CN217682014U

CN217682014U - Valve control system for rocket engine, engine and sounding rocket

Info

Publication number: CN217682014U
Application number: CN202221224204.XU
Authority: CN
Inventors: 谢坤; 戈鑫; 曾诚; 张春本; 陈涛; 常克宇
Original assignee: Zhejiang Landspace Technology Co Ltd
Current assignee: Zhejiang Landspace Technology Co Ltd
Priority date: 2022-05-19
Filing date: 2022-05-19
Publication date: 2022-10-28
Anticipated expiration: 2032-05-19

Abstract

The utility model provides a valve control system, engine and sounding rocket for rocket engine. The valve control system includes: the system comprises a control valve group, a methane main valve and an oxygen main valve; wherein the control valve group comprises a first valve, a second valve and a third valve. The first valve is connected with the methane main valve through a first control path conduit so as to control the opening of the methane main valve; the second valve is connected with the oxygen main valve through a second control path conduit so as to control the opening of the oxygen main valve; the third valve is connected with the methane main valve and the oxygen main valve through a third control path conduit. The third control path conduit comprises a first parallel branch and a second parallel branch which are connected in parallel and are used for being respectively connected with the methane main valve and the oxygen main valve so as to control the methane main valve and the oxygen main valve to be closed simultaneously. The valve control system can open and close the oxygen main valve and the methane main valve in a time-sharing manner, and the reliability of the valve control system is improved.

Description

Valve control system for rocket engine, engine and sounding rocket

Technical Field

The utility model relates to a space flight technology field, concretely relates to a valve control system, engine and sounding rocket for rocket engine.

Background

The sounding rocket is mainly used for sounding the near-earth space and performing partial scientific experiments, and is an effective vehicle with the flying height of 30-200 kilometers. The sounding rocket can detect atmospheric structures, components, parameters and the like in different height directions so as to research multiple natural phenomena such as a geomagnetic field, an ionosphere, solar ultraviolet rays, cosmic rays and the like, and provide important environment variable parameters for the development and the use of aircrafts such as a carrier rocket, a man-made satellite, a manned spacecraft, a ballistic missile and the like.

The rocket valve is used as a core control component of a liquid rocket power system and controls the supply of propellant, and the operational reliability of the rocket valve is related to the success of rocket launching. In a rocket-sounding engine, two independent valve control systems for the fuel supply system and the oxidant supply system are usually set up. Propellant waste results because the methane main valve controlling the fuel supply system and the oxygen main valve controlling the oxidizer supply system cannot be closed at the same time.

Therefore, it is important to design a valve control system for a rocket engine for a sounding rocket.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to overcome prior art's not enough, provide a valve control system, engine and visit empty rocket for rocket engine.

The utility model provides a valve control system, engine and sounding rocket for rocket engine, wherein, valve control system includes: a control valve group, a methane main valve and an oxygen main valve; wherein the control valve group comprises a first valve, a second valve and a third valve; the methane main valve is used for controlling fuel to enter the thrust chamber, and the oxygen main valve is used for controlling oxidant to enter the thrust chamber; the first valve is connected with the methane main valve through a first control path conduit so as to control the opening of the methane main valve; the second valve is connected with the oxygen main valve through a second control path conduit so as to control the opening of the oxygen main valve; the third valve is connected with the methane main valve and the oxygen main valve through a third control path conduit; the third control path conduit comprises a first parallel branch and a second parallel branch which are connected in parallel and are used for respectively connecting the methane main valve and the oxygen main valve so as to control the methane main valve and the oxygen main valve to be closed simultaneously.

Another aspect of the present invention provides a rocket engine, including: the valve control system, the thrust chamber, the oxygen tank and the methane tank as described above; the oxygen tank is used for storing an oxidant, and the methane tank is used for storing fuel; the thrust chamber is connected with the oxygen storage tank through an oxygen path conduit and is connected with the methane storage tank through a methane path conduit; the oxygen main valve is arranged on the oxygen path guide pipe, and the methane main valve is arranged on the methane path guide pipe.

