CN112343734A - Pneumatic combination valve of rocket engine, rocket engine and carrier rocket - Google Patents
Pneumatic combination valve of rocket engine, rocket engine and carrier rocket Download PDFInfo
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- CN112343734A CN112343734A CN202110021129.0A CN202110021129A CN112343734A CN 112343734 A CN112343734 A CN 112343734A CN 202110021129 A CN202110021129 A CN 202110021129A CN 112343734 A CN112343734 A CN 112343734A
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- valve
- sleeve
- moving assembly
- channel
- valve body
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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
- F02K9/56—Control
- F02K9/58—Propellant feed valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K11/00—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves
- F16K11/10—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with two or more closure members not moving as a unit
- F16K11/14—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with two or more closure members not moving as a unit operated by one actuating member, e.g. a handle
- F16K11/16—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with two or more closure members not moving as a unit operated by one actuating member, e.g. a handle which only slides, or only turns, or only swings in one plane
- F16K11/161—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with two or more closure members not moving as a unit operated by one actuating member, e.g. a handle which only slides, or only turns, or only swings in one plane only slides
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K31/00—Actuating devices; Operating means; Releasing devices
- F16K31/12—Actuating devices; Operating means; Releasing devices actuated by fluid
- F16K31/122—Actuating devices; Operating means; Releasing devices actuated by fluid the fluid acting on a piston
- F16K31/1221—Actuating devices; Operating means; Releasing devices actuated by fluid the fluid acting on a piston one side of the piston being spring-loaded
Abstract
The embodiment of the application provides a pneumatic combination valve of a rocket engine, the rocket engine and a carrier rocket. The pneumatic combination valve of the rocket engine comprises: the valve comprises a valve cover, a valve body, a first moving assembly and a second moving assembly; the valve cover and the valve body enclose to form a cavity; the chamber houses a first portion of the first moving assembly and a first portion of the second moving assembly; the valve body comprises a first valve body part and a second valve body part; the first valve body part is provided with a first passage, and the first moving assembly passes through the first passage; the second valve body has a second passage through which the second moving assembly passes; the first moving assembly and the second moving assembly are used for respectively stopping the first channel and the second channel; the first moving assembly is used for driving the second moving assembly to move, so that the first channel and the second channel are both communicated. According to the embodiment of the application, the fuel and the oxidant can be controlled to enter the fuel gas generator for combustion through the pneumatic combination valve, so that the lightweight design and the structural simplification of the carrier rocket are facilitated.
Description
Technical Field
The application relates to the technical field of carrier rockets, in particular to a pneumatic combination valve of a rocket engine, the rocket engine and the carrier rocket.
Background
In recent years, the aerospace industry in China is developed rapidly, and all the technologies related to the rocket related field are all rapidly advanced. The main power source of the aerospace device is a rocket, and a rocket engine is the most core device of the rocket and is a component with higher technical content. The rocket engine utilizes impulse principle, self-carrying propellant, independent of outside air, changes the propellant in a propellant storage tank or a carrier into high-speed jet flow, and generates thrust due to Newton's third law of motion.
However, in the existing rocket engine, the number of pneumatic valves is large, so that the pneumatic valves are complex to control, the occupied space of a control system of the pneumatic valves is large, the weight of the control system is increased, and the lightweight design and the system simplification of the rocket engine are not facilitated.
Disclosure of Invention
The application aims at the defects of the existing mode and provides a pneumatic combination valve of a rocket engine, the rocket engine and a carrier rocket, and the technical problem that the pneumatic valves are complex to control due to the fact that the pneumatic valves are large in number in the prior art is solved.
In a first aspect, an embodiment of the present application provides a pneumatic combination valve of a rocket engine, including:
the valve comprises a valve cover, a valve body, a first moving assembly and a second moving assembly;
the valve cover and the valve body enclose to form a cavity;
the chamber houses a first portion of the first moving assembly and a first portion of the second moving assembly;
the valve body comprises a first valve body part and a second valve body part; the first valve body has a first passage through which the second portion of the first moving assembly passes; the second valve body portion having a second passage through which a second portion of the second moving assembly passes;
the first moving assembly and the second moving assembly are used for respectively stopping the first channel and the second channel; or the first moving assembly is used for driving the second moving assembly to move, so that the first channel and the second channel are both communicated.
