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1 
Hybrid Magnetic Attitude Controller for Low Earth Orbit Satellites using the Timevarying Linear Quadratic RegulatorSeth, Nitin 22 September 2009 (has links)
The following is a study of an attitude control system (ACS) for a low earth orbit
nanosatellite. Control actuation is applied using three reaction wheels and three mutually
orthogonal currentdriven magnetorquers which produce torques by interacting
with the earth’s magnetic field. Control torques are distributed amongst the actuators
allowing them to work together in concert. This type of control is referred to as hybrid
magnetic attitude control. To account for the nearly periodic behavior of the earth’s
magnetic field, control torques are assigned using periodic and optimal control theory.
The primary focus is to apply the timevarying Linear Quadratic Regulator controller to
test the stability and energy consumption of the ACS when reaction wheels are removed
from the control law, or are simulated to be missing. Other situations studied include
the effects of control saturation, introducing uncertainty in the orbital inclination, and
observing performance as the number of magnetic coils is increased.

2 
Hybrid Magnetic Attitude Controller for Low Earth Orbit Satellites using the Timevarying Linear Quadratic RegulatorSeth, Nitin 22 September 2009 (has links)
The following is a study of an attitude control system (ACS) for a low earth orbit
nanosatellite. Control actuation is applied using three reaction wheels and three mutually
orthogonal currentdriven magnetorquers which produce torques by interacting
with the earth’s magnetic field. Control torques are distributed amongst the actuators
allowing them to work together in concert. This type of control is referred to as hybrid
magnetic attitude control. To account for the nearly periodic behavior of the earth’s
magnetic field, control torques are assigned using periodic and optimal control theory.
The primary focus is to apply the timevarying Linear Quadratic Regulator controller to
test the stability and energy consumption of the ACS when reaction wheels are removed
from the control law, or are simulated to be missing. Other situations studied include
the effects of control saturation, introducing uncertainty in the orbital inclination, and
observing performance as the number of magnetic coils is increased.

3 
Performance characterization of the attitude control system for the GRACE missionBenegalrao, Suyog Suresh, 1986 29 October 2012 (has links)
The Gravity Recovery and Climate Experiment (GRACE) mission is a breakthrough Earth science mission launched in the spring of 2002 that uses satellitetosatellite tracking (SST) to map the Earth gravity field. In this framework, the nonuniform gravity distribution is inferred using the range change experienced between two satellites. The range change is measured using a microwave Kband ranging system, and nongravitational forces are accounted for using accelerometer (ACC) data. The vectoroffset between the satellite center of mass (CM) and the Kband phase center represents the correction between measured and modeled ranging data. In addition, the offset between the satellite CM and the ACC proofmass multiplies the attitude angles, rates, and jitter which in turn add spurious signals to the ACC output. For both of these reasons, proper knowledge and control of attitude behavior is vital to successful mission performance. An examination of the GRACE attitude control system (ACS) is presented in this study.
The GRACE ACS system is composed of a PD control law, star camera sensing as the knowledge source, coldgas thrusters as primary actuators, and magnetic torque rods as supplementary actuators. The dependencies inherent in the ACS are inferred using a sensitivity analysis performed on a simulation model of the GRACE science mode ACS. The results from this sensitivity study are applicable to the general controller class of which the GRACE ACS system is an exemplar.
In this study, the modeled attitude data quality is most sensitive to star camera measurement noise. It is hypothesized that this is because star cameras are used as the sole knowledge source in the ACS scheme. In contrast, the experimental results associated with magnetometer, thruster, and magnetic torque rod perturbations did not significantly affect attitude quality. However, these perturbations do cause thruster activity to significantly magnify. This results in higher attitude acceleration PSD for the frequency band in which timevariable gravity components are captured. A number of future experiments can be performed to improve both attitude quality performance and frequencybased magnifications. Examples include sensor fusion studies, reaction wheel versus thruster assessment, and gravity field estimation sensitivity in response to attitude quality degradation. / text

