CN115387934B - Solid rocket engine and throat adjusting device thereof - Google Patents
Solid rocket engine and throat adjusting device thereof Download PDFInfo
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- CN115387934B CN115387934B CN202211114963.5A CN202211114963A CN115387934B CN 115387934 B CN115387934 B CN 115387934B CN 202211114963 A CN202211114963 A CN 202211114963A CN 115387934 B CN115387934 B CN 115387934B
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- 239000007787 solid Substances 0.000 title claims abstract description 75
- 238000009413 insulation Methods 0.000 claims abstract description 43
- 230000005540 biological transmission Effects 0.000 claims abstract description 29
- 239000007921 spray Substances 0.000 claims abstract description 23
- 230000001105 regulatory effect Effects 0.000 claims description 18
- 238000007789 sealing Methods 0.000 claims description 8
- 238000009423 ventilation Methods 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 abstract description 11
- 238000013461 design Methods 0.000 abstract description 8
- 239000007789 gas Substances 0.000 description 74
- 238000002485 combustion reaction Methods 0.000 description 20
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 8
- 239000002737 fuel gas Substances 0.000 description 8
- 230000000149 penetrating effect Effects 0.000 description 5
- 238000004891 communication Methods 0.000 description 4
- 229910052757 nitrogen Inorganic materials 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 238000007726 management method Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000003870 refractory metal Substances 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N Phenol Chemical compound OC1=CC=CC=C1 ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 229910001873 dinitrogen Inorganic materials 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000009347 mechanical transmission Effects 0.000 description 1
- QJGQUHMNIGDVPM-UHFFFAOYSA-N nitrogen group Chemical group [N] QJGQUHMNIGDVPM-UHFFFAOYSA-N 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
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- 239000000377 silicon dioxide Substances 0.000 description 1
- 229920002379 silicone rubber Polymers 0.000 description 1
- 239000004945 silicone rubber Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/86—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross- section
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/10—Shape or structure of solid propellant charges
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Lift Valve (AREA)
Abstract
The application relates to the technical field of solid rocket engines, in particular to a solid rocket engine and a throat adjusting device thereof; comprising the following steps: the device comprises a convergent section heat insulation layer, a spray pipe shell, an adjusting heat insulation layer, an adjusting shell, a throat liner, an expansion section heat insulation layer, an expansion section shell, a gas storage bottle, a gas transmission pipeline, a driving valve cavity, a driving valve, a connecting body, a main valve cavity, a main valve support body and a main valve. The application can reduce the design difficulty of the throat bolt driving mechanism in a high-temperature environment under the requirements of limited space and structural quality, improve the adjusting capability of the throat bolt driving mechanism and reduce the influence on the structure and the performance of the solid rocket engine.
Description
Technical Field
The application relates to the technical field of solid rocket engines, in particular to a solid rocket engine and a throat adjusting device thereof.
Background
The solid rocket engine has the advantages of simple structure, convenient maintenance, high reliability and simple and convenient operation, and is widely applied to missile power systems. However, compared with a liquid rocket engine, the solid rocket engine has poor controllability, so that the solid rocket engine energy management technology becomes a technical problem to be solved and broken through in the industry, and is one of the important development directions of the solid rocket engine. The method has the advantages that the real-time effective control of the engine energy output in the working process of the solid rocket engine is realized, the optimal distribution of the solid rocket engine energy is realized according to the requirements, and the method has important significance for improving the energy utilization rate of the solid rocket engine, increasing the range and improving the motor capacity and the battlefield adaptability, so that the spanning type upgrading of a missile system is realized.
Currently, adjusting the throat area of a solid rocket engine through throat plugs is one way to adjust the energy output. The throat bolt is usually driven by a motor, but due to the constraint of structure and size, the main movable parts of the throat bolt are always directly positioned in the fuel gas in a combustion chamber, and the whole motor direct driving mechanism faces to the environment of high-temperature, high-pressure of more than 10 megapascals and high-speed fuel gas flow flushing close to sonic velocity. The mechanical transmission mechanism of the motor direct driving mechanism has great challenges for structural design, heat protection and dynamic sealing at high temperature, and increases design difficulty. Moreover, the layout of the throat bolt driving mechanism may often affect the loading combustion chamber of the solid rocket motor and even the whole solid rocket motor. Meanwhile, as the throat area of the solid rocket engine is increased, the pressure is increased, the direct stress of the throat bolt is also increased, the throat bolt is directly driven by a motor, the energy density required by the motor is higher, and the size and the mass of the motor are also required to be larger.
Therefore, how to reduce the design difficulty of the throat bolt driving mechanism in a high-temperature environment under the requirements of limited space and structural quality, improve the adjusting capability of the throat bolt driving mechanism and reduce the influence on the structure and the performance of the solid rocket engine is a technical problem which needs to be solved by the current technicians in the field.
Disclosure of Invention
The application provides a solid rocket engine and a throat adjusting device thereof, which adopt gas to control a driving valve to move so as to drive a main valve to axially act along the throat of the engine, thereby realizing the adjustment of the throat area of the solid rocket engine and achieving the purpose of changing the flow and the thrust of the solid rocket engine.
