scholarly journals Formation of an Additional Motion Control Loop for the Nanosatellite to Adapt its Onboard Model to the Current Operating Conditions

2022 ◽  
Vol 1215 (1) ◽  
pp. 012008
Author(s):  
I. A. Lomaka
Keyword(s):  
Attitude Control ◽  
Statistical Modelling ◽  
Operating Conditions ◽  
Control Law ◽  
Time Interval ◽  
Control Loop ◽  
Attitude Control System ◽  
Additional Feedback ◽  
Current Operating ◽  
Selection Of

Abstract The paper presents the formation of additional feedback in the loop of the attitude control system of a nanosatellite. Feedback is based on the assessment of the inertial characteristics of the nanosatellite. The influence of the accuracy of knowledge of the inertial characteristics of a nanosatellite on the formation of an optimal control law in the problem of reorientation was estimated. Statistical modelling has been carried out to assess the effectiveness of nanosatellite on-board sensors in the problem of identifying the inertial characteristics of a nanosatellite. Recommendations for the selection of sensor’s characteristics and time interval of data collection have been formulated.

PLUG AND PLAY INNOSAT ACS SIMULATOR

2015 ◽  
Vol 76 (8) ◽  
Author(s):  
S. M. Sharun ◽  
M. Y. Mashor ◽  
Fadzilah Hashim
Keyword(s):  
Attitude Control ◽  
Operating Conditions ◽  
Matlab Simulation ◽  
Dynamics Model ◽  
Attitude Control System ◽  
Close Match ◽  
Novel Approach ◽  
Simulator Design ◽  
Hardware In Loop ◽  
Hardware In Loop Simulation

This research proposes a novel approach of satellite simulator design where the simulator will be in the form of both software and hardware. A software simulator will represent the satellite dynamics model, incorporating all the operating conditions of the satellite in orbit. The control algorithm for Attitude Control System (ACS) will be implemented on Rabbit Micro Controller (RCM4100) and the dynamics model of Innovative Satellite (InnoSAT) plant in PC have been tested using real-time hardware-in-loop-simulation (HILS) technique. The results that have been obtained show that the InnoSAT ACS simulator can produce as good result as MATLAB simulation for the InnoSAT plants. The MSE values that have been calculated also show that there are a close match between HILS and MATLAB simulation where the MSEs different value are small. From both results, it is enough to verify that the developed protocol working satisfyingly and seems to be possible to be implemented on the actual flight.

Research on Attitude Law of Mass Moment Missile Based on Mulriple Control

2011 ◽  
Vol 181-182 ◽  
pp. 919-925
Author(s):  
Peng Wu ◽  
Qi Chao Chen ◽  
Jiao Ding Ning
Keyword(s):  
Attitude Control ◽  
Variable Structure ◽  
Control System Design ◽  
Control Law ◽  
Attitude Control System ◽  
Sign Function ◽  
Structure Control ◽  
System A ◽  
Mass Moment ◽  
Simulation Results

Aimed at characteristics of mass moment of missiles in exo-atmosphere, it’s inferred that 6-DOF mathematical model based on mass moment controlling stabilities on three axes. Considering the problem of harmoniously controlling two moving masses, moving mass based non-linear theorem was used to solve a series of problems met in attitude control system design. In order to weaken the chattering of the system, a saturation function is introduced to substitute for Sign function to improve the variable structure control law so that the chattering can be depressed. The simulation results illustrate the efficiency of this method.

scholarly journals Nonlinear suboptimal attitude control law for near-space hypersonic vehicle: Eigenvalue analysis and weight matrices design

2022 ◽  
Author(s):  
Peichao Mi ◽  
Qingxian Wu ◽  
Yuhui Wang
Keyword(s):  
Optimal Control ◽  
Control System ◽  
Attitude Control ◽  
Stable Manifold ◽  
Closed Loop ◽  
Suboptimal Control ◽  
Control Law ◽  
Attitude Dynamics ◽  
Attitude Control System ◽  
Near Space