In one possible implementation, the pneumatic combination valve includes at least one of:
the first moving assembly is provided with an adjusting piece, the adjusting piece and the second moving assembly are separated by a first design interval, and the first moving assembly drives the second moving assembly to move through the adjusting piece;
the first and second valve body portions are spaced apart by a second design spacing.
In one possible implementation, the valve cover is provided with a first opening for externally connecting the air source device;
the chambers include a first chamber housing a first portion of the first moving assembly and a second chamber housing a first portion of the second moving assembly;
the first moving assembly comprises a first piston, a first valve core and a first elastic piece, wherein the first piston is connected with the inner wall of the first cavity in a sliding mode, and the first elastic piece is sleeved on the first valve core;
the first chamber comprises a first sub-chamber which is formed by enclosing a first piston and a valve cover, and a first opening is communicated with the first sub-chamber;
one end of the first valve core is fixedly connected with the first piston, and the other end of the first valve core penetrates through the first channel;
two ends of the first elastic piece are respectively abutted against the first piston and the first valve body.
In one possible implementation, the first piston includes a first piston head and a first sleeve;
the first piston head is in sliding connection with the inner wall of the first chamber;
the first valve body part is provided with a second sleeve, the second sleeve is sleeved in the first sleeve, and the second sleeve is connected with the first sleeve in a sliding manner;
the first valve core penetrates through the second sleeve, and the first elastic piece is partially positioned in the second sleeve.
In one possible implementation manner, the first piston further comprises a connecting part fixedly connected with the first sleeve, the connecting part extends into the second cavity, and the adjusting part is fixedly connected with the connecting part;
the second moving assembly comprises a third sleeve, a second valve core and a second elastic piece sleeved on the second valve core;
one end of the second valve core is fixedly connected with the third sleeve, and the other end of the second valve core penetrates through the second channel;
two ends of the second elastic piece are respectively propped against the third sleeve and the second valve body part;
the central axes of the first valve core and the second valve core are parallel;
the first design spacing is a spacing between the trim and the third sleeve.
In one possible implementation, the second valve body part is provided with a fourth sleeve, the fourth sleeve is sleeved in the third sleeve, and the fourth sleeve is connected with the third sleeve in a sliding manner;
the second valve spool passes through the fourth sleeve, and the second elastic part is partially positioned in the fourth sleeve.
In one possible implementation manner, a first sealing ring is arranged between the first sleeve and the second sleeve;
a second sealing ring is arranged between the third sleeve and the fourth sleeve;
a third sealing ring is arranged between the first piston head and the inner wall of the first chamber.
In one possible implementation mode, the pressure parameter and the diameter parameter of the dynamic sealing surface of the pneumatic combination valve meet the design condition; the pressure parameters comprise the pressure of the first channel, the second channel and the first sub-chamber, the dynamic sealing diameter parameters comprise the dynamic sealing surface diameters of the first sealing ring, the second sealing ring and the third sealing ring, and the dynamic sealing surface diameter is the diameter of the sliding surface of the sealing ring.
In a second aspect, embodiments of the present application provide a rocket engine including a pneumatic combination valve as in the first aspect.
In a third aspect, embodiments of the present application provide a launch vehicle comprising a fuel supply, an oxidant supply, a gas generator, and a pneumatic combining valve as in the first aspect;
two ends of one channel of the first channel and the second channel are respectively connected with the fuel supply device and the gas generator, and two ends of the other channel of the first channel and the second channel are respectively connected with the oxidant supply device and the gas generator.
The beneficial technical effects brought by the technical scheme provided by the embodiment of the application comprise:
the pneumatic combination valve comprises a first moving assembly and a second moving assembly, wherein the first moving assembly and the second moving assembly are used for respectively enabling a first channel and a second channel to be cut off, or the first moving assembly is used for driving the second moving assembly to move, so that the first channel and the second channel are both switched on, and therefore fuel and oxidant can be controlled to enter a fuel gas generator to be combusted through one pneumatic combination valve, and the number of pneumatic valves is reduced. Moreover, the first moving assembly can drive the second moving assembly to move, mixed combustion of fuel and oxidant can be achieved only by one set of control system of the pneumatic valve, the control process is simple, the occupied space and the weight of the control system of the pneumatic valve are reduced, and light weight design and structure simplification of the carrier rocket are facilitated.
Additional aspects and advantages of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the present application.
