CN114136635B - Large-flow quick-response solid-liquid rocket engine ground conveying system - Google Patents
Large-flow quick-response solid-liquid rocket engine ground conveying system Download PDFInfo
- Publication number
- CN114136635B CN114136635B CN202111477389.5A CN202111477389A CN114136635B CN 114136635 B CN114136635 B CN 114136635B CN 202111477389 A CN202111477389 A CN 202111477389A CN 114136635 B CN114136635 B CN 114136635B
- Authority
- CN
- China
- Prior art keywords
- pipeline
- pressure
- valve
- supply unit
- solenoid valve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
本申请涉及航空航天技术领域,尤其是涉及一种大流量快速响应固液火箭发动机地面输送系统。大流量快速响应固液火箭发动机地面输送系统包括推进剂存储单元、高压供给单元以及低压供给单元;推进剂存储单元的输出端分别与高压供给单元和低压供给单元连通;高压供给单元和低压供给单元的输出端分别通过主路与燃烧室连通。高压供给单元与低压供给单元是一种并联排布结构,本申请巧妙地将高压供给单元和低压供给单元结合到一起,在试验过程中可以灵活切换不同的供给单元,即可以满足燃烧室低压的工况,又能够满足燃烧室高压的工况,从而提高了大流量快速响应固液火箭发动机地面输送系统的效率。
The present application relates to the field of aerospace technology, in particular to a large-flow fast-response solid-liquid rocket engine ground conveying system. The large-flow and fast-response solid-liquid rocket engine ground transportation system includes a propellant storage unit, a high-pressure supply unit and a low-pressure supply unit; the output ends of the propellant storage unit are respectively communicated with the high-pressure supply unit and the low-pressure supply unit; the high-pressure supply unit and the low-pressure supply unit The output ends of the two are respectively communicated with the combustion chamber through the main road. The high-pressure supply unit and the low-pressure supply unit are in a parallel arrangement. This application cleverly combines the high-pressure supply unit and the low-pressure supply unit. During the test, different supply units can be flexibly switched to meet the requirements of the low-pressure combustion chamber. It can also meet the working condition of high pressure in the combustion chamber, thereby improving the efficiency of the ground transportation system of the solid-liquid rocket engine with large flow and rapid response.
Description
技术领域technical field
本申请涉及航空航天技术领域,尤其是涉及一种大流量快速响应固液火箭发动机地面输送系统。The present application relates to the field of aerospace technology, in particular to a large-flow fast-response solid-liquid rocket engine ground conveying system.
背景技术Background technique
目前,固液混合火箭发动机地面输送系统包含气路和液路。其中,气路具有两个作用,一是作为增压路,给贮箱增压,使得贮箱保持一定压力;二是作为吹除管路,将大量惰性氮气吹入发动机,从而吹熄发动机,保证点火试验结束后的推进剂的安全熄灭。液路通常由贮箱增压,经过一系列阀门,将液态推进剂送入燃烧室,与固体推进剂进行反应,现有的为了提高燃烧室内的压强,常在液路中加入电动泵,将贮箱中的低压液体再次增压,从而保证液体推进剂以一定流量进入高压的燃烧室,然后进行反应。At present, the ground delivery system of the solid-liquid hybrid rocket engine includes a gas circuit and a liquid circuit. Among them, the gas circuit has two functions, one is as a pressurizing circuit, pressurizing the storage tank, so that the storage tank maintains a certain pressure; the other is as a blowing pipe, blowing a large amount of inert nitrogen into the engine to blow out the engine, To ensure the safe extinguishing of the propellant after the ignition test is completed. The liquid path is usually pressurized by the storage tank. After a series of valves, the liquid propellant is sent into the combustion chamber to react with the solid propellant. In order to increase the pressure in the combustion chamber, an electric pump is often added to the liquid path. The low-pressure liquid in the tank is pressurized again to ensure that the liquid propellant enters the high-pressure combustion chamber at a certain flow rate, and then reacts.
然而由于燃烧室的压力工况不同,电动泵输送系统在燃烧室压力较低时,效率不高,导致电动泵输送系统无法满足燃烧室压力较低的情况。However, due to the different pressure conditions of the combustion chamber, the efficiency of the electric pump conveying system is not high when the combustion chamber pressure is low, resulting in the electric pump conveying system unable to meet the low pressure of the combustion chamber.
因此,亟需一种大流量快速响应固液火箭发动机地面输送系统在一定程度上以解决现有技术中存在的技术问题。Therefore, there is an urgent need for a large-flow and fast-response solid-liquid rocket motor ground transportation system to a certain extent to solve the technical problems existing in the prior art.
发明内容SUMMARY OF THE INVENTION
本申请的目的在于提供一种大流量快速响应固液火箭发动机地面输送系统,以在一定程度上解决现有技术中采用电动泵输送系统,无法满足燃烧室压力较低的工况的技术问题。The purpose of the present application is to provide a large-flow fast-response solid-liquid rocket engine ground conveying system, so as to solve the technical problem that the electric pump conveying system in the prior art cannot meet the working condition of low combustion chamber pressure to a certain extent.
本申请提供了一种大流量快速响应固液火箭发动机地面输送系统,用于将推进剂推进至燃烧室;大流量快速响应固液火箭发动机地面输送系统包括推进剂存储单元、高压供给单元以及低压供给单元;The application provides a large-flow fast-response solid-liquid rocket engine ground transportation system for propelling propellant to the combustion chamber; the large-flow fast-response solid-liquid rocket engine ground transportation system includes a propellant storage unit, a high-pressure supply unit and a low-pressure supply unit;
所述推进剂存储单元的输出端分别与所述高压供给单元和所述低压供给单元连通;The output ends of the propellant storage unit are respectively communicated with the high pressure supply unit and the low pressure supply unit;
所述高压供给单元和所述低压供给单元的输出端分别通过主路与所述燃烧室连通。The output ends of the high pressure supply unit and the low pressure supply unit are respectively communicated with the combustion chamber through a main circuit.
在上述技术方案中,进一步地,所述高压供给单元包括高压管路;In the above technical solution, further, the high-pressure supply unit includes a high-pressure pipeline;
所述高压管路上依次设置于第一电磁阀、第一压力传感器、电动泵、第二压力传感器以及第一单向阀;The high-pressure pipeline is sequentially arranged on the first solenoid valve, the first pressure sensor, the electric pump, the second pressure sensor and the first one-way valve;
所述第一电磁阀靠近所述推进剂存储单元,所述第一单向阀靠近所述燃烧室。The first solenoid valve is proximate the propellant storage unit, and the first one-way valve is proximate the combustion chamber.
