logo

SCIENCE CHINA Information Sciences, Volume 60, Issue 5: 050204(2017) https://doi.org/10.1007/s11432-016-9034-7

Analysis and design of parameters in soft docking of micro/small satellites

More info
  • ReceivedDec 18, 2016
  • AcceptedJan 17, 2017
  • PublishedApr 1, 2017

Abstract

Although substantial research has been conducted on the soft docking problem, the design of the docking mechanism is always conducted using experience. The challenge for conducting factor analysis and design lies in an accurate theoretical model, and the evaluation criteria of a successful docking. In this paper, the soft docking model of micro/small satellites is proposed using an analytical method and validated using a commercial FE package. The evaluation criterion of a successful docking is defined by considering the operational principle of the capturing mechanism used in micro (or small) paired satellites. The effect of the parameters on the soft docking result is discussed and their value domains are designed based on our proposed criteria of a successful docking.


Acknowledgment

This work was supported by National Natural Science Foundation of China (Grant Nos. 91216201, 51205403, 11404405).

  • Figure 1

    Soft docking of micro/small satellites. (a) Prior to docking; (b) chaser satellite during docking; (c) target satellite during docking.

  • Figure 2

    Operational principle of the capturing mechanism used in micro/small satellites. (a) Prior to capture and protectłinebreak (b) captured.

  • Figure 3

    (Color online) Comparison of the predicted results between the newly developed model and the commercial code LSDYNA. The velocity components along the respective $X$ (a) and $Y$ (b) directions of the paired satellites ($V_{1x}$, $V_{1y} $, $V_{2x}$, $V_{2y})$, (c) rotational angle $\theta _2 $ of the target satellite, and (d) relative docking velocity $V_{\rm rd}$.

  • Figure 4

    (Color online) Effect of the probe bending stiffness (EI) on velocities of the paired satellites. (a) Relative docking velocity ($V_{\rm rd})$, and (b) relative capturing velocity ($V_{\rm rc})$.

  • Figure 5

    (Color online) Effect of the cone angle ($\beta )$ on velocities of the paired satellites. (a) Relative docking velocity ($V_{\rm rd})$, and (b) relative capturing velocity ($V_{\rm rc} )$.

  • Figure 6

    (Color online) Effect of the friction coefficient ($\mu )$ on velocities of the paired satellites. (a) Relative docking velocity ($V_{\rm rd})$, and (b) relative capturing velocity ($V_{\rm rc})$.

  • Figure 7

    (Color online) Contact design domains. (a) Fitting chart and (b) contour chart in terms of probe bending stiffness (EI) and cone angle ($\beta )$; (c) fitting chart and (d) contour chart in terms of probe bending stiffness (EI) and friction coefficient ($\mu)$.

Copyright 2020 Science China Press Co., Ltd. 《中国科学》杂志社有限责任公司 版权所有

京ICP备18024590号-1