scholarly journals Sun-Pointing Attitude Control Scheme for Magnetic-based Satellite

2021 ◽  
Author(s):  
Xiwang Xia ◽  
Yonghe ZHANG ◽  
Jun Jiang
Keyword(s):  
Attitude Control ◽  
Attitude Determination ◽  
Direct Method ◽  
Low Cost ◽  
Solar Array ◽  
Solar Panels ◽  
Control Effort ◽  
Control Scheme ◽  
Control Schemes ◽  
Magnetic Attitude Control

Abstract For some low-orbit satellites, SADA (solar array drive assembly) is not necessary but steady sun-pointing is required. Magnetic-based attitude control schemes are adopted by more and more low-cost low-orbit satellites and magnetic-based sunpointing attitude control schemes have been proposed for various satellites. For magnetic Attitude Determination and Control System (ADCS), magnetometer and magnetic torquer are the core ADCS components while sun sensor and gyro, which would be employed to determine or estimate sun vector, are important ones. Due to the underactuated characteristics, magnetic attitude control torque could not stabilize the full attitude but the two components of the attitude, simultaneously, which means that magnetic attitude control effort could orientate the solar panels to the Sun. A Lyapunov function, combining the rotational energy and sun angle, is formulated and a PD-type sun-pointing attitude control scheme is proposed to meet the requirements corresponding to sun-pointing task. Further, the effectiveness of the PD-type sun angle-based magnetic attitude control scheme, composed of proportional term, damping term and spinning term, has been verified by use of Lyapunov direct method. Simulations show that, the proposed PD-type attitude control scheme is a suitable sun-pointing scheme for magnetic satellites.

Adaptive fuzzy Jacobian control of spacecraft combined attitude and Sun tracking system

2020 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Yew-Chung Chak ◽  
Renuganth Varatharajoo ◽  
Nima Assadian
Keyword(s):  
Attitude Control ◽  
Tracking System ◽  
Solar Array ◽  
The Sun ◽  
Solar Panels ◽  
Content Type ◽  
Adaptive Fuzzy ◽  
Control Scheme ◽  
Adaptation Law ◽  
Pointing Control

Purpose The paper aims to address the combined attitude control and Sun tracking problem in a flexible spacecraft in the presence of external and internal disturbances. The attitude stabilization of a flexible satellite is generally a challenging control problem, because of the facts that satellite kinematic and dynamic equations are inherently nonlinear, the rigid–flexible coupling dynamical effect, as well as the uncertainty that arises from the effect of actuator anomalies. Design/methodology/approach To deal with these issues in the combined attitude and Sun tracking system, a novel control scheme is proposed based on the adaptive fuzzy Jacobian approach. The augmented spacecraft model is then analyzed and the Lyapunov-based backstepping method is applied to develop a nonlinear three-axis attitude pointing control law and the adaptation law. Findings Numerical results show the effectiveness of the proposed adaptive control scheme in simultaneously tracking the desired attitude and the Sun. Practical implications Reaction wheels are commonly used in many spacecraft systems for the three-axis attitude control by delivering precise torques. If a reaction wheel suffers from an irreversible mechanical breakdown, then it is likely going to interrupt the mission, or even leading to a catastrophic loss. The pitch-axis mounted solar array drive assemblies (SADAs) can be exploited to anticipate such situation to generate a differential torque. As the solar panels are rotated by the SADAs to be orientated relative to the Sun, the pitch-axis wheel control torque demand can be compensated by the differential torque. Originality/value The proposed Jacobian control scheme is inspired by the knowledge of Jacobian matrix in the trajectory tracking of robotic manipulators.