Abstract This paper considers a nonlinear suboptimal control problem for a near-space hypersonic vehicle's (NSHV's) attitude dynamics. The least-square and stable manifold methods first solve an unconstrained approximately optimal control law corresponding to the nonlinear attitude model. Then, to further meet the dynamic performance requirement of the attitude control system, a novel strategy based on the Koopman operator, symplectic geometric theory, and the stable manifold theorem is proposed to approximate the eigenvalues of the closed-loop nonlinear unconstrained approximated optimal control system. The weight matrices in the optimal performance index, which directly determine the output responses of the nonlinear attitude dynamics, can be appropriately designed according to the eigenvalues. The final control law considers the actuator constraints. The NSHV's closed-loop attitude control system is proved to be locally exponentially stable, and the suboptimality of the control law is analyzed. Numerical simulation demonstrates the effectiveness of the proposed scheme.

Stability Analysis of the Microsatellite Attitude Control System

2015 ◽  
Vol 798 ◽  
pp. 297-302
Author(s):  
Meirbek Moldabekov ◽  
Suleimen Yelubayev ◽  
Kuanysh Alipbayev ◽  
Anna Sukhenko ◽  
Timur Bopeyev ◽  
...  
Keyword(s):  
Mathematical Model ◽  
Control System ◽  
Stability Analysis ◽  
Electric Motor ◽  
Attitude Control ◽  
Control Process ◽  
Control Voltage ◽  
Control Law ◽  
Attitude Control System ◽  
Technical Specifications

The problem of development of the microsatellite attitude control system on the base of reaction wheels positioned along its principal central axes of inertia is considered in this article. As difference from the classical mathematical models describing the microsatellite motion, this article includes the mathematical model of reaction wheel which is controlled by the input voltage of the electric motor. PD-controller is used as the basis for the development of the control law for microsatellite attitude. The stability analysis of the microsatellite attitude control process was carried out with the help of Lyapunov function method. This analysis allowed to prove that obtained attitude control law provides the asymptotic stability of the microsatellite rotational motion. Further, the function of control voltage for the reaction wheel’s electric motor with account of its technical specifications was obtained based on the derived mathematical model of the reaction wheel’s dynamics. The results of performed simulation showed the effectiveness of developed control. Obtained results of the study provide a base for the use of presented approach to the development of attitude control system for microsatellites with various missions.

scholarly journals Design of Attitude Control System for UAV Based on Feedback Linearization and Adaptive Control

2014 ◽  
Vol 2014 ◽  
pp. 1-8 ◽  
Author(s):  
Wenya Zhou ◽  
Kuilong Yin ◽  
Rui Wang ◽  
Yue-E Wang
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Attitude Control ◽  
Feedback Linearization ◽  
Control Law ◽  
Attitude Control System ◽  
Model Uncertainties ◽  
Performance Indexes ◽  
Attitude Dynamic ◽  
Adaptive Control Law

Attitude dynamic model of unmanned aerial vehicles (UAVs) is multi-input multioutput (MIMO), strong coupling, and nonlinear. Model uncertainties and external gust disturbances should be considered during designing the attitude control system for UAVs. In this paper, feedback linearization and model reference adaptive control (MRAC) are integrated to design the attitude control system for a fixed wing UAV. First of all, the complicated attitude dynamic model is decoupled into three single-input single-output (SISO) channels by input-output feedback linearization. Secondly, the reference models are determined, respectively, according to the performance indexes of each channel. Subsequently, the adaptive control law is obtained using MRAC theory. In order to demonstrate the performance of attitude control system, the adaptive control law and the proportional-integral-derivative (PID) control law are, respectively, used in the coupling nonlinear simulation model. Simulation results indicate that the system performance indexes including maximum overshoot, settling time (2% error range), and rise time obtained by MRAC are better than those by PID. Moreover, MRAC system has stronger robustness with respect to the model uncertainties and gust disturbance.

