CN114109654B - Solid-liquid mixed engine and aircraft - Google Patents
Solid-liquid mixed engine and aircraft Download PDFInfo
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- CN114109654B CN114109654B CN202111415892.8A CN202111415892A CN114109654B CN 114109654 B CN114109654 B CN 114109654B CN 202111415892 A CN202111415892 A CN 202111415892A CN 114109654 B CN114109654 B CN 114109654B
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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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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 housing; a nozzle; a combustion chamber; a propellant; a gas storage tank; the oxidant storage tank is connected with the gas storage tank through a first pipeline; a plurality of oxidizer nozzles connected to the oxidizer tank; the solid fuel storage tank is provided with an inner cavity, a squeezing plate which divides the inner cavity into a fuel cavity and an air cavity is movably arranged in the solid fuel storage tank, the fuel cavity is provided with solid fuel and is arranged close to the combustion chamber, and the air cavity is connected with the gas storage tank through a second pipeline; and the plurality of fuel nozzles are distributed in the solid fuel storage tank in an array and are communicated with the fuel cavity. The solid-liquid mixed engine provided by the invention ingeniously utilizes the thermal feedback principle of the combustion chamber to realize the accurate adjustment of the flow of the solid fuel, so that the solid fuel quantity sprayed by the fuel nozzle and the supply quantity of the oxidant are always in a chemical proper ratio, the utilization efficiency of energy and fuel generated by combustion is improved, and the waste of the fuel is reduced.
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 supply amount of the oxidizer are difficult to match, and the generated energy is low, and thus, researches are urgently needed to solve the problem.
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 combustion rate of the solid fuel is not matched with the supply amount of the oxidant, so that the chemical right ratio cannot be achieved, the generated energy is low, the combustion speed of the solid fuel is low, the fuel allowance is large after the engine works, and the fuel waste is serious.
Disclosure of Invention
The invention provides a solid-liquid mixing engine, and aims to solve the problems that the combustion rate of solid fuel of the solid-liquid mixing engine in the prior art is not matched with the supply quantity of an oxidant, so that the chemical right ratio cannot be achieved, the generated energy is low, the fuel allowance is large after the engine works, and the fuel waste is serious.
The present invention is achieved as described above, and provides a solid-liquid hybrid engine including:
a housing;
a nozzle connected to the housing;
the combustion chamber is arranged in the shell and communicated with the spray pipe;
a propellant disposed within the combustion chamber;
the gas storage box is arranged in the shell and stores compressed gas;
the oxidant storage tank is arranged in the shell and stores oxidant, and the oxidant storage tank is connected with the gas storage tank through a first pipeline;
a plurality of oxidizer nozzles distributed in the combustion chamber and connected to the oxidizer tank;
the solid fuel storage tank is arranged on one side of the combustion chamber and provided with an inner cavity, a squeezing plate which divides the inner cavity into a fuel cavity and an air cavity is movably arranged in the solid fuel storage tank, the fuel cavity is provided with solid fuel and is arranged close to the combustion chamber, and the air cavity is connected with the gas storage tank through a second pipeline;
And the fuel nozzles are distributed on one side of the solid fuel storage tank close to the combustion chamber in an array manner and are communicated with the fuel cavity.
Preferably, the plurality of oxidant nozzles are symmetrically arranged at opposite sides of the plurality of fuel nozzles, and the plurality of oxidant nozzles are arranged toward the center of the combustion chamber.
Preferably, a plurality of said oxidant nozzles are connected to said oxidant tank by a third line.
Preferably, the compressed gas is carbon dioxide, nitrogen, helium or air.
Preferably, the oxidant is gaseous oxygen, liquid oxygen, dinitrogen oxide, dinitrogen tetroxide or carbon dioxide.
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.
Preferably, the non-metal block is a paraffin block, a rubber block, a plastic block or a boron block.
Preferably, the propellant is a butylated hydroxytrister propellant.
The invention also provides an aircraft comprising the solid-liquid hybrid engine.