Design of GA-Based Control for Electrical Servo Drive

2011 ◽  
Vol 201-203 ◽  
pp. 2375-2378
Author(s):  
Kuo Ho Su ◽  
Feng Hsiang Hsiao
Keyword(s):  
Genetic Algorithm ◽  
Gradient Descent ◽  
Nonlinear Dynamical System ◽  
Servo Drive ◽  
Control Effort ◽  
Nonlinear Dynamical ◽  
Supervisory Controller ◽  
Control Scheme ◽  
Control Schemes ◽  
System States

An alternative control scheme including a directional genetic algorithm controller (DGAC) and a supervisory controller is developed to control the position of an electrical servo drive in this study. In the DGAC design, the spirit of gradient descent training is embedded in genetic algorithm (GA) to construct a main controller to search optimum control effort under possible occurrence of uncertainties. In order to ensure the system states around a defined bound region, a supervisory controller, which is derived in the sense of Lyapunov stability theorem, is added to adjust the control effort. Compared with enunciated GA control methods, the proposed control scheme possesses some salient advantages of simple framework, fewer executing time and good self-organizing properties even for nonlinear dynamical system. The effectiveness is demonstrated by simulation results, and its advantages are indicated in comparison with other GA control schemes for a field-oriented control induction motor drive.

Path following control for a stratospheric airship with actuator saturation

2016 ◽  
Vol 39 (7) ◽  
pp. 987-999 ◽  
Author(s):  
Zewei Zheng ◽  
Keyu Yan ◽  
Shuaixian Yu ◽  
Bing Zhu ◽  
Ming Zhu
Keyword(s):  
Attitude Control ◽  
Closed Loop ◽  
Actuator Saturation ◽  
Path Following ◽  
Stratospheric Airship ◽  
Closed Loop Systems ◽  
Path Following Control ◽  
Control Scheme ◽  
Control Schemes ◽  
Guidance Laws

This paper proposes two different path following control schemes for a stratospheric airship with actuator saturation. Each of the control schemes consists of a guidance loop and an attitude control loop. In both schemes, guidance laws are designed according to the line-of-sight guidance-based path following principle. In the first control scheme, a robust H∞ controller without constraints is designed based on the planar model of a stratospheric airship to stabilize path-following errors. The input constraints are then addressed by using a regional [Formula: see text]-based model recovery anti-windup compensator, which prevents the unconstrained controller from misbehaving in the constrained closed loop with anti-windup augmentation and ensures the systematic stability. In the second control scheme, model predictive control is applied to guarantee the path-following of the closed-loop system and explicitly address the magnitude and rate of rudders of the stratospheric airship. Theoretical results are illustrated by numerical simulations where both closed-loop systems are capable of following their desired paths and the constraints on control inputs are satisfied.

MiniCarb: A Passive, Occultation-Viewing, 6U CubeSat for Observations of CO2, CH4, and H2O

2021 ◽  
Author(s):  
Emily L Wilson ◽  
Vincent J. Riot ◽  
A. J. DiGregorio ◽  
guruthisvaran Ramu ◽  
Paul Cleveland ◽  
...  
Keyword(s):  
Attitude Control ◽  
Low Cost ◽  
Lawrence Livermore National Laboratory ◽  
National Laboratory ◽  
Space Station ◽  
Solar Panels ◽  
Attitude Control System ◽  
Environmental Testing ◽  
Nasa Goddard Space ◽  
Modular Platform

Abstract We present the final design, environmental testing, and launch history of MiniCarb, a 6U CubeSat developed through a partnership between NASA Goddard Space Flight Center and Lawrence Livermore National Laboratory. MiniCarb’s science payload, developed at Goddard, was an occultation-viewing, passive laser heterodyne radiometer for observing methane, carbon dioxide, and water vapor in Earth’s atmosphere at ~1.6 microns. MiniCarb’s satellite, developed at Livermore, implemented their CubeSat Next Generation Bus plug-and-play architecture to produce a modular platform that could be tailored to a range of science payloads. Following the launch on December 5, 2019, MiniCarb traveled to the International Space Station and was set into orbit on February 1, 2020 via Northrop Grumman’s (NG) Cygnus capsule which deployed MiniCarb with tipoff rotation of about 20 deg/sec (significantly higher than the typical rate of 3 deg/sec from prior CubeSats), from which the attitude control system was unable to recover resulting in a loss of power. In spite of this early failure, MiniCarb had many successes including rigorous environmental testing, successful deployment of its solar panels, and a successful test of the radio and communication through the Iridium network. This prior work and enticing cost (approximately $2M for the satellite and $250K for the payload) makes MiniCarb an ideal candidate for a low-cost and rapid rebuild as a single orbiter or constellation to globally observe key greenhouse gases.

