CN114263548B - Solid-liquid mixed engine and aircraft - Google Patents
Solid-liquid mixed engine and aircraft Download PDFInfo
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- CN114263548B CN114263548B CN202111581353.1A CN202111581353A CN114263548B CN 114263548 B CN114263548 B CN 114263548B CN 202111581353 A CN202111581353 A CN 202111581353A CN 114263548 B CN114263548 B CN 114263548B
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention is suitable for the technical field of aircraft power, and provides a solid-liquid hybrid engine and an aircraft, wherein the solid-liquid hybrid engine comprises: a combustion chamber; the fuel storage box is arranged at one side of the combustion chamber and internally provided with solid fuel; the fuel nozzles are arranged on one side, close to the combustion chamber, of the fuel storage tank and are respectively communicated with the interior of the fuel storage tank; a gas tank connected to the fuel tank; a plurality of thermal feedback members disposed within the combustion chamber and respectively connected to the corresponding fuel nozzles; a plurality of oxidant nozzles disposed in the combustion chamber; an oxidizer tank in communication with the plurality of oxidizer nozzles. The solid-liquid mixing engine provided by the invention utilizes the heat generated by combustion in the combustion chamber to carry out thermal feedback on the fuel nozzle, and meanwhile, the thermal feedback piece is utilized to absorb the flame temperature in the combustion chamber and then transmit the flame temperature to the fuel nozzle, so that the thermal feedback rate of the combustion heat of the combustion chamber to the solid fuel can be increased, and the thrust generated by the solid-liquid mixing engine is effectively increased.
Description
Technical Field
The invention relates to the technical field of aircraft power, in particular to a solid-liquid hybrid engine and an aircraft.
Background
Engines of aircrafts (such as rockets and missiles) are always popular in all countries as main power sources of the aircrafts. At present, the engines of aircraft with more practical applications can be divided into three categories: solid engines, liquid engines, and solid-liquid hybrid engines. The solid-liquid mixed engine has the advantages of high specific impulse, adjustable thrust, capability of being shut down and started for multiple times, easiness in storage of the solid engine, simple structure and high reliability, and is an object of important research in recent years. However, the solid-liquid hybrid rocket engine also has a problem that the combustion rate of the solid fuel and the amount of oxidant supplied are difficult to match, and the thrust generated is low, and thus, researches are urgently needed.
In the prior art, the solid fuel of the solid-liquid mixing engine is integrally placed in a combustion chamber, and meanwhile, oxidant with fixed flow is introduced to the surface of an inner hole of the solid fuel by utilizing an oxidant storage tank, so that the solid fuel is combusted in the combustion chamber to generate thrust, and the thrust is provided for an aircraft. However, the solid fuel is not sufficiently thermally fed back by the heat generated by combustion in the combustion chamber, so that the solid fuel is low in melting rate, and the thrust of the solid-liquid mixed engine is difficult to improve.
Disclosure of Invention
The invention provides a solid-liquid mixing engine, and aims to solve the problems that the solid-liquid mixing engine in the prior art has insufficient heat feedback of heat generated by combustion in a combustion chamber on solid fuel and low melting rate of the solid fuel, so that the thrust of the solid-liquid mixing engine is difficult to improve.
The present invention is achieved as described above, and provides a solid-liquid hybrid engine, including:
a combustion chamber;
the fuel storage box is arranged on one side of the combustion chamber, and solid fuel is arranged in the fuel storage box;
the fuel nozzles are arranged on one side, close to the combustion chamber, of the fuel storage tank and are respectively communicated with the interior of the fuel storage tank;
a gas tank storing a compressed gas and connected to the fuel tank, the compressed gas being capable of compressing the solid fuel to cause the solid fuel to be ejected from the plurality of fuel nozzles into the combustion chamber;
the thermal feedback pieces are arranged in the combustion chamber and are respectively connected with the corresponding fuel nozzles, and the thermal feedback pieces are used for transmitting the flame temperature in the combustion chamber to the fuel nozzles;
a plurality of oxidant nozzles disposed in the combustion chamber; and
an oxidizer tank storing oxidizer and communicating with the plurality of oxidizer nozzles.