The invention provides a solid-liquid mixing engine which is provided with a gas storage tank, an oxidant storage tank, a solid fuel storage tank, a plurality of oxidant nozzles and a plurality of fuel nozzles, wherein the oxidant storage tank is connected with the gas storage tank through a first pipeline, a squeezing plate for dividing an inner cavity into a fuel cavity and an air cavity is movably arranged in the solid fuel storage tank, and the air cavity of the solid fuel storage tank is connected with the gas storage tank through a second pipeline. When the solid-liquid mixing engine works, the heat generated in the combustion chamber is utilized to carry out thermal feedback on the fuel nozzle, so that the solid fuel close to the fuel nozzle in the solid fuel storage tank is continuously heated and melted and is sprayed out to the combustion chamber from the fuel nozzle under the extrusion action of the extrusion plate, the flow rate of the solid fuel is accurately adjusted by skillfully utilizing the thermal feedback principle of the combustion chamber, the solid fuel quantity sprayed out by the fuel nozzle and the supply quantity of the oxidant are always in a chemical proper ratio, the combustion rate of the solid fuel is matched with the supply quantity of the oxidant, the fuel is combusted in the chemical proper ratio, the utilization efficiency of the energy generated by combustion and the fuel is improved, and the energy utilization rate of the solid-liquid mixing engine is obviously improved; moreover, because the solid fuel is combusted in a chemical proper ratio, the consumption of the solid fuel can be reduced, the situation that the fuel surplus is large after the engine works is avoided, the waste of the fuel is reduced, the whole weight of the solid-liquid mixed engine can be reduced, and the waste of energy generated by the fuel is avoided.
Drawings
FIG. 1 is a schematic structural diagram of a solid-liquid hybrid engine at a starting stage according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a solid-liquid hybrid engine in a formal working stage according to an embodiment of the present invention.
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.
The solid-liquid mixing engine provided by the embodiment of the invention is provided with the gas storage tank, the oxidant storage tank, the solid fuel storage tank, the oxidant nozzles and the fuel nozzles, wherein the oxidant storage tank is connected with the gas storage tank through a first pipeline, the solid fuel storage tank is movably provided with the extrusion plate which divides the inner cavity of the solid fuel storage tank into the fuel cavity and the air cavity, and the air cavity of the solid fuel storage tank is connected with the gas storage tank through a second pipeline. When the solid-liquid mixed engine works, the flow of solid fuel is accurately adjusted by ingeniously utilizing the thermal feedback principle of the combustion chamber, so that the solid fuel sprayed by the fuel nozzle and the supply quantity of an oxidant are always in a chemically correct ratio, the utilization efficiency of energy and fuel generated by combustion is improved, the energy utilization rate of the solid-liquid mixed engine is obviously improved, the using quantity of the solid fuel can be reduced, the waste of the fuel is reduced, the integral weight of the solid-liquid mixed engine can be reduced, and the waste of the energy generated by the fuel is avoided.
Referring to fig. 1-2, an embodiment of the present invention provides a solid-liquid hybrid engine, including:
a housing 1;
a nozzle 2 connected to the casing 1;
the combustion chamber 3 is arranged in the machine shell 1 and communicated with the spray pipe 2;
a propellant 4 disposed within the combustion chamber 3;
a gas storage tank 5 which is provided in the casing 1 and stores compressed gas;
an oxidizer storage tank 6 which is arranged in the machine shell 1 and stores an oxidizer 61, wherein the oxidizer storage tank 6 is connected with the gas storage tank 5 through a first pipeline 7;
a plurality of oxidizer nozzles 8, a plurality of oxidizer nozzles 8 being distributed in the combustion chamber 3 in an array and connected to the oxidizer storage tank 6;
the solid fuel storage tank 9 is arranged at one side of the combustion chamber 3 and is provided with an inner cavity, a squeezing plate 93 which divides the inner cavity into a fuel cavity 91 and an air cavity 92 is movably arranged in the solid fuel storage tank 9, the fuel cavity 91 is provided with solid fuel 94 and is arranged close to the combustion chamber 3, and the air cavity 92 is connected with the gas storage tank 5 through a second pipeline 10;
a plurality of fuel nozzles 11, a plurality of fuel nozzles 11 being distributed in an array on a side of the solid fuel storage tank 9 near the combustion chamber 3 and communicating with the fuel cavity 91.
