The Experts below are selected from a list of 294 Experts worldwide ranked by ideXlab platform
Colin R Mcinnes - One of the best experts on this subject based on the ideXlab platform.
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Passive Sorting of Asteroid Material Using Solar Radiation Pressure
Journal of Guidance Control and Dynamics, 2014Co-Authors: Daniel Garcia Yarnoz, J.p. Sanchez, Colin R McinnesAbstract:Understanding dust dynamics in the vicinity of asteroids is key for future science missions and, in the long-term, for asteroid exploitation. This paper analyzes the feasibility of manipulating asteroid material by means of Solar Radiation Pressure. A novel method is proposed for passively sorting material as a function of its grain size or density, where Solar Radiation Pressure is used as a passive in-situ "mass spectrometer". A simplified analysis shows that in principle this method allows an effective sorting of regolith material. This could have immediate applications for a sample return mission, and for industrial scale in-situ resource utilization to separate and concentrate regolith according to particle size or composition.
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Solar Radiation Pressure augmented deorbiting passive end of life disposal from high altitude orbits
Journal of Spacecraft and Rockets, 2013Co-Authors: Charlotte Lucking, Camilla Colombo, Colin R McinnesAbstract:A deorbiting strategy for small satellites is proposed that exploits the effect of Solar Radiation Pressure to increase the spacecraft orbit eccentricity so that the perigee falls below an altitude where atmospheric drag will cause the spacecraft orbit to naturally decay. This is achieved by fitting the spacecraft with an inflatable reflective balloon. Once this is fully deployed, the overall area-to-mass ratio of the spacecraft is increased; hence, Solar Radiation Pressure and aerodynamic drag have a greatly increased effect on the spacecraft orbit. An analytical model of the orbit evolution due to Solar Radiation Pressure and the J2 effect as a Hamiltonian system show the evolution of an initially circular orbit. The maximum reachable orbit eccentricity as a function of semimajor axis and area-to-mass ratio is found analytically for deorbiting from circular equatorial orbits of different altitudes. The analytical planar model is then adapted for sun-synchronous orbits. The model is validated numerically...
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orbital dynamics of high area to mass ratio spacecraft with j2 and Solar Radiation Pressure for novel earth observation and communication services
Acta Astronautica, 2012Co-Authors: Camilla Colombo, Charlotte Lucking, Colin R McinnesAbstract:This paper investigates the effect of planetary oblateness and Solar Radiation Pressure on the orbits of high area-to-mass spacecraft. A planar Hamiltonian model shows the existence of equilibrium orbits with the orbit apogee pointing towards or away from the Sun. These solutions are numerically continued to non-zero inclinations and considering the obliquity of the ecliptic plane relative to the equator. Quasi-frozen orbits are identified in eccentricity, inclination and the angle between the Sun-line and the orbit perigee. The long-term evolution of these orbits is then verified through numerical integration. A set of ‘heliotropic’ orbits with apogee pointing in the direction of the Sun is proposed for enhancing imaging and telecommunication on the day side of the Earth. The effects of J2 and Solar Radiation Pressure are exploited to obtain a passive rotation of the apsides line following the Sun; moreover the effect of Solar Radiation Pressure enables such orbits at higher eccentricities with respect to the J2 only case.
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orbital dynamics of high area to mass ratio spacecraft with j2 and Solar Radiation Pressure for novel earth observation and communication services
Acta Astronautica, 2012Co-Authors: Camilla Colombo, Charlotte Lucking, Colin R McinnesAbstract:This paper investigates the effect of planetary oblateness and Solar Radiation Pressure on the orbits of high area-to-mass spacecraft. A planar Hamiltonian model shows the existence of equilibrium orbits with the orbit apogee pointing towards or away from the Sun. These solutions are numerically continued to non-zero inclinations and considering the obliquity of the ecliptic plane relative to the equator. Quasi-frozen orbits are identified in eccentricity, inclination and the angle between the Sun-line and the orbit perigee. The long-term evolution of these orbits is then verified through numerical integration. A set of ‘heliotropic’ orbits with apogee pointing in the direction of the Sun is proposed for enhancing imaging and telecommunication on the day side of the Earth. The effects of J2 and Solar Radiation Pressure are exploited to obtain a passive rotation of the apsides line following the Sun; moreover the effect of Solar Radiation Pressure enables such orbits at higher eccentricities with respect to the J2 only case.
