Oblique detonation engine with water as coolant and propellant and aircraft

Abstract

The invention discloses an oblique detonation engine with water as a coolant and a propellant and an aircraft, and relates to the field of hypersonic aircraft design. Comprising a hypersonic aircraft body, a cooling system, a hydrogen preparation device, an air inlet channel, an injection structure, a combustion chamber and an exhaust nozzle. The aircraft is cooperatively operated by a cooling system, a hydrogen production system and a propelling system, liquid water absorbs heat in a circulation pipeline of the cooling system on the surface of the aircraft during flight, cooled high-temperature water enters the hydrogen production system, and hydrogen and oxygen are prepared and stored by utilizing an electrolysis or thermochemical circulation decomposition technology. After hydrogen and air in the air inlet channel are mixed, the hydrogen enters the combustion chamber after the equivalent ratio is precisely regulated and controlled through the injection structure, oblique detonation waves are generated through wedge surface induction to release energy, and gas generated through combustion expands at the exhaust nozzle to generate thrust. The problems of thermal protection and hydrogen fuel carrying and storage of the hypersonic flight vehicle are effectively solved, efficient utilization of energy is achieved, the advantages of being excellent in cooling performance, environmentally friendly and the like are achieved, and a feasible scheme is provided for oblique detonation flight vehicle engineering application.

Description

Technical Field

[0001] The present invention relates to the field of hypersonic aircraft design, and in particular to an oblique detonation engine and an aircraft using water as a coolant and a propellant. Background Art

[0002] Hypersonic vehicles will play an important strategic role in the future military, scientific research and economy due to their extremely high speed advantage. However, their extremely high speed also brings a series of technical problems, of which thermal protection and propulsion are two main aspects.

[0003] In terms of thermal protection, hypersonic vehicles bring huge aerodynamic heat due to their extremely high speed, so effective methods of thermal protection are needed. The current mainstream thermal protection methods can be divided into two categories: active protection and passive protection (Xiao Hongyu, Gao Feng, Li Ning. Application and development of regenerative cooling technology in scramjet engines [J]. Aerospace Missile, 2013 (08): 78-81). Passive protection is to use ablation-resistant materials to provide thermal protection for aircraft. According to the properties of the materials, there are two types: heat-insulating materials and heat-absorbing materials. Active protection is to reduce the temperature of the aircraft surface by actively introducing cooling media such as gas or liquid through heat absorption. Compared with passive protection, the outstanding advantages of active protection are good cooling effect and sustainable cycle, so it has received widespread attention.

[0004] In terms of propulsion technology, traditional engines based on deflagration combustion cannot adapt to high Mach number working conditions. However, due to its higher combustion efficiency and adaptability to high Mach numbers, detonation combustion is a good choice for hypersonic vehicle propulsion technology (Wang Bing, Xie Qiaofeng, Wen Haocheng, et al. Research Progress of Detonation Engines [J]. Propulsion Technology, 2021, 42(04): 721-737). There are many choices for propellants for detonation combustion, including solid aluminum powder, liquid kerosene, and gaseous hydrogen. Among them, gaseous fuel can better adapt to the working conditions of the engine with its lower ignition temperature. However, due to the flammable and explosive properties of hydrogen fuel, if liquid hydrogen fuel is carried directly, it is necessary to maintain an extreme environment of low temperature and high pressure at all times during storage, which limits the use of hydrogen fuel in aircraft. Summary of the invention

[0005] The purpose of the present invention is to provide an oblique detonation engine and an aircraft using water as a coolant and propellant. On the one hand, the solution uses water as a coolant to enhance the cooling performance of the aircraft; on the other hand, the hydrogen produced at high temperature can be used as a fuel for the oblique detonation engine, solving the problem of carrying and storing hydrogen in the detonation engine, achieving efficient use of energy, and improving the overall performance and sustainability of the aircraft.

[0006] To achieve the above objectives, the present invention adopts the following technical solutions.

[0007] An oblique detonation engine and aircraft using water as a coolant and propellant, comprising a hypersonic aircraft body, a cooling system, a hydrogen production device, an air inlet, an injection structure, a combustion chamber and a tail nozzle;

[0008] The hypersonic vehicle body, as the main structure of the vehicle, is used to carry various components of the vehicle and provide lift;

[0009] The cooling system includes a circulation pipeline arranged on the surface of the aircraft. The cooling system is evenly distributed on the surface of the aircraft, especially on the parts that are subjected to strong heat. Liquid water is introduced and flows in the circulation pipeline of the cooling system to absorb the heat generated by the aircraft, thereby protecting the aircraft structure from being damaged by high temperature.

