Fuel supply flow channel, injection device, supply system, engine, aircraft

Abstract

The invention relates to a fuel supply channel, an injection device, a supply system, a continuous rotating detonation engine and an aircraft. The technical problem to be solved is that the diffusion, fragmentation, atomization degree and circumferential distribution uniformity of liquid-phase fuel are poor. The fuel supply channel can have a liquid-phase channel assembly and a gas-phase channel assembly. Multiple liquid-phase channel sub-components include a liquid-phase main channel and a branch channel. The outlet of each liquid-phase branch channel is smaller than the liquid-phase branch channel. The axes of the cylindrical holes of the rear sections of all gas-phase branches uniformly distributed circumferentially converge at one point. The total number of liquid-phase branches is the same as the total number of gas-phase branches and corresponds one to one. The local cylindrical outer wall surface of each liquid-phase branch channel partially extends into the corresponding cylindrical hole of the rear section of the gas-phase branch channel and forms a coaxial relationship. The technical means of arranging a large number of liquid-phase fuel channels uniformly distributed circumferentially and the liquid-phase fuel of each channel is respectively coaxially sprayed with the oxidant to achieve the technical effect of improving the mixing uniformity and circumferential uniformity of the combustible mixture.

Description

Technical Field

[0001] The invention relates to a fuel supply flow channel, a fuel injection device, a fuel supply system, a continuous rotating detonation engine, and an aircraft using the continuous rotating detonation engine. Background Art

[0002] The most relevant comparative documents to the present invention are: Document 1: A rotating detonation engine experimental device, Chinese invention patent, application number 201510055761.1; Document 2: Bykovskii, FA, Zhdan, SA & Vedernikov, EF Continuous Detonation of the Liquid Kerosene—Air Mixture with Addition of Hydrogen or Syngas [J], Combustion, Explosion, and Shock Waves, 2019, 55 (5): 589-598; Document 3: Jan Kindracki, Experimental research on rotating detonation in liquid fuel-gaseous air mixtures [J], Aerospace Science and Technology, 2015, 43: 445-453. In the prior art, the main purpose is to improve the mixing uniformity and circumferential uniformity of the combustible mixture; the main technical feature is to arrange 4 to 8 cylindrical fuel channels circumferentially on the outer wall of the cylindrical combustion chamber, and rely on the high-speed flowing oxidant to collide with the fuel at the outlet of each cylindrical fuel channel; the main effect is that the limited area near the collision point of the fuel and the oxidant can form local diffusion of the fuel and local mixing with the oxidant. In the process of realizing the present invention, the inventor found that there are at least the following problems in the prior art: when liquid fuel is used, that is, the fuel exists in the form of liquid phase upstream of the channel outlet, the diffusion, fragmentation and atomization of the fuel downstream of the channel outlet are poor, and the circumferential distribution uniformity of the fuel is poor. Summary of the invention

[0003] The technical problem to be solved by the present invention is that the diffusion, fragmentation, atomization degree and circumferential distribution uniformity of liquid fuel are poor.

[0004] In order to solve the above technical problems, the specific technical solutions adopted by the present invention are as follows.

[0005] The fuel supply flow channel involved in the first aspect of the present invention may include a liquid flow channel component and a gas flow channel component. The liquid flow channel component includes two or more liquid flow channel sub-components. Each liquid flow channel sub-component includes a liquid main channel and two or more liquid branch channels.

[0006] Each liquid phase main channel has one or more liquid phase main channel inlets. The outer wall surface of each liquid phase branch channel is partially cylindrical. Each liquid phase branch channel has a liquid phase branch channel outlet. The flow cross-sectional area of ​​each liquid phase branch channel outlet is smaller than the flow cross-sectional area of ​​each liquid phase branch channel. The flow cross-sectional areas of all liquid phase branch channel outlets are equal.

[0007] The gas phase flow channel assembly includes a gas phase main channel and two or more gas phase branch channels. The gas phase main channel has one or more gas phase main channel inlets. Each gas phase branch channel has a gas phase branch channel front section, a gas phase branch channel rear section, and a gas phase branch channel outlet. Each gas phase branch channel rear section is a cylindrical hole. The axes of the cylindrical holes of all gas phase branch channel rear sections meet at one point. All gas phase branch channel rear section cylindrical holes are evenly distributed circumferentially.

