Propellant conveying system
阅读说明:本技术 一种推进剂输送系统 (Propellant conveying system ) 是由 孙礼杰 何鹏 任安宇 蒋赞 张�浩 于 2019-09-20 设计创作,主要内容包括:本发明公开了一种推进剂输送系统,包括贮箱,用于储存推进剂;输送管,输送管的第一端连接于贮箱的出料口,输送管的第二端连接于发动机的进料口;气动泵,设于输送管上,用于输送推进剂;高压气体部,用于储存高压气体;预压管,预压管的第一端与高压气体部的出气口相连,预压管的第二端与气动泵的进气口相连;预压管控制部,设于预压管上,用于开关预压管内的气体通道;增压管,增压管的第一端连接于气动泵的出气口,增压管的第二端与贮箱的进气口相连。本发明提高了推进剂的输送压力,对贮箱进行了增压,使整个增压输送系统体积小、重量轻。(The invention discloses a propellant delivery system, comprising a storage tank for storing propellant; the first end of the conveying pipe is connected with the discharge hole of the storage box, and the second end of the conveying pipe is connected with the feed inlet of the engine; the pneumatic pump is arranged on the conveying pipe and used for conveying the propellant; a high pressure gas section for storing high pressure gas; the first end of the pre-pressing pipe is connected with the air outlet of the high-pressure gas part, and the second end of the pre-pressing pipe is connected with the air inlet of the pneumatic pump; the pre-pressing pipe control part is arranged on the pre-pressing pipe and used for opening and closing a gas channel in the pre-pressing pipe; and the first end of the pressurizing pipe is connected to the air outlet of the pneumatic pump, and the second end of the pressurizing pipe is connected with the air inlet of the storage tank. The invention improves the conveying pressure of the propellant, and pressurizes the storage tank, so that the whole pressurizing conveying system has small volume and light weight.)
1. A propellant delivery system, comprising:
a tank for storing a propellant;
the first end of the conveying pipe is connected to the discharge hole of the storage box, and the second end of the conveying pipe is connected to the feed inlet of the engine;
the pneumatic pump is arranged on the conveying pipe and used for conveying the propellant;
a high pressure gas section for storing high pressure gas;
the first end of the pre-pressing pipe is connected with the air outlet of the high-pressure gas part, and the second end of the pre-pressing pipe is connected with the air inlet of the pneumatic pump;
the pre-pressing pipe control part is arranged on the pre-pressing pipe and used for opening and closing a gas channel in the pre-pressing pipe;
and the first end of the pressurizing pipe is connected to the air outlet of the pneumatic pump, and the second end of the pressurizing pipe is connected with the air inlet of the storage tank.
2. The propellant delivery system of claim 1 comprising a pre-cooling system, the pre-cooling system comprising:
the first end of the return pipe is connected with the feed port of the storage tank;
a first inlet of the backflow control valve is connected with the second end of the delivery pipe, a second outlet of the backflow control valve is connected with a feed inlet of the engine combustion chamber, and a third outlet of the backflow control valve is connected with the second end of the backflow pipe;
the first end of the pre-cooling pipe is connected with the air outlet of the high-pressure gas part, and the second end of the pre-cooling pipe is connected with the air inlet of the pneumatic pump;
and the pre-cooling pipe control part is arranged on the pre-cooling pipe and used for opening and closing a gas channel in the pre-cooling pipe.
3. The propellant delivery system of claim 2 wherein the pre-cooling tube control is a pre-cooling solenoid valve.
4. The propellant delivery system of claim 3 including a pre-cooled gas pressure relief device provided on the pre-cooling tube between the pre-cooled solenoid valve and the pneumatic pump.
5. The propellant delivery system of claim 4 wherein the pre-cooled gas pressure relief device comprises a first pressure relief valve and a first orifice plate, the first pressure relief valve and the first orifice plate being sequentially disposed on the pre-cooling tube between the pre-cooling solenoid valve and the pneumatic pump.
6. The propellant delivery system of claim 5 wherein the first pressure relief valve is an automatically adjusting pressure relief valve and the first orifice plate is a bowl.
7. The propellant delivery system of claim 1 wherein the pre-pressure tube control is a pre-pressure solenoid valve.
8. The propellant delivery system of claim 7 including a pre-pressurized gas pressure relief device disposed on the pre-pressurized tube between the pre-pressurized solenoid valve and the pneumatic pump.
