Attitude control of a rigid spacecraft with two momentum wheel actuators using genetic algorithm

Abstract-This paper describes the design, fabrication, characterization, and satellite integration of a miniaturized two axis sun sensor which has been used in the attitude control system of the Spanish nano-satellite NANOSAT-1B. This device is made of four silicon photodiodes monolithically integrated in a crystalline silicon substrate, protected by a transparent cover glass assembled on the same silicon die against space radiation damage. The sensor fabrication combines standard silicon processing technology with a high performance solar cell fabrication process. The sensor, including electronics and mechanical and electrical interfacing with the satellite, has a small size (3 cm 3 cm) and low weight (24 gr.), with a sun field-of-view greater than 60 with an angle accuracy better than 0.15 . Three of these sensors have already been integrated in the NANOSAT-1B platform that has been successfully launched in July 2009. Index Terms-Angle measurement, cover glass, field-of-view (FOV), satellite attitude control, silicon photodiodes, sun sensor.

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“…1(a). The FOV is restricted in a cone of , and therefore, using basics trigonometry, angles and must satisfy (1) (1)…”

Section: A Conceptmentioning

confidence: 99%

“…actuators [1]- [4]. Gyroscopes, horizon earth detectors, magnetometers, earth gravity sensors, infrared earth radiation detection, or star trackers are commonly used as attitude sensors [5]- [7].…”

mentioning

confidence: 99%

A Miniaturized Two Axis Sun Sensor for Attitude Control of Nano-Satellites

et al. 2010

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“…The total angular momentum vector of the system is given, in the spacecraft body frame, by [12] R(θ,ψ,φ)H = Jω…”

Section: Models Of a Spacecraft Systemsmentioning

confidence: 99%

“…Therefore the vectors b 1 and b 2 are given by b 1 = {1, 0, 0} T , b 2 = {0, 1, 0} T . The mass and geometry parameters of the spacecraft with two momentum wheels are chosen as follows [12] The attitude motions of a rigid spacecraft with two momentum wheels from the initial configuration to the final configuration are chosen as…”

Section: Numerical Simulationmentioning

confidence: 99%

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Optimal motion planning for a rigid spacecraft with two momentum wheels using quasi-Newton method

Zhang

Chen

2006

Acta Mech. Solida Sin.

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An optimal motion planning scheme based on the quasi-Newton method is proposed for a rigid spacecraft with two momentum wheels. A cost functional is introduced to incorporate the control energy, the final state errors and the constraints on states. The motion planning for determining control inputs to minimize the cost functional is formulated as a nonlinear optimal control problem. Using the control parametrization, one can transform the infinite dimensional optimal control problem to a finite dimensional one that is solved via the quasi-Newton methods for a feasible trajectory which satisfies the nonholonomic constraint. The optimal motion planning scheme was applied to a rigid spacecraft with two momentum wheels. The simulation results show the effectiveness of the proposed optimal motion planning scheme.

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Optimal control of a spacecraft with deployable solar arrays using particle swarm optimization algorithm

Sun

2011

Sci. China Technol. Sci.

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The optimal control problem of the multibody dynamics of a spacecraft in space, modeled as a central body with one-sided connected deployable solar arrays, is investigated. The dynamical equations of motion of the spacecraft with solar arrays are derived using the multibody dynamics method. The control of the attitude motion of a spacecraft system can be transformed into the motion planning problem of nonholonomic system when the initial angular momentum is zero. These are then used to investigate the motion planning of the spacecraft during solar arrays deployment via particle swarm optimization (PSO) and results are obtained with the optimal control input and the optimal trajectory. The results of numerical simulation show that this approach is effective for the control problem of the attitude of a spacecraft during the deployment process of its solar arrays. multibody spacecraft, attitude dynamics, optimal control, particle swarm optimization Citation:Ge X S, Sun K. Optimal control of a spacecraft with deployable solar arrays using particle swarm optimization algorithm.

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Attitude control of a rigid spacecraft with two momentum wheel actuators using genetic algorithm

Cited by 41 publications

References 9 publications

A Miniaturized Two Axis Sun Sensor for Attitude Control of Nano-Satellites

A Miniaturized Two Axis Sun Sensor for Attitude Control of Nano-Satellites

Optimal motion planning for a rigid spacecraft with two momentum wheels using quasi-Newton method

Optimal control of a spacecraft with deployable solar arrays using particle swarm optimization algorithm

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