在上述技术方案中,进一步地,所述低压供给单元包括低压管路;In the above technical solution, further, the low pressure supply unit includes a low pressure pipeline;
所述低压管路上依次设置有第二电磁阀和第二单向阀;所述第二电磁阀靠近所述推进剂存储单元,所述第二单向阀靠近所述燃烧室。A second solenoid valve and a second one-way valve are sequentially arranged on the low-pressure pipeline; the second solenoid valve is close to the propellant storage unit, and the second one-way valve is close to the combustion chamber.
在上述技术方案中,进一步地,所述推进剂存储单元包括贮箱以及推进剂供给管路;In the above technical solution, further, the propellant storage unit includes a storage tank and a propellant supply pipeline;
所述推进剂供给管路上依次设置有过滤器、电动球阀、第一手阀以及流量计;所述过滤器靠近所述贮箱,所述流量计靠近所述高压供给单元或所述低压供给单元;A filter, an electric ball valve, a first hand valve and a flowmeter are arranged in sequence on the propellant supply pipeline; the filter is close to the storage tank, and the flowmeter is close to the high-pressure supply unit or the low-pressure supply unit ;
所述贮箱上设置有第三压力传感器和加注泻出阀。The storage tank is provided with a third pressure sensor and a filling and discharging valve.
在上述技术方案中,进一步地,所述主路上依次设置有第一调节阀、第三电磁阀、第三单向阀以及第六压力传感器;In the above technical solution, further, the main road is provided with a first regulating valve, a third solenoid valve, a third one-way valve and a sixth pressure sensor in sequence;
所述第一调节阀靠近所述高压供给单元的输出端或所述低压供给单元的输出端;所述第六压力传感器靠近所述燃烧室。The first regulating valve is close to the output end of the high pressure supply unit or the output end of the low pressure supply unit; the sixth pressure sensor is close to the combustion chamber.
在上述技术方案中,进一步地,还包括增压单元;所述增压单元包括气瓶以及增压管路,所述增压管路的输入端与所述气瓶连通,且输出端与所述推进剂存储单元连通;In the above technical solution, it further includes a pressurizing unit; the pressurizing unit includes a gas cylinder and a pressurizing pipeline, the input end of the pressurizing pipeline is communicated with the gas cylinder, and the output end is connected to the gas cylinder. the propellant storage unit is connected;
所述增压管路上依次设置有第四压力传感器、第四电磁阀、第一减压器、第二手阀以及第五电磁阀;A fourth pressure sensor, a fourth solenoid valve, a first pressure reducer, a second hand valve and a fifth solenoid valve are sequentially arranged on the boosting pipeline;
所述第四压力传感器靠近所述气瓶,所述第五电磁阀靠近所述推进剂存储单元。The fourth pressure sensor is near the gas cylinder and the fifth solenoid valve is near the propellant storage unit.
在上述技术方案中,进一步地,还包括吹除单元,所述吹除单元包括吹除管路;In the above technical solution, further, a blow-off unit is further included, and the blow-off unit includes a blow-off pipeline;
所述吹除管路的输入端与所述增压管路连通,且输出端与所述燃烧室连通;The input end of the blow-off pipeline is communicated with the pressurization pipeline, and the output end is communicated with the combustion chamber;
所述吹除管路上依次设置有第三压力传感器、第三手阀、第五压力传感器、第六电磁阀以及第四单向阀;A third pressure sensor, a third hand valve, a fifth pressure sensor, a sixth solenoid valve and a fourth one-way valve are sequentially arranged on the blow-off pipeline;
所述第三压力传感器靠近所述第四电磁阀,所述第四单向阀靠近所述燃烧室。The third pressure sensor is close to the fourth solenoid valve, and the fourth one-way valve is close to the combustion chamber.
在上述技术方案中,进一步地,还包括循环单元,所述循环单元包括循环管路;In the above technical solution, further, a circulation unit is further included, and the circulation unit includes a circulation pipeline;
所述循环管路的一端与推进剂存储单元连通,另一端与所述主路连通;One end of the circulation pipeline is communicated with the propellant storage unit, and the other end is communicated with the main circuit;
所述循环管路上依次设置有第五单向阀、第七电磁阀、第二调节阀以及缓冲器;A fifth one-way valve, a seventh solenoid valve, a second regulating valve and a buffer are sequentially arranged on the circulation pipeline;
所述第五单向阀靠近所述推进剂存储单元,所述缓冲器靠近所述高压供给单元。The fifth one-way valve is adjacent to the propellant storage unit, and the buffer is adjacent to the high pressure supply unit.
在上述技术方案中,进一步地,还包括辅助单元,所述辅助单元包括辅助管路;In the above technical solution, further, an auxiliary unit is further included, and the auxiliary unit includes an auxiliary pipeline;
所述辅助管路上设置有靠近所述第七电磁阀的第八电磁阀以及靠近所述主路的第五单向阀。The auxiliary pipeline is provided with an eighth solenoid valve close to the seventh solenoid valve and a fifth check valve close to the main circuit.
在上述技术方案中,进一步地,还包括旁通管路;所述旁通管路的一端与所述主路连通,所述旁通管路上设置有第四手阀。In the above technical solution, a bypass pipeline is further included; one end of the bypass pipeline is communicated with the main pipeline, and a fourth hand valve is arranged on the bypass pipeline.
与现有技术相比,本申请的有益效果为:Compared with the prior art, the beneficial effects of the present application are:
本申请提供的一种大流量快速响应固液火箭发动机地面输送系统,用于将推进剂推进至燃烧室;大流量快速响应固液火箭发动机地面输送系统包括推进剂存储单元、高压供给单元以及低压供给单元;The application provides a large-flow fast-response solid-liquid rocket engine ground transportation system for propelling propellant to the combustion chamber; the large-flow fast-response solid-liquid rocket engine ground transportation system includes a propellant storage unit, a high-pressure supply unit and a low-pressure supply unit;
所述推进剂存储单元的输出端分别与所述高压供给单元和所述低压供给单元连通;The output ends of the propellant storage unit are respectively communicated with the high pressure supply unit and the low pressure supply unit;
所述高压供给单元和所述低压供给单元的输出端分别通过主路与所述燃烧室连通。The output ends of the high pressure supply unit and the low pressure supply unit are respectively communicated with the combustion chamber through a main circuit.
