Abstract: The presence of parts separating from the launch vehicle (LV) during of the active part of the flight, such as the tail and interstage compartments, and payload fairing calls for the solution of the problem associated with the allocation of significant impact areas. This is a common problem in all spaceships, including the cases when recoverable and reusable first stages are used, for example, Falcon 9 launch vehicles. This paper considers one of the possible solutions to this problem, based on the combustion of separating parts during the descent trajectory flight. The study subject is a combustible demonstrator (CD), a small element of the three-layer shell of the payload fairing. The layers of the shell are the sheathings and the filler charge placed between them. The filler charge is a pyrotechnic composition (PC) initiated by the command, and the sheathing is a combustible polymer composite material (PCM). The material for the structures of the separating parts is produced as follows. First, a CD is created due to the chosen PCs and sheathings. Then, the required strength of the CD is ensured. Finally, the demonstrator structure is guaranteed to burn up or be fragmented finely for the given time. © 2021 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc.

Cite: Trushlyakov V.I. , Panichkin A.V.
Methodology for the design of combustible structures of separating launch vehicle parts
Journal of Spacecraft and Rockets. 2021. V.58. N4. P.1200-1206. DOI: 10.2514/1.A34920 WOS Scopus OpenAlex

Identifiers:

Web of science:	WOS:000682852400024
Scopus:	2-s2.0-85114429502
OpenAlex:	W3135879123

Citing:

DB	Citing
Scopus	2
OpenAlex	1
Web of science	1

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