CN116044617A - Nozzle and rocket engine - Google Patents

Nozzle and rocket engine Download PDF

Info

Publication number
CN116044617A
CN116044617A CN202310183308.3A CN202310183308A CN116044617A CN 116044617 A CN116044617 A CN 116044617A CN 202310183308 A CN202310183308 A CN 202310183308A CN 116044617 A CN116044617 A CN 116044617A
Authority
CN
China
Prior art keywords
control valve
rocket engine
motor
nozzle
combustion chamber
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202310183308.3A
Other languages
Chinese (zh)
Inventor
李伟
刘百奇
张胜敏
杨向明
杨乐
肖波
刘建设
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Beijing Xinghe Power Aerospace Technology Co ltd
Beijing Xinghe Power Equipment Technology Co Ltd
Anhui Galaxy Power Equipment Technology Co Ltd
Galactic Energy Shandong Aerospace Technology Co Ltd
Jiangsu Galatic Aerospace Technology Co Ltd
Original Assignee
Beijing Xinghe Power Aerospace Technology Co ltd
Beijing Xinghe Power Equipment Technology Co Ltd
Anhui Galaxy Power Equipment Technology Co Ltd
Galactic Energy Shandong Aerospace Technology Co Ltd
Jiangsu Galatic Aerospace Technology Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Beijing Xinghe Power Aerospace Technology Co ltd, Beijing Xinghe Power Equipment Technology Co Ltd, Anhui Galaxy Power Equipment Technology Co Ltd, Galactic Energy Shandong Aerospace Technology Co Ltd, Jiangsu Galatic Aerospace Technology Co Ltd filed Critical Beijing Xinghe Power Aerospace Technology Co ltd
Priority to CN202310183308.3A priority Critical patent/CN116044617A/en
Publication of CN116044617A publication Critical patent/CN116044617A/en
Pending legal-status Critical Current

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97Rocket nozzles
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97Rocket nozzles
    • F02K9/974Nozzle- linings; Ablative coatings
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16KVALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K31/00Actuating devices; Operating means; Releasing devices
    • F16K31/02Actuating devices; Operating means; Releasing devices electric; magnetic
    • F16K31/04Actuating devices; Operating means; Releasing devices electric; magnetic using a motor
    • F16K31/041Actuating devices; Operating means; Releasing devices electric; magnetic using a motor for rotating valves
    • F16K31/042Actuating devices; Operating means; Releasing devices electric; magnetic using a motor for rotating valves with electric means, e.g. for controlling the motor or a clutch between the valve and the motor
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16KVALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K31/00Actuating devices; Operating means; Releasing devices
    • F16K31/02Actuating devices; Operating means; Releasing devices electric; magnetic
    • F16K31/04Actuating devices; Operating means; Releasing devices electric; magnetic using a motor
    • F16K31/041Actuating devices; Operating means; Releasing devices electric; magnetic using a motor for rotating valves
    • F16K31/043Actuating devices; Operating means; Releasing devices electric; magnetic using a motor for rotating valves characterised by mechanical means between the motor and the valve, e.g. lost motion means reducing backlash, clutches, brakes or return means
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16KVALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K31/00Actuating devices; Operating means; Releasing devices
    • F16K31/44Mechanical actuating means
    • F16K31/53Mechanical actuating means with toothed gearing
    • F16K31/535Mechanical actuating means with toothed gearing for rotating valves
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16KVALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K5/00Plug valves; Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary
    • F16K5/04Plug valves; Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary with plugs having cylindrical surfaces; Packings therefor

Abstract

The embodiment of the application provides a spray pipe and a rocket engine. In the spray pipe that this application embodiment provided, in the boosting stage of rocket engine, the first through-hole of control valve and the first passageway intercommunication of throat lining for the air current that the combustion chamber produced is through the spray pipe blowout, is switched to the duration stage by the boosting stage at rocket engine, and actuating mechanism drives the control valve and rotates, blocks the intercommunication of first through-hole and first passageway, can prevent the air current blowout that the combustion chamber produced, thereby can change rocket engine's thrust, makes rocket engine have different thrusts in boosting stage and duration stage, and then can increase the thrust ratio of rocket engine who has this spray pipe of application.

