CN115075984B - Boosting engine of carrier rocket and carrier rocket - Google Patents
Boosting engine of carrier rocket and carrier rocket Download PDFInfo
- Publication number
- CN115075984B CN115075984B CN202210707012.2A CN202210707012A CN115075984B CN 115075984 B CN115075984 B CN 115075984B CN 202210707012 A CN202210707012 A CN 202210707012A CN 115075984 B CN115075984 B CN 115075984B
- Authority
- CN
- China
- Prior art keywords
- self
- thrust
- output port
- engine
- thrust reverser
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract description 51
- 230000005284 excitation Effects 0.000 claims abstract description 39
- 239000003999 initiator Substances 0.000 claims abstract description 25
- 238000010304 firing Methods 0.000 claims abstract description 8
- 238000005520 cutting process Methods 0.000 claims description 22
- 230000035939 shock Effects 0.000 claims description 16
- 239000003380 propellant Substances 0.000 claims description 7
- 230000004888 barrier function Effects 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 4
- 238000004891 communication Methods 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 230000010354 integration Effects 0.000 abstract description 4
- 238000009434 installation Methods 0.000 abstract 1
- AJDIZQLSFPQPEY-UHFFFAOYSA-N 1,1,2-Trichlorotrifluoroethane Chemical compound FC(F)(Cl)C(F)(Cl)Cl AJDIZQLSFPQPEY-UHFFFAOYSA-N 0.000 description 18
- 239000012634 fragment Substances 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 239000007787 solid Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000001154 acute effect Effects 0.000 description 2
- 230000001419 dependent effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000005474 detonation Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000013507 mapping Methods 0.000 description 2
- 230000013011 mating Effects 0.000 description 2
- 229920002160 Celluloid Polymers 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 239000000376 reactant Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
Classifications
-
- 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
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
-
- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
-
- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
-
- 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
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/805—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control servo-mechanisms or control devices therefor
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- General Details Of Gearings (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The embodiment of the application provides a boosting engine of a carrier rocket and the carrier rocket. The boost stage engine includes: the engine body is provided with a combustion chamber, a propulsion output port, an excitation opening and a reverse thrust output port; the propulsion output port and the reverse thrust output port are respectively positioned at two opposite ends of the engine body, and the excitation opening is positioned between the propulsion output port and the reverse thrust output port; a thrust reverser, comprising: the explosion-proof device comprises an initiator, an explosion-conducting rope and a self-destruction baffle assembly; the initiator extends at least partially into the combustion chamber through the firing opening; the two ends of the detonating cord are respectively connected with the exploder and the self-destruction baffle plate assembly; the self-destroying baffle plate assembly covers the reverse thrust output port. The embodiment of the application realizes the reverse thrust time sequence control by utilizing a physical structure, has precise time control, high integration level, compact structure, easy production and easy installation of components, does not need a sensor and other program control systems, simplifies control logic and control systems, reduces manufacturing cost and running cost, improves instantaneity, strengthens coverage and improves flight reliability.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to a boosting engine of a carrier rocket and the carrier rocket.
Background
In the modern solid rocket flight process, because of the requirement of interstage separation, a boosting stage engine is generally designed with a reverse thrust device, can be controlled to be opened according to the flight time sequence, provides a backward reaction force, is beneficial to interstage separation and improves the rocket flight reliability. The traditional back thrust device is characterized in that real-time data is acquired through an acceleration sensor or a pressure sensor by depending on internal trajectory parameters in the working process of an engine, the opening time is controlled by judging that the total program is lower than a certain threshold value, and the whole system is provided with a relatively obvious short plate.
Firstly, the design of the back-push system is complex, a plurality of systems are required to coordinate and work, and the difficulty and the complexity are high.
Secondly, the time sequence control is to collect data through a sensor in the flying process, actual data has larger interference factors, and the control of the data accuracy on time point has a certain influence.
In summary, the solid rocket engine in the prior art has the technical problems of high working difficulty, high complexity, and poor accuracy and reliability of the thrust back system.
Disclosure of Invention
Aiming at the defects of the existing mode, the application provides a boosting engine of a carrier rocket and the carrier rocket, which are used for solving the technical problems of high working difficulty, high complexity, poor accuracy or poor reliability of a reverse thrust system of a solid rocket engine in the prior art.