As an embodiment of the invention, the propellant 4 is a butylated hydroxytricopol propellant. The hydroxyl-terminated polybutadiene three-component propellant has the characteristics of low burning rate, small energy loss and high stability, and can keep low burning and good burning stability.
In the embodiment of the invention, when the solid-liquid mixed engine is started (as shown in fig. 1), the propellant 4 is used for ignition, the heat generated by the propellant 4 is used for heating and feeding back the fuel nozzle 11, so that the solid fuel close to the fuel nozzle 11 in the fuel cavity 91 is heated and melted, and when the solid-liquid mixed engine subsequently enters a formal working stage, the fuel nozzle 11 can timely and quickly spray a corresponding amount of solid fuel to the combustion chamber 3, so that the fuel is combusted in a chemically proper ratio, and the energy generated by combustion and the utilization efficiency of the fuel are improved.
As a preferred embodiment of the present invention, the compressed gas is carbon dioxide, nitrogen, helium or air. Wherein, the compressed gas in the gas storage tank 5 can be any one of 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, dinitrogen tetroxide or carbon dioxide. Besides this embodiment, the oxidizing agent may be other oxidizing agents. Preferably, the oxidizing agent is liquid oxygen.
In the embodiment of the present invention, the air chamber 92 of the solid fuel storage tank 9 is connected to the gas storage tank 5 through the second pipeline 10, so that the compressed gas in the gas storage tank 5 can push the pressing plate 93 to move toward the solid fuel 94 to press the solid fuel 94, so that the heated and melted fuel is ejected from the fuel nozzle 11 to the combustion chamber 3, and the fuel ejected from the fuel nozzle 11 is combusted after contacting with the oxidant ejected from the oxidant nozzle 8.
As an embodiment of the invention, the gas tank 5 is provided with a valve through which the first line 7 and the second line 10 are connected to the gas tank 5, respectively. When the solid-liquid mixing engine is in a starting stage, the valve is in a closed state, so that compressed gas in the gas storage tank 5 does not enter the first pipeline 7 and the second pipeline 10; when the solid-liquid hybrid engine enters a formal working stage, the valve is in an open state, so that compressed gas in the gas storage tank 5 respectively enters the first pipeline 7 and the second pipeline 10, the compressed gas entering the oxidizer storage tank 6 pushes the oxidizer 61 to enter the combustion chamber 3 through the oxidizer nozzle 8, the compressed gas entering the air cavity 92 of the solid fuel storage tank 9 pushes the extrusion plate 93 to move towards the solid fuel 94, so that the solid fuel 94 moves towards the fuel nozzle 11, so that the solid fuel heated and melted close to the fuel nozzle 11 is sprayed into the combustion chamber 3 through the fuel nozzle 11, and the oxidizer 61 sprayed from the oxidizer nozzle 8 is contacted with the solid fuel sprayed from the fuel nozzle 11 and then combusted, so that flight power is provided for an aircraft.
As one embodiment of the present invention, the solid fuel 94 is a metallic or non-metallic 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 and plastic blocks. Preferably, the solid fuel 94 is a paraffin block, and the solid fuel 94 has a low melting point and can be implemented at a low cost.
As an embodiment of the invention, a plurality of oxidant nozzles 8 are connected to the oxidant tank 6 via a third line 12.
In this embodiment, the compressed gas entering the oxidizer tank 6 pushes the oxidizer 61 along the third pipe 12 into the plurality of oxidizer nozzles 8, respectively, and the oxidizer 61 is ejected from the plurality of oxidizer nozzles 8 into the combustion chamber 3. In addition to this embodiment, a plurality of oxidant nozzles 8 can also be connected directly to the oxidant tank 6.
