CN220434898U - Rotary detonation engine device and aircraft - Google Patents

Abstract

The utility model discloses a rotary detonation engine device and an aircraft. The rotary knocking engine device comprises a rotary knocking engine body and a solid fuel supply device, wherein the rotary knocking engine body is provided with a combustion chamber; the solid fuel supply device comprises a solid fuel supply module and a fluidization module, wherein the solid fuel supply module is connected with the fluidization module and is used for supplying solid fuel to the fluidization module; the fluidization module is in communication with the combustion chamber and is configured to fluidize the solid fuel into a solid powder and deliver the solid powder to the combustion chamber. The rotary detonation engine device provided by the application has the characteristics of simplifying the structure and the process of the rotary detonation engine device and shortening the launching period of an aircraft under the condition of obtaining higher thrust.

Description

Rotary detonation engine device and aircraft

Technical Field

The present application relates to the field of engines, and more particularly, to a rotary detonation engine device and aircraft.

Background

In nature, two combustion modes of slow combustion and detonation combustion exist, the flame propagation rate of the slow combustion is relatively low, and the combustion modes in power devices such as an internal combustion engine, an aeroengine, a gas turbine and the like are slow combustion. The detonation combustion is characterized in that the upstream of the combustion zone is of a shock wave structure, shock waves are coupled with the combustion zone to propagate, and the propagation speed of flame of the detonation combustion is far higher than that of the slow combustion, and can reach thousands of meters per second. The rotary detonation engine is an engine type created by utilizing the combustion mode of detonation, and detonation waves are spread along the circular axis of the engine to continuously ignite fuel injected into a combustion chamber.

The aerospace field is more and more competitive, and with the continuous and intensive research on hypersonic aircrafts and single-stage in-orbit power systems, novel rotary detonation engine technologies are rapidly developed. The rotary detonation engine has fundamental difference with the traditional aero-engine, rocket engine and the like, the rotary detonation engine can generate larger thrust under the low pressure ratio, the design of a combustion chamber is smaller, and the thrust-weight ratio is higher. Research shows that the propulsion technology based on detonation combustion can greatly reduce fuel consumption, greatly improve the specific impulse characteristic of the power device, and has important significance for widening the work envelope of the air suction type aircraft and improving the economical efficiency and operational performance of the existing weaponry.

Knock engines can be broadly divided into the following three categories according to their operating modes: pulsed detonation engines, continuous Rotation Detonation Engines (RDE), and inclined detonation engines. The detonation engine can be divided into a rocket type detonation engine, a stamping type detonation engine and a combined detonation engine according to application modes of the detonation engine.

Because the gas fuel and the liquid fuel have the characteristics of strong fluidity and easy pushing control, the rotary detonation engine generally adopts the gas fuel or the liquid fuel to perform detonation combustion. Rotary detonation engines using gaseous or liquid fuels face the following problems: special gas fuel or liquid fuel storage and supply devices and oxidant storage and supply devices are required to be arranged, and the storage and supply devices occupy a large amount of space of the engine; and the gas or liquid fuel storage device must be structurally sound; the transportation of gas or liquid fuel to the engine takes up a lot of manpower and man-hours, extending the firing cycle of the aircraft.

Disclosure of Invention

Solid fuels have unique advantages over gaseous and liquid fuels: on one hand, the energy density of part of solid fuel is higher, the stability is better, the environmental adaptability is stronger, the storage and transportation are convenient, the raw materials are widely available, and the price is low. On the other hand, solid fuel engines also have their unique advantages, including better reliability, simpler construction, etc. In addition, solid fuel engines do not require a complex and time consuming fuel filling process prior to ignition, and therefore have a shorter emission cycle and a faster response.

Rotary detonation combustion generally uses gaseous fuel or liquid combustion, and solid powder fuel is rarely used, particularly in the field of continuous rotary detonation ramjet engines of solid fuel, no related patent or engineering practice exists. The main reason why rotary detonation combustion rarely uses solid pulverized fuel is: knocking combustion modes require particularly severe combustion conditions such as good blending modes, ignition conditions, engine geometry, etc.

The main purpose of the embodiment of the utility model is as follows: provided is a rotary detonation engine device which is capable of achieving a smaller structural design, a higher thrust-weight ratio, and a higher thermal efficiency of solid fuel, simplifying the device structure and process of a fuel supply portion by feeding solid fuel powder that has been fluidized to a rotary detonation engine body by a fluidization module of the solid fuel supply device, and performing tissue combustion by continuous rotary detonation waves.