In order to solve the technical problems, the application provides the following technical scheme:
A solid rocket engine throat adjustment device, comprising: the device comprises a gas storage bottle, a gas transmission pipeline, a driving valve cavity, a driving valve, a connecting body, a main valve cavity, a main valve supporting body and a main valve; wherein, the solid rocket engine includes: the device comprises a convergent section heat insulation layer, a spray pipe shell, an adjusting heat insulation layer, an adjusting shell, a throat liner, an expansion section heat insulation layer and an expansion section shell; the outlet of the spray pipe shell is communicated with the inlet of the adjusting shell, and the outlet of the adjusting shell is communicated with the inlet of the expansion section shell; the convergent section heat insulation layer is attached to the inner surface of the spray pipe shell to form a spray pipe cavity, the adjusting heat insulation layer is attached to the inner surface of the adjusting shell to form an adjusting cavity, and the divergent section heat insulation layer is attached to the inner surface of the divergent section shell to form a divergent section cavity; the throat liner is positioned at the throat part of the expansion section heat insulation layer; the adjusting shell protrudes outwards so that the diameter of the adjusting cavity is larger than the diameters of the straight pipe section of the spray pipe cavity and the straight pipe section of the expanding section cavity; the tail part of the main valve is inserted into the cavity of the main valve cavity, and the head part of the main valve faces the throat liner; the main valve cavity is fixed in the adjusting cavity and is provided with a track groove which penetrates through the inside and the outside, the extending direction of the track groove is the same as the extending and retracting directions of the main valve, and one end of the connecting body penetrates through the track groove to be fixedly connected with the main valve; the head of the driving valve passes through the driving valve hole on the side wall of the adjusting shell far away from the throat lining to be fixedly connected with the other end of the connecting body in the adjusting cavity, wherein the extending direction of the driving valve hole is the same as the extending and retracting directions of the main valve; the tail part of the driving valve is inserted into a cavity of the driving valve cavity, the opening of the head part of the driving valve cavity is fixedly connected to the outer surface of the adjusting shell, the tail part of the driving valve cavity is communicated with the gas storage bottle through a gas transmission pipeline, and the tail part of the driving valve cavity is also communicated to the outside through an exhaust pipeline; the diameter of the head part of the driving valve is smaller than that of the tail part of the driving valve, and a vent hole which penetrates through a movable space and the movable space of the driving valve cavity is formed in the driving valve cavity, wherein the movable space is a space between the head part of the driving valve and the inner surface of a cavity of the driving valve cavity.
In the solid rocket engine throat adjustment device as described above, it is preferable that the direction of the combined force of the pressure applied to the head of the drive valve and the pressure applied to the main valve is directed away from the throat liner in a state where the tail of the drive valve is fitted to the tail of the drive valve chamber. The solid rocket engine throat adjustment device as described above, wherein preferably the sum of the areas of the heads of all the driving valves is not smaller than the radial cross-sectional area of the tail of the main valve.
The solid rocket engine throat adjustment device as described above, wherein the area of the tail portion of the drive valve is preferably not smaller than 2 times the area of the head portion of the drive valve.
The solid rocket engine throat adjusting device as described above, wherein preferably, the main valve cavity is provided with two track grooves, and the two track grooves are arranged oppositely; one end of one connecting body is fixedly connected with the driving valve through one track groove, and one end of the other connecting body is fixedly connected with the driving valve through the other track groove; the adjusting shell is provided with two driving valve holes, the two driving valve holes are oppositely arranged, the head part of one driving valve penetrates through one driving valve hole to be fixedly connected with the other end of one connecting body, and the head part of the other driving valve penetrates through the other driving valve hole to be fixedly connected with the other end of the other connecting body; the tail part of one driving valve is inserted into the cavity of one driving valve cavity, the tail part of the other driving valve is inserted into the cavity of the other driving valve cavity, the head openings of the two driving valve cavities are fixedly connected to the outer surface of the adjusting shell, and the tail parts of the two driving valve cavities are communicated to the gas storage bottle through the gas transmission pipeline.
The solid rocket engine throat adjusting device as described above, wherein preferably, a driving valve head sealing ring is provided between the circumferential surface of the driving valve head and the driving valve hole; a sealing ring at the tail of the driving valve is arranged between the tail of the driving valve and a cavity of the driving valve cavity.
The solid rocket engine throat adjustment device as described above, wherein preferably, further comprising: a flow regulating valve and a first servo motor; the flow regulating valve is communicated to the gas transmission pipeline and connected with the first servo motor, so that the flow regulating valve is controlled by the first servo motor, and the control of the flow of gas in the gas transmission pipeline is realized.
The solid rocket engine throat adjustment device as described above, wherein preferably, further comprising: a three-way valve and a second servo motor; the exhaust pipeline and the gas transmission pipeline are the same pipeline, the gas inlet and the gas outlet of the three-way valve are connected to the gas transmission pipeline, the gas outlet of the three-way valve is communicated to the external environment, the second servo motor is connected with the three-way valve, so that the three-way valve is controlled by the second servo motor, the gas inlet and the gas outlet of the three-way valve are communicated with the gas outlet and the gas outlet of the three-way valve, or the gas outlet and the gas outlet of the three-way valve are communicated with the gas inlet and the gas outlet of the three-way valve.
The solid rocket engine throat adjusting device is characterized in that the driving valve cavity is provided with a plurality of driving valve cavity movable space vent holes, and the driving valve cavity movable space vent holes are positioned on the same circumference of the driving valve cavity.
