High-mobility transmedia ramjet and vehicle

Abstract

The present application relates to the technical field of cross-medium ramjet engine and aircraft, in particular to high-mobility cross-medium ramjet engine and aircraft, comprising an engine structure, the engine structure comprises an engine shell, a communication control valve pipe, a control atomizer, a vent valve seat and an airflow passage pipe, the rear end of the engine shell is provided with the communication control valve pipe, the rear end of the communication control valve pipe is provided with the control atomizer in communication, the rear end of the control atomizer is provided with the vent valve seat, the rear end of the vent valve seat is provided with the airflow passage pipe in communication, the engine structure further comprises a powder fuel storage, a first communication control pipe, a second communication control pipe, a combustion chamber, a combined tail nozzle, a closed adjusting block and a protection ring block, the control atomizer and the airflow passage pipe are provided in communication with the combustion chamber, and the rear end of the combustion chamber is provided with the combined tail nozzle, through the structure, cross-medium driving work is facilitated.

Description

Technical Field

[0001] This invention relates to the field of transmedium ramjet engines and aircraft technology, specifically to high-maneuverability transmedium ramjet engines and aircraft. Background Technology

[0002] A cross-medium vehicle is a new type of aircraft or navigation equipment that can navigate in two or more different media. It can freely switch between the two media, such as air and water. The advantages of cross-medium vehicles are very obvious. Traditional single-medium aircraft have a relatively fixed flight medium, and naturally the opponent has relatively clear countermeasures. Cross-medium vehicles have better flexibility and improved adaptability.

[0003] As the closest existing technology, Chinese patent publication number CN109098891A relates to a cross-medium ramjet engine based on solid propulsion. The flow channels are uniformly arranged on the outer circumference of the gas generator, and the flow channels and gas generator are integrated into a single design, ensuring both normal engine operation and the streamlined shape of the gas generator. The flow channel baffles are driven by a baffle drive motor, controlling the opening and closing of the upper and lower flow channel baffles to switch between air intake and water intake modes. A parallel flow channel design integrates the air intake and water intake channels of the cross-medium ramjet engine. By controlling the start-up, shutdown, and movement speed of the powder supply device, fuel delivery, stopping, and flow control can be achieved, thus better realizing the controllable supply of powdered fuel and meeting the gas flow requirements during different modes and thrust adjustments.

[0004] Currently, high-maneuverability cross-medium ramjet engines, aircraft, and the structures mentioned above cannot control flight dynamics to a greater extent during use, which can lead to problems with rapid state switching. Therefore, improvements are needed to address these issues. Summary of the Invention

[0005] To address the problems in the prior art, the present invention provides a high-maneuverability transmedium ramjet engine and an aircraft.

[0006] The technical solution adopted by the present invention to solve its technical problem is: a high-maneuverability transmedium ramjet engine and aircraft, including an engine structure, the engine structure including an engine casing, a connecting control valve pipe, a control atomizer, a ventilation valve seat, and an airflow channel pipe, the rear end of the engine casing is provided with a connecting control valve pipe, the rear end of the connecting control valve pipe is connected to a control atomizer, the rear end of the control atomizer is provided with a ventilation valve seat, and the rear end of the ventilation valve seat is connected to an airflow channel pipe;