Drawings
The foregoing and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 is a schematic structural diagram of a pneumatic combination valve provided in an embodiment of the present application;
FIG. 2 is an enlarged view of area A of FIG. 1;
FIG. 3 is an enlarged view of region B of FIG. 1;
fig. 4 is a schematic structural diagram of a launch vehicle according to an embodiment of the present application.
Reference numerals:
10-a pneumatic combination valve;
100-a valve body;
110-a first valve body portion, 111-a first channel, 1111-a first communication port, 112-a second sleeve, 130-a first connection seat, 131-a third channel;
120-a second valve body part, 121-a second channel, 1211-a second communication port, 122-a fourth sleeve, 140-a second connecting seat and 141-a fourth channel;
200-a first moving assembly, 210-a first piston, 2101-a first piston head, 2102-a first sleeve, 2103-a connecting part, 220-a first valve core, 221-a first rod part, 222-a first head part, 230-a first elastic part;
300-a second moving assembly, 310-a third sleeve, 320-a second valve core, 321-a second rod part, 322-a second head part, 330-a second elastic part;
400-a conditioning element;
500-valve cap, 510-first opening;
610-first chamber, 611-first sub-chamber, 620-second chamber;
700-first sealing ring, 800-second sealing ring, 900-third sealing ring;
a-a first design pitch, b-a second design pitch;
20-fuel supply means, 30-oxidant supply means, 40-gas generator.
Detailed Description
Reference will now be made in detail to the present application, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar parts or parts having the same or similar functions throughout. In addition, if a detailed description of the known art is not necessary for illustrating the features of the present application, it is omitted. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present application and are not to be construed as limiting the present application.
It will be understood by those within the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. It will be understood that when an element is referred to as being "connected" or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements may also be present. Further, "connected" or "coupled" as used herein may include wirelessly connected or wirelessly coupled. As used herein, the term "and/or" includes all or any element and all combinations of one or more of the associated listed items.
The following describes the technical solutions of the present application and how to solve the above technical problems with specific embodiments.
The embodiment of the present application provides a pneumatic combination valve 10 of a rocket engine, as shown in fig. 1, including: the valve cover 500, the valve body 100, the first moving assembly 200, and the second moving assembly 300.
The bonnet 500 encloses a chamber with the valve body 100.
The chamber houses a first portion of the first moving assembly 200 and a first portion of the second moving assembly 300.
The valve body 100 includes a first valve body portion 110 and a second valve body portion 120. The first valve body portion 110 has a first passage 111, and the second portion of the first moving assembly 200 passes through the first passage 111.
The second valve body portion 120 has a second passage 121, and the second portion of the second moving assembly 300 passes through the second passage 121.
The first moving assembly 200 and the second moving assembly 300 are used for respectively stopping the first channel 111 and the second channel 121; or, the first moving assembly 200 is used to drive the second moving assembly 300 to move, so that the first channel 111 and the second channel 121 are both conducted.
Alternatively, the first and second passages 111 and 121 may be used to convey fuel and oxidant, respectively.
The inventors of the present application have found that in a liquid rocket engine, an oxidizer and a fuel are separately introduced into a combustion chamber by a pump or a high-pressure gas, and two propellant components are mixed and combusted in the combustion chamber. In a propellant supply system for a rocket engine, pneumatic valves are mounted on fuel and oxidizer supply lines, respectively, for opening and closing passages. In the rocket engine in the prior art, a pneumatic valve is needed for each of the fuel pipeline and the oxidant pipeline, a set of pneumatic actuating mechanism is needed for each pipeline, a set of air supply/exhaust pipeline is needed for each pipeline, and the whole structure occupies a large space and has a large weight.
In view of the above, the present embodiment can control the combustion of fuel and oxidant into the gas generator 40 through one pneumatic combination valve 10, thereby reducing the number of pneumatic valves. Moreover, the first moving assembly 200 can drive the second moving assembly 300 to move, mixed combustion of fuel and oxidant can be realized only by one set of control system of the pneumatic valve, the control process is simple, the occupied space and the weight of the control system of the pneumatic valve are reduced, and light weight design and structure simplification of the carrier rocket are facilitated.
In some embodiments, referring to fig. 1 and 2, the first moving assembly 200 is provided with an adjusting member 400, the adjusting member 400 is spaced from the second moving assembly 300 by a first designed distance a, and the first moving assembly 200 drives the second moving assembly 300 to move through the adjusting member 400.