Description

Nozzle and rocket engine
Technical Field
The application relates to the technical field of engines of aircrafts, in particular to a spray pipe and a rocket engine.
Background
The jet pipe is an important part of the existing rocket solid engine and is mainly used for accelerating expansion of air flow generated after combustion in a combustion chamber and jetting out to generate thrust.
For the existing rocket solid engine, the diameter of the throat part in the spray pipe is always constant, so that the thrust of the rocket solid engine is smaller, and the use requirement is difficult to meet.
Disclosure of Invention
Aiming at the defects of the existing mode, the application provides a spray pipe and a rocket engine, which are used for solving the technical problem that the thrust of the rocket solid engine is smaller in the prior art.
In a first aspect, embodiments of the present application provide a nozzle for installation in an outlet end of a combustion chamber in a rocket engine, the nozzle comprising:
a housing;
a throat liner disposed within the housing, the throat liner including a first passage in communication with the combustion chamber;
the control valve at least part of which penetrates through the shell and the laryngeal mask along the radial direction of the laryngeal mask; the control valve comprises a first through hole, and the first through hole is communicated with the first channel when the rocket engine is in a boosting stage;
the driving mechanism is connected with the control valve, and drives the control valve to rotate under the condition that the rocket engine is switched from the boosting stage to the cruising stage, so that the communication between the first through hole and the first channel is blocked.
Optionally, the drive mechanism comprises a motor and a timing device;
the motor is electrically connected with the timing device, and the timing device controls the motor to start to drive the control valve to rotate after working for a set period of time; the set time length is the same as the working time length of the boosting stage of the rocket engine.
Optionally, the drive mechanism comprises a motor and a sensing device;
the motor is electrically connected with the sensing device, and the sensing device is used for monitoring the pressure of the combustion chamber, and after the pressure of the combustion chamber is reduced to a set threshold value, the motor is controlled to start so as to drive the control valve to rotate.
Optionally, the driving mechanism further comprises a transmission assembly, wherein the input end of the transmission assembly is connected with the output end of the motor, and the output end of the transmission assembly is connected with the control valve.
Optionally, the transmission assembly includes a gear ring, a driving gear, a connecting frame, and at least two driven gears;
the gear ring is fixedly connected with the motor, the output end of the motor is connected with the driving gear, and the gear ring, the output end of the motor and the driving gear are coaxially arranged; the driven gear is meshed with the inner peripheral wall of the gear ring and the driving gear; the link is fixedly connected with all driven gears, and one end of the link, which is far away from the driven gears, is provided with the output end of the transmission assembly.
Optionally, the nozzle further comprises: the heat insulation layer is connected to the inner wall of the shell, and the throat liner is connected to one side, far away from the shell, of the heat insulation layer; the thickness of the heat insulation layer is larger than that of other parts along the radial direction of the throat liner.
Optionally, the nozzle further comprises: at least one seal;
the shell comprises a through hole penetrating through the control valve, and a sealing piece is arranged at one end, close to the through hole, of the control valve.
Optionally, the throat liner and the control valve are made of the same material and are made of tungsten-copper alloy or carbon-carbon composite material.
In a second aspect, embodiments of the present application provide a rocket engine, comprising: at least one of the first aspects provides any one of the nozzles.
Optionally, at least one normally open spray pipe and at least two spray pipes are arranged at the outlet end of the combustion chamber of the rocket engine, and the spray pipes are symmetrically arranged relative to the normally open spray pipe in a radial plane of the outlet end;
in the boosting stage, all normally open spray pipes and first channels of throat liners in all spray pipes are communicated with the outside; during the cruising phase, the first passages of at least two nozzles arranged symmetrically about the normally open nozzle axis are blocked by the control valve.
The beneficial technical effects that technical scheme that this application embodiment provided brought include:
in the spray pipe that this application embodiment provided, in the boosting stage of rocket engine, the first through-hole of control valve and the first passageway intercommunication of throat lining for the air current that the combustion chamber produced is through the spray pipe blowout, is switched to the duration stage by the boosting stage at rocket engine, and actuating mechanism drives the control valve and rotates, blocks the intercommunication of first through-hole and first passageway, can prevent the air current blowout that the combustion chamber produced, thereby can change rocket engine's thrust, makes rocket engine have different thrusts in boosting stage and duration stage, and then can increase the thrust ratio of rocket engine who has this spray pipe of application.
Additional aspects and advantages of the 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 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, in which:
fig. 1 is a schematic perspective view of a nozzle in an open state according to an embodiment of the present application;
FIG. 2 is a schematic perspective view of the nozzle of FIG. 1 in a closed state according to an embodiment of the present disclosure;
FIG. 3 is a front view of the nozzle of FIG. 1 provided in an embodiment of the present application;
FIG. 4 is a schematic view of an AA-direction cross-section of the nozzle of FIG. 3 according to an embodiment of the present disclosure;
FIG. 5 is a schematic cross-sectional view of the nozzle BB of FIG. 3 according to an embodiment of the present application;
FIG. 6 is a front view of the nozzle of FIG. 2 provided in an embodiment of the present application;
FIG. 7 is a schematic view of a cross-section CC of the nozzle of FIG. 6 according to an embodiment of the present application;
FIG. 8 is a schematic structural view of another nozzle according to an embodiment of the present disclosure;
FIG. 9 is a schematic diagram of a driving structure in a nozzle according to an embodiment of the present disclosure;
FIG. 10 is a schematic view of a frame of another drive structure in a nozzle according to an embodiment of the present disclosure;
fig. 11 is a schematic structural view of a driving mechanism in the nozzle shown in fig. 8 according to an embodiment of the present application.
Reference numerals illustrate:
10-a housing;
20-laryngeal mask;
30-a control valve; 31-a first through hole;
40-a driving mechanism; 41-an electric motor; 42-timing means; 43-a sensing device; 44-a transmission assembly; 441-ring gear; 442-a drive gear; 443-connecting frame; 444-driven gear;
50-a heat insulating layer;
60-seal.
Detailed Description
Embodiments of the present application are described below with reference to the drawings in the present application. It should be understood that the embodiments described below with reference to the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application, and the technical solutions of the embodiments of the present application are not limited.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless expressly stated otherwise, as understood by those skilled in the art. 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 other features, information, data, steps, operations, elements, components, and/or groups thereof, etc. that may be implemented as desired in the art. 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 be present. Further, "connected" or "coupled" as used herein may include wirelessly connected or wirelessly coupled. The term "and/or" as used herein refers to at least one of the items defined by the term, e.g., "a and/or B" may be implemented as "a", or as "B", or as "a and B".