[0008] The total number of liquid branch channels is the same as the total number of gas branch channels and corresponds one to one. The total number of liquid branch channel outlets is the same as the total number of gas branch channel outlets and corresponds one to one. The total number of liquid branch channel outlets is greater than or equal to 12.

[0009] The diameter of the local cylindrical outer wall of each liquid phase branch channel is smaller than the diameter of the corresponding rear cylindrical hole of the gas phase branch channel. The local cylindrical outer wall of each liquid phase branch channel partially extends into the corresponding rear cylindrical hole of the gas phase branch channel. The axis of the local cylindrical outer wall of each liquid phase branch channel forms a coaxial relationship with the axis of the rear cylindrical hole of the corresponding gas phase branch channel.

[0010] The fuel injection device involved in the second aspect of the present invention may include a fuel flow on-off actuator and the fuel supply flow channel of the first aspect. The number of the fuel flow on-off actuator is the same as the total number of liquid phase main channel inlets and corresponds one to one, and each corresponding fuel flow on-off actuator and liquid phase main channel inlet have a high hydraulic seal fit with each other.

[0011] The fuel supply system involved in the third aspect of the present invention may include a fuel storage component, a fuel pressurizing component, and a fuel injection component. The fuel storage component and the fuel pressurizing component are connected by a pipeline, and the fuel pressurizing component and the fuel injection component are connected by a pipeline. Among them, the fuel injection component is the fuel injection device of the second aspect mentioned above.

[0012] The continuous rotating detonation engine involved in the fourth aspect of the present invention may have a fuel supply component, a combustion chamber component, and an ignition component. The fuel supply component and the combustion chamber component are connected by a pipeline, and the ignition component extends into the interior of the combustion chamber component through a hole in the outer wall of the shell of the combustion chamber component. Among them, the fuel supply component is the fuel supply system of the third aspect mentioned above. The fuel supply flow channel and the outer wall of the shell of the combustion chamber component are connected, fastened and sealed under high pressure by a connector.

[0013] The aircraft involved in the fifth aspect of the present invention may include an engine component, a control component, and a load component. The engine component and the control component are connected by a communication data line, and the load component includes an aircraft shell and a filling material, and the filling material, the control component, and the engine component are arranged in the upper, middle, and lower positions inside the aircraft shell in sequence. Among them, the engine component is the continuous rotating detonation engine of the fourth aspect mentioned above.

[0014] One of the above technical solutions has the following advantages or beneficial effects:

[0015] The fuel supply flow channel involved in the first aspect of the present invention adopts a technical means of arranging a large number of liquid fuel channels that are evenly distributed in the circumference, and the liquid fuel in each channel forms a coaxial injection with the oxidant, so it overcomes the technical problem of "poor diffusion, fragmentation, atomization degree and circumferential distribution uniformity of liquid fuel", thereby achieving the technical effect of improving the mixing uniformity and circumferential uniformity of the combustible mixture. In terms of specific quantification of this effect, the average diameter index of the droplets of liquid aviation fuel under the steady flow condition of 60MPa pressure difference can be improved to 45 microns, and the circumferential uniformity can be improved to more than 1.5 times.

[0016] The fuel injection device according to the second aspect of the present invention has the fuel supply flow path of the first aspect, so it has the technical effect of the fuel supply flow path. Moreover, the Sauter mean diameter index of the droplets of liquid aviation fuel under the single injection flow condition of 180 MPa pressure difference can be improved to 25 microns.

[0017] The fuel supply system involved in the third aspect of the present invention has the fuel supply flow path of the first aspect, so it has the technical effect of the fuel supply flow path. In addition, the average diameter index of the droplets of liquid aviation fuel under the single or multiple or steady injection flow conditions of 180MPa pressure difference can be improved to 25 microns.

[0018] The continuous rotating detonation engine involved in the fourth aspect of the present invention has the fuel supply flow channel of the first aspect, and has the technical effect of the fuel supply flow channel, wherein the improvement of the mixing uniformity of the combustible mixture can improve the combustion efficiency, wherein the improvement of the circumferential uniformity of the combustible mixture can improve the combustion stability. Moreover, it overcomes the deficiency of the prior art that the liquid phase fuel needs to be ignited with the aid of gas phase fuel, and achieves the technical effect of forming continuous rotating detonation combustion with only liquid phase fuel.