4 
On the librational dynamics of damped satellitesTschann, Christian Aime January 1970 (has links)
The thesis examines diverse methods of damping the librational motion of earthorbiting satellites. Starting with passive stabilization, two classical mechanisms for energy dissipation are studied, for performance comparison, when executing librations in the orbital plane. The first model, consisting of a sliding mass restricted to relative translational motion with respect to the main satellite body, establishes the suitability of various approaches to the problem in circular orbit. In this case, numerical and analog methods do not readily yield information on the influence of parameters and approximate methods are found to be particularly helpful. Butenin's method based on averaging techniques predicts the response of the satellite with good accuracy for small damping constant while the exact solution to the linearized equations provides optimum damper characteristics for motion in the small. A comparison of the sliding mass damper model with a damper boom mechanism involving only relative rotational displacements, is then performed for equal equilibrium inertias of the damping devices. It indicates that, for optimum transient tuning, the damper boom would have a better timeindex while the sliding mass would lead to smaller steadystate amplitudes for low eccentricity orbits. A numerical example using GEOSA satellite data illustrates the outcome of the study when applied to physical situations. A stability analysis is also included which uses Routh and Lyapunov approaches to determine the domain of parameters leading to asymptotic stability, as well as numerical methods to define the bounds on stable initial disturbances: it is found that for most practical applications, the stability contour in circular orbit is close to that of the undamped case. However, for eccentric trajectory, the amount of damping critically affects asymptotic stability.
The next model, which involves active stabilization, uses solar radiation pressure to achieve planar librational control of a satellite orbiting in the plane of the ecliptic. This is obtained by adjusting the position of the center of pressure with respect to the center of mass through a controller depending on a linear combination of librational velocity and displacement. The motion in circular orbit is; first investigated through the W.K.B. method. Although the approximate equation involves an infinity of turning points, only a few of them are required to evaluate the damped behaviour of the system. A comparison of the analytical results with a numerical integration of the exact equation of motion shows good agreement only over a limited range of parameters and, therefore, the latter is used to complete the study for circular and elliptic cases. The concept leads to great versatility in positioning a satellite at any angle with respect to the local vertical. Also, high transient ; performance is observed about local vertical and horizontal and the dichotomous property of good transient associated with poor steadystate inherent to passive damping can be avoided by selecting appropriate controller parameters. An example is included which substantiates the feasibility of the configuration.
Finally, the attention is directed towards the influence of gravity torques on the stability of damped axisymmetric dualspin satellites. The nutation damper mounted on the slowlyspinning section is of the pendulum type. For this section rotating at orbital angular rate, application of the KelvinTaitChetaev theorem indicates that the asymptotic stability region reduces basically to the mainly positive stable spin region of the undamped case. However, some care is required depending upon the shape and natural frequency of the damper. If the damper section rotates at a much higher rate than the orbital one, torquefree motion need only be considered for short term predictions. Stability charts corresponding to this case, given for comparison, emphasize the effect of gravity. / Applied Science, Faculty of / Mechanical Engineering, Department of / Graduate

5 
Attitude control of spinning satellites using environmental forcesPande, Kailash Chandra January 1973 (has links)
The feasibility of utilizing the environmental forces for threeaxis librational damping and attitude control of spinning satellites is investigated in detail. An appreciation of the environmental influence is first gained through a librational dynamics study of spinning, axisymmetric, cylindrical satellites in the solar radiation pressure field. The highly nonlinear, nonautonomous, coupled equations of motion are analyzed approximately using the method of variation of parameters. The closed form solution proves to be quite useful in locating periodic solutions and resonance characteristics of the system. A numerical parametric analysis, involving large amplitude motion, establishes the effect of the radiation pressure to be substantial and destabilizing. Next, a possibility of utilizing this adverse influence to advantage through judiciously located rotatable control surfaces is explored. A controller configuration for a dualspin spacecraft is analyzed first. The governing
equations, in the absence of a known exact solution, are solved numerically to evaluate the effect of system parameters on the performance of the control system. The available control moments are found to be sufficient to
compensate for the rotor spin decay, thus dispensing with the necessity of energy sources maintaining the spin rate. The controller is able to damp extremely severe disturbances in a fraction of an orbit and is capable of imparting arbitrary orientations to a satellite, thus permitting it to undertake diverse missions. The development of an efficient yet structurally simple controller configuration is then considered. A logical approach for solar controller design is proposed which suggests a fourplate configuration. Its performance in conjunction with a bangbang control law is studied in detail. The utilization of maximum available control moments leads to a substantial improvement of the damping characteristics. Attention is then focussed on using the earth's magnetic field interaction with onboard dipoles for attitude control. Magnetic torquing, however, is unable to provide first order pitch control in near equatorial orbital planes. The shortcoming is overcome by hybridizing the concepts of magnetic and solar control. Two magnetic controller models, employing a single rotatable dipole or two fixed dipoles, are proposed in conjunction with a solar pitch controller. The system performance is evaluated for a wide range of system parameters and initial conditions. Although high spin rates lend considerable gyroscopic stiffness to the
spacecraft, the controllers continue to be quite effective even in the absence of any spin. Even with extremely severe disturbances, damping times of the order of a few orbital degrees are attainable. As before, the concept enables a satellite to change the desired attitude in orbit. The effectiveness of the controllers at high altitudes having been established, the next logical step was to extend the analysis to nearearth satellites in free molecular environment. A hybrid control system, using the solar pressure at high altitudes and the aerodynamic forces near perigee, is proposed. The influence of important system parameters on the bangbang operation of the controller is analyzed. The concept appears to be quite effective in damping the satellite librations. Both the orbit normal and the local vertical orientations of the axis of symmetry of the satellite are attainable. However, for arbitrary pointing of the symmetry axis, small limit cycle oscillation about the desired final orientation results. Finally, the timeoptimal control, through solar radiation pressure, of an unsymmetrical satellite executing planar pitch librations is examined analytically. The switching criterion, synthesized for the linear case, is found to be quite accurate even when the system is subjected to large disturbances.
Throughout, the semipassive character of the system promises an increased lifespan for a satellite. / Applied Science, Faculty of / Mechanical Engineering, Department of / Graduate