An embodiment of the present utility model provides a rotary knock engine device including:

a rotary detonation engine body provided with a combustion chamber; and

a solid fuel supply device comprising a solid fuel supply module and a fluidisation module, the solid fuel supply module being connected to the fluidisation module and arranged to supply solid fuel to the fluidisation module; the fluidization module is in communication with the combustion chamber and is configured to fluidize the solid fuel into a solid powder and deliver the solid powder to the combustion chamber.

An embodiment of the present utility model provides an aircraft comprising a rotary detonation engine device as in any of the above exemplary embodiments.

According to the rotary detonation engine device, the fluidized solid powder is conveyed to the rotary detonation engine body through the fluidization module of the solid fuel supply device, and the continuous rotary detonation wave is used for carrying out tissue combustion to generate thrust. Because the detonation wave of the rotary detonation engine has self-boosting property, the pressure and the thermal efficiency of the combustion chamber can be greatly improved, and the rotary detonation engine has the advantages that larger thrust can be generated under the low pressure ratio, the combustion chamber can be designed to be smaller relatively, and the thrust-weight ratio is higher.

In addition, the rotary detonation engine device adopts the fluidization module of the solid fuel supply device to supply solid fuel to the rotary detonation engine device, and part of the solid fuel has the advantages of higher energy density, better stability, stronger environmental adaptability, convenience in storage and transportation, wide raw material availability and low price compared with liquid and gas fuel. Therefore, the rotary detonation engine device can blow the solid powder by utilizing the air flowing at a high speed to form the solid powder which is more easy to burn and is similar to a fluid state, and the special design of an oxidant supply device and a gas-liquid fuel supply device with a complex structure is not needed, so that compared with the rotary detonation engine device supplied by gas and liquid fuel, the rotary detonation engine device has the advantages that the structural design of the engine device can be simplified, the thermal efficiency of fuel can be improved, the emission period of the engine can be shortened, the fuel filling process can be simplified, and the manufacturing cost of the engine can be reduced under the condition of higher thrust effect.

In addition, the solid powder fuel has better flow following property, is convenient to adjust, and can realize the capability of multiple starting and thrust adjustment of the engine.

Other features and advantages of the rotary detonation engine device of the embodiments of the present application will be set forth in the description that follows.

Drawings

The accompanying drawings are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate and do not limit the utility model.

FIG. 1 is a schematic structural view of a rotary knock engine device according to an embodiment of the present application;

FIG. 2 is a schematic cross-sectional view of the rotary knock engine apparatus of FIG. 1;

FIG. 3 is a schematic cross-sectional view of the rotary knock engine device of FIG. 2 taken along the direction A-A.

Reference numerals:

1-rotary detonation engine body, 11-combustion chamber, 12-intake duct, 13-intake duct cone, 131-cavity, 14-intake duct housing, 15-tail injection module, 16-ignition module, 2-solid fuel supply device, 21-solid fuel supply module, 211-solid fuel storage cavity, 212-drive module, 2121-piston, 22-fluidization module, 221-airflow channel, 222-fluidization cavity, 2221-first intake duct, 23-blending module, 231-blending cavity, 232-premixing module, 233-secondary blending module, 2321-first blending cavity, 2331-second blending cavity, 2332-second intake duct, 234-compensating channel.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the present utility model more apparent, embodiments of the present utility model will be described in detail hereinafter with reference to the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Currently, existing rotary detonation combustion generally uses either gaseous fuel or liquid fuel combustion. The main reason why the rotary detonation combustion does not use solid pulverized fuel is: knocking combustion modes require particularly severe combustion conditions such as good blending modes, ignition conditions, engine geometry, etc.

Solid fuels have unique advantages over gaseous and liquid fuels: on one hand, the energy density of part of solid fuel is higher, the stability is better, the environmental adaptability is stronger, the storage and transportation are convenient, the raw materials are widely available, and the price is low. On the other hand, solid fuel engines also have their unique advantages, including better reliability, simpler construction, etc. In addition, solid fuel engines do not require a complex and time consuming fuel filling process prior to ignition, and therefore have a shorter emission cycle and a faster response.