In a first aspect, an embodiment of the present application provides a boost stage engine for a launch vehicle, including: the engine body is provided with a combustion chamber for containing propellant, and a propulsion output port, an excitation opening and a reverse thrust output port which are respectively communicated with the combustion chamber; the propulsion output port and the reverse thrust output port are respectively positioned at two opposite ends of the engine body, and the excitation opening is positioned between the propulsion output port and the reverse thrust output port;
a thrust reverser, comprising: the explosion-proof device comprises an initiator, an explosion-conducting rope and a self-destruction baffle assembly; the initiator extends at least partially through the firing opening into the combustion chamber for forming a shock wave upon combustion of the propellant in the ignitable range; the two ends of the detonating cord are respectively connected with the exploder and the self-destruction baffle plate assembly and are used for transmitting shock waves; the self-destroying baffle plate component covers the reverse pushing output port and is used for self-destroying under the excitation of shock waves.
In some embodiments of the application, the self-destructing baffle assembly includes a pressure-bearing baffle and a cutting cable positioned on a side of the pressure-bearing baffle remote from the combustion chamber and in contact with the pressure-bearing baffle.
In some embodiments of the application, the pressure-bearing barrier has a recess in a surface of the side remote from the combustion chamber, at least one end of the cutting cord is connected to the detonating cord, and a portion of the cutting cord is embedded in the recess.
In some embodiments of the application, the thrust reverser further comprises an excitation support fixedly connected to the engine block, an orthographic projection of the excitation support on the engine block at least partially surrounding the excitation aperture, and the initiator is secured to the excitation support.
In some embodiments of the application, the thrust reverser further comprises a thrust reverser support fixedly connected to the engine block, wherein a front projection of the thrust reverser support on the engine block at least partially encloses the thrust reverser output port, and the self-destructing baffle assembly is embedded in the thrust reverser support.
In some embodiments of the present application, the thrust reverser further includes a snap ring, the snap ring being located on a side of the self-destructing baffle assembly remote from the combustion chamber and being fixed to the thrust reverser support for limiting the self-destructing baffle assembly.
In some embodiments of the application, the thrust reverser further comprises a sealed electrical connector, wherein a through hole is formed on one side of the thrust reverser support towards the excitation opening, the detonating cord passes through the through hole and is connected with the self-destruction baffle assembly, and the sealed electrical connector is arranged between the thrust reverser support and the detonating cord and is used for sealing the through hole.
In some embodiments of the application, the thrust reverser further comprises a mesh cover plate and a cover plate connector, wherein the mesh cover plate is positioned on the side of the self-destructing baffle assembly away from the combustion chamber and is fixed on the thrust reverser support by the cover plate connector.
In some embodiments of the application, the thrust reverser further comprises a support pad positioned on a side of the self-destructing baffle assembly adjacent the combustion chamber
In a second aspect, an embodiment of the present application provides a launch vehicle, including: a booster stage engine of a launch vehicle as in any one of the embodiments of the first aspect.
The technical scheme provided by the embodiment of the application has the beneficial technical effects that: the explosion initiator, the detonating cord and the self-destruction baffle plate component in the back-pushing device are linked, so that the time sequence control of back-pushing is realized by utilizing a physical structure in combination with the 'parallel layer combustion rule' of the propellant in the engine, the time control is accurate, the integration level is high, the structure is compact, the components are easy to produce and install, a program control system such as a sensor is not needed, the control logic and the control system are simplified, the manufacturing cost and the running cost are reduced, the instantaneity is improved, the coverage is enhanced, and the flight reliability is improved. 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 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 diagram of a boost engine of a launch vehicle according to an embodiment of the present application;
fig. 2 is a schematic structural diagram of a thrust reverser according to an embodiment of the present application.
In the figure;
1-a thrust reverser; 2-an engine block;
101-an initiator; 102-exciting a support; 103-detonating cord; 104-sealing the electrical connector; 105-back-pushing the support; 106-a cover plate connector; 107-mesh cover plate; 108-a pressure-bearing baffle plate; 109-cutting the cable; 110-snap ring; 111-support pads; 112-a heat insulating layer; 113-propellant.
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 should be further understood that the terms "comprises" and/or "comprising," when used in this specification of the present application, specify the presence of stated features, elements, and/or components, but do not preclude the presence or addition of other features, information, data, elements, components, and/or groups thereof, all being implemented as one or more other features, information, data, elements, components, and/or groups thereof supported by the present technology. 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.
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 with reference to the accompanying drawings.
The research discovers that the design of the back-thrust system is complex, so that a plurality of systems are required to coordinate and work, and the difficulty and the complexity are high. Secondly, the time sequence control is to collect data through a sensor in the flying process, actual data has larger interference factors, and the control of the data accuracy on time point has a certain influence. In the prior art, the solid rocket engine has the technical problems of high working difficulty, high complexity, poor accuracy and reliability of a thrust reverser system.
The application provides a boosting engine of a carrier rocket and the carrier rocket, and aims to solve the technical problems in the prior art. The following describes the technical scheme of the present application and how the technical scheme of the present application solves 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.