[0010] The hydrogen production device is used to receive the high-temperature water flowing out of the cooling system, decompose the water through the reaction device to produce hydrogen and store it as fuel for the aircraft;

[0011] The air inlet is arranged at the front end of the aircraft, and is used to decelerate, pressurize and increase the temperature of the airflow before it enters the combustion chamber, so that the air and fuel are more easily burned after being mixed, thereby improving the combustion efficiency;

[0012] The injection structure is provided with an injection hole, through which the fuel (hydrogen) produced and stored by the hydrogen production device is sprayed from the storage location, mixed with the air introduced from the intake duct, and then enters the combustion chamber for combustion;

[0013] The combustion chamber is used for detonation combustion of fuel (hydrogen) and air after mixing, so as to release chemical energy and generate thrust;

[0014] The tail nozzle is used to expand the high-temperature and high-pressure gas generated by the combustion chamber, further converting the internal energy into kinetic energy, generating thrust, and driving the aircraft to achieve hypersonic cruise.

[0015] Furthermore, the circulating pipeline of the cooling system is made of high temperature resistant and corrosion resistant alloy material.

[0016] Furthermore, the cooling system is equipped with an efficient heat exchanger that can quickly transfer the absorbed heat to liquid water, thereby improving the cooling efficiency.

[0017] Furthermore, the hydrogen production device includes a reaction device, a catalyst integrated module, a pressure and temperature sensor, and a gas separation and storage interface;

[0018] The reaction device adopts advanced electrolysis technology or thermochemical cycle decomposition technology. Under high temperature conditions, the high-temperature water flowing out of the cooling system is decomposed into hydrogen and oxygen; the reaction device is provided with a reaction chamber inside, which can provide suitable space and conditions for the water decomposition reaction and ensure that the reaction is fully carried out.

[0019] The catalyst integration module is used to integrate efficient catalysts, which are evenly distributed inside the reaction device and fully contact with water to promote the reaction, thereby reducing the activation energy of the water decomposition reaction, accelerating the reaction rate, and improving the hydrogen production efficiency;

[0020] The pressure and temperature sensors are distributed at key locations of the reaction device using high-precision pressure and temperature sensors to monitor the pressure and temperature changes during the reaction in real time. Once the pressure or temperature exceeds the set range, the system will automatically adjust the reaction conditions to ensure the safety and stability of the hydrogen production process.

[0021] The gas separation and storage interface, the hydrogen and oxygen generated by the reaction are separated by a special gas separation device, and then connected to their respective storage devices (hydrogen is stored in the hydrogen storage device, and oxygen is stored in the oxygen storage device) through corresponding pipelines, so as to achieve safe storage and subsequent use of the gas.

[0022] Furthermore, the intake duct adopts a variable geometry intake duct design, which can automatically adjust the shape and size of the intake duct according to the changes in flight speed and altitude, and slow down, pressurize and increase the temperature of the incoming airflow. The interior of the intake duct adopts a special flow channel design and thermal insulation materials to reduce the energy loss and heat leakage of the airflow, making it easier for the air entering the combustion chamber to burn after mixing with the fuel, thereby improving combustion efficiency.

[0023] Furthermore, the injection structure adopts a multi-nozzle, multi-angle design to achieve uniform distribution and rapid mixing of hydrogen. And according to the design requirements of the aircraft, the equivalent ratio of hydrogen and air can be adjusted through a precise flow control system, and the oxygen generated by the hydrogen production system and stored in the device can also be injected into the combustion chamber, further optimizing the combustion process and improving combustion stability and thrust performance.

[0024] Furthermore, the combustion chamber is provided with a wedge surface, and the hydrogen and air / oxygen mixed gas passes through the wedge surface at a very high speed, generating an oblique detonation wave. The combustion chamber is made of high-temperature resistant and high-strength ceramic-based composite materials, and a special flame stabilizer and spoiler structure are designed inside to promote the rapid combustion and energy release of the mixed gas, and efficiently release the chemical energy of the fuel and convert it into thrust to propel the aircraft forward.

[0025] Furthermore, the tail nozzle adopts a convergent-divergent design, which automatically adjusts the expansion ratio of the nozzle according to the flight status and needs of the aircraft to adapt to different flight conditions and improve thrust efficiency.

[0026] The working principle of the present invention is:

[0027] During flight, the liquid water carried by the aircraft absorbs the heat generated by the high temperature on the surface of the aircraft through the cooling system; the high-temperature water flows into the hydrogen production system, hydrogen is produced by water decomposition, and the obtained hydrogen and oxygen are stored separately; the stored hydrogen is mixed with the air in the air inlet through the injection device, and the equivalence ratio is adjusted according to the design requirements of the aircraft. The mixed gas flows into the combustion chamber, generating an oblique detonation wave under the induction of the wedge surface; the gas in the combustion chamber enters the tail nozzle and continues to expand, further generating thrust, which propels the aircraft to perform hypersonic cruise.