According to an embodiment of the present invention, the methane conduit is provided with a first adjusting element for adjusting the fuel flow in the methane conduit.

According to an embodiment of the present invention, the inlet and the outlet of the first adjusting element are provided with a first pressure sensor and a second pressure sensor, respectively, for measuring the inlet pressure and the outlet pressure of the first adjusting element, respectively.

According to an embodiment of the invention, the thrust chamber head is provided with a cartridge for igniting fuel and oxidant in the combustion chamber of the thrust chamber.

According to an embodiment of the utility model, the device also comprises a first blow-off gas cylinder and a second blow-off gas cylinder; the first blowing gas cylinder and the second blowing gas cylinder are respectively connected with the methane main valve and the oxygen main valve through a first blowing guide pipe and a second blowing guide pipe; the first blowing guide pipe and the second blowing guide pipe are provided with a first one-way valve and a second one-way valve so as to respectively control the first blowing gas cylinder and the second blowing gas cylinder to blow gas to the oxygen path guide pipe and the methane path guide pipe.

According to an embodiment of the utility model, the device also comprises a control gas cylinder and a control gas circuit; the control valve group is a pneumatic valve; the control gas cylinder is connected with the control valve group through the control gas circuit so as to control the control valve group to be opened or closed.

According to an embodiment of the present invention, the device further comprises a thrust chamber support; the thrust chamber bracket is connected with the thrust chamber through welding; the control valve group is arranged on the thrust chamber bracket.

According to one embodiment of the present invention, a liquid collecting ring is disposed around the axial direction of the thrust chamber at the lower portion thereof, and the liquid collecting ring is communicated with the methane passage conduit through a fuel nozzle pipe; the outer wall of the thrust chamber is provided with a cooling channel along the axial direction of the thrust chamber, and the cooling channel is communicated with the liquid collecting ring and extends to the head of the thrust chamber; fuel flows through the collector ring and the cooling channels to cool the thrust chamber.

Another aspect of the present invention provides a sounding rocket, comprising a valve control system, a thrust chamber, an oxygen tank, and a methane tank as described above; the oxygen tank is used for storing an oxidant, and the methane tank is used for storing fuel; the valve control system is used for controlling the oxygen storage tank and the methane storage tank to respectively provide oxidant and fuel for the thrust chamber, so that the oxidant and the fuel enter the thrust chamber to be combusted to generate thrust.

According to the utility model discloses a valve control system for rocket engine, methane main valve and oxygen main valve are controlled respectively through parallelly connected first parallelly connected branch road and the parallelly connected branch road of second to the control valve group, have realized the purpose that simultaneous control methane main valve and oxygen main valve closed, and can reduce the waste of propellant.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate exemplary embodiments of the invention and together with the description, serve to explain the principles of the invention.

Fig. 1 is a schematic view of a valve control system and an engine of a rocket engine according to an embodiment of the present invention.

Description of the reference numerals:

1-thrust chamber, 2-cartridge, 3-control valve group, 4-oxygen main valve, 5-methane main valve, 6-second one-way valve, 7-first regulating element, 8-thrust chamber support, 9-oxygen line conduit, 10-methane line conduit, 11-first control line conduit, 12-second control line conduit, 13-first parallel branch, 14-second parallel branch, 15-first one-way valve, 16-first valve, 17-second valve, 18-third valve, 19-third control line conduit, 20-oxygen tank, 21-methane tank, 22-first blow-off gas cylinder, 23-second blow-off gas cylinder, 24-first blow-off conduit, 25-second blow-off conduit, 26-control gas cylinder, 27-control gas circuit, P1-first pressure sensor, P2 second pressure sensor.

Detailed Description

The features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention, for the purpose of illustrating the principles of the invention. Additionally, the components in the drawings are not necessarily to scale. For example, the dimensions of some of the structures or regions in the figures may be exaggerated relative to other structures or regions to help improve understanding of embodiments of the present invention.