According to the embodiment of the application, the solid fuel powder is fluidized and injected, so that the structural strength of a combustion chamber and the detonation conditions of detonation waves are guaranteed.

Referring to fig. 1 to 3 of the drawings, an embodiment of the present application provides a rotary knock engine device including a rotary knock engine body 1 and a solid fuel supply device 2, wherein the rotary knock engine body 1 is provided with a combustion chamber 11; the solid fuel supply device 2 includes a solid fuel supply module 21 and a fluidization module 22; the solid fuel supply module 21 is connected to the fluidization module 22 and is arranged to supply solid fuel to the fluidization module 22; the fluidization module 22 communicates with the combustion chamber 11 and is arranged to fluidize the solid fuel into a solid powder and to deliver it to the combustion chamber 11.

Specifically, as shown in fig. 1 to 2, the rotary knock engine device of the present application includes not only a rotary knock engine body 1 but also a solid fuel supply device 2, and the rotary knock engine body 1 includes a combustion chamber 11, an intake duct 12 and an intake device (not shown in the drawings), a tail injection module 15, and an ignition module 16. The air inlet device can be a special oxidant air inlet device, and can also be directly communicated with the outside atmosphere.

Notably, the fluidization module 22 communicates with the combustion chamber 11 and is configured to fluidize the solid fuel into a solid powder and deliver the solid powder to the combustion chamber 11. Wherein the fluidization module 22 may be a device that blows the solid powder with high pressure gas to form a fluid-like state that burns more easily. Of course, the solid powder and the high-pressure gas are not necessarily mixed to form the fluidized solid powder, and for example, the method may include pulverizing the large-particle solid and then performing the mixing fluidization, which is not limited herein.

According to the rotary detonation engine device, the fluidized solid powder is conveyed to the rotary detonation engine body through the fluidization module of the solid fuel supply device, and the continuous rotary detonation wave is used for carrying out tissue combustion to generate thrust. Because the detonation wave of the rotary detonation engine has self-supercharging property, compared with the traditional power devices such as an internal combustion engine, an aeroengine, a gas turbine and the like, the rotary detonation engine can greatly improve the pressure and the heat efficiency of a combustion chamber, has the advantages of the rotary detonation engine, can generate larger thrust under a low pressure ratio, and has smaller relative design and higher thrust-weight ratio.

The current rotatory detonation engine all adopts gas or liquid fuel to supply with the combustion chamber, and the rotatory detonation engine device of this application adopts solid fuel supply device to provide solid fuel to rotatory detonation engine device, and partial solid fuel compares liquid and gas fuel and has the energy density higher, and stability is better, and environmental suitability is stronger, is convenient for store transportation, and raw and other materials draw materials extensively, advantage low price. In addition, the rotary detonation engine device can blow the solid powder by utilizing the air flowing at a high speed to form the solid powder which is more easy to burn and similar to a fluid state, and thus, an oxidant supply device and a gas-liquid fuel supply device with a complex structure are not required to be specially designed, so that the rotary detonation engine device has the advantages that compared with the rotary detonation engine device supplied by gas and liquid fuels, under the condition of higher thrust effect, the structural design of the engine device can be simplified, the thermal efficiency of fuel is improved, the emission period of the engine is shortened, the fuel filling process is simplified, and the manufacturing cost of the engine is reduced.

In addition, the solid powder fuel has better flow following property, is convenient to adjust, and can realize the capability of multiple starting and thrust adjustment of the engine. .

In an exemplary embodiment, as shown in fig. 2, the fluidization module 22 is provided with an airflow channel 221 and a fluidization chamber 222, and a first air inlet duct 2221 is provided in a chamber wall of the fluidization chamber 222 to communicate the airflow channel 221 with the fluidization chamber 222.

The solid fuel supply module 21 is provided with a solid fuel storage cavity 211 and a driving module 212, wherein the solid fuel storage cavity 211 is communicated with the fluidization cavity 222, and the driving module 212 is used for driving solid fuel powder in the solid fuel storage cavity 211 into the fluidization cavity 222 so as to fluidize the solid fuel powder under the action of air flow conveyed by the air flow channel 221.

Specifically, as shown in fig. 2, the first air intake duct 2221 may be provided with multiple layers of air intake ducts along the axial direction of the cavity wall of the fluidization cavity 222, and each layer of air intake duct is provided with multiple air intake holes at intervals along the circumferential direction of the cavity wall of the fluidization cavity 222.