In the embodiment of the present invention, the arrangement of the plurality of oxidant nozzles 8 and the plurality of fuel nozzles 11 is not limited. The oxidant nozzles 8 arranged in a plurality of arrays eject the oxidant and the fuel nozzles 11 arranged in a plurality of arrays eject the solid fuel, so that the oxidant 61 ejected from the oxidant nozzles 8 and the solid fuel ejected from the fuel nozzles 11 are uniformly mixed and the combustion is performed sufficiently.
As an embodiment of the present invention, the plurality of oxidant nozzles 8 are symmetrically disposed on two opposite sides of the plurality of fuel nozzles 11, and the plurality of oxidant nozzles 8 are disposed toward the center of the combustion chamber 3, so that the oxidant 61 sprayed from the oxidant nozzles 8 is more uniformly mixed with the solid fuel sprayed from the fuel nozzles 11.
In the embodiment of the invention, in the starting stage (as shown in fig. 1) of the solid-liquid mixed engine, the engine starts to work after the propellant 4 is ignited, and the fuel nozzle 11 is heated and fed back, so that the solid fuel in the fuel cavity 91 close to the fuel nozzle 11 is heated and melted until the propellant 4 is burnt, and then the engine enters the formal working stage.
When the solid-liquid mixing engine enters a formal working stage (as shown in fig. 2), at this time, a valve on the gas storage tank 5 is opened, compressed gas in the gas storage tank 5 enters gas cavities 92 of the oxidizer storage tank 6 and the solid fuel storage tank 9 through a first pipeline 7 and a second pipeline 10, the compressed gas entering the oxidizer storage tank 6 pushes the oxidizer 61 to enter the combustion chamber 3 through the oxidizer nozzle 8, the compressed gas entering the gas cavity 92 of the solid fuel storage tank 9 pushes the extrusion plate 93 to move towards the solid fuel 94 to push the solid fuel 94 to move towards the fuel nozzle 11 as a whole, so that the heated and melted solid fuel close to the fuel nozzle 11 is ejected into the combustion chamber 3 through the fuel nozzle 11, the oxidizer ejected from the oxidizer nozzle 8 contacts with the solid fuel ejected from the fuel nozzle 11 to be combusted, and the solid-liquid mixing engine continues to work until the end, to provide flight power to the aircraft.
The solid-liquid mixed engine utilizes the heat generated by combustion in the combustion chamber 3 to carry out thermal feedback on the fuel nozzle 11 in the whole working stage, so that the solid fuel 94 close to the fuel nozzle 11 is continuously heated and melted, since the rate at which the solid fuel 94 is heated to melt is determined by the amount of heat generated by combustion in the combustion chamber 3, and the heated area of the solid fuel 94 is kept constant, can ensure that the quantity of the solid fuel melted by heating the solid fuel 94 keeps a chemical right ratio with the quantity of the oxidant, automatically realize the accurate adjustment of the flow of the solid fuel by skillfully utilizing the thermal feedback principle of the combustion chamber, so that the solid fuel and the oxidant sprayed from the fuel nozzle 11 are always in a chemically correct ratio, therefore, the combustion rate of the solid fuel is matched with the supply quantity of the oxidant, the fuel is combusted in a chemical proper ratio, the utilization efficiency of the energy generated by combustion and the fuel is improved, and the energy utilization rate of the solid-liquid mixing engine is obviously improved; moreover, because the solid fuel is combusted in a chemical proper ratio, the consumption of the solid fuel can be reduced, the condition that the fuel allowance is large after the engine works 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. Further, the air chambers 92 of the oxidizer tank 6 and the solid fuel tank 9 are connected to the gas tank 5 via the first pipe 7 and the second pipe 10, respectively, so that the adjustment of the amount of ejected oxidizer and the amount of ejected solid fuel can be synchronously performed by the gas tank 5, and the solid fuel and the oxidizer in the adjustment process are always in a chemically appropriate ratio.
