CN115045777B - Variable thrust solid-liquid rocket engine based on combined explosive columns - Google Patents
Variable thrust solid-liquid rocket engine based on combined explosive columns Download PDFInfo
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- CN115045777B CN115045777B CN202210666260.7A CN202210666260A CN115045777B CN 115045777 B CN115045777 B CN 115045777B CN 202210666260 A CN202210666260 A CN 202210666260A CN 115045777 B CN115045777 B CN 115045777B
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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
- F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
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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
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- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a variable thrust solid-liquid rocket engine based on a combined grain, which comprises an oxidant catalytic supply component, a switching injector and a combined grain which are connected in sequence, wherein the oxidant catalytic supply component is used for catalytically decomposing an oxidant into high-temperature oxygen, and the high-temperature oxygen is sent into a combustion channel of the combined grain through the switching injector; the combined grain comprises a base body formed by low-moving-rate fuel and a plurality of uniformly distributed blades, high-moving-rate fuel is filled in a combustion channel formed between every two adjacent blades, the blades still keep a combustion channel structure in the combustion process of the high-moving-rate fuel, and the switching injector can inject high-temperature oxygen in a straight-flow mode along the axial direction of the combustion channel of the high-moving-rate fuel or in a swirling flow mode along the axial direction of the combustion channel of the high-moving-rate fuel; according to the invention, different injection modes of the oxidant are coupled with the spirally nested grain to obtain the variable thrust solid-liquid rocket engine, so that the robustness is better.
Description
Technical Field
The invention relates to the technical field of solid-liquid rocket engines, in particular to a variable thrust solid-liquid rocket engine based on combined explosive columns.
Background
The complexity of the structure of the liquid rocket engine determines the high manufacturing and using cost of the liquid rocket engine, while the solid rocket engine adopts solid fuel and oxidizer simultaneously, which causes difficulty in realizing repeated starting and thrust adjustment, although the two rocket engines are still developed, the defects cannot be solved by using single liquid phase or solid phase propellant, and the solid-liquid hybrid rocket engine adopts liquid and solid materials as the oxidizer and the fuel respectively, so that the technical and cost problems can be effectively solved, and the solid-liquid hybrid rocket engine gradually becomes a hot point of research of a rocket propulsion system.
The low combustion surface retreating speed of the traditional fuel grain is a core scientific problem which restricts the development of a solid-liquid engine, the height of the combustion surface retreating speed is closely related to the magnitude of the engine thrust, and the existing solid-liquid rocket engine has the following defects:
(1) The moving back rate of the solid-liquid engine is in direct proportional relation with the flow flux of the oxidant, so that the traditional variable thrust solid-liquid rocket engine mainly depends on the regulation of the flow of the oxidant, which has extremely high requirements on the variable flow control technology and large thrust replacement operation error;
(2) Due to the low retreating rate of the traditional fuel, the oxygen-fuel ratio is usually deviated when the flow of the oxidant is adjusted, so that the thrust regulation and control precision of the current solid-liquid rocket engine is difficult to guarantee.
Disclosure of Invention
The invention aims to provide a variable thrust solid-liquid rocket engine based on combined type grain, which is based on the influence characteristics of different injection modes of oxidant on the retreating speed of the fuel combined type grain, changes the injection mode through a switching injector, regulates and controls the retreating speed of a novel grain, and finally realizes the variable thrust regulation and control of the solid-liquid rocket engine so as to solve the technical problems that the thrust regulation and control precision of the current solid-liquid rocket engine is difficult to ensure in the prior art, and the thrust of the engine is difficult to improve directly due to the lower retreating speed of the traditional fuel grain.