具体地,本申请中所述高压供给单元与所述低压供给单元是一种并联排布结构,本申请巧妙地将高压供给单元和低压供给单元结合到一起,在试验过程中可以灵活切换不同的供给单元,既可以满足燃烧室低压的工况,又能够满足燃烧室高压的工况,从而提高了大流量快速响应固液火箭发动机地面输送系统的效率。Specifically, the high-voltage supply unit and the low-voltage supply unit in this application are arranged in parallel. The supply unit can satisfy both the low pressure working condition of the combustion chamber and the high pressure working condition of the combustion chamber, thereby improving the efficiency of the ground conveying system of the solid-liquid rocket engine with large flow and rapid response.
附图说明Description of drawings
为了更清楚地说明本申请具体实施方式或现有技术中的技术方案,下面将对具体实施方式或现有技术描述中所需要使用的附图作简单地介绍,显而易见地,下面描述中的附图是本申请的一些实施方式,对于本领域普通技术人员来讲,在不付出创造性劳动的前提下,还可以根据这些附图获得其他的附图。In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the accompanying drawings that need to be used in the description of the specific embodiments or the prior art will be briefly introduced below. The drawings are some embodiments of the present application. For those of ordinary skill in the art, other drawings can also be obtained from these drawings without any creative effort.
图1为本申请实施例一提供的大流量快速响应固液火箭发动机地面输送系统的结构示意图;1 is a schematic structural diagram of a large-flow fast-response solid-liquid rocket motor ground transportation system provided in Embodiment 1 of the present application;
图2为本申请实施例二提供的大流量快速响应固液火箭发动机地面输送系统的结构示意图;2 is a schematic structural diagram of a large-flow fast-response solid-liquid rocket motor ground transportation system provided in
图3为本申请实施例三提供的大流量快速响应固液火箭发动机地面输送系统的结构示意图;3 is a schematic structural diagram of a large-flow fast-response solid-liquid rocket motor ground transportation system provided in
图4为本申请实施例四提供的大流量快速响应固液火箭发动机地面输送系统的结构示意图。FIG. 4 is a schematic structural diagram of a large-flow fast-response solid-liquid rocket motor ground transportation system provided in
附图标记:1-气瓶;2-第四压力传感器;3-第四电磁阀;4-第二减压器;5-第三手阀;6-第五压力传感器;7-第六电磁阀;8-第四单向阀;9-第一减压器;10-第二手阀;11-第五电磁阀;12-第三压力传感器;13-安全阀;14-贮箱;15-加注泻出阀;16-过滤器;17-电动球阀;18-第一手阀;19-流量计;20-第二电磁阀;21-第二单向阀;22-第一电磁阀;23-第一压力传感器;24-电动泵;25-第二压力传感器;26-第一单向阀;27-缓冲器;28-第一调节阀;29-第三电磁阀;30-第三单向阀;31-第六压力传感器;32-第四手阀;33-第二调节阀;34-第七电磁阀;35-第五单向阀;36-第八电磁阀;37-第六单向阀;101-高压管路;102-主路;103-低压管路;104-推进剂供给管路;105-增压管路;106-吹除管路;108-循环管路;109-辅助管路;110-旁通管路;800-燃烧室。Reference numerals: 1-gas cylinder; 2-fourth pressure sensor; 3-fourth solenoid valve; 4-second pressure reducer; 5-third hand valve; 6-fifth pressure sensor; 7-sixth solenoid valve; 8- the fourth one-way valve; 9- the first pressure reducer; 10- the second hand valve; 11- the fifth solenoid valve; 12- the third pressure sensor; 13- safety valve; 14- tank; 15 -Filling and escaping valve; 16-filter; 17-electric ball valve; 18-first hand valve; 19-flow meter; 20-second solenoid valve; 21-second check valve; 22-first solenoid valve 23-first pressure sensor; 24-electric pump; 25-second pressure sensor; 26-first one-way valve; 27-buffer; 28-first regulating valve; 29-third solenoid valve; 30-first Three one-way valve; 31-sixth pressure sensor; 32-fourth hand valve; 33-second regulating valve; 34-seventh solenoid valve; 35-fifth one-way valve; 36-eighth solenoid valve; 37- The sixth one-way valve; 101-high pressure pipeline; 102-main circuit; 103-low pressure pipeline; 104-propellant supply pipeline; 105-pressurization pipeline; 106-blowing pipeline; 108-circulation pipeline ; 109 - auxiliary pipeline; 110 - bypass pipeline; 800 - combustion chamber.
具体实施方式Detailed ways
下面将结合附图对本申请的技术方案进行清楚、完整地描述,显然,所描述的实施例是本申请一部分实施例,而不是全部的实施例。The technical solutions of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present application, but not all of the embodiments.
通常在此处附图中描述和显示出的本申请实施例的组件可以以各种不同的配置来布置和设计。因此,以下对在附图中提供的本申请的实施例的详细描述并非旨在限制要求保护的本申请的范围,而是仅仅表示本申请的选定实施例。The components of the embodiments of the present application generally described and shown in the drawings herein may be arranged and designed in a variety of different configurations. Thus, the following detailed description of the embodiments of the application provided in the accompanying drawings is not intended to limit the scope of the application as claimed, but is merely representative of selected embodiments of the application.
基于本申请中的实施例,本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例,都属于本申请保护的范围。Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.
在本申请的描述中,需要说明的是,术语“中心”、“上”、“下”、“左”、“右”、“竖直”、“水平”、“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系,仅是为了便于描述本申请和简化描述,而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作,因此不能理解为对本申请的限制。此外,术语“第一”、“第二”、“第三”仅用于描述目的,而不能理解为指示或暗示相对重要性。In the description of this application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the accompanying drawings, which is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the indicated device or element must have a specific orientation or a specific orientation. construction and operation, and therefore should not be construed as limitations on this application. Furthermore, the terms "first", "second", and "third" are used for descriptive purposes only and should not be construed to indicate or imply relative importance.
在本申请的描述中,需要说明的是,除非另有明确的规定和限定,术语“安装”、“相连”、“连接”应做广义理解,例如,可以是固定连接,也可以是可拆卸连接,或一体地连接;可以是机械连接,也可以是电连接;可以是直接相连,也可以通过中间媒介间接相连,可以是两个元件内部的连通。对于本领域的普通技术人员而言,可以具体情况理解上述术语在本申请中的具体含义。In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it may be a fixed connection or a detachable connection Connection, or integral connection; can be mechanical connection, can also be electrical connection; can be directly connected, can also be indirectly connected through an intermediate medium, can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood in specific situations.