According to the embodiment of the application, by adjusting the first design distance a between the adjusting member 400 and the second moving assembly 300, the time difference of the first moving assembly 200 and the second moving assembly 300 for conducting the first channel 111 and the second channel 121 can be controlled, so that the time difference of the supply of the fuel and the oxidant can be effectively controlled, the complexity and the production cost of a control system can be effectively reduced, and the mutual influence between two media with great temperature difference between the fuel and the oxidant can be avoided.
Optionally, the conditioning element 400 is cylindrical. The adjusting member 400 is screwed with the first moving assembly 200, or the adjusting member 400 is detachably connected with the first moving assembly 200, for example, a nut is used for fixing, so that the distance between the adjusting member 400 and the second moving assembly 300 can be adjusted conveniently, and the design requirement of the first design distance a is met.
In some embodiments, referring to fig. 1 and 3, the first and second valve body portions 110, 120 are spaced apart by a second design spacing b. Specifically, the second design interval b may be a minimum interval between the first and second valve body portions 110 and 120 where the first and second passages 111 and 121 are located.
The first valve body part 110 and the second valve body part 120 are separated by the second design distance b, so that the heat insulation effect can be improved, the heat transfer channel between the fuel channel and the oxidant channel is separated, the valve body can be used for two media with great temperature difference between normal-temperature fuel and low-temperature oxidant, and the temperature difference influence between the two media of the fuel and the oxidant is avoided. In practical applications, the fuel and the oxidizer may not be limited to normal temperature fuel and normal temperature oxidizer, such as kerosene and liquid oxygen, where the freezing point of kerosene (-49 degrees centigrade) is higher than the temperature of liquid oxygen (-183 degrees centigrade).
Alternatively, the first design interval a and the second design interval b may be selected according to practical applications. In practical application, the first design interval a can be selected from 2mm to 5mm, the second design interval b can be selected from 0.5mm to 1.5mm, and the value range includes endpoint values.
In some embodiments, referring to FIG. 1, the valve cover 500 is provided with a first opening 510 for receiving an external air supply device.
The chambers include a first chamber 610 housing a first portion of the first moving assembly 200 and a second chamber 620 housing a first portion of the second moving assembly 300. The first chamber 610 and the second chamber 620 communicate.
The first moving assembly 200 includes a first piston 210 slidably connected to an inner wall of the first chamber, a first valve core 220, and a first elastic member 230 fitted around the first valve core 220.
The first chamber 610 includes a first sub-chamber 611, the first sub-chamber 611 is enclosed by the first piston 210 and the valve cover 500, and the first opening 510 communicates with the first sub-chamber 611.
One end of the first valve spool 220 is fixedly connected to the first piston 210, and the other end passes through the first passage 111.
Both ends of the first elastic member 230 respectively abut against the first piston 210 and the first valve body portion 110.
Alternatively, referring to fig. 1, the first channel 111 is opened with a first communication port 1111, and the first valve element 220 moves to open and close the first communication port 1111, so that the first channel 111 is opened and closed.
Optionally, the external air source device is communicated with the first opening 510 through a pipeline, the pipeline is provided with a solenoid valve, and by controlling opening and closing of the solenoid valve, the external air source device charges and discharges air to and from the first opening 510, the air of the first opening 510 enters the first sub-chamber 611, the pressure of the first sub-chamber 611 is increased, the first moving assembly 200 is pushed to move towards the first channel 111, so that the first channel 111 is opened by the first valve element 220.
In some embodiments, referring to fig. 1, the first piston 210 comprises a first piston head 2101 and a first sleeve 2102.
The first piston head 2101 is slidably connected to the inner wall of the first chamber 610.
The first valve body portion 110 is provided with a second sleeve 112, the second sleeve 112 is sleeved in the first sleeve 2102, and the second sleeve 112 is slidably connected with the first sleeve 2102.
The first valve spool 220 passes through the second sleeve 112, and the first elastic member 230 is partially located in the second sleeve 112.
Optionally, referring to fig. 1, the first sub-chamber 611 is a chamber formed by the first piston head 2101 and the first chamber 610, and is configured to control the first piston head 2101 to move under the action of an external air source, so as to drive the first valve element 220 to move.
Optionally, the second sleeve 112 is slidably connected to the first sleeve 2102 and functions to define the moving direction of the first sleeve 2102, and the portion of the first resilient member 230 located within the second sleeve 112 also functions to define the moving direction of the first resilient member 230, thereby defining the moving direction of the first valve core 220.