Preferably, an inner cavity is arranged in the fuel storage tank, the inner cavity is provided with a movable extrusion plate which divides the inner cavity into a fuel cavity and an air cavity, the plurality of fuel nozzles are respectively communicated with the fuel cavity, the air cavity is communicated with the gas storage tank, and the compressed gas can push the movable extrusion plate to extrude the solid fuel so that the solid fuel is sprayed out of the plurality of fuel nozzles to the combustion chamber.
Preferably, a plurality of the fuel nozzles and a plurality of the oxidizer nozzles are distributed on one side of the fuel storage tank close to the combustion chamber, and the fuel nozzles and the oxidizer nozzles are alternately arranged at intervals.
Preferably, a plurality of the fuel nozzles and a plurality of the oxidant nozzles are distributed in a honeycomb cell array.
Preferably, each thermal feedback member is connected to a tip end of one of the fuel nozzles, and each thermal feedback member extends from the fuel nozzle toward a center of the combustion chamber.
Preferably, the sum of the surface areas of the plurality of thermal feedback members is greater than the area of the cross-section of the combustion chamber.
Preferably, the compressed gas is carbon dioxide, nitrogen, helium or air; and/or the oxidant is gas oxygen, liquid oxygen, dinitrogen oxide or dinitrogen tetroxide.
Preferably, the solid fuel is a metal block or a non-metal block.
Preferably, the metal block is an aluminum block, a magnesium block, an iron block or a zirconium block; and/or the non-metal block is a paraffin block, a rubber block, a boron block or a plastic block.
The invention also provides an aircraft comprising the solid-liquid mixed engine.
According to the solid-liquid mixed engine provided by the invention, the plurality of fuel nozzles and the plurality of thermal feedback pieces are arranged in the combustion chamber and are respectively connected with the corresponding fuel nozzles, on one hand, the thermal feedback is directly carried out on the fuel nozzles by utilizing the heat generated by combustion in the combustion chamber, and the fuel nozzles carry out thermal feedback on the solid fuel in the fuel storage tank, so that the solid fuel close to the fuel nozzles is continuously heated and melted and is sprayed out to the combustion chamber from the fuel nozzles, the chemical proper ratio of the amount of the solid fuel melted by heating to the amount of the oxidant is kept, and the energy generated by the combustion of the solid fuel and the utilization efficiency of the solid fuel are improved; on the other hand, the thermal feedback piece is used for absorbing the flame temperature in the combustion chamber and then transmitting the flame temperature to the fuel nozzle, so that more heat can be added to the fuel nozzle, the thermal feedback rate of the fuel nozzle to the solid fuel in the fuel storage tank is improved, the fuel storage tank can melt more solid fuel, the flow velocity of the solid fuel sprayed by the plurality of fuel nozzles is increased, the solid-liquid mixing engine can generate larger thrust, and the thrust of the solid-liquid mixing engine is effectively improved.
Drawings
FIG. 1 is a schematic structural diagram of a solid-liquid hybrid engine according to an embodiment of the present invention;
FIG. 2 is a schematic sectional view taken along the line A-A in FIG. 1;
fig. 3 is a schematic sectional view taken along the direction B-B in fig. 1.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
According to the solid-liquid mixed engine provided by the embodiment of the invention, the plurality of fuel nozzles and the plurality of thermal feedback pieces are arranged, on one hand, the thermal feedback is directly carried out on the fuel nozzles by utilizing the heat generated by combustion in the combustion chamber, the fuel nozzles carry out thermal feedback on the fuel storage tank, the solid fuel close to the fuel nozzles is continuously heated and melted and is sprayed out to the combustion chamber from the fuel nozzles, so that the chemical right ratio of the amount of the solid fuel melted by heating to the amount of the oxidant is kept, and the utilization efficiency of the energy generated by the combustion of the solid fuel and the solid fuel is improved; on the other hand, the thermal feedback part is used for absorbing the flame temperature in the combustion chamber and then transmitting the flame temperature to the fuel nozzle, so that more heat can be added to the fuel nozzle, the thermal feedback rate of the fuel nozzle to the solid fuel in the fuel storage tank is improved, more solid fuel can be melted, the flow velocity of the solid fuel sprayed out by the plurality of fuel nozzles is increased, the solid-liquid mixing engine can generate larger thrust, and the thrust of the solid-liquid mixing engine is effectively improved.