[0007] The engine structure also includes a powdered fuel storage device, a first connecting control pipe, a second connecting control pipe, a combustion chamber, a combined tailpipe, a closing adjustment block, and a protective ring block. The regulating atomizer and airflow passage pipe are both connected to the combustion chamber. The combined tailpipe is located at the rear end of the combustion chamber, and a protective ring block is fixedly connected inside the combined tailpipe. The closing adjustment block is controlled by a motor within the protective ring block, and its front end is hinged to the combined tailpipe. The second connecting control pipe is located at the front end of the combustion chamber, and the first connecting control pipe is located at the front end of the second connecting control pipe. A powdered fuel storage device is installed at the front end of the first connecting control pipe. The powdered fuel storage device, the first connecting control pipe, and the second connecting control pipe are fixed and limited by the engine casing. This structural design facilitates the intake of fuel... The engine is driven and controlled by a connecting regulating valve and a regulating atomizer on the engine casing. The connecting regulating valve introduces atomized water through the regulating atomizer, allowing the atomized water to reach the combustion chamber. At this time, the powdered fuel storage device controls the fuel to be conducted through the first and second connecting regulating pipes to the combustion chamber, where it is ignited. Then, the combined tail nozzle controls the drive operation. A closed adjusting block is elastically set on the protective ring block. Under pressure, the closed adjusting block can open; when there is no pressure, the closed adjusting block can close, serving the purpose of protecting the internal structure of the engine. When the engine structure is in the air, the ventilation valve seat introduces gas through the airflow channel pipe, and the fuel is guided through the powdered fuel storage device to the first and second connecting regulating pipes, where it is ignited in the combustion chamber to perform the drive operation.

[0008] An aircraft includes an aircraft structure, the lower end of which is fixedly connected to an engine structure, and the aircraft structure controls flight adjustment through the engine structure.

[0009] Specifically, the aircraft structure includes an aircraft component, a first state adjustment component, and a second state adjustment component. The first state adjustment component is movably hinged to one side of the aircraft component, and the second state adjustment component is movably hinged to the other side of the aircraft component. The first state adjustment component and the second state adjustment component have the same structure.

[0010] Specifically, the aircraft components include an aircraft tail fin, a probe head, a support block, a fixed mounting frame, a combined cabin, a first propeller mount, and a second propeller mount. The side end of the probe head is fixed by the support block. The rear ends of the probe head and the support block are fixedly connected to the combined cabin. The lower end of the combined cabin is fixedly connected to the fixed mounting frame, which is used for the fixed assembly of the engine structure. The rear end of the combined cabin is fixedly connected to the aircraft tail fin. The center rear end of the aircraft tail fin is fixedly connected to the first propeller mount. The rear end of the first propeller mount is fixedly connected to the second propeller mount. Propellers are rotatably mounted inside the first and second propeller mounts, and the propellers rotate relative to the combined cabin. A control motor is provided inside the combined cabin to control the rotation of the propellers within the first and second propeller mounts.

[0011] Specifically, the first state adjustment component includes a fixed side frame, a fixed connecting column, and a fixed mounting block. The fixed mounting block is fixedly connected to the center of the fixed connecting column, and the fixed side frame is fixedly connected to the lower end of the fixed connecting column. The fixed side frame is fixedly connected to the fixed mounting block through the fixed connecting column.

[0012] Specifically, the first state adjustment component further includes a connecting wing plate, an electro-hydraulic telescopic rod, a driven telescopic adjustment frame, and a hinged end frame. The fixed side frame is hinged to the hinged end frame, and the upper end of the hinged end frame is limitedly connected to the connecting wing plate. The center of the connecting wing plate is hinged to the electro-hydraulic telescopic rod, and the other end of the electro-hydraulic telescopic rod is hinged to the fixed side frame. The fixed side frame has a driven telescopic adjustment frame located at the lower end of the electro-hydraulic telescopic rod, and the driven telescopic adjustment frame is hinged to the fixed side frame. Through the structural design of the aircraft, state switching is convenient. The aircraft component is equipped with a first state adjustment component and a second state adjustment component. When in water, the first state adjustment component and the second state adjustment component retract to reduce drag. When in the air... At this time, the first and second state adjustment components are open, enabling floating operation. The first and second propeller mounts are equipped with propellers, which can work together to provide stable transmission in water. The fixed side frame in the first state adjustment component is supported and fixed by a fixed mounting block. A connecting wing plate is hinged to the fixed side frame through a hinged end frame. With the extension and retraction of the electro-hydraulic telescopic rod, the connecting wing plate can be rotated and adjusted to change its angle. The driven telescopic adjustment frame is located at the lower end of the electro-hydraulic telescopic rod, which can play an auxiliary role and improve the stability of the connecting wing plate. The probe head is equipped with a probe for detection and identification. The fixed mounting frame facilitates the fixation of the engine structure. The tail fin of the aircraft is set at the rear of the combined cabin, which provides support and protection.