In a first aspect, an embodiment of the present application provides a boost stage engine for a launch vehicle. As shown in fig. 1 and fig. 2, fig. 1 is a schematic structural diagram of a booster engine of a carrier rocket according to an embodiment of the present application, and fig. 2 is a schematic structural diagram of a thrust reverser 1 according to an embodiment of the present application. A boost stage engine for a launch vehicle, comprising: an engine block 2 and a thrust reverser 1.
An engine body 2 having a combustion chamber for containing a propellant 113, and a propellant output port 203, a firing opening 202 and a reverse-thrust output port 201, which are respectively communicated with the combustion chamber; the propulsion output port 203 and the reverse thrust output port 201 are respectively positioned at two opposite ends of the engine body 2, and the excitation opening 202 is positioned between the propulsion output port 203 and the reverse thrust output port 201;
the thrust reverser 1 comprises: an initiator 101, detonating cord 103 and self-destructing barrier assembly; the initiator 101 extends at least partially through the firing opening 202 into the combustion chamber for forming a shock wave upon combustion of the propellant 113 within a detonatable range; the two ends of the detonating cord 103 are respectively connected with the exploder 101 and the self-destruction baffle assembly and are used for transmitting shock waves; the self-destructing baffle assembly covers the thrust reverser outlet 201 for self-destruction under the excitation of a shock wave.
In the embodiment of the application, the engine body 2 of the carrier rocket utilizes impulse principle to change reactants (propellant 113) in a storage tank of the propellant 113 or a carrier into high-speed jet flow to flow out from the propulsion output port 203, and propulsion is generated due to Newton's third law of motion. The axis of the propulsion output 203 is parallel to or at an acute angle to the direction of travel of the launch vehicle, i.e. the direction of travel of the launch vehicle is co-directional with the direction of propulsion, or the direction of travel of the launch vehicle is co-directional with the direction of the component vector of propulsion.
The boost stage engine also comprises a reverse thrust device 1 for separating the discarded boost stage engine due to the need for interstage separation. The connection between the engine body 2 and the thrust reverser 1 at least comprises a thrust reverser outlet 201 and an excitation opening 202, and part of the high-speed jet generated by the propellant 113 flows out of the thrust reverser outlet 201 to generate thrust reverser. The thrust output port 203 and the thrust output port 201 are respectively located at opposite ends of the engine body 2. The direction of the counter thrust is opposite to the direction of the thrust or the direction of the component vector of the counter thrust is opposite to the direction of the thrust.
In this embodiment, the engine body 2 includes at least a head 301, a cylinder 302, and a head 303 connected in this order. The nozzle 303 is provided with an opening, i.e. the push-out outlet 203. One or more openings, namely a thrust reverser outlet 201, are formed on the seal head 301 or on one side of the cylinder 302, which is close to the seal head 301. The high-velocity jet exiting the thrust output 203 is in a direction that is exactly opposite to the high-velocity jet exiting the thrust output 201, or the high-velocity jet exiting the thrust output 203 is in a direction that is opposite to the component of the high-velocity jet exiting the thrust output 201.
In embodiments in which the high-velocity jet exiting the thrust output 203 is in a direction that is diametrically opposite to the high-velocity jet exiting the thrust output 201, the engine block 2 includes one or more thrust output 201, the axis of the engine block 2, and the axis of the thrust output 203 being parallel to one another.
In an embodiment in which the direction of the component of the high-velocity jet exiting the thrust output 203 is opposite to the direction of the component of the high-velocity jet exiting the thrust output 201, the engine block 2 comprises at least two thrust output 201, the axis of the engine block 2 being parallel to the axis of the thrust output 203, the axis of the thrust output 201 being at an acute angle to the axis of the thrust output 203. At least two thrust reverser output ports 201 are distributed in a central symmetry manner with the axis of the engine body 2 as a central axis, that is, at least two thrust reverser output ports 201 guide the airflow to form a first thrust reverser, a second thrust reverser, even a third thrust reverser and more thrust reversers respectively. The components of the first counter thrust and the second counter thrust in the direction parallel to the axis of the engine body 2 are superimposed on each other to form a resultant force opposite to the propulsive force. The first counter thrust and the second counter thrust are opposite in the direction of the component in the direction perpendicular to the axis of the engine body 2, and cancel each other out. In the embodiment having the third thrust and more, the same as in the above-described two-thrust embodiments, the plurality of thrust forces form a resultant force in a direction parallel to the axis of the engine body 2, and cancel each other out in a direction perpendicular to the circumferential line of the engine body 2, which is not described here again.
