Parallel Load-Bearing and Damping System Design and Test for Satellite Vibration Suppression

Yanjie Liu,Zhongwen Pan,Yanwu Zheng,Shenyan Chen,Minxiao Ying,Zihan Yang

doi:10.3390/app10041548

Abstract

The traditional series-type satellite vibration suppression scheme significantly decreases satellite frequency, which leads to difficulty in controlling the amplitude. In the present work, a new parallel viscous damping scheme is adopted on the Payload Adaptor Fitting (PAF), which aims to integrate a load-bearing design and vibration reduction. The vibration amplitude and weight are the most important design requirements of the damping system. The Finite Element (FE) model of PAF was established. Through a series of analyses, the appropriate number and coefficient of dampers were determined. The damping force was calculated according to the damping coefficient and the relative velocity between the two ends of the damper. Based on the damping force and the installation dimensions, the damping rod was designed. The force–velocity test was carried out on the damping rod prototype, which showed its performance satisfies the requirements. With the topology optimization and sizing optimization technology, the light-weight supports were designed and manufactured. One damping rod and two supports were assembled as one set of dampers. Eight sets of dampers were installed on the PAF. Vibration tests were conducted on the damping state PAF. The results showed that the proposed system is effective at suppressing vibration and maintaining stiffness simultaneously.

Highlights

Satellites are subjected to a complex vibration environment during launch [1]
The results prove that the new system can reduce the vibration response and achieve the integration of load bearing and vibration isolation, as well as maintaining the Payload Adaptor Fitting (PAF)’s stiffness
After designing the vibration isolation system, frequency response experiments were conducted to verify the effectiveness of the system

Summary

Introduction

Satellites are subjected to a complex vibration environment during launch [1]. The high-frequency random vibration is mainly produced by noise excitation [2,3]. The low-frequency vibration is generally under 100 Hz, which is mainly caused by two sources: (1) the free vibration decay from the transient excitations, such as the rocket engine’s ignition/shutdown, the inter-stage separations, and the booster separations; and (2) unstable vibrations from the intercoupling between the liquid rocket propulsion system and the structure system [4,5]. The fundamental frequency of a satellite structure is usually under 100 Hz, which is near the low-frequency vibration environment. There is vibration amplification in flight and ground tests, which might cause serious consequences such as structural damage

Objectives

Results

Conclusion