[0013] Specifically, the fixed mounting block is fixedly connected to the combined cabin, the probe head, and the support block. The probe head has an arc-shaped structure, the tail fin of the aircraft is symmetrically distributed in a conical shape, and the fixed mounting frame has a mounting hole at its center, which is fixedly connected to the engine structure by rivets.

[0014] Specifically, the electro-hydraulic telescopic rod extends and retracts to push the connecting wing plate to rotate and adjust around the hinged end frame. The driven telescopic adjustment frame follows the connecting wing plate and is stretched and adjusted accordingly. The driven telescopic adjustment frame, the connecting wing plate, and the fixed side frame are all hinged.

[0015] Specifically, the fixed side frame has a dual-piece design, the probe head is equipped with a probe, and the connecting wing plate has two adjustable forms. The connecting wing plate can fit the fixed side frame in an underwater posture.

[0016] Specifically, the connecting wing plate can also be moved away from the fixed side frame to achieve a flight attitude, and the first propeller mount is provided with a groove for diversion.

[0017] The beneficial effects of this invention are:

[0018] First, this invention facilitates state switching through the structural design of the aircraft. The aircraft components are equipped with a first state adjustment component and a second state adjustment component. In water, these components retract to reduce drag. In the air, they extend to enable buoyancy. Propellers are housed in the first and second propeller mounts for stable transmission in water. The fixed side frame within the first state adjustment component is supported and fixed by a fixed mounting block. A connecting wing plate is hinged to the fixed side frame via a hinged end frame. The connecting wing plate can be rotated and adjusted by the extension and retraction of an electro-hydraulic telescopic rod, changing its angle. A driven telescopic adjustment bracket located at the lower end of the electro-hydraulic telescopic rod provides auxiliary support and improves the stability of the connecting wing plate. A probe is installed within the detection head for detection and identification. The fixed mounting bracket facilitates the fixation of the engine structure. A tail fin is located at the rear of the combined cabin for support and protection. This structural design achieves rapid state switching.

[0019] Second, this invention facilitates drive control through the structural design of the engine. A connecting regulating valve and a regulating atomizer are installed on the engine casing. The connecting regulating valve, through the regulating atomizer, introduces atomized water, ensuring it reaches the combustion chamber. The powder fuel storage unit controls the fuel to be conducted through the first and second connecting control pipes, guiding it to the combustion chamber where it ignites. The combined tailpipe then controls the drive operation. A flexible closing adjustment block is elastically installed on the protective ring block. Under pressure, the closing adjustment block opens; without pressure, it closes, serving as a structural protection mechanism within the engine. When the engine is in the air, the ventilation valve seat introduces gas through the airflow channel pipe, and the fuel, through the powder fuel storage unit, is guided to the first and second connecting control pipes, igniting in the combustion chamber for drive operation. Attached Figure Description

[0020] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0021] Figure 1 This is a three-dimensional structural diagram of the main body from a frontal perspective in this invention;

[0022] Figure 2 This is a split view of the main body of the present invention;

[0023] Figure 3 This is a three-dimensional structural diagram of the aircraft structure from a frontal view in this invention;

[0024] Figure 4 This is a three-dimensional structural diagram of the aircraft component from a frontal view in this invention;

[0025] Figure 5 This is a three-dimensional structural diagram of the front view of the first state adjustment component in this invention;

[0026] Figure 6 This is a three-dimensional structural diagram of the first state adjustment component from the rear view in this invention.

