Abstract
In this paper, a dynamic model for long-term on-orbit operation of the tethered solar power satellite (Tethered-SPS) is established. Because the Tethered-SPS is a super-large and super-flexible structure, the coupling among the orbit, attitude, and structure vibration of the system should be considered in comparison with the traditional spacecraft dynamic models. Based on the absolute nodal coordinate formulation (ANCF), the dynamic equation of the Tethered-SPS is established by Hamiltonian variational principle, and the dual equations of the Hamiltonian system are established by introducing generalized momentum through Legendre transformation. The symplectic Runge–Kutta method is used for numerical simulation, and the validation of the modeling method is verified by a numerical example. The effects of orbital altitude, initial attitude angle, length of solar panel, and orbital eccentricity on the orbit and attitude of the Tethered-SPS are analyzed. The numerical simulation results show that the effect of orbital altitude and length of solar panel on the orbital error of midpoint of beam is small. However, the initial attitude angle has a significant effect on the orbital error of midpoint of solar panel. The effect of the length of solar panel on the attitude angle of the system is not significant, but orbital altitude, orbital eccentricity, and initial attitude angle of the system severely affect the attitude angle of the system. Then, the stability of the system is affected.
Highlights
With the use of a large number of mineral energy, the global natural environment has been seriously polluted, which has caused the destruction of the ecological environment
In order to utilize solar energy more effectively, Glaser [2] first proposed the concept of space solar power station (SPS): solar energy is converted into electric energy in space; the electric energy is transmitted to the ground rectenna receiver through microwave, and the electric energy is transmitted to users
In order to facilitate the study, this paper only considers the motion of the system in the orbit plane. e Tethered-SPS system can be simplified as a dynamic model consisting of Euler-Bernoulli beam and particle. e beam AB and point P are connected by 21 springs [20], and point C is the midpoint of beam AB. e inertial coordinate system is established, in which the coordinate origin O coincides with Earth’s center of mass, and the Ox axis and the Oy axis are in the orbit plane
Summary
With the use of a large number of mineral energy, the global natural environment has been seriously polluted, which has caused the destruction of the ecological environment. In 2003, Fujii et al [21] established a one-dimensional flexible beam for Tethered-SPS and designed a method to control attitude and structural vibration of the system by adjusting the tethers. E dynamic model of the Tethered-SPS was established by simplifying the bus system as a particle, the tethers as a mass-free springs, and the solar array panel as flexible panels in [26], and the effect of thermal deformation of solar panels on the attitude of the system was studied. A simplified model of the Tethered-SPS was established, and the effects of solar pressure on structural vibration and attitude of the system were analyzed. Li and Zhu [39] established the dynamics model of the tethered satellite by finite element method and used the fourth-order symplectic Runge–Kutta method for numerical simulation. Based on the above background, the symplectic method is used to study the orbit and attitude dynamic response of the Tethered-SPS
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