Boron-based powder fuel power device capable of flying in wide speed range and control method of boron-based powder fuel power device

Abstract

The invention discloses a wide-speed-range flight boron-based powder fuel power device and a control method thereof, the device comprises a gas inlet assembly, a combustion chamber, an annular fuel gas generator and a pneumatic choking type powder fuel supply assembly, and a solid fuel gas generator is arranged in the gas inlet assembly; a first concave cavity and a second concave cavity are formed in an injection section of the combustion chamber, a plurality of first powder through hole arrays and a plurality of gas through hole arrays are formed in the injection section, and the first powder through hole arrays and the gas through hole arrays are evenly distributed in the circumferential direction of the injection section. The annular fuel gas generator is used for conveying rich fuel gas to the injection section; the pneumatic choking type powder fuel supply assembly is used for driving and fluidizing boron-based powder fuel by means of incoming flow; the solid fuel gas generator and the annular fuel gas generator are both controlled by an external control system to ignite. The powder fuel can be stably conveyed, the mixing combustion efficiency with incoming flow is high, and zero-speed starting and smooth mode conversion can be achieved.

Description

Technical Field

[0001] This invention relates to the field of powder engine technology, and in particular to a wide-speed-range flight boron-based powder fuel power plant and its control method. Background Technology

[0002] Wide-range engines typically refer to power units that can operate continuously and efficiently from standstill or low speed to hypersonic speed. Their core characteristic is that they do not rely on a single thermodynamic cycle, but are an integrated propulsion system composed of multiple engines with different operating modes, capable of multi-modal and multi-cycle intelligent combination and switching.

[0003] Rocket-based combined cycle (RBCC) engines are currently the main research focus for high-efficiency engines operating across a wide speed range. RBCCs deeply integrate rocket and ramjet engines, forming four operating modes: zero-speed start-up ejection mode, subsonic ramjet mode, scramjet mode, and pure rocket mode, covering a wide flight speed range. However, existing RBCC engines mostly use liquid fuels such as liquid hydrogen and kerosene, or gaseous fuels. Liquid fuels suffer from drawbacks such as low fuel density and system complexity. Furthermore, they exhibit problems like the dissociation of hydrocarbon combustion products at high Mach numbers, poor combustion stability, and limited engine specific impulse. While hydrogen possesses excellent reactivity and a wide flammability limit, its low density, inconvenient storage and transportation, and safety hazards limit its application.

[0004] To address the aforementioned issues, existing technologies employ boron-based powdered fuels as high-energy solid propellants to replace RBCC liquid and gaseous fuels. Boron-based powdered fuels possess unique advantages such as extremely high volumetric energy density, stability at room temperature and pressure, and safe and convenient storage and transportation. Using high-calorific-value, storage-stable, and safe boron-based powdered fuels can significantly improve the engine's specific impulse performance; at high Mach numbers, the higher total incoming flow temperature makes the combustion products of the powdered fuel less prone to dissociation, allowing for the full release of the fuel's chemical energy.

[0005] However, when applying boron-based powdered fuel to a wide-speed-range RBCC engine and achieving stable and efficient operation from zero-speed start-up to high Mach numbers, it is difficult to achieve stable and controllable continuous delivery of the powder under a wide range of varying back pressure environments. Furthermore, powdered fuel has high inertia and low mixing efficiency with high-speed incoming flow. Its extremely short residence time in supersonic airflow leads to problems such as difficulty in ignition, unstable combustion, and low efficiency. Especially at low speeds, the low total temperature of the incoming flow makes mixing and combustion even more challenging. Summary of the Invention

[0006] Based on this, it is necessary to address the aforementioned technical problems by providing a wide-speed-range flight boron-based powder fuel power plant and its control method that can stably deliver powder fuel, achieve high combustion efficiency when mixed with the incoming flow, and enable zero-speed start-up and smooth mode transition.

[0007] In a first aspect, the present invention provides a wide-speed-range flight boron-based powder fuel power device, comprising: The intake assembly is used to introduce and compress incoming air, and a solid fuel gas generator is installed inside the intake assembly. The combustion chamber is provided with an integrally connected straight section, injection section and expansion section. The straight section is axially fixed to the rear end of the intake assembly. The injection section has a first cavity and a second cavity arranged in sequence along the direction away from the intake assembly. The injection section has a plurality of first powder through holes arrays located in front of the first cavity and a plurality of gas through holes arrays located between the first cavity and the second cavity. The plurality of first powder through holes arrays and the plurality of gas through holes arrays are all evenly distributed along the circumference of the injection section. An annular fuel gas generator is used to deliver fuel-rich gas to the injection section through a gas through-hole array. It is sleeved on the outside of the injection section, with its front end located behind the first powder through-hole array and fixedly connected to the outer wall of the injection section, and its rear end located at the end of the injection section. A pneumatic plug-type powder fuel supply assembly is used to drive and fluidize boron-based powder fuel by means of incoming flow, and to deliver boron-based powder fuel to the injection section through a first powder through-hole array. Both solid fuel gas generators and annular fuel gas generators have their ignition conditions controlled by an external control system.

[0008] In one embodiment, the annular fuel gas generator includes a first annular hollow shell, a second annular hollow shell, an annular guide plate, a first annular solid fuel propellant grain, and a second annular solid fuel propellant grain; The first and second annular hollow shells are both fitted onto the injection section; The first and second annular hollow shells are open on opposite sides and sealed on opposite sides. The two end walls of the annular drainage concave plate are axially fixedly connected to the outer walls of the first and second annular hollow shells, respectively. The first annular solid fuel propellant grain is filled inside the first annular hollow shell, and the second annular solid fuel propellant grain is filled inside the second annular hollow shell. The gap between the inner walls of the first annular hollow shell and the second annular hollow shell forms a fuel-rich gas passage, and the gap distance is greater than or equal to the width of the gas passage array along the engine axis. Igniters are fixedly mounted on the inner side of the outer wall of the opening of both the first and second annular hollow shells, and the igniters are electrically connected to the external control system.

[0009] In one embodiment, the pneumatic plug-type powder fuel supply assembly includes an annular flow channel component and a powder supply assembly; The annular flow guide channel component is fitted into the combustion chamber to introduce the incoming flow and divide the incoming flow into fluidizing gas and driving gas, which are then delivered to the powder supply assembly. The powder supply assembly is fitted onto the annular guide channel component and is used to drive the internal boron-based powder fuel output with the aid of driving gas and input it into the combustion chamber through the first powder through-hole array. During the output of the boron-based powder fuel, the boron-based powder fuel is atomized by fluidized gas.

