@techreport{oai:jaxa.repo.nii.ac.jp:00044643,
 author = {吉村, 庄市 and 上村, 平八郎 and 山中, 龍夫 and YOSHIMURA, Shoichi and KAMIMURA, Heihachiro and YAMANAKA, Tatsuo},
 month = {Nov},
 note = {A computer simulation study has been carried out for the orbital transfer of the space vehicle by the use of a low-thrust propulsion system. In the formulation of the basic equations of motion, two kinds of forces are regarded as the perturbation forces, i.e., one is the thrust generated by a low-thrust propulsion system, and the other is the disturbing force from the coefficient J2 of zonal harmonics of the earth’s gravitational potential. The disturbed orbit has been derived by direct integration of a set of so-called osculating orbital elements. As an example, an orbital transfer has been investigated, which is one from a low altitude elliptic parking orbit, with a 30 degrees inclination to the equator, to the synchronous equatorial orbit, namely so-called 24-hour orbit. This kind of mission will be important for future space development program of Japan, because there might be a limit to the capability of their launching rocket. In the simulation, two kinds of maneuvers have been compared with. One is the parallel maneuvers of orbit raising and plane change, and the other is the serial ones of these two operations, i.e., after orbit raising has been over, plane change is started. The effect of the earth’s shadow, eclipse, on the transfer orbit also has been discussed, because the space vehicle must have a coasting flight during every eclipse in order to save the weight of batteries., 資料番号: NALTR0395000, レポート番号: NAL TR-395},
 title = {微小推力による人工衛星の軌道遷移についての数値シミュレーション},
 year = {1974}
}