Method for transferring between planetary circular displaced orbits of solar sail spacecraft

Abstract

The invention discloses a method for transferring between planetary circular displaced orbits of a solar sail spacecraft. According to the method, firstly dynamic models of a planetary circular displaced orbit and an elliptical displaced orbit are analyzed, and a solution method of a solar sail attitude parameter and a reflectivity parameter to achieve the two orbits is given; meanwhile, a boundary condition to conduct splicing and transferring between original and targeted planetary circular displaced orbits and the planetary elliptical displaced orbits is analyzed; and then, according to mission requirements, the orbit parameters of the original circular displaced orbit and a final circular displaced orbit to conduct transferring on the spacecraft are determined, the planetary elliptical displaced orbit used for orbit transferring is solved according to the boundary condition, and further the solar sail attitude parameter and the reflectivity parameter are worked out by combining the dynamic balance point of the planetary elliptical displaced orbit with a sunlight pressure model. The method can give an appropriate planetary elliptical displaced orbit aiming at the problem of transferring between the planetary circular displaced orbits.

Description

technical field [0001] The invention belongs to the technical field of aerospace and relates to a transfer method between planetary circular suspension orbits of a solar sail spacecraft. Background technique [0002] In recent years, with the development and breakthrough of advanced material technology and aerospace technology, new propulsion technologies such as solar sail propulsion technology and electric propulsion technology have developed rapidly. Generally speaking, the solar sail propulsion technology can generate thrust with the help of sunlight without consuming the chemical fuel of the spacecraft itself; the electric propulsion device has a large specific impulse and can reduce the consumption of chemical fuel in the process of propelling the spacecraft. Therefore, compared with traditional propulsion devices, these two types of propulsion systems have significant advantages in long-duration, high-energy space missions, and are especially suitable for missions tha...

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Problems solved by technology

[0004] At present, research on mission orbits based on solar sail propulsion technology mainly focuses on heliocentric, planetary circular levitation orbits, Lagrangian translation point orbits, and heliocentric elliptical levitation orbits. Research on planetary elliptical levitation orbits is still limited rare

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