The directional terms appearing in the following description are directions shown in the drawings and are not intended to limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise stated, the terms "mounted", "connected" and "connected" should be interpreted broadly, and may be, for example, a fixed connection, a detachable connection, or an integral connection; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood as the case may be, by those of ordinary skill in the art.

Furthermore, the terms "comprises," "comprising," "includes," "including," "has," "having" or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a structure or component comprising a list of elements does not include only those elements but may include other mechanical components not expressly listed or inherent to such structure or component. Without further limitation, an element defined by the phrases "comprising 8230; \8230;" 8230; "does not exclude the presence of additional like elements in an article or device comprising the element.

Spatial relationship terms such as "below," "at \8230," "lower," "above," "at \8230," "upper," "higher," and the like are used for convenience in description to explain the positioning of one element relative to a second element, indicating that the terms are intended to encompass different orientations of the device in addition to orientations different from those shown in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc., and are not particularly meant to imply a sequential or chronological meaning, and should not be taken as limiting. Like terms refer to like elements throughout the description.

In the following description of the present invention, only "rocket," "launch vehicle," "spacecraft," "space vehicle," or "missile" may be used in a certain scenario description, which is for convenience of description only and the content is not limited to the specific words used. In general, rockets of the invention include both launch vehicles for launching satellites or spacecraft or other detectors, space vehicles, target projectiles and the like, as well as various missiles, rocket projectiles and the like for launching military loads, and similar products capable of delivering payloads into the air. Those skilled in the art, in interpreting the above specific terms, should not be construed as limiting the rocket to only one of a spacecraft or a missile, depending on the specific terms used in describing the scenario, thereby reducing the scope of the present invention.

It will be apparent to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples thereof.

As shown in fig. 1, the present invention provides a valve control system for a rocket engine, comprising: a control valve group 3, a methane main valve 5 and an oxygen main valve 4. The control valve group 3 includes a first valve 16, a second valve 17, and a third valve 18. A methane main valve 5 is used to control the fuel into the thrust chamber 1 and an oxygen main valve 4 is used to control the oxidant into the thrust chamber 1. The first valve 16 is connected to the methane main valve 5 through the first control conduit 11 to control the opening of the methane main valve 5. The second valve 17 is connected with the oxygen main valve 4 through a second control path conduit 12 to control the opening of the oxygen main valve 4. The third valve 18 is connected to the methane main valve 5 and the oxygen main valve 4 via a third control line conduit 19. The third control conduit 19 comprises a first parallel branch 13 and a second parallel branch 14 connected in parallel for connecting the methane main valve 5 and the oxygen main valve 4, respectively, to control the closing of the methane main valve 5 and the oxygen main valve 4 simultaneously.

Specifically, since the valve control system needs to be in the oxycombustion state when it is ignited, the oxygen main valve is required to be opened before the methane main valve, and therefore the oxygen main valve is required to be opened by independent control. For the closing of the oxygen main valve and the methane main valve, because the closing time responses of the oxygen main valve and the methane main valve have dispersion, if the methane main valve is closed later, redundant fuel (such as methane) is discharged after the engine is shut down, and the excess fuel and the ambient oxygen are combusted again, so that the tempering effect is aggravated. At the same time, it also results in waste of fuel. Similarly, if the oxygen valve closes later, oxidant (e.g., liquid oxygen) is wasted.

In this embodiment, only the control valve group including three valves is taken as an example for description, and the number of the valves in the control valve group is not limited. In the valve control system of this embodiment, the first valve is connected to the methane main valve by a single line through the first control line conduit, and is used for opening the methane main valve. The second valve is connected with the oxygen main valve single line through a second control path conduit and is used for opening the oxygen main valve. And the third valve is respectively connected with the methane main valve and the oxygen main valve through the first parallel branch and the second parallel branch which are connected in parallel and is used for closing the methane main valve and the oxygen main valve at the same time.

The methane main valve and the oxygen main valve in this embodiment may be cut-off type valve switches, that is, valves having only a switching function. The valve can be an adjusting valve switch, namely a switch capable of adjusting the opening range of the valve, and the flow of fluid in the pipeline can be adjusted.

