Liquid launch vehicle tank pressurization method and pressurization system
By obtaining the inlet pressure and changes of the propellant pump in the liquid launch vehicle tank, the pressure after the delay time of the solenoid valve is estimated. Combined with the control of the opening and closing of the solenoid valve within the set pressure range, the problems of reduced rocket carrying capacity and control complexity caused by pressurization margin are solved, and refined control and improved carrying capacity are achieved.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- BEIJING GALAXY POWER EQUIP TECH CO LTD
- Filing Date
- 2026-04-17
- Publication Date
- 2026-07-17
AI Technical Summary
Existing technologies require a large pressurization margin to compensate for pressure loss and fluctuations when pressurizing the propellant tanks of liquid-fueled launch vehicles, resulting in a decrease in rocket carrying capacity and an increase in control complexity.
By acquiring the average pressure and pressure changes at the propellant pump inlet, the pressure after the solenoid valve delay time is estimated. Combined with the set pressure range, the opening and closing of the solenoid valve is controlled, reducing the pressure margin and achieving fine control.
It improves the rocket's carrying capacity and control precision, reduces the system's pressurization margin and initial air cushion volume, and is suitable for propellant pump inlet pressure regulation in large cryogenic liquid rockets.
Smart Images
Figure CN122407402A_ABST