For the purpose of making the objects, technical solutions and advantages of the present application more apparent, the embodiments of the present application will be described in further detail below with reference to the accompanying drawings.
Several terms which are referred to in this application are first introduced and explained:
thrust ratio, which is the ratio of thrust produced by a rocket engine in the boosting stage and the cruising stage, is one of the important indexes for measuring the quality of the rocket engine.
For the existing single-chamber double-thrust solid rocket engine, the diameter of the throat part in the spray pipe is always constant, and the structure of the grain is mainly changed, so that the rocket engine has different thrust in a boosting stage and a cruising stage, for example, the grain is formed by adopting the combination of propellants with different combustion speeds, however, the pressure of the combustion chamber of the single-chamber double-thrust solid rocket engine in the boosting stage is not too high, otherwise, the thrust in the cruising stage is correspondingly low, and the thrust of the single-chamber double-thrust solid rocket engine is relatively small.
The jet pipe and the rocket engine provided by the application aim to solve the technical problems in the related art.
The following describes the technical solutions of the present application and how the technical solutions of the present application solve the above technical problems in detail with specific embodiments. It should be noted that the following embodiments may be referred to, or combined with each other, and the description will not be repeated for the same terms, similar features, similar implementation steps, and the like in different embodiments.
The embodiment of the application provides a spray pipe, and a schematic structural diagram of a spray pipe product is shown in fig. 1-8, which comprises: the housing 10, the throat insert 20, the control valve 30 and the drive mechanism 40.
The nozzle provided by the embodiment of the application is used for being arranged at the outlet end of a combustion chamber in a rocket engine, optionally, the rocket is a carrier rocket, and the engine is a solid engine.
In the present embodiment, the throat insert 20 is disposed within the housing 10, the throat insert 20 including a first passageway in communication with the combustion chamber; at least part of the control valve 30 is arranged through the shell 10 and the throat liner 20 along the radial direction of the throat liner 20, the control valve 30 comprises a first through hole 31, and the first through hole 31 is communicated with the first channel when the rocket engine is in a boosting stage; the driving mechanism 40 is connected with the control valve 30, and when the rocket engine is switched from the boosting stage to the cruising stage, the driving mechanism 40 drives the control valve 30 to rotate, so that the communication between the first through hole 31 and the first channel is blocked.
In the jet pipe provided in this embodiment of the present application, in the boosting stage of the rocket engine, the first through hole 31 of the control valve 30 is communicated with the first channel of the throat liner 20, so that the air flow generated by the combustion chamber is ejected through the jet pipe, in the rocket engine from the boosting stage to the cruising stage, the driving mechanism 40 drives the control valve 30 to rotate, the communication between the first through hole 31 and the first channel is blocked, the air flow generated by the combustion chamber can be prevented from being ejected, and thus the thrust of the rocket engine can be changed, so that the rocket engine has different thrust in the boosting stage and the cruising stage, and further the thrust ratio of the rocket engine with the jet pipe can be increased.
In this embodiment, as shown in fig. 1 and fig. 2, schematic perspective views of the nozzle provided in the embodiment of the present application in an open state and a closed state are respectively shown, where in the open state of the nozzle, the first through hole 31 of the control valve 30 is in communication with the first channel of the throat liner 20; the first through hole 31 of the control valve 30 is not in communication with the first passage of the throat insert 20 when the nozzle is in the closed condition.
In this embodiment, as shown in fig. 1 and 2, the throat liner 20 is disposed in the housing 10, the throat liner 20 includes a first channel, and the outer peripheral wall of the throat liner 20 is connected to the housing 10, so that the first channel of the throat liner 20 communicates with the combustion chamber, so that the air flow generated by the combustion chamber can be ejected through the first channel. Optionally, the laryngeal mask 20 and the housing 10 are coaxially arranged, i.e. the central axis of the laryngeal mask 20 coincides with the central axis of the housing 10.
As shown in fig. 1 to 8, at least part of the control valve 30 is provided to penetrate the housing 10 and the throat insert 20 in the radial direction of the throat insert 20, and the control valve 30 includes a first through hole 31. Alternatively, as shown in fig. 1 and 2, the control valve 30 has a cylindrical shape, and one end of the control valve 30 sequentially passes through the housing 10 and the throat insert 20 and is exposed such that both ends of the control valve 30 are exposed to the housing 10.
In this embodiment, in the stage of boosting the rocket engine, the nozzle is in an open state, and the extending direction of the first through hole 31 is parallel to the axial direction of the throat liner 20, optionally, the central axis of the first through hole 31 coincides with the central axis of the throat liner 20, so that the first through hole 31 is communicated with the first channel, so that the air flow generated by the combustion chamber can be ejected through the first channel and the first through hole 31.
Under the condition that the rocket engine is switched from the boosting stage to the cruising stage, the driving mechanism 40 drives the control valve 30 to rotate, so that the extending direction of the first through hole 31 is parallel to the radial direction of the throat liner 20, alternatively, the central axis of the first through hole 31 is perpendicular to the central axis of the throat liner 20, the communication between the first through hole 31 and the first channel is blocked, the spray pipe is switched to the closed state, and the air flow generated by the combustion chamber can be prevented from being sprayed out from the first channel.
In this embodiment of the present application, by setting the control valve 30 and the driving mechanism 40, the nozzle is in an open state in the boosting stage and in a closed state in the cruising stage, so that the rocket engine with the nozzle has different thrust in the boosting stage and the cruising stage, and the thrust ratio of the rocket engine with the nozzle can be increased.
Alternatively, in the embodiment of the present application, the aperture of the first through hole 31 gradually changes along the axial direction of the first through hole 31. Alternatively, the aperture of the first through hole 31 is gradually decreased and then gradually increased in the axial direction of the first through hole 31. By controlling the variation in the aperture of the first through hole 31 in the axial direction, the ejection speed of the air flow generated by the combustion chamber can be controlled.