[0010] In one embodiment, the annular guide channel component is provided with a hollow annular shell, an annular fixed disk, and a first annular support disk. The first annular support disk is integrally connected to the front end of the hollow annular shell, and the annular fixed disk is integrally connected to the rear end face of the hollow annular shell. The inner wall of the first annular support disk is fixedly connected to the portion of the straight section located at the front end of the first powder through-hole array. The inner diameters of the annular fixed disk and the first annular support disk are both smaller than the inner diameter of the inner wall of the hollow annular shell and are equal to the outer diameter of the injection section. The outer wall of the hollow annular shell is provided with at least two rings of evenly distributed fluidizing gas passages and at least two rings of evenly distributed driving gas passages along the circumferential direction, and at least one air inlet is provided at the front end of the outer wall; the fluidizing gas passages are provided at the front end of the first cavity, and the driving gas passages are provided at the rear end of the hollow annular shell. The hollow annular shell is provided with a second powder through hole array in the part in front of the fluidizing gas through hole, penetrating the inner and outer walls; the second powder through hole array in the inner wall of the hollow annular shell and the second powder through hole array in the outer wall are sealed and connected by an arc-shaped connecting plate, and the projection of each through hole of the second powder through hole array on the outer side wall of the combustion chamber along the radial direction of the hollow annular shell coincides with each through hole of the second powder through hole array. Inside the hollow annular shell, there are first and second annular baffles of the same size and with inner diameters equal to those of the straight section. The first and second annular baffles are located on both sides of the first powder through-hole array along the axial direction of the straight section.

[0011] In one embodiment, the powder supply assembly includes a hollow annular powder storage tank, a fluidizing cone, a fluidizing disc, an annular piston, and an annular regulating sleeve. The front end of the hollow annular powder storage box is open, and the rear end is sealed. The front end of the hollow annular powder storage box is located on the rear side of the fluidizing gas passage along the combustion chamber axis, and the rear end is fixedly assembled with the annular fixed plate. The larger opening sides of both the fluidizing cone and the fluidizing disk face the hollow annular powder storage tank. An annular adjusting sleeve is located on the axial front side of the second powder through-hole array along the combustion chamber and is fixedly sleeved onto the hollow annular shell. The front end of the fluidizing disc is located between the second powder through-hole array and the fluidizing gas through-hole, and is sleeved on the hollow annular shell. The rear end of the fluidizing disc is axially fixedly connected to the front end face of the hollow annular powder storage tank. The front end of the fluidizing cone is fixedly sleeved to the annular adjusting sleeve, and the rear end is axially fixedly connected to the front end face of the hollow annular powder storage tank. The annular piston is located inside the hollow annular powder storage box. Its outer side wall abuts against the inner side of the outer side wall of the hollow annular powder storage box, and its inner side wall abuts against the inner side of the inner side wall of the hollow annular powder storage box. It can slide along the axial direction of the fluidizing disk of the hollow annular powder storage box under the action of the driving gas.

[0012] In one embodiment, the annular regulating sleeve includes a second annular support plate and an annular sealing plate. The second annular support plate is fixedly sleeved on the hollow annular shell, and the front end of the annular sealing plate is integrally sleeved on the second annular support plate. The cavity formed between the annular sealing plate and the hollow annular shell is a powder flow regulating cavity. A third annular support plate is vertically fixed to the inner side of the inner wall of the hollow annular powder storage box. The third annular support plate is located on the rear side of the drive air passage along the combustion chamber axis. The cavity formed between the inner wall of the hollow annular powder storage box and the hollow annular shell is an annular flow guiding and regulating cavity. The powder flow regulating chamber is equipped with a first annular regulating plate that can slide along the axial direction of the hollow annular shell. The first annular regulating plate is sleeved on the hollow annular shell and is used to adjust the overall opening of the second powder through hole array. The annular flow guiding and regulating cavity is provided with a second annular regulating plate and a third annular regulating plate that can slide along the axial direction of the hollow annular shell. Both the second annular regulating plate and the third annular regulating plate are sleeved on the hollow annular shell, and the second annular regulating plate is located close to the fluidizing plate. The second annular adjusting plate is used to adjust the number of opening turns of the fluidizing air passage, and the third annular adjusting plate is used to adjust the number of opening turns of the driving air passage.

[0013] In one embodiment, the intake assembly includes an intake pipe and a guide cone, with the rear end of the intake pipe fixedly connected to the front end of the straight section. The front end of the guide cone extends out of the intake pipe, the middle part is fixedly connected to the inner wall of the front end of the intake pipe through ribs circumferentially assembled on its outer wall, and the end is located at the tail of the intake pipe. The gap between the intake pipe and the guide cone forms an intake channel. The solid fuel gas generator is fixedly assembled inside the guide cone. A second gas passage is provided at the end of the guide cone. The outlet pipe of the solid fuel gas generator is connected to the second gas passage. The second gas passage is fitted with a spray plate, which has several spray holes.

[0014] In one embodiment, a Laval nozzle is fitted inside the rear end of the expansion section, and an annular connecting piece is fixedly connected to the rear end face of the expansion section by an explosive bolt. The inner diameter of the annular connecting piece is smaller than the rear end inner diameter of the Laval nozzle, and the rear end face of the Laval nozzle is fixedly connected to the annular connecting piece by an explosive bolt. The explosive bolts are electrically connected to the external control system.

[0015] In one embodiment, a plurality of injection holes on the injection plate penetrate through the front and rear ends of the injection plate, and the plurality of injection holes are distributed in the central circular straight hole area and the annular oblique hole area fitted within the circular straight hole area. The injection direction of the injection holes in the middle circular straight hole area is parallel to the axis of the straight section, while the injection direction of the injection holes in the annular oblique hole area is inclined at 30-45° from the axis of the straight section towards its inner wall surface.

[0016] Secondly, the present invention also provides a control method for a wide-speed-range flight boron-based powder fuel power device, wherein during the ejection start-up phase, the igniter of the solid fuel gas generator is controlled by an external control system to ignite, and the igniter of the annular fuel gas generator is turned off. After the ejection initiation phase is completed, the electric igniter built into the explosive bolt is ignited by the external control system, and the igniter of the annular fuel gas generator is ignited by the external control system.

[0017] The beneficial effects of this invention are: (1) The present invention uses a pneumatic plug-type powder fuel supply component, which divides the incoming flow into driving gas and fluidizing gas to drive and fluidize the boron-based powder fuel, and inputs it into the combustion chamber through the first powder through-hole array. By using the incoming flow to transport boron-based powder fuel and fluidize it at the same time, the stable delivery of boron-based powder fuel can be achieved.