In addition, in order to prove the technical effects obtained by the invention, the inventor compares the solid-liquid mixing engine of the invention with the traditional solid-liquid mixing engine by the following experiments:
if the total flight time of the planned trajectory of the aircraft is 55s, the aircraft works for 40s under the condition of basic thrust 240000N, and the regulation ratio is 4: 1, working for 15s under the condition of a thrust 960000N, and the total impact reaches 24000kN & s. If a conventional solid-liquid hybrid engine is used, the fuel is HTPB and the oxidant is N2O, design point is oxygen-fuel ratio 3: 1, the specific impulse of the engine at design point was 2400N · s/kg, and after deviation from design point the combustion surface recession rate of the solid fuel charge could not be increased due to increased oxidizer flow, so that the ratio of the specific impulse of the engine at design point was 6: the fuel works under the oxygen-fuel ratio of about 1, the specific impulse is only about 1600 N.s/kg, and the total mass of the solid fuel and the oxidant is 13 tons.
If the solid-liquid mixing engine is used, the paraffin blocks are used as solid fuel, and the oxidant is N2And O, assuming that 500kg of the three-component propellant containing the hydroxyl groups is used for boosting for 5s, 1200kN & s total thrust can be generated, the melting point of paraffin is 70 ℃, the paraffin at the front end is melted into liquid after ignition, and after the three-component propellant containing the hydroxyl groups is combusted, the solid-liquid mixed engine is started (as shown in figure 2), and the oxygen-fuel ratio is 3: the theoretical specific impulse of 1 is about 2400N · s/kg. Increase oxidant flow when needing to carry out thrust adjustment, the combustion chamber is burnt and is become more violent, makes fuel injector receive thermal feedback also more violent to make melting speed of paraffin become fast, the flow of paraffin liquid also increases simultaneously, thereby makes the engine work 3 all the time: 1, except the impulse of 1200kN & s generated by the three-component propellant of hydroxyl group, the impulse of 22800kN & s is also needed, so the total mass of the solid fuel and the oxidant is 9.5 tons, and the total mass of the three-component propellant of hydroxyl group, the solid fuel and the oxidant is 10 tons, therefore, the total weight of the energy substances of the solid-liquid mixed engine using the invention can be saved by 23 percent compared with the total weight of the energy substances of the traditional solid-liquid mixed engine.
The embodiment of the invention also provides an aircraft which comprises the solid-liquid hybrid engine of the embodiment. According to the aircraft provided by the embodiment of the invention, by arranging the solid-liquid mixing engine, the solid-liquid mixing engine ingeniously utilizes the combustion chamber thermal feedback principle to realize accurate adjustment of the flow of the solid fuel, so that the supply quantity of the solid fuel sprayed by the fuel nozzle and the supply quantity of the oxidant are always in a chemically appropriate ratio, the utilization efficiency of energy and fuel generated by combustion is improved, the energy utilization rate of the solid-liquid mixing engine is obviously improved, the consumption of the solid fuel can be reduced, the energy waste of the engine is avoided, the overall weight of the solid-liquid mixing engine can be reduced, and the overall weight and the production cost of the aircraft can be reduced.