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Coupled orbit and attitude dynamics of a reconfigurable spacecraft with Solar Radiation Pressure
2012Co-Authors: Andreas Borggrafe, Matteo Ceriotti, Jeannette Heiligers, Colin R McinnesAbstract:This work investigates the orbital and attitude dynamics of future reconfigurable multi-panel Solar sails able to change their shape during a mission. This can be enabled either by changing the relative position of the individual panels, or by using articulated mechanisms and deployable, retractable and/or inflatable structures. Such a model introduces the concept of modular spacecraft of variable morphology to large gossamer spacecraft. However, this joint concept is complex in nature and requires equations for coupled orbit/attitude dynamics. Therefore, as a starting point, the system is modelled as a rigid-body dumbbell consisting of two tip masses connected by a rigid, massless panel. The system is subjected to a central gravitational force field under consideration of Solar Radiation Pressure forces. Therefore, we assign reflectivity coefficients to the tip masses and a high area-to-mass ratio. An analytical Hamiltonian approach is used to describe the planar motion of the system in Sun-centred Keplerian and non-Keplerian circular orbits. The stability and controllability of the system is enabled through changing the reflectivity coefficients, for example through the use of electro-chromic coating on its surface. The creation of artificial unstable equilibria of the system due to the presence of Solar Radiation Pressure and heteroclinic connections between the equilibria are investigated. We further derive a constraint for the Solar Radiation Pressure forces to maintain the system on a circular Sun-centred orbit. It is planned that the structure is eventually capable of reconfiguring between the equilibria by a minimum actuation effort.
Krishna Dev Kumar - One of the best experts on this subject based on the ideXlab platform.
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Multiple spacecraft formation reconfiguration using Solar Radiation Pressure
Acta Astronautica, 2014Co-Authors: Kamran Shahid, Krishna Dev KumarAbstract:Abstract In this paper the use of Solar Radiation Pressure for spacecraft formation reconfiguration at the L 2 Sun–Earth/Moon collinear libration point is presented. The system consisting of a leader and three follower spacecraft is considered. The leader spacecraft is assumed to be in a fixed halo trajectory and the follower spacecraft position relative to the leader satellite is controlled using two angles and area; these are varied based on a variable structure model reference adaptive control technique to achieve the desired formation reconfiguration. This approach ensures that all follower spacecraft complete the required maneuver in the same time. An intertially fixed circular trajectory, which is suitable for interferometer missions, is used in this paper. The stability of the proposed controller is established using Lyapunov theory. The performance of the proposed controller is tested through numerical simulation of the governing nonlinear equations of motion and is applied for formation initialization, resizing, retargeting, and rotation. The numerical results demonstrate the effectiveness of the proposed control technique for spacecraft formation reconfiguration using Solar Radiation Pressure at the L 2 libration point. Furthermore, control inputs on the order of 15 degrees and 2 m 2 for area change are sufficient to execute the maneuvers.
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Multiple Satellite Formation Flying using Differential Solar Radiation Pressure
AIAA AAS Astrodynamics Specialist Conference, 2010Co-Authors: Surjit Varma, Krishna Dev KumarAbstract:*† In this paper we propose the use of differential Solar Radiation Pressure for multiple satellite formation flying. The nonlinear dynamics describing the motion of the follower satellite relative to the leader satellite is considered for the case where the leader satellite is in an unperturbed reference orbit, and the stability of such a formation in the presence of external perturbations is investigated. Several cases are considered to examine the performance of the proposed control strategy to maintain the relative motion of the follower satellites by correcting for any initial offset errors and external perturbation effects that tend to disturb the formation system. Numerical simulation results confirm that the suggested methodology using differential Solar Radiation Pressure yields reasonable formation keeping precision and its effectiveness in ensuring formation maneuvering .
