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Liquid oxygen methane rocket and drop pressure type pressurization design method for liquid oxygen methane rocket storage tank

A technology of liquid oxygen methane and design method, which is applied in rocket engine devices, mechanical equipment, jet propulsion devices, etc., can solve problems such as adaptability limitation and rocket loss of carrying capacity, and achieve the effect of improving carrying capacity and simplifying structural design.

Active Publication Date: 2019-10-15
BEIJING LANDSPACETECH CO LTD
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to self-generated pressurization using propellant as the pressurized medium, the rocket will lose a certain amount of carrying capacity, and there are certain limitations in adaptability

Method used

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  • Liquid oxygen methane rocket and drop pressure type pressurization design method for liquid oxygen methane rocket storage tank
  • Liquid oxygen methane rocket and drop pressure type pressurization design method for liquid oxygen methane rocket storage tank
  • Liquid oxygen methane rocket and drop pressure type pressurization design method for liquid oxygen methane rocket storage tank

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Embodiment Construction

[0029] Various exemplary embodiments of the present invention will now be described in detail. The detailed description should not be considered as a limitation of the present invention, but rather as a more detailed description of certain aspects, features and embodiments of the present invention.

[0030] It should be understood that the terminology described in the present invention is only used to describe specific embodiments, and is not used to limit the present invention. In addition, regarding the numerical ranges in the present invention, it should be understood that the upper and lower limits of the range and every intermediate value therebetween are specifically disclosed. Each smaller range between any stated value or intervening value in a stated range and any other stated value or intervening value in a stated range is encompassed within the invention. The upper and lower limits of these smaller ranges may independently be included or excluded from the range.

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Abstract

The invention provides a liquid oxygen methane rocket and a drop pressure type pressurization design method for a liquid oxygen methane rocket storage tank. The drop pressure type pressurization design method comprises the steps that at the first period of work of a main engine, the storage tank is pressurized in a self-generation pressurization mode; and after the main engine stops working, in atleast part of time in the second period of traveling engines, the storage tank is pressurized by at least one of evaporation of a cryogenic propellant and gas expansion in the storage tank. In the drop pressure type pressurization design method for the liquid oxygen methane rocket storage tank, the difference of pressurization pressures needed by inlets of the main engine and the traveling engines is fully utilized, self-generation pressurization systems of the traveling engines are canceled, rocket structure design is simplified, and rocket carrying capacity is promoted.

Description

technical field [0001] The invention belongs to the field of pressurized delivery of storage tanks, and relates to a novel rocket propellant liquid oxygen methane self-generated pressurization system, in particular to a self-generated pressurized scheme in a flight state under the combination of a main engine engine and a traveling plane. Background technique [0002] The pressurization system is used to provide the pressure of the air pillow of the liquid rocket propellant tank. The pressurized gas enters the propellant tank, expands and occupies the space after the propellant is discharged, and generates working pressure on the liquid propellant. In order to meet the normal working pressure of the propellant inlet required for engine starting and flight; to meet the internal pressure requirements required by the thin-walled structure of the rocket propellant tank, and to ensure that the tank structure has sufficient strength and rigidity. [0003] The pressurization method...

Claims

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Application Information

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IPC IPC(8): F02K9/60
CPCF02K9/60F02K9/605
Inventor 杜正刚张铮智李秀明郭凤明陈志愿
Owner BEIJING LANDSPACETECH CO LTD
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