The solid-liquid mixing engine provided by the embodiment of the invention is provided with a gas storage tank, an oxidant storage tank, a solid fuel storage tank, a plurality of oxidant nozzles and a plurality of fuel nozzles, wherein the oxidant storage tank is connected with the gas storage tank through a first pipeline, an extrusion plate for dividing an inner cavity into a fuel cavity and an air cavity is movably arranged in the solid fuel storage tank, and the air cavity of the solid fuel storage tank is connected with the gas storage tank through a second pipeline. When the solid-liquid mixing engine works, heat generated in the combustion chamber is used for carrying out heat feedback on the fuel nozzle, so that solid fuel close to the fuel nozzle in the solid fuel storage tank is continuously heated and melted and is sprayed out from the fuel nozzle to the combustion chamber under the extrusion action of the extrusion plate, the heat feedback principle of the combustion chamber is ingeniously used for realizing the accurate adjustment of the flow of the solid fuel, and the solid fuel sprayed out from the fuel nozzle and the supply quantity of an oxidant are always in a chemical proper ratio, so that the combustion rate of the solid fuel is matched with the supply quantity of the oxidant, the fuel is combusted in the chemical proper ratio, the utilization efficiency of energy generated by combustion and the fuel is improved, and the energy utilization rate of the solid-liquid mixing engine is obviously improved; moreover, because the solid fuel is combusted in a chemical proper ratio, the consumption of the solid fuel can be reduced, the condition that the fuel allowance is large after the engine works is avoided, the waste of the fuel is reduced, the whole weight of the solid-liquid mixed engine can be reduced, and the waste of energy generated by the fuel is avoided.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalents 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 housing;
a nozzle connected to the housing;
the combustion chamber is arranged in the shell and is communicated with the spray pipe;
a propellant disposed within the combustion chamber;
a gas storage tank which is arranged in the shell and stores compressed gas;
the oxidant storage tank is arranged in the shell and stores an oxidant, and the oxidant storage tank is connected with the gas storage tank through a first pipeline;
a plurality of oxidizer nozzles distributed in the combustion chamber and connected to the oxidizer tank;
the solid fuel storage box is arranged on one side of the combustion chamber and provided with an inner cavity, an extrusion plate which divides the inner cavity into a fuel cavity and an air cavity is movably arranged in the solid fuel storage box, the fuel cavity is provided with solid fuel and is arranged close to the combustion chamber, and the air cavity is connected with the gas storage box through a second pipeline;
And the fuel nozzles are distributed on one side of the solid fuel storage tank close to the combustion chamber in an array manner and are communicated with the fuel cavity.
2. A solid-liquid mixing engine according to claim 1, characterized in that a plurality of said oxidant nozzles are symmetrically arranged on opposite sides of a plurality of said fuel nozzles, and a plurality of said oxidant nozzles are arranged towards the center of said combustion chamber.
3. A solid-liquid hybrid engine according to claim 1, characterized in that a plurality of said oxidant nozzles are connected to said oxidant tank by a third line.
4. A solid-liquid hybrid engine according to claim 1, characterized in that the compressed gas is carbon dioxide, nitrogen, helium or air.
5. A solid-liquid hybrid engine according to claim 1, characterized in that the oxidant is gaseous oxygen, liquid oxygen, nitrous oxide, nitrous tetraoxide or carbon dioxide.
6. A solid-liquid hybrid engine according to claim 1, characterized in that the solid fuel is a metallic or non-metallic block.
7. A solid-liquid hybrid engine according to claim 6, characterized in that the metal block is an aluminum block, a magnesium block, an iron block or a zirconium block.
8. A solid-liquid hybrid engine according to claim 6, characterized in that the non-metallic block is a paraffin block, a rubber block, a plastic block or a boron block.
9. A solid-liquid hybrid engine according to claim 1, characterized in that the propellant is a butylated hydroxytrigel propellant.
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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| CN202111415892.8A CN114109654B (en) | 2021-11-25 | 2021-11-25 | Solid-liquid mixed engine and aircraft |
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| US5394690A (en) * | 1993-09-20 | 1995-03-07 | The United States Of America As Represented By The Secretary Of The Army | Constant pressure, variable thrust bipropellant engine |
| KR20110082309A (en) * | 2010-01-11 | 2011-07-19 | 한국과학기술원 | Hybrid rocket by using catalytic decomposition of oxidizer |
| CN102400814B (en) * | 2011-10-27 | 2013-09-18 | 北京航空航天大学 | Solid-liquid hybrid rocket ramjet for test |
| CN105156231A (en) * | 2015-09-10 | 2015-12-16 | 中国航天科技集团公司第四研究院第四十一研究所 | Gas self-pressurization hybrid rocket engine |
| CN113202655B (en) * | 2021-06-07 | 2022-05-24 | 北京理工大学 | Solid-liquid stamping combined engine |
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