A solid rocket engine, comprising: the device comprises a convergent section heat insulation layer, a spray pipe shell, an adjusting heat insulation layer, an adjusting shell, a throat liner, an expansion section heat insulation layer, an expansion section shell and a solid rocket engine throat adjusting device; the outlet of the spray pipe shell is communicated with the inlet of the adjusting shell, and the outlet of the adjusting shell is communicated with the inlet of the expansion section shell; the convergent section heat insulation layer is attached to the inner surface of the spray pipe shell to form a spray pipe cavity, the adjusting heat insulation layer is attached to the inner surface of the adjusting shell to form an adjusting cavity, and the divergent section heat insulation layer is attached to the inner surface of the divergent section shell to form a divergent section cavity; the throat liner is positioned at the throat part of the expansion section heat insulation layer; the adjusting shell protrudes outwards so that the diameter of the adjusting cavity is larger than the diameters of the straight pipe section of the spray pipe cavity and the straight pipe section of the expanding section cavity; the throat adjusting device of the solid rocket engine comprises: the device comprises a gas storage bottle, a gas transmission pipeline, a driving valve cavity, a driving valve, a connecting body, a main valve cavity, a main valve supporting body and a main valve; the tail part of the main valve is inserted into the cavity of the main valve cavity, and the head part of the main valve faces the throat liner; the main valve cavity is fixed in the adjusting cavity and is provided with a track groove which penetrates through the inside and the outside, the extending direction of the track groove is the same as the extending and retracting directions of the main valve, and one end of the connecting body penetrates through the track groove to be fixedly connected with the main valve; the head of the driving valve passes through the driving valve hole on the side wall of the adjusting shell far away from the throat lining to be fixedly connected with the other end of the connecting body in the adjusting cavity, wherein the extending direction of the driving valve hole is the same as the extending and retracting directions of the main valve; the tail part of the driving valve is inserted into a cavity of the driving valve cavity, the opening of the head part of the driving valve cavity is fixedly connected to the outer surface of the adjusting shell, the tail part of the driving valve cavity is communicated with the gas storage bottle through a gas transmission pipeline, and the tail part of the driving valve cavity is also communicated to the outside through an exhaust pipeline; the diameter of the head part of the driving valve is smaller than that of the tail part of the driving valve, and a vent hole which penetrates through a movable space and the movable space of the driving valve cavity is formed in the driving valve cavity, wherein the movable space is a space between the head part of the driving valve and the inner surface of a cavity of the driving valve cavity.
The beneficial effects are that:
The main valve is driven to move by pushing the driving valve through gas, the throat area is adjusted, the thrust of the solid rocket engine is adjusted in real time, the stepless adjustment of the thrust in the interval can be realized according to the required thrust range, the energy management of the solid rocket engine can be associated with missile tasks, the maneuvering flexibility of the missile is improved, and the multi-task requirement is met.
The application adopts a mode that gas pushes the driving valve to drive the main valve, the driving valve and the main valve are directly connected into a whole, no complex rotating parts exist in the high-temperature gas environment of the combustion chamber, the design requirements on mechanical strength, connection structure, dynamic seal and the like in the thermal environment are reduced, and the design difficulty of the whole regulating mechanism is reduced.
The application adopts gas as the main driving source, and reduces the requirement on the driving mechanism compared with the gas driving source; meanwhile, compared with direct drive of a motor, the energy density requirement on the motor is reduced, and the volume and the mass of the driving mechanism are reduced.
The two ends of the driving valve adopt T-shaped structural design, so that the requirement on a driving source is further reduced, and the negative structural quality of the whole device is reduced.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings may be obtained according to these drawings for a person having ordinary skill in the art.
FIG. 1 is a cross-sectional view of a solid rocket engine provided by an embodiment of the present application;
FIG. 2 is a front view of a solid rocket engine provided by an embodiment of the present application;
FIG. 3 is a top view of a solid rocket engine provided by an embodiment of the present application;
FIG. 4 is an enlarged view of a portion of a solid rocket engine provided by an embodiment of the present application;
FIG. 5 is a front view of a portion of the components of a solid rocket engine throat adjustment device provided by an embodiment of the present application;
FIG. 6 is a right side view of a portion of the components of a solid rocket engine throat adjustment device provided by an embodiment of the present application;
fig. 7 is a front view of part of the components of a solid rocket engine throat adjustment device provided by an embodiment of the present application.
The device comprises a 1-convergence section heat insulation layer, a 2-spray pipe shell, a 3-adjustment heat insulation layer, a 4-adjustment shell, a 5-throat liner, a 6-expansion section heat insulation layer, a 7-expansion section shell, an 8-gas storage bottle, a 9-gas transmission pipeline, a 10-flow adjustment valve, a 11-first servo motor, a 12-three-way valve, a 13-second servo motor, a 14-driving valve cavity, a 15-driving valve, a 16-driving valve tail sealing ring, a 17-driving valve cavity movable space vent hole, a 18-driving valve head sealing ring, a 19-connector, a 20-main valve cavity, a 21-main valve support and a 22-main valve.
Detailed Description
Embodiments of the present application are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the application.
As shown in fig. 1 to 7, a solid rocket engine includes: convergent section heat insulation layer 1, spray pipe shell 2, adjusting heat insulation layer 3, adjusting shell 4, throat liner 5, divergent section heat insulation layer 6, divergent section shell 7 and solid rocket engine throat adjusting device; wherein, solid rocket engine throat adjusting device includes: a gas storage bottle 8, a gas transmission pipeline 9, a driving valve cavity 14, a driving valve 15, a connecting body 19, a main valve cavity 20 and a main valve 22.