In order to solve the technical problems, the invention specifically provides the following technical scheme:
a variable thrust solid-liquid rocket engine based on combined grains comprises an oxidant catalytic supply assembly, a switching injector and the combined grains which are sequentially connected, wherein the oxidant catalytic supply assembly is used for catalytically decomposing an oxidant into high-temperature oxygen, and the high-temperature oxygen is fed into a combustion channel of the combined grains through the switching injector;
the combined grain comprises a base body formed by low-retreating-rate fuel and a plurality of blades uniformly distributed on the inner wall of the base body, wherein a combustion channel formed between every two adjacent blades is filled with high-retreating-rate fuel, and the blades still maintain a combustion channel structure in the combustion process of the high-retreating-rate fuel;
the switching injector is capable of injecting the high temperature oxygen in a straight stream along an axial direction of the combustion path of the high recession rate fuel or in a swirling stream along an axial direction of the combustion path of the high recession rate fuel.
As a preferable scheme of the present invention, the oxidant catalytic supply assembly includes an oxidant storage tank, a main gas circuit, and a catalytic bed in sequence according to a moving direction of an oxidant;
wherein the oxidant storage tank is used for conveying an oxidant to the combined grain;
the oxidant is catalytically decomposed after contacting the catalytic bed and releases heat to be decomposed into high-temperature oxygen;
and the high-temperature oxygen is contacted with the solid fuel of the fuel combined type grain to realize the self-ignition starting.
As a preferable scheme of the invention, the catalytic bed adopts a multi-layer pure silver net structure.
As a preferable scheme of the invention, the blades of the combined grain are spirally arranged along the inner wall of the matrix, and a spiral channel is formed between every two adjacent blades.
As a preferable mode of the present invention, the switching injector includes three sub-stage injectors, the three sub-stage injectors include a co-rotating injector, a direct-flow injector, and a counter-rotating injector, and the co-rotating injector, the direct-flow injector, and the counter-rotating injector are respectively connected to the tip of the oxidizer catalytic assembly through parallel gas paths.
As a preferable scheme of the present invention, a shunt valve is arranged in the parallel gas path, and the shunt valve is used for controlling the on-off of the gas supply of the co-rotation injector, the direct-current injector, the counter-rotation injector and the oxidant catalytic assembly.
As a preferable scheme of the invention, the rotational flow direction of the oxidant passing through the co-rotating injector is the same as the direction of the spiral channel of the combined grain;
injecting an oxidant in the direct current injector along the axial direction of the combined grain;
the rotational flow direction of the oxidant passing through the reverse-rotation injector is opposite to the spiral channel of the combined grain.
As a preferred aspect of the present invention, the switching injector is coupled to the spiral channel of the combined grain by using three injection modes, so as to change the fuel migration rate of the combined grain in different injection modes and adjust the combustion thrust of the combined grain.
As a preferred scheme of the invention, the tail end of the combined grain is connected with a spray pipe, and the throat part of the spray pipe adopts a graphite throat.
Compared with the prior art, the invention has the following beneficial effects:
(1) Different injection modes of the oxidant are coupled with the spirally nested grain, and the combustion surface retreating speed of the spirally nested grain is influenced by the different injection modes of the oxidant, namely the fuel quantity of the spirally nested grain and the thrust of the engine are influenced by the different injection modes of the oxidant, so that the solid-liquid rocket engine with variable thrust is obtained;
(2) The invention only needs to switch the injection mode, further changes the combustion surface retreating speed, and compared with the traditional method for adjusting the valve opening or oxidant supply pressure to adjust the thrust of the engine by changing the oxidant flow, the invention is easier to realize in engineering application, has better robustness, and can further widen the thrust adjusting range of the solid-liquid rocket engine.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary and that other implementation drawings may be derived from the provided drawings by those of ordinary skill in the art without inventive effort.
FIG. 1 is a schematic structural diagram of a variable thrust solid-liquid rocket engine provided by an embodiment of the invention;
fig. 2 is a detailed schematic diagram of a fuel combination cartridge according to an embodiment of the present invention.
FIG. 3 is a schematic diagram of a switching injector provided in accordance with an embodiment of the present invention;
FIG. 4 is a graph showing the relative variation of the recession rate and oxidant flux of the fuel combination cartridge coupled with different injection modes according to an embodiment of the present invention;
FIG. 5 is a graph showing the relative change of the oxygen-fuel ratio and the oxidant flow rate of the fuel combination cartridge coupled with different injection modes according to an embodiment of the present invention.
