Modal Test of Large-Sized Low-Frequency Space Structures by Passive Weight Compensation

Aeronautical and Space-Rocket Engineering


Аuthors

Maksimov V. N.1, 2*, Maksimov P. N.1, 2**, Kondratyev K. V.1***

1. Compani «Information satellite systems of academician M.F. Reshetnev», 52, Lenin str., Zheleznogorsk, Krasnoyarsk region, 662972, Russia
2. Siberian State University of Science and Technology named after academician M.F. Reshetnev, 31, Krasnoyarsky Rabochy av., Krasnoyarsk, 660014, Russia

*e-mail: 1928d@mail.ru
**e-mail: 1528d@mail.ru
***e-mail: kondratevkv@iss-reshetnev.ru

Abstract

The article examines the results of the large-size low-frequency space structures test with application of the passive weight compensation system developed at the M.F. Reshetnev “Information Satellite systems” stock company. The purpose of the study consisted in the dynamic characteristics experimental determining of the spacecraft solar array wing in its deployed state, as well as validation of the finite-element model. Model etests conducting allowed revealing both natural frequencies and vibration modes of the structures, as well as determining damping coefficients, characterizing energy losses at the oscillatory motion.
A passive weight compensating aerostatic system based on application of the sliding supports with air lubrication was employed for the zero-gravity conditions modeling.
The support design allows minimizing the testing equipment effect on the dynamic characteristics of the object under study, ensuring the obtained data integrity.
Experimental scheme for the in-plane oscillations excitation by the vibration exciter and accelerometer system was developed and implemented. To eliminate the tooling impact on the structure behavior, the lightweight carbon fiber elements and needle hinges, ensuring freedom of movement without the need for additional rigid couplings, were employed. Special attention was paid to the air environment effect on the dynamic parameters, particularly to the added air mass and the damping coefficient increase due to the vortex zones formation.
Nine natural vibration modes were recorded experimentally and compared with the numerical simulation results. The vibration modes concurrency confirmed the developed finite element model correctness, while frequencies discrepancy did not exceed 3%, which is indicative of high fidelity and accuracy of the conducted measurements.
The test results demonstrated the passive aerostatic weight compensation system effectiveness and confirmed its applicability for the modal studies of large spacecraft components. The obtained dynamic characteristics are recommended for further application in digital models validating and computational techniques refining. Further study of the weight compensation system dissipative properties is necessary to assess their impact on the test object.

Keywords:

the MD SB damping coefficient, the MD SB modal tests, active weight compensation system, the MD SB first modes of oscillations, first natural low frequencies

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