SPACE AIRCRAFT WITH OPTIMISED DESIGN AND ARCHITECTURE
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United States of America Patent
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Issued Date -
Oct 6, 2022
app pub date -
Jun 5, 2020
filing date -
Jun 7, 2019
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Abstract
A space aircraft including a fuselage, two wings arranged on either side of the fuselage, and two nacelles arranged at the ends of the wings and each carrying a horizontal tail and a vertical tail, the fuselage having a cross section of variable size along the longitudinal axis with a maximum cross section being located in a longitudinal position located in front of the longitudinal position of the leading edges of the wings at the fuselage, making it possible in particular to help prevent the space aircraft from losing longitudinal static stability, the space aircraft thus having an optimized design and architecture which are suitable for the severe conditions encountered by such a space aircraft, in particular during atmospheric re-entry.
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