The Optimal Attitude Controller Design and Simulation of Three-Axis Dual Rotor Helicopter

2011 ◽  
Vol 128-129 ◽  
pp. 1265-1268 ◽  
Author(s):  
Cai Zheng Xu ◽  
Ting Zhang
Keyword(s):  
Optimal Control ◽  
Attitude Control ◽  
Control Algorithm ◽  
Controller Design ◽  
Dead Zone ◽  
Control Law ◽  
Attitude Control System ◽  
Environment Simulation ◽  
Attitude Controller ◽  
Time And Energy

In this paper, the model of three-axis dual rotor helicopter is built, through a new motor control algorithm of real-time grouping, the decoupling and independent control of pitch, yaw and roll channels is realized; then the “dead zone” is introduced to design the attitude controller on the basis of the optimal control law which minimize the weighted sum of response time and energy consumption, to achieve optimal control of the attitude of the helicopter; finally, the simulation model of the attitude control system is established in the MATLAB/Simulink environment. Simulation results show the feasibility of the optimal attitude controller design.

A Variable Structure Attitude Control System Design Based on Finite Time Stability

2013 ◽  
Vol 446-447 ◽  
pp. 1141-1145
Author(s):  
Rui Min Jiang ◽  
Jun Zhou ◽  
Jian Guo Guo
Keyword(s):  
Control System ◽  
Finite Time ◽  
Attitude Control ◽  
Angular Rate ◽  
Variable Structure ◽  
Control System Design ◽  
Control Loop ◽  
Time Stability ◽  
Attitude Control System ◽  
Finite Time Stability

A variable structure attitude control system design method that guarantees the finite-time stability is proposed for hypersonic vehicle attitude control. According to the characteristics of the hypersonic vehicle longitudinal attitude model, it is considered to comprise attack angle control loop and angular rate control loop. The attack angle controller and pitch angular rate controller based on variable structure control are designed respectively which ensure the finite-time stability. The finite-time stability of the whole attitude control system has been proved .The simulation results illustrated that the proposed attitude controller has good rapidity and robustness.

Modeling and Attitude Control of a Spinning Spacecraft with Internal Moving Mass

2013 ◽  
Vol 760-762 ◽  
pp. 1216-1220 ◽  
Author(s):  
Peng Fei Guo ◽  
Liang Yu Zhao
Keyword(s):  
Nonlinear Dynamics ◽  
Control System ◽  
Attitude Control ◽  
Linear Quadratic Regulator ◽  
Control Law ◽  
Moving Mass ◽  
Newtonian Mechanics ◽  
Attitude Control System ◽  
Linear Quadratic ◽  
The Mathematical Model

An attitude control system of a spinning spacecraft with internal moving mass is presented in this paper. This system consists of a rigid body and two internal radial moving masses. The mathematical model, including attitude kinematics and nonlinear dynamics equations, is established based on Newtonian mechanics. The control law is designed based on the linear-quadratic-regulator (LQR) theory. The performance of the controller is demonstrated in numerical simulation, and the response shows that the attitude control system is stable and effective.

scholarly journals Modelling the attitude dynamics of small spacecraft with a magnetic attitude control system in three-axis stabilization mode

2019 ◽  
Vol 488 (4) ◽  
pp. 377-382
Author(s):  
V. M. Kulkov ◽  
Yu. G. Egorov ◽  
S. O. Firsyuk ◽  
V. V. Terentyev ◽  
A. O. Shemyakov
Keyword(s):  
Magnetic Field ◽  
Mathematical Model ◽  
Control System ◽  
Attitude Control ◽  
Control Law ◽  
Attitude Dynamics ◽  
Attitude Control System ◽  
Small Spacecraft ◽  
Magnetic Attitude Control ◽  
System Movement

The problem of modeling the attitude-control modes of small spacecraft with the use of electromagnetic systems, interacting with the Earths magnetic field is considered. A small spacecraft angular motion mathematical model is developed. A control law for magnetic attitude control system of small spacecraft is formulated. Results of satellite with magnetic attitude control system movement numerical modelling are presented.

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