[0018] (2) In this invention, the powdered fuel can be initially mixed and burned in the first concave cavity with the incoming flow, and the fuel-rich gas generated by the annular fuel gas generator can be mixed and burned with the incoming flow in the second concave cavity to form a downstream high-temperature region. The low-speed recirculation region generated by the two-stage concave cavity structure design prolongs the residence time of the powdered fuel in the engine and improves the mixing and combustion efficiency of the powdered fuel with the incoming flow.

[0019] (3) In the ejector start-up stage, i.e., in the 0-3 Ma stage, the solid fuel gas generator can be ignited by controlling the solid fuel gas generator. The fuel-rich gas generated by the solid fuel gas generator forms a low-pressure zone at the end of the intake duct. Air is drawn in through the ejector effect, which greatly improves the pressure recovery capability of the intake duct and overcomes the defect that traditional ramjet engines cannot start at zero speed. After the ejector start-up stage is completed, in the 3-6 Ma stage, the annular fuel gas generator and the solid fuel gas generator work simultaneously. The fuel-rich gas generated by the annular solid fuel gas generator mixes and burns with the incoming flow in the downstream to form a high-temperature zone. The powdered fuel is fully burned in the high-temperature zone, and the combustion chamber enters a sub-combustion state. When it is greater than 6 Ma, the injection flow rate of the powder can be changed by adjusting the drive, fluidization and powder inlet channel area. At this time, the total temperature of the incoming flow is already high enough. Under the action of the fuel-rich gas, the powdered fuel is fully mixed and burned with the incoming flow in the low-speed recirculation area formed by the two-stage concave cavity. At this time, the combustion chamber enters the supercombustion mode. Therefore, the power device of the present invention can achieve smooth switching of each mode and has a wide speed range of 0 to above 6 Mach.

[0020] (4) The device of the present invention forms airflow channels and powder channels through structural opening design, avoiding a large number of external pipes and effectively reducing the redundant mass of the overall device. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the overall structure of the wide-speed-range flight boron-based powder fuel power device provided in an embodiment of the present invention; Figure 2 yes Figure 1 A schematic cross-sectional view along the combustion chamber axis; Figure 3 This is a schematic diagram of the overall structure of the combustion chamber provided in an embodiment of the present invention; Figure 4 yes Figure 3 A cross-sectional view along the axis; Figure 5 This is a schematic diagram of the overall structure of the annular fuel gas generator provided in an embodiment of the present invention; Figure 6 yes Figure 5 A cross-sectional view along the axis; Figure 7 This is a schematic diagram of the structure of the pneumatic plug-type powder fuel supply assembly provided in an embodiment of the present invention; Figure 8 yes Figure 7 A cross-sectional view along the axis; Figure 9 This is a schematic diagram of the structure of the annular flow guiding channel component provided in an embodiment of the present invention; Figure 10 yes Figure 9 A cross-sectional view along the axis; Figure 11 yes Figure 9 A cross-sectional view along the centerline of the arc-shaped connecting plate parallel to the combustion chamber axis; Figure 12 This is a schematic diagram of the air intake assembly provided in an embodiment of the present invention; Figure 13 yes Figure 12 A cross-sectional view along the axis; Figure 14 This is a schematic diagram of the structure of the injection plate provided in an embodiment of the present invention.

[0022] Explanation of reference numerals in the attached drawings: 10. Intake assembly; 11. Solid fuel gas generator; 12. Intake pipe; 13. Guide cone; 14. Rib; 15. Second gas through-hole; 16. Injection plate; 17. Injection orifice; 171. Central circular straight hole area; 172. Annular oblique hole area; 20. Combustion chamber; 21. Straight section; 22. Injection section; 23. Expansion section; 24. First concave cavity; 25. Second concave cavity; 26. First powder through-hole array; 27. Gas through-hole array; 28. Laval nozzle; 29. ​​Annular connecting piece; 30. Annular fuel gas generator; 31. First annular hollow shell; 32. Second annular hollow shell; 33. Annular guide concave plate; 34. First annular solid fuel propellant grain; 35. 36. Second annular solid fuel propellant grain; 37. Fuel-rich gas through-hole; 40. Igniter; 41. Pneumatic plug-type powder fuel supply assembly; 41. Annular guide channel component; 411. Hollow annular shell; 412. Annular fixed disk; 413. First annular support disk; 414. Fluidizing gas through-hole; 415. Driving gas through-hole; 416. Air inlet; 417. Second powder through-hole array; 418. First annular baffle; 419. Second annular baffle; 420. Arc-shaped connecting plate; 42. Powder supply assembly; 421. Hollow annular powder storage tank; 422. Fluidizing cone; 423. Fluidizing disk; 424. Annular piston; 425. Annular adjusting sleeve; 4251. Second annular support disk; 4252. Annular sealing plate; 4253. Powder flow regulating chamber; 4254. Third annular support plate; 4255. Annular flow guiding regulating chamber; 4256. First annular regulating plate; 4257. Second annular regulating plate; 4258. Third annular regulating plate. Detailed Implementation

[0023] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0024] It should be noted that in the description of this invention, "upper," "lower," "top," "bottom," and orientation or positional relationship are based on the appendix. Figure 1The orientations or positional relationships shown are for the convenience of describing the present invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

[0025] In one embodiment, such as Figure 1 and Figure 2 As shown, the wide-speed-range flight boron-based powder fuel power device of this embodiment includes: The intake assembly 10 is used to introduce and compress incoming air, and a solid fuel gas generator 11 is installed inside the intake assembly 10. The intake assembly 10 is used to supply compressed air into the combustion chamber 20. The solid fuel gas generator 11 consists of a sleeve, an insulation layer, a propellant grain, a front end cap, a rear end cap, an igniter 37, a tail nozzle, and an injector. Specifically, in this embodiment, the propellant grain is an oxygen-lean star-shaped propellant grain. The combustion of the propellant grain can produce a stable fuel-rich gas, which is injected into the combustion chamber 20. A low-pressure zone is formed at the end of the intake assembly 10, and air is drawn in through the ejector effect, which greatly improves the pressure recovery capability of the intake duct and overcomes the defect that traditional ramjet engines cannot start at zero speed.

