TY  - JOUR
T1  - Estimates of the Trajectory Parameters and Thermal Loads for a Ballistic Capsule
Returning from the Moon with Multiple Dives into the Earth Atmosphere
AU - V. Leonov, Victor AU - Grishko, Dmitriy A. 
JO  - Journal of Engineering and Applied Sciences
VL  - 14
IS  - 6
SP  - 1775
EP  - 1780
PY  - 2019
DA  - 2001/08/19
SN  - 1816-949x
DO  - jeasci.2019.1775.1780
UR  - https://makhillpublications.co/view-article.php?doi=jeasci.2019.1775.1780
KW  - Moon exploration
KW  -return trajectory
KW  -multiple dives into the atmosphere
KW  -ballistic capsule
KW  -descent
module
KW  -ablative thermal protection system
AB  - 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.
ER  -