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Formation Control at the Sun-Earth L2 Libration Point Using Solar Radiation Pressure
Journal of Spacecraft and Rockets, 2010Co-Authors: Kamran Shahid, Krishna Dev KumarAbstract:In this paper the use of Solar Radiation Pressure for spacecraft formation flying at theL2 sun–Earth/moon collinear libration point is presented. The system consisting of a leader and a follower satellite is considered. The leader satellite is assumed to be in a fixed halo trajectory and the follower satellite position relative to the leader satellite is controlled using two angles and area; these are varied based on a higher-order sliding-mode control technique to achieve the desired formation control. The stability of the proposed controller is established using Lyapunov theory. The performance of the proposed controller is tested through numerical simulation of the governing nonlinear equations of motion and is applied for both formationkeeping and formation reconfiguration in the elliptical restricted three-body problem. The effects of initial state errors, nonnatural formations and optical Solar sail material degradation are considered. The numerical results demonstrate the effectiveness of the proposed control technique for precise satellite formation flying using Solar Radiation Pressure at the L2 libration point. Furthermore, control inputs on the order of 10 deg and 4 m for area change are sufficient to control formation reconfiguration changes as large as 25 km.
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Satellite attitude stabilization using Solar Radiation Pressure and magnetotorquer
Control Engineering Practice, 2009Co-Authors: Krishna Dev Kumar, Min-jea Tahk, Hyochoong BangAbstract:Abstract The paper presents three-dimensional (3-D) attitude stabilization of a geosynchronous satellite. The Solar Radiation Pressure is considered for the satellite pitch and roll stabilization while the yaw attitude is stabilized by a magnetotorquer. The general formulation of the system comprised of a satellite body, two Solar flaps, and a magnetotorquer is obtained through Euler's equations. The linearized system model is derived and then the control laws are developed for suitable rotations of Solar flaps and variations in magnetic moment. The numerical simulation of the governing nonlinear system equations of motion establishes the feasibility of achieving the desired 3-D satellite attitude. The controllers are successful in stabilizing the satellite attitude even in the presence of orbital eccentricity and variations in system parameters.
Daniel J. Scheeres - One of the best experts on this subject based on the ideXlab platform.
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Precise Solar Radiation Pressure Models for Small-Body Orbiters: Applications to OSIRIS-REx Spacecraft
Journal of Guidance Control and Dynamics, 2017Co-Authors: Siamak G. Hesar, Daniel J. Scheeres, Jay W. McmahonAbstract:This paper presents a framework for the precise representation of Solar Radiation Pressure effects on spacecraft orbiting around small bodies. It uses a Fourier-series expansion to model the Solar ...
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Improving Space Object Catalog Maintenance Through Advances in Solar Radiation Pressure Modeling
Journal of Guidance Control and Dynamics, 2015Co-Authors: Jay W. Mcmahon, Daniel J. ScheeresAbstract:This paper investigates the weaknesses of using the cannonball model to represent the Solar Radiation Pressure force on an object in an orbit determination process, and it presents a number of alternative models that greatly improve the orbit determination performance. These weaknesses are rooted in the fact that the cannonball model is not a good representation of the true Solar Radiation Pressure force acting on an arbitrary object. Using an erroneous force model results in poor estimates, inaccurate trajectory propagation, unrealistic covariances, and the inability to fit long and/or dense arcs of data. The alternative models presented are derived from a Fourier series representation of the Solar Radiation Pressure force. The simplest instantiation of this model requires only two more parameters to be estimated, however, this results in orders of magnitude improvements in tracking accuracy. This improvement is illustrated through numerical examples of a discarded upper stage in a geosynchronous transfe...
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laplace plane dynamics with Solar Radiation Pressure in the vicinity of an asteroid
AIAA AAS Astrodynamics Specialist Conference, 2014Co-Authors: Samantha Rieger, Daniel J. ScheeresAbstract:The modified Laplace plane (modified by including Solar Radiation Pressure as a perturbation) gives a surface of frozen orbits that could be advantageous for spacecraft. The modified Laplace plane is defined by an angle and circular orbit radius from a small body where the perturbations from the Sun, J2 and Solar Radiation Pressure are balanced. The modified Laplace plane will be applied to an object around an asteroid. The modified Laplace plane and various other initial conditions will be investigated at three different asteroids, Bennu, 66391 (1999 KW4) and Vesta. These asteroids have different masses, shape, spin axes and orbits around the Sun that will lead to various results. A spacecraft of varying mass-to-area ratio will also be investigated. These different parameters will help determine what causes instability with regard to escape or collision of the spacecraft. The analysis will focus on determining how stable the modified Laplace plane and the Sun terminator plane are to escapes and collisions.