On the other hand, as shown in fig. 1, the present invention also provides a rocket engine, including: the valve control system, the thrust chamber 1, the oxygen tank 20 and the methane tank 21 as described above. The oxygen tank 20 is used to store oxidant and the methane tank 21 is used to store fuel. The thrust chamber 1 is connected to an oxygen storage tank 20 through an oxygen line conduit 9 and to a methane storage tank 21 through a methane line conduit 10. The oxygen main valve 4 is provided in the oxygen line pipe 9, and the methane main valve 5 is provided in the methane line pipe 10.

Particularly, in recent years, with the rapid development of the aerospace industry, the market demand for small sounding rockets has been increasing. The method has incomplete statistics, and the annual launching volume of the small-sized sounding rocket is up to thousands of rockets. The current small-sized exploration rocket mainly adopts solid fuel, however, the solid fuel engine has the defects of high cost, low reliability, small power and the like. In order to reduce the cost of the sounding rocket, it is conceivable to use a liquid fuel engine. Liquid rocket engines can be classified into extrusion engines and pump engines according to the propellant supply principle.

Although the pumping-type engine greatly improves the engine thrust, the pumping-type engine is not suitable for the low-altitude flight of the sounding rocket and the situation of low cost budget due to the addition of the turbine pump assembly and the secondary system and the increase of the weight and the size of the engine. The extrusion type rocket engine has the characteristics of simple system and lower cost. Although the thrust of the extrusion type rocket engine is small, the extrusion type rocket engine can completely cover the requirement range of a small sounding rocket, and is an ideal engine system scheme.

The rocket engine of the embodiment adopts liquid propellant, and the fuel is easy to obtain. Wherein the oxygen tank is configured to store liquid oxidant (e.g., liquid oxygen) and the methane tank is configured to store liquid fuel (e.g., liquid methane), thereby reducing the cost of the rocket engine as compared to engines that use solid fuel. Liquid oxymethane as a propellant also has the characteristics of green, no pollution and high reusability, is widely used in the field of rocket engines, and starts to show the horn. Meanwhile, the engine of the embodiment does not have the turbine pump assembly and the secondary system thereof, so the system is simple and has low success. In addition, the rocket engine of this embodiment need not the precooling and can reliably work, has shortened the engine preparation time before the ignition, and oxygen main valve and methane main valve need not set up the let out mouth, and the structure is simpler, can be applicable to on the lower sounding rocket of flying height or target bomb.

As shown in fig. 1, according to an embodiment of the present invention, the methane conduit 10 is provided with a first adjusting element 7, and the first adjusting element 7 is used for adjusting the fuel flow in the methane conduit 10.

As shown in fig. 1, according to an embodiment of the present invention, the inlet and the outlet of the first regulating element 7 are provided with a first pressure sensor P1 and a second pressure sensor P2, respectively, for measuring the inlet pressure and the outlet pressure of the first regulating element 7, respectively.

In this embodiment, the oxygen conduit may also be provided with a second regulating element for regulating the flow of oxidant in the oxygen conduit. Similarly, a pressure sensor may be provided at the inlet and outlet of the second control element, respectively, for measuring the inlet pressure and the outlet pressure of the second control element. For example, the engine needs to generate 15KN of thrust. The drift diameters of the oxygen channel conduit and the methane channel conduit in the embodiment can be set to be 14-16 mm, the liquid oxygen pressure is set to be 6-7MPa, and the methane pressure is set to be 8-9MPa. Through the inlet and outlet pressure measuring points of the first and second regulating elements, the flow resistance coefficients of the first and second regulating elements can be calculated to adjust the mixing ratio of the fuel and the oxidant in the thrust chamber.

According to one embodiment of the invention, the thrust chamber 1 is provided with a cartridge 2 at the head for igniting the fuel and the oxidant in the combustion chamber of the thrust chamber 1.