Referring to fig. 1 to fig. 3, an embodiment of the present invention provides a solid-liquid hybrid engine, including:
a combustion chamber 1;
a fuel storage tank 2 which is arranged at one side of the combustion chamber 1 and is internally provided with solid fuel 20;
a plurality of fuel nozzles 3 provided on the side of the fuel storage tank 2 close to the combustion chamber 1, the plurality of fuel nozzles 3 being communicated with the inside of the fuel storage tank 2, respectively;
a gas tank 4 storing compressed gas and connected to the fuel tank 2, the compressed gas being capable of extruding the solid fuel 20 so that the solid fuel 20 is ejected from the plurality of fuel nozzles 3 to the combustion chamber 1;
a plurality of thermal feedback members 5 provided in the combustion chamber 1 and connected to the corresponding fuel nozzles 3, respectively;
a plurality of oxidizer nozzles 6 provided in the combustion chamber 1; and
an oxidizer tank 7 storing oxidizer and communicating with the plurality of oxidizer nozzles 6.
In the embodiment of the invention, the solid-liquid mixing engine also comprises a spray pipe 8 communicated with the combustion chamber 1, when the solid-liquid mixing engine works, the molten solid fuel 20 is sprayed to the combustion chamber 1 from the plurality of fuel nozzles 3, the oxidant in the oxidant storage tank 7 is sprayed to the combustion chamber 1 from the plurality of oxidant nozzles 6, the solid fuel and the oxidant are mixed and combusted in the combustion chamber 1, and combustion gas is sprayed from the spray pipe 8 to provide thrust for the aircraft.
As an embodiment of the invention, the solid fuel is a metal block or a non-metal block. Wherein the metal block is an aluminum block, a magnesium block, an iron block or a zirconium block; the nonmetal blocks are paraffin blocks, rubber blocks, boron blocks or plastic blocks. Preferably, the solid fuel is a paraffin block, and the solid fuel is convenient to melt by utilizing the characteristics of low melting point and low cost of the paraffin block, and the cost is reduced.
In the embodiment of the invention, when the solid-liquid mixed engine works, on one hand, heat generated by combustion in the combustion chamber 1 is utilized to carry out thermal feedback on the fuel nozzle 3, so that the solid fuel close to the fuel nozzle 3 is continuously heated and melted, the compressed gas in the gas storage tank 4 enters the fuel storage tank 2, the compressed gas pushes the solid fuel to move towards the fuel nozzle 3, so that the solid fuel close to the fuel nozzle 3 and heated and melted is sprayed into the combustion chamber 1 through the fuel nozzle 3, and the oxidant sprayed by the oxidant nozzle 6 is combusted after being contacted with the solid fuel sprayed by the fuel nozzle 3, so as to provide thrust for an aircraft. On the other hand, the thermal feedback piece 5 is used for absorbing the flame temperature in the combustion chamber 1 and then transmitting the flame temperature to the fuel nozzle 3, so that more heat can be added to the fuel nozzle 3, the thermal feedback rate of the fuel nozzle 3 to the fuel storage tank 2 is improved, more solid fuel can be melted in the fuel storage tank 2, the flow velocity of the solid fuel sprayed by the plurality of fuel nozzles 3 is increased, and the solid-liquid mixing engine can generate larger thrust.