实施例一Example 1
下面参照图1描述根据本申请一些实施例所述的大流量快速响应固液火箭发动机地面输送系统。The following describes a large-flow fast-response solid-liquid rocket motor ground transportation system according to some embodiments of the present application with reference to FIG. 1 .
在该实施例中提供了一种大流量快速响应固液火箭发动机地面输送系统,用于将推进剂推进至燃烧室800;大流量快速响应固液火箭发动机地面输送系统包括推进剂存储单元、高压供给单元以及低压供给单元;In this embodiment, a large-flow fast-response solid-liquid rocket motor ground transportation system is provided for propelling propellant to the
所述推进剂存储单元用于存储推进剂(推进剂是指液体氧化剂),其输出端能够分别与所述高压供给单元和所述低压供给单元连通;所述高压供给单元和所述低压供给单元的输出端分别通过主路102与所述燃烧室800连通;本申请中所述高压供给单元与所述低压供给单元是一种并联排布结构,巧妙地将高压供给单元和低压供给单元结合到一起,在试验过程中可以灵活切换不同的供给单元,即可以满足燃烧室800低压的工况,又能够满足燃烧室800高压的工况,从而提高了大流量快速响应固液火箭发动机地面输送系统的效率。The propellant storage unit is used for storing propellant (propellant refers to liquid oxidant), and its output end can communicate with the high-pressure supply unit and the low-pressure supply unit, respectively; the high-pressure supply unit and the low-pressure supply unit The output ends of the
具体地,所述主路102上依次设置有第一调节阀28、第三电磁阀29、第三单向阀30以及第六压力传感器31;所述第一调节阀28靠近所述高压供给单元的输出端或所述低压供给单元的输出端;所述第六压力传感器31靠近所述燃烧室800。Specifically, a
进一步地,第一调节阀28能够调节主路102上液体氧化剂的流量。Further, the
进一步地,第三电磁阀29能够控制主路102的开启和关闭,也就是控制点火的开始和结束。Further, the
进一步地,第三单向阀30是一种能够防止燃烧室800高压气体倒灌阀,防止燃烧室800内的液体氧化剂反向进入高压供给单元和低压供给单元内。Further, the third one-
进一步地,第一压力传感器23作为燃烧室800前的压力传感器,能够监测燃烧室800前端的实时压力。Further, the
具体地,大流量快速响应固液火箭发动机地面输送系统所述还包括旁通管路110;所述旁通管路110的一端与所述主路102连通,所述旁通管路110上设置有第四手阀32。Specifically, the large-flow fast-response solid-liquid rocket engine ground transportation system further includes a
进一步地,第四手阀32能够在主路102充填液体氧化剂的过程中,排放主路102中积存的气体。Further, the
具体地,所述高压供给单元包括高压管路101;所述高压管路101的一端与所述推进剂存储单元连通,且另一端与所述燃烧室800连通;所述高压管路101上依次设置有第一电磁阀22、第一压力传感器23、电动泵24、第二压力传感器25以及第一单向阀26;其中,所述第一电磁阀22靠近所述推进剂存储单元,所述第一单向阀26靠近所述燃烧室800。Specifically, the high-pressure supply unit includes a high-
进一步地,所述第一电磁阀22是高压管路101的控制开关;当第一电磁阀22开启时,高压管路101开启,则启用电动泵24所在高压管路101,电动泵24将对推进剂进行增压,将高压推进剂送入燃烧室800。Further, the
进一步地,第一压力传感器23用于监控电动泵24前的推进剂的实时压力。Further, the
进一步地,电动泵24是整个高压供给单元的能量输入元件,电动泵24能够将泵前的低压推进剂增压为高压推进剂,提高推进剂的压力势能,从而使得推进剂具有高压力,并进入至高压的燃烧室800。Further, the
进一步地,第二压力传感器25是监控电动泵24后的推进剂的实时压力。Further, the
进一步地,第一单向阀26能够防止主路102的推进剂倒灌进入电动泵24内。当启用低压供给单元,停用高压供给单元时,主路102的推进剂有可能反向流入电动泵24,因此需要设置第一单向阀26防止推进剂进入电动泵24。Further, the first one-
综上,高压供给单元主要包括高压管路101以及设置在高压管路101上的第一电磁阀22、第一压力传感器23、电动泵24、第二压力传感器25以及第一单向阀26。当燃烧室800压力较高,流量较大时启用高压管路101,此时低压管路103停用,推进剂仅仅通过高压管路101。经过电动泵24的做功增压后,推进剂将以较大流量被推入高压燃烧室800内。To sum up, the high pressure supply unit mainly includes the
具体地,所述低压供给单元包括低压管路103;所述低压管路103的一端与所述推进剂存储单元连通,且另一端与所述燃烧室800连通;所述低压管路103上依次设置有第二电磁阀20和第二单向阀21;所述第二电磁阀20靠近所述推进剂存储单元,所述第二单向阀21靠近所述燃烧室800。Specifically, the low-pressure supply unit includes a low-pressure pipeline 103; one end of the low-pressure pipeline 103 is communicated with the propellant storage unit, and the other end is communicated with the
进一步地,第二电磁阀20能够控制低压管路103的开启和关闭。Further, the second solenoid valve 20 can control the opening and closing of the low pressure pipeline 103 .
进一步地,第二单向阀21能够防止推进剂倒灌。Further, the second one-
综上,低压管路103主要包括第二电磁阀20和第二单向阀21。低压管路103作为电动泵24所在的高压管路101的旁路,其能够在燃烧室800为低室压工况时工作,停用电动泵24及其所在的高压管路101,开启第二电磁阀20,启用低压管路103。To sum up, the low-pressure pipeline 103 mainly includes the second solenoid valve 20 and the second one-
具体地,所述推进剂存储单元包括贮箱14以及与所述贮箱14连通的推进剂供给管路104;所述推进剂供给管路104上依次设置有过滤器16、电动球阀17、第一手阀18以及流量计19;所述过滤器16靠近所述贮箱14,所述流量计19靠近所述高压供给单元或所述低压供给单元;所述贮箱14上设置有第三压力传感器12和加注泻出阀15。Specifically, the propellant storage unit includes a
进一步地,所述贮箱14是个压力容器,能够储存一定量的推进剂(液体氧化剂),并且能够承受一定压力,可以将液体氧化剂顺利地挤入高压供给单元或低压供给单元。Further, the
进一步地,加注泻出阀15一方面能够作为液体氧化剂加注使用,通过加注泻出阀15往贮箱14加注液体氧化剂,另一方面能够作为泄出阀,通过加注泻出阀15将贮箱14中的剩余的液体氧化剂排出。Further, on the one hand, the filling and discharging
进一步地,过滤器16用于过滤液体氧化剂中掺杂的固体杂物,防止固体杂物堵塞推进剂供给管路104以及防止固体杂物进入燃烧室800内。Further, the
进一步地,电动球阀17可靠性更高,密封性更好,能够作为贮箱14的封口,在试验开始前堵住贮箱14内的液体氧化剂,防止贮箱14内液体氧化剂的流出。Further, the
进一步地,第一手阀18能够作为推进剂管路的备用开关,当第一电磁阀22或第二电磁阀20失效或推进剂供给管路104内液体氧化剂的流动异常时,可以手动关闭第一手阀18。Further, the
进一步地,流量计19能够监视推进剂供给管路104的实时流量,确保液体氧化剂的流量达到目标流量值。Further, the
实施例二
下面参照图2描述根据本申请一些实施例所述的大流量快速响应固液火箭发动机地面输送系统。The following describes a large-flow fast-response solid-liquid rocket motor ground transportation system according to some embodiments of the present application with reference to FIG. 2 .