9. The propellant delivery system of claim 8 wherein the pre-pressurized gas relief device comprises a second relief valve and a second orifice plate, the second relief valve and the second orifice plate being sequentially disposed on the pre-pressurized tube between the pre-pressurized solenoid valve and the pneumatic pump.
10. The propellant delivery system of claim 9 wherein the second pressure relief valve is an automatically adjusting pressure relief valve and the second orifice plate is a bowl.
11. The propellant delivery system of claim 1 wherein the reservoir and the delivery tube are each of thin-walled metal construction, and the outer walls of the reservoir and the delivery tube are each provided with a layer of thermal insulation.
12. The propellant delivery system of claim 1 wherein the booster duct is a metal thin-walled structure.
13. The propellant delivery system of claim 2 wherein the return tube is of metal thin-walled construction.
Technical Field
The invention belongs to the field of fuel conveying, and particularly relates to a propellant conveying system.
Background
Rocket engines rely on propellant for operation and the pressure of the propellant entering the engine needs to be high, so a delivery system is required to increase the inlet pressure of the propellant into the engine.
Rocket engine conveying systems generally work by utilizing a self-generated pressurization system, namely, a propellant storage tank of the same type is pressurized by utilizing gas formed by heating and evaporating the propellant.
However, when the requirement for the inlet pressure of the engine is higher in the face of a complex flight mission, the autogenous pressurization system cannot meet the requirement, the requirement for the high inlet pressure of the engine causes the mass of the pressurized gas and the large scale of the pressurization conveying system, the weight of the storage box structure is increased, and the structural efficiency of the carrier rocket is reduced.
Disclosure of Invention
In order to solve the problems, the invention provides a propellant conveying system, which aims to solve the technical problems of increasing the conveying pressure of the propellant and pressurizing a storage tank.
The technical scheme of the invention is as follows:
a propellant delivery system comprising:
a tank for storing a propellant;
the first end of the conveying pipe is connected to the discharge hole of the storage box, and the second end of the conveying pipe is connected to the feed inlet of the engine;
the pneumatic pump is arranged on the conveying pipe and used for conveying the propellant;
a high pressure gas section for storing high pressure gas;
the first end of the pre-pressing pipe is connected with the air outlet of the high-pressure gas part, and the second end of the pre-pressing pipe is connected with the air inlet of the pneumatic pump;
the pre-pressing pipe control part is arranged on the pre-pressing pipe and used for opening and closing a gas channel in the pre-pressing pipe;
and the first end of the pressurizing pipe is connected to the air outlet of the pneumatic pump, and the second end of the pressurizing pipe is connected with the air inlet of the storage tank.
The conveying pressure of the propellant is improved, the pressurization requirement on the storage tank is met, the weight and the volume of the whole system are reduced, and the pneumatic pump is safe and reliable.
According to an embodiment of the present invention, the system includes a pre-cooling system, and the pre-cooling system includes:
the first end of the return pipe is connected with the feed port of the storage tank;
a first inlet of the backflow control valve is connected with the second end of the conveying pipe, a second outlet of the backflow control valve is connected with a feed port of the engine, and a third outlet of the backflow control valve is connected with the second end of the backflow pipe;
the first end of the pre-cooling pipe is connected with the air outlet of the high-pressure gas part, and the second end of the pre-cooling pipe is connected with the air inlet of the pneumatic pump;
and the pre-cooling pipe control part is arranged on the pre-cooling pipe and used for opening and closing a gas channel in the pre-cooling pipe.
The engine can be circularly precooled, the normal work of the engine is ensured, the propellant can flow back, and the utilization rate is improved.
According to an embodiment of the present invention, the pre-cooling pipe control part is a pre-cooling solenoid valve. The electromagnetic valve is a common gas on-off control element, and is simple and practical.
According to an embodiment of the invention, the pre-cooling system comprises a pre-cooling gas pressure reducing device, wherein the pre-cooling gas pressure reducing device is arranged on the pre-cooling pipe between the pre-cooling electromagnetic valve and the pneumatic pump.
According to an embodiment of the present invention, the precooling gas pressure reducing device includes a first pressure reducing valve and a first orifice plate, and the first pressure reducing valve and the first orifice plate are sequentially disposed on the precooling pipe between the precooling solenoid valve and the pneumatic pump. The pressure reducing valve and the perforated plate are common pressure reducing devices, and realize pressure reduction and steady flow of gas.
According to an embodiment of the present invention, the first pressure reducing valve is an automatic adjusting pressure reducing valve, and the first orifice plate is a bowl-shaped structure.