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Solar Radiation Pressure: Exact Analysis
Orbital Motion in Strongly Perturbed Environments, 2012Co-Authors: Daniel J. ScheeresAbstract:Moving beyond gravity-only dynamics about small bodies, we first consider the combined effect of Solar Radiation and Solar tide perturbations on a spacecraft orbiting about an asteroid or comet. In this section we assume the central body can be modeled as a sphere, and neglect gravitational perturbations. This situation models orbital dynamics when far from asteroids or comets where the dominant perturbation will be from Solar effects. We shall also see that for large enough bodies, such as Eros, Solar Radiation Pressure only plays a minimal role. For missions to bodies whose sizes are on the order of a few kilometers or less, however, Solar Radiation Pressure is the principal concern for orbital stability. It is interesting to note that the Solar tide is generally negligible when compared to Solar Radiation Pressure, yet it is included in this discussion for completeness. From a direct analysis of the equations of motion and their equilibrium points specific limits can be derived on orbit semi-major axis for when Solar Radiation can strip a spacecraft out of orbit. The analysis given here is based on some earlier work by Dankowicz [27] and the analysis given in [171].
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Solar Radiation Pressure: Averaged Analysis
Orbital Motion in Strongly Perturbed Environments, 2012Co-Authors: Daniel J. ScheeresAbstract:Stating the same problem analyzed in the previous chapter as a perturbation problem allows us to introduce averaging to the dynamics of the system. In the following we show that the averaged dynamics of an orbiter subject to Solar Radiation Pressure (SRP) and orbiting about a point mass can be solved in closed form with a very simple solution that still exhibits significantly complex behavior. Given this solution we are able to identify a set of stable “frozen orbits” that are suitable for spacecraft mission design and which enable a spacecraft to orbit about very small asteroids without the need for active control.
John L. Crassidis - One of the best experts on this subject based on the ideXlab platform.
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ACC - Adaptive control for spacecraft formation flying with Solar Radiation Pressure and reduction of secular drift
2016 American Control Conference (ACC), 2016Co-Authors: Aniketh Kalur, Kavyashree Shivakumar, Matthias Schmid, John L. CrassidisAbstract:A major problem faced while trajectory planning of spacecraft formation flying is obtaining a “drift-free” case to optimize fuel consumption. The paper considers the effect of non-linearity on relative motion dynamics of spacecraft formation flying with disturbance caused by Solar Radiation Pressure on the formation of spacecraft. The non-linearity is a function of initial conditions, and a perturbation approach is used to correct the initial conditions while maintaining the formation in bounds and also satisfying the zero secular growth requirements. A full state feedback adaptive control law is developed which accounts for the Solar Radiation Pressure, and also estimates and updates the unknown spacecraft mass for formation keeping. The relative dynamics are written as a function of the true anomaly ensuring that the control law works effectively for highly eccentric orbits. Lastly, a Lyapunov stability analysis is shown to ensure the stability of the controller.
Camilla Colombo - One of the best experts on this subject based on the ideXlab platform.
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Solar Radiation Pressure hamiltonian feedback control for unstable libration point orbits
Journal of Guidance Control and Dynamics, 2017Co-Authors: Stefania Soldini, Camilla Colombo, Scott J I WalkerAbstract:This work investigates a Hamiltonian structure-preserving control that uses the acceleration of Solar Radiation Pressure for the stabilization of unstable periodic orbits in the circular restricted...