在该实施例中,所述大流量快速响应固液火箭发动机地面输送系统还包括增压单元;所述增压单元包括气瓶1以及与所述气瓶1连通的增压管路105,所述增压管路105的输入端与所述气瓶1连通,且输出端与所述推进剂存储单元连通;In this embodiment, the large-flow fast-response solid-liquid rocket engine ground transportation system further includes a booster unit; the booster unit includes a gas cylinder 1 and a
所述增压管路105上依次设置有第四压力传感器2、第四电磁阀3、第一减压器9、第二手阀10以及第五电磁阀11;所述第四压力传感器2靠近所述气瓶1,所述第五电磁阀11靠近所述推进剂存储单元。A
进一步地,气瓶1内用于存有高压氮气,可以作为气源;一方面作为增压气源,给贮箱14增压,使得贮箱14保持一定压力;另一方面作为吹除气源,将大量惰性高压氮气吹入燃烧室800,从而吹熄燃烧室800,保证点火试验结束后的推进剂的安全熄灭。Further, the gas cylinder 1 is used to store high-pressure nitrogen, which can be used as a gas source; on the one hand, as a pressurized gas source to pressurize the
进一步地,第四压力传感器2用于监视气瓶1内的压力,气瓶1的压力过高,需要从吹除管路106(吹除管路106在实施例三种有介绍)放气,气瓶1的压力过低则需要给气瓶1充气。Further, the
进一步地,第四电磁阀3是增压管路105的总阀,作为增压管路105和吹除管路106的总开关。Further, the
进一步地,第一减压器9作为可调节流元件,能够将气瓶1的高压降为贮箱14可用的压力。Further, the
进一步地,第二手阀10作为增压管路105的手动开关,控制贮箱14的开启和关闭,是备用开关,一旦第五电磁阀11,则启动第二手阀10。Further, the
进一步地,第五电磁阀11是增压管路105的电控开关;在试验前,需要开启第五电磁阀11,增压管路105向装有液体氧化剂的贮箱14送入高压气体,从而对贮箱14增压,之后维持在目标贮箱14压力,等待试验。值得注意的是:在试验过程中,也需要开启贮箱14前置的第五电磁阀11,增压管路105源源不断地往装有液体氧化剂的贮箱14送气,从而保证贮箱14一直稳定在一定的压力范围内,避免贮箱14由于液体推进剂的大量流出,贮箱14内气体空间增大,从而导致贮箱14压力大幅度下降。Further, the
进一步地,第三压力传感器12能够是监视贮箱14压力;在调整贮箱14压力的过程中,首先需要开启贮箱14前置的第二手阀10和贮箱14前置的第五电磁阀11,然后缓慢增大贮箱14的第一减压器9的开度,同时目测贮箱14的第三压力传感器12的读数,不断调整,直至贮箱14的第三压力传感器12的实时读数与目标贮箱14压力一致。Further, the
进一步地,安全阀13用于保证贮箱14的压力不超过限定值,如果贮箱14的压力超过限定值,则打开安全阀13,从而降低贮箱14压力,避免操作第一减压器9失误,贮箱14压力过高而发生爆炸的风险。Further, the
综上,增压单元能够保证贮箱14压力具有一定压力,并保证大量液体推进剂流出时,贮箱14的压力能够稳定,使得液体推进剂从贮箱14到电动泵24前,或是从贮箱14到燃烧室800之间具有一定压力差,该压力差可以顺利将液体推进剂从贮箱14挤出并保证一定流量。To sum up, the booster unit can ensure that the pressure of the
实施例三
下面参照图3描述根据本申请一些实施例所述的大流量快速响应固液火箭发动机地面输送系统。The following describes a large-flow fast-response solid-liquid rocket motor ground transportation system according to some embodiments of the present application with reference to FIG. 3 .
在该实施例中,所述大流量快速响应固液火箭发动机地面输送系统还包括吹除单元,所述吹除单元包括吹除管路106;所述吹除管路106的输入端与所述增压管路105连通,且输出端与所述燃烧室800连通;所述吹除管路106上依次设置有第二减压器4、第三手阀5、第五压力传感器6、第六电磁阀7以及第四单向阀8;所述第二减压器4靠近所述第四电磁阀3,所述第四单向阀8靠近所述燃烧室800。In this embodiment, the large-flow fast-response solid-liquid rocket engine ground transportation system further includes a blow-off unit, and the blow-off unit includes a blow-off
进一步地,第二减压器4作为可调节流元件,能够将气瓶1的高压降为吹除管路106可用的压力。Further, the
进一步地,第三手阀5作为吹除管路106的手动开关,控制吹除管路106的开启和关闭,是备用开关,当第六电磁阀7失效时启用。Further, the
进一步地,第二减压器4能够监视吹除管路106的压力。在调整吹除管路106压力的过程中,首先需要开启第四电磁阀3和第三手阀5,然后缓慢增大第二减压器4的开度,同时目测第二减压器4读数,不断调整,直至第二减压器4的实时读数与目标吹除压力一致。Further, the
进一步地,第六电磁阀7在试验过程中作为吹除管路106的电控开关。在以下情况下开启,第一种情况是试验正常结束,开启第六电磁阀7吹熄固液发动机,向燃烧室800送入大量氮气,降低燃烧室800温度。第二种情况是试验异常,遇到紧急情况,开启第六电磁阀7,向燃烧室800通入大量惰性氮气,将发动机吹熄,紧急停机。Further, the
进一步地,第四单向阀8能够防止液体氧化剂倒灌至吹除管路106内。保证吹除管路106只能单方向的向燃烧室800吹气。Further, the fourth one-
综上,吹除单元保证吹除气的正常供应,使得整个输送系统随时具备向燃烧室800送入大量惰性气体的能力,从而保证试验安全。To sum up, the blowing unit ensures the normal supply of blowing gas, so that the entire conveying system has the ability to feed a large amount of inert gas into the
实施例四
下面参照图4描述根据本申请一些实施例所述的大流量快速响应固液火箭发动机地面输送系统。The following describes a large-flow fast-response solid-liquid rocket motor ground transportation system according to some embodiments of the present application with reference to FIG. 4 .