In addition, the speed of the solid fuel which is heated and melted is determined by the heat generated by combustion in the combustion chamber 1, so that the solid fuel quantity which is heated and melted by the solid fuel and the oxidant quantity can be ensured to keep a chemical proper ratio, the utilization efficiency of the energy and the fuel which are generated by combustion is improved, the using amount of the solid fuel can be reduced, the situation that the engine has more fuel allowance after working is avoided, the waste of the fuel is reduced, the whole weight of the solid-liquid mixed engine can be reduced, and the energy waste of the engine can be reduced.
In the embodiment of the invention, the heat feedback required by a specific requirement can be achieved by adjusting the spatial position of the thermal feedback piece 5 in the combustion chamber 1, the material of the thermal feedback piece 5, the size of the thermal feedback piece 5 and the shape of the thermal feedback piece 5, the heat of the combustion chamber 1 is transferred from the thermal feedback piece 5 to the fuel nozzle 3 and then transferred to the solid fuel in the fuel storage tank 2 through the fuel nozzle 3, so that the solid fuel is liquefied at a certain speed, and the liquefied solid fuel is controlled to be injected into the combustion chamber 1 at a certain mass flow under the action of compressed gas so as to meet the thrust required by an aircraft. Preferably, the thermal feedback member 5 is made of metal, and the specific material of the thermal feedback member 5 can be set according to the thrust required by the aircraft.
In the embodiment of the present invention, the shape of the thermal feedback member 5 may be a sphere, a cone, a column or other shapes, and the thermal feedback member 5 may also be a combination of shapes. In the present embodiment, the thermal feedback member 5 is a combination of a columnar shape and a tapered shape, the thermal feedback member 5 includes a rod portion 51 connected to the fuel nozzle 3, and a tapered portion 52 connected to the rod portion 51, the rod portion 51 is columnar, and the tapered portion 52 is tapered.
As an embodiment of the invention, the sum of the surface areas of the plurality of thermal feedback members 5 is larger than the area of the cross section of the combustion chamber 1. The combustion chamber 1 has a cross-section opposite to the bottom surface 25 of the fuel reservoir 2. The sum of the surface areas of the thermal feedback parts 5 is set to be larger than the area of the cross section of the combustion chamber 1, the heating area of the fuel storage tank 2 is increased by the thermal feedback parts 5, more solid fuels can be melted in the fuel storage tank 2, and therefore the fuel nozzles 3 can spray more solid fuels to the combustion chamber 1, and the solid-liquid hybrid rocket can generate larger thrust.
As an embodiment of the present invention, an inner cavity is provided in the fuel storage tank 2, the inner cavity is provided with a movable extrusion plate 23 dividing the inner cavity into a fuel cavity 21 and an air cavity 22, the air cavity 22 is communicated with the gas storage tank 4, the plurality of fuel nozzles 3 are respectively communicated with the fuel cavity 21, and the compressed gas can push the movable extrusion plate 23 to extrude the solid fuel, so that the solid fuel is ejected from the plurality of fuel nozzles 3 to the combustion chamber 1. Wherein the gas chamber 22 is communicated with the gas tank 4 through a pipeline, and the plurality of fuel nozzles 3 are respectively communicated with the fuel chamber 21 through pipelines.
In this embodiment, when the solid-liquid hybrid engine works, the valve on the gas tank 4 is opened at this time, the compressed gas in the gas tank 4 enters the air cavity 22 of the fuel tank 2 through the pipeline, the compressed gas entering the air cavity 22 of the fuel tank 2 pushes the movable extrusion plate 23 to move towards the solid fuel, so as to push the solid fuel to move towards the fuel nozzle 3 as a whole, so as to eject the heated and melted solid fuel close to the fuel nozzle 3 into the combustion chamber 1 through the fuel nozzle 3, and the oxidant ejected from the oxidant nozzle 6 contacts with the solid fuel ejected from the fuel nozzle 3 and then burns, so that the solid-liquid hybrid engine continuously works until the end, so as to provide the flight power for the aircraft. The solid fuel is extruded by pushing the movable extrusion plate 23 with compressed gas, the supply amount of the solid fuel can be self-regulated, the supply of the solid fuel can be stably realized, and the structure is simple.