[0028] Compared with the prior art, the advantages of the present invention are as follows:

[0029] The hypersonic aircraft obtained by utilizing this design scheme has the characteristics of both safety and high performance. Using water as a coolant not only solves the problem of heat reduction in hypersonic aircraft, but also effectively improves the cooling performance of the aircraft. At the same time, the water after the aircraft is cooled is used to produce hydrogen, which provides the fuel required by the oblique detonation engine. There is no need to carry additional hydrogen as fuel, which solves the problem that hydrogen is difficult to carry and store. By rationally designing the aircraft scheme and using water for aircraft cooling and hydrogen production, the present invention enhances the cooling performance of the aircraft while also solving the problem of carrying and storing hydrogen, converting harmful aerodynamic heat into the energy required for decomposition and hydrogen production, achieving effective energy recovery and utilization, and improving the energy efficiency of the aircraft. It provides a practical solution for the engineering application of oblique detonation aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic diagram of the overall structure of the hypersonic aircraft of the present invention.

[0031] Figure 2 It is a schematic diagram of the hydrogen production and combustion process of the present invention.

[0032] Figure 3 It is a cloud diagram of the hydrogen content of the oblique detonation wave flow field of the present invention.

[0033] Figure 1 The marks in the figure are: A represents the main body of the aircraft, B represents the cooling system of the aircraft, C represents the hydrogen production device, D represents the air inlet, E represents the injection structure, F represents the combustion chamber, and G represents the tail nozzle.

[0034] Figure 2The marks in the figure are: 1 represents a device for storing liquid water, 2 represents a surface of the aircraft body, 3 represents a hydrogen production device, 4 represents a hydrogen storage device, 5 represents an oxygen storage device, 6 represents a wedge surface of the oblique detonation combustion chamber, and 7 represents a pipeline for gas transmission.

[0035] Figure 3 The markings in the figure are: Region I is the fuel after hydrogen is mixed with air / oxygen, Region II is the gas after the fuel is burned, and Mark III is the oblique detonation wave generated by the mixed gas passing through the wedge surface. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the following embodiments will further illustrate the present invention in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0037] An oblique detonation engine and aircraft using water as a coolant and propellant, including a cooling system, a hydrogen production system and a propulsion system; in the cooling system, in the flight state, liquid water carried by the aircraft passes through a circulation pipeline arranged on the surface of the aircraft, and absorbs heat generated by the high temperature on the surface of the aircraft in the process; then, the high-temperature water flows into the hydrogen production system, hydrogen is produced by water decomposition, and the obtained hydrogen and oxygen are stored separately; then, the stored hydrogen is mixed with the air of the air inlet through an injection device, and the equivalence ratio is adjusted according to the design requirements of the aircraft. The mixed gas flows into the combustion chamber, and an oblique detonation wave is generated under the induction of the wedge surface. The gas in the combustion chamber then enters the tail nozzle to continue to expand, further generating thrust, and driving the aircraft to perform hypersonic cruise.

[0038] like Figure 1 As shown, the oblique detonation engine and hypersonic aircraft design of the present invention include main structures such as an aircraft body A, a cooling system B, a hydrogen production device C, an air inlet D, an injection structure E, a combustion chamber F and a tail nozzle G.

[0039] The aircraft body A is the main structure of the aircraft, which is used to carry various components of the aircraft and provide lift.

[0040] The cooling system B includes a circulation pipeline arranged on the surface of the aircraft. The cooling system is evenly distributed on the surface of the aircraft, especially in the parts that are subjected to strong heat. By introducing liquid water, the liquid water flows in the circulation pipeline of the cooling system to absorb the heat generated by the aircraft, thereby protecting the aircraft structure from being damaged by high temperature.

[0041] The hydrogen production device C is used to receive the high-temperature water flowing out of the cooling system, decompose the water through the reaction device to produce hydrogen and store it as fuel for the aircraft.

[0042] The air inlet D is located at the front end of the aircraft and is used to slow down, pressurize and heat the airflow before it enters the combustion chamber, making it easier for the air and fuel to burn after mixing, thereby improving combustion efficiency.

[0043] The injection structure E is provided with an injection hole, through which the fuel (hydrogen) produced and stored by the hydrogen production device is sprayed from the storage location, mixed with the air introduced by the intake duct, and then enters the combustion chamber for combustion.