It should be noted that, in the embodiment of the present application, in order to facilitate the reader to intuitively understand the arrangement relationship between the control valve 30 and the housing 10 and the throat insert 20, the driving mechanism 40 is not shown in fig. 1 to 7, and the structure of the driving mechanism 40 will be described in detail hereinafter, which is not repeated here.
Optionally, in one embodiment of the present application, the control valve 30 is provided with a first limit portion, and the housing 10 is provided with a second limit portion that mates with the first limit portion. Optionally, the first limiting portion is a protruding portion, the second limiting portion is a clamping groove, and in the process that the driving mechanism 40 drives the control valve 30 to rotate, the protruding portion slides along the clamping groove, and after the first through hole 31 is blocked from being communicated with the first channel, i.e. after the spray pipe is switched to a closed state, the side wall of the clamping groove can block the protruding portion from continuously moving, so that the spray pipe is always kept in the closed state in a subsequent stage.
Alternatively, in the embodiment of the present application, the housing 10 is made of a metal material, and optionally, the manufacturing material of the housing 10 includes titanium alloy, heat-resistant alloy steel, and the like.
Alternatively, as shown in fig. 9, in one embodiment of the present application, the drive mechanism 40 includes a motor 41 and a timing device 42; the motor 41 is electrically connected with the timing device 42, and the timing device 42 controls the motor 41 to start to drive the control valve 30 to rotate after the set working time period; the set time length is the same as the working time length of the boosting stage of the rocket engine.
In this embodiment, as shown in fig. 9, the driving mechanism 40 includes a motor 41 and a timing device 42 that are electrically connected, where the motor 41 is connected to the control valve 30 and is used to drive the control valve 30 to rotate. In this embodiment, the timing device 42 starts the motor 41 after a working set time, and for a rocket of the same model, the working duration of the boosting stage is always constant, so the working set time duration of the timing device 42 is set to be the same as the working duration of the boosting stage of the rocket engine, and after the rocket is launched, when the rocket engine is switched from the end boosting stage to the cruising stage, the timing device 42 automatically starts the motor 41, so that the motor 41 drives the control valve 30 to rotate, and the nozzle is switched to the closed state.
In this embodiment of the present application, the timing device 42 is provided to control the start of the motor 41, for example, the timing device 42 controls the on-off of the motor 41 and the power supply, so that the start of the motor 41 is not required to be controlled by the control center on the ground or in space, the situation that the motor 41 is not started in time due to fluctuation in the wireless transmission process of the communication signal can be avoided, thereby improving the reliability of the driving mechanism 40 and improving the reliability of the nozzle.
Alternatively, the timing device 42 controls the motor 41 to start after a set time of operation, and turns off the motor 41 after the motor 41 drives the control valve 30 to rotate to switch the nozzle to the off state, so that the nozzle is always kept in the off state at a later stage.
Alternatively, as shown in fig. 10, in one embodiment of the present application, the drive mechanism 40 includes a motor 41 and a sensing device 43; the motor 41 is electrically connected with the sensing device 43, and the sensing device 43 is used for monitoring the pressure of the combustion chamber, and after the pressure of the combustion chamber is reduced to a set threshold value, the motor 41 is controlled to start so as to drive the control valve to rotate.
In this embodiment, as shown in fig. 10, the driving mechanism 40 includes a motor 41 and a sensing device 43 that are electrically connected, where the motor 41 is connected to the control valve 30 and is used to drive the control valve 30 to rotate.
It will be appreciated by those skilled in the art that, for a rocket engine, the pressure of the combustion chamber in the boosting phase and the cruising phase are significantly different due to the different propellants in the boosting phase and the cruising phase, and when the rocket engine is switched from the end of the boosting phase to the cruising phase, the pressure of the combustion chamber is significantly reduced, so that by setting the sensing device 43 to detect the pressure change of the combustion chamber, it is also possible to determine whether the rocket engine is in the boosting phase or in the cruising phase.
In this embodiment, the sensing device 43 is configured to monitor the pressure of the combustion chamber, and after the pressure of the combustion chamber is reduced to a set threshold, it can be determined that the rocket engine ends the boosting stage and cuts off the rocket engine towards the cruising stage, at this time, the sensing device 43 will automatically start the motor 41, so that the motor 41 drives the control valve 30 to rotate, so as to switch the nozzle to the closed state.
In this embodiment of the present application, the sensor 43 is provided to control the start of the motor 41, for example, the sensor 43 controls the on-off of the motor 41 and the power supply, so that the start of the motor 41 is not required to be controlled by the control center on the ground or in space, the situation that the motor 41 is not started in time due to fluctuation in the wireless transmission process of the communication signal can be avoided, the reliability of the driving mechanism 40 can be improved, and the reliability of the spray pipe can be improved.
Alternatively, the sensing device 43 controls the motor 41 to start after a set time of operation, and turns off the motor 41 after the motor 41 drives the control valve 30 to rotate to switch the nozzle to the off state, so that the nozzle is always kept in the off state at a later stage.
Optionally, the driving mechanism 40 in the embodiment of the present application further includes a processor, which is electrically connected to the motor 41, and is configured to control the start of the motor 41 according to the signal transmitted by the timing device 42 or the sensing device 43. The processor may be provided separately or may be integrated in the timing means 42 or the sensing means 43.
Alternatively, the processor may be a CPU (Central Processing Unit, central processor), general purpose processor, DSP (Digital Signal Processor, data Signal processor), ASIC (Application Specific Integrated Circuit ), FPGA (Field-Programmable Gate Array, field programmable Gate array) or other programmable logic device, transistor logic device, hardware component, or any combination thereof.
Alternatively, as shown in fig. 11, in one embodiment of the present application, the driving mechanism 40 further includes a transmission assembly 44, an input end of the transmission assembly 44 is connected to an output end of the motor 41, and an output end of the transmission assembly 44 is connected to the control valve 30.
In this embodiment, as shown in fig. 11, the driving mechanism 40 further includes a transmission assembly 44, an input end of the transmission assembly 44 is connected with an output end of the motor 41, and an input end of the transmission assembly 44 is a power input end of the transmission assembly 44; the output end of the transmission assembly 44 is connected with the control valve 30, and the output end of the transmission assembly 44 is the power output end of the transmission assembly 44, so that the motor 41 drives the transmission assembly 44 to rotate, and then the transmission assembly 44 drives the control valve 30 to rotate.