In an exemplary embodiment, the rotary detonation engine body 1 is provided with an inlet duct 12, the inlet duct 12 being arranged to convey gaseous oxidant, an output end of the inlet duct 12 being in communication with an input end of the airflow channel 221.

Specifically, the intake duct 12 is provided to convey the gaseous oxidizing agent, and an output end of the intake duct 12 communicates with an input end of the gas flow passage 221, so that the gas flow for fluidizing the solid powder originates from the intake duct 12 that conveys the gaseous oxidizing agent. Of course, the gas flow channels 221 and gas flow for fluidizing the solid powder may also originate from other gas fuel devices, using gaseous fuel to fluidize the solid fuel powder and achieve multiple fuel mixed combustion in the combustion chamber. Communicating the output end of the intake duct 12 with the input end of the airflow passage 221 can simplify the structural design and process of the rotary knock engine device of the present application.

In an exemplary embodiment, the inlet port 12 is in communication with the ambient atmosphere at an inlet end thereof, and the airflow channel 221 surrounds the outside of the solid fuel storage cavity 211 and the fluidization cavity 222.

Specifically, the input end of the air inlet 12 is communicated with the external atmosphere, and then the air flow channel 221 is communicated with the air inlet 12, so that the air is used as an air inlet source, oxygen in the air is used as an oxidant, the oxygen and solid fuel (namely a reducing agent) provided by the fluidization module 22 of the solid fuel supply device 2 undergo detonation reaction in the rotary detonation engine to form high-temperature and high-pressure air, and the high-pressure air is discharged through the spray pipe module 15 to form thrust, so that the rotary detonation engine device of the application becomes the rotary detonation ramjet engine device. The design can simplify the structural design and process of the rotary detonation engine without specially designing an oxidant supply device.

In one exemplary embodiment, the solid fuel storage cavity 211 communicates with the fluidization cavity 222 to form a unitary structure, which may simplify the structural design and space occupation of the solid fuel supply device 2, which may be advantageous for cost reduction.

In one exemplary embodiment, the cross-sectional area of the fluidization chamber 222 gradually decreases in a direction toward the combustion chamber 11.

In one exemplary embodiment, the solid fuel storage cavity 211 communicates with the fluidization cavity 222 to form a unitary structure, and the cross-sectional area of the fluidization cavity 222 gradually decreases in a direction approaching the combustion chamber 11.

Specifically, as shown in fig. 2, the first air intake duct 2221 is provided in the chamber wall region where the cross-sectional area of the fluidization chamber 222 gradually decreases, and this structure enables the air flow through the air flow passage 221 and the first air intake duct 2221 to converge more effectively, and to be in full contact with the solid fuel powder, achieving the fluidization process.

In one exemplary embodiment, the drive module 212 includes: a piston 2121 disposed within the solid fuel reservoir 211, and a driver (not shown) coupled to the piston 2121. The fluidization chamber 222 communicates with the end of the solid fuel reservoir 211 remote from the piston 2121.

A driver (not shown) is provided to drive the piston 2121 in motion to push the solid fuel powder to the fluidization chamber 222.

In an exemplary embodiment, as shown in fig. 2, the rotary knock engine body 1 further includes an intake port inner cone 13 and an intake port outer shell 14, and the intake port outer shell 14 is sleeved outside the intake port inner cone 13 and surrounds the intake port 12 with the intake port inner cone 13. The inlet cone 13 is provided with a cavity 131, the cavity 131 being connected to a solid fuel storage chamber 211 for receiving a driving member (not shown). The space inside the air inlet channel is reasonably utilized to accommodate the driving piece, and other spaces are not required to be additionally arranged to accommodate the driving piece, so that the size of the engine is reduced, and the weight of the engine is reduced.

In one exemplary embodiment, the driving member (not shown) is a motor or a cylinder; when the driving member (not shown) is a cylinder, the inlet cone 13 is provided with a through hole communicating the inlet 12 with the cavity 131.

In particular, since the powder particles in the solid fuel storage cavity 211 are in a discrete solid state, there is no flowability, and thus a corresponding flow carrier is required to achieve fluidization and powder transport. In order to maintain the solid powder in the solid fuel storage cavity 211 to have the same density in the spatial distribution of the cavity, it is common practice to incorporate a piston 2121 in the solid fuel storage cavity 211, the piston 2121 being applied to push the solid powder forward so as to fill the gap left by the output powder. Depending on how the piston 2121 is driven, the drive module 212 may be divided into a pneumatically driven piston and a motor driven piston, i.e., the drive member (not shown) is a motor or a cylinder.

