Abstract: With the development of cryogenic rocket carrying capacity, the requirement of filling flow of propellant is increasing. The original small diameter filling pipeline does not meet the requirements of large flow filling, a series of large diameter cryogenic tube must be designed. It is faced with problems such as large cryogenic tube assembly technology, thermal insulation joint design technology, etc. This paper introduces a new type of multi-layer thermal insulation hose, which is designed to adapt to the change of the position of the propellant filling connector in a specific narrow cabin, including the design of the overall scheme, the calculation of the key parameters and so on. The method has been applied to the design and manufacture of a propellant conveying pipeline, and has been tested by the actual working conditions, which verifies the correctness of the design method and has a certain reference value for the design of similar cryogenic equipments.