[0019] The aircraft involved in the fifth aspect of the present invention has the fuel supply flow channel of the first aspect, so it has the technical effect of the fuel supply flow channel, wherein the improvement of the mixing uniformity of the combustible mixture can improve the thrust and the Mach number, wherein the improvement of the circumferential uniformity of the combustible mixture can improve the flight stability. Moreover, it overcomes the complexity of the aircraft using the liquid-phase fuel continuous rotating detonation engine in the prior art that needs to be equipped with an auxiliary gas-phase fuel system, and achieves the technical effect of improving the working reliability and volume energy density. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the relationship between embodiments of several aspects of the present invention.

[0021] Figure 2A It is a schematic structural diagram (section A) of an embodiment of a fuel supply channel according to the present invention.

[0022] Figure 2B It is a schematic structural diagram of an embodiment of a fuel supply channel according to the present invention (partial details of section A).

[0023] Figure 3 It is a schematic structural diagram of an embodiment of a fuel supply channel according to the present invention (partial details of section B).

[0024] Figure 4 It is a schematic diagram of the sealing structure of an embodiment of the fuel injection device according to the present invention (section A).

[0025] Figure 5 The invention discloses a schematic diagram of a connecting member structure of an embodiment of a continuous rotating detonation engine.

[0026] Explanation of symbols

[0027] 100 fuel supply flow channel

[0028] 120 Liquid phase flow channel sub-components

[0029] 130 Liquid Phase Channel

[0030] 132 Liquid phase channel entrance

[0031] 140 Liquid phase branch

[0032] 142 Partial cylindrical outer wall

[0033] 144 Liquid phase branch outlet

[0034] 160 Gas Correlation Channel

[0035] 170 Gas Phase Branch

[0036] 172 Gas phase branch front

[0037] 174 Gas phase branch posterior segment

[0038] 176 Gas phase branch outlet

[0039] 178 Gas phase branch rear section cylindrical hole

[0040] 190 Fuel flow on-off actuator

[0041] 200 fuel injection device

[0042] 210 inner cone-spherical crown seal fit A

[0043] 300 fuel supply system

[0044] 320 fuel storage components

[0045] 340 fuel booster parts

[0046] 360 fuel injection parts

[0047] 400 continuous rotating detonation engine

[0048] 420 fuel supply components

[0049] 440 Combustion chamber parts

[0050] 442 Shell outer wall

[0051] 444 screw fit A

[0052] 446 Metal Pad A

[0053] 460 Detonation Components

[0054] 500 aircraft

[0055] 520 engine parts

[0056] 540 control components

[0057] 560 load components DETAILED DESCRIPTION

[0058] like Figure 1 As shown, the relationship between the embodiments of several aspects of the present invention is illustrated, and the embodiments of several aspects of the present invention are arranged in series.

[0059] like Figure 2A and relevant local details Figure 2B As shown, an embodiment of the fuel supply flow channel 100 involved in the first aspect of the present invention may include a liquid phase flow channel component and a gas phase flow channel component.

[0060] The liquid phase flow channel assembly includes two or more liquid phase flow channel sub-components 120. Each liquid phase flow channel sub-component 120 includes a liquid phase main channel 130 and two or more liquid phase branch channels 140.

[0061] Each liquid phase channel 130 has one or more liquid phase channel inlets 132. The liquid phase channels 130 may be: the center line shape of all liquid phase channels 130 is arc-shaped, the center line arc radius of all liquid phase channels 130 is equal, the sum of the arc radii of the center line arcs of all liquid phase channels 130 is less than or equal to 2π, all liquid phase channels 130 are evenly distributed in the circumferential direction, the flow cross-sectional shape of each liquid phase channel 130 is circular, and the flow cross-sectional area of ​​each liquid phase channel 130 is less than or equal to 4 square millimeters.

[0062] The flow cross-sectional shape of each liquid phase branch channel 140 can be circular and the flow cross-sectional area is less than or equal to 2 square millimeters. The outer wall surface of each liquid phase branch channel 140 is partially cylindrical, that is, the partially cylindrical outer wall surface 142. Each liquid phase branch channel 140 has a liquid phase branch channel outlet 144. The flow cross-sectional area of ​​each liquid phase branch channel outlet 144 is smaller than the flow cross-sectional area of ​​each liquid phase branch channel 140. The flow cross-sectional areas of all liquid phase branch channel outlets 144 are equal, and the flow cross-sectional area of ​​each liquid phase branch channel outlet 144 is less than or equal to 0.2 square millimeters. The flow cross-sectional shape of each liquid phase branch channel outlet 144 can be circular.