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the end of life disposal of satellites in libration point orbits using Solar Radiation Pressure
Advances in Space Research, 2016Co-Authors: Stefania Soldini, Camilla Colombo, Scott J I WalkerAbstract:This paper proposes an end-of-life propellant-free disposal strategy for libration-point orbits which uses Solar Radiation Pressure to restrict the evolution of the spacecraft motion. The spacecraft is initially disposed into the unstable manifold leaving the libration-point orbit, before a reflective sun-pointing surface is deployed to enhance the effect of Solar Radiation Pressure. Therefore, the consequent increase in energy prevents the spacecraft’s return to Earth. Three European Space Agency missions are selected as test case scenarios: Herschel, SOHO and Gaia. Guidelines for the end-of-life disposal of future libration-point orbit missions are proposed and a preliminary study on the effect of the Earth’s orbital eccentricity on the disposal strategy is shown for the Gaia mission.
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Solar Radiation Pressure augmented deorbiting passive end of life disposal from high altitude orbits
Journal of Spacecraft and Rockets, 2013Co-Authors: Charlotte Lucking, Camilla Colombo, Colin R McinnesAbstract:A deorbiting strategy for small satellites is proposed that exploits the effect of Solar Radiation Pressure to increase the spacecraft orbit eccentricity so that the perigee falls below an altitude where atmospheric drag will cause the spacecraft orbit to naturally decay. This is achieved by fitting the spacecraft with an inflatable reflective balloon. Once this is fully deployed, the overall area-to-mass ratio of the spacecraft is increased; hence, Solar Radiation Pressure and aerodynamic drag have a greatly increased effect on the spacecraft orbit. An analytical model of the orbit evolution due to Solar Radiation Pressure and the J2 effect as a Hamiltonian system show the evolution of an initially circular orbit. The maximum reachable orbit eccentricity as a function of semimajor axis and area-to-mass ratio is found analytically for deorbiting from circular equatorial orbits of different altitudes. The analytical planar model is then adapted for sun-synchronous orbits. The model is validated numerically...
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orbital dynamics of high area to mass ratio spacecraft with j2 and Solar Radiation Pressure for novel earth observation and communication services
Acta Astronautica, 2012Co-Authors: Camilla Colombo, Charlotte Lucking, Colin R McinnesAbstract:This paper investigates the effect of planetary oblateness and Solar Radiation Pressure on the orbits of high area-to-mass spacecraft. A planar Hamiltonian model shows the existence of equilibrium orbits with the orbit apogee pointing towards or away from the Sun. These solutions are numerically continued to non-zero inclinations and considering the obliquity of the ecliptic plane relative to the equator. Quasi-frozen orbits are identified in eccentricity, inclination and the angle between the Sun-line and the orbit perigee. The long-term evolution of these orbits is then verified through numerical integration. A set of ‘heliotropic’ orbits with apogee pointing in the direction of the Sun is proposed for enhancing imaging and telecommunication on the day side of the Earth. The effects of J2 and Solar Radiation Pressure are exploited to obtain a passive rotation of the apsides line following the Sun; moreover the effect of Solar Radiation Pressure enables such orbits at higher eccentricities with respect to the J2 only case.
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orbital dynamics of high area to mass ratio spacecraft with j2 and Solar Radiation Pressure for novel earth observation and communication services
Acta Astronautica, 2012Co-Authors: Camilla Colombo, Charlotte Lucking, Colin R McinnesAbstract:This paper investigates the effect of planetary oblateness and Solar Radiation Pressure on the orbits of high area-to-mass spacecraft. A planar Hamiltonian model shows the existence of equilibrium orbits with the orbit apogee pointing towards or away from the Sun. These solutions are numerically continued to non-zero inclinations and considering the obliquity of the ecliptic plane relative to the equator. Quasi-frozen orbits are identified in eccentricity, inclination and the angle between the Sun-line and the orbit perigee. The long-term evolution of these orbits is then verified through numerical integration. A set of ‘heliotropic’ orbits with apogee pointing in the direction of the Sun is proposed for enhancing imaging and telecommunication on the day side of the Earth. The effects of J2 and Solar Radiation Pressure are exploited to obtain a passive rotation of the apsides line following the Sun; moreover the effect of Solar Radiation Pressure enables such orbits at higher eccentricities with respect to the J2 only case.