The outlet of the nozzle housing 2 communicates with the inlet of the regulator housing 4, and the outlet of the regulator housing 4 communicates with the inlet of the divergent housing 7. The convergent section insulation layer 1 is attached to the inner surface of the nozzle housing 2 to form a nozzle cavity inside the convergent section insulation layer 1; the adjusting heat insulation layer 3 is attached to the inner surface of the adjusting housing 4 to form an adjusting cavity inside the adjusting heat insulation layer 3; the expansion section heat insulating layer 6 is attached to the inner surface of the expansion section housing 7 to form an expansion section cavity inside the expansion section heat insulating layer 6. The convergent section heat insulating layer 1 is connected to the adjustment heat insulating layer 3, and the adjustment heat insulating layer 3 is connected to the divergent section heat insulating layer 6, thereby insulating the solid rocket engine. In addition, the laryngeal mask 5 is positioned in the throat of the expansion section insulating layer 6 to protect the laryngeal ablation.
The main valve chamber 20 is fixed into the adjustment chamber, and the opening of the main valve chamber 20 is directed toward the laryngeal mask 5. Optionally, the solid rocket engine throat adjusting device further comprises: a plurality of main valve supports 21; the outer surface of the main valve chamber 20 is fixedly connected to one ends of a plurality of main valve supports 21 extending radially, and the other ends of the plurality of main valve supports 21 are fixedly connected to the regulating insulation layer 3 (i.e., on the inner profile of the regulating insulation layer 3) to fix the main valve chamber 20 into the regulating chamber. Alternatively, the outer surface of the main valve chamber 20 is fixedly connected with three radially extending main valve supports 21, the three main valve supports 21 being evenly distributed on the same circumference of the outer surface of the main valve chamber 20, i.e. spaced 120 ° between two adjacent main valve supports 21. Alternatively, the main valve support 21 is fixed to the adjusting insulating layer 3 near the outlet of the adjusting housing 4, so as to avoid blocking the movement of the connecting body 19 that drives the extension or retraction of the main valve 22. Alternatively, the main valve support 21 and the main valve chamber 20 are integrally formed.
The tail of the main valve 22 is inserted into the cavity of the main valve chamber 20 and the head of the main valve 22 is directed toward the throat insert 5 so that the main valve 22 can be moved in a direction toward the throat insert 5 and in a direction away from the throat insert 5 to achieve the effect of changing the throat area. Specifically, the main valve 22 reduces the throat area when extending from the interior of the chamber of the main valve chamber 20 in the direction of the throat insert 5, and increases the throat area when retracting the main valve 22 from the direction of the throat insert 5 into the chamber of the main valve chamber 20. In order to be able to adjust the throat area stepwise, the head of the main valve 22 in the present application increases in diameter gradually from a direction toward the throat insert 5 to a direction away from the throat insert 5.
In order to provide sufficient thrust, the solid rocket engine increases the velocity of the fuel gas in the combustion chamber from subsonic to sonic in the vicinity of the throat insert 5, and increases the velocity of the fuel gas from sonic to supersonic in the vicinity of the throat insert 5 to the diverging section. Accordingly, the pressure in the combustion chamber will decrease at a location closer to the throat 5, and at a location further from the throat 5, the pressure will remain at an average level in the combustion chamber, i.e. at a location further from the throat 5 in the combustion chamber, with the pressure being substantially the same. The pressure to which the tail of the main valve 22 located in the regulation chamber is subjected is the pressure in the combustion chamber, whereas the pressure to which the head of the main valve 22 directed towards the throat insert 5 is subjected is much lower than the pressure to which the tail of the main valve 22 is subjected (for example, the pressure to which the tail of the main valve 22 is subjected is 2 times the pressure to which the head of the main valve 22 is subjected), so that the main valve 22 always has a tendency to move towards the throat insert 5 under the thrust of the gas in the combustion chamber.
Then, in order to retract the main valve 22 from the direction of the throat insert 5 into the chamber of the main valve chamber 20, it is necessary not only to overcome the pressure difference generated by the gas in the combustion chamber to the tail of the main valve 22 and the head of the main valve 22, but also to provide a driving force for retracting the main valve 22 into the chamber of the main valve chamber 20, so that the total driving force provided to the main valve 22 is large, thereby increasing the demand for driving components.
In order to drive the main valve 22 to extend from the main valve chamber 20 toward the throat 5 or to drive the main valve 22 to retract from the throat 5 toward the main valve chamber 20, the main valve chamber 20 is further provided with a rail groove penetrating the inside and the outside, and the extending direction of the rail groove is the same as the extending and retracting directions of the main valve 22. One end of the connecting body 19 passes through the track groove and is fixedly connected with the main valve 22, so that the main valve 22 is driven to axially move in a designed stroke by driving the connecting body 19. Optionally, the main valve cavity 20 is provided with two track grooves penetrating the inside and the outside, and the two track grooves are arranged oppositely, so that the main valve 22 can be driven through two opposite connectors 19, and the main valve 22 can be driven more uniformly.