在该实施例中,所述大流量快速响应固液火箭发动机地面输送系统还包括循环单元,所述循环单元包括循环管路108;所述循环管路108的一端与推进剂存储单元连通,另一端与所述主路102连通;所述循环管路108上依次设置有第五单向阀35、第七电磁阀34、第二调节阀33以及缓冲器27;所述第五单向阀35靠近所述推进剂存储单元,所述缓冲器27靠近所述高压供给单元。In this embodiment, the large-flow fast-response solid-liquid rocket motor ground transportation system further includes a circulation unit, and the circulation unit includes a
进一步地,第二调节阀33与第一调节阀28结构以及作用相同;在试验过程中同步动作,即试验开始时是实时保持一致的。Further, the
进一步地,第七电磁阀34能够控制循环管路108的开启和关闭。Further, the
进一步地,第五单向阀35能够防止液体氧化剂反向流动,即避免液体氧化剂流体从贮箱14流入循环管路108。Further, the fifth one-
进一步地,缓冲器27作为压力容器罐,用于对液体氧化剂起到缓冲作用,使得第七电磁阀34瞬间开启时,循环管路108内压力更加平稳。Further, the
综上,通过配置电动泵24的循环管路108和第一调节阀28,第二调节阀33的双路调节阀,规避了电动泵24需缓慢启动,缓慢停止的缺点,大大提高了电动泵24的泵压式输送系统的流量响应能力。To sum up, by configuring the
在该实施例中,所述大流量快速响应固液火箭发动机地面输送系统还包括辅助单元,所述辅助单元包括辅助管路109;所述辅助管路109上设置有靠近所述第七电磁阀34的第八电磁阀36以及靠近所述主路102的第六单向阀37。In this embodiment, the large-flow fast-response solid-liquid rocket motor ground transportation system further includes an auxiliary unit, and the auxiliary unit includes an
进一步地,第八电磁阀36能够控制辅助管路109的开启和关闭。Further, the
进一步地,第六单向阀37防止液体氧化剂反向流动,避免液体氧化剂从主路102反向流入辅路管路。Further, the sixth one-
综上,通过配置主路102和辅路管路,且主路102和辅路管路上均配置有调节阀,可以保证瞬间开启主路102和辅路管路中任意一者或者同时开启主路102和辅路管路,使得主路102和辅路管路上的调节阀能够同时调节。相比于传统的单路,双调节阀管路的流量的调节范围更广,实时响应能力更快。In summary, by configuring the
结合上述实施例一到实施例四,本申请的具体工作过程如下:In conjunction with the above-mentioned Embodiment 1 to
步骤100:试验前准备工作:需要进行贮箱14增压加注、吹除气配置、管路液体氧化剂充填。Step 100: Preparatory work before the test: It is necessary to pressurize and fill the
步骤101:贮箱14增压加注是将一定量的液体推进剂通过加注泄出阀加注到贮箱14,并且通过增压管路105的第一减压器9将贮箱14增压至目标贮箱14压力,使得第三压力传感器12的实时读数为目标贮箱14压力。Step 101: Pressurizing and filling the
步骤102:吹除气配置是通过第二减压器4将吹除压力调整至目标吹除压力,使得第五压力传感器6的实时读数为目标吹除压力。Step 102: The blow-off gas configuration is to adjust the blow-off pressure to the target blow-off pressure through the
具体地,管路液体氧化剂充填的过程如下:充填过程为将第三电磁阀29之前的管路充满液体推进剂,防止有部分气体积存于管路中。充填操作的准备工作是贮箱14增压和阀门准备。贮箱14增压是将贮箱14增压至较低压力,保证可以将液体氧化剂挤入管路。阀门准备是将控制相关阀门的位置到位,保证液体氧化剂能够按照预期路线依次充填管路各个部分,主要过程为:关闭第三电磁阀29,关闭第七电磁阀34和第八电磁阀36,开启电动球阀17、第一手阀18。充填顺序是低压管路103充填、高压管路101充填和辅助管路109充填。Specifically, the process of filling the pipeline with liquid oxidant is as follows: the filling process is to fill the pipeline before the
步骤103:进行低压管路103充填:关闭第一电磁阀22,停用高压管路101,开启第二电磁阀20,启用低压管路103。之后手动打开第四手阀32,直至流入外界的液体氧化剂中不掺杂气体。Step 103 : Filling the low pressure pipeline 103 : closing the
步骤104:进行高压管路101充填:关闭第二电磁阀20,停用低压管路103,开启第一电磁阀22,启用高压管路101。之后手动打开第四手阀32,直至流入外界的液体氧化剂中不掺杂气体。Step 104 : Filling the high pressure pipeline 101 : closing the second solenoid valve 20 , deactivating the low pressure pipeline 103 , opening the
步骤105:辅助管路109充填:首先关闭高压管路101,开启低压管路103,即第一电磁阀22,开启第二电磁阀20;然后将第一调节阀28开度调至较小开度,第二调节阀33调节至较大开度,从而保证液体氧化剂主要部分顺利流入辅助管路109;最后开启第八电磁阀36和第四手阀32,直至流入外界的液体氧化剂中不掺杂气体。Step 105: Filling the auxiliary pipeline 109: firstly close the
步骤200:当燃烧室800的目标流量较小,且燃烧室800压力较小时,启用低压管路103,停用高压管路101。Step 200: When the target flow rate of the
步骤201:试验前准备:确保贮箱14加注液体氧化剂完毕,且贮箱14压力已增压至目标贮箱14压力;确保吹除管路106内压力调整至目标吹除压力;确保低压管路103,高压管路101,主路102,辅助管路109中无气体,并充满液体推进剂。Step 201: Preparations before the test: ensure that the
步骤202:当流量较小且燃烧室800压力较小时,仅启用低压管路103,整个输送系统是一种挤压式输送系统;具体地,开启低压管路103,停用高压管路101,停用辅助管路109和循环管路108,即开启第二电磁阀20,关闭第一电磁阀22,关闭第八电磁阀36和第七电磁阀34。Step 202: When the flow rate is small and the pressure of the
更具体地,试验前增压管路105的阀门状态为:第二手阀10开启,第五电磁阀11开启。试验前吹除路管路的阀门状态为:第三手阀5开启,第六电磁阀7关闭。试验前低压管路103的阀门状态为:电动球阀17开启,第一手阀18开启,第二电磁阀20开启,第三电磁阀29关闭。其他路的阀门均关闭,即第一电磁阀22关闭,第七电磁阀34关闭,第八电磁阀36关闭,第四手阀32关闭。More specifically, the valve state of the boosting
步骤203:流量调整:手动开启第四手阀32,通过流量计19的实时读数,实时逐步增大第一调节阀28的开度大小,直至流量计19的读数与目标流量一致,关闭第四手阀32,流量调整完毕。Step 203: Flow adjustment: manually open the
若试验的目标流量较大,采用第一调节阀28开度至最大,流量依旧无法达到目标流量,此时可启用辅助管路109。流体经过低压管路103之后分流,同时经过主路102和辅助管路109,最终流入燃烧室800的流量为主路102流量和辅助管路109流量之和。开启辅路第八电磁阀36,将第一调节阀28开度调整至最大,继而逐步增大第二调节阀33的开度,直至流量计19读数达到目标流量。之后保持第一调节阀28和第二调节阀33的开度,关闭第四手阀32,等待试验。If the target flow rate of the test is relatively large, the opening of the