[0026] The combustion chamber 20 is equipped with an integrally connected straight section 21, injection section 22, and expansion section 23. For example... Figure 3 and Figure 4 As shown, the straight section 21 is axially fixedly connected to the rear end of the air intake assembly 10. The injection section 22 has a first cavity 24 and a second cavity 25 arranged sequentially in the direction away from the air intake assembly 10. The injection section 22 has a plurality of first powder through hole arrays 26 located in front of the first cavity 24 and a plurality of gas through hole arrays 27 located between the first cavity 24 and the second cavity 25. The plurality of first powder through hole arrays 26 and the plurality of gas through hole arrays 27 are evenly distributed along the circumference of the injection section 22.

[0027] In this embodiment, the axes of each hole in the powder through-hole array and the gas through-hole array 27 are perpendicular to the axis of the combustion chamber 20, and the injection direction is radially injected into the combustion chamber 20. Each powder through-hole array and gas through-hole array 27 includes multiple arrayed through-holes. Specifically, in this embodiment, each of the two arrays includes 3×3 through-holes. The powder injection flow rate and gas injection flow rate can be adjusted by adjusting the number of openings in the powder through-hole array and the gas through-hole array 27. The device of this embodiment forms airflow channels and powder channels through structural opening design, avoiding a large number of external pipes and effectively reducing the redundant mass of the overall device.

[0028] In this embodiment, the straight section 21 is fixedly connected to the rear end of the intake assembly 10 via a flange. The expansion section 23 has an expansion angle of 1-2°. The high-temperature, high-pressure, supersonic gas generated by fuel combustion is accelerated and ejected through the expansion section 23, generating thrust.

[0029] The annular fuel gas generator 30 is used to supply fuel-rich gas to the injection section 22 through the gas through hole array 27. It is sleeved on the outside of the injection section 22, with its front end located behind the first powder through hole array 26 and fixedly connected to the outer wall of the injection section 22, and its rear end located at the end of the injection section 22.

[0030] Powdered fuel is injected into the combustion chamber 20 from the front of the first concave cavity 24, where it is initially mixed and burned with the high-temperature incoming flow in the primary concave cavity. The gas generated by the annular fuel gas generator 30 is injected into the combustion chamber 20 between the first concave cavity 24 and the second concave cavity 25, forming a high-temperature recirculation zone in the second concave cavity 25, where it is fully mixed and burned with the powdered fuel. The combustion chamber 20 is designed with two stages of concave cavities; this design enhances the degree of fuel mixing, stabilizes combustion, and improves combustion efficiency.

[0031] The pneumatic plug-type powder fuel supply assembly 40 is used to drive and fluidize boron-based powder fuel by means of incoming flow, and to deliver boron-based powder fuel to the injection section 22 through the first powder through-hole array 26. By using incoming flow to deliver and simultaneously fluidize the powder fuel, stable delivery of boron-based powder fuel can be achieved. Furthermore, by uniformly replacing traditional liquid fuels such as liquid hydrogen and kerosene with high volumetric energy density boron-based powder fuel, the contradictions of low density of liquid hydrogen and limited specific impulse of kerosene are fundamentally solved. This allows the power unit of this embodiment to store more energy in the same volume, or to have a more compact structure and lighter weight for the same energy demand, thereby significantly improving the payload coefficient and thrust-to-weight ratio of the aircraft equipped with the power unit of this embodiment.

[0032] Both the solid fuel gas generator 11 and the annular fuel gas generator 30 are controlled by an external control system. The external control system sends an ignition signal to the igniter 37 to control the ignition of the two gas generators, thereby delivering fuel-rich gas to the outlet of the combustion chamber 20 and between the first cavity 24 and the second cavity 25 of the injection section 22. The operating conditions of the two gas generators can be controlled according to different modal requirements.

[0033] In one embodiment, such as Figure 5 and Figure 6 As shown, the annular fuel gas generator 30 includes a first annular cylindrical hollow shell 31, a second annular cylindrical hollow shell 32, an annular guide plate 33, a first annular solid fuel propellant grain 34, and a second annular solid fuel propellant grain 35.

[0034] The first annular hollow shell 31 and the second annular hollow shell 32 are both sleeved on the injection section 22; the opposite sides of the first annular hollow shell 31 and the second annular hollow shell 32 are open, and the opposite sides are sealed. The two end walls of the annular drainage concave plate 33 are axially fixedly connected to the outer side walls of the first annular hollow shell 31 and the second annular hollow shell 32, respectively.

[0035] In this embodiment, the first annular hollow shell 31 and the second annular hollow shell 32 are the same size and are symmetrically arranged relative to the annular guide plate 33. The annular guide plate 33 is concave inward, and its function is to guide the ignited gas into the combustion chamber 20.

[0036] The first annular solid fuel propellant grain 34 is filled inside the first annular hollow shell 31, and the second annular solid fuel propellant grain 35 is filled inside the second annular hollow shell 32.

[0037] Specifically, the annular solid fuel propellant grain can be, but is not limited to, a combination of hydroxyl-terminated polybutadiene, ammonium perchlorate, and aluminum powder, which produces fuel-rich combustion gases upon combustion.

[0038] The gap between the inner walls of the first annular hollow shell 31 and the second annular hollow shell 32 forms a fuel-rich gas passage 36, and the gap distance is greater than or equal to the width of the gas passage array 27 along the engine axis. Igniters 37 are fixedly mounted on the inner side of the outer wall of the openings of the first annular hollow shell 31 and the second annular hollow shell 32, and the igniters 37 are electrically connected to the external control system.

[0039] After the annular solid fuel propellant grain is ignited, the combustion-rich gas produced is sealed and transitioned from the combustion-rich gas through-hole 36 into the gas through-hole array 27, and then injected into the middle of the first concave cavity 24 and the second concave cavity 25. It mixes and burns with the incoming flow in the second concave cavity 25 to form a downstream high-temperature region, which can improve the combustion efficiency of the powder.

[0040] In one embodiment, such as Figure 7 and Figure 8 As shown, the pneumatic plug-type powder fuel supply assembly 40 includes an annular guide channel component 41 and a powder supply assembly 42.

[0041] The annular flow guide channel component 41 is sleeved on the combustion chamber 20 to introduce the incoming flow and divide the incoming flow into fluidizing gas and driving gas, which are then transported to the powder supply component 42.

[0042] The powder supply assembly 42 is sleeved on the annular guide channel component 41 and is used to drive the internal boron-based powder fuel to be output by means of driving gas and input into the combustion chamber 20 through the first powder through hole array 26. During the output of boron-based powder fuel, the boron-based powder fuel is atomized by means of fluidized gas.

