The invention provides an assembly process of a spacecraft, and belongs to the technical field of spacecraft production and assembly. The technical problem that an existing spacecraft assembling process is low in efficiency is solved. The process comprises the following steps of cabin plate split charging, wherein functional elements are fixedly installed on a + Z cabin plate, a-Z cabin plate, a + X partition plate, a-X partition plate, a + X cabin plate, a-X cabin plate, a + Y cabin plate and a-Y cabin plate correspondingly; assembly before testing: wherein the-Z cabin plate, the + X partition plate, the-X partition plate, the + Z cabin plate, the + X cabin plate and the-X cabin plate are sequentially spliced and spliced through connecting pieces; a normal-pressure thermal cycle test: under a normal-pressure condition, the spacecraft which is assembled before testing is exposed to a preset high-low temperature alternating test environment for testing; and cabin sealing and assembling: the + Y cabin plate and the-Y cabin plate to the spacecraft subjected to the normal-pressure thermal cycle test are assembled by a connecting piece. According to the assembly process of the spacecraft, the assembly quality of the spacecraft can be guaranteed while the efficiency is improved.
本发明提供了一种航天器的组装工艺,属于航天器生产装配技术领域。它解决了现有航天器的组装工艺效率较低技术问题。本航天器的组装工艺,包括如下步骤:舱板分装:将功能元件安装固定在对应的+Z舱板、‑Z舱板、+X隔板、‑X隔板、+X舱板、‑X舱板、+Y舱板和‑Y舱板上;测前合装:将‑Z舱板、+X隔板、‑X隔板、+Z舱板、+X舱板和‑X舱板依次拼合并通过连接件形成拼装;常压热循环试验:在常压条件下,将测前合装完成的航天器暴露于预设的高低温交替试验环境中进行的试验;封舱合装:将+Y舱板和‑Y舱板通过连接件拼装至完成常压热循环试验的航天器上。本航天器的组装工艺可在提高效率的同时保证航天器的组装质量。
Assembly process of spacecraft
一种航天器的组装工艺
2022-02-18
Patent
Electronic Resource
Chinese