As an embodiment of the present invention, the oxidizer storage tank 7 is respectively communicated with the plurality of oxidizer nozzles 6 through a pipe 9, and the oxidizer in the oxidizer storage tank 7 is sprayed to the combustion chamber 1 through the pipe 9 and respectively from the plurality of oxidizer nozzles 6.
As an embodiment of the present invention, a plurality of fuel nozzles 3 and a plurality of oxidizer nozzles 6 are distributed in an array on one side of the fuel storage tank 2 near the combustion chamber 1, and the fuel nozzles 3 and the oxidizer nozzles 6 are alternately arranged at intervals.
In this embodiment, the oxidant nozzles 6 arranged in an array spray the oxidant and the fuel nozzles 3 arranged in an array spray the solid fuel, so that the oxidant sprayed from the oxidant nozzles 6 and the solid fuel sprayed from the fuel nozzles 3 are mixed more uniformly, and the solid fuel is combusted more fully.
In this embodiment, the fuel nozzles 3 and the oxidant nozzles 6 are alternately arranged at intervals, that is, the fuel nozzles 3 and the oxidant nozzles 6 are alternately arranged in sequence, so that the oxidant sprayed from the oxidant nozzles 6 and the solid fuel sprayed from the fuel nozzles 3 are uniformly mixed, and the fuel nozzles 3 and the oxidant nozzles 6 have a certain physical distance to prevent heat from being transferred to the pipeline 9.
As an embodiment of the present invention, the plurality of fuel nozzles 3 and the plurality of oxidant nozzles 6 are respectively distributed in a honeycomb hole array, so that the oxidant sprayed from the oxidant nozzles 6 is mixed with the solid fuel sprayed from the fuel nozzles 3 in the form of the honeycomb hole array, the plurality of fuel nozzles 3 and the plurality of oxidant nozzles 6 are densely arranged, the oxidant and the solid fuel are mixed more uniformly, and the solid fuel is combusted more fully.
As an embodiment of the present invention, each thermal feedback member 5 is connected to the end of one fuel nozzle 3, and each thermal feedback member 5 extends from the fuel nozzle 3 toward the center of the combustion chamber 1. Each thermal feedback piece 5 transmits the flame temperature at the center of the combustion chamber 1 to the corresponding fuel nozzle 3, and then the fuel nozzles 3 feed back the heat to the fuel storage tank 2, so that the corresponding amount of solid fuel is melted, and each fuel nozzle 3 utilizes one thermal feedback piece 5 to increase the thermal feedback rate, thereby improving the thrust of the solid-liquid mixing engine. The number of the thermal feedback members 5 is equal to the number of the fuel nozzles 3, and the number of the thermal feedback members 5 and the number of the fuel nozzles 3 can be set according to actual needs. The number of thermal feedback elements 5 and the number of fuel nozzles 3 shown in fig. 2 are 25.
As an embodiment of the present invention, the compressed gas is carbon dioxide, nitrogen, helium or air. In addition to the present embodiment, the compressed gas may be other gases,
as an embodiment of the present invention, the oxidizing agent is gaseous oxygen, liquid oxygen, dinitrogen oxide, or dinitrogen tetroxide. Besides this embodiment, the oxidizing agent may be other oxidizing agents. Preferably, the oxidizing agent is liquid oxygen.