In order to avoid the gas from damaging the drive components of the drive connection 19, the drive components of the drive connection 19 need to be arranged outside the combustion chamber, i.e. outside the lance housing 2, the adjustment housing 4 and the expansion section housing 7. In order to make the most of the driving force of the driving member, the direction of the driving force of the driving member is made parallel to the direction of the pressure applied to the main valve 22. Since the solid rocket engine needs to ensure tightness, the size of the outlet of the nozzle housing 2 is the same as the size of the inlet of the adjusting housing 4, the size of the outlet of the adjusting housing 4 is the same as the size of the inlet of the expansion section housing 7, and therefore, the direction of the driving force of the driving component positioned outside the combustion chamber is ensured to be parallel to the direction of the pressure applied to the main valve 22, the adjusting housing 4 and the adjusting insulating layer 3 are protruded outwards, so that the size of the adjusting cavity is larger than the size of the inlet and the outlet of the adjusting housing 4, that is, the diameter of the adjusting cavity is larger than the diameter of the straight pipe section of the nozzle cavity, and the diameter of the adjusting cavity is larger than the diameter of the straight pipe section of the expansion section cavity. Also, the outward bulge of the adjustment housing 4 also results in the adjustment housing 4 having a side wall perpendicular or nearly perpendicular to the straight tube section of the nozzle chamber and having a side wall perpendicular or nearly perpendicular to the straight tube section of the diverging section chamber. Alternatively, the shape of the adjustment housing 4 is cylindrical, and then the shape of the adjustment chamber is also cylindrical.
The side wall of the adjusting shell 4 far away from the throat lining 5 is provided with a driving valve hole penetrating through the inner side and the outer side of the adjusting cavity, and the extending direction of the driving valve hole is the same as the extending and retracting direction of the main valve 22, so that the head of the driving valve 15 penetrates through the driving valve hole to extend into the adjusting cavity and is fixedly connected with the other end of the connecting body 19 in the adjusting cavity, and the direction of the driving force applied by the driving valve 15 to the connecting body 19 is ensured to be parallel to the direction of the pressure applied by the main valve 22. In addition, since the head of the driving valve 15 extends into the adjusting chamber, the head of the driving valve 15 will bear the pressure in the adjusting chamber, that is, the pressure in the combustion chamber, and since the driving valve hole is located on the side wall of the adjusting housing 4 away from the throat lining 5, the direction in which the head of the driving valve 15 bears the pressure of the fuel gas in the adjusting chamber to press the driving valve 22 is opposite to the direction in which the fuel gas in the combustion chamber presses the main valve 22 (that is, the pressure difference generated by the tail of the main valve 22 and the head of the main valve 22), so that the pressure borne by the head of the driving valve 15 fully or partially counteracts the pressure of the fuel gas borne by the main valve 22, thereby reducing the driving force provided.
Alternatively, the drive valve opening is provided in the side wall of the cylindrical adjustment housing 4 adjacent to the lance housing 2. Still alternatively, the adjusting housing 4 has two driving valve holes penetrating through the inner and outer sides of the adjusting cavity, and the two driving valve holes are disposed opposite to each other, so that the head of one driving valve 15 can pass through the head of one driving valve 15 in each driving valve hole, so that the head of the other driving valve 15 is fixedly connected with one connecting body 19 in the adjusting cavity, and the head of the other driving valve 15 is fixedly connected with the other connecting body 19 in the adjusting cavity, so that the two connecting bodies 19 can be driven more uniformly.
On the basis of the above, since the extension direction of the driving valve hole is the same as the extension and retraction directions of the main valve 22, that is, the movement direction of the driving valve 15 is the same as the movement direction of the main valve 22, the rear section of the connecting body 19 connected to the driving valve 15 is parallel to the driving valve 15 in the present application, the front section of the connecting body 19 connected to the main valve 22 is perpendicular to the main valve 22, and then the front section of the connecting body 19 and the rear section of the connecting body 19 are perpendicularly connected.
The tail part of the driving valve 15 is inserted into the cavity of the driving valve cavity 14, the opening of the head part of the driving valve cavity 14 is fixedly connected to the outer surface of the adjusting shell 4, the tail part of the driving valve cavity 14 is communicated with the gas storage bottle 8 through the gas transmission pipeline 9, so that gas in the gas storage bottle 8 can be input into the cavity of the driving valve cavity 14 through the tail part of the driving valve cavity 14 through the gas transmission pipeline 9, and further, the driving of the connecting body 19 is realized through pushing the driving valve 15. Optionally, the tail of one driving valve 15 is inserted into the cavity of one driving valve cavity 14, the tail of the other driving valve 15 is inserted into the cavity of the other driving valve cavity 14, the head openings of the two driving valve cavities 14 are fixedly connected to the outer surface of the adjusting shell 4, and the tail of the two driving valve cavities 14 are communicated with the gas storage bottle 8 through the gas transmission pipeline 9. Alternatively, the gas storage bottle 8 is a nitrogen bottle, so that the driving valve 15 is pushed by nitrogen, so that when the main valve 22 is retracted into the cavity of the main valve cavity 20, that is, when the driving valve 15 is retracted into the cavity of the driving valve cavity 14, nitrogen in the cavity of the driving valve cavity 14 can be discharged to the atmosphere, thereby avoiding the use of a gas recovery device and reducing the weight of the solid rocket engine. Since it is necessary to vent the nitrogen gas in the chamber of the drive valve chamber 14 to the atmosphere when the drive valve 15 is retracted into the chamber of the drive valve chamber 14, the tail of the drive valve chamber 14 is also communicated to the external environment through the vent line. Alternatively, the gas storage bottle 8 is an annular storage bottle, and the annular storage bottle surrounds the outside of the spout housing 2. In addition, the driving air source is nitrogen, and the heat protection and control requirements of the air source on the control component can be reduced.