[0043] This embodiment achieves the driving and fluidization of powdered fuel by dividing the incoming flow.

[0044] In one embodiment, such as Figure 9 and Figure 10 As shown, the annular guide channel component 41 is provided with a hollow annular shell 411, an annular fixing disk 412, and a first annular support disk 413. The first annular support disk 413 is integrally connected to the front end of the hollow annular shell 411, and the annular fixing disk 412 is integrally connected to the rear end face of the hollow annular shell 411. The inner wall of the first annular support disk 413 is fixedly connected to the portion of the straight section 21 located at the front end of the first powder through-hole array 26. The inner diameters of the annular fixing disk 412 and the first annular support disk 413 are both smaller than the inner diameter of the inner wall of the hollow annular shell 411, and are equal to the outer diameter of the injection section 22.

[0045] The annular fixed plate 412 and the first annular support plate 413 form a sealed cavity between the annular flow guide channel member 41 and the wall of the combustion chamber 20 to house the annular fuel gas generator 30. The rear end of the annular fuel gas generator 30 is fixedly connected to the annular fixed plate 412 by bolts.

[0046] The outer wall of the hollow annular shell 411 is provided with at least two rings of evenly distributed fluidizing gas passages 414 and at least two rings of evenly distributed driving gas passages 415 along the circumferential direction, and at least one air inlet 416 is provided at the front end of the outer wall; the fluidizing gas passages 414 are provided at the front end of the first cavity 24, and the driving gas passages 415 are provided at the rear end of the hollow annular shell 411.

[0047] Specifically, in this embodiment, both the fluidizing gas passage 414 and the driving gas passage 415 have 3 turns, and the through holes in each turn are evenly distributed along the outer wall of the hollow annular shell 411.

[0048] The hollow annular shell 411, located in front of the fluidizing gas passage 414, is provided with a second powder passage array 417 that penetrates both the inner and outer walls. For example... Figure 11 As shown, the second powder through hole array 417 on the inner wall of the hollow annular shell 411 and the second powder through hole array 417 on the outer wall are sealed and connected by an arc-shaped connecting plate 420, and the projection of each through hole of the second powder through hole array 417 on the outer wall of the combustion chamber 20 along the radial direction of the hollow annular shell 411 coincides with each through hole of the second powder through hole array 417.

[0049] An arc-shaped connecting plate 420 is integrally connected to the inner and outer walls of the hollow annular shell 411. Multiple holes, equal in number to the number of through holes in the second powder through-hole array 417, are distributed on the plate to connect the inner and outer walls of the hollow annular shell 411. Adjacent arc-shaped connecting plates 420 are spaced apart, allowing the incoming flow to pass between them.

[0050] Inside the hollow annular shell 411, there are vertically fixed first annular baffles 418 and second annular baffles 419 of the same size and with inner diameters equal to those of the straight section 21. The first annular baffles 418 and the second annular baffles 419 are located on both sides of the first powder through-hole array 26 along the axial direction of the straight section 21.

[0051] The function of the first annular baffle 418 and the second annular baffle 419 is to form a sealed channel between the second powder through-hole array 417 and the first powder through-hole array 26.

[0052] In one embodiment, the powder supply assembly 42 includes a hollow annular powder storage tank 421, a fluidizing cone 422, a fluidizing disc 423, an annular piston 424, and an annular adjusting sleeve 425.

[0053] The front end of the hollow annular powder storage tank 421 is open, and the rear end is sealed. The front end of the hollow annular powder storage tank 421 is located on the rear side of the fluidizing gas passage 414 along the axial direction of the combustion chamber 20, and the rear end is fixedly assembled with the annular fixed plate 412. The rear end of the hollow annular powder storage tank 421 is fixedly connected to the annular fixed plate 412 by bolts.

[0054] The larger opening sides of the fluidizing cone 422 and the fluidizing disk 423 both face the hollow annular powder storage tank 421, which is filled with boron-based powder fuel.

[0055] An annular adjusting sleeve 425 is disposed on the front side of the second powder through hole array 417 along the axial direction of the combustion chamber 20 and is fixedly sleeved on the hollow annular shell 411.

[0056] The front end of the fluidizing disc 423 is located between the second powder through-hole array 417 and the fluidizing gas through-hole 414, and is sleeved on the hollow annular shell 411. The rear end of the fluidizing disc 423 is axially fixedly connected to the front end face of the hollow annular powder storage tank 421. The front end of the fluidizing cone 422 is fixedly sleeved on the annular adjusting sleeve 425, and the rear end is axially fixedly connected to the front end face of the hollow annular powder storage tank 421 through a flange.

[0057] An annular piston 424 is disposed inside a hollow annular powder storage tank 421. Its outer side wall abuts against the inner side of the outer side wall of the hollow annular powder storage tank 421, and its inner side wall abuts against the inner side of the inner side wall of the hollow annular powder storage tank 421. Under the action of driving gas, it can slide along the axial direction of the hollow annular powder storage tank 421 towards the fluidizing disk 423. When the annular piston 424 slides, it can push the powder in the hollow annular powder storage tank 421 to slide out of the storage tank outlet. An annular sealing strip is embedded in the outer side wall of the annular piston 424.

[0058] In this embodiment, the area between the fluidizing cone 422 and the fluidizing disk 423 is the powder inlet cavity, the area between the fluidizing disk 423 and the head of the hollow annular powder storage box 421 is the fluidizing cavity, and the area between the piston and the tail of the hollow annular powder storage box 421 is the driving cavity.

[0059] To achieve adjustable piston thrust and fluidization degree, in one embodiment, the annular adjusting sleeve 425 includes a second annular support plate 4251 and an annular sealing plate 4252. The second annular support plate 4251 is fixedly sleeved on the hollow annular shell 411, and the front end of the annular sealing plate 4252 is integrally sleeved on the second annular support plate 4251. The cavity formed between the annular sealing plate 4252 and the hollow annular shell 411 is the powder flow rate adjusting cavity 4253.

[0060] A third annular support plate 4254 is vertically fixed to the inner side of the inner wall of the hollow annular powder storage box 421. The third annular support plate 4254 is located on the rear side of the drive air passage 415 along the combustion chamber 20 axis. The cavity formed between the inner wall of the hollow annular powder storage box 421 and the hollow annular shell 411 is an annular flow guiding and regulating cavity 4255.

[0061] The powder flow regulating cavity 4253 is provided with a first annular regulating plate 4256 that can slide along the axial direction of the hollow annular shell 411. The first annular regulating plate 4256 is sleeved on the hollow annular shell 411 and is used to adjust the overall opening of the second powder through hole array 417.

