Attitude Control of a Flexible Solar Sail in Low Earth Orbit

2018 ◽  
Vol 41 (8) ◽  
pp. 1715-1730 ◽  
Author(s):  
Shahin Firuzi ◽  
Shengping Gong
Keyword(s):  
Attitude Control ◽  
Solar Sail ◽  
Low Earth Orbit ◽  
Earth Orbit

Two-timescale magnetic attitude control of Low-Earth-Orbit spacecraft

2021 ◽  
pp. 106884
Author(s):  
Giulio Avanzini ◽  
Emanuele L. de Angelis ◽  
Fabrizio Giulietti
Keyword(s):  
Attitude Control ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Magnetic Attitude Control

Near-Optimal Solar-Sail Orbit-Raising from Low Earth Orbit

2005 ◽  
Vol 42 (5) ◽  
pp. 954-958 ◽  
Author(s):  
Giovanni Mengali ◽  
Alessandro A. Quarta
Keyword(s):  
Solar Sail ◽  
Low Earth Orbit ◽  
Earth Orbit

scholarly journals Design And Analysis Of Attitude Control Algorithm For Low Earth Orbiting Satellite With Magnetic Torquer Concepts Using Non- Linear Unscented Kalman Filter

2018 ◽  
Vol 7 (2.18) ◽  
Author(s):  
RAJA MUNUSAMY ◽  
Ugur Guven ◽  
Om Prakash
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Unscented Kalman Filter ◽  
Euler Angle ◽  
Attitude Estimation ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Attitude Control System ◽  
Attitude Stabilization ◽  
Attitude Sensor

Attitude control system plays the important role for to maintain the satellite to desired orientation. To control the satellite it is necessary to do the attitude stabilization. Attitude stabilization achieved by Star sensor, sun sensor, Earth sensors. Attitude control is mainly used for antenna pointing accuracy, camera focus to earth surface and solar panel pointing toward sun. Due to tumbling effect satellite will rotate all the direction in the space. To maintain the orientation of the satellite it is necessary to design the attitude determination and control. Satellite consider as the rigid body. Inertia matrix describes the rigid body dynamics.  The orientation of the satellite determine by Euler angle and Quaternion. Low earth orbit satellite will have enormous amount of aerodynamic drag stinking the satellite body and gravitational attraction another problem. Because of that satellite dwell time is reduced. It means satellite more time spending particular part of the earth. The attitude estimation is measures by the orientation of vectors. Attitude estimation means to find the position and orientation of flying object with respect to the fixed reference of reference. Vector remains considered in the frame of reference to compute for find the orientation of the body of the satellite in the inertial reference system. Earth is an inertial reference frame, Satellite is a body frame. Attitude sensor used to measure the satellite orientation in the reference frame. This will help in accurately predicting the orbit deviation and a control system to correct if any by providing the satellite momentum means ‘mass in motion’ changes in a body rapidly in Low earth orbit due to centripetal force acting on a satellite. Attitude control system (ACS) need the numerical simulation to find the required torque demand by the help of difference between reference input (Attitude) signal and feedback signal measure by attitude sensor to trim the control surface maintain the actuator required orientation . The results will consist of two parts the first part consisting of the attitude estimation using Euler angle and Quaternion method, second part consist of estimate the control torque from magnetic torquer and error estimation using non-linear filter (Unscented Kalman Filter) with MATLAB simulation.

Three-axis attitude control by two-step rotations using only magnetic torquers in a low Earth orbit near the magnetic equator

2016 ◽  
Vol 128 ◽  
pp. 696-706 ◽  
Author(s):  
Takaya Inamori ◽  
Kensuke Otsuki ◽  
Yoshiki Sugawara ◽  
Phongsatorn Saisutjarit ◽  
Shinichi Nakasuka
Keyword(s):  
Attitude Control ◽  
Low Earth Orbit ◽  
Magnetic Equator ◽  
Earth Orbit

Thermally Induced Dynamic Response of a Stripped Solar Sail in Low Earth Orbit

2020 ◽  
Vol 57 (3) ◽  
pp. 621-627 ◽  
Author(s):  
Junhui Zhang ◽  
Na Wu ◽  
An Tong ◽  
Yinghua Liu
Keyword(s):  
Dynamic Response ◽  
Solar Sail ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Thermally Induced

The Holographic Solar Photon Thruster (SPT) : A Low-Earth Orbit Solar Sail

Solar Energy ◽  
2003 ◽  
Author(s):  
Gregory L. Matloff
Keyword(s):  
Solar Sail ◽  
Low Earth Orbit ◽  
Back Pressure ◽  
Orbital Energy ◽  
Earth Orbit ◽  
Atmospheric Drag ◽  
Net Radiation ◽  
Solar Sails ◽  
The Earth ◽  
Fixed Orientation

Atmospheric drag limits most solar sails to altitudes>1000 km. A two-sail variant, the Solar-Photon Thruster (SPT) , could be used in Low-Earth Orbit (LEO). An SPT has a fixed-orientation collector sail that focuses light against a smaller, adjustable thruster sail. Maintaining the collector surface parallel to the Earth minimizes SPT drag in LEO. To minimize solar-radiation back pressure towards Earth, the upper collector surface is non-reflective. The reflective lower collector surface directs light reflected and reradiated from the Earth against the thruster. Thruster orientation is adjusted in LEO to increase the orbital energy by the net radiation-pressure. Experiments reveal that holograms are tolerant to solar-wind radiation. SPTs with white-light holographic thrusters are useful in LEO because small thruster rotations produce greatly altered reflectivity. It may be possible to holographically combine SPT collector and thruster.

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