Alternatively, in the embodiment of the present application, the transmission assembly 44 is a reduction gear, so that the rotation speed of the motor 41 can be reduced while the output torque of the motor 41 can be increased by providing the transmission assembly 44.
Alternatively, as shown in FIG. 11, in one embodiment of the present application, the drive assembly 44 includes a gear ring 441, a drive gear 442, a coupling carrier 443, and at least two driven gears 444; the gear ring 441 is fixedly connected with the motor 41, the output end of the motor 41 is connected with the driving gear 442, and the gear ring 441, the output end of the motor 41 and the driving gear 442 are coaxially arranged; the driven gear 444 is meshed with both the inner peripheral wall of the ring gear 441 and the drive gear 442; the connection frame 443 is fixedly connected with all the driven gears 444, and an output end of the transmission assembly 44 is arranged at one end of the connection frame 443 away from the driven gears 444.
In the embodiment of the present application, as shown in fig. 11, the gear ring 441 is fixedly connected to the motor 41, and the driving gear 442 and the driven gear 444 are surrounded by the peripheral wall of the gear ring 441, so that the driving gear 442 and the driven gear 444 can rotate in the region surrounded by the peripheral wall of the gear ring 441.
As shown in fig. 11, the output end of the motor 41 is connected to the driving gear 442, so that the motor 41 can drive the driving gear 442 to rotate. The driven gear 444 is engaged with both the inner peripheral wall of the gear ring 441 and the driving gear 442, and when the driving gear 442 rotates, the driving gear 442 drives the driven gear 444 to rotate along the inner peripheral wall of the gear ring 441. All the driven gears 444 are fixedly connected with the connecting frame 443, one end of the connecting frame 443 away from the driven gears 444 is an output end of the transmission assembly 44, optionally, as shown in fig. 11, one end of the connecting frame 443 away from the driven gears 444 is provided with a cylindrical protruding portion, which is an output end of the transmission assembly 44, so that when the driven gears 444 rotate, the protruding portion of the connecting frame 443 away from one end of the driven gears 444 can be driven to rotate, and the protruding portion can drive the control valve 30 to rotate, so that the spray pipe is switched from an open state to a closed state.
In this embodiment, as shown in fig. 11, the transmission assembly 44 is a planetary gear speed reducer, which has the advantages of small volume and light weight, so that the volume and weight of the nozzle can be prevented from being excessively increased, and the payload load of the carrier rocket can be ensured. Meanwhile, the planetary gear speed reducer is high in transmission efficiency, and the spray pipe can be ensured to be switched from an open state to a closed state in time.
Optionally, as shown in fig. 1-8, in one embodiment of the present application, the nozzle further includes: a heat insulating layer 50, the heat insulating layer 50 being connected to the inner wall of the housing 10, the throat insert 20 being connected to a side of the heat insulating layer 50 remote from the housing 10; the thickness of the thermal insulation layer 50 where the throat insert 20 is connected is greater than the thickness of the other portions in the radial direction of the throat insert 20.
In this embodiment, as shown in fig. 1 to 8, the nozzle further includes a heat insulation layer 50, the heat insulation layer 50 is connected to the inner wall of the casing 10, and the throat liner 20 is connected to one side of the heat insulation layer 50 away from the casing 10, so that high-temperature air flow ablation discharged by the combustion chamber and damage to the casing 10 of the nozzle can be avoided by arranging the heat insulation layer 50.
Alternatively, in the embodiment of the present application, the heat insulating layer 50 includes a second channel, and the outer circumferential wall of the heat insulating layer 50 is connected to the inner wall of the housing 10, and the outer circumferential wall of the throat liner 20 is connected to the inner circumferential wall of the heat insulating layer 50, that is, the throat liner 20 is disposed in the second channel of the heat insulating layer 50, so that the second channel of the heat insulating layer 50 communicates with the first channel of the throat liner 20, so that the air flow discharged from the combustion chamber can be ejected through the second channel and the first channel.
Optionally, the central axis of the thermal insulation layer 50 coincides with the central axis of the laryngeal mask 20. Optionally, the central axis of the second passageway in the insulation 50 coincides with the central axis of the first passageway in the laryngeal mask 20.
Optionally, the thickness of the insulating layer 50 where the laryngeal liner 20 is attached is greater than elsewhere in the radial direction of the laryngeal liner 20. As shown in fig. 4, the thickness of the insulating layer 50 where the throat insert 20 is not connected is d1, and the thickness of the insulating layer 50 where the throat insert 20 is connected is d2, and as is apparent from fig. 4, d2 is greater than d1.
In the embodiment of the present application, since the heat insulating layer 50 has a hollow cylindrical structure and the radial thickness of the peripheral wall of the heat insulating layer 50 varies along the axial direction of the heat insulating layer 50, the boundary line where the thickness varies in the heat insulating layer 50 is shown by a solid line in the cross-sectional view shown in fig. 4.
Alternatively, in embodiments of the present application, the material of the thermal insulation layer 50 comprises a high silicon oxygen material.
Optionally, as shown in fig. 5 and 7, in an embodiment of the present application, the nozzle further includes: at least one seal 60; the housing 10 includes a through hole penetrating the control valve 30, and a sealing member 60 is provided at one end of the control valve 30 near the through hole.
In the embodiment of the present application, as shown in fig. 5 and 7, one end of the control valve 30 sequentially passes through the housing 10, the throat insert 20 and the heat insulation layer 50 and is exposed, so that both ends of the control valve 30 are exposed to the housing 10. Since the control valve 30 rotates relative to the housing 10, the throat insert 20 and the heat insulating layer 50, it is necessary to secure sealability between the control valve 30 and the housing 10, the throat insert 20 and the heat insulating layer 50, and to prevent leakage of high-temperature and high-pressure air flow generated in the combustion chamber through the connection between the control valve 30 and the housing 10, the throat insert 20 and the heat insulating layer 50, so as to secure the performance of the nozzle.
In the per se embodiment, as shown in fig. 5 and 7, the housing 10 is provided with two opposing through holes, and therefore, both ends of the control valve 30 are provided with seals 60. Optionally, the sealing element 60 is a sealing ring, the sealing element 60 is sleeved on the control valve 30, the inner peripheral wall of the sealing element 60 is in interference contact with the control valve 30, and the outer peripheral wall of the sealing element 60 is in interference contact with the heat insulation layer 50, so that the sealing performance between the control valve 30 and the heat insulation layer 50 is ensured.
It should be noted that, since the maximum thickness of the thermal insulation layer 50 is often much greater than the maximum thickness of the throat insert 20, in the present embodiment, a seal 60 is provided between the control valve 30 and the thermal insulation layer 50, thereby facilitating the manufacture of the spout. Of course, a person skilled in the art may provide a seal 60 between the control valve 30 and the laryngeal mask 20 as is practical.