Design and Simulation of Attitude Determination and Control Subsystem of CubeSat Using Extended Kalman Filtering and Linear Quadratic Gain Controller

2013 ◽  
Vol 694-697 ◽  
pp. 1582-1586
Author(s):  
Xiao Han ◽  
Xiao Jun Yang ◽  
Naqvi Najam Abbas
Keyword(s):  
Attitude Control ◽  
Attitude Determination ◽  
Low Cost ◽  
Linear Quadratic ◽  
Extended Kalman Filtering ◽  
Position Information ◽  
Control Subsystem ◽  
Linear Quadratic Regulation ◽  
Integral Scheme ◽  
And Control

This paper describes an integral scheme of the design and simulation of the Attitude Determination and Control Subsystem (ADCS) of CubeSat. CubeSat is an educational low-cost, cube-shaped Pico spacecraft. Attitude Determination (AD) is the problem of expressing the orientation of a spacecraft with respect to a given coordinate system. Three axis magneto-resistive digital magnetometer is selected as an attitude sensor. The International Geomagnetic Reference Field (IGRF) is used as reference for magnetometer to obtain attitude information. An enhanced orbit estimate/propagator is implemented to provide position information to IGRF model. Satellite environmental torque is modeled along with satellite kinematics and dynamics. Attitude estimation is done using Extended Kalman Filter (EKF) while the magnetic coils are used as actuators. Attitude Control is applied using Linear Quadratic Regulation (LQR) Controller. The designed ADCS is implemented in Matlab/Simulink.

Back-Stepping Adaptive Attitude Control of Over-Actuated Spacecraft

2013 ◽  
Vol 712-715 ◽  
pp. 2783-2786
Author(s):  
Hui Fang ◽  
Jun Hui Gong
Keyword(s):  
Attitude Control ◽  
Lyapunov Functions ◽  
Adaptive Controller ◽  
Attitude Maneuver ◽  
Control Scheme ◽  
Control Schemes ◽  
Rigid Spacecraft ◽  
Robust Adaptive ◽  
Back Stepping Control ◽  
Robust Adaptive Controller

A novel robust adaptive back-stepping control scheme for attitude maneuver of over-actuated spacecraft system with redundant reaction fly-wheels (RWs) is proposed. The robust adaptive controller based on back-stepping may achieve the high accuracy and speed of the attitude control for the rigid spacecraft with uncertain inertia matrix and bounded external disturbs. The Lyapunov functions are employed to analyze and prove the systems stability, so the fine and accuracy performances are ensured. The numerical simulation results verify the effectiveness and feasibility of the control schemes derived here using the MATLAB/SIMULINK software.

scholarly journals Decentralized Control for Scalable Quadcopter Formations

2016 ◽  
Vol 2016 ◽  
pp. 1-10
Author(s):  
Qasim Ali ◽  
Sergio Montenegro
Keyword(s):  
Position Control ◽  
Linear Quadratic Regulator ◽  
Linear Quadratic ◽  
Time Duration ◽  
Control Effort ◽  
Ground Station ◽  
Model Following ◽  
Control Scheme ◽  
Control Schemes ◽  
And Control

An innovative framework has been developed for teamwork of two quadcopter formations, each having its specified formation geometry, assigned task, and matching control scheme. Position control for quadcopters in one of the formations has been implemented through a Linear Quadratic Regulator Proportional Integral (LQR PI) control scheme based on explicit model following scheme. Quadcopters in the other formation are controlled through LQR PI servomechanism control scheme. These two control schemes are compared in terms of their performance and control effort. Both formations are commanded by respective ground stations through virtual leaders. Quadcopters in formations are able to track desired trajectories as well as hovering at desired points for selected time duration. In case of communication loss between ground station and any of the quadcopters, the neighboring quadcopter provides the command data, received from the ground station, to the affected unit. Proposed control schemes have been validated through extensive simulations using MATLAB®/Simulink® that provided favorable results.

Sign in / Sign up

Export Citation Format

Share Document