Scholarlink

Based on the requirement of multiple satellites simultaneous launching into MEO or GEO, a new propulsion module structure is proposed for one main satellite and multiple small satellites. The propulsion module is only consists of only main structure and propulsion system, and the main control commands of the propulsion module are send by the main satellite. The propulsion module structure is composed of a cone bearing cylinder, a column bearing cylinder, internal storage tank installation brackets and partitions. The upper part of the cone cylinder is the installation surface for the main satellite, and the outer wall of the1 columnar cylinder can be used for the installation and arrangement of small satellites. After the propulsion module entered the predetermined orbit, it controls separate the small satellites first, and then separates the main satellite. The configuration design was conducted for the propulsion module, a finite element model of the propulsion module was established, and the reasonability of the design was verified using a mechanical simulation method. The results show that the propulsion module has the characteristics of light weight, low center of mass, good stiffness, good versatility and strong adaptability.

错误：搜索内容不能为空，请输入英文关键词
错误：关键词超出字数限制，请精简
高级检索

Structucal Design of a Propulsion Module Suitable for Multi Satellites Launch to Medium and High Orbit

  • 会议论文

  • 发表日期：

    2026年

查看全文
  • Zhao Chuan,
  • Cai Yibo,
  • Qi Kexin,
  • Zhang Xiaotong,
  • Zhou Yiqian,
  • Yin jian

摘要

Based on the requirement of multiple satellites simultaneous launching into MEO or GEO, a new propulsion module structure is proposed for one main satellite and multiple small satellites. The propulsion module is only consists of only main structure and propulsion system, and the main control commands of the propulsion module are send by the main satellite. The propulsion module structure is composed of a cone bearing cylinder, a column bearing cylinder, internal storage tank installation brackets and partitions. The upper part of the cone cylinder is the installation surface for the main satellite, and the outer wall of the1 columnar cylinder can be used for the installation and arrangement of small satellites. After the propulsion module entered the predetermined orbit, it controls separate the small satellites first, and then separates the main satellite. The configuration design was conducted for the propulsion module, a finite element model of the propulsion module was established, and the reasonability of the design was verified using a mechanical simulation method. The results show that the propulsion module has the characteristics of light weight, low center of mass, good stiffness, good versatility and strong adaptability.