[0063] like Figure 3 As shown, the gas phase flow channel assembly includes a gas phase main channel 160 and two or more gas phase branch channels 170. The gas phase main channel 160 has one or more gas phase main channel inlets. Each gas phase branch channel 170 has a gas phase branch channel front section 172, a gas phase branch channel rear section 174, and a gas phase branch channel outlet 176. The flow cross-section shape of each gas phase branch channel front section 172 can be circular.

[0064] Each gas phase branch channel rear section 174 is a cylindrical hole, namely, a gas phase branch channel rear section cylindrical hole 178. The axes of all gas phase branch channel rear section cylindrical holes 178 meet at one point. All gas phase branch channel rear section cylindrical holes 178 are evenly distributed in the circumferential direction.

[0065] The total number of liquid branch channels 140 is the same as and corresponds to the total number of gas branch channels 170. The total number of liquid branch channel outlets 144 is the same as and corresponds to the total number of gas branch channel outlets 176. The total number of liquid branch channel outlets 144 is greater than or equal to 12, and further, the total number of liquid branch channel outlets 144 can be greater than or equal to 30.

[0066] The diameter of the local cylindrical outer wall surface 142 of each liquid phase branch channel 140 is smaller than the diameter of the corresponding gas phase branch channel rear section cylindrical hole 178. Further, the difference between the diameter of the local cylindrical outer wall surface 142 of each liquid phase branch channel 140 and the diameter of the corresponding gas phase branch channel rear section cylindrical hole 178 can be less than or equal to 4 mm. The local cylindrical outer wall surface 142 of each liquid phase branch channel 140 partially extends into the corresponding gas phase branch channel rear section cylindrical hole 178. The axis of the local cylindrical outer wall surface 142 of each liquid phase branch channel 140 forms a coaxial relationship with the axis of the corresponding gas phase branch channel rear section cylindrical hole 178. The geometric center point of each corresponding liquid phase branch channel outlet 144 can form a coincidence relationship with the geometric center point of the gas phase branch channel outlet 176.

[0067] The whole set of liquid phase flow channel components can have a structural strength and high hydraulic sealing performance to withstand an internal hydraulic pressure greater than or equal to 30 MPa. Further, the whole set of liquid phase flow channel components can have a structural strength and high hydraulic sealing performance to withstand an internal hydraulic pressure greater than or equal to 180 MPa.

[0068] The technical effect that can be achieved by this embodiment is that a large number of liquid fuel channels are arranged and evenly distributed in the circumference, and the liquid fuel in each channel is sprayed coaxially with the oxidant, so the technical problem of "poor diffusion, fragmentation, atomization and circumferential distribution uniformity of liquid fuel" is overcome, thereby achieving the technical effect of improving the mixing uniformity and circumferential uniformity of the combustible mixture. In terms of specific quantification of this effect, the average diameter index of the droplets of liquid aviation fuel under the steady flow condition of 60MPa pressure difference can be improved to 45 microns, and the circumferential uniformity can be improved to more than 1.5 times.

[0069] like Figure 4As shown, an embodiment of the fuel injection device 200 involved in the second aspect of the present invention may include a fuel flow on-off actuator 190 and an embodiment of the fuel supply flow channel 100 of the first aspect described above. The number of the fuel flow on-off actuator 190 is the same as the total number of the liquid phase main channel inlets 132 and corresponds one to one. Each corresponding fuel flow on-off actuator 190 and the liquid phase main channel inlet 132 have a high hydraulic seal fit with each other, and an embodiment of the seal fit may be an inner cone-spherical crown seal fit A210, and an implementation means of the clamping force provided to the inner cone-spherical crown seal fit A210 may be the thread axial force of the screw. The embodiment of the fuel injection device 200 includes an embodiment of the fuel supply flow channel 100, so it has the technical effect of the embodiment of the fuel supply flow channel 100. Moreover, the average diameter index of the droplet Soter under the single injection flow condition of the liquid phase aviation fuel with a pressure difference of 180MPa can be improved to 25 microns.

