Journal of Engineering and Applied Sciences
ISSN: Online 1818-7803ISSN: Print 1816-949x
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Abstract
Numerical analysis of an approximate return trajectory from the Moon with multiple dives into the atmosphere is carried out. The motion which is assumed to be planar is modeled in a central gravity field. The target perigee altitude is a variate for the first dive into the atmosphere. The descent vehicle is a ballistic capsule with zero lift-drag. The target perigee altitude is shown as having an effect on the number of dives into the atmosphere and on the apogee altitude of the orbit formed after a successive penetration into the atmosphere. Estimates are given for the thermal loads on the vehicle in the dense atmosphere and for the mass of the ablative thermal protection entrained from the space vehicle surface. Feasibility of such trajectories is shown, their advantages and disadvantages are discussed.
How to cite this article:
Victor V. Leonov and Dmitriy A. Grishko. Estimates of the Trajectory Parameters and Thermal Loads for a Ballistic Capsule
Returning from the Moon with Multiple Dives into the Earth Atmosphere.
DOI: https://doi.org/10.36478/jeasci.2019.1775.1780
URL: https://www.makhillpublications.co/view-article/1816-949x/jeasci.2019.1775.1780