The initiator 101, the detonating cord 103 and the self-destruction baffle plate component in the reverse thrust device 1 are linked, and the 'parallel layer combustion rule' of the propellant 113 in the engine is combined, so that reverse thrust time sequence control is realized by utilizing a physical structure, the time control is accurate, the integration level is high, the structure is compact, the components are easy to produce and install, a sensor and other program control systems are not needed, the control logic and the control system are simplified, the manufacturing cost and the running cost are reduced, the instantaneity is improved, the coverage is enhanced, and the flight reliability is improved.
According to the combustion rule of the parallel layer, in an ideal state, in the combustion process of the propellant 113, each point of the combustion surface is retreated along the normal direction perpendicular to the surface where the point is located, and the combustion obeys the rule of retreating the parallel layer, assuming that each ignition speed on the combustion surface is the same.
The working principle of the thrust reverser 1 is as follows:
when the engine body 2 is in the working state, the self-destroying baffle plate assembly covers the reverse thrust output port 201, the propellant 113 in the combustion chamber combusts to generate high-speed jet flow which flows out from the thrust output port 203, and the carrier rocket moves by the thrust force.
When the engine body 2 enters the end stage of operation, the initiator 101 is detonated by the combustion surface of the propellant 113 to form a shock wave, the shock wave acts on one end of the detonating cord 103, the shock wave is transmitted along the extension path of the detonating cord 103, the self-destruction baffle assembly is excited by the shock wave to execute self-destruction, the reverse thrust output port 201 is opened, part of high-speed jet generated by the combustion of the propellant 113 flows out from the reverse thrust output port 201, and the boosting engine is also subjected to reverse thrust. The shock wave comprises a detonation wave.
It is worth mentioning that, since there is a certain time difference between the detonation of the initiator 101 and the self-destruction of the self-destruction flap assembly, this time difference is mainly dependent on the length of the extension path of the detonating cord 103, which is dependent on the distance between the excitation support 102 and the thrust reverser support 105. Since the thrust reverser output port 201 and the thrust reverser output port 203 are respectively located at two opposite ends of the engine body 2, the position of the thrust reverser support 105 is located at the side of the seal head 301 area or the cylinder 302 close to the seal head 301, the position change range is smaller than that of the excitation support 102, the influence of the position of the thrust reverser support 105 on the time difference is smaller than that of the excitation support, and the default thrust reverser support 105 position is unchanged in a mapping table described below.
A mapping table is established with the distance between the excitation support 102 and the propellant 113 as an independent variable and the time difference between when the initiator 101 is detonated and when the self-destruct baffle assembly performs self-destruction as an independent variable. In different types of launch vehicles, the thrust reversal opening time may be varied by varying the position of the excitation support 102.
In some embodiments of the application, the self-destructing baffle assembly includes a pressure-bearing baffle 108 and a cutting cable 109, the cutting cable 109 being located on a side of the pressure-bearing baffle 108 remote from the combustion chamber and in contact with the pressure-bearing baffle 108.
In this embodiment, one end of the cutting cable 109 is connected to the detonating cord 103, and the other end is in contact with the pressure-bearing baffle 108, and after the cutting cable 109 receives the shock wave signal transmitted by the detonating cord 103, the pressure-bearing baffle 108 is cut to break a whole piece of the pressure-bearing baffle 108 into multiple fragments.
In some embodiments of the present application, the self-destruction baffle assembly includes a pressure-bearing baffle 108 and a cutting cable 109, wherein a groove is formed on a side of the pressure-bearing baffle 108 away from the combustion chamber, and one end of the cutting cable 109 is connected to the detonating cord 103, and the other end is pre-buried in the groove.
In this embodiment, the side of the pressure-bearing shield 108 facing away from the combustion chamber has a groove, such as an annular groove, in which the cutting cord 109 is mounted, the cutting cord 109 being at least partially embedded in the groove to at least limit the position of the end of the cutting cord 109.
The cutting rope 109 is subjected to the impact wave to cut the pressure-bearing baffle plate 108, so that the pressure-bearing baffle plate 108 is broken into a plurality of fragments, a cutting track can pass through the grooves, and the thickness of the grooves of the pressure-bearing baffle plate 108 is smaller than that of the non-groove areas, so that the cutting is easier. The cutting track is more free without passing through the groove.
Alternatively, the material of the pressure barrier 108 may comprise a combustible material, and the fragments of the fragments produced after cutting may be ignited by the burning propellant 113 and depleted.
In some embodiments of the present application, the thrust reverser 1 further comprises an excitation mount 102, the excitation mount 102 being fixedly connected to the engine block 2, and an orthographic projection of the excitation mount 102 on the engine block 2 at least partially surrounding the excitation aperture 202.
In the present embodiment, excitation bracket 102 is secured to engine block 2 for carrying and securing the associated components. The front projection of excitation bracket 102 at least partially surrounds excitation aperture 202 to facilitate mating with components at excitation aperture 202.