In order to reduce the total gas supply pressure of the gas storage bottle 8 and to reduce the requirements for gas supply and structural strength, the drive valve 15 is of T-shaped design, i.e. the diameter of the head of the drive valve 15 is smaller than the diameter of the tail of the drive valve 15. Since the diameter of the head of the driving valve 15 is smaller than the diameter of the tail of the driving valve 15, so that a movable space is formed between the head of the driving valve 15 and the inner surface of the chamber of the driving valve cavity 14, in order to enable the driving valve 15 to move smoothly, a vent hole 17 penetrating through the movable space and the external environment is also required to be formed in the driving valve cavity 14, so that when the driving valve 15 extends out of the chamber of the driving valve cavity 14, the gas in the movable space can be discharged to the atmosphere, and when the driving valve 15 retracts into the chamber of the driving valve cavity 14, the gas can be sucked into the movable space. Alternatively, the drive valve chamber movable space vent 17 is located at a position where the drive valve chamber 14 is close to the adjustment housing 4. Optionally, a plurality of vent holes 17 for the movable space of the driving valve cavity are formed in the driving valve cavity 14. Alternatively, a plurality of the drive valve chamber movable space ventilation holes 17 are located on the same circumference of the drive valve chamber 14.
On the basis of the above, in the state that the driving valve cavity 14 is completely emptied of driving gas, the area of the head of the driving valve 15 is designed so that the resultant force of the throat adjusting device of the whole solid rocket engine is axially directed to the direction of the combustion chamber and can stably maintain the state. That is, in a state where the tail of the drive valve 15 is fitted to the tail of the chamber of the drive valve chamber 14, it is necessary to ensure that the resultant force of the pressure applied to the head of the drive valve 15 and the pressure applied to the main valve 22 is directed away from the throat 5. In this way, even in the case where the gas storage bottle 8 does not supply the driving gas, it is ensured that the main valve 22 does not move toward the throat insert 5 by the driving of the gas.
In addition, in order to satisfy the condition that the drive valve chamber 14 is completely evacuated of the drive gas, the drive valve 15 and the main valve 22 as a whole have resultant forces directed in a direction away from the throat 5, that is, in a direction toward the combustion chamber, it is required that the area of the head portions of all the drive valves 22 be not smaller than the radial cross-sectional area of the tail portions of the main valve 22. Alternatively, the sum of the areas of the heads of all the actuation valves 15 is made equal to the radial cross-sectional area of the tail of the main valve 22.
In order to further reduce the requirement for the driving air source, the area of the tail part of the driving valve 15 can be not smaller than 2 times of the area of the head part of the driving valve 15, so that the requirement for the air source pressure can be reduced. Even more, the air source pressure can be reduced to be not lower than half of the combustion chamber pressure (the combustion chamber pressure of most solid rocket engines is generally not higher than 20 MPa), which greatly reduces the air source requirement and the requirement on a control valve, thereby reducing the quality of a throat adjusting device of the solid rocket engine.
In order to ensure a tight fit of the head of the drive valve 15 with the drive valve bore, a drive valve head sealing ring 18 is provided between the circumferential surface of the head of the drive valve 15 and the drive valve bore. In order to ensure a tight fit of the tail of the drive valve 15 with the chamber of the drive valve chamber 14, a drive valve tail sealing ring 16 is arranged between the circumferential surface of the tail of the drive valve 15 and the chamber of the drive valve chamber 14. Alternatively, the drive valve head seal 18 and the drive valve tail seal 17 are both O-ring seals. Still alternatively, the O-ring seal is a silicone rubber O-ring seal.
In order to reduce heat conduction and ensure good connection, the driving valve 15 is made of a nonmetallic heat insulating material such as high silica/phenol, the connecting body 19 is made of a refractory metal material such as tungsten-impregnated copper, and the connecting body 19 and the driving valve 15 are connected by adhesion, screw connection, or the like. In addition, all structures of the driving valve 15, the main valve cavity 20, the main valve supporting body 21, the main valve 22 and the like which are directly positioned in the fuel gas adopt tungsten-copper-infiltrated refractory metal materials.
In order to control the gas in the gas transmission pipeline 9, the solid rocket engine throat adjusting device of the application further comprises: a flow rate regulating valve 10; the flow regulating valve 10 is communicated to the gas transmission pipeline 9, so that the flow of gas in the gas transmission pipeline 9 is controlled by controlling the flow regulating valve 10, and the flow and the thrust of the solid rocket engine are regulated. On this basis, solid rocket engine throat adjusting device still includes: a first servo motor 11; the flow regulating valve 10 is connected with a first servo motor 11 to control the flow regulating valve 10 through the first servo motor 11, thereby realizing the control of the flow of the gas in the gas transmission pipeline 9.