步骤204:开启试验。设定固液发动机点火时间为T0时刻至T1秒时刻,即T0时刻点火,T1时刻关闭固液发动机。点火前,再次校验贮箱14压力和吹除单元压力,检查各阀门状态。Step 204: Start the test. The solid-liquid engine ignition time is set from time T0 to time T1 seconds, that is, the ignition time is T0, and the solid-liquid engine is turned off at T1. Before ignition, check the pressure of the
T0时刻,开启第三电磁阀29,由于第三电磁阀29开度已到位,故流量迅速提升至目标流量;At time T0, the
T1时刻关闭第三电磁阀29,流量迅速降至零;The
T1+0.1s时刻,开启第六电磁阀7,向燃烧室800吹入大量惰性氮气,将发动机熄火和降温,保障试验安全。At T1+0.1s, the
待发动机熄火和降温完毕,关闭第六电磁阀7。至此,试验结束。步骤300:当目标流量较大,且燃烧室800压力较高时,流量控制过程如下:流量较大,主路102压力较高,传统挤压式输送系统已无法满足要求,此时需要在高压管路101中加入能量输入元件,即电动泵24。此时需要切换系统模式,停用低压管路103,启用高压管路101,系统将改为电动泵24式的泵压式输送系统。After the engine is turned off and cooled down, the
步骤301:试验前准备。确保贮箱14加注完毕,贮箱14压力已增压至目标贮箱14压力;确保吹除单元压力调整至目标吹除压力;确保低压管路103,高压管路101,主路102,辅助管路109中无气体,充满液体推进剂。Step 301: Preparation before the test. Make sure that the
步骤302:试验前管路阀门配置:流量较大,且燃烧室800压力较高,需启用含电动泵24的高压管路101,整个输送系统为泵压式输送系统。开启高压管路101,停用低压管路103,启用循环管路108,超大流量工况下启用辅助管路109,常规工况下停用辅助管路109。即开启第一电磁阀22和第七电磁阀34,关闭第二电磁阀20、第八电磁阀36和第四手阀32。Step 302: Pipeline valve configuration before the test: the flow rate is large, and the pressure of the
试验前增压管路105的阀门状态为:第二手阀10开启,第五电磁阀11开启。Before the test, the valve state of the
试验前吹除管路106的阀门状态为:第三手阀5开启,第六电磁阀7关闭。Before the test, the valve state of the blow-off
试验前主路102的阀门状态为:电动球阀17开启,第一手阀18开启,第三电磁阀29、第七电磁阀34开启,第二电磁阀20、第八电磁阀36关闭。The valve states of the
步骤303:流量调整。开启高压管路101和循环管路108,逐步调整电动泵24的转速和第二调节阀33开度,直至电动泵24的第二压力传感器25读数满足目标压力,流量计19读数达到目标流量。即开启电动球阀17、第一手阀18、第一电磁阀22、第七电磁阀34,液路其余阀门均处于关闭状态。开启电动泵24,逐步提高转速,直至电动泵24后压力符合要求,也就是电动泵24后第二压力传感器25读数大于设定电动泵24后压力。保持泵转速不变,然后逐步增大第二调节阀33开度,直至流量达到设定的目标流量,也就是流量计19读数达到设定流量值。此时,由于第二调节阀33开度增大,流量增大,电动泵24之后的压力会下降,此时又需要提高电动泵24转速,直至电动泵24后压力大于设定的电动泵24后压力。接着,转速不变,调整第二调节阀33的开度。通过反复调整电动泵24转速和第二调节阀33的开度,保证流量和电动泵24后压力满足需求。记录此时符合要求的电动泵24的转速为W1,第二调节阀33的开度为K1。随后将第一调节阀28的开度同样调整为K1,即第一调节阀28和第二调节阀33的结构尺寸,阀门开度等均相同。Step 303: Flow adjustment. Open the
步骤304:开启试验。设定固液发动机点火时间为T0时刻至T1秒时刻,即T0时刻点火,T1时刻关闭固液发动机。点火前,再次校验贮箱14压力和吹除单元的压力,检查各阀门状态;保证电动泵24转速为W1,第一调节阀28和第二调节阀33的开度均为K1。Step 304: Start the test. The solid-liquid engine ignition time is set from time T0 to time T1 seconds, that is, the ignition time is T0, and the solid-liquid engine is turned off at T1. Before ignition, check the pressure of the
T0时刻,开启第三电磁阀29,关闭第七电磁阀34。由于第一调节阀28和第二调节阀33的结构尺寸和开度时一致的,当流体不在经过循环管路108回贮箱14,而是通过主路102流向燃烧室800时,流量计19的读数不会改变,即流量依旧是目标流量,电动泵24后压力依旧大于设定电动泵24后压力,流量和电动泵24后压力均满足要求。之后,通往燃烧室800的推进剂的流量迅速变为设定的目标流量。At time T0, the
T1时刻,关闭第三电磁阀29,开启第七电磁阀34,主路102流量迅速降至零,循环管路108流量转为目标流量。之后为避免电动泵24损坏,电动泵24逐渐降低转速,缓慢停机。电动泵24停转之后,关闭第七电磁阀34。At T1 time, the
T1+0.1s时刻,开启第六电磁阀7,往燃烧室800吹入大量惰性氮气,将发动机熄火和降温,保障试验安全。At T1+0.1s, the
待发动机熄火和降温完毕,关闭第六电磁阀7。至此,试验结束。综上,本申请配置循环管路108,管路流量响应快。一方面可以在第三电磁阀29开启后迅速达到目标流量。另一方面点火结束,流量可以迅速降为零,大大缓解了流量拖尾问题,即点火结束后,解决了流量不能立刻归零的问题。本申请在T0至T1的点火时间段内,流入燃烧室800的流量都是迅速升至目标流量,之后也是迅速降为0,流量时间曲线十分稳定。After the engine is turned off and cooled down, the
除此之外,本申请具有主路102和辅助管路109,且两路均配置调节阀,可以瞬间开启一路或者开启两路,两路阀门同时调节,统一开度。相比于传统的单路,双调节阀管路的流量的调节范围更广实时响应能力更快。In addition, the present application has a
最后应说明的是:以上各实施例仅用以说明本申请的技术方案,而非对其限制;尽管参照前述各实施例对本申请进行了详细的说明,本领域的普通技术人员应当理解:其依然可以对前述各实施例所记载的技术方案进行修改,或者对其中部分或者全部技术特征进行等同替换;而这些修改或者替换,并不使相应技术方案的本质脱离本申请各实施例技术方案的范围。Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, but not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: The technical solutions described in the foregoing embodiments can still be modified, or some or all of the technical features thereof can be equivalently replaced; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the technical solutions of the embodiments of the present application. scope.
Claims (6)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202111477389.5A CN114136635B (en) | 2021-12-06 | 2021-12-06 | Large-flow quick-response solid-liquid rocket engine ground conveying system |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202111477389.5A CN114136635B (en) | 2021-12-06 | 2021-12-06 | Large-flow quick-response solid-liquid rocket engine ground conveying system |
Publications (2)
Publication Number | Publication Date |
---|---|
CN114136635A CN114136635A (en) | 2022-03-04 |