[0044] Combustion chamber F is used for the fuel (hydrogen) and air to mix and then undergo detonation combustion, releasing chemical energy and generating thrust.

[0045] The tail nozzle G is used to expand the high-temperature and high-pressure gas generated by the combustion chamber, further converting the internal energy into kinetic energy, generating thrust, and driving the aircraft to achieve hypersonic cruise.

[0046] Before the aircraft takes off, liquid water is stored in Figure 2 In the structure of the device 1 for storing liquid water shown, the device for storing liquid water can be arranged inside the aircraft. When the aircraft is flying, liquid water flows into the cooling system arranged on the surface of the aircraft through the pipeline structure. Since the intense friction between the surface and the air generates heat when the aircraft is flying at high speed, the liquid water can effectively take away this part of the heat through the flow. This process has two advantages: on the one hand, the heat on the surface of the aircraft is reduced, which effectively reduces the temperature of the surface of the aircraft and ensures the structural safety of the aircraft; on the other hand, the heat of the aircraft increases the temperature of the liquid water, creating suitable thermodynamic conditions for the subsequent water decomposition hydrogen production reaction, which facilitates the hydrogen production reaction.

[0047] The cooling system can be equipped with a circulation pump to ensure that liquid water can flow continuously in the pipeline, and by adjusting the rotation speed of the circulation pump, the flow rate and cooling effect of the liquid water can be accurately controlled to meet the thermal protection requirements under different flight conditions.

[0048] Figure 2 The schematic diagram of the hydrogen production and combustion process of the present invention is given, showing the liquid water storage device, the aircraft body surface, the hydrogen production device, the hydrogen and oxygen storage device, the wedge surface of the oblique detonation combustion chamber, and the gas transmission pipeline and other structures, as well as the process of liquid water producing hydrogen and hydrogen mixed with air / oxygen for combustion. The whole process of fuel production, transmission and combustion can be clearly seen from the figure. After the high-temperature water flows out of the cooling system, it enters Figure 2 In the hydrogen production device 3 shown in the figure, hydrogen and oxygen are produced by decomposing water to produce hydrogen, and the generated hydrogen is stored in a pipeline. Figure 2 In the device 4 shown. At the same time, oxygen is stored in Figure 2 The oxygen storage device 5 is shown. Then, the produced hydrogen is passed through Figure 1The injection structure 5 shown is fully mixed with the air flowing into the air intake duct. In order to meet the requirements of the hydrogen and oxygen mixing equivalence ratio under different flight conditions, the oxygen generated in the hydrogen production system 3 and stored in the oxygen storage device 5 can also be injected into the combustion chamber according to actual conditions. In the combustion chamber of oblique detonation, after hydrogen is mixed with air / oxygen, it passes through the wedge surface at a very high speed to generate an oblique detonation wave. The composition, temperature, pressure and other parameters of the mixed gas are monitored in real time by sensors, and the working state of the injection structure is adjusted to ensure the stability and efficiency of the combustion process.

[0049] The hydrogen content cloud diagram of the oblique detonation wave flow field of the present invention is as follows: Figure 3 As shown in the figure, the oblique detonation wave is a shock wave-induced combustion reaction. During this process, hydrogen burns to produce water that is pollution-free to the environment. At the same time, chemical energy is converted into kinetic energy, generating a portion of thrust. After the combustion chamber, the high-temperature and high-pressure gas generated in the combustion chamber enters the tail nozzle and continues to expand. The expansion process of the gas converts the internal energy into kinetic energy, further generating thrust, and driving the aircraft to perform hypersonic cruise.

[0050] The invention discloses a hypersonic aircraft using water as a coolant and a propellant. The water is used to reduce the surface temperature of the aircraft, and the hydrogen obtained by decomposing the water can also be used as the propellant of the aircraft. While enhancing the cooling performance of the aircraft and improving the structural safety, the problem of the difficulty of carrying and storing hydrogen fuel is solved, and the aircraft is a good design scheme.

[0051] The above embodiments are only preferred embodiments of the present invention and cannot be considered to limit the scope of the present invention. All equivalent changes and improvements made within the scope of the present invention should still fall within the scope of the present invention.

