CN105971768B - A kind of supercharging supply system certainly based on re-generatively cooled - Google Patents
A kind of supercharging supply system certainly based on re-generatively cooled Download PDFInfo
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- 238000001816 cooling Methods 0.000 claims abstract description 49
- 239000007788 liquid Substances 0.000 claims abstract description 49
- 239000003380 propellant Substances 0.000 claims abstract description 43
- 238000002485 combustion reaction Methods 0.000 claims abstract description 38
- 239000002826 coolant Substances 0.000 claims abstract description 15
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 11
- 229920006395 saturated elastomer Polymers 0.000 claims abstract description 8
- 239000000956 alloy Substances 0.000 claims description 4
- 229910000881 Cu alloy Inorganic materials 0.000 claims description 2
- 229910045601 alloy Inorganic materials 0.000 claims description 2
- 239000010935 stainless steel Substances 0.000 claims description 2
- 229910001220 stainless steel Inorganic materials 0.000 claims description 2
- 238000003466 welding Methods 0.000 claims description 2
- 239000004744 fabric Substances 0.000 claims 1
- 239000000843 powder Substances 0.000 claims 1
- 230000001172 regenerating effect Effects 0.000 abstract description 13
- 238000000034 method Methods 0.000 abstract description 9
- 238000002309 gasification Methods 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 17
- PXBRQCKWGAHEHS-UHFFFAOYSA-N dichlorodifluoromethane Chemical compound FC(F)(Cl)Cl PXBRQCKWGAHEHS-UHFFFAOYSA-N 0.000 description 6
- 235000019404 dichlorodifluoromethane Nutrition 0.000 description 6
- GQPLMRYTRLFLPF-UHFFFAOYSA-N Nitrous Oxide Chemical compound [O-][N+]#N GQPLMRYTRLFLPF-UHFFFAOYSA-N 0.000 description 4
- 238000001125 extrusion Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 2
- OBNDGIHQAIXEAO-UHFFFAOYSA-N [O].[Si] Chemical compound [O].[Si] OBNDGIHQAIXEAO-UHFFFAOYSA-N 0.000 description 1
- XTYUEDCPRIMJNG-UHFFFAOYSA-N copper zirconium Chemical compound [Cu].[Zr] XTYUEDCPRIMJNG-UHFFFAOYSA-N 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000001272 nitrous oxide Substances 0.000 description 1
- 239000011555 saturated liquid Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000009834 vaporization Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/50—Feeding propellants using pressurised fluid to pressurise the propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
本发明属于航天器系统技术领域，主要应用于采用高饱和蒸汽压推进剂的液体推进系统或固‑液混合推进系统。为了解决自增压供应系统工作过程中贮箱内推进剂温度降低、压力下降严重的问题，本发明提供了一种基于再生冷却的自增压方案，由安全阀、贮箱、加注管路、加注阀、单向阀、冷却通道、集液腔、主供应管路、冷却剂管路、燃烧剂管路、主阀、增压管路等组成。推进剂在冷却燃烧室室壁的同时获得热量，换热气化之后的推进剂返回贮箱给推进剂增压。本发明可在贮箱内液体推进剂排空之前保持贮箱压强基本稳定，从而保证推力基本稳定。
The invention belongs to the technical field of spacecraft systems and is mainly applied to liquid propulsion systems or solid-liquid hybrid propulsion systems using high saturated vapor pressure propellants. In order to solve the problem that the temperature of the propellant in the storage tank is lowered and the pressure drops seriously during the working process of the self-pressurization supply system, the present invention provides a self-pressurization scheme based on regenerative cooling, which consists of a safety valve, a storage tank, and a filling pipeline. , Filling valve, one-way valve, cooling channel, liquid collection chamber, main supply pipeline, coolant pipeline, combustion agent pipeline, main valve, booster pipeline, etc. The propellant gains heat while cooling the chamber wall of the combustion chamber, and the propellant after heat exchange and gasification returns to the storage tank to pressurize the propellant. The invention can keep the pressure of the storage tank basically stable before the liquid propellant in the storage tank is emptied, thereby ensuring the basic stability of the thrust.