The fluidization powder feeding structure of the pneumatic driving piston is more compact, the negative mass of the driving module 212 is smaller, and in order to prevent solid powder from accumulating in the convergence part, a flow gas path is generally added in the convergence structure, and the fluidization powder feeding structure of the pneumatic driving piston enables the powder flow rate to be flexibly adjusted.

The fluidization powder feeding structure of the motor driving piston adopts a driving cavity and a fluidization cavity to be connected with pipeline powder feeding so as to keep the pressure difference at the end of the piston relatively stable. The motor drives the piston to move to realize powder feeding, a system pipeline is relatively simple, the thrust adjustment operation difficulty is relatively small, the motor drives the piston to have larger negative mass, the requirement on the integration level of an engine system is higher, the movement rate of the piston can be controlled by adjusting the rotation speed of the motor, and the stability of the movement of the piston is realized.

In an exemplary embodiment, as shown in FIG. 2, the solid fuel supply device 2 further comprises at least one blending module 23 located between the fluidization module 22 and the combustion chamber 11, the blending module 23 being provided with a blending chamber 231. The rotary knock engine block 1 is provided with an intake duct 12, the intake duct 12 being arranged to convey gaseous oxidant, the intake duct 12 being in communication with the blending chamber 231.

The blending module 23 is configured to mix the solid fuel powder fluidized by the fluidization module 22 with the gaseous oxidant delivered by the inlet 12.

Specifically, at least one blending module 23 between the fluidization module 22 and the combustion chamber 11 to more fully fluidize and more fully mix the solid powder after fluidization by the fluidization module 22; at the same time, the solid fuel powder output by fluidization module 22 in a fluidization way is mixed with the gaseous oxidant conveyed by air inlet 12, so that the fuel and the oxidant are mixed, and the air-fuel ratio of the rotary detonation engine can be adjusted conveniently.

In an exemplary embodiment, as shown in fig. 2, the number of the blending modules 23 is two, the two blending modules 23 are a premixing module 232 and a secondary blending module 233, the blending chambers 231 of the premixing module 232 and the blending chambers 231 of the secondary blending module 233 are respectively denoted as a first blending chamber 2321 and a second blending chamber 2331, and an electric control valve (not shown in the figure) is disposed between the first blending chamber 2321 and the second blending chamber 2331; the fluidization module 22, the premixing module 232, an electrically controlled valve (not shown), the secondary blending module 233, and the combustion chamber 11 are connected in this order.

Wherein the premixing module 232 is configured to premix the solid fuel powder with the gaseous oxidizer under the influence of the airflow delivered by the inlet 12; the secondary blending module 233 is configured to secondarily blend the solid fuel powder with the gaseous oxidant under the influence of the compensating air flow delivered by the inlet 12. The primary purpose of the secondary blending is to avoid solid fuel powder build-up during delivery and also to facilitate optimum air-fuel ratio.

It should be noted that the number of blending modules 23 is not limited to two, but may be one, three or more, so that the fluidized solid powder blending effect is better and the air-fuel ratio between the solid powder and the gas oxidizer is better adjusted.

An electric control valve is arranged between the first mixing chamber 2321 and the second mixing chamber 2331, and the second mixing chamber 2331 is combined by opening and closing an electromagnetic valve, so that the function of adjusting the air-fuel ratio between the solid powder and the gas oxidizer is also achieved.

In one exemplary embodiment, as shown in FIG. 2, the fluidization module 22 is provided with a fluidization chamber 222, the first blending chamber 2321 communicates with the fluidization chamber 222, the input end of the inlet duct 12 communicates with the outside atmosphere, and the output end of the inlet duct 12 communicates with the fluidization chamber 222 through the airflow passage 221.

The air flow channel 221 is connected with a compensation flow channel 234, two ends of the compensation flow channel 234 are respectively communicated with the air flow channel 221 and the second mixing chamber 2331, and the air inlet 12 is indirectly communicated with the second mixing chamber 2331 through the air flow channel 221 and the compensation flow channel 234.