In addition, since the gas input into the chamber of the driving valve cavity 14 and the gas output from the chamber of the driving valve cavity 14 are not performed simultaneously, the exhaust pipeline for communicating the driving valve cavity 14 with the external environment may be the same pipeline as the gas pipeline 9, and then the solid rocket engine throat adjusting device of the present application further comprises: a three-way valve 12; the air inlet and the air outlet of the three-way valve 12 are connected to the air delivery pipeline 9, and the air outlet of the three-way valve 12 is communicated to the external environment, so that when the air in the air storage bottle 8 is input into the cavity of the driving valve cavity 14 through the air delivery pipeline 9, the air inlet and the air outlet of the three-way valve 12 are communicated, and when the air in the cavity of the driving valve cavity 14 is discharged through the air delivery pipeline 9, the air outlet of the three-way valve 12 is communicated with the air outlet. On this basis, solid rocket engine throat adjusting device still includes: a servo motor No. 13; the three-way valve 12 is connected with the second servo motor 13 to control the three-way valve 12 through the second servo motor 13, so that the communication between the air inlet and the air outlet of the three-way valve 12 is switched to the communication between the air outlet and the air outlet of the three-way valve 12, or the communication between the air outlet and the air outlet of the three-way valve 12 is switched to the communication between the air inlet and the air outlet of the three-way valve 12.
When the first servo motor 11 receives the signal, the flow regulating valve 10 is opened, and the gas in the gas storage bottle 8 is output. The second servo motor 13 is started, the three-way valve 12 rotates forward, and the air inlet and the air outlet of the three-way valve are communicated, so that the air transmission pipeline 9 and the cavity of the driving valve cavity 14 are communicated. When the target pressure is reached in the cavity of the driving valve cavity 14, the driving valve 15 is driven to move along with the pressure rise, the main valve 22 is pushed to move in the cavity of the main valve cavity 20 along the axial direction towards the direction close to the throat liner 5 by the connecting rod 19, the throat area is gradually reduced, the pressure rise, the flow increase and the thrust increase in the combustion chamber of the solid rocket engine are realized.
When the first servo motor 11 receives the signal, the flow regulating valve 10 is closed, and the gas in the gas storage bottle 8 stops being output. The second servo motor 13 is started, the three-way valve 12 rotates reversely, and the air outlet of the three-way valve is communicated with the air outlet, so that the cavity driving the valve cavity 14 is communicated with the external environment. The gas in the cavity of the driving valve cavity 14 is discharged to the external environment, along with the pressure reduction, the cavity of the driving valve cavity 14 is emptied to the ambient pressure, the driving valve 15 is driven to move, the main valve 22 is driven to move in the main valve cavity 20 along the axial direction far away from the throat liner 5 through the connecting rod 19, the throat area is gradually increased, the pressure in the combustion chamber of the solid rocket engine is reduced, the flow is reduced, and the thrust is reduced.
It will be evident to those skilled in the art that the application is not limited to the details of the foregoing illustrative embodiments, and that the present application may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the application being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.
Claims (10)
1. A solid rocket engine throat adjustment device, comprising: the device comprises a gas storage bottle, a gas transmission pipeline, a driving valve cavity, a driving valve, a connecting body, a main valve cavity, a main valve supporting body and a main valve;
Wherein, the solid rocket engine includes: the device comprises a convergent section heat insulation layer, a spray pipe shell, an adjusting heat insulation layer, an adjusting shell, a throat liner, an expansion section heat insulation layer and an expansion section shell; the outlet of the spray pipe shell is communicated with the inlet of the adjusting shell, and the outlet of the adjusting shell is communicated with the inlet of the expansion section shell; the convergent section heat insulation layer is attached to the inner surface of the spray pipe shell to form a spray pipe cavity, the adjusting heat insulation layer is attached to the inner surface of the adjusting shell to form an adjusting cavity, and the divergent section heat insulation layer is attached to the inner surface of the divergent section shell to form a divergent section cavity; the throat liner is positioned at the throat part of the expansion section heat insulation layer; the adjusting shell protrudes outwards so that the diameter of the adjusting cavity is larger than the diameters of the straight pipe section of the spray pipe cavity and the straight pipe section of the expanding section cavity;
The tail part of the main valve is inserted into the cavity of the main valve cavity, and the head part of the main valve faces the throat liner;
The main valve cavity is fixed in the adjusting cavity and is provided with a track groove which penetrates through the inside and the outside, the extending direction of the track groove is the same as the extending and retracting directions of the main valve, and one end of the connecting body penetrates through the track groove to be fixedly connected with the main valve;
the head of the driving valve passes through the driving valve hole on the side wall of the adjusting shell far away from the throat lining to be fixedly connected with the other end of the connecting body in the adjusting cavity, wherein the extending direction of the driving valve hole is the same as the extending and retracting directions of the main valve;
The tail part of the driving valve is inserted into a cavity of the driving valve cavity, the opening of the head part of the driving valve cavity is fixedly connected to the outer surface of the adjusting shell, the tail part of the driving valve cavity is communicated with the gas storage bottle through a gas transmission pipeline, and the tail part of the driving valve cavity is also communicated to the outside through an exhaust pipeline;
the diameter of the head part of the driving valve is smaller than that of the tail part of the driving valve, and a vent hole which penetrates through a movable space and the movable space of the driving valve cavity is formed in the driving valve cavity, wherein the movable space is a space between the head part of the driving valve and the inner surface of a cavity of the driving valve cavity.
2. A solid rocket engine throat adjustment device according to claim 1, further comprising: in the state that the tail of the driving valve is attached to the tail of the driving valve cavity, the direction of the combined force of the pressure born by the head of the driving valve and the pressure born by the main valve is directed away from the laryngeal lining.
3. A solid rocket engine throat adjustment device according to claim 2, wherein the sum of the areas of the heads of all the driving valves is not smaller than the radial cross-sectional area of the tail of the main valve.