Optionally, the first elastic member 230 is a spring, two ends of the first elastic member 230 may be fixedly connected to the first sleeve 2102 and the second sleeve 112, or two ends of the first elastic member 230 are respectively defined in the first sleeve 2102 and the second sleeve 112, and the first elastic member 230 is in a compressed state, so as to drive the first valve element 220 to reset and close the first communication port 1111.
Optionally, the first valve body portion 110 is provided with a first groove that surrounds the outside of the second sleeve 112 to provide room for the first sleeve 2102 to move.
Optionally, the first valve body portion 110 is further provided with a fifth sleeve, the fifth sleeve is located in the first passage 111, the first valve spool 220 passes through the fifth sleeve, and the arrangement of the fifth sleeve further defines the moving direction of the first valve spool 220.
Alternatively, as shown in fig. 1, the first valve spool 220 is threadably coupled to the first sleeve 2102.
Alternatively, referring to fig. 1, the first valve spool 220 includes a first stem portion 221 and a first head portion 222, the first stem portion 221 passes through the first passage 111, the first head portion 222 is located outside the first passage 111, and the first head portion 222 is configured to open and close the first communication port 1111 of the first passage 111, thereby enabling the first passage 111 to be communicated with and blocked from each other.
Alternatively, the width of the side of the first head portion 222 close to the first communication port 1111 is larger than that of the first communication port 1111, and the side of the first head portion 222 away from the first communication port 1111 has a spherical shape.
Optionally, referring to fig. 1, the valve body 100 further includes a first connection seat 130 fixedly connected to the first valve body portion 110, the first connection seat 130 defines a third channel 131, one end of the third channel 131 is capable of communicating with the first communication port 1111, and the other end of the third channel 131 is used for outputting fuel gas.
Optionally, the first valve body portion 110 and the first connecting seat 130 are of an integrally formed structure.
In some embodiments, referring to fig. 1, the first piston 210 further comprises a connecting portion 2103 fixedly connected to the first sleeve 2102, the connecting portion 2103 extends into the second cavity, and the adjusting member 400 is fixedly connected to the connecting portion 2103.
Optionally, the second moving assembly 300 includes a third sleeve 310, a second valve spool 320, and a second elastic member 330 fitted over the second valve spool 320.
One end of the second valve spool 320 is fixedly connected to the third sleeve 310, and the other end passes through the second passage 121.
Both ends of the second elastic member 330 respectively abut against the third sleeve 310 and the second valve body portion 120;
the central axes of the first and second valve spools 220 and 320 are parallel.
The first design spacing a is the spacing between the conditioning element 400 and the third sleeve 310.
Alternatively, referring to fig. 1, the second channel 121 is opened with a second communication port 1211, and the second valve element 320 moves to open and close the second communication port 1211, so that the second channel 121 is opened and closed.
In some embodiments, referring to FIG. 1, the second valve body 120 is provided with a fourth sleeve 122, the fourth sleeve 122 is nested within a third sleeve 310, and the fourth sleeve 122 is slidably coupled to the third sleeve 310.
The second valve spool 320 passes through the fourth sleeve 122, and the second elastic member 330 is partially disposed in the fourth sleeve 122.
Optionally, the fourth sleeve 122 is slidably connected to the third sleeve 310 to define the moving direction of the third sleeve 310, and the second elastic member 330 is partially located in the fourth sleeve 122 to also define the moving direction of the second valve spool 320 by the second elastic member 330.
Optionally, the second elastic element 330 is a spring, two ends of the second elastic element 330 may be fixedly connected to the third sleeve 310 and the fourth sleeve 122, or two ends of the second elastic element 330 may be respectively defined in the first sleeve 2102 and the second sleeve 112, and the second elastic element 330 is in a compressed state, so as to drive the second valve spool 320 to reset and close the first communication port 1111.
Optionally, the first valve body portion 110 is provided with a first groove that surrounds the outside of the second sleeve 112 to provide room for the first sleeve 2102 to move.
Optionally, the second valve body portion 120 is further provided with a sixth sleeve, the sixth sleeve is located in the second channel 121, the second valve spool 320 passes through the sixth sleeve, and the arrangement of the sixth sleeve further defines the moving direction of the second valve spool 320.
Alternatively, referring to fig. 1, the second valve spool 320 is threadedly coupled to the third sleeve 310.
