Multi-body Dynamics Simulations of Spacecraft Docking by Monte Carlo Technique

Abstract

Spacecraft docking is one of the key technology demonstrations in space sector. It paves way for several advanced space missions including on-orbit servicing of satellites, space robotics, and development of space station. One of the major sub-systems in this mission is mechanisms sub-system. This has several constituents including mechanism for capture, mechanism for integrating two satellites after capture. The success of the docking event is dependent on the proper alignment of the two spacecrafts rings, which in turn influences the dynamics during the docking. From this perspective, the spacecraft docking problem statement can be considered to be determination of the dynamic envelope for successful capture of the two spacecrafts. This involves study on the dynamic behavior of the two spacecrafts during docking under different approach conditions. This paper presents the different studies that have been carried out to understand the dynamic docking envelope of two spacecrafts. The number of simulations required is very high given the large number of permutations and combinations among the approach parameters. Toward this, a simulation-based approach has been adopted for analysis based on Monte Carlo technique for generating random sample space of approach parameters. The studies have been carried out with the objective of optimizing the computational resources required for multi-body dynamics analysis while not compromising upon the accuracy of results. Multi-body dynamics software MSC software ADAMS has been used for carrying out the dynamic simulations. The details of this methodology along with the results obtained from simulations have been presented in the paper.