Description
技术领域technical field
本发明属于航天推进系统技术领域，特别涉及一种基于再生冷却的自增压供应系统。The invention belongs to the technical field of aerospace propulsion systems, in particular to a self-pressurized supply system based on regenerative cooling.
背景技术Background technique
目前使用的化学火箭推进系统有：液体推进系统、固体推进系统、气体推进系统和固-液混合推进系统。在上述各类推进系统中，液体推进系统、固-液推进系统和气体推进系统都需要推进剂增压输送装置，这类增压装置又分为泵压式和挤压式两大类。泵压式系统的主要优点是推进剂贮箱不必承受高压，可采用较轻质量的贮箱，但由于采用涡轮泵增加了系统复杂性和成本，通常只用于大推力、长寿命的大型运载火箭。对于飞行器辅助推进系统和上面级姿轨控系统等推进剂质量较小的系统，通常采用挤压式推进剂供应系统。挤压式供应系统结构简单、可靠，又分为恒压式和落压式两种方案，前者依靠高压气瓶通过减压阀恒定输出，为贮箱增压，但增压气体和高压气瓶以及减压阀等部件大大增加了系统的质量；后者依靠贮箱气垫的压力工作，对贮箱承压的要求较高，且其压力将逐渐降低，推力输出不恒定。The currently used chemical rocket propulsion systems are: liquid propulsion system, solid propulsion system, gas propulsion system and solid-liquid hybrid propulsion system. Among the above-mentioned types of propulsion systems, liquid propulsion systems, solid-liquid propulsion systems and gas propulsion systems all require propellant pressurized delivery devices, and such pressurized devices are further divided into two categories: pump pressure type and extrusion type. The main advantage of the pump pressure system is that the propellant storage tank does not have to withstand high pressure, and a lighter weight storage tank can be used. However, due to the increased complexity and cost of the system by using a turbo pump, it is usually only used for large-scale transportation with high thrust and long life. Rocket. For systems with small propellant mass, such as aircraft auxiliary propulsion systems and upper-level attitude and orbit control systems, extruded propellant supply systems are usually used. The extrusion type supply system has a simple and reliable structure, and is divided into two schemes: constant pressure type and falling pressure type. The former relies on the constant output of high-pressure gas cylinders through the pressure-reducing valve to pressurize the storage tank, but the pressurized gas and high-pressure gas cylinders The quality of the system is greatly increased by components such as pressure reducing valves; the latter relies on the pressure of the air cushion of the tank to work, and has higher requirements on the pressure of the tank, and its pressure will gradually decrease, and the thrust output is not constant.