Alternatively, referring to fig. 1, the second valve core 320 includes a second rod portion 321 and a second head portion 322, the second rod portion 321 passes through the second channel 121, the second head portion 322 is located outside the second channel 121, and the second head portion 322 is used for opening and closing the second communication port 1211 of the second channel 121, so as to realize the conduction and the cutoff of the first channel 111.
Alternatively, the width of the second head portion 322 on the side close to the second communication port 1211 is larger than the width of the second communication port 1211, and the side of the second head portion 322 far from the second communication port 1211 is spherical.
Optionally, referring to fig. 1, the valve body 100 further includes a second connecting seat 140 fixedly connected to the second valve body portion 120, the second connecting seat 140 is opened with a fourth channel 141, one end of the fourth channel 141 is capable of being communicated with the second communication port 1211, and the other end of the fourth channel 141 is used for outputting the oxidant.
Optionally, the second valve body portion 120 and the second connecting seat 140 are an integrally formed structure.
Alternatively, the first and second connection holders 130 and 140 are fixedly connected. The first valve body 110, the second valve body 120, the first connecting seat 130 and the second connecting seat 140 are integrally formed.
In some embodiments, a first seal ring 700 is disposed between the first sleeve 2102 and the second sleeve 112.
A second seal ring 800 is disposed between the third sleeve 310 and the fourth sleeve 122.
A third seal 900 is provided between the first piston head 2101 and the inner wall of the first chamber 610.
In some embodiments, the pressure parameter and the dynamic seal surface diameter parameter of the pneumatic combination valve 10 satisfy the design condition; the pressure parameters comprise the pressures of the first channel 111, the second channel 121 and the first sub-chamber 611, and the dynamic sealing diameter parameters comprise the diameters of dynamic sealing surfaces of the first sealing ring 700, the second sealing ring 800 and the third sealing ring 900, wherein the diameter of the dynamic sealing surface is the diameter of a sealing ring sliding surface.
Optionally, the design condition is satisfied as a condition satisfying expression one as follows:
In the first expression, P1 is the pressure when the medium flows in the first channel 111, P2 is the pressure when the fluid flows in the second channel 121, P3 is the pressure when the gas source device is filled in the first sub-chamber 611, D1 is the diameter of the contact surface between the first seal ring 700 and the first sleeve 2102, D2 is the diameter of the contact surface between the second seal ring 800 and the third sleeve 310, and D3 is the diameter of the contact surface between the third seal ring 900 and the inner wall of the first chamber 610.
Based on the technical scheme, the working principle of the pneumatic combination valve 10 applied to the embodiment of the application is as follows:
the gas from the gas source device enters the first sub-chamber 611 through the first opening 510, and the gas pushes the first piston 210 to move toward the first channel 111, so as to drive the first valve core 220 to move, and due to the existence of the first design distance a, the adjusting member 400 will contact with the third sleeve 310 after a predetermined time difference, and then push the third sleeve 310 to move, so as to drive the second valve core 320 to move. That is, after the first piston 210 drives the first valve element 220 to move so as to conduct the first passage 111, after a predetermined time difference elapses, the first piston 210 drives the third sleeve 310 to move, so that the third sleeve 310 drives the second valve element 320 to move so as to conduct the second passage 121.
When the gas from the first sub-chamber 611 is released from the first opening 510, the first piston 210 returns to the original position under the elastic force of the first elastic member 230, and drives the first valve element 220 to return to the original position, and presses the first valve body 110 upward under the elastic force of the first elastic member 230, so as to close and keep the first communication port 1111 closed, and the first passage 111 is in the closed state. Meanwhile, under the action of the elastic force of the second elastic member 330, the third sleeve 310 returns to the original position, drives the second valve core 320 to return to the original position, and presses the second valve body 120 upward under the action of the elastic force of the second elastic member 330, so as to close and keep the second communication port 1211 closed, and the second channel 121 is in a closed state.
Based on the same inventive concept, the embodiment of the application provides a rocket engine which comprises the pneumatic combination valve 10 of any embodiment of the application.
The pneumatic combination valve 10 of the embodiment of the application realizes that the first channel 111 and the second channel 121 are simultaneously controlled to be switched on and switched off by using a set of pneumatic actuating mechanism, so that the occupied space is reduced, and the weight of the rocket engine is reduced.
Based on the same inventive concept, the embodiment of the present application provides a launch vehicle, as shown in fig. 4, which includes a fuel supply 20, an oxidant supply 30, a gas generator 40, and the pneumatic combination valve 10 of any embodiment of the present application.