6 
In orbit calibration of satellite inertia matrix and thruster coefficientsElBordany, Refaat January 2001 (has links)
In this research study, several new inorbit algorithms are proposed to improve the performance of Attitude Determination and Control System (ADCS) by estimating the inertia matrix and calibrating the cold gas thruster system of the UoSAT12 spacecraft. Computerbased simulation models will be constructed using MATLAB and SIMULINK in order to evaluate the expected performance. The first focus is on the identification of the satellite inertia matrix. A new algorithm based on a Recursive Least Square (RLS) estimation technique is proposed for inorbit use to estimate the inertia matrix (moments and products of inertia parameters) of a satellite. To facilitate this, one attitude axis is disturbed using a reaction wheel whilst the other two axes are controlled to keep their respective angular" rates small. Within a fraction of an orbit three components of the inertia matrix can be accurately determined. This procedure is then repeated for the other two axes to obtain all nine elements of the inertia matrix. The procedure is designed to prevent the build up of momentum in the reaction wheels, whilst keeping the attitude disturbance to the satellite within acceptable limits. It can also overcome potential errors introduced by unmodeled external disturbance torques and attitude sensor noise. The second focus is on a new algorithm for inorbit use to calibrate thruster coefficients for thrust level and alignment, using three reaction wheel actuators. These algorithms will ensure robustness against modeling errors. The algorithms assume no prior knowledge of the thruster parameters and only an initial guess of the inertia matrix. It is proposed that this calibration can be used during normal mission conditions when the satellite is stabilised. The final goal of this research study was to apply the proposed algorithms in realtime. Firstly, the thruster calibration algorithm was tested on an airbearing table. Finally, both thruster calibration and moment of inertia algorithms were tested using data generated by UoSAT12 while in orbit. The practical estimation results proved the feasibility of proposed algorithms.

7 
Investigation of Active Vibration Suppression of a Flexible Satellite using Magnetic Attitude ControlFindlay, Everett 07 December 2011 (has links)
The problem of attitude control of a flexible satellite using magnetic attitude control is investigated. The work is motivated by JC2Sat  a joint CSA and JAXA mission whose main purpose is a proof of concept of two satellites performing differential drag formation flying. The impact of additional flexible drag panels (of various sizes) on the attitude control is assessed. JC2Sat's attitude control system consists of three perpendicular magnetorquers and one reaction/biasmomentum wheel. Four Linear Quadratic Regulator controllers are compared, ranging in complexity from being timeinvariant and assuming a rigid satellite, to being periodic and actively suppressing panel vibrations. These include the first controllers which use magnetic attitude control to actively suppress vibrations, and where the periodic vibration suppression controller is able to guarantee asymptotic stability of the linearized system. It was found that for larger panels, the controllers which actively suppressed the vibrations outperformed those that did not.

8 
Magnetic Attitude Control of Microsatellites In Geocentric OrbitsDutia, Jiten 18 March 2013 (has links)
Attitude control of spacecraft in low Earth orbits can be achieved by exploiting the torques generated by the geomagnetic field. Recent research has demonstrated that attitude stability of a spacecraft is possible using a linear combination of Euler parameters and angular velocity feedback. The research carried out in this thesis implements a hybrid scheme consisting of
magnetic control using onboard dipole moments and a threeaxis actuation scheme such as reaction wheels and thrusters. A stability analysis is formulated and analyzed using Floquet and Lyapunov stability theorems.

9 
Investigation of Active Vibration Suppression of a Flexible Satellite using Magnetic Attitude ControlFindlay, Everett 07 December 2011 (has links)
The problem of attitude control of a flexible satellite using magnetic attitude control is investigated. The work is motivated by JC2Sat  a joint CSA and JAXA mission whose main purpose is a proof of concept of two satellites performing differential drag formation flying. The impact of additional flexible drag panels (of various sizes) on the attitude control is assessed. JC2Sat's attitude control system consists of three perpendicular magnetorquers and one reaction/biasmomentum wheel. Four Linear Quadratic Regulator controllers are compared, ranging in complexity from being timeinvariant and assuming a rigid satellite, to being periodic and actively suppressing panel vibrations. These include the first controllers which use magnetic attitude control to actively suppress vibrations, and where the periodic vibration suppression controller is able to guarantee asymptotic stability of the linearized system. It was found that for larger panels, the controllers which actively suppressed the vibrations outperformed those that did not.

10 
Magnetic Attitude Control of Microsatellites In Geocentric OrbitsDutia, Jiten 18 March 2013 (has links)
Attitude control of spacecraft in low Earth orbits can be achieved by exploiting the torques generated by the geomagnetic field. Recent research has demonstrated that attitude stability of a spacecraft is possible using a linear combination of Euler parameters and angular velocity feedback. The research carried out in this thesis implements a hybrid scheme consisting of
magnetic control using onboard dipole moments and a threeaxis actuation scheme such as reaction wheels and thrusters. A stability analysis is formulated and analyzed using Floquet and Lyapunov stability theorems.

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