Alternatively, in one embodiment of the present application, the first end of the control valve 30 is connected to the driving mechanism 40, and the second end of the control valve 30, which is far from the driving mechanism 40, is disposed in the heat insulating layer 50 and does not pass through the housing 10, so that only the seal 60 needs to be disposed between the portion of the control valve 30 near the first end and the heat insulating layer 50, and the second end of the control valve 30 does not need to be disposed with the seal.
Alternatively, in one embodiment of the present application, the throat insert 20 and the control valve 30 are the same material, both of tungsten copper or carbon composite.
In this embodiment of the present application, the throat liner 20 and the control valve 30 are made of the same material, so that the throat liner 20 and the control valve 30 have good structural matching, so that the throat liner 20 and the control valve 30 have the same physical and chemical properties, and in particular, the throat liner 20 and the control valve 30 can be ensured to have the same wear rate, and the problem of inconsistent wear degrees of the throat liner 20 and the control valve 30 can be avoided, thereby ensuring the tightness between the throat liner 20 and the control valve 30.
Alternatively, the throat insert 20 and the control valve 30 are both made of tungsten copper alloy, so that the throat insert 20 and the control valve 30 have good ablation resistance.
Optionally, the throat liner 20 and the control valve 30 are made of carbon-carbon composite materials, so that the throat liner 20 and the control valve 30 have lighter weight, thereby avoiding excessively increasing the volume and the weight of the spray pipe and ensuring the effective load of the carrier rocket.
Based on the same inventive concept, embodiments of the present application provide a rocket engine, including: at least one of any of the various embodiments described above provides a nozzle.
In this embodiment, since the rocket engine adopts any of the nozzles provided in the foregoing embodiments, the principle and technical effects thereof refer to the foregoing embodiments, and are not described herein.
Optionally, the rocket engine is a solid engine of a carrier rocket, and by adopting any one of the spray pipes provided in the foregoing embodiments, the spray pipes are controlled to be closed in a cruising stage of the solid engine, so that the solid engine has different thrust in a boosting stage and a cruising stage, and the thrust ratio of the solid engine can be increased.
Optionally, in one embodiment of the present application, the outlet end of the combustion chamber of the rocket engine is provided with at least one normally open nozzle and at least two nozzles, the nozzles being symmetrically arranged about the normally open nozzle axis in a radial plane of the outlet end; in the boosting stage, all normally open spray pipes and first channels of throat liners in all spray pipes are communicated with the outside; during the cruising phase, the first passages of at least two nozzles arranged symmetrically about the normally open nozzle axis are blocked by the control valve.
The following description will be given by taking a case that a normally open nozzle and two nozzles are provided at an outlet end of a combustion chamber of a rocket engine.
In this embodiment, the normally open nozzle is located at the center of the radial plane of the outlet end of the combustion chamber, and the two nozzles are symmetrically arranged with respect to the normally open nozzle axis. The normally open spray pipe is the existing spray pipe, and air flow generated by the combustion chamber can be sprayed out through the spray pipe in both a boosting stage and a cruising stage.
During the boost phase, the first through hole 31 of the control valve 30 in the nozzle communicates with the first passage of the throat insert 20 so that the air flow generated by the combustion chamber is ejected through the nozzle. I.e. the normally open nozzle and both nozzles are in an open state during the boost phase. The inventor finds that the pressure in the boosting stage can reach 21MPa through measurement and calculation.
In the cruising stage, the driving mechanism 40 in the two spray pipes drives the control valve 30 to rotate, and the communication between the first through hole 31 and the first channel is blocked, so that the two spray pipes are in a closed state. In the cruising stage, only the normally open spray pipe positioned at the center is in an open state. The inventor finds that the pressure intensity in the cruising stage can reach 2MPa through measurement and calculation. So that the thrust ratio of the rocket motor is greater than 10.
In the rocket engine provided by the embodiment of the application, through setting up normally open spray tube and spray tube, under the condition that does not reduce the pressure of combustion chamber by a wide margin, the thrust ratio of rocket engine can be increased to can avoid the pressure fluctuation of combustion chamber too big to lead to the condition of rocket engine damage to appear, can improve rocket engine's reliability.
By applying the embodiment of the application, at least the following beneficial effects can be realized:
in the jet pipe provided in this embodiment of the present application, in the boosting stage of the rocket engine, the first through hole 31 of the control valve 30 is communicated with the first channel of the throat liner 20, so that the air flow generated by the combustion chamber is ejected through the jet pipe, in the rocket engine from the boosting stage to the cruising stage, the driving mechanism 40 drives the control valve 30 to rotate, the communication between the first through hole 31 and the first channel is blocked, the air flow generated by the combustion chamber can be prevented from being ejected, and thus the thrust of the rocket engine can be changed, so that the rocket engine has different thrust in the boosting stage and the cruising stage, and further the thrust ratio of the rocket engine with the jet pipe can be increased.
Those of skill in the art will appreciate that the various operations, methods, steps in the flow, actions, schemes, and alternatives discussed in the present application may be alternated, altered, combined, or eliminated. Further, other steps, means, or steps in a process having various operations, methods, or procedures discussed in this application may be alternated, altered, rearranged, split, combined, or eliminated. Further, steps, measures, schemes in the prior art with various operations, methods, flows disclosed in the present application may also be alternated, altered, rearranged, decomposed, combined, or deleted.
In the description of the present application, the directions or positional relationships indicated by the words "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., are based on the exemplary directions or positional relationships shown in the drawings, are for convenience of description or simplifying the description of the embodiments of the present application, and do not indicate or imply that the apparatus or components referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present application.
The terms "first," "second," and the like, 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 defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present application, unless otherwise indicated, the meaning of "a plurality" is two or more.
In the description of the present application, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.
In the description of the present specification, a particular feature, structure, material, or characteristic may be combined in any suitable manner in one or more embodiments or examples.
The foregoing is only a part of the embodiments of the present application, and it should be noted that, for those skilled in the art, other similar implementation means based on the technical ideas of the present application are adopted without departing from the technical ideas of the solutions of the present application, and also belong to the protection scope of the embodiments of the present application.