4. A solid rocket engine throat adjustment device according to claim 2 or 3, wherein the area of the tail of the drive valve is not less than 2 times the area of the head of the drive valve.
5. A solid rocket engine throat adjustment device according to any one of claims 1 to 3 wherein the main valve chamber has two orbital slots thereon, and the two orbital slots are disposed opposite each other;
One end of one connecting body is fixedly connected with the driving valve through one track groove, and one end of the other connecting body is fixedly connected with the driving valve through the other track groove;
The adjusting shell is provided with two driving valve holes, the two driving valve holes are oppositely arranged, the head part of one driving valve penetrates through one driving valve hole to be fixedly connected with the other end of one connecting body, and the head part of the other driving valve penetrates through the other driving valve hole to be fixedly connected with the other end of the other connecting body;
The tail part of one driving valve is inserted into the cavity of one driving valve cavity, the tail part of the other driving valve is inserted into the cavity of the other driving valve cavity, the head openings of the two driving valve cavities are fixedly connected to the outer surface of the adjusting shell, and the tail parts of the two driving valve cavities are communicated to the gas storage bottle through the gas transmission pipeline.
6. A solid rocket engine throat adjustment device according to any one of claims 1 to 3 wherein a drive valve head seal is provided between the circumferential surface of the drive valve head and the drive valve bore; a sealing ring at the tail of the driving valve is arranged between the tail of the driving valve and a cavity of the driving valve cavity.
7. A solid rocket engine throat adjustment device according to any one of claims 1-3, further comprising: a flow regulating valve and a first servo motor; the flow regulating valve is communicated to the gas transmission pipeline and connected with the first servo motor, so that the flow regulating valve is controlled by the first servo motor, and the control of the flow of gas in the gas transmission pipeline is realized.
8. A solid rocket engine throat adjustment device according to claim 7, further comprising: a three-way valve and a second servo motor;
The exhaust pipeline and the gas transmission pipeline are the same pipeline, the gas inlet and the gas outlet of the three-way valve are connected to the gas transmission pipeline, the gas outlet of the three-way valve is communicated to the external environment, the second servo motor is connected with the three-way valve, so that the three-way valve is controlled by the second servo motor, the gas inlet and the gas outlet of the three-way valve are communicated with the gas outlet and the gas outlet of the three-way valve, or the gas outlet and the gas outlet of the three-way valve are communicated with the gas inlet and the gas outlet of the three-way valve.
9. A solid rocket engine throat adjustment device according to any one of claims 1-3, wherein the drive valve chamber is provided with a plurality of drive valve chamber movable space ventilation holes, and the plurality of drive valve chamber movable space ventilation holes are located on the same circumference of the drive valve chamber.
10. A solid rocket engine, comprising: the device comprises a convergent section heat insulation layer, a spray pipe shell, an adjusting heat insulation layer, an adjusting shell, a throat liner, an expansion section heat insulation layer, an expansion section shell and a solid rocket engine throat adjusting device;
The outlet of the spray pipe shell is communicated with the inlet of the adjusting shell, and the outlet of the adjusting shell is communicated with the inlet of the expansion section shell; the convergent section heat insulation layer is attached to the inner surface of the spray pipe shell to form a spray pipe cavity, the adjusting heat insulation layer is attached to the inner surface of the adjusting shell to form an adjusting cavity, and the divergent section heat insulation layer is attached to the inner surface of the divergent section shell to form a divergent section cavity; the throat liner is positioned at the throat part of the expansion section heat insulation layer; the adjusting shell protrudes outwards so that the diameter of the adjusting cavity is larger than the diameters of the straight pipe section of the spray pipe cavity and the straight pipe section of the expanding section cavity;
the throat adjusting device of the solid rocket engine comprises: the device comprises a gas storage bottle, a gas transmission pipeline, a driving valve cavity, a driving valve, a connecting body, a main valve cavity, a main valve supporting body and a main valve;
The tail part of the main valve is inserted into the cavity of the main valve cavity, and the head part of the main valve faces the throat liner;
The main valve cavity is fixed in the adjusting cavity and is provided with a track groove which penetrates through the inside and the outside, the extending direction of the track groove is the same as the extending and retracting directions of the main valve, and one end of the connecting body penetrates through the track groove to be fixedly connected with the main valve;
the head of the driving valve passes through the driving valve hole on the side wall of the adjusting shell far away from the throat lining to be fixedly connected with the other end of the connecting body in the adjusting cavity, wherein the extending direction of the driving valve hole is the same as the extending and retracting directions of the main valve;
The tail part of the driving valve is inserted into a cavity of the driving valve cavity, the opening of the head part of the driving valve cavity is fixedly connected to the outer surface of the adjusting shell, the tail part of the driving valve cavity is communicated with the gas storage bottle through a gas transmission pipeline, and the tail part of the driving valve cavity is also communicated to the outside through an exhaust pipeline;
the diameter of the head part of the driving valve is smaller than that of the tail part of the driving valve, and a vent hole which penetrates through a movable space and the movable space of the driving valve cavity is formed in the driving valve cavity, wherein the movable space is a space between the head part of the driving valve and the inner surface of a cavity of the driving valve cavity.
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| CN202211114963.5A CN115387934B (en) | 2022-09-14 | 2022-09-14 | Solid rocket engine and throat adjusting device thereof |
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