scholarly journals Dynamic Modeling and Analysis of Spacecraft With Variable Tilt of Flexible Appendages

2014 ◽  
Vol 136 (2) ◽  
Author(s):  
Nicolas Guy ◽  
Daniel Alazard ◽  
Christelle Cumer ◽  
Catherine Charbonnel
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Solar Panel ◽  
Physical Parameters ◽  
Attitude Control System ◽  
Multibody Modeling ◽  
Modeling And Analysis ◽  
Complete Revolution ◽  
The Stability ◽  
Flexible Appendages

This article describes a general framework to generate linearized models of satellites with large flexible appendages. The obtained model is parameterized according to the tilt of flexible appendages and can be used to validate an attitude control system over a complete revolution of the appendage. Uncertainties on the characteristic parameters of each substructure can be easily considered by the proposed generic and systematic multibody modeling technique, leading to a minimal linear fractional transformation (LFT) model. The uncertainty block has a direct link with the physical parameters avoiding nonphysical parametric configurations. This approach is illustrated to analyze the attitude control system of a spacecraft fitted with a tiltable flexible solar panel. A very simple root locus allows the stability of the closed-loop system to be characterized for a complete revolution of the solar panel.

Vibration Suppression of an Underactuated Dynamic System Using Virtual Actuators

2016 ◽  
Vol 138 (6) ◽  
Author(s):  
A. M. Khoshnood ◽  
I. Azad ◽  
S. M. Hasani
Keyword(s):  
Control System ◽  
Dynamic System ◽  
Attitude Control ◽  
Vibration Suppression ◽  
Nonlinear Dynamic Model ◽  
Attitude Control System ◽  
Suppression Technique ◽  
A New Technique ◽  
And Performance ◽  
The Stability

Sloshing is one of the critical problems in aerospace vehicles with liquid containers. Motion of the liquid in resonance situations can degrade the stability and performance of attitude control systems. Two important characteristics of this time varying phenomenon are sensorless and underactuated properties which lead to difficulty of attitude control system design. In this paper, a new technique based on soft sensor and virtual actuator is used to suppress the effects of fuel sloshing in an aerospace launch vehicle (ALV). For this purpose, a nonlinear dynamic model of the vehicle with mechanical model of the fuel sloshing is considered as a multibody dynamic system. The preliminary attitude control system of the vehicle is extended using the new vibration suppression technique and a numerical simulation of the nonlinear model is carried out. Results of the simulation show that the undesired effects of the fuel sloshing are effectively decreased using the proposed vibration suppression technique.

Multibody Modeling of Sloshing in Spacecraft Ascent and Landing Maneuvers

2016 ◽  
Author(s):  
Paolo Lunghi ◽  
Pierangelo Masarati ◽  
Michéle Lavagna
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Significant Fraction ◽  
Space Vehicles ◽  
Attitude Control System ◽  
Multibody Modeling ◽  
Violent Sloshing ◽  
Typical Method

Sloshing of liquids in tanks has been always a problem in the design of space vehicles. This is especially true in launch and powered landing systems, in which a significant fraction of the mass is made up of propellant. In such systems, uncontrolled or unexpected violent sloshing phenomena can even lead to the loss of the spacecraft. A typical method to cope with sloshing is to ensure that the attitude control system operates at frequencies much higher than those of the sloshing motion of the fuel. In this case, the project of the controller is realized assuming the liquid as static [1].

scholarly journals Asymptotic Stability of Quaternion-based Attitude Control System with Saturation Function

2017 ◽  
Vol 7 (4) ◽  
pp. 1994 ◽  
Author(s):  
Harry Septanto ◽  
Djoko Suprijanto
Keyword(s):  
Control System ◽  
Angular Velocity ◽  
Rigid Body ◽  
Attitude Control ◽  
Asymptotically Stable ◽  
Attitude Control System ◽  
Saturation Function ◽  
Continuous Scheme ◽  
Rotational Motions ◽  
The Stability

In the design of attitude control, rotational motion of the spacecraft is usually considered as a rotation of rigid body. Rotation matrix parameterization using quaternion can represent globally attitude of a rigid body rotational motions. However, the representation is not unique hence implies difficulties on the stability guarantee. This paper presents asymptotically stable analysis of a continuous scheme of quaternion-based control system that has saturation function. Simulations run show that the designed system applicable for a zero initial angular velocity case and a non-zero initial angular velocity case due to utilization of deadzone function as an element of the defined constraint in the stability analysis.

scholarly journals High Accuracy Attitude Control System Design for Satellite with Flexible Appendages

2014 ◽  
Vol 2014 ◽  
pp. 1-6 ◽  
Author(s):  
Wenya Zhou ◽  
Haixu Wang ◽  
Zhengwei Ruan ◽  
Zhigang Wu ◽  
Enmei Wang
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Design Method ◽  
Notch Filter ◽  
Vibration Signal ◽  
High Accuracy ◽  
Frequency Variation ◽  
Attitude Control System ◽  
The Impact ◽  
Flexible Appendages

In order to realize the high accuracy attitude control of satellite with flexible appendages, attitude control system consisting of the controller and structural filter was designed. When the low order vibration frequency of flexible appendages is approximating the bandwidth of attitude control system, the vibration signal will enter the control system through measurement device to bring impact on the accuracy or even the stability. In order to reduce the impact of vibration of appendages on the attitude control system, the structural filter is designed in terms of rejecting the vibration of flexible appendages. Considering the potential problem of in-orbit frequency variation of the flexible appendages, the design method for the adaptive notch filter is proposed based on the in-orbit identification technology. Finally, the simulation results are given to demonstrate the feasibility and effectiveness of the proposed design techniques.

Double Fail-Safe Attitude Control System for Artificial Meteor Microsatellite ALE-1

2021 ◽  
Vol 19 (1) ◽  
pp. 9-16
Author(s):  
Shinya FUJITA ◽  
Yuji SATO ◽  
Toshinori KUWAHARA ◽  
Yuji SAKAMOTO ◽  
Yoshihiko SHIBUYA ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Attitude Control System ◽  
Fail Safe

Flight performance of the LES-8/9 three-axis attitude control system

1980 ◽  
Author(s):  
F. FLOYD ◽  
C. MUCH ◽  
N. SMITH ◽  
J. VERNAU ◽  
J. WOODS
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Flight Performance ◽  
Attitude Control System
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