The reference numerals in the drawings denote the following, respectively:
1-an oxidant storage tank, 2-a main gas path, 3-a catalytic bed, 4-a switching injector, 5-a combined grain, 6-a combustion channel and 7-a spray pipe;
41-sub-stage injector; 42-a shunt valve;
51-base, 52-blade.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in figure 1, the invention provides a variable thrust solid-liquid rocket engine based on combined grains, which sequentially comprises an oxidant catalytic assembly, a switching type injector 4, the combined grains 5 and a spray pipe 7 according to an air inlet combustion sequence.
The oxidant catalytic assembly is used for outputting high-temperature oxygen through catalysis, and the high-temperature oxygen increases the combustion surface retreating speed of the combined explosive column 5.
The switching injector 4 has a plurality of injection modes for injecting the oxidizer into the combined grain 5, and the switching injector 4 is used to change a swirl mode in which the oxidizer in the oxidizer catalytic assembly is introduced into the combined grain 5.
The different injection modes of the switching injector 4 are coupled with the combined grain 5 so as to change the fuel retreating speed of the combined grain 5 under the different injection modes and adjust the combustion thrust of the combined grain 5.
The combined grain 5 is internally provided with a combustion channel 6 for providing a combustion reaction space, and the combustion channel 6 is spiral. The tail end of the combined grain 5 is connected with a spray pipe 7, the throat part of the spray pipe 7 adopts a graphite throat, and the graphite throat lining is used for preventing ablation and is a conventional part of a solid-liquid rocket engine.
As a preference of the present embodiment, the oxidizer catalytic assembly includes an oxidizer tank 1, a main gas path 2, and a catalytic bed 3 in order along the flow direction of the oxidizer.
Wherein, the oxidant storage tank 1 is used for delivering the oxidant for the combined grain 5.
The catalytic bed 3 adopts a multi-layer pure silver net structure to replace an igniter of the combined explosive column 5, an oxidant is catalytically decomposed and releases heat after contacting with the catalytic bed 3, and the oxidant is decomposed into high-temperature oxygen, and the high-temperature oxygen contacts with the solid fuel of the combined explosive column 5 to realize spontaneous combustion starting.
As shown in fig. 1, the oxidizing agent H in the oxidizing agent storage tank 1 2 O 2 Enters a catalytic bed 3 through a main gas path 2 2 O 2 The high-temperature oxygen is catalyzed by a catalytic bed 3 and then decomposed to release a large amount of heat and oxygen to obtain high-temperature oxygen, the high-temperature oxygen contacts with a combined explosive column 5 through a switching injector 4 to ignite the explosive column, so that the self-ignition starting of the engine is realized, the whole combustion channel 6 is filled with the combustion, and high-temperature and high-pressure fuel gas is generated and is sprayed out through a spray pipe 7 to generate thrust.
As shown in FIG. 2, the combined grain 5 comprises a base 51 and a plurality of vanes 52 uniformly arranged on the inner wall of the base 51, and a fuel filling groove is formed between two adjacent vanes 52, wherein the base is composed of low-migration-rate fuel, and the fuel filling groove is filled with high-migration-rate fuel.
The base body 51 is formed by integrally extruding low-moving-rate fuel, the moving rates of the fuel forming the base body 51 and the fuel in the fuel filling groove are different, and the moving rate of the fuel forming the base body 51 is smaller than the moving rate of the fuel filled in the fuel filling groove.
The base body 51 is made of low-migration-rate fuel, such as ABS, PLA, HTPB, aluminum-magnesium alloy and the like, and the fuel filling groove is filled with high-migration-rate fuel, such as paraffin-based fuel, paraffin-doped HTPB fuel and the like.
Preferably, the blades (52) of the combined grain (5) are spirally arranged along the inner wall of the base body (51), a spiral combustion channel is formed between every two adjacent blades (52), and based on the difference between the low-withdrawal-rate fuel and the high-withdrawal-rate fuel, the combined grain (5) generates a characteristic structure, namely an internal spiral structure, in the combustion process, the characteristic structure can increase the residence time of gas in the combustion channel (6), and is beneficial to improving the withdrawal rate and the combustion efficiency of the grain.
