Physics
Scientific paper
Sep 2000
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2000stin...0169677u&link_type=abstract
Technical Report, NASDA-ETR-000003; NASDA-TMR-980010 Advanced Mission Research Center
Physics
Perturbation Theory, Celestial Mechanics, Lagrangian Equilibrium Points, Planetary Gravitation, Three Body Problem, Spacecraft Orbits, Radiation Pressure, Gravitational Effects, Solar Observatories, Eccentricity
Scientific paper
Each celestial body system such as Sun-Earth system, Earth-Moon system, Sun-Jupiter system, and so on has five Lagrangian points. Until now, only L1 point in the Sun-Earth system has been utilized for solar observatory mission. A new solar observatory positioned at L5 point in the Sun-Earth system and a SpaceGuard Space Telescope positioned at L4 or L5 point in the Sun-Earth system are proposed as new missions in the near future. Spacecraft motion near these L4 and L5 points are described in reference I based on the circular restricted three body problem. This report studied effects of the eccentricity of the Earth, the gravity of planets, and the solar radiation pressure to orbits near the L4 and L5 points in the Sun-Earth system. In chapter 2, results of brief paper survey were shown. In chapter 3, effects of the eccentricity of the Earth orbit were studied. It was known from analytical treatment that the point which forms an equilateral triangle with the Sun and the instant position of the Earth becomes L4, or L5 point in the elliptical restricted three body problem. Periodic orbits around the L4 or L5 point mentioned above could be realized by adjusting the initial velocities. In chapter 4, effects of the gravity of planets were studied. Both direct and indirect terms were included for the gravity of planets. It was found that the short periodic terms of the semi-major axis due to the tidal force by planets are dominant. They depend upon the difference between the celestial longitudes of a planet and the Earth at the epoch, and most effects of planets could also be cancelled by adjusting the initial velocity. The magnitude of adjustment is less than 1 m/s. In chapter 5, the combined effects of the Earth's eccentricity and planetary gravities were studied, and it was confirmed that those combined effects could be accurately approximately as the simple superposition. In chapter 6, an L5 mission orbit with the minimum fuel for transfer was briefly stated, and effects of injection errors at L5 point were described. The maximum drift for 5 years by no control of the injection errors was about 250 x 104 km. In chapter 7, effects of the solar radiation pressure were studied analytically at first, then confirmed by the numerical integrations. It was found that the radiation pressure makes the L4 and L5 points shift to the Sun direction with the unchanged distance from the Earth, and that the movement around the shifted L4 or L5 point was not affected by the radiation pressure in the approximation of neglect of the Earth's mass. After all, most effects of the eccentricity of the Earth, the gravity of planets, and the solar radiation pressure to orbits near the L4 and L5 points in the Sun-Earth system were found to be cancelled by adjusting the initial position and velocity.
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