  
Yu. Plotnikov ◽  
V. Belov
Keyword(s):  
Invariant Control

scholarly journals A Drift-Free Left Invariant Control System on the Lie Group SO(3)×R3×R3

2015 ◽  
Vol 2015 ◽  
pp. 1-9 ◽  
Author(s):  
Camelia Pop
Keyword(s):  
Control System ◽  
Numerical Integration ◽  
Lie Algebra ◽  
Lie Group ◽  
Poisson Structure ◽  
Dual Space ◽  
Free System ◽  
Geometrical Properties ◽  
Free Left ◽  
Invariant Control

A controllable drift-free system on the Lie group G=SO(3)×R3×R3 is considered. The dynamics and geometrical properties of the corresponding reduced Hamilton’s equations on g∗,·,·- are studied, where ·,·- is the minus Lie-Poisson structure on the dual space g∗ of the Lie algebra g=so(3)×R3×R3 of G. The numerical integration of this system is also discussed.

scholarly journals Frequency-Domain Robust Performance Condition for Controller Uncertainty in SISO LTI Systems: A Geometric Approach

2009 ◽  
Vol 2009 ◽  
pp. 1-9
Author(s):  
Vahid Raissi Dehkordi ◽  
Benoit Boulet
Keyword(s):  
Frequency Domain ◽  
Linear Time ◽  
Order Reduction ◽  
Geometric Approach ◽  
Geometrical Approach ◽  
Robust Performance ◽  
Linear Time Invariant ◽  
Additive Perturbation ◽  
Plant Uncertainty ◽  
Invariant Control

This paper deals with the robust performance problem of a linear time-invariant control system in the presence of robust controller uncertainty. Assuming that plant uncertainty is modeled as an additive perturbation, a geometrical approach is followed in order to find a necessary and sufficient condition for robust performance in the form of a bound on the magnitude of controller uncertainty. This frequency domain bound is derived by converting the problem into an optimization problem, whose solution is shown to be more time-efficient than a conventional structured singular value calculation. The bound on controller uncertainty can be used in controller order reduction and implementation problems.

Analytical synthesis of the pitch-invariant control of the helicopter longitudinal motion with invariance of a pitch angle

2021 ◽  
Author(s):  
Keyword(s):  
Pitch Angle ◽  
Mimo System ◽  
Pole Placement ◽  
Longitudinal Motion ◽  
System Decomposition ◽  
Linearized Model ◽  
Invariant Control ◽  
Poles Placement ◽  
Analytical Expressions ◽  
Analytical Synthesis

The control for the linearized model of the longitudinal motion fourth order for a single-rotor helicopter is analytically synthesized which ensures the invariance of the pitch angle in the presence of disturbances in the control channels, as well as the required the poles placement of the closed-loop system, given from the region of their stability. The results of the numerical synthesis control for the longitudinal motion of a single-rotor helicopter by using analytically synthesized laws of invariant control, which confirm the reliability of the analytical expressions are shown. Keywords invariance; disturbances in the control channels; MIMO-system; decomposition; pole placement; analytical synthesis; longitudinal motion of a single-rotor helicopter; poles of a dynamical system

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