Zobrazeno 1 - 5
of 5
pro vyhledávání: '"Bo-yong He"'
Publikováno v:
Earth, Planets and Space, Vol 75, Iss 1, Pp 1-18 (2023)
Abstract Different from the Apollo flight mode, a safer trans-lunar flight mode for the crews is preferred. The previous-arrived lunar module rendezvouses with the crew exploration vehicle at a low lunar destination orbit, and then the crews ride the
Externí odkaz:
https://doaj.org/article/8c9038209d1846a2872fb0e8b9db482a
Publikováno v:
Scientific Reports, Vol 11, Iss 1, Pp 1-13 (2021)
Abstract The retrograde geostationary earth orbit (retro-GEO) is an Earth’s orbit. It has almost the same orbital altitude with that of a GEO, but an inclination of 180°. A retro-GEO monitor-satellite gives the GEO-assets vicinity space-debris war
Externí odkaz:
https://doaj.org/article/0282e3ead1b342ee874d35c7bb69f183
Publikováno v:
Scientific Reports, Vol 11, Iss 1, Pp 1-13 (2021)
The retrograde geostationary earth orbit (retro-GEO) is an Earth’s orbit. It has almost the same orbital altitude with that of a GEO, but an inclination of 180°. A retro-GEO monitor-satellite gives the GEO-assets vicinity space-debris warnings per
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::15855311d696a7b9221997412209bdca
https://doaj.org/article/0282e3ead1b342ee874d35c7bb69f183
https://doaj.org/article/0282e3ead1b342ee874d35c7bb69f183
Autor:
Bo-yong He, Hong-xin Shen
Publikováno v:
Astrodynamics. 4:75-86
The solution set of the Sun-perturbed optimal two-impulse trans-lunar orbit is helpful for overall optimization of the lunar exploration mission. A model for computing the two-impulse trans-lunar orbit, which strictly satisfies the boundary constrain
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0efe4aaf0210e19990f89da1b880e089
https://doi.org/10.1007/s42064-020-0069-6
https://doi.org/10.1007/s42064-020-0069-6
Publikováno v:
The Journal of the Astronautical Sciences. 66:446-459
To design a free-return orbit for manned lunar mission based on low earth orbit (LEO) rendezvous, an adaptive LEO-phase free-return orbit design method based on high-precision dynamics model is proposed. First, the radius of perilune and the absolute
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::82ac056d8c49f2dce5ab94bb554d9c2d
https://doi.org/10.1007/s40295-019-00182-3
https://doi.org/10.1007/s40295-019-00182-3