In some embodiments of the present application, the initiator 101 is fixed to the firing support 102, and an end of the initiator 101 remote from the combustion chamber is connected to the detonating cord 103.
In this embodiment, the initiator 101 passes through the firing opening 202, with a portion of the initiator 101 located within the combustion chamber and another portion located outside the combustion chamber. The portion of the initiator 101 located outside the combustion chamber is fixed to the excitation mount 102, and the detonating cord 103 is connected to the end of the initiator 101 located outside the combustion chamber. The detonating cord 103 is at least partially wound, adhered or extended to the thrust back support 105 through the opening on the excitation support 102, and the excitation support 102 has a certain limiting function on the detonating cord 103, so that the detonating cord 103 is prevented from scattering and flying randomly.
In some embodiments of the present application, the thrust reverser 1 further comprises a thrust bearing 105, the thrust bearing 105 is fixedly connected with the engine body 2, the thrust output port is at least partially surrounded by the front projection of the thrust bearing 105 on the engine body 2, and the self-destructing baffle assembly is embedded in the thrust bearing 105.
In the present embodiment, the thrust reverser support 105 is fixed to the engine block 2 for carrying and fixing the relevant components. The forward projection of the thrust bearing 105 at least partially surrounds the thrust reverser output port 201 to facilitate mating with a component at the thrust reverser output port 201.
In this embodiment, the thrust reverser support 105 includes at least a cartridge sidewall that is used to limit the position of the self-destructing baffle assembly perpendicular to the side of the engine block 2.
Optionally, the front projection contour of the cartridge side wall on the engine body 2 is circular, and correspondingly, the front projection of the self-destruction baffle assembly on the engine body 2 is circular, the circular outer contour coincides with the circular inner contour, and the self-destruction baffle assembly is just embedded into the cartridge side wall of the thrust reverser support 105.
In another embodiment, thrust bearing 105 includes at least a plurality of planar sidewalls that are joined end-to-end.
Optionally, the front projection profile on the engine body 2 is a hollow polygon, and correspondingly, the front projection of the self-destruction baffle assembly on the engine body 2 is a solid polygon, the side lengths of the two are equal, and the self-destruction baffle assembly is abutted with a plurality of side walls in the thrust back support 105. In the two embodiments, the side wall of the back-pushing support 105 is used for limiting the self-destroying baffle assembly, so that the position of the front projection of the self-destroying baffle assembly on the engine body 2 is restrained.
In some embodiments of the present application, the thrust reverser 1 further includes a snap ring 110, where the snap ring 110 is located on a side of the self-destructing baffle assembly away from the combustion chamber and is fixed to the thrust reverser support 105 for limiting the self-destructing baffle assembly.
On the basis of the above embodiment, the thrust reverser 1 further includes a snap ring 110, the snap ring 110 is fixed on the thrust reverser support 105, and the snap ring 110 includes at least one limit structure, the limit structure is located at one side of the self-destruct baffle assembly far away from the engine body 2, and the limit structure of the snap ring 110 abuts against or is in clearance fit with the self-destruct baffle assembly, so as to prevent the self-destruct baffle assembly from falling out in the direction far away from the engine body 2 before cutting. In combination with the above constraint on the orthographic projection position of the self-destructing baffle assembly, the snap ring 110 constrains the maximum distance between the self-destructing baffle assembly and the engine body 2, and the relative position of the self-destructing baffle assembly and the engine body 2 is fixed.
In some embodiments of the present application, the thrust reverser 1 further comprises a sealed electrical connector 104, wherein a side of the thrust reverser support 105 facing the excitation opening, that is, facing the excitation support 102, is provided with a through hole, the detonating cord 103 is connected with the self-destructing barrier assembly through the through hole, and the sealed electrical connector 104 is disposed between the thrust reverser support 105 and the detonating cord 103, for sealing the through hole.
In this embodiment, the cylindrical side wall or the plurality of planar side walls of the thrust reverser support 105 are closed surfaces, and after the thrust reverser output port 201 is opened, the high-speed jet flow facing to one side of the thrust reverser output port 201 flows out from the thrust reverser output port 201, so that the high-speed jet flow is prevented from escaping from the side walls, and the magnitude of the thrust reverser is prevented from being influenced.
In order to facilitate the extension of the detonating cord 103 from the initiator 101 on the firing support 102 to the self-destructing baffle assembly located in the thrust back support 105, the sidewall of the thrust back support 105 is provided with a through hole, and the detonating cord 103 passes through two ends of the through hole to be respectively connected with the initiator 101 and the self-destructing baffle assembly.