自增压是一种落压式方案，它利用密封容器内饱和液体的能量将液体从容器中挤出。其实现方式如下：推进剂从贮箱流出时，贮箱内的压力将降低，当压力低于推进剂的饱和蒸气压时，贮箱内剩下的液体推进剂将会部分气化，产生的蒸气维持贮箱内的压力基本恒定。这种增压方式不需要另外设置高压气瓶和减压阀，既有气瓶-贮箱型挤压式供应系统结构简单的优点，又兼具泵压式供应系统贮箱质量小、燃烧室压力高的优良性能。大量试验验证了这种增压方式的可行性，但同时也表明，在自增压供应系统工作过程中，由于气垫做功和液体气化，贮箱内推进剂的温度将降低，压力下降严重，使得供应系统不能够以恒定质量流量供应推进剂。为解决这个问题，较简单的方法是对推进剂贮箱进行热补偿。通常采用的电加热方式结构简单、加热功率可调节，但缺点是需要消耗弹箭/卫星上宝贵的电能资源。Self-pressurization is a drop-pressure solution that uses the energy of a saturated liquid in a sealed container to force liquid out of the container. Its implementation is as follows: when the propellant flows out of the tank, the pressure in the tank will decrease, and when the pressure is lower than the saturated vapor pressure of the propellant, the remaining liquid propellant in the tank will be partially vaporized, resulting in The vapor maintains a substantially constant pressure in the tank. This pressurization method does not need additional high-pressure gas cylinders and pressure reducing valves. It not only has the advantages of simple structure of the cylinder-storage type extrusion type supply system, but also has the advantages of small mass of the storage tank of the pump pressure type supply system and the low mass of the combustion chamber. Excellent performance under high pressure. A large number of tests have verified the feasibility of this pressurization method, but it also shows that during the working process of the self-pressurization supply system, due to the work of the air cushion and the vaporization of the liquid, the temperature of the propellant in the tank will decrease, and the pressure will drop seriously. This makes it impossible for the supply system to supply propellant at a constant mass flow rate. A simpler solution to this problem is to thermally compensate the propellant tanks. The commonly used electric heating method has a simple structure and adjustable heating power, but the disadvantage is that it needs to consume precious electric energy resources on the rocket/satellite.
发明内容Contents of the invention
本发明的目的是：在传统自增压供应系统工作过程中压力下降严重，不能维持贮箱压力恒定的情况下，提出一种推进剂自增压供应系统。该系统采用类似再生冷却的方法，在燃烧室室壁布置冷却通道，让推进剂作为冷却剂流经冷却通道进行换热，在冷却燃烧室壁的同时，推进剂获得了热量从而被气化，被气化的推进剂被送回贮箱，给贮箱增压，达到使贮箱压力基本稳定的目的。The purpose of the present invention is to propose a propellant self-pressurizing supply system when the traditional self-pressurizing supply system has a serious pressure drop and cannot maintain a constant tank pressure. The system adopts a method similar to regenerative cooling. Cooling channels are arranged on the wall of the combustion chamber, and the propellant flows through the cooling channel as a coolant for heat exchange. While cooling the wall of the combustion chamber, the propellant gains heat and is vaporized. The gasified propellant is sent back to the storage tank to pressurize the storage tank to achieve the purpose of basically stabilizing the pressure of the storage tank.
本发明“一种基于再生冷却的自增压供应系统”是按下述方案实现的：The present invention "a self-supercharging supply system based on regenerative cooling" is realized according to the following scheme:
该系统包括安全阀1、贮箱2、加注管路3、加注阀4、单向阀5、冷却通道6、集液腔7、主供应管路8、冷却剂管路8a、燃烧剂管路8b、主阀9、增压管路10、燃烧室11、推进剂12。The system includes safety valve 1, storage tank 2, filling pipeline 3, filling valve 4, one-way valve 5, cooling passage 6, liquid collection chamber 7, main supply pipeline 8, coolant pipeline 8a, combustion agent Pipeline 8b, main valve 9, booster pipeline 10, combustion chamber 11, propellant 12.
