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The spinning deployment process of solar sails is analyzed in this study.A simplified model is established by considering the out-of-plane and in-plane motions of solar sails.The influences of structure parameters,initial conditions,and feedback control parameters are also analyzed.A method to build the geometric model of a solar sail is presented by analyzing the folding process of solar sails.The finite element model of solar sails is then established,which contains continuous cables and sail membranes.The dynamics of the second-stage deployment of solar sails are simulated by using ABAQUS software.The influences of the rotational speed and out-of-plane movement of the hub are analyzed by different tip masses,initial velocities,and control parameters.Compared with the results from theoretical models,simulation results show good agreements. 相似文献
73.
V.V. Lyahov V.M. Neshchadim 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
A procedure for investigating the stability of a current sheath, taking into account the effect of plasma polarization, is offered. The kinetic equation with a self-consistent electromagnetic field for perturbation of the distribution function is solved. On the basis of this solution, the tensor of dielectric permeability for a non-electroneutral current sheath plasma is calculated, and the dispersion equation for the study of possible instability modes of this current sheath is obtained. The instability of the current sheath of the magnetospheric tail with respect to tearing perturbations, and the influence of the effect of plasma polarization on the development of tearing instability, are investigated. 相似文献
74.
Stability and shape analysis of relative equilibrium for three-spacecraft electromagnetic formation 总被引:1,自引:0,他引:1
The invariant shapes for close formation flying with inter-craft electromagnetic force ensure several potential space applications. However, the 6-DOF relative equilibrium problem has not been systematically investigated. This paper mainly analyzes the invariant shapes of relative equilibrium for the three-spacecraft electromagnetic formation, and studies the families of invariant shape solutions with real and constant magnetic moments as well as their linear stability. The problem is examined based on the full nonlinear coupled dynamic models for collinear and general triangular configurations. The relative equilibrium conditions are analyzed to determine whether an invariant shape do exist, and the corresponding families of invariant shape solutions are identified for static and spinning configurations respectively. Finally, the linear stability of such invariant shapes is numerically discussed, which have shown that most invariant shapes are unstable and controllable. 相似文献
75.
Marc Jorba-Cuscó Ariadna Farrés Àngel Jorba 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2021,67(9):2812-2822
Solar sails change the natural dynamics of systems: Trajectories that are driven by gravitational forces can be displaced and changed because of the effect of Solar Radiation Pressure (SRP). Moreover, if the lightness number of the sail is large enough, the instability of certain orbits can be diminished and even removed. In this paper we modify two models for the motion of a probe in the Earth-Moon system that include the effect of Sun’s gravity to take also into account the effect of SRP. These models, the Bicircular Problem (BCP) and the Quasi-Bicircular Problem (QBCP), are periodic perturbations of the Earth-Moon Restricted Three Body Problem (RTBP). The models are modified to consider the effect of the SRP upon a solar sail. We provide examples of periodic orbits that are stabilized (or made less unstable) due to the effect of SRP. 相似文献
76.
Hanlun Lei Christian Circi Emiliano Ortore Bo Xu 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2019,63(2):1017-1037
In this work, equilibrium attitude configurations, attitude stability and periodic attitude families are investigated for rigid spacecrafts moving on stationary orbits around asteroid 216 Kleopatra. The polyhedral approach is adopted to formulate the equations of rotational motion. In this dynamical model, six equilibrium attitude configurations with non-zero Euler angles are identified for a spacecraft moving on each stationary orbit. Then the linearized equations of attitude motion at equilibrium attitudes are derived. Based on the linear system, the necessary conditions of stability of equilibrium attitudes are provided, and stability domains on the spacecraft’s characteristic plane are obtained. It is found that the stability domains are distributed in the first and third quadrants of the characteristic plane and the stability domain in the third quadrant is separated into two regions by an unstable belt. Subsequently, we present the linear solution around a stable equilibrium attitude point, indicating that there are three types of elemental periodic attitudes. By means of numerical approaches, three fundamental families of periodic solutions are determined in the full attitude model. 相似文献
77.
全球卫星导航系统(GNSS)载波相位时间传递技术是高精度时间传递领域的主要研究方法之一,但目前关于该部分的研究主要集中在中低纬度地区,在高纬度地区并不多见。不同GNSS由于星座设计不同,在高纬度地区结构差异较大,因此需要对不同GNSS在高纬度地区的时间传递性能进行分析。实验结果表明,在高纬度地区时间传递中,Galileo稳定度最高,GPS和BDS次之,GLONASS最差。同时因在高纬度地区卫星的高度角普遍偏低,为合理平衡低高度角时可视卫星多和多路径误差大的矛盾,对不同截止高度角下获取的链路时间传递性能进行了分析。结果表明,在5°截止高度角下,高纬度地区的时间传递链路稳定性最好。 相似文献
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80.
带飞轮的充液摆的稳定性包光伟(上海交通大学工程力学系,200030)关键词充液刚体动力学,液体晃动,运动稳定性,航天器动力学一、引言研究三轴定向充液卫星的姿态稳定性,在不考虑系统质心横向运动的情况下,一个较为简单的力学模型是充液摆作定点摆动的模型.对... 相似文献