In order to avoid affecting the efficacy of the detonating cord 103 in transmitting shock waves, the diameter of the through hole is larger than the diameter of the detonating cord 103. A sealed electric connector 104 is arranged between the detonating cord 103 and the side wall of the thrust reverser support 105, and the sealed electric connector 104 seals the through hole to prevent high-speed jet from escaping from the side wall of the thrust reverser support 105.
The sealed electrical connector 104 may cover at least one side of the through hole, either the side facing the inner space of the back-pushing holder 105 or the side facing the outside of the back-pushing holder 105, or both sides of the through hole. The central region of the sealed electrical connector 104 includes a sub-aperture whose orthographic projection onto the thrust bearing 105 is covered by the orthographic projection of the through-hole. The diameter of the sub-hole is equal to the diameter of the detonating cord 103, the detonating cord 103 passes through the sub-hole and extends from the outer side of the thrust back support 105 to the inner side of the thrust back support 105, and the sealed electric connector 104 and the detonating cord 103 jointly seal the through hole.
In some embodiments of the present application, the thrust reverser 1 further comprises a mesh cover 107 and a cover connector 106, wherein the mesh cover 107 is located on a side of the self-destructing baffle assembly remote from the combustion chamber and is fixed to the thrust reverser support 105 by the cover connector 106.
In this embodiment, the side of the thrust reverser 1, which is far away from the engine body 2, is further provided with a cover plate, the cover plate includes a plurality of criss-cross grid bars, the cover plate is divided into a plurality of grid structures by the grid bars, and the grid structures can prevent large-volume sundries from passing through the cover plate to affect the thrust reverser 1 to take effect and prevent fragments broken by the self-destruction baffle assembly from escaping to the outside under the condition of reducing the influence on the air inlet and outlet flow as much as possible. The side of the back-pushing support 105 facing the reticular cover plate 107 is provided with a threaded hole, and the reticular cover plate 107 is fixedly connected with the back-pushing support 105 through a cover plate connecting piece 106.
Optionally, the cover plate connector 106 includes at least one of a bolt, a screw, a rivet.
In some embodiments of the application, the thrust reverser 1 further comprises a support pad 111, the support pad 111 being located on the side of the self-destructing baffle assembly adjacent to the combustion chamber.
The material of the support pad 111 includes a celluloid material, and has good rigidity.
The self-destructing baffle assembly is limited by a snap ring 110 in a direction away from the engine block 2 and a support pad 111 in a direction towards the engine block 2.
The combustion chamber is internally loaded with a propellant 113 in the form of a medicine column, a heat insulating layer 112 is arranged between the combustion chamber and the thrust reverser 1, and the support pad 111 can prevent the self-destroying baffle plate assembly from moving in the direction approaching the engine body 2, and the heat insulating layer 112 and the propellant 113 are extruded to deform or damage the heat insulating layer 112 and the propellant 113.
Based on the same inventive concept, in a second aspect, an embodiment of the present application provides a carrier rocket, including: a booster stage engine of a launch vehicle as in any one of the embodiments of the first aspect.
By applying the embodiment of the application, at least the following beneficial effects can be realized: the initiator 101, the detonating cord 103 and the self-destruction baffle plate component in the reverse thrust device 1 are linked, and the 'parallel layer combustion rule' of the propellant 113 in the engine is combined, so that reverse thrust time sequence control is realized by utilizing a physical structure, the time control is accurate, the integration level is high, the structure is compact, the components are easy to produce and install, a sensor and other program control systems are not needed, the control logic and the control system are simplified, the manufacturing cost and the running cost are reduced, the instantaneity is improved, the coverage is enhanced, and the flight reliability is improved.
Compared with the traditional back-pushing device, the non-program-controlled accurate-opening back-pushing device has a relatively simple structure, and the designed system is less, so that the control logic is facilitated; compared with the traditional thrust reverser, the non-program-controlled accurate opening thrust reverser does not need sensor measurement input, does not need program control time sequence instruction, has simple control logic and is easy for closed-loop control; compared with the traditional thrust reverser, the non-program-controlled accurate opening thrust reverser has the advantages that the structure is relatively simple, a program control time sequence instruction is not needed, the technical difficulty is reduced, the reliability is high, and the cost control is facilitated; compared with the traditional back-pushing device, the input instruction is from the data of the pressure sensor or the acceleration sensor on the rocket, and the effectiveness and the instantaneity are slightly poor due to the judgment of the time sequence; the non-program-controlled accurate opening back-pushing device depends on the physical characteristics of the combustion of the parallel layers of the propellant 113, so that the timeliness is higher and the reliability is higher;
the traditional back-pushing device can be started only when the pressure intensity is obviously reduced (misjudgment is placed), but the non-program-controlled accurate-opening back-pushing device provided by the application depends on the physical characteristics of the combustion of the parallel layers of the propellant 113 as the input point of starting, can be combined with the pushing process of the combustion surface according to the overall requirements, can be provided with different starting points, and has strong coverage.
