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Сибирский государственный университет
науки и технологий имени академика М.Ф. Решетнева

Сибирский аэрокосмический журнал
ISSN 2712-8970 (Print) ISSN 2782-5760 (on-line)

Сведения об образовательной организации

UDK 629.042:629.783
DOUBLE-CONIC ADAPTER FOR LAUNCHING THE BLOCK OF THREE SPACECRAFTS
A. A. Khakhlenkova
Reshetnev Siberian State Aerospace University 31, Krasnoyarsky Rabochy Av., Krasnoyarsk, 660037, Russian Federation
Group launching of several spacecrafts by the use of one launch vehicle is the difficult engineering task. The solution of this task will allow cutting down considerably expenses on formation of the orbital group consisting of a set of the same spacecrafts. In this task the main question demanding careful study is a connection of the block of spacecrafts with the carrier rocket. Traditionally integration of both the single spacecraft, and the block from several devices with the carrier rocket is carried out by means of the so-called separating device. Integral part of this device is the adapter – the transitional design serving for placement of various elements of the separating device (such as locks, pushers, clamping and rotary devices) and rigid connection of the spacecraft or the block of spacecrafts with the carrier rocket. This construction receives the loadings arising at ground operations and transportation and also at starting of the carrier rocket therefore it has to possess high rigidity and durability. Now the metallic truss construction is used for a carrying into orbit of the block of three spacecrafts. This truss represents a set of the fittings connected among themselves by hollow aluminum pipes. Such construction possesses a number of essential shortcomings. In the article essentially new adapter is offered. Its construction having rather small weight and high rigidity thanks to using the modern composite materials allows distributing evenly load on the carrier rocket's interface points. The production technology of elements of such construction is worked off on many Russian spacecrafts. The parametrical analysis of the offered adapter construction is carried out. The ways of increase of rigidity of the adapter are shown: using of materials with the high module of elasticity, changing of thickness of coverings of the panel, and also changing of parameters of lattice structure of conic shells. Also preliminary estimate of mass of the offered construction is made.
Keywords: group launching of spacecrafts, spacecraft adapter, finite-element modelling, lattice conic shell, honeycomb panel, truss construction.
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Khakhlenkova Аnna Аleksandrovna – Master’s degree student, junior researcher, Reshetnev Siberian State

Aerospace University. E-mail SparkleA@yandex.ru.