[0070] An embodiment of the fuel supply system 300 involved in the third aspect of the present invention may include a fuel storage component 320, a fuel pressurization component 340, and a fuel injection component 360. The fuel storage component 320 and the fuel pressurization component 340 are connected by a pipeline, and the fuel pressurization component 340 and the fuel injection component 360 are connected by a pipeline. The pipeline can be a high-pressure oil pipe assembly commonly used in the hydraulic industry. Such a common high-pressure oil pipe assembly can refer to the national mechanical industry standard JB / T12036-2015 when implemented. Among them, the fuel injection component 360 is an embodiment of the fuel injection device 200 of the second aspect mentioned above. The fuel supply system 300 embodiment includes a fuel supply flow channel 100 embodiment, so it has the technical effect of the fuel supply flow channel 100 embodiment. Moreover, the average diameter index of the droplet of liquid aviation fuel under the condition of single or multiple injections or steady flow with a pressure difference of 180MPa can be improved to 25 microns.

[0071] An embodiment of the continuous rotating detonation engine 400 involved in the fourth aspect of the present invention may include a fuel supply component 420, a combustion chamber component 440, and an ignition component 460. The fuel supply component 420 and the combustion chamber component 440 are connected by a pipeline, and the pipeline may be a high-pressure oil pipe assembly commonly used in the hydraulic industry. The ignition component 460 extends into the interior of the combustion chamber component 440 through a hole in the outer wall of the shell of the combustion chamber component 440. Among them, the fuel supply component 420 is an embodiment of the fuel supply system 300 of the third aspect mentioned above. The fuel supply flow channel 100 and the outer wall 442 of the shell of the combustion chamber component 440 are connected, fastened and sealed under high pressure by connecting parts; such as Figure 5 As shown, a fastening embodiment of the connector can be a screw fit A444; Figure 3As shown, a connection and high-pressure sealing embodiment of the connector can be a metal gasket A446. The continuous rotating detonation engine 400 embodiment has a fuel supply channel 100 embodiment, and has the technical effect of the fuel supply channel 100 embodiment, wherein the improvement of the mixing uniformity of the combustible mixture can improve the combustion efficiency, wherein the improvement of the circumferential uniformity of the combustible mixture can improve the combustion stability. Moreover, it overcomes the deficiency of the prior art that the liquid phase fuel needs to be ignited with the aid of gas phase fuel, and achieves the technical effect of forming continuous rotating detonation combustion with only liquid phase fuel.

[0072] An embodiment of the aircraft 500 involved in the fifth aspect of the present invention may include an engine component 520, a control component 540, and a load component 560. The engine component 520 and the control component 540 are connected by a communication data line, and the load component 560 includes an aircraft shell and a filler, and the filler, the control component 540 and the engine component 520 are arranged in the upper, middle and lower positions inside the aircraft shell in sequence. Among them, the engine component 520 is an embodiment of the continuous rotating detonation engine 400 of the fourth aspect mentioned above. The aircraft 500 embodiment is equipped with a fuel supply flow channel 100 embodiment, so it has the technical effect of the fuel supply flow channel 100 embodiment, wherein the improvement of the mixing uniformity of the combustible mixture can improve the thrust and Mach number, wherein the improvement of the circumferential uniformity of the combustible mixture can improve the flight stability. Moreover, it overcomes the complexity of the aircraft using the liquid phase fuel continuous rotating detonation engine in the prior art that needs to be equipped with an auxiliary gas phase fuel system, and achieves the technical effect of improving the working reliability and volume energy density.