Claims (10)

1. A nozzle for installation at an outlet end of a combustion chamber in a rocket engine, said nozzle comprising:
a housing;
a throat insert disposed within the housing, the throat insert including a first passageway in communication with the combustion chamber;
the control valve at least partially penetrates through the shell and the laryngeal lining along the radial direction of the laryngeal lining; the control valve comprises a first through hole, and the first through hole is communicated with the first channel when the rocket engine is in a boosting stage;
the driving mechanism is connected with the control valve, and drives the control valve to rotate under the condition that the rocket engine is switched from a boosting stage to a cruising stage, so that the communication between the first through hole and the first channel is blocked.
2. The spout of claim 1 wherein the drive mechanism comprises a motor and a timing device;
the motor is electrically connected with the timing device, and the timing device controls the motor to start to drive the control valve to rotate after working for a set time length; the set time length is the same as the working time length of the boosting stage of the rocket engine.
3. The spout of claim 1 wherein the drive mechanism comprises a motor and a sensing device;
the motor is electrically connected with the sensing device, the sensing device is used for monitoring the pressure of the combustion chamber, and after the pressure of the combustion chamber is reduced to a set threshold value, the motor is controlled to start so as to drive the control valve to rotate.
4. A spout according to claim 2 or 3 wherein the drive mechanism further comprises a transmission assembly, the input of which is connected to the output of the motor, the output of which is connected to the control valve.
5. The spout of claim 4 wherein the drive assembly comprises a gear ring, a drive gear, a connecting frame, and at least two driven gears;
the gear ring is fixedly connected with the motor, the output end of the motor is connected with the driving gear, and the gear ring, the output end of the motor and the driving gear are coaxially arranged; the driven gear is meshed with the inner peripheral wall of the gear ring and the driving gear; the connecting frame is fixedly connected with all the driven gears, and one end, far away from the driven gears, of the connecting frame is provided with an output end of the transmission assembly.
6. The spout of claim 1 further comprising: the heat insulation layer is connected to the inner wall of the shell, and the throat liner is connected to one side, far away from the shell, of the heat insulation layer; the thickness of the heat insulation layer at the position where the throat liner is connected is larger than that of the heat insulation layer at other positions along the radial direction of the throat liner.
7. The spout of claim 1 further comprising: at least one seal;
the shell comprises a through hole penetrating through the control valve, and one end, close to the through hole, of the control valve is provided with the sealing element.
8. The nozzle of claim 1, wherein the throat insert and the control valve are the same material and are tungsten copper alloy or carbon-carbon composite material.
9. A rocket engine, comprising: at least one nozzle according to any one of claims 1 to 8.
10. A rocket engine according to claim 9, wherein an outlet end of a combustion chamber of the rocket engine is provided with at least one normally open nozzle and at least two of said nozzles, said nozzles being symmetrically disposed about said normally open nozzle axis in a radial plane of said outlet end;
in the boosting stage, all the normally open spray pipes and all the first channels of the throat liners in the spray pipes are communicated with the outside; during a cruising phase, the first passages of at least two of the nozzles symmetrically disposed about the normally open nozzle axis are blocked by a control valve.
CN202310183308.3A 2023-03-01 2023-03-01 Nozzle and rocket engine Pending CN116044617A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310183308.3A CN116044617A (en) 2023-03-01 2023-03-01 Nozzle and rocket engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310183308.3A CN116044617A (en) 2023-03-01 2023-03-01 Nozzle and rocket engine