In the description of the present application, directions or positional relationships indicated by words such as "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., are based on exemplary directions or positional relationships shown in the drawings, are for convenience of description or simplification of describing embodiments of the present application, and do not indicate or imply that the devices or components referred to must have a specific orientation, be configured and operated in a specific orientation, and thus 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 above terms in the present application will be understood in specific cases by those of ordinary skill in the art.
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 idea of the present application may be adopted without departing from the technical idea of the solution of the present application, which is also within the protection scope of the embodiments of the present application.
Claims (10)
1. A boost stage engine for a launch vehicle, comprising:
an engine body having a combustion chamber for containing a propellant, and a propulsion output, an excitation opening, and a thrust reverser output each in communication with the combustion chamber; the propulsion output port and the reverse thrust output port are respectively positioned at two opposite ends of the engine body, and the excitation opening is positioned between the propulsion output port and the reverse thrust output port;
a thrust reverser, comprising: the explosion-proof device comprises an initiator, an explosion-conducting rope and a self-destruction baffle assembly; the initiator extends at least partially into the combustion chamber through the firing opening for forming a shock wave upon combustion of the propellant in a detonatable region; the two ends of the detonating cord are respectively connected with the exploder and the self-destruction baffle assembly and are used for transmitting the shock waves; the self-destroying baffle plate assembly covers the reverse pushing output port and is used for self-destroying under the excitation of the shock wave.
2. The booster stage engine of claim 1, wherein the self-destructing baffle assembly includes a pressure-bearing baffle and a cutting cable positioned on a side of the pressure-bearing baffle remote from the combustion chamber and in contact with the pressure-bearing baffle.
3. The booster stage engine of claim 2, wherein a side surface of the pressure-bearing baffle remote from the combustion chamber has a recess, at least one end of the cutting wire being connected to the detonating cord, a portion of the cutting wire being embedded in the recess.
4. The boost stage engine of claim 1, wherein said thrust reverser further comprises an excitation mount fixedly attached to said engine block, an orthographic projection of said excitation mount on said engine block at least partially surrounding said excitation aperture, said initiator being secured to said excitation mount.
5. The boost stage engine of claim 1, wherein the thrust reverser further comprises a thrust bracket fixedly attached to the engine block, wherein an orthographic projection of the thrust bracket on the engine block at least partially surrounds the thrust output port, and wherein the self-destructing baffle assembly is embedded in the thrust bracket.
6. The boost stage engine of claim 5, wherein said thrust reverser further comprises a snap ring positioned on a side of said self-destructing baffle assembly remote from said combustion chamber and secured to said thrust reverser mount for limiting said self-destructing baffle assembly.
7. The boost stage engine of claim 5, wherein the thrust reverser further comprises a sealed electrical connector, a side of the thrust reverser support facing the excitation opening has a through hole, the detonating cord passes through the through hole to connect with the self-destructing barrier assembly, and the sealed electrical connector is disposed between the thrust support and the detonating cord for sealing the through hole.
8. The boost stage engine of claim 5, wherein the thrust reverser further comprises a mesh cover plate and a cover plate connector, the mesh cover plate being positioned on a side of the self-destructing baffle assembly remote from the combustion chamber and secured to the thrust reverser mount by the cover plate connector.
9. The boost stage engine of claim 1, wherein the thrust reverser further comprises a support pad positioned on a side of the self-destructing baffle assembly adjacent the combustion chamber.