安全阀1设置在贮箱2上，位于贮箱气垫端。加注管路3与贮箱2连通，加注时，液态推进剂12经加注阀4由加注管路3进入贮箱。主供应管路8与贮箱2连通，主供应管路8上设置主阀9。在主阀9下游，主供应管路8分为冷却剂管路8a和燃烧剂管路8b两条支路，其中冷却剂管路8a与集液腔7连通，该支路上还设置了单向阀5，燃烧剂管路8b直接与燃烧室11连通。槽肋式冷却通道6设置在燃烧室11的内外壁之间，冷却通道6的入口端与集液腔7连接，出口端与增压管路10的入口端连接。增压管路10连通冷却通道6与贮箱2，其出口端位于贮箱气垫端。所述气垫端指的是贮箱上部有气体的一端。The safety valve 1 is arranged on the storage tank 2 and is located at the air cushion end of the storage tank. The filling pipeline 3 communicates with the storage tank 2. When filling, the liquid propellant 12 enters the storage tank from the filling pipeline 3 through the filling valve 4. The main supply pipeline 8 communicates with the storage tank 2 , and the main supply pipeline 8 is provided with a main valve 9 . Downstream of the main valve 9, the main supply pipeline 8 is divided into two branches, the coolant pipeline 8a and the combustion agent pipeline 8b, wherein the coolant pipeline 8a communicates with the liquid collection chamber 7, and a one-way valve is also set on the branch. The valve 5 and the combustion agent pipeline 8b communicate directly with the combustion chamber 11. The slot-and-rib cooling channel 6 is arranged between the inner and outer walls of the combustion chamber 11 , the inlet end of the cooling channel 6 is connected to the liquid collection chamber 7 , and the outlet end is connected to the inlet end of the booster pipeline 10 . The pressurized pipeline 10 communicates with the cooling channel 6 and the storage tank 2, and its outlet end is located at the air cushion end of the storage tank. The air cushion end refers to the end with gas on the upper part of the storage tank.
作为冷却剂的推进剂12必须是液体，且要求其具有较高的饱和蒸汽压(常温下高于1MPa，例如，N2O在287.15K时的饱和蒸汽压为4.58MPa，在298.15K时的饱和蒸汽压约为5.38MPa)，加热条件下不易分解，与冷却通道室壁材料具有较好的相容性。The propellant 12 as the coolant must be liquid, and it is required to have a higher saturated vapor pressure (higher than 1MPa at room temperature, for example, the saturated vapor pressure of N2O at 287.15K is 4.58MPa, and at 298.15K The saturated vapor pressure is about 5.38MPa), it is not easy to decompose under heating conditions, and it has good compatibility with the wall material of the cooling channel.
冷却通道6的工作原理与通常的再生冷却方式相同，由内部的槽肋式结构(内壁)和外部支承结构(外壁)构成，内壁采用热导率较高的铜合金材料，通过机械加工铣出矩形槽道和肋片供冷却剂流动；外壁采用不锈钢或高温合金以承受燃烧室11内的高温和高压。内外结构之间采用焊接方式密封。The working principle of the cooling channel 6 is the same as the usual regenerative cooling method. It is composed of an internal groove rib structure (inner wall) and an external support structure (outer wall). The inner wall is made of copper alloy material with high thermal conductivity, which is milled out by machining Rectangular channels and fins are used for coolant flow; the outer wall is made of stainless steel or high-temperature alloy to withstand the high temperature and high pressure in the combustion chamber 11 . The internal and external structures are sealed by welding.
在开始工作之前，打开加注阀4，将液体推进剂由加注管路3加注到贮箱2内。加注完成后，关闭加注阀4，贮箱2内留有一定体积的气垫，达到平衡后，气垫压强为推进剂的饱和蒸汽压。Before starting to work, the filling valve 4 is opened, and the liquid propellant is filled into the storage tank 2 through the filling pipeline 3 . After the filling is completed, the filling valve 4 is closed, and there is a certain volume of air cushion in the storage tank 2. After reaching equilibrium, the pressure of the air cushion is the saturated vapor pressure of the propellant.
发动机开始工作时，开启主阀9，贮箱2内的液体推进剂在气垫压力作用下从主供应管路8流出，贮箱2内的压力将降低，根据相平衡关系，贮箱内一部分液体将气化，以弥补液体推进剂排出所空出的气相体积。随着工作的继续，气垫体积增大，贮箱2中的压力和温度都将降低。When the engine starts to work, the main valve 9 is opened, and the liquid propellant in the storage tank 2 flows out from the main supply pipeline 8 under the pressure of the air cushion, and the pressure in the storage tank 2 will decrease. According to the phase equilibrium relationship, a part of the liquid in the storage tank will will be vaporized to make up for the volume of the gas phase vacated by the expulsion of the liquid propellant. Along with the continuation of work, the air cushion volume increases, and the pressure and temperature in the storage tank 2 all will reduce.