In this embodiment, the cartridge may be ignited under cable control. High-temperature fuel gas generated by the cartridge igniter enters a combustion chamber of the thrust chamber, fuel and oxidant (such as liquid methane and liquid oxygen) entering the thrust chamber are ignited, and the generated high-temperature working medium is expanded and accelerated in a spray pipe of the thrust chamber and then sprayed out of the spray pipe, so that thrust is generated by using reaction force.

According to an embodiment of the present invention, a first blow-off cylinder 22 and a second blow-off cylinder 23 are further included. The first blowing gas cylinder 22 and the second blowing gas cylinder 23 are connected with the main methane valve 5 and the main oxygen valve 4 through a first blowing conduit 24 and a second blowing conduit 25, respectively. The first and second blow-off

pipes

24 and 25 are provided with the first and second check valves 15 and 6 to control the first and second blow-off

gas cylinders

22 and 23 to blow gas into the oxygen line pipe 9 and the methane line pipe 10, respectively.

In the embodiment, before the engine is ignited or before a test run test of the engine is started, an external air source, namely a first blow-off air cylinder and a second blow-off air cylinder can blow air to the oxygen path conduit and the methane path conduit through the first one-way valve and the second one-way valve respectively so as to blow off the oxygen path conduit and the methane path conduit, impurities, water vapor and the like in an engine system can be blown off, and the reliability of the engine is improved.

Further, the first one-way valve may be integrated on the oxygen main valve and the second one-way valve may be integrated on the methane main valve.

According to the utility model discloses an embodiment still includes control gas cylinder 26 and control gas circuit 27. The control valve group 3 is a pneumatic valve. The control gas cylinder 26 is connected with the control valve group 3 through a control gas path 27 to control the control valve group 3 to open or close.

According to an embodiment of the present invention, a thrust chamber support 8 is further included. The thrust chamber bracket 8 is connected with the thrust chamber 1 through welding. The control valve group 3 is arranged on the thrust chamber bracket 8.

In this embodiment, the thrust chamber bracket may be integrally formed with the thrust chamber by welding. The oxygen main valve, the methane main valve and the control valve set can be arranged on the thrust chamber bracket.

According to the utility model discloses an embodiment, 1 lower part of thrust chamber is provided with the collection liquid ring around its axial, and the collection liquid ring is through fuel nozzle pipe and methane way pipe 10 intercommunication. The outer wall of the thrust chamber 1 is provided with a cooling channel along the axial direction thereof, the cooling channel is communicated with the liquid collecting ring and extends to the head of the thrust chamber 1. The fuel flows through the collector ring and the cooling channels to cool the thrust chamber 1.

In this embodiment, the liquid collecting ring may be disposed at the lowermost portion of the thrust chamber nozzle and provided with a fuel nipple for connection to the methane conduit outlet, with liquid fuel (e.g., liquid methane) flowing through the liquid collecting ring and cooling channels into the thrust chamber head cavity. The liquid methane of the engine of the present embodiment is capable of cooling the entire thrust chamber.

In another aspect, as shown in fig. 1, the present invention further provides a sounding rocket including the valve control system, the thrust chamber 1, the oxygen tank 20, and the methane tank 21 as described above. The oxygen tank 20 is used to store oxidant and the methane tank 21 is used to store fuel. The valve control system is used for controlling the oxygen storage tank 20 and the methane storage tank 21 to respectively supply the oxidant and the fuel to the thrust chamber 1, so that the oxidant and the fuel enter the thrust chamber 1 to be combusted to generate thrust.

The sounding rocket of the embodiment comprises a valve control system, a thrust chamber, an oxygen storage tank and a methane storage tank, wherein the valve control system, the thrust chamber, the oxygen storage tank and the methane storage tank form a propellant supply system of the sounding rocket, and the propellant supply system is used for conveying fuel and oxidant (such as high-pressure low-temperature liquid methane and liquid oxygen) in the storage tanks to the thrust chamber for combustion. The sounding rocket system is simple, low in success rate and capable of reliably working without precooling the engine. By adopting the sounding rocket of the embodiment, the cost is reduced, and the existing sounding rocket based on solid fuel can be replaced.