According to an embodiment of the present invention, the pre-pressure pipe control portion is a pre-pressure solenoid valve. The electromagnetic valve is a common gas on-off control element, and is simple and practical.
According to an embodiment of the present invention, the pneumatic pump further comprises a pre-compressed gas pressure reducing device, and the pre-compressed gas pressure reducing device is disposed on the pre-compressed pipe between the pre-compressed solenoid valve and the pneumatic pump.
According to an embodiment of the present invention, the pre-pressurized gas pressure reducing device includes a second pressure reducing valve and a second orifice plate, and the second pressure reducing valve and the second orifice plate are sequentially disposed on the pre-pressurized pipe between the pre-pressurized solenoid valve and the pneumatic pump. The pressure reducing valve and the perforated plate are common pressure reducing devices, and realize pressure reduction and steady flow of gas.
According to an embodiment of the present invention, the second pressure reducing valve is an automatic adjusting pressure reducing valve, and the second orifice plate is a bowl-shaped structure.
According to one embodiment of the invention, the storage tank and the conveying pipe are both of metal thin-wall structures, and the outer walls of the storage tank and the conveying pipe are both provided with heat insulation layers. The metal thin-wall structure can reduce the weight.
According to an embodiment of the invention, the pressure inlet pipe is of a metal thin-wall structure. The metal thin-wall structure can reduce the weight.
According to an embodiment of the present invention, the return pipe is a metal thin-wall structure. The metal thin-wall structure can reduce the weight.
Due to the adoption of the technical scheme, compared with the prior art, the invention has the following advantages and positive effects:
(1) in one embodiment of the invention, the pneumatic pump is arranged to convey the propellant, the gas at the gas outlet of the pneumatic pump is conveyed into the storage tank through the pressurization pipe and is used for pressurizing the propellant, the conveying pressure of the propellant is improved, the pressurization requirement on the storage tank is realized, the gas after the pneumatic pump is recycled and utilized for pressurizing the storage tank, the high-efficiency utilization of the gas is realized, special pressurization equipment is not required to be arranged for the storage tank independently, the weight and the volume of the whole system are further reduced, and the pneumatic pump is safe and reliable.
(2) In one embodiment of the invention, the precooling system is arranged and comprises a return pipe, a backflow control valve, a precooling pipe and a precooling control part, and the propellant circularly flows through the engine, so that the circulating precooling of the engine is realized, the normal work of the engine is ensured, the propellant can flow back, and the utilization rate is improved.
(3) In one embodiment of the invention, the precooling gas pressure reducing device and the prepressing gas pressure reducing device are arranged, so that the functions of reducing the pressure of the high-pressure gas and stabilizing the gas pressure are achieved.
Drawings
The following detailed description of embodiments of the invention is provided in conjunction with the appended drawings, in which:
FIG. 1 is a schematic diagram of the overall construction of a propellant delivery system of the present invention;
description of reference numerals:
1: a storage tank; 2: a pneumatic pump; 3: a delivery pipe; 4: a return pipe; 5: a reflux control valve; 6: an engine; 7: a high pressure gas section; 8: a precooling electromagnetic valve; 9: prepressing the electromagnetic valve; 10: a first pressure reducing valve; 11: a second pressure reducing valve; 12: a first orifice plate; 13: a second orifice plate; 14: and (4) pressurizing the pipe.
Detailed Description
A propellant delivery system in accordance with the present invention is described in further detail below with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are all used in a non-precise ratio for the purpose of facilitating and distinctly aiding in the description of the embodiments of the invention.
Referring to fig. 1, the present invention provides a propellant delivery system comprising a
The pre-cooling system is used for pre-cooling the
Further, the device comprises a precooling gas pressure reducing device, and the precooling gas pressure reducing device is arranged on a precooling pipe between the precooling electromagnetic valve 8 and the
Further, the first
Further, the device comprises a pre-pressing gas pressure reducing device, wherein the pre-pressing gas pressure reducing device is arranged on the pre-pressing pipe between the pre-pressing electromagnetic valve 9 and the
Further, the second
The following further illustrates the specific working of the present invention:
firstly, precooling an
When the rocket is ignited, the precooling electromagnetic valve 8 is controlled to be closed, the prepressing electromagnetic valve 9 is opened, high-pressure gas in the high-
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, it is still within the scope of the present invention if they fall within the scope of the claims of the present invention and their equivalents.
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