由贮箱2流出的液体推进剂12，流经主阀9后，一部分经燃烧剂管路8b直接进入燃烧室11，进行燃烧反应产生高温燃气，从而产生推力。另一小部分经冷却剂管路8a，流经单向阀5，进入集液腔7内，由集液腔7分配到燃烧室11外布置的槽肋式冷却通道6内。作为冷却剂的该部分液体推进剂在冷却通道6内吸收燃气经过燃烧室11内壁传递的热量，温度升高并气化，同时冷却了燃烧室室壁。气化后的推进剂由冷却通道6流出后经增压管路10回到贮箱2内，实现对贮箱2的压力补偿和热补偿，从而维持贮箱2的压强在工作过程中基本恒定，直到贮箱2内的液体推进剂全部排空，系统停止工作。The liquid propellant 12 flowing out of the storage tank 2 flows through the main valve 9, and part of it directly enters the combustion chamber 11 through the combustion agent pipeline 8b, and undergoes combustion reaction to generate high-temperature gas, thereby generating thrust. Another small part passes through the coolant pipeline 8a, flows through the one-way valve 5, enters the liquid collection chamber 7, and is distributed by the liquid collection chamber 7 to the slot-and-rib cooling channel 6 arranged outside the combustion chamber 11. The part of the liquid propellant used as the coolant absorbs the heat transferred by the gas through the inner wall of the combustion chamber 11 in the cooling passage 6, the temperature rises and gasifies, and at the same time cools the chamber wall of the combustion chamber. The gasified propellant flows out from the cooling channel 6 and returns to the storage tank 2 through the pressurization pipeline 10 to realize pressure compensation and heat compensation for the storage tank 2, thereby maintaining the pressure of the storage tank 2 basically constant during the working process , until the liquid propellant in the storage tank 2 is completely emptied, the system stops working.
其中安全阀1在贮箱2的压强高于安全阈值时打开，排出部分气体以确保贮箱压强不致过高；贮箱2的压强低于安全阈值时，安全阀1保持关闭。The safety valve 1 opens when the pressure of the storage tank 2 is higher than the safety threshold, and discharges part of the gas to ensure that the pressure of the storage tank is not too high; when the pressure of the storage tank 2 is lower than the safety threshold, the safety valve 1 remains closed.
其中单向阀5防止推进剂逆向流动，确保冷却通道6内的气体由增压管路10进入贮箱2。Wherein the one-way valve 5 prevents the propellant from flowing backwards, and ensures that the gas in the cooling channel 6 enters the storage tank 2 from the booster pipeline 10 .
所述冷却通道6，可以布置在固-液混合火箭发动机的前燃室、装药段、后燃室或喷管中的一段或几段，可以串联布置或并联布置，根据冷却和增压的需求具体确定其布置方式。所述冷却通道6亦可用于液体推进剂火箭发动机的自增压，可以布置在液体推进剂火箭发动机的燃烧室中的一段或多段；可以串联布置或并联布置。The cooling channel 6 can be arranged in one or more sections of the front combustion chamber, charge section, after-combustion chamber or nozzle of the solid-liquid hybrid rocket engine, and can be arranged in series or in parallel, depending on the cooling and supercharging Requirements specifically determine its layout. The cooling channel 6 can also be used for self-pressurization of the liquid propellant rocket motor, and can be arranged in one or more sections of the combustion chamber of the liquid propellant rocket motor; it can be arranged in series or in parallel.
