Modeling and Simulation of Clamp Band Dynamic Envelope in a LV/SC Separation System

Abstract

The clamp band system is a typical locked and separated device of the launch vehicle (LV) / the spacecraft (SC), and its release-separation process is one of the important factors that affect the LV/SC separation movement. A nonlinear spring-damper model was employed to describe the contact-impact behavior between the V-segment of the clamp band and the LV/SC interface, and lumped mass method was used to depict the clamp band. By using ADAMS, a dynamic model of the clamp band system was established. The simulation results show that the impulse of the explosive bolts and the stiffness of lateral-restraining springs have significant effects on the clamp band dynamic envelope. The shock of the satellite-vehicle separation is very vulnerable to the clamp band pretension and the friction coefficient between the V-segment and the LV/SC interface.

Uncertainty analysis and reliability estimation of clamp band joints

“…The applied external moment could be greater or lower than M max,1 . In cases where M < M max,1 , when the jth spring reaches its maximum allowable load, the equation T m,j = K j Y 0 cos(θ j ) governs according to Equation (10). Therefore, the maximum displacement of the joint, at the moment that at least one spring is going to fail could be calculated as follows:…”

“…These models were utilised to optimise the design of the joint [9]. In addition, the dynamic behaviour of the band and clamps during the separation process of multistage launch vehicle and spacecraft were investigated using the numerical methods [10][11][12] and simplified analytical methods [13,14]. The maximum allowable load of clamp band joints was investigated using empirical methods [15], and also, the impact of the flange geometry and its dimensions was investigated on the ultimate load [16].…”

Dynamic analysis of satellite separation considering the flexibility of interface rings

“…Comparing with the proposed dynamic simulation model in the literatures, 12–14 the main improvement of the new simulation model in this paper is the introduction of flexible interface rings, which can be achieved by employing the co-simulation of flexible bodies based on ANSYS and ADAMS software platforms. To accomplish this objective, the finite element models of satellite interface ring and payload adapter are built in the finite element analysis software ANSYS firstly as shown in Figure 2.…”

“…Li et al. 13,14 improved Tan’s method for designing and analyzing separation systems and illustrated the 2-D and 3-D dynamic envelopes of clamp band. Bhosale et al.…”

“…As an extension of the authors’ previous work in the literatures, 12–14 the purpose of this paper is to develop a modeling and simulation method for comprehensively predicting the dynamic characteristics of satellite separation. Therefore, first, a multi-body model of the typical clamp band joint of satellite separation system containing flexible interface rings is established in the ADAMS software.…”