DETERMINATION OF LOADS FOR STRENGTH CALCULATIONS OF THE ATTACHMENT FITTINGS OF THE DEVICES AND ASSEMBLIES OF A SPACECRAFT IN A POWERED FLIGHT


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Abstract

The paper presents the technique of the study of the loads on the gyroscopes of the spacecraft motion control system in the flight segment as a part of a space rocket. This problem is a problem of vibration resistance and is solved mainly for the attachments, which is mounted to the body of a vehicle. These attachments can be the mechanisms, antennas, locks, explosive charges, electrical actuators, telemetry transmitters, devices, and assemblies of a spacecraft. In addition to the above mentioned the elements of fastening equipment: fittings, landing planes, brackets, and flanges may be an object of consideration as well.

The goal of the study is the description of the calculation of the loads (dynamic analysis) for the onboard equipment of a spacecraft in the flight segment as a part of a space rocket. The load values are necessary for strength calculations, the results of which are considered when designing the fixtures for the devices and units, as well as when designing and configuring the devices of rocket and space technology.

As an example of calculation, the authors chose the gyroscopes of the motion control system of small spacecraft “AIST-2D”, the load case was “the max-q”. Based on the initial data, the authors constructed a finite element model (FEM) of the plants to determine the loading values. The model is constructed in the FEMAP software program for interactive creation and maintenance. NX NASTRAN is the solver that is used to carry out the dynamic analysis of the structure – the transient analysis.

As a result of the solution, based on the data obtained, the time change of characteristic parameters of loading – acelerations – is shown. Operational overloads influencing the gyroscope assemblies in each direction of the rectangular coordinate system are obtained from the acceleration graphs by dividing by the acceleration of gravity. The authors compared the calculated and experimental data. For the convenience of performance evaluation, the values are shown for one of four gyroscopes mounted in the spacecraft service systems module.

About the authors

A. A. Popkov

Academician S.P. Korolev Samara State National Research University

Author for correspondence.
Email: fake@neicon.ru
Russian Federation

V. A. Filatov

Academician S.P. Korolev Samara State National Research University

Email: fake@neicon.ru
Russian Federation

A. G. Filipov

Academician S.P. Korolev Samara State National Research University

Email: fake@neicon.ru
Russian Federation

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