Of the first and second passages 111 and 121, one passage has both ends connected to the fuel supply device 20 and the gas generator 40, respectively, and the other passage has both ends connected to the oxidant supply device 30 and the gas generator 40, respectively.
Alternatively, the fuel supply device 20 and the gas generator 40 are connected to both ends of the first passage 111, respectively, for delivering fuel to the gas generator 40 through the first passage 111.
Alternatively, the oxidant supply device 30 and the gas generator 40 are connected to both ends of the second passage 121, respectively, for delivering the oxidant to the gas generator 40 through the second passage 121.
By applying the embodiment of the application, at least the following beneficial effects can be realized:
(1) the embodiment of the present application can control the fuel and the oxidant to enter the gas generator 40 for combustion through one pneumatic combination valve 10, thereby reducing the number of pneumatic valves. Moreover, the first moving assembly 200 can drive the second moving assembly 300 to move, mixed combustion of fuel and oxidant can be realized only by one set of control system of the pneumatic valve, the control process is simple, the occupied space and the weight of the control system of the pneumatic valve are reduced, and light weight design and structure simplification of the carrier rocket are facilitated.
(2) The first design distance a is designed between the adjusting member 400 and the second moving assembly 300 of the pneumatic combination valve 10 in the embodiment of the present application, and the time difference between the first moving assembly 200 and the second moving assembly 300 for communicating the first channel 111 and the second channel 121 can be controlled, so that the time difference between the supply of the fuel and the supply of the oxidant can be effectively controlled, the complexity and the production cost of the control system can be effectively reduced, and the mutual influence between two media with different temperature differences between the fuel and the oxidant can be avoided.
(3) The first valve body part 110 and the second valve body part 120 are separated by the second design distance b, so that the heat insulation effect can be improved, the heat transfer channel between the fuel channel and the oxidant channel is separated, the valve body can be used for two media with great temperature difference between normal-temperature fuel and low-temperature oxidant, and the temperature difference influence between the two media of the fuel and the oxidant is avoided.
(4) The pneumatic combination valve 10 of the embodiment of the application realizes that the first channel 111 and the second channel 121 are simultaneously controlled to be switched on and switched off by using a set of pneumatic actuating mechanism, so that the occupied space is reduced, and the weight of the rocket engine is reduced.
Those of skill in the art will appreciate that the various operations, methods, steps in the processes, acts, or solutions discussed in this application can be interchanged, modified, combined, or eliminated. Further, other steps, measures, or schemes in various operations, methods, or flows that have been discussed in this application can be alternated, altered, rearranged, broken down, combined, or deleted. Further, steps, measures, schemes in the prior art having various operations, methods, procedures disclosed in the present application may also be alternated, modified, rearranged, decomposed, combined, or deleted.
In the description of the present application, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and thus should not be construed as limiting the present application.
The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless otherwise specified.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
In the description herein, particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples.
It should be understood that, although the steps in the flowcharts of the figures are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not performed in the exact order shown and may be performed in other orders unless explicitly stated herein. Moreover, at least a portion of the steps in the flow chart of the figure may include multiple sub-steps or multiple stages, which are not necessarily performed at the same time, but may be performed at different times, which are not necessarily performed in sequence, but may be performed alternately or alternately with other steps or at least a portion of the sub-steps or stages of other steps.
The foregoing is only a partial embodiment of the present application, and it should be noted that, for those skilled in the art, several modifications and decorations can be made without departing from the principle of the present application, and these modifications and decorations should also be regarded as the protection scope of the present application.
Claims (10)
1. A pneumatic combination valve for a rocket engine, comprising: the valve comprises a valve cover, a valve body, a first moving assembly and a second moving assembly;
the valve cover and the valve body enclose to form a cavity;
the chamber housing a first portion of the first moving assembly and a first portion of the second moving assembly;
the valve body comprises a first valve body portion and a second valve body portion; the first valve body having a first passage through which a second portion of the first moving assembly passes; the second valve body portion having a second passage through which a second portion of the second moving assembly passes;
the first moving assembly and the second moving assembly are used for respectively stopping the first channel and the second channel; or, the first moving assembly is used for driving the second moving assembly to move, so that the first channel and the second channel are both communicated.
2. A rocket engine pneumatic combiner valve as recited in claim 1, wherein said pneumatic combiner valve comprises at least one of:
the first moving assembly is provided with an adjusting piece, the adjusting piece and the second moving assembly are separated by a first design space, and the first moving assembly drives the second moving assembly to move through the adjusting piece;
the first valve body portion and the second valve body portion are spaced apart by a second design spacing.
