By Robin Biesbroek
This ebook presents readers with a transparent description of the categories of lunar and interplanetary trajectories, and the way they impression satellite-system layout. the outline follows an engineering instead of a mathematical method and comprises many examples of lunar trajectories, in accordance with genuine missions. It is helping readers achieve an figuring out of the using subsystems of interplanetary and lunar satellites. The tables and graphs displaying positive aspects of trajectories make the e-book effortless to understand.
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Extra info for Lunar and Interplanetary Trajectories
Example text
24 shows a typical Earth-Mars transfer with an arrival date after the dust storm. The USA launched the Mariner 9 mission (see Fig. 25) on 30 May 1970 by an Atlas rocket. It arrived at Mars on 14 November in the same year. It became the first spacecraft to orbit another planet however after it entered Mars orbit, Mars was covered with clouds and the pictures did not reveal any feature of the surface. After months of waiting, the storm finally disappeared and the 560 kg spacecraft started the first 34 2 Transfer to a Planet Fig.
We mostly do this to decrease the launch C3, but it could also be done to shorten transfer time. The maneuver is basically an encounter with a planet without establishing an orbit around this planet but rather swing by it, therefore altering the trajectory on a heliocentric level, see Fig. 1. The total transfer energy consists of potential energy (a function of the distance to the Sun) and kinetic energy (a function of the heliocentric velocity). e. the position of the planet, the potential energy stays constant.
The arrival C3 can only be minimized by implementing swing-bys and/or Deep-Space Maneuvers within the trajectory. 6 shows a typical Earth-Mercury trajectory. 4 shows the results for transfers to Venus. 6 years, there are years where there is no short-transfer solution for a transfer to Venus. A long transfer is then the result (>1 year), which allows the spacecraft to ‘wait in orbit’ for the next arrival possibility. In 2025 no solution was found. 5°. 5; the constraint leads different dates and a higher arrival C3.