[0027] Figure 7 This is a three-dimensional structural diagram of the engine structure from a frontal view in this invention;

[0028] Figure 8 This is a three-dimensional sectional view of the engine structure in this invention.

[0029] In the diagram: 1-Aircraft structure, 2-Engine structure, 3-Aircraft component, 4-First state adjustment component, 5-Second state adjustment component, 6-Aircraft tail fin, 7-Detector head, 8-Support block, 9-Fixed mounting bracket, 10-Combined cabin, 11-First propeller mount, 12-Second propeller mount, 13-Fixed side frame, 14-Fixed connecting column, 15-Fixed mounting block, 16-Connecting wing plate, 17-Electro-hydraulic telescopic rod, 18-Driven telescopic adjustment frame, 19-Hinged end frame, 20-Engine casing, 21-Connecting control valve pipe, 22-Control atomizer, 23-Ventilation valve seat, 24-Airflow channel pipe, 25-Powder fuel storage, 26-First connecting control pipe, 27-Second connecting control pipe, 28-Combustion chamber, 29-Combined tail nozzle, 31-Closed adjustment block, 32-Protective ring block. Detailed Implementation

[0030] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0031] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate for the embodiments of this application described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0032] The invention will be further described below with reference to the accompanying drawings.

[0033] Example

[0034] like Figure 1-8As shown, the high-mobility transmedium ramjet engine and aircraft of the present invention include an engine structure 2. The engine structure 2 includes an engine casing 20, a connecting control valve pipe 21, a control atomizer 22, a ventilation valve seat 23, and an airflow channel pipe 24. The engine casing 20 is provided with a connecting control valve pipe 21 at its rear end. The connecting control valve pipe 21 is connected to the control atomizer 22 at its rear end. The control atomizer 22 is provided with a ventilation valve seat 23 at its rear end. The ventilation valve seat 23 is connected to the airflow channel pipe 24 at its rear end.

[0035] Engine structure 2 also includes a powdered fuel storage device 25, a first connecting control pipe 26, a second connecting control pipe 27, a combustion chamber 28, a combined tail nozzle 29, a closing adjustment block 31, and a protective ring block 32. The regulating atomizer 22 and the airflow passage pipe 24 are both connected to the combustion chamber 28. The combined tail nozzle 29 is located at the rear end of the combustion chamber 28, and a protective ring block 32 is fixedly connected inside the combined tail nozzle 29. The closing adjustment block 31 is controlled by a motor within the protective ring block 32. The front end of the closing adjustment block 31 is hinged to the combined tail nozzle 29. The second connecting control pipe 27 is located at the front end of the combustion chamber 28, and the first connecting control pipe 26 is located at the front end of the second connecting control pipe 27. The powdered fuel storage device 25 is installed at the front end of the first connecting control pipe 26. The powdered fuel storage device 25, the first connecting control pipe 26, and the second connecting control pipe 27 are fixed and limited by the engine housing 20. The engine housing 20 within engine structure 2 is equipped with a connecting regulating valve pipe 21, a regulating atomizer 22, a ventilation valve seat 23, and an airflow passage pipe 24. 4. The connecting control valve pipe 21, the controlling atomizer 22, the ventilation valve seat 23, and the airflow channel pipe 24 are used separately. When underwater, the connecting control valve pipe 21 and the controlling atomizer 22 are activated, while the ventilation valve seat 23 and the airflow channel pipe 24 are closed. Water is conducted through the connecting control valve pipe 21 and the controlling atomizer 22, undergoing atomization, and then discharged to the combustion chamber 28. Fuel is introduced into the powder fuel storage device 25, allowing the fuel to be conducted through the first connecting control pipe 26 and the second connecting control pipe 27 to reach the combustion chamber. In the combustion chamber 28, the combustion reaction is controlled, and the exhaust can drive the closed regulating block 31 to move, ensuring uniform emission performance. When in the air, the ventilation valve seat 23 and the airflow channel pipe 24 are activated, the connecting regulating valve pipe 21 and the regulating atomizer 22 are closed, and the gas reaches the position of the combustion chamber 28. The powder fuel storage 25 guides the fuel to the combustion chamber 28 through the first connecting control pipe 26 and the second connecting control pipe 27, where it is reacted and processed, thereby driving the aircraft structure 1 to move.

