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Combined piston type liquid propellant storage tank

A liquid propellant and combined piston technology, applied in jet propulsion devices, rocket engine devices, machines/engines, etc., can solve the problems of low emptying efficiency, low space utilization, and heavy weight, and achieve tight gas-liquid isolation, Light weight and improved internal space utilization

Inactive Publication Date: 2021-08-13
XIAN AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the technical problems of heavy weight, low space utilization rate and low emptying efficiency in the existing liquid propellant storage tank, and propose a combined piston type liquid propellant storage tank

Method used

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  • Combined piston type liquid propellant storage tank
  • Combined piston type liquid propellant storage tank
  • Combined piston type liquid propellant storage tank

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Embodiment Construction

[0025] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0026] Such as figure 1 As shown, a combined piston type liquid propellant storage tank is composed of an air chamber head 1, a combined piston assembly 2, a cylinder body 3, and a liquid chamber head 4; an air chamber head 1, a cylinder body 3, and a liquid chamber The head 4 is made of the same metal material and welded from left to right to form a closed cavity. The metal material can be titanium alloy, aluminum alloy or stainless steel; the combined piston assembly 2 is assembled in the inner cylinder of the closed cavity On the surface of the body 3, it can be located at any position inside the cylinder; the left side surface of the combined piston assembly 2 forms an air cavity space 9 between the cylinder body 3 and the air cavity head 1, and the right side surface of the combined piston assembly 2 A closed liquid chamber space 10 is fo...

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Abstract

The invention relates to a liquid propellant storage tank, in particular to a combined piston type liquid propellant storage tank. The combined piston type liquid propellant storage tank aims at solving the technical problems that an existing propellant storage tank is large in weight, low in space utilization rate and low in emptying efficiency. The combined piston type liquid propellant storage tank reciprocates along a barrel body through the combined piston assembly to realize the liquid feeding and discharging functions of the storage tank, According to the combined piston assembly, gas-liquid isolation is achieved through a flexible film, the flexible film is tightly attached to a gas cavity end socket and a liquid cavity end socket in the full filling state and the emptying state, the unavailable storage space of the storage box shell and the non-discharging amount of liquid are effectively reduced, the utilization rate of the internal space of the storage box and the emptying efficiency are improved, and meanwhile the weight of the storage box is lighter.

Description

technical field [0001] The invention relates to a liquid propellant storage tank, in particular to a combined piston type liquid propellant storage tank. Background technique [0002] Liquid propellant storage tanks are used in liquid rocket power systems, and their main function is to store and manage liquid propellants. When the liquid propellant storage tank is working, the storage tank delivers continuous liquid propellant without air inclusion to the downstream system of the storage tank under the action of the upstream squeezed gas. As the requirements for the lightweight and miniaturization of the liquid power system are getting higher and higher, the internal space of the liquid power system is becoming more and more compact, the installation space of the storage tank is shrinking, and the shape is becoming more and more complex. Compared with the spherical structure and the spherical conical structure, the elongated tank structure with a relatively large length-to-...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/60F02K9/50F02K9/44
CPCF02K9/605F02K9/50F02K9/44
Inventor 苏浩苏志一宁继荣刘炜邢丽静邓永锋郝方楠
Owner XIAN AEROSPACE PROPULSION INST
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