As shown in fig. 3, the switching injector 4 is used for adjusting an injection mode in which catalytically decomposed high-temperature oxygen is input into the combined grain 5, and specifically, the switching injector 4 includes three sub-stage injectors 41, namely a co-rotating injector, a direct-current injector and a counter-rotating injector, the co-rotating injector, the direct-current injector and the counter-rotating injector are respectively connected with the tail end of the oxidant catalytic assembly through parallel gas paths, a shunt valve 42 is arranged in the parallel gas paths, and the shunt valve 42 is used for controlling the on-off of the gas supply of the co-rotating injector, the direct-current injector and the counter-rotating injector and the oxidant catalytic assembly.
Wherein, the rotational flow direction of the oxidant in the co-rotating injector is consistent with the spiral direction of the combined grain 5; the oxidant in the direct current injector is injected along the axial direction of the combined grain 5; the rotational flow direction of the oxidant in the backspin injector is opposite to the spiral direction of the combined grain 5.
As shown in fig. 4 and 5, the present embodiment is different from the conventional variable thrust hybrid rocket engine in that different injection modes of the oxidant are coupled with the spirally nested grain, and the variable thrust hybrid rocket engine is obtained because the different injection modes of the oxidant affect the combustion surface recession rate of the spirally nested grain, that is, the different injection modes of the oxidant affect the fuel quantity of the spirally nested grain and the thrust of the engine, so that the combustion characteristic of the hybrid rocket engine can be effectively controlled based on the influence characteristics of the different injection modes of the oxidant on the combustion surface recession rate of the combined grain 5.
In addition, the injection mode is changed only through valve switching of parallel gas circuits, the combustion surface retreating speed is further changed, the traditional adjusting valve opening or oxidant supply pressure is not changed, the thrust of the engine is adjusted through changing the oxidant flow, the method is easy to achieve in engineering application, good in robustness, and capable of further widening the thrust adjusting range of the solid-liquid rocket engine.
This embodiment will spiral nested type grain and whirl jet coupling, compare in traditional haplopore grain, very big influence its speed that moves back change law, and need emphasize, when this combination grain 5 was coupled with whirl jet, can very big improvement its speed that moves back, the experiment has proven to adopt ABS fuel based on adopting fuel combination formula grain base member, filling fuel adopts paraffin base fuel, when oxidant jet angle was unanimous with the helical line direction of the helical blade of grain base member, this combination grain 5 moves back speed and obviously promotes.
Therefore, it is easily concluded from the above experimental results that when the three sub-stage injectors of the switching injector 4 inject high-temperature oxygen into the combined grain 5, for the spiral grain, the three sub-stage injectors have the effect of increasing the combustion surface retreating rate of the combined grain 5 by the co-rotating injector > direct-current injector > anti-rotating injector, so that the switching injector 4 is adjusted according to the thrust requirement of the current solid-liquid rocket engine, and high-temperature oxygen is injected into the combined grain 5 through the co-rotating injector, the direct-current injector or the anti-rotating injector, thereby realizing variable thrust driving.
The above embodiments are only exemplary embodiments of the present application, and are not intended to limit the present application, and the protection scope of the present application is defined by the claims. Various modifications and equivalents may be made to the disclosure by those skilled in the art within the spirit and scope of the disclosure, and such modifications and equivalents should also be considered as falling within the scope of the disclosure.