Claims

1. An oblique detonation engine and aircraft using water as a coolant and propellant, characterized in that It includes the hypersonic vehicle body, cooling system, hydrogen production device, air inlet, injection structure, combustion chamber and tail nozzle; The hypersonic vehicle body, as the main structure of the vehicle, is used to carry various components of the vehicle and provide lift; The cooling system includes a circulation pipeline arranged on the surface of the aircraft. The cooling system is evenly distributed on the surface of the aircraft, especially on the parts that are subjected to strong heat. Liquid water is introduced and flows in the circulation pipeline of the cooling system to absorb the heat generated by the aircraft, thereby protecting the aircraft structure from being damaged by high temperature. The hydrogen production device is used to receive the high-temperature water flowing out of the cooling system, decompose the water through the reaction device to produce hydrogen and store it as fuel for the aircraft; The air inlet is arranged at the front end of the aircraft, and is used to decelerate, pressurize and increase the temperature of the airflow before it enters the combustion chamber, so that the air and fuel are more easily burned after being mixed, thereby improving the combustion efficiency; The injection structure is provided with an injection hole, through which the fuel produced and stored by the hydrogen production device is sprayed from the storage location, mixed with the air introduced by the intake duct, and then enters the combustion chamber for combustion; The combustion chamber is used for detonation combustion of fuel and air after mixing, so as to release chemical energy and generate thrust; The tail nozzle is used to expand the high-temperature and high-pressure gas generated by the combustion chamber, further converting the internal energy into kinetic energy, generating thrust, and driving the aircraft to achieve hypersonic cruise.

2. An oblique detonation engine and aircraft using water as a coolant and propellant as claimed in claim 1, characterized in that The cooling system is also equipped with an efficient heat exchanger that can quickly transfer the absorbed heat to liquid water, improving cooling efficiency.

3. An oblique detonation engine and aircraft using water as a coolant and a propellant as claimed in claim 1, characterized in that The hydrogen production device includes a reaction device, a catalyst integrated module, a pressure and temperature sensor, and a gas separation and storage interface; The reaction device adopts advanced electrolysis technology or thermochemical cycle decomposition technology; under high temperature conditions, the high-temperature water flowing out of the cooling system is decomposed into hydrogen and oxygen; a reaction chamber is provided inside the reaction device, which can provide suitable space and conditions for the water decomposition reaction to ensure that the reaction is fully carried out; The catalyst integration module is used to integrate efficient catalysts, which are evenly distributed inside the reaction device and fully contact with water to promote the reaction, thereby reducing the activation energy of the water decomposition reaction, accelerating the reaction rate, and improving the hydrogen production efficiency; The pressure and temperature sensors are distributed at key locations of the reaction device using high-precision pressure and temperature sensors to monitor the pressure and temperature changes during the reaction in real time. Once the pressure or temperature exceeds the set range, the system will automatically adjust the reaction conditions to ensure the safety and stability of the hydrogen production process. The gas separation and storage interface separates the hydrogen and oxygen generated by the reaction through a special gas separation device, and then connects to respective storage devices through corresponding pipelines. Hydrogen is stored in the hydrogen storage device, and oxygen is stored in the oxygen storage device, so as to achieve safe storage and subsequent use of the gas.

4. An oblique detonation engine and aircraft using water as a coolant and a propellant as claimed in claim 1, characterized in that The air intake adopts a variable geometry air intake design, which can automatically adjust the shape and size of the air intake according to changes in flight speed and altitude, and slow down, pressurize and heat the incoming airflow; the interior of the air intake adopts a special flow channel design and thermal insulation materials to reduce energy loss and heat leakage of the airflow, making the air entering the combustion chamber easier to burn after mixing with the fuel, thereby improving combustion efficiency.

5. An oblique detonation engine and aircraft using water as a coolant and a propellant as claimed in claim 1, characterized in that The injection structure adopts a multi-nozzle, multi-angle design, which can achieve uniform distribution and rapid mixing of hydrogen; and according to the design requirements of the aircraft, the equivalence ratio of hydrogen and air can be adjusted through a precise flow control system, and the oxygen generated by the hydrogen production system and stored in the device can also be injected into the combustion chamber, further optimizing the combustion process and improving combustion stability and thrust performance.

6. An oblique detonation engine and aircraft using water as a coolant and a propellant as claimed in claim 1, characterized in that The combustion chamber is provided with a wedge surface, and the hydrogen and air / oxygen mixture passes through the wedge surface at an extremely high speed, generating an oblique detonation wave; the combustion chamber is made of high-temperature resistant, high-strength ceramic-based composite materials, and a special flame stabilizer and spoiler structure are designed inside to promote the rapid combustion and energy release of the mixed gas, and efficiently release the chemical energy of the fuel and convert it into thrust to propel the aircraft forward.

7. An oblique detonation engine and aircraft using water as a coolant and a propellant as claimed in claim 1, characterized in that The tail nozzle adopts a convergent-divergent design, which automatically adjusts the expansion ratio of the nozzle according to the flight status and needs of the aircraft to adapt to different flight conditions and improve thrust efficiency.

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