Publications (1)

Publication Number Publication Date
CN116044617A true CN116044617A (en) 2023-05-02

Family

ID=86129686

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310183308.3A Pending CN116044617A (en) 2023-03-01 2023-03-01 Nozzle and rocket engine

Country Status (1)

Country Link
CN (1) CN116044617A (en)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3943708A (en) * 1973-11-26 1976-03-16 The United States Of America As Represented By The Secretary Of The Navy Two area rocket nozzle
US20050120703A1 (en) * 2003-12-05 2005-06-09 Rohrbaugh Eric M. Steerable, intermittently operable rocket propulsion system
US20080315142A1 (en) * 2007-06-19 2008-12-25 Snecma Long-stroke regulator valve with a stop function
CN104454236A (en) * 2014-11-24 2015-03-25 江西洪都航空工业集团有限责任公司 Variable thrust control device for solid engine
CN104454241A (en) * 2014-11-27 2015-03-25 江西洪都航空工业集团有限责任公司 Engine jet pipe with throat diameter adjustable
CN105889548A (en) * 2016-04-26 2016-08-24 西北工业大学 High-temperature fuel gas adjusting valve used for rocket engine
CN111577484A (en) * 2020-05-26 2020-08-25 湖南宏大日晟航天动力技术有限公司 Gas flow adjusting device of rotary nozzle valve of solid rocket ramjet engine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3943708A (en) * 1973-11-26 1976-03-16 The United States Of America As Represented By The Secretary Of The Navy Two area rocket nozzle
US20050120703A1 (en) * 2003-12-05 2005-06-09 Rohrbaugh Eric M. Steerable, intermittently operable rocket propulsion system
US20080315142A1 (en) * 2007-06-19 2008-12-25 Snecma Long-stroke regulator valve with a stop function
CN104454236A (en) * 2014-11-24 2015-03-25 江西洪都航空工业集团有限责任公司 Variable thrust control device for solid engine
CN104454241A (en) * 2014-11-27 2015-03-25 江西洪都航空工业集团有限责任公司 Engine jet pipe with throat diameter adjustable
CN105889548A (en) * 2016-04-26 2016-08-24 西北工业大学 High-temperature fuel gas adjusting valve used for rocket engine
CN111577484A (en) * 2020-05-26 2020-08-25 湖南宏大日晟航天动力技术有限公司 Gas flow adjusting device of rotary nozzle valve of solid rocket ramjet engine

Similar Documents

Publication Publication Date Title
EP1982067B1 (en) Rotary heat engine
CN102943719B (en) Turbulence device for postcombustion chamber of hybrid rocket engine
CN106121864A (en) A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket
CN103967653A (en) Axial injection end combustion solid-liquid rocket engine structure
CN113464311B (en) Rotating detonation engine with adjustable detonation wave propagation mode and application method
CN106837608A (en) Fire change propulsive solid-liquid rocket structure in a kind of decking end
JP3930413B2 (en) Variable boost cycle propulsor system
CN108894893A (en) Rocket punching press combined engine Film cooling Rocket ejector motor power room
CN116044617A (en) Nozzle and rocket engine
JPH02115560A (en) Discharger for high-temperature gas discharged from combustion chamber and injector head for high-temperature gas discharger
US2720749A (en) Nozzle closure assembly
CN201376665Y (en) Ship propeller
US11795858B1 (en) Marine drives having a muffler for tertiary exhaust outlet
CN111794862B (en) Deicing device and deicing method for air inlet lip of aircraft engine
US5074750A (en) Air motor assembly
CN218221876U (en) Blending device for multielement shielding gas in magnesium alloy die casting process
RU2465482C2 (en) Low-thrust liquid-propellant engine chamber
US20050163608A1 (en) Gas turbine engine
CN212806566U (en) Furnace wall oxygen lance capable of automatically controlling pressure
JP4303338B2 (en) Emergency fluid shut-off valve
CN101475056B (en) Ship propeller
CN111894761A (en) Centripetal turbofan jet engine
CN210738693U (en) Gas flow adjusting device of solid-flushing engine
CN111749791B (en) Three-dimensional multidirectional jet cutting-jet aeroengine and application method thereof
CN219692270U (en) Automatically-controlled case of on-off gas

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination