8 / 10
Г.П. Швецов, В.А. Романенков, П.В. Круглов
8
Инженерный журнал: наука и инновации
# 10·2017
Determination of the mechanical characteristics
of the subliming thermal protective coating
for rocket and space technology
© G.P. Shvetsov
1
, V.A. Romanenkov
1
, P.V. Kruglov
2
1
Closed JSC Experimental Machinery Plant “S.P. Korolev RSC Energia”,
Korolev town, Moscow region, 141070, Russia
2
Bauman Moscow State Technical University, Moscow, 105005, Russia
Thermal protective coatings are used in rocket and space technology to ensure reliable
operation of the structure in a specified temperature range. One method for implement-
ing heat-shielding is the ablation method, based on the destruction of the thermal protec-
tive coating simultaneously with heat removal. Closed JSC Experimental Machinery
Plant “RSC Energia” is the only enterprise in the country manufacturing thermal protec-
tion for manned spacecraft. The enterprise is currently working on the creation of new
promising spacecraft for manned interplanetary flights, where thermal protection is one
of the main constituent parts of the design. When creating a technology for the rocket and
space equipment production due to technology multivariance it is necessary for individu-
al structural elements to possess the best physical and mechanical properties. Here the
results of experiments to determine the mechanical characteristics of the fluorolon: the
ultimate strength and ultimate elongation are presented. Based on the results of the ex-
periments, relationships for the stresses and strains are constructed. The values of the
tensile strength of 23.1 MPa and the ultimate elongation of 57.5% are obtained. It should
be noted that significant elongation of the samples is characterizing the plasticity of the
fluorolon. Therewith the strength of the material is higher than the assumed design val-
ues. These results will be useful in the technological preparation of the production of
thermal protective coatings for rocket and space technology.
Keywords:
subliming thermal protective coating, ablation method, thermal protection, me-
chanical characteristics, composite materials
REFERENCES
[1]
Dzhur E.A., Vdovin S.I., Kuchma L.D. et al.
Tekhnologiya proizvodstva
kosmicheskikh raket
[Space rocket manufacturing technology]. Dnepropetrovsk,
Dnepropetrovsk State University Publ., 1992, 184 p.
[2]
Kalinchev V.A.
Tekhnologiya teplozashchity i teploizolyatsii izdeliy
[Technology of thermal protection and thermal insulation of products]. Moscow,
BMSTU Publ., 1993, 61 p.
[3]
Romanenkov V.A., Kolesnichenko A.F., Martynov M.V. et al. Povyshenie
fiziko-mekhanicheskikh
pokazateley
teplozashchitnykh
pokrytiy
pri
avtoklavnom formovanii v neytralnoy srede [Increase of physical and
mechanical characteristics of thermal protective coatings when autoclave
molding in a neutral environment].
XL Akademicheskie chteniya po
kosmonavtike, posvyashchennye pamyati akademika S.P. Koroleva i drugikh
vydayushchikhsya otechestvennykh uchenykh — pionerov osvoeniya
kosmicheskogo prostranstva.
Sbornik tezisov [Collection of abstracts of XL
Academic readings on cosmonautics, dedicated to the memory of Academician
S.P. Korolev and other outstanding domestic scientists — pioneers of space
exploration]. Moscow, BMSTU Publ., 2015, pp. 406–407.