Thermal performance test of vacuum composite insulation material for Cryogenic Rocket Tank Based on cryocooler
- Paper number
IAC-20,D2,5,7,x56967
- Author
Mr. Shaohua Zhang, China, China Academy of Launch Vehicle Technology(CALT)
- Year
2020
- Abstract
Based on the guide bar calorimetric method, a testing platform for the vacuum multilayer insulation material of the liquid hydrogen storage tank was built with the cryocooler as the cold source. The vacuum degree of the testing system was designed as 5e-4Pa. The experiment was carried out in a vacuum tank with a diameter of 1m. The insulation component was wrapped outside the uniform temperature cold cylinder. The outer diameter of the cold cylinder was 146mm and the height was 220mm. The guide bar was connected with the cold cylinder and supported the cold cylinder. The outer diameter of the heat tube is 252mm, and the heat tube can be heated to 400k, which is used to provide the boundary temperature. The apparent thermal conductivity of several multilayer insulation components with different structures in the temperature range of 40k-90k is obtained, which provides support for the design of long-term on orbit storage system of liquid hydrogen.
- Abstract document
- Manuscript document
IAC-20,D2,5,7,x56967.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.