When the solid-liquid mixed engine provided by the invention works, heat generated by combustion in the combustion chamber 1 is utilized to carry out heat feedback on the fuel nozzle 3, meanwhile, the heat feedback piece 5 is utilized to absorb the flame temperature in the combustion chamber 1 and then transmit the flame temperature to the fuel nozzle 3, the fuel nozzle transmits the heat to the fuel storage tank 2, so that the solid fuel close to the fuel nozzle 3 is continuously heated and melted, the heat feedback piece 5 is utilized to simultaneously heat to carry out heat feedback on the fixed fuel in the fuel storage tank 2, and the heat feedback rate of the fuel nozzle 3 to the fuel storage tank 2 is improved. Compressed gas in the gas storage tank 4 enters an air cavity of the fuel storage tank 2 through a pipeline, the compressed gas entering the air cavity of the fuel storage tank 2 pushes a movable extrusion plate 23 to move towards the solid fuel so as to push the solid fuel to move towards the fuel nozzle 3 integrally, so that the heated and melted solid fuel close to the fuel nozzle 3 is sprayed out through the fuel nozzle 3 to enter the combustion chamber 1, an oxidant sprayed out from the oxidant nozzle 6 is contacted with the solid fuel sprayed out from the fuel nozzle 3 and then is combusted, and the solid-liquid mixing engine is enabled to continuously work until the operation is finished so as to provide flight power for the aircraft.
In addition, in order to prove the technical effects obtained by the invention, the inventor carries out the following two groups of comparative experiments on the solid-liquid mixed engine of the invention and the traditional solid-liquid mixed engine. Wherein, the fixed fuel of the two experiments adopts paraffin blocks, and the oxidant adopts N2O。
The first set of experiments was conducted using a conventional solid-liquid hybrid engine capable of producing 2.8 tons of thrust, and the thermal feedback power of the combustion chamber to the paraffin block was found to be 916088W, and the melting rate of the paraffin block was found to be 2.32 kg/s.
A second set of experiments was carried out with a solid-liquid hybrid engine according to the invention with a thermal feedback 5, the fuel tank 2 having a bottom surface area of 1.13m2The number of the fuel nozzles 3 is 25, each fuel nozzle 3 is connected with one thermal feedback piece 5, the diameter of the bottom surface of the conical part 52 of each thermal feedback piece 5 is 0.14m, the length of the generatrix is 0.163m, and the surface area of the single conical part 52 is 0.0512m2The surface area of the stem 51 of the thermal feedback member 5 is 0.1024m2Each thermal feedback member 5 has a surface area of 0.1536m2And the total surface area of the 25 thermal feedback members 5 is 3.84m2The thermal feedback power of the combustion chamber to the paraffin block is 3113076W, the melting rate of the paraffin block is 6.534kg/s, and the solid-liquid mixing engine can generate 7.885 tons of thrust.
Therefore, the invention can obviously increase the heat feedback rate of the solid fuel by increasing the fuel nozzle 3 and the heat feedback piece 5, obviously increase the melting rate of the solid fuel in the fuel storage tank 2, and effectively increase the thrust of the solid-liquid mixing engine.
The embodiment of the invention also provides an aircraft comprising the solid-liquid hybrid engine of the embodiment. According to the aircraft provided by the embodiment of the invention, the solid-liquid mixing engine absorbs the flame temperature in the combustion chamber 1 by using the thermal feedback piece 5 and then transfers the flame temperature to the fuel nozzles 3, so that the thermal feedback rate of the fuel storage tank 2 is increased, more solid fuels can be melted in the fuel storage tank 2, more solid fuels can be sprayed out by the plurality of fuel nozzles 3 to be mixed and combusted with the oxidant, and the aircraft can generate larger thrust.