In this embodiment, the sounding rocket may be connected in parallel with a plurality (including two) of the rocket motors at the propellant inlet, so as to provide a larger thrust for the flight of the sounding rocket.

The above embodiments of the present invention can be combined with each other, and have corresponding technical effects.

The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements (such as structure, process) and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A valve control system for a rocket engine, comprising: a control valve group, a methane main valve and an oxygen main valve;

wherein the control valve group comprises a first valve, a second valve and a third valve;

the methane main valve is used for controlling fuel to enter the thrust chamber, and the oxygen main valve is used for controlling oxidant to enter the thrust chamber;

the first valve is connected with the methane main valve through a first control path conduit so as to control the opening of the methane main valve;

the second valve is connected with the oxygen main valve through a second control path conduit so as to control the opening of the oxygen main valve;

the third valve is connected with the methane main valve and the oxygen main valve through a third control path conduit; the third control path conduit comprises a first parallel branch and a second parallel branch which are connected in parallel and are used for being respectively connected with the methane main valve and the oxygen main valve so as to control the methane main valve and the oxygen main valve to be closed simultaneously.

2. A rocket engine, comprising: the valve control system of claim 1, a thrust chamber, an oxygen tank, and a methane tank;

the oxygen tank is used for storing an oxidant, and the methane tank is used for storing fuel;

the thrust chamber is connected with the oxygen storage tank through an oxygen path conduit and is connected with the methane storage tank through a methane path conduit;

the oxygen main valve is arranged on the oxygen path guide pipe, and the methane main valve is arranged on the methane path guide pipe.

3. A rocket engine as recited in claim 2, wherein said methanic conduit is provided with a first adjustment element for adjusting a fuel flow within said methanic conduit.

4. A rocket engine as recited in claim 3, wherein said first regulating element is provided with a first pressure sensor and a second pressure sensor at an inlet and an outlet, respectively, for measuring an inlet pressure and an outlet pressure, respectively, of said first regulating element.

5. A rocket engine as recited in claim 2, wherein said thrust chamber head is provided with a cartridge for igniting fuel and an oxidizer in a combustion chamber of said thrust chamber.

6. A rocket engine as recited in claim 2, further comprising a first blow-off cylinder and a second blow-off cylinder;

the first blowing gas cylinder and the second blowing gas cylinder are respectively connected with the methane main valve and the oxygen main valve through a first blowing guide pipe and a second blowing guide pipe;

the first blowing guide pipe and the second blowing guide pipe are provided with a first one-way valve and a second one-way valve so as to respectively control the first blowing gas cylinder and the second blowing gas cylinder to blow gas to the oxygen path guide pipe and the methane path guide pipe.

7. A rocket engine as recited in claim 2, further comprising a control gas cylinder and a control gas circuit;

the control valve group is a pneumatic valve;

the control gas cylinder is connected with the control valve group through the control gas circuit so as to control the control valve group to be opened or closed.

8. A rocket engine as recited in claim 2, further comprising a thrust chamber support;

the thrust chamber bracket is connected with the thrust chamber through welding;

the control valve group is arranged on the thrust chamber support.

9. A rocket engine as recited in claim 2, wherein said lower thrust chamber portion is provided with a liquid-collecting ring about an axial direction thereof, said liquid-collecting ring being in communication with said methane passage conduit through a fuel nipple;

the outer wall of the thrust chamber is provided with a cooling channel along the axial direction of the thrust chamber, and the cooling channel is communicated with the liquid collecting ring and extends to the head part of the thrust chamber;

fuel flows through the collector ring and the cooling channels to cool the thrust chamber.

10. A sounding rocket comprising the valve control system of claim 1, a thrust chamber, an oxygen tank, and a methane tank;

the valve control system is used for controlling the oxygen storage tank and the methane storage tank to respectively provide oxidant and fuel for the thrust chamber, so that the oxidant and the fuel enter the thrust chamber to be combusted to generate thrust.