[0036] The aircraft includes an aircraft structure 1, with an engine structure 2 fixedly connected to the lower end of the aircraft structure 1. The aircraft structure 1 controls flight regulation through the engine structure 2.

[0037] The aircraft structure 1 includes an aircraft component 3, a first state adjustment component 4, and a second state adjustment component 5. The first state adjustment component 4 is movably hinged on one side of the aircraft component 3, and the second state adjustment component 5 is movably hinged on the other side of the aircraft component 3. The first state adjustment component 4 and the second state adjustment component 5 have the same structure.

[0038] The aircraft component 3 includes an aircraft tail fin 6, a probe head 7, a support block 8, a fixed mounting frame 9, a combined cabin 10, a first propeller mount 11, and a second propeller mount 12. The side end of the probe head 7 is fixed by the support block 8. The rear ends of the probe head 7 and the support block 8 are fixedly connected to the combined cabin 10. The lower end of the combined cabin 10 is fixedly connected to the fixed mounting frame 9, which is used for the fixed assembly of the engine structure 2. The rear end of the combined cabin 10 is fixedly connected to the aircraft tail fin 6. The center rear end of the aircraft tail fin 6 is fixedly connected to the first propeller mount 11. The rear end of the first propeller mount 11 is fixedly connected to the second propeller mount 12. Propellers are rotatably installed in the first propeller mount 11 and the second propeller mount 12, and the propellers rotate relative to the combined cabin 10. The combined cabin 10 is equipped with a control motor to control the propellers to rotate in the first propeller mount 11 and the second propeller mount 12.

[0039] The first state adjustment component 4 includes a fixed side frame 13, a fixed connecting column 14, and a fixed mounting block 15. The fixed mounting block 15 is fixedly connected to the center of the fixed connecting column 14, and the fixed side frame 13 is fixedly connected to the lower end of the fixed connecting column 14. The fixed side frame 13 is fixedly connected to the fixed mounting block 15 through the fixed connecting column 14.

[0040] The first state adjustment component 4 also includes a connecting wing plate 16, an electro-hydraulic telescopic rod 17, a driven telescopic adjustment frame 18, and a hinged end frame 19. The fixed side frame 13 is hinged to the hinged end frame 19, with the connecting wing plate 16 connected to its upper end. The electro-hydraulic telescopic rod 17 is hinged to the center of the connecting wing plate 16, and the other end of the electro-hydraulic telescopic rod 17 is hinged to the fixed side frame 13. The driven telescopic adjustment frame 18 is located at the lower end of the electro-hydraulic telescopic rod 17 on the fixed side frame 13, and is hinged to the fixed side frame 13. The aircraft structure 1 performs attitude adjustment work, with the aircraft component 3 within the aircraft structure 1 providing support. The first state adjustment component 4 and the second state adjustment component 5 are located on the side of the aircraft component 3, enabling flight adjustment work. When in flight mode, the first state adjustment component 4 and the second state adjustment component 5... When component 5 is opened, it enables flight assistance functions. The probe 7 inside component 3 performs sensing and detection through the probe. The support block 8, probe 7, and combined cabin 10 are fixed. The lower end of the combined cabin 10 is equipped with a fixed mounting bracket 9, which supports and fixes the engine structure 2. The rear end of the combined cabin 10 is equipped with the aircraft tail 6, which can maintain balance. The combined cabin 10 can control the propeller rotation through the motor. The propeller rotates in the first propeller seat 11 and the second propeller seat 12 to perform underwater auxiliary power control. During flight, the fixed side frame 13, fixed connecting column 14, and fixed mounting block 15 are fixed. The electro-hydraulic telescopic rod 17 is telescopically adjusted, pushing the connecting wing plate 16 to move, so that the connecting wing plate 16 rotates around the hinged end frame 19. When the connecting wing plate 16 moves, it can drive the driven telescopic adjustment frame 18 to adjust and maintain stable performance.