本发明基于再生冷却的自增压供应系统主要应用于液体推进系统或固-液混合推进系统，其优点在于：The self-pressurized supply system based on regenerative cooling of the present invention is mainly applied to liquid propulsion systems or solid-liquid hybrid propulsion systems, and its advantages are:
(1)基于再生冷却的自增压供应系统不需要增压气瓶和涡轮泵就能对推进剂产生较高的增压压力，在保证一定增压性能的同时减小了供应系统的质量和复杂性；(1) The self-supercharging supply system based on regenerative cooling can generate a high boost pressure for the propellant without the need for booster cylinders and turbo pumps, which reduces the quality and cost of the supply system while ensuring a certain boost performance. Complexity;
(2)基于再生冷却的自增压供应系统不需要增压气瓶、减压阀和涡轮泵等造价昂贵的部件，降低了供应系统的成本；(2) The self-pressurized supply system based on regenerative cooling does not require expensive components such as pressurized cylinders, pressure reducing valves and turbo pumps, which reduces the cost of the supply system;
(3)基于再生冷却的自增压供应系统在增压的同时能实现对燃烧室壁面的冷却，适用于液体推进系统；对于固-液混合推进系统，在冷却段不需要设置高硅氧等昂贵的隔热内衬，可节约成本，确保安全。(3) The self-pressurization supply system based on regenerative cooling can cool the wall of the combustion chamber while supercharging, which is suitable for liquid propulsion systems; for solid-liquid hybrid propulsion systems, it is not necessary to set high silicon oxygen in the cooling section Expensive insulating liner for cost savings and safety.
附图说明Description of drawings
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例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，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动性的前提下，还可以根据这些附图获得其他的附图。In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only These are some embodiments of the present invention. For those skilled in the art, other drawings can also be obtained according to these drawings without any creative effort.
图1本发明中自增压系统的示意图；The schematic diagram of self-supercharging system in Fig. 1 the present invention;
图2本发明实施例中槽肋式冷却通道的三维立体图；Fig. 2 is a three-dimensional perspective view of the slot-and-rib cooling channel in the embodiment of the present invention;
图3本发明实施例中贮箱压强随工作时间变化的曲线图。Fig. 3 is a graph showing the variation of tank pressure with working time in the embodiment of the present invention.
图例说明：illustration:
1-安全阀；2-贮箱；3-加注管路；4-加注阀；5-单向阀；6-冷却通道；7-集液腔；8-主供应管路；8a-冷却剂管路；8b-燃烧剂管路；9-主阀；10-增压管路；11-燃烧室；12-液体推进剂；61-燃烧室内壁面，62-燃烧室外壁面，63-槽肋结构。1-safety valve; 2-storage tank; 3-filling pipeline; 4-filling valve; 5-check valve; 6-cooling channel; 7-collecting chamber; 8-main supply pipeline; 8a-cooling 8b-combustion agent pipeline; 9-main valve; 10-pressurization pipeline; 11-combustion chamber; 12-liquid propellant; 61-combustion inner wall, 62-combustion outer wall, 63-groove rib structure.
具体实施方式detailed description
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
本发明“一种基于再生冷却的自增压供应系统”包括：安全阀1、贮箱2、加注管路3、加注阀4、单向阀5、冷却通道6、集液腔7、主供应管路8、冷却剂管路8a、燃烧剂管路8b、主阀9、增压管路10、燃烧室11、推进剂12。The present invention "a self-pressurized supply system based on regenerative cooling" includes: a safety valve 1, a storage tank 2, a filling pipeline 3, a filling valve 4, a one-way valve 5, a cooling channel 6, a liquid collection chamber 7, Main supply line 8 , coolant line 8 a , combustion agent line 8 b , main valve 9 , booster line 10 , combustion chamber 11 , propellant 12 .
在本实施例中，采用氧化亚氮N2O作为液体推进剂。In this embodiment, nitrous oxide N 2 O is used as the liquid propellant.
在开始工作之前，打开加注阀4，将液体推进剂由加注管路3加注到贮箱2内。加注完成后，关闭加注阀4，贮箱2内留有一定体积的气垫，达到平衡后，气垫压强为推进剂的饱和蒸汽压。环境温度为287K时，贮箱内的压力约为4.58MPa。Before starting to work, the filling valve 4 is opened, and the liquid propellant is filled into the storage tank 2 through the filling pipeline 3 . After the filling is completed, the filling valve 4 is closed, and there is a certain volume of air cushion in the storage tank 2. After reaching equilibrium, the pressure of the air cushion is the saturated vapor pressure of the propellant. When the ambient temperature is 287K, the pressure in the tank is about 4.58MPa.
发动机开始工作时，打开主阀9，贮箱2内的液体推进剂在气垫压力作用下从主供应管路8流出，同时贮箱2内的一部分液体将气化，气垫体积增大，压力和温度都有所降低。When the engine starts to work, the main valve 9 is opened, and the liquid propellant in the storage tank 2 flows out from the main supply pipeline 8 under the pressure of the air cushion, and at the same time, a part of the liquid in the storage tank 2 will be vaporized, and the volume of the air cushion will increase. The temperature has been lowered.
由贮箱2流出的液体推进剂12，流经主阀9后，一部分经燃烧剂管路8b进入燃烧室11，进行燃烧反应产生高温燃气，从而产生推力。另一部分经冷却剂管路8a，流经单向阀5，进入集液腔7内，由集液腔7分配到燃烧室11外布置的槽肋式冷却通道6内。其中槽肋式冷却通道6的结构如图2所示，内壁面采用锆铜材料，外壁面采用30CrMnSi材料。The liquid propellant 12 flowing out of the storage tank 2 flows through the main valve 9, and part of it enters the combustion chamber 11 through the combustion agent pipeline 8b, and undergoes combustion reaction to generate high-temperature gas, thereby generating thrust. The other part passes through the coolant pipeline 8a, flows through the one-way valve 5, enters the liquid collection chamber 7, and is distributed by the liquid collection chamber 7 to the slot-and-rib cooling channel 6 arranged outside the combustion chamber 11. The structure of the groove-rib cooling channel 6 is shown in Fig. 2, the inner wall surface is made of zirconium copper material, and the outer wall surface is made of 30CrMnSi material.
如图3所示，横轴表示时间，纵轴表示贮箱压力，实线表示当有4.1％的再生冷却出口流量用作自增压气体时，贮箱内压力随时间变化的曲线；虚线表示无再生冷却系统时，贮箱内压力随时间变化的曲线。可以看到，本发明中的贮箱内的压力在0～约3500秒时段，基本保持稳定。其原理是：液体推进剂在冷却通道6内吸收燃气传递的热量，温度升高并气化，同时冷却燃烧室室壁。气化后的推进剂由冷却通道6流出后，经增压管路10回到贮箱2内，实现对贮箱2的压力补偿和热补偿，从而维持贮箱2内的压强在工作过程中恒定，一直保持在4.5MPa左右，直到贮箱2内的液体推进剂排空，系统停止工作。而无再生冷却系统时，贮箱内压力急剧下降，基本无稳定段。As shown in Figure 3, the horizontal axis represents time, the vertical axis represents the tank pressure, and the solid line represents the curve of the pressure in the tank with time when 4.1% of the regenerative cooling outlet flow is used as self-pressurized gas; the dotted line represents When there is no regenerative cooling system, the pressure inside the tank changes with time. It can be seen that the pressure in the storage tank in the present invention is basically kept stable during the period of 0 to about 3500 seconds. The principle is: the liquid propellant absorbs the heat transferred by the gas in the cooling channel 6, the temperature rises and gasifies, and at the same time cools the chamber wall of the combustion chamber. After the gasified propellant flows out from the cooling channel 6, it returns to the storage tank 2 through the pressurization pipeline 10 to realize pressure compensation and heat compensation for the storage tank 2, thereby maintaining the pressure in the storage tank 2 during the working process. Constant, kept at about 4.5MPa, until the liquid propellant in the storage tank 2 is emptied, and the system stops working. When there is no regenerative cooling system, the pressure in the storage tank drops sharply, and there is basically no stable section.
如果工作过程中，贮箱2的压强高于安全阈值，安全阀1将打开，排出部分气体以确保贮箱压强不致过高；贮箱2的压强低于安全值时，安全阀1保持关闭。其中单向阀5防止推进剂逆向流动，确保冷却通道6内的气体由增压管路10进入贮箱2If the pressure of storage tank 2 is higher than the safety threshold during work, safety valve 1 will open to discharge part of the gas to ensure that the pressure of the storage tank will not be too high; when the pressure of storage tank 2 is lower than the safe value, safety valve 1 will remain closed. Wherein the one-way valve 5 prevents the reverse flow of the propellant, and ensures that the gas in the cooling channel 6 enters the storage tank 2 from the booster pipeline 10
以上所述，仅为本发明的具体实施方式，但本发明的保护范围并不局限于此，任何熟悉本技术领域的技术人员在本发明揭露的技术范围内，可轻易想到的变化或替换，都应涵盖在本发明的保护范围之内。因此，本发明的保护范围应该以权利要求书的保护范围为准。The above is only a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Anyone skilled in the art can easily think of changes or substitutions within the technical scope disclosed in the present invention. All should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be determined by the protection scope of the claims.
Claims (5)
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| CN108119260B (en) * | 2018-01-23 | 2023-12-05 | 陕西蓝箭航天技术有限公司 | Liquid engines and carriers |
| CN108590888A (en) * | 2018-03-27 | 2018-09-28 | 北京零壹空间科技有限公司 | Cryogenic propulsion system |
| CN108590887A (en) * | 2018-03-27 | 2018-09-28 | 北京零壹空间科技有限公司 | Cryogenic propulsion system based on steam cooling screen |
| CN108826018B (en) * | 2018-07-19 | 2024-03-26 | 北京航天动力研究所 | Microminiature pressurization system and pressurization method based on liquefied gas |
| CN109779787A (en) * | 2018-12-28 | 2019-05-21 | 中国运载火箭技术研究院 | Reusable aircraft liquid methane circulating pre-cooling system |
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| CN109826725B (en) * | 2019-02-19 | 2024-08-09 | 北京星际荣耀空间科技股份有限公司 | Power mechanism of propulsion system, propulsion system and liquid rocket system |
| CN110030115A (en) * | 2019-03-27 | 2019-07-19 | 上海宇航系统工程研究所 | A kind of propellant tank combination pressure charging system |
| CN110131073B (en) * | 2019-05-06 | 2022-02-18 | 上海空间推进研究所 | Space propulsion system suitable for filling of large-capacity storage tank |
| CN110700966A (en) * | 2019-09-18 | 2020-01-17 | 北京星际荣耀空间科技有限公司 | Rocket engine heat exchanger and aerospace vehicle |
| CN110979738A (en) * | 2019-12-23 | 2020-04-10 | 北京宇航推进科技有限公司 | Pressure-drop type integrated power system and power propulsion method |
| CN111042950A (en) * | 2019-12-31 | 2020-04-21 | 西北工业大学 | Motor Pump Auxiliary Speed Regulated Turbine Pump Supply System |
| CN112160848A (en) * | 2020-09-29 | 2021-01-01 | 西北工业大学 | Self-supercharging solid-liquid mixed engine |
| CN112196695A (en) * | 2020-10-19 | 2021-01-08 | 北京天兵科技有限公司 | Self-generated pressurization system and pressurization method for liquid rocket engine |
| CN113386981B (en) * | 2021-06-07 | 2022-09-27 | 上海空间推进研究所 | Corrugated conical column diaphragm storage tank |
| CN113565652B (en) * | 2021-07-27 | 2022-08-19 | 中国人民解放军国防科技大学 | Multilayer fixed high-temperature fluid channel |
| CN114320667B (en) * | 2021-09-16 | 2023-06-20 | 西北工业大学 | A squeeze-type oxidant supply solid-liquid hybrid engine |
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