10. A launch vehicle comprising a booster stage engine of the launch vehicle according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210707012.2A CN115075984B (en) | 2022-06-21 | 2022-06-21 | Boosting engine of carrier rocket and carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210707012.2A CN115075984B (en) | 2022-06-21 | 2022-06-21 | Boosting engine of carrier rocket and carrier rocket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115075984A CN115075984A (en) | 2022-09-20 |
| CN115075984B true CN115075984B (en) | 2023-11-14 |
Family
ID=83252721
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210707012.2A Active CN115075984B (en) | 2022-06-21 | 2022-06-21 | Boosting engine of carrier rocket and carrier rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115075984B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115839287B (en) * | 2023-01-03 | 2023-05-09 | 东方空间(西安)宇航技术有限公司 | Rocket engine self-destruction device, rocket engine and rocket assembly method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20070013723A (en) * | 2005-07-27 | 2007-01-31 | 국방과학연구소 | Device of thrust cut off for rocket motor |
| CN101012786A (en) * | 2006-09-20 | 2007-08-08 | 西北工业大学 | High-frequency pulse pinking engine and control method thereof |
| RU2403428C1 (en) * | 2009-07-08 | 2010-11-10 | Открытое акционерное общество Научно-производственное объединение "Искра" | Solid propellant rocket engine |
| CN108869100A (en) * | 2018-07-03 | 2018-11-23 | 北京航空航天大学 | Separation pushes away solid-liquid rocket and rocket auxiliary braking system with counter |
| CN112325708A (en) * | 2020-11-02 | 2021-02-05 | 中国运载火箭技术研究院 | Multi-stage carrier rocket |
| CN112983679A (en) * | 2021-05-06 | 2021-06-18 | 星河动力(北京)空间科技有限公司 | Carrier rocket upper-stage propulsion system and carrier rocket |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11499505B2 (en) * | 2020-06-09 | 2022-11-15 | Raytheon Company | Multi-pulse rocket motor with flight termination destruct charge |
-
2022
- 2022-06-21 CN CN202210707012.2A patent/CN115075984B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20070013723A (en) * | 2005-07-27 | 2007-01-31 | 국방과학연구소 | Device of thrust cut off for rocket motor |
| CN101012786A (en) * | 2006-09-20 | 2007-08-08 | 西北工业大学 | High-frequency pulse pinking engine and control method thereof |
| RU2403428C1 (en) * | 2009-07-08 | 2010-11-10 | Открытое акционерное общество Научно-производственное объединение "Искра" | Solid propellant rocket engine |
| CN108869100A (en) * | 2018-07-03 | 2018-11-23 | 北京航空航天大学 | Separation pushes away solid-liquid rocket and rocket auxiliary braking system with counter |
| CN112325708A (en) * | 2020-11-02 | 2021-02-05 | 中国运载火箭技术研究院 | Multi-stage carrier rocket |
| CN112983679A (en) * | 2021-05-06 | 2021-06-18 | 星河动力(北京)空间科技有限公司 | Carrier rocket upper-stage propulsion system and carrier rocket |
Non-Patent Citations (1)
| Title |
|---|
| 新型级间分离方案设计与仿真;李慧通，赵阳，黄意新，王旭刚;固体火箭技术;第39卷(第4期);580-587 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115075984A (en) | 2022-09-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN115075984B (en) | Boosting engine of carrier rocket and carrier rocket | |
| CN107795409A (en) | A kind of solid rocket ramjet gas flow adjusting means | |
| US4807532A (en) | Base bleed unit | |
| CN109630315B (en) | Solid rocket scramjet engine, arc-shaped gas generator and central injection device | |
| CN113218251B (en) | Air flying net capturing bomb and working method thereof | |
| CN111305973B (en) | Small solid rocket engine ignition device | |
| US7510210B2 (en) | Air bag module | |
| US5481977A (en) | Work-controlled launching device with accumulator | |
| JP3092240B2 (en) | Shaped explosive warhead for reactive armor | |
| CN115182821A (en) | Ignition structure, combustion chamber structure and engine | |
| US4495763A (en) | Dual-thrust nozzle apparatus for rockets | |
| US20050279083A1 (en) | Folded detonation initiator for constant volume combustion device | |
| CN109882315B (en) | Pulse detonation engine | |
| US20140137539A1 (en) | Thrust-producing device with detonation motor | |
| CN110985240A (en) | Ignition device suitable for end fuel column and assembling method | |
| RU2708755C1 (en) | Solid-propellant gas generator | |
| CN114894042B (en) | Modularized general type collaborative microminiature missile based on boosting separation | |
| CN217686888U (en) | Whole-process control aircraft based on pulse attitude control engine | |
| CN221256957U (en) | Solid rocket engine with different annular combustion chamber and controllable tail end acceleration time | |
| CN113101576B (en) | Fire extinguishing bomb | |
| US4721042A (en) | Missiles with annular flare | |
| RU2251628C1 (en) | Solid-propellant impulse rocket engine | |
| RU2134860C1 (en) | Rocket | |
| CN114087927A (en) | Bullet without shell | |
| US20070240417A1 (en) | Actuator |
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 | ||
| CB02 | Change of applicant information |
Address after: Room 403, Floor 4, Building 2, Yard 15, Ronghua South Road, Daxing District, Beijing Economic-Technological Development Area, 100176 Applicant after: Beijing Xinghe Power Aerospace Technology Co.,Ltd. Applicant after: Beijing Xinghe Power Equipment Technology Co.,Ltd. Address before: 100176 room 1301, 13 / F, building 7, yard 15, Ronghua South Road, Beijing Economic and Technological Development Zone, Daxing District, Beijing Applicant before: Xinghe power (Beijing) Space Technology Co.,Ltd. Applicant before: Beijing Xinghe Power Equipment Technology Co.,Ltd. |
|
| CB02 | Change of applicant information | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |