Method for controlling pressure of propellant storage box

A propellant storage tank and pressure technology, which is applied in the direction of fluid pressure control, non-electric variable control, control/regulation system, etc., can solve the problems that cannot meet the requirements of the test task book

Active Publication Date: 2013-07-24
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the existing whole process from the pre-stabilization stage to the overload stage, the booster valve during boosting is completely controlled automatically by the program. If there is a deviation in the adjustment calculation, it may not meet the requirements of the test task book

Method used

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  • Method for controlling pressure of propellant storage box
  • Method for controlling pressure of propellant storage box
  • Method for controlling pressure of propellant storage box

Examples

Experimental program
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Embodiment

[0101] A method of controlling the pressure of a propellant tank comprising the steps of:

[0102] 1] Connect the propellant pressurization system;

[0103] 2] Start the control center, and realize the control of the pump inlet pressure according to the pump inlet pressure curve required by the user (mission statement): the pump inlet pressure curve includes the pre-stabilization section, boost section, overload section and deflation section connected in sequence: as figure 2 As shown in the mission statement, the requirements of the task book are: the inlet pressure is stable at a+0.05MPa in 0~150 seconds, we call this period of time the pre-stabilization period; the inlet pressure increases from aMPa to bMPa in 150~210 seconds, we call this period of time boost section; 210 seconds to 600 seconds, the inlet pressure is kept at bMPa, we call this period of time overload; after 600 seconds, the main engine shuts down, and the inlet pressure needs to be reduced to cMPa, and th...

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Abstract

The invention relates to a method for controlling the pressure of a propellant storage box. The method comprises the following steps: (1) establishing a boosting system; and (2) starting a control center, realizing control over the pump inlet pressure according to a pump inlet pressure curve required by a user, and realizing control over a front stable segment, a boosting segment, an overload segment, a discharging segment and a back stable segment in sequence, wherein the pump inlet pressure curve comprises the front stable segment, the boosting segment, the overload segment and the discharging segment which are connected in sequence. According to the method, specific to the aim of realizing stability from the front stable segment to the overload segment within a time interval required by an assignment book by accurately controlling the pump inlet pressure, factors such as the pressure reducer outlet pressure, propellant flow and calculated flow adjusting coefficient influencing the boosting time of a propellant boosting system are researched, so that the problem of corresponding requirement on the test pump inlet pressure and time of an engine is solved, the outlet boosting coefficient of a pore plate is analyzed, calculated and optimized, and an accurate control method is concluded.

Description

technical field [0001] The present invention relates to a method of controlling the pressure of a propellant tank. Background technique [0002] The engine test needs to ensure that the inlet pressure of the oxidizer and fuel pump meets the requirements of the test task specification. During the test run, the inlet pressure of the pump is mainly guaranteed by the pressure of the propellant tank, and the control accuracy of the pressure of the propellant tank determines the control accuracy of the pump inlet pressure. The relationship between pump inlet pressure and propellant tank pressure is determined by Equation (1). [0003] P oy =P oyq +△P y -0.01425×(H 0 +H sh ) (1) [0004] in: [0005] P oy — pressure value of propellant tank at a certain moment, MPa; [0006] P oyq —The pump inlet pressure value at the corresponding moment, MPa; [0007] ΔP y —Corresponding time flow resistance value, MPa; [0008] h 0 —The corresponding pipeline drop when the liqui...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D16/00
Inventor 程磊王广飚赵建军赵政社寇兴华李陆昊王晓华史超
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST
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