CN114136635B true CN114136635B (en) | 2022-08-23 |
Family
ID=80384025
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN202111477389.5A Active CN114136635B (en) | 2021-12-06 | 2021-12-06 | Large-flow quick-response solid-liquid rocket engine ground conveying system |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN114136635B (en) |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5941645A (en) * | 1982-07-28 | 1984-03-07 | メツセルシユミツト−ベルコウ−ブロ−ム・ゲゼルシヤフト・ミト・ベシユレンクテル・ハフツング | Sub-current structure type liquid rocket drive for driving in vacuum space |
CN103234761A (en) * | 2013-04-12 | 2013-08-07 | 北京航空航天大学 | Mobile test platform for low-thrust rocket engines |
CN104329187A (en) * | 2014-09-05 | 2015-02-04 | 西北工业大学 | Variable working condition type primary rocket system of rocket based combined cycle engine |
-
2021
- 2021-12-06 CN CN202111477389.5A patent/CN114136635B/en active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5941645A (en) * | 1982-07-28 | 1984-03-07 | メツセルシユミツト−ベルコウ−ブロ−ム・ゲゼルシヤフト・ミト・ベシユレンクテル・ハフツング | Sub-current structure type liquid rocket drive for driving in vacuum space |
CN103234761A (en) * | 2013-04-12 | 2013-08-07 | 北京航空航天大学 | Mobile test platform for low-thrust rocket engines |
CN104329187A (en) * | 2014-09-05 | 2015-02-04 | 西北工业大学 | Variable working condition type primary rocket system of rocket based combined cycle engine |
Also Published As
Publication number | Publication date |
---|---|
CN114136635A (en) | 2022-03-04 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN109630320B (en) | Blowout systems and blowout adapters for cryogenic liquid rocket engines | |
KR101588173B1 (en) | Hydrogen station | |
CN107587954A (en) | Gas oxygen kerosene Rocket Engines pressurizing transmission system and small rocket motor propellant-feed system | |
US8936009B2 (en) | Fuel system having dual fuel pressure regulator | |
CN107237703A (en) | Solid-liquid rocket electrodynamic pump induction system | |
CN103670802B (en) | A kind of small air pillow pressurization system | |
US20010054290A1 (en) | Low-cost general aviation fuel control system | |
WO2021121399A1 (en) | Hydrogen storage system of fuel cell vehicle and fuel cell vehicle | |
CN110131073B (en) | Space propulsion system suitable for filling of large-capacity storage tank | |
CN114136635B (en) | Large-flow quick-response solid-liquid rocket engine ground conveying system | |
JP2016161071A (en) | Hydrogen filling system | |
EP4242457A1 (en) | Apparatus and method for cryogenic pump cooldown | |
CN107514320A (en) | A kind of micromass culture modular structure based on high pressure frontier technology | |
CN111272404A (en) | Fire truck fire pipeline test system | |
EP4144981A1 (en) | Fuel processing unit and fuel storage and supply system having same | |
CN112922912B (en) | Wave compensation type closed rotary hydraulic control system for marine trestle | |
CN114526443A (en) | Control system for hydrogen switching | |
CN112594093A (en) | Control system of reciprocating displacement pump for solid-liquid rocket engine | |
CN209145736U (en) | Blowout Adapters for Cryogenic Liquid Engines | |
CN111271193A (en) | A low temperature liquid rocket propellant pipeline control system and liquid rocket engine | |
CN215764594U (en) | Gas pressure stabilizing and adjusting system | |
CN114508447A (en) | Electric pump pressure type solid-liquid rocket engine test conveying system and method | |
CN117108511B (en) | Self-adaptive centrifugal pressure test pump set and pump system capable of avoiding overpressure | |
CN111895267B (en) | Vehicle-mounted gas cylinder pressurization control system and control method thereof | |
CN115306586A (en) | A propellant storage tank pressure control device and control method thereof |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PB01 | Publication | ||
PB01 | Publication | ||
SE01 | Entry into force of request for substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
GR01 | Patent grant | ||
GR01 | Patent grant |