Solar Orbiter Mission Design Overview and Navigation Analysis

Preliminary ISAS Mercury orbiter mission design

Acta Astronautica ◽

10.1016/s0094-5765(99)00136-8 ◽

1999 ◽

Vol 45 (4-9) ◽

pp. 187-195 ◽

Cited By ~ 4

Author(s):

Hiroshi Yamakawa ◽

Hirobumi Saito ◽

Jun'ichiro Kawaguchi ◽

Yasunori Kobayashi ◽

Hajime Hayakawa ◽

...

Keyword(s):

Mission Design ◽

Orbiter Mission

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Mission Design and Analysis for Mars Orbiter Mission

The Journal of the Astronautical Sciences ◽

10.1007/s40295-019-00199-8 ◽

2019 ◽

Vol 67 (3) ◽

pp. 932-949

Author(s):

Kuldeep Negi ◽

B. S. Kiran ◽

Satyendra Kumar Singh

Keyword(s):

Mission Design ◽

Orbiter Mission

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Modern mission design with the high inclined orbit formation using gravity assists: main methods

Mathematica Montisnigri ◽

10.20948/mathmontis-2020-49-7 ◽

2020 ◽

Vol 49 ◽

pp. 87-95

Author(s):

Gennady Konstantinovich Borovin ◽

◽

Alexey Vasilyevich Grushevskii ◽

Andrey Georgievich Tuchin ◽

Denis Andreevich Tuchin

Keyword(s):

Low Cost ◽

Space Mission ◽

Flight Time ◽

Mission Design ◽

Space Technology ◽

Stage Of Development ◽

Gravity Assists ◽

Orbiter Mission ◽

Current Stage ◽

Inner Heliosphere

An effective space exploration is impossible without gravity assists (GA) using. Their application relaxes the constraints imposed on the space mission scenarios by the characteristic velocity budgets being realized at the current stage of development of space technology. A significant change in the inclinations of operational spacecraft (SC) orbits in flight aimed at studying the inner heliosphere from out-of ecliptic positions (the ESA “Solar Orbiter” mission, Russian “Interheliozond”) is needed to accomplish some prospective space missions. Low-cost tours for the high inclined orbit formation in the Solar system with use of gravity assists near its planets (Earth and Venus) with the full ephemeris using are considered. The limited dynamic possibilities of using gravity maneuvers require their repeated performance. Based on the formalization of the search for the GA- timetables with subsequent adaptive involvement of a large number of options, a high-precision algorithm for synthesizing chains of increasing gravity assists was built. Its use leads to a significant inclination change of the research SC's orbit without significant fuel consumption during a reasonable flight time.

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