Claims (5)
1. A variable thrust solid-liquid rocket engine based on combined explosive columns is characterized in that,
the device comprises an oxidant catalytic assembly, a switching injector (4) and a combined grain (5) which are connected in sequence, wherein the oxidant catalytic assembly is used for catalytically decomposing an oxidant into high-temperature oxygen, and the high-temperature oxygen is fed into a combustion channel of the combined grain (5) through the switching injector (4);
the combined explosive column (5) comprises a base body (51) formed by low-migration-rate fuel and a plurality of blades (52) uniformly distributed on the inner wall of the base body (51), wherein high-migration-rate fuel is filled in a combustion channel (6) formed between every two adjacent blades (52), and the blades (52) still maintain a combustion channel structure in the combustion process of the high-migration-rate fuel, wherein the blades (52) of the combined explosive column (5) are spirally arranged along the inner wall of the base body (51), and spiral combustion channels are formed between every two adjacent blades (52);
the switching injector (4) can inject the high-temperature oxygen in a straight flow along the axial direction of the combustion channel of the high-recession rate fuel and can also inject the high-temperature oxygen in a swirling flow along the axial direction of the combustion channel of the high-recession rate fuel;
the switching injector (4) comprises three secondary injectors (41), the three secondary injectors (41) comprise a co-rotating injector, a direct-current injector and a counter-rotating injector, and the co-rotating injector, the direct-current injector and the counter-rotating injector are respectively connected with the tail end of the oxidant catalysis assembly through parallel gas paths;
the rotational flow direction of the oxidant passing through the co-rotating injector is the same as the spiral direction of the combined grain (5);
the oxidant passing through the direct current injector is injected along the axial direction of the combined grain (5);
the rotational flow direction of the oxidant passing through the reverse-rotation injector is opposite to the spiral direction of the combined grain (5);
the switching injector (4) is coupled with the spiral combustion channel of the combined grain (5) by three injection modes to change the fuel migration rate of the combined grain (5) in different injection modes and adjust the thrust of the solid-liquid rocket engine.
2. The variable thrust solid-liquid rocket engine based on the combined grain of powder according to claim 1,
the oxidant catalytic assembly sequentially comprises an oxidant storage tank (1), a main gas path (2) and a catalytic bed (3) according to the moving direction of an oxidant;
wherein the oxidant storage tank (1) is used for conveying an oxidant to the combined grain (5);
the oxidant is catalytically decomposed and releases heat after contacting the catalytic bed (3) and is decomposed into high-temperature oxygen;
the high-temperature oxygen is contacted with the solid fuel of the combined grain (5) to realize the start of spontaneous combustion.
3. The variable thrust solid-liquid rocket engine based on the combined grain of powder according to claim 2,
the catalytic bed (3) adopts a multi-layer pure silver net structure.
4. The variable thrust solid-liquid rocket engine based on combined grains according to claim 1,
and a shunt valve (42) is arranged in the parallel gas circuit, and the shunt valve (42) is used for controlling the on-off of the gas supply of the co-rotating injector, the direct-current injector and the counter-rotating injector and the oxidant catalytic assembly.
5. The variable thrust solid-liquid rocket engine based on the combined grain of powder according to claim 1,
the tail end of the combined grain (5) is connected with a spray pipe (7), and the throat part of the spray pipe (7) adopts a graphite throat lining.
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Citations (3)
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| CN106121864A (en) * | 2016-07-22 | 2016-11-16 | 北京航空航天大学 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
| CN109989850A (en) * | 2019-04-12 | 2019-07-09 | 中国科学院力学研究所 | A kind of powder column for solid-liquid rocket |
| CN113357051A (en) * | 2021-06-25 | 2021-09-07 | 中国科学院力学研究所 | Internal spiral injection type solid-liquid engine explosive column |
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| US6684624B2 (en) * | 1998-07-22 | 2004-02-03 | The Board Of Trustees Of The Leland Stanford Junior University | High regression rate hybrid rocket propellants |
| KR20110082309A (en) * | 2010-01-11 | 2011-07-19 | 한국과학기술원 | Hybrid rocket by using catalytic decomposition of oxidizer |
| TWI504538B (en) * | 2013-05-31 | 2015-10-21 | Nat Applied Res Laboratories | Dual-vortical-flow hybrid rocket engine |
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| CN106121864A (en) * | 2016-07-22 | 2016-11-16 | 北京航空航天大学 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
| CN109989850A (en) * | 2019-04-12 | 2019-07-09 | 中国科学院力学研究所 | A kind of powder column for solid-liquid rocket |
| CN113357051A (en) * | 2021-06-25 | 2021-09-07 | 中国科学院力学研究所 | Internal spiral injection type solid-liquid engine explosive column |
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