[0062] The annular flow guiding and regulating cavity 4255 is provided with a second annular regulating plate 4257 and a third annular regulating plate that can slide along the axial direction of the hollow annular shell 411. Both the second annular regulating plate 4257 and the third annular regulating plate are sleeved on the hollow annular shell 411. The second annular regulating plate 4257 is located close to the fluidizing plate 423. The second annular regulating plate 4257 is used to adjust the number of opening turns of the fluidizing air passage 414, and the third annular regulating plate is used to adjust the number of opening turns of the driving air passage 415.

[0063] Specifically, in this embodiment, both the powder flow regulating cavity 4253 and the annular flow guiding regulating cavity 4255 are equipped with several drive motors and several adjusting rods. The drive motors are electrically connected to the external control system, and the adjusting rods are connected to the annular adjusting plate. The drive motors drive the adjusting rods to stretch, thereby causing the annular adjusting plate to slide axially, thereby realizing the adjustment of the opening of the corresponding through hole.

[0064] In one embodiment, such as Figure 12 and Figure 13 As shown, the intake assembly 10 includes an intake pipe 12 and a guide cone 13, with the rear end of the intake pipe 12 fixedly connected to the front end of the straight section 21. The front end of the guide cone 13 extends out of the intake pipe 12, the middle part is fixedly connected to the inner wall of the front end of the intake pipe 12 through the rib 14 circumferentially assembled on its outer wall, and the end is located at the tail of the intake pipe 12. The gap between the intake pipe 12 and the guide cone 13 forms an intake channel. The solid fuel gas generator 11 is fixedly installed inside the guide cone 13. The end of the guide cone 13 is provided with a second gas passage hole 15. The gas outlet pipe of the solid fuel gas generator 11 is connected to the second gas passage hole 15. The injection plate 16 is fixedly installed inside the second gas passage hole 15. The injection plate 16 is provided with a number of injection holes 17.

[0065] like Figure 14 As shown, a plurality of injection holes 17 on the injection plate 16 penetrate through both the front and rear ends of the injection plate 16. The plurality of injection holes 17 are distributed in the central circular straight hole region 171 and the annular oblique hole region 172 fitted within the circular straight hole region. The plurality of injection holes 17 on the injection plate 16 have a honeycomb shape, which increases the uniformity of gas mixing and plays a rectifying role in order to generate stable combustion gas.

[0066] The injection direction of the injection hole 17 in the central circular straight hole region 171 is parallel to the axis of the straight section 21, while the injection direction of the injection hole 17 in the annular inclined hole region 172 is inclined at 30-45° from the axis of the straight section 21 towards its inner wall surface. The injection hole 17 in the annular inclined hole region 172 can realize the injection of fuel-rich gas into the wall of the combustion chamber 20.

[0067] In one embodiment, a Laval nozzle 28 is fitted inside the rear end of the expansion section 23. An annular connecting piece 29 is fixedly connected to the rear end face of the expansion section 23 by an explosive bolt. The inner diameter of the annular connecting piece 29 is smaller than the rear end inner diameter of the Laval nozzle 28. The rear end face of the Laval nozzle 28 is fixedly connected to the annular connecting piece 29 by the explosive bolt. The explosive bolt is electrically connected to an external control system.

[0068] The Laval nozzle 28 accelerates the subsonic airflow within the combustion chamber 20. At speeds greater than Mach 6, the combustion chamber 20 enters a scramjet mode. The external control system sends a separation command to the explosive bolt. Upon receiving the electrical command signal from the control system, the explosive bolt ignites the internal propellant through its built-in electric igniter. The bolt's load-bearing path is interrupted, and the connection structure rapidly separates under the action of preload or external springs and other auxiliary devices. The annular connecting piece 29 falls off, and the inner nozzle, lacking support, detaches from the expansion section 23 under the impact of the high-speed airflow.

[0069] Based on the same invention, this invention also provides a control method for a wide-speed-range flight boron-based powder fuel power plant, used to control the wide-speed-range flight boron-based powder fuel power plant of any of the above embodiments. The method includes: After the ejection initiation phase is completed, the electric igniter built into the explosive bolt is ignited by the external control system, and the igniter 37 of the annular fuel gas generator 30 is ignited by the external control system.

[0070] During the ejector initiation phase (0-3 Ma), the igniter 37 of the solid fuel gas generator 11 is ignited via an external control system, while the igniter 37 of the annular fuel gas generator 30 is deactivated. At 0-3 Ma, the power unit is in ejector mode. The solid fuel gas generator 11 inside the intake duct operates, and the igniter 37 ignites the oxygen-deficient solid propellant. The propellant undergoes initial combustion, and the resulting fuel-rich gas enters the combustion chamber 20 through the gas through-hole array 27. The fuel-rich gas generated by the gas generator forms a low-pressure zone at the end of the intake duct, drawing in air through the ejector effect to prepare for subsequent combustion. The drawn-in air mixes violently with the fuel-rich gas in the region near the end of the intake duct. The fuel-rich gas transfers momentum to the air, accelerating and compressing it, thereby increasing the total airflow pressure. A portion of the fuel-rich gas, guided by the injection holes 17 on the outer ring of the injection plate 16, is injected downstream towards the oxygen-rich propellant poured onto the wall of the combustion chamber 20, where it combusts and generates a high-temperature zone. In the mixed gas stream, unburned fuel and air undergo secondary combustion in the high-temperature zone formed downstream. The fuel-rich gas is mixed with the oxygen-rich gas produced by the oxygen-enriched propellant, resulting in secondary combustion and full heat release. The high-temperature, high-pressure gas generated by combustion is accelerated and ejected through the extension section and inner nozzle to generate thrust.

[0071] After the ejection initiation phase is completed, at the critical Mach 3, the electric igniter built into the explosive bolt is controlled by the external control system to ignite the Laval nozzle 28, causing it to detach. Simultaneously, the igniter 37 of the annular fuel gas generator 30 is ignited by the external control system. Between Mach 3 and 6, the power unit operates in the sub-fuel mode of a dual-mode ramjet engine. When the aircraft accelerates above Mach 3, the propellant in the front solid fuel gas generator 11 and poured onto the walls of the combustion chamber 20 is exhausted, and air is compressed from the intake duct into the isolation section and combustion chamber 20. The gas generated by the annular fuel gas generator 30 is injected into the combustion chamber 20 from between the first cavity 24 and the second cavity 25, mixing and burning with the supersonic flow in the second cavity 25 region to form a high-temperature recirculation zone. Powdered fuel, driven by the annular piston 424 and fluidized by the fluidizing gas, is introduced into the combustion chamber 20 from the front end of the first cavity 24, mixing with the supersonic flow in the first cavity. The mixed gas-solid two-phase flow is ignited and combusted in the second concave cavity 25 region, which is the high-temperature recirculation zone formed by the mixing and combustion of the fuel gas and the incoming flow. The high-temperature and high-pressure gas expands and does work through the expansion section, converting the chemical energy of the powdered fuel into kinetic energy, and the inner nozzle detaches.