In this way, air flows can be provided to the fluidization chamber 222, the first blending chamber 2321, and the second blending chamber 2331 through the same air inlet passage, greatly simplifying the air supply structure of the engine.

In an exemplary embodiment, the air flow channel 221 surrounds the outside of the fluidization chamber 222, and the number of the compensating channels 234 is plural, and the compensating channels 234 are disposed at intervals along the circumference of the air flow channel 221.

Specifically, as shown in fig. 3, the compensating flow paths 234 are arranged at intervals along the circumferential direction of the air flow path 221, and the number of compensating flow paths 234 is 6, although the number of compensating flow paths 234 is not limited to 6.

In an exemplary embodiment, as shown in fig. 2-3, a plurality of second air inlet ports 2332 are provided at an end of the second mixing chamber 2331 adjacent to the combustion chamber 11, and the second air inlet ports 2332 provide for the mixed solid fuel powder and gaseous oxidant to enter the combustion chamber 11.

Specifically, in the schematic cross-sectional structure of the rotary knock engine device of the embodiment shown in fig. 3, the second intake duct 2332 is a 3-turn intake duct, and of course, the second intake duct 2332 of the rotary knock engine device of the present application is not limited to 3 turns.

In one exemplary embodiment, the solid fuel powder includes at least one of boron powder, magnesium powder.

Specifically, high-energy metal or/and metalloid powder such as boron powder or magnesium powder is used as fuel, stable continuous knocking can be realized, the propulsion performance of the rotary knocking engine device is greatly improved, and the specific impact and range of the aircraft are greatly improved.

In an exemplary embodiment, as shown in fig. 1 and 3, the rotary detonation engine body 1 further includes an ignition module 16, and the ignition module 16 may be a pre-detonation tube, an electric detonator. Of course, the ignition module 16 is not limited to pre-detonation tubes, electric detonators.

In an exemplary embodiment, as shown in fig. 1 and 2, the rotary detonation engine body 1 further includes a tail jet module 15, and a tail jet passage is formed between the tail jet module 15 and the combustion chamber 11 for discharging a tail jet stream to generate thrust.

Embodiments of the present application provide an aircraft comprising a rotary detonation engine device as in any of the above exemplary embodiments.

The aircraft provided in the embodiments of the present application includes the rotary knock engine device according to any one of the above exemplary embodiments, and therefore has technical features and advantages of the rotary knock engine device according to any one of the above exemplary embodiments, which are not described herein.

Unless specifically stated or limited otherwise, the terms "mounted," "connected," "secured" and the like should be construed broadly, as they may be fixed, removable, or integral, for example; can be mechanically or electrically connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be.

In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present application. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.

Although embodiments of the present application have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the application, and that variations, modifications, alternatives, and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the application.

Claims (15)

1. A rotary knock engine device characterized by comprising:

a rotary knock engine body (1) provided with a combustion chamber (11); and

-a solid fuel supply device (2) comprising a solid fuel supply module (21) and a fluidization module (22), the solid fuel supply module (21) being connected to the fluidization module (22) and being arranged to supply solid fuel to the fluidization module (22); the fluidization module (22) is in communication with the combustion chamber (11) and is arranged to fluidize the solid fuel into a solid powder and to deliver it to the combustion chamber (11).

2. The rotary detonation engine device of claim 1, wherein the fluidization module (22) is provided with an airflow channel (221) and a fluidization cavity (222), and a first air inlet duct (2221) communicating the airflow channel (221) with the fluidization cavity (222) is arranged on a cavity wall of the fluidization cavity (222);

the solid fuel supply module (21) is provided with a solid fuel storage cavity (211) and a driving module (212), the solid fuel storage cavity (211) is communicated with the fluidization cavity (222), and the driving module (212) is used for driving solid fuel powder in the solid fuel storage cavity (211) into the fluidization cavity (222) so as to enable the solid fuel powder to be fluidized under the action of air flow conveyed by the air flow channel (221).

3. The rotary detonation engine device according to claim 2, characterized in that the rotary detonation engine body (1) is provided with an inlet duct (12), the inlet duct (12) being arranged to convey gaseous oxidant, the outlet end of the inlet duct (12) being in communication with the inlet end of the airflow channel (221).

4. A rotary detonation engine device as claimed in claim 3, characterised in that the inlet port (12) is in communication with the external atmosphere at its inlet end, the air flow channel (221) surrounding the outside of the solid fuel storage chamber (211) and the fluidization chamber (222).