3. A rocket engine pneumatic combination valve as recited in claim 2, wherein said valve cover is provided with a first opening for receiving an external air supply means;
the chambers include a first chamber housing a first portion of the first moving assembly and a second chamber housing a first portion of the second moving assembly;
the first moving assembly comprises a first piston, a first valve core and a first elastic piece, wherein the first piston is connected with the inner wall of the first cavity in a sliding mode, and the first elastic piece is sleeved on the first valve core;
the first chamber comprises a first sub-chamber which is enclosed by the first piston and the valve cover, and the first opening is communicated with the first sub-chamber;
one end of the first valve core is fixedly connected with the first piston, and the other end of the first valve core penetrates through the first channel;
two ends of the first elastic piece are respectively abutted against the first piston and the first valve body.
4. A rocket engine pneumatic combiner valve as recited in claim 3, wherein said first piston comprises a first piston head and a first sleeve;
the first piston head is in sliding connection with the inner wall of the first chamber;
the first valve body part is provided with a second sleeve, the second sleeve is sleeved in the first sleeve, and the second sleeve is connected with the first sleeve in a sliding manner;
the first valve core penetrates through the second sleeve, and the first elastic piece is partially positioned in the second sleeve.
5. A rocket engine pneumatic combination valve as recited in claim 4, wherein said first piston further comprises a connecting portion fixedly connected to said first sleeve, said connecting portion extending into said second chamber, said adjustment member being fixedly connected to said connecting portion;
the second moving assembly comprises a third sleeve, a second valve core and a second elastic piece sleeved on the second valve core;
one end of the second valve core is fixedly connected with the third sleeve, and the other end of the second valve core penetrates through the second channel;
two ends of the second elastic piece respectively abut against the third sleeve and the second valve body part;
the central axes of the first valve core and the second valve core are parallel;
the first design spacing is a spacing between the adjustment member and the third sleeve.
6. A rocket engine pneumatic combination valve as recited in claim 5, wherein said second valve body portion is provided with a fourth sleeve, said fourth sleeve being nested within said third sleeve, said fourth sleeve being slidably connected to said third sleeve;
the second valve spool penetrates through the fourth sleeve, and the second elastic part is partially positioned in the fourth sleeve.
7. A rocket engine pneumatic combination valve as recited in claim 6, wherein a first sealing ring is disposed between said first sleeve and said second sleeve;
a second sealing ring is arranged between the third sleeve and the fourth sleeve;
and a third sealing ring is arranged between the first piston head and the inner wall of the first chamber.
8. A pneumatic combination valve of a rocket engine as recited in claim 7, wherein the pressure parameter and dynamic seal surface diameter parameter of the pneumatic combination valve satisfy design conditions; the pressure parameters comprise the pressures of the first channel, the second channel and the first sub-chamber, the dynamic sealing diameter parameters comprise the dynamic sealing surface diameters of the first sealing ring, the second sealing ring and the third sealing ring, and the dynamic sealing surface diameter is the diameter of the sliding surface of the sealing ring.
9. A rocket engine comprising a pneumatically operated combination valve as recited in any of claims 1-8.
10. A launch vehicle comprising a fuel supply, an oxidant supply, a gas generator, and a pneumatic combination valve as claimed in any one of claims 1 to 8;
and two ends of one channel of the first channel and the second channel are respectively connected with the fuel supply device and the gas generator, and two ends of the other channel of the first channel and the second channel are respectively connected with the oxidant supply device and the gas generator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110021129.0A CN112343734A (en) | 2021-01-08 | 2021-01-08 | Pneumatic combination valve of rocket engine, rocket engine and carrier rocket |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110021129.0A CN112343734A (en) | 2021-01-08 | 2021-01-08 | Pneumatic combination valve of rocket engine, rocket engine and carrier rocket |
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| CN112343734A true CN112343734A (en) | 2021-02-09 |
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| CN202110021129.0A Pending CN112343734A (en) | 2021-01-08 | 2021-01-08 | Pneumatic combination valve of rocket engine, rocket engine and carrier rocket |
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| WO2022268155A1 (en) * | 2021-06-25 | 2022-12-29 | 浙江三花汽车零部件有限公司 | Control valve |
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Application publication date: 20210209 |