The embodiment of the invention provides a propellant filling system and a propellant filling method, the propellant filling system and the propellant filling method are used for propellant filling ofa carrier rocket, and the system comprises a heat exchanger, a coolant filling pipeline, a propellant filling pipeline and a receiving system pipeline; wherein the heat exchanger comprises a heat exchanger shell pass and a heat exchanger tube pass, the heat exchanger shell pass is connected with the coolant filling pipeline, and the heat exchanger tube pass is connected with the propeller fillingpipeline and the receiving system pipeline; a coolant is fed to the heat exchanger shell pass through the coolant filling pipeline. The propellant at the standard boiling point is conveyed to the tube pass of the heat exchanger through a propellant filling pipeline; the heat exchanger is used for densifying the propellant through a coolant to obtain a densified propellant; and a densification propellant is conveyed to a preset receiving system through a receiving system pipeline. The propellant is densified, so that the total amount of the effective propellant loaded by the carrier rocket isincreased, and the rocket launching cost is reduced.

    本发明实施例提供了一种推进剂加注系统和一种推进剂加注方法,其用于运载火箭的推进剂加注,所述系统包括换热器、冷却剂加注管道、推进剂加注管道、以及接收系统管道;换热器包括换热器壳程以及换热器管程,换热器壳程与冷却剂加注管道连接,换热器管程分别连接推进器加注管道以及接收系统管道;冷却剂通过冷却剂加注管道向换热器壳程输送;处于标准沸点下的推进剂通过推进剂加注管道向换热器管程输送;换热器用于通过冷却剂,致密化处理推进剂,得到致密化推进剂;致密化推进剂通过接收系统管道向预设的接收系统输送。通过对推进剂进行致密化处理,提高运载火箭装载的有效推进剂总量,减低火箭发射成本。


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    Title :

    Propellant filling system and propellant filling method


    Additional title:

    一种推进剂加注系统和一种推进剂加注方法


    Contributors:
    LI AIHUA (author)

    Publication date :

    2020-11-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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