5. The rotary knock engine device according to claim 2, characterized in that,

the solid fuel storage cavity (211) is communicated with the fluidization cavity (222) to form an integrated structure; and/or

The cross-sectional area of the fluidization chamber (222) gradually decreases in a direction approaching the combustion chamber (11).

6. The rotary detonation engine device of any of claims 2 to 5, wherein the drive module (212) includes: a piston (2121) disposed inside the solid fuel storage chamber (211) and a driving member connected to the piston (2121), the fluidization chamber (222) being in communication with an end of the solid fuel storage chamber (211) remote from the piston (2121);

the driver is configured to drive the piston (2121) in motion to push the solid fuel powder to the fluidization chamber (222).

7. The rotary knock engine device according to claim 6, characterized in that the rotary knock engine body (1) further comprises an intake duct inner cone (13) and an intake duct outer shell (14), the intake duct outer shell (14) being sleeved outside the intake duct inner cone (13) and surrounding an intake duct (12) with the intake duct inner cone (13); the air inlet inner cone (13) is provided with a cavity (131), and the cavity (131) is connected with the solid fuel storage cavity (211) and is used for accommodating the driving piece.

8. The rotary detonation engine device of claim 7, wherein the driver is an electric motor or a cylinder; when the driving part is a cylinder, the air inlet channel inner cone (13) is provided with a through hole which is communicated with the air inlet channel (12) and the cavity (131).

9. The rotary detonation engine device according to any of claims 1 to 5, characterized in that the solid fuel supply device (2) further comprises at least one blending module (23) located between the fluidization module (22) and the combustion chamber (11), the blending module (23) being provided with a blending chamber (231); the rotary knocking engine body (1) is provided with an air inlet channel (12), the air inlet channel (12) is used for conveying gaseous oxidant, and the air inlet channel (12) is communicated with the mixing cavity (231);

the blending module (23) is arranged to mix the solid fuel powder fluidizedly output by the fluidising module (22) with the gaseous oxidant delivered by the inlet duct (12).

10. The rotary detonation engine device of claim 9, wherein the number of the blending modules (23) is two, the two blending modules (23) are a premixing module (232) and a secondary blending module (233) respectively, the blending chambers (231) of the premixing module (232) and the secondary blending module (233) are respectively marked as a first blending chamber (2321) and a second blending chamber (2331), and an electric control valve is arranged between the first blending chamber (2321) and the second blending chamber (2331); the fluidization module (22), the premixing module (232), the electric control valve, the secondary blending module (233) and the combustion chamber (11) are sequentially connected;

wherein the premixing module (232) is configured to premix the solid fuel powder with the gaseous oxidant under the influence of the air flow delivered by the air inlet duct (12); the secondary blending module (233) is configured to secondarily blend the solid fuel powder with the gaseous oxidant under the effect of the compensating air flow delivered by the inlet duct (12).

11. The rotary detonation engine device of claim 10, wherein the fluidization module (22) is provided with a fluidization chamber (222), the first blending chamber (2321) is in communication with the fluidization chamber (222), the input of the air intake (12) is in communication with the outside atmosphere, and the output of the air intake (12) is in communication with the fluidization chamber (222) through an airflow channel (221);

the air flow channel (221) is connected with a compensation flow channel (234), two ends of the compensation flow channel (234) are respectively communicated with the air flow channel (221) and the second mixing cavity (2331), and the air inlet channel (12) is indirectly communicated with the second mixing cavity (2331) through the air flow channel (221) and the compensation flow channel (234).

12. The rotary detonation engine device of claim 11, wherein the air flow channel (221) surrounds the outside of the fluidization chamber (222), the number of the compensating channels (234) is plural, and the compensating channels (234) are arranged at intervals along the circumferential direction of the air flow channel (221).

13. The rotary detonation engine device of claim 10, wherein an end of the second blending chamber (2331) adjacent to the combustion chamber (11) is provided with a plurality of second air intake channels (2332), the second air intake channels (2332) being for the mixed solid fuel powder and the gaseous oxidant to enter the combustion chamber (11).

14. The rotary detonation engine device of any one of claims 1 to 5, wherein the solid fuel powder includes at least one of boron powder, magnesium powder.

15. An aircraft comprising a rotary detonation engine device as claimed in any one of claims 1 to 14.