[0072] When the temperature is greater than 6 Ma, the power unit is in the supersonic mode of the dual-mode ramjet engine. After the propellant in the annular fuel gas generator 30 is completely consumed, the total temperature of the incoming flow is relatively high. The powdered fuel is directly mixed and burned with the supersonic incoming flow in the two-stage concave combustion chamber 20 under the drive of the piston and the fluidization effect of the fluidizing gas. After expanding and doing work in the expansion section 23, it accelerates and generates thrust.

[0073] In addition, after the ejection start-up phase is completed, the flow rate of powder injection, driving gas, fluidizing gas and fuel-rich gas generated by the annular solid gas generator can be adjusted by the motor-driven annular regulating plate, thereby dynamically matching the operating conditions of the aircraft and achieving stable and adjustable thrust.

[0074] The method of the present invention controls a wide-speed-range flight boron-based powder fuel propulsion device, enabling the aircraft equipped with the propulsion device to smoothly switch between the ejection start-up phase, sub-burning mode, and superburning mode.

[0075] The embodiments described above are merely illustrative of several implementations of the present invention, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the appended claims.

Claims

1. A wide-speed-range flight boron-based powder fuel power plant, characterized in that, include: An intake assembly (10) is used to introduce and compress incoming air, and a solid fuel gas generator (11) is provided inside the intake assembly (10); The combustion chamber (20) is provided with an integrally connected straight section (21), injection section (22) and expansion section (23). The straight section (21) is axially fixedly connected to the rear end of the intake assembly (10). The injection section (22) has a first cavity (24) and a second cavity (25) arranged sequentially in the direction away from the intake assembly (10). The injection section (22) has a plurality of first powder through hole arrays (26) located in front of the first cavity (24) and a plurality of gas through hole arrays (27) located between the first cavity (24) and the second cavity (25). The plurality of first powder through hole arrays (26) and the plurality of gas through hole arrays (27) are uniformly distributed along the circumference of the injection section (22). An annular fuel gas generator (30) is used to supply fuel-rich gas to the injection section (22) through the gas through hole array (27). It is sleeved on the outside of the injection section (22), with its front end located behind the first powder through hole array (26) and fixedly connected to the outer wall of the injection section (22), and its rear end located at the end of the injection section (22). A pneumatic plug-type powder fuel supply assembly (40) is used to drive and fluidize boron-based powder fuel by means of incoming flow and to deliver boron-based powder fuel to the injection section (22) through the first powder through-hole array (26). The solid fuel gas generator (11) and the annular fuel gas generator (30) are both controlled by an external control system to control their ignition conditions.

2. The wide-speed-range flight boron-based powder fuel power plant according to claim 1, characterized in that, The annular fuel gas generator (30) includes a first annular cylindrical hollow shell (31), a second annular cylindrical hollow shell (32), an annular flow guide plate (33), a first annular solid fuel propellant grain (34), and a second annular solid fuel propellant grain (35); The first annular hollow shell (31) and the second annular hollow shell (32) are both fitted onto the injection section (22); The first annular hollow shell (31) and the second annular hollow shell (32) are open on opposite sides and sealed on opposite sides. The two end walls of the annular drainage concave plate (33) are axially fixedly connected to the outer walls of the first annular hollow shell (31) and the second annular hollow shell (32), respectively. The first annular solid fuel propellant grain (34) is filled inside the first annular hollow shell (31), and the second annular solid fuel propellant grain (35) is filled inside the second annular hollow shell (32); The gap between the inner walls of the first annular hollow shell (31) and the second annular hollow shell (32) forms a fuel-rich gas through hole (36), and the gap distance is greater than or equal to the width of the gas through hole array (27) along the engine axis; An igniter (37) is fixedly mounted on the inner side of the outer wall of the opening of the first annular hollow shell (31) and the second annular hollow shell (32), and the igniter (37) is electrically connected to the external control system.

3. The wide-speed-range flight boron-based powder fuel power plant according to claim 2, characterized in that, The pneumatic plug-type powder fuel supply assembly (40) includes an annular flow channel component (41) and a powder supply assembly (42); The annular flow guide channel component (41) is sleeved on the combustion chamber (20) to introduce the incoming flow and divide the incoming flow into fluidizing gas and driving gas to be delivered to the powder supply component (42); The powder supply assembly (42) is sleeved on the annular guide channel component (41) and is used to drive the internal boron-based powder fuel to be output by means of driving gas and input into the combustion chamber (20) through the first powder through hole array (26), and to atomize the boron-based powder fuel by means of fluidized gas during the output of boron-based powder fuel.

4. The wide-speed-range flight boron-based powder fuel power plant according to claim 3, characterized in that, The annular guide channel component (41) is provided with a hollow annular shell (411), an annular fixing disk (412) and a first annular support disk (413). The first annular support disk (413) is integrally connected to the front end of the hollow annular shell (411), and the annular fixing disk (412) is integrally connected to the rear end face of the hollow annular shell (411). The inner wall of the first annular support disk (413) is fixedly connected to the portion of the straight section (21) located at the front end of the first powder through-hole array (26). The inner diameters of the annular fixing disk (412) and the first annular support disk (413) are both smaller than the inner diameter of the inner wall of the hollow annular shell (411) and are equal to the outer diameter of the injection section (22). The outer wall of the hollow annular shell (411) is provided with at least two rings of evenly distributed fluidizing gas passages (414) and at least two rings of evenly distributed driving gas passages (415) along the circumferential direction, and at least one air inlet (416) is provided at the front end of the outer wall; the fluidizing gas passages (414) are provided at the front end of the first cavity (24), and the driving gas passages (415) are provided at the rear end of the hollow annular shell (411); The hollow annular shell (411) is provided with a second powder through hole array (417) in the part in front of the fluidizing gas through hole (414) that penetrates the inner wall and the outer wall; the second powder through hole array (417) on the inner wall of the hollow annular shell (411) and the second powder through hole array (417) on the outer wall are sealed and connected by an arc-shaped connecting plate (420), and the projection of each through hole of the second powder through hole array (417) on the outer wall of the combustion chamber (20) along the radial direction of the hollow annular shell (411) coincides with each through hole of the second powder through hole array (417); The hollow annular shell (411) has a first annular baffle (418) and a second annular baffle (419) of the same size and with an inner diameter equal to that of the straight section (21) vertically fixed inside. The first annular baffle (418) and the second annular baffle (419) are respectively located on both sides of the first powder through hole array (26) along the axial direction of the straight section (21).