Claims

1. A fuel supply channel, characterized in that include: Liquid phase flow channel components and gas phase flow channel components; The liquid phase flow channel assembly includes two or more liquid phase flow channel sub-components, each of which includes a liquid phase main channel and two or more liquid phase branch channels; Each of the liquid phase channels has one or more liquid phase channel inlets; The outer wall of each of the liquid phase branch channels is partially cylindrical, each of the liquid phase branch channels has a liquid phase branch channel outlet, the flow cross-sectional area of ​​each of the liquid phase branch channel outlets is smaller than the flow cross-sectional area of ​​each of the liquid phase branch channels, and the flow cross-sectional areas of all the liquid phase branch channel outlets are equal; The gas phase flow channel component comprises a gas phase main channel and two or more gas phase branch channels, and the gas phase main channel has one or more gas phase main channel inlets; Each of the gas phase branch channels has a gas phase branch channel front section, a gas phase branch channel rear section, and a gas phase branch channel outlet; The rear section of each gas phase branch channel is a cylindrical hole, the axes of all the cylindrical holes of the rear section of the gas phase branch channels intersect at one point, and all the cylindrical holes of the rear section of the gas phase branch channels are evenly distributed circumferentially; The total number of the liquid phase branch channels is the same as the total number of the gas phase branch channels and corresponds one to one, the total number of the liquid phase branch channel outlets is the same as the total number of the gas phase branch channel outlets and corresponds one to one, and the total number of the liquid phase branch channel outlets is greater than or equal to 12; The diameter of the local cylindrical outer wall surface of each of the liquid phase branch channels is smaller than the diameter of the corresponding cylindrical hole of the rear section of the gas phase branch channel, and the local cylindrical outer wall surface of each of the liquid phase branch channels partially extends into the corresponding cylindrical hole of the rear section of the gas phase branch channel. The axis of the local cylindrical outer wall surface of each of the liquid phase branch channels is coaxial with the axis of the cylindrical hole of the rear section of the corresponding gas phase branch channel.

2. The fuel supply channel according to claim 1, characterized in that: The center line shape of the liquid phase dry channel is an arc shape, the center line arc radii of all the liquid phase dry channels are equal, the sum of the center line arc radii of all the liquid phase dry channels is less than or equal to 2π, all the liquid phase dry channels are evenly distributed in the circumferential direction, the flow cross-sectional shape of the liquid phase dry channel is circular, and the flow cross-sectional area of ​​each liquid phase dry channel is less than or equal to 4 square millimeters.

3. The fuel supply channel according to claim 1, characterized in that: The flow cross-sectional shape of each liquid phase branch channel is circular, the flow cross-sectional area of ​​each liquid phase branch channel is less than or equal to 2 square millimeters, the flow cross-sectional area of ​​each liquid phase branch channel outlet is less than or equal to 0.2 square millimeters, and the flow cross-sectional shape of each liquid phase branch channel outlet is circular.

4. The fuel supply channel according to claim 1, characterized in that: The flow cross-section shape of the front section of each gas phase branch channel is circular.

5. The fuel supply channel according to claim 1, characterized in that: The total number of the liquid phase branch outlets is greater than or equal to 30.

6. The fuel supply channel according to claim 1, characterized in that: The difference between the diameter of the local cylindrical outer wall of each liquid phase branch channel and the diameter of the corresponding cylindrical hole in the rear section of the gas phase branch channel is less than or equal to 4 mm, and the geometric center point of each corresponding liquid phase branch channel outlet coincides with the geometric center point of the gas phase branch channel outlet. The entire liquid phase flow channel assembly has a structural strength capable of withstanding an internal hydraulic pressure greater than or equal to 30 MPa and high hydraulic sealing.

7. A fuel injection device, characterized in that: It is equipped with fuel flow on-off actuators and the fuel supply flow channel as described in claim 1; the number of the fuel flow on-off actuators is the same as the total number of the liquid phase main channel inlets and corresponds one to one, and each corresponding fuel flow on-off actuator and liquid phase main channel inlet has a high hydraulic sealing fit with each other.

8. A fuel supply system, comprising a fuel storage component, a fuel pressurizing component, and a fuel injection component; the fuel storage component and the fuel pressurizing component are connected by a pipeline, and the fuel pressurizing component and the fuel injection component are connected by a pipeline; characterized in that: The fuel injection component is defined as the fuel injection device according to claim 7.

9. A continuous rotating detonation engine, comprising a fuel supply component, a combustion chamber component, and an ignition component; the fuel supply component and the combustion chamber component are connected by a pipeline, and the ignition component extends into the interior of the combustion chamber component through a hole on the outer wall of the shell of the combustion chamber component; characterized in that: The fuel supply component is defined as the fuel supply system according to claim 8, and the fuel supply flow channel and the outer wall surface of the shell of the combustion chamber component are connected, fastened and sealed under high pressure by connecting parts.

10. An aircraft, comprising an engine component, a control component, and a load component; the engine component and the control component are connected by a communication data line, the load component comprises an aircraft shell and a filling, the filling, the control component, and the engine component are sequentially arranged at the upper, middle, and lower positions inside the aircraft shell; characterized in that: The engine component is defined as the continuously rotating detonation engine as claimed in claim 9.

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