According to the solid-liquid mixed engine provided by the embodiment of the invention, the plurality of fuel nozzles and the plurality of thermal feedback pieces are arranged in the combustion chamber and are respectively connected with the corresponding fuel nozzles, on one hand, the thermal feedback is directly carried out on the fuel nozzles by utilizing the heat generated by combustion in the combustion chamber, and the fuel nozzles carry out thermal feedback on the fuel storage tank, so that the solid fuel close to the fuel nozzles is continuously heated and melted and is sprayed out to the combustion chamber from the fuel nozzles, the chemical proper ratio of the amount of the solid fuel melted by heating to the amount of the oxidant is kept, and the utilization efficiency of the energy generated by the combustion of the solid fuel and the utilization efficiency of the solid fuel are improved; on the other hand, the thermal feedback piece is used for absorbing the flame temperature in the combustion chamber and then transmitting the flame temperature to the fuel nozzle, so that more heat can be added to the fuel nozzle, the thermal feedback rate of the fuel nozzle to the solid fuel in the fuel storage tank is improved, the fuel storage tank can melt more solid fuel, the flow velocity of the solid fuel sprayed by the plurality of fuel nozzles is increased, the solid-liquid mixing engine can generate larger thrust, and the thrust of the solid-liquid mixing engine is effectively improved.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A solid-liquid hybrid engine, comprising:
a combustion chamber;
the fuel storage tank is arranged on one side of the combustion chamber, and solid fuel is arranged in the fuel storage tank;
the fuel nozzles are arranged on one side, close to the combustion chamber, of the fuel storage tank and are respectively communicated with the interior of the fuel storage tank;
a gas tank storing a compressed gas and connected to the fuel tank, the compressed gas being capable of compressing the solid fuel to cause the solid fuel to be ejected from the plurality of fuel nozzles into the combustion chamber;
the thermal feedback pieces are arranged in the combustion chamber and are respectively connected with the corresponding fuel nozzles, and the thermal feedback pieces are used for transmitting the flame temperature in the combustion chamber to the fuel nozzles;
a plurality of oxidant nozzles disposed in the combustion chamber; and
an oxidizer tank storing oxidizer and communicating with the plurality of oxidizer nozzles.
2. The solid-liquid mixing engine according to claim 1, wherein an inner chamber is provided in the fuel tank, the inner chamber is provided with a movable squeeze plate dividing the inner chamber into a fuel chamber and an air chamber, the plurality of fuel nozzles are respectively communicated with the fuel chamber, the air chamber is communicated with the gas tank, and the compressed gas can push the movable squeeze plate to squeeze the solid fuel so that the solid fuel is ejected from the plurality of fuel nozzles to the combustion chamber.
3. The solid-liquid hybrid engine of claim 1, wherein a plurality of the fuel nozzles and a plurality of the oxidizer nozzles are distributed on a side of the fuel tank near the combustion chamber, and the fuel nozzles and the oxidizer nozzles are alternately spaced.
4. The solid-liquid hybrid engine of claim 1, wherein a plurality of the fuel nozzles and a plurality of the oxidant nozzles are distributed in a honeycomb array.
5. The solid-liquid hybrid engine of claim 1, wherein each of the thermal feedback members is connected to a tip end of a corresponding one of the fuel nozzles, and each of the thermal feedback members extends from the fuel nozzle toward a center of the combustion chamber.
6. The solid-liquid hybrid engine of claim 1, wherein the sum of the surface areas of the plurality of thermal feedback members is greater than the area of the combustion chamber cross-section.
7. A solid-liquid hybrid engine according to claim 1, characterized in that the compressed gas is carbon dioxide, nitrogen, helium or air; and/or the oxidant is gas oxygen, liquid oxygen, dinitrogen oxide or dinitrogen tetroxide.
8. The solid-liquid hybrid engine of claim 1, characterized in that the solid fuel is a metallic or non-metallic block.
9. The solid-liquid hybrid engine of claim 8, characterized in that the metal block is an aluminum block, a magnesium block, an iron block, or a zirconium block; and/or the non-metal block is a paraffin block, a rubber block, a boron block or a plastic block.
10. An aircraft, characterized in that it comprises a solid-liquid hybrid engine according to any one of claims 1 to 9.
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