TY - GEN
T1 - Coupled attitude-orbit dynamic modelling of high area-To-mass spacecraft and significance analysis of perturbation factors
AU - Ren, Zhongjing
AU - Yuan, Jianping
AU - Shi, Yong
AU - Qiao, Qiao
N1 - Publisher Copyright:
Copyright © 2015 by the American Institute Federation of Aeronautics and Astronautics. Inc. All rights reserved.
PY - 2015
Y1 - 2015
N2 - The past few years have seen a rapid development on the engineering and space experiment of High Area-To- Mass ratio Spacecraft (HAMS), such as ChipSat, CubeSail, etc. Compared to the traditional satellites, the effects of terrestrial perturbations on spacecraft with high area-To-mass ratio are more significant, especially on the low earth orbit (LEO). It is possible to utilize the perturbation actively to propel spacecraft through available design of structure and actuation. In order to achieve higher ratio of area-To-mass (more than 10tn2/kg), configuration with flat plate or membrane and materials with small density are chosen. Since there is no need to install the propulsion system which contains large amount of propellant, the mass of the system could be further reduced, and so is the launch costs. Recent researches on HAMS focus on the influence of various perturbation on the orbital evolution of uncontrolled objects, such as space debris. However, the attitude and orbital motion of the high area-To-mass ratio object is strong coupling, and that would make more sense when considering perturbations that could be used by the controlled actuation system of HAMS. In this way, more potential applications could be exploited. Therefore, it would be of great importance and necessity to establish the coupled attitude-orbit dynamic model for HAMS under the multi-force system on the LEO, including gravity, Solar Radiation Pressure (SRP), aerodynamic forces, and J2 perturbation. The work presented in this paper can be divided into three parts. First, a conceptual design of an active actuation system named "ChipSail" utilizing solar pressure and geomagnetic force with the help of novel material and Micro Electro-Mechanical System (MEMS) technology is proposed. Second, the coupled motion between the attitude and orbit is characterized through analyzing the influence of the individual perturbation exerting on the spacecraft, which would contribute to the modelling of the coupled dynamics. Third, the dynamic model is then used to quantify the effect of each perturbation on the coupled motion of spacecraft, and six orbital parameters and another two attitude parameters are used to describe range of significance for different area-To-mass ratio. The work showed in this paper will lay a solid foundation for the further design of optimal control.
AB - The past few years have seen a rapid development on the engineering and space experiment of High Area-To- Mass ratio Spacecraft (HAMS), such as ChipSat, CubeSail, etc. Compared to the traditional satellites, the effects of terrestrial perturbations on spacecraft with high area-To-mass ratio are more significant, especially on the low earth orbit (LEO). It is possible to utilize the perturbation actively to propel spacecraft through available design of structure and actuation. In order to achieve higher ratio of area-To-mass (more than 10tn2/kg), configuration with flat plate or membrane and materials with small density are chosen. Since there is no need to install the propulsion system which contains large amount of propellant, the mass of the system could be further reduced, and so is the launch costs. Recent researches on HAMS focus on the influence of various perturbation on the orbital evolution of uncontrolled objects, such as space debris. However, the attitude and orbital motion of the high area-To-mass ratio object is strong coupling, and that would make more sense when considering perturbations that could be used by the controlled actuation system of HAMS. In this way, more potential applications could be exploited. Therefore, it would be of great importance and necessity to establish the coupled attitude-orbit dynamic model for HAMS under the multi-force system on the LEO, including gravity, Solar Radiation Pressure (SRP), aerodynamic forces, and J2 perturbation. The work presented in this paper can be divided into three parts. First, a conceptual design of an active actuation system named "ChipSail" utilizing solar pressure and geomagnetic force with the help of novel material and Micro Electro-Mechanical System (MEMS) technology is proposed. Second, the coupled motion between the attitude and orbit is characterized through analyzing the influence of the individual perturbation exerting on the spacecraft, which would contribute to the modelling of the coupled dynamics. Third, the dynamic model is then used to quantify the effect of each perturbation on the coupled motion of spacecraft, and six orbital parameters and another two attitude parameters are used to describe range of significance for different area-To-mass ratio. The work showed in this paper will lay a solid foundation for the further design of optimal control.
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M3 - Conference contribution
AN - SCOPUS:84991632813
T3 - Proceedings of the International Astronautical Congress, IAC
SP - 5652
EP - 5665
BT - 66th International Astronautical Congress 2015, IAC 2015
T2 - 66th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015
Y2 - 12 October 2015 through 16 October 2015
ER -