Vibration Antiresonance Design for a Spacecraft Multifunctional Structure

Abstract

Spacecraft must withstand rigorous mechanical environment experiences such as acceleration, noise, vibration, and shock during the process of launching, satellite-vehicle separation, and so on. In this paper, a new spacecraft multifunctional structure concept designed by us is introduced. The multifunctional structure has the functions of not only load bearing, but also vibration reduction, energy source, thermal control, and so on, and we adopt a series of viscoelastic parts as connections between substructures. Especially in this paper, a vibration antiresonance design method is proposed to realize the vibration reduction. The complex zero-point equations of the vibration system are firstly established, and then the vibration antiresonance design for the system is achieved. For solving the difficulties due to viscoelastic characteristics of the connecting parts, we present the determining formulas to obtain the structural parameters, so that the complex zero-point equations can be satisfied. Numerical simulation and ground experiment demonstrate the correctness and effectiveness of the proposed method. This method can solve the structural vibration control problem under the function constraints of load bearing and energy supplying and will expand the performance of spacecraft functional modules.

Seismic response control of base‐isolated buildings using multiple tuned mass dampers

“…Hence, numerous researchers analyzed three-dimensional (3D) structures equipped with a single tuned vibration absorber (TVA) or multiple TVAs. [29][30][31][32][33][34][35][36][37][38][39][40] The general conclusion of the studies shows that multiple TVAs are more robust and efficient as compared with the single TVA in response improvement (mitigation) of 3D structures.…”

Dynamic characteristics of multifunctional structure for spacecraft

“…The viscoelastic components have absorbed some mechanical energy. 29 The observed maximum PSD of the MFS during the random excitation testing is 1.95 g 2 /Hz. The maximum and minimum temperatures observed on the MFS during its in-orbit tests are 13℃ and 28℃.…”

Modeling of unsteady aerodynamic characteristics at high angles of attack

“…The fractional derivative theory has been utilized to describe the hysteresis characteristics of the dynamic mechanical properties of a spacecraft structure containing the viscoelastic materials in our previous work. [27][28][29][30][31][32][33] And in the present paper, an improved differential equation is investigated to describe the hysteresis characteristics of the aerodynamic coefficients.…”