5. The wide-speed-range flight boron-based powder fuel power plant according to claim 4, characterized in that, The powder supply assembly (42) includes a hollow annular powder storage tank (421), a fluidizing cone (422), a fluidizing disc (423), an annular piston (424), and an annular adjusting sleeve (425); The front end face of the hollow annular powder storage box (421) is open and the rear end face is sealed. The front end face of the hollow annular powder storage box (421) is located on the rear side of the fluidizing gas passage (414) along the axial direction of the combustion chamber (20), and the rear end face is fixedly assembled with the annular fixed plate (412). The larger opening sides of both the fluidizing cone (422) and the fluidizing disk (423) face the hollow annular powder storage tank (421); The annular adjusting sleeve (425) is disposed on the front side of the second powder through hole array (417) along the axial direction of the combustion chamber (20) and is fixedly sleeved on the hollow annular shell (411); The front end of the fluidizing disk (423) is located between the second powder through hole array (417) and the fluidizing gas through hole (414), and is sleeved on the hollow annular shell (411). The rear end of the fluidizing disk (423) is axially fixedly connected to the front end face of the hollow annular powder storage tank (421). The front end of the fluidizing cone (422) is fixedly sleeved on the annular adjusting sleeve (425), and the rear end is axially fixedly connected to the front end face of the hollow annular powder storage tank (421). The annular piston (424) is disposed inside the hollow annular powder storage box (421). Its outer side wall abuts against the inner side of the outer side wall of the hollow annular powder storage box (421), and its inner side wall abuts against the inner side of the inner side wall of the hollow annular powder storage box (421). It can slide along the axial direction of the hollow annular powder storage box (421) toward the fluidizing plate (423) under the action of the driving gas.

6. The wide-speed-range flight boron-based powder fuel power plant according to claim 5, characterized in that, The annular regulating sleeve (425) includes a second annular support plate (4251) and an annular sealing plate (4252). The second annular support plate (4251) is fixedly sleeved on the hollow annular shell (411). The front end of the annular sealing plate (4252) is integrally sleeved on the second annular support plate (4251). The cavity formed between the annular sealing plate (4252) and the hollow annular shell (411) is a powder flow regulating cavity (4253). The inner wall of the hollow annular powder storage tank (421) is vertically fixed with a third annular support plate (4254). The third annular support plate (4254) is located on the rear side of the drive air passage (415) along the axial direction of the combustion chamber (20). The cavity formed between the inner wall of the hollow annular powder storage tank (421) and the hollow annular shell (411) is an annular flow guiding and regulating cavity (4255). The powder flow regulating cavity (4253) is provided with a first annular regulating plate (4256) that can slide along the axial direction of the hollow annular shell (411). The first annular regulating plate (4256) is sleeved on the hollow annular shell (411) and is used to adjust the overall opening of the second powder through hole array (417). The annular flow guiding and regulating cavity (4255) is provided with a second annular regulating plate (4257) and a third annular regulating plate that can slide along the axial direction of the hollow annular shell (411). The second annular regulating plate (4257) and the third annular regulating plate are both sleeved on the hollow annular shell (411). The second annular regulating plate (4257) is located close to the fluidizing plate (423). The second annular adjusting plate (4257) is used to adjust the number of opening turns of the fluidizing air passage (414), and the third annular adjusting plate is used to adjust the number of opening turns of the driving air passage (415).

7. The wide-speed-range flight boron-based powder fuel power plant according to claim 6, characterized in that, The intake assembly (10) includes an intake pipe (12) and a guide cone (13), and the rear end of the intake pipe (12) is fixedly connected to the front end of the straight section (21); The front end of the guide cone (13) extends from the air intake pipe (12), the middle part is fixedly connected to the inner wall of the front end of the air intake pipe (12) through the rib (14) circumferentially assembled on its outer wall, and the end is located at the tail of the air intake pipe (12). The gap between the air inlet pipe (12) and the guide cone (13) forms an air inlet channel. The solid fuel gas generator (11) is fixedly assembled inside the guide cone (13). The end of the guide cone (13) is provided with a second gas through hole (15). The gas outlet pipe of the solid fuel gas generator (11) is connected to the second gas through hole (15). The second gas passage (15) is fixedly fitted with a spray plate (16), and the spray plate (16) is provided with a plurality of spray holes (17).

8. The wide-speed-range flight boron-based powder fuel power plant according to claim 7, characterized in that, The rear end of the expansion section (23) is equipped with a Laval nozzle (28). The rear end face of the expansion section (23) is fixedly connected to an annular connecting piece (29) by an explosive bolt. The inner diameter of the annular connecting piece (29) is smaller than the rear end inner diameter of the Laval nozzle (28). The rear end face of the Laval nozzle (28) is fixedly connected to the annular connecting piece (29) by an explosive bolt. The explosive bolt is electrically connected to the external control system.

9. The wide-speed-range flight boron-based powder fuel power plant according to claim 8, characterized in that, The injection plate (16) has several injection holes (17) that penetrate the front and rear ends of the injection plate (16). The injection holes (17) are distributed in the middle circular straight hole area (171) and the annular oblique hole area (172) fitted in the circular straight hole area. The injection direction of the injection hole (17) in the intermediate circular straight hole region (171) is parallel to the axis of the straight section (21), and the injection direction of the injection hole (17) in the annular oblique hole region (172) is inclined at 30-45° from the axis of the straight section (21) toward its inner wall surface.

10. A control method for a wide-speed-range flight boron-based powder fuel power plant, used to control the wide-speed-range flight boron-based powder fuel power plant according to any one of claims 1 to 9, characterized in that, During the ejector start-up phase, the igniter (37) of the solid fuel gas generator (11) is ignited by the external control system, and the igniter (37) of the annular fuel gas generator (30) is turned off. After the ejection initiation phase is completed, the electric igniter built into the explosive bolt is ignited by the external control system, and the igniter (37) of the annular fuel gas generator (30) is ignited by the external control system.

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