[0041] The fixed mounting block 15 is fixedly connected to the combined cabin 10, the probe head 7, and the support block 8. The probe head 7 is set in an arc-shaped structure, and the tail fin 6 of the aircraft is symmetrically distributed in a conical shape. The fixed mounting bracket 9 has a mounting hole in the center, and the mounting hole is fixedly connected to the engine structure 2 by rivets.

[0042] The electro-hydraulic telescopic rod 17 extends and retracts, pushing the connecting wing plate 16 to rotate and adjust around the hinged end frame 19. The driven telescopic adjustment frame 18 follows the connecting wing plate 16 and is stretched and adjusted accordingly. The driven telescopic adjustment frame 18, the connecting wing plate 16, and the fixed side frame 13 are all hinged.

[0043] The fixed side frame 13 has a dual-plate design. The probe is installed inside the probe head 7. The connecting wing plate 16 has two adjustable forms. The connecting wing plate 16 can fit the fixed side frame 13 in an underwater posture.

[0044] The connecting wing plate 16 can also be moved away from the fixed side frame 13 to maintain a flight attitude. The first propeller mount 11 is provided with a groove for diverting air.

[0045] The working principle is as follows: During use, the aircraft structure 1 and engine structure 2 are fixed together. The engine structure 2 provides the driving function, while the aircraft structure 1 performs attitude adjustment. The aircraft component 3 within the aircraft structure 1 provides support. The side of the aircraft component 3 is equipped with a first state adjustment component 4 and a second state adjustment component 5, enabling flight adjustment. During flight, the first state adjustment component 4 and the second state adjustment component 5 are activated, providing flight assistance functions. The probe 7 within the aircraft component 3 performs sensing detection. The support block 8, the probe 7, and the combined cabin 10 are fixed together. The lower end of the cabin 10 is equipped with a fixed mounting bracket 9, which supports and fixes the engine structure 2. The rear end of the combined cabin 10 is equipped with a tail fin 6 to maintain balance. The combined cabin 10 can control the propeller rotation via a motor. The propeller rotates within the first propeller mount 11 and the second propeller mount 12 to perform underwater auxiliary power control. During flight, the fixed side frame 13, fixed connecting column 14, and fixed mounting block 15 are fixed, and the electro-hydraulic telescopic rod 17 is extended and adjusted to push the connecting wing plate 16 to move, causing the connecting wing plate 16 to rotate around the hinged end frame 19. When the connecting wing plate 16 moves, it can... The driven telescopic adjustment frame 18 is adjusted to maintain stable performance. The engine casing 20 within the engine structure 2 is equipped with a connecting control valve pipe 21, a control atomizer 22, a ventilation valve seat 23, and an airflow passage pipe 24. The connecting control valve pipe 21 and control atomizer 22 are used separately from the ventilation valve seat 23 and airflow passage pipe 24. When submerged underwater, the connecting control valve pipe 21 and control atomizer 22 are activated, while the ventilation valve seat 23 and airflow passage pipe 24 are closed. Water is conducted through the connecting control valve pipe 21 and control atomizer 22, undergoing atomization, and then discharged to the combustion chamber 28. The powdered fuel storage device 25 then introduces fuel. The fuel is conducted through the first connecting control pipe 26 and the second connecting control pipe 27 to the combustion chamber 28, controlling the combustion reaction. The exhaust can drive the closed regulating block 31 to move, ensuring uniform emission performance. When in the air, the ventilation valve seat 23 and the airflow channel pipe 24 are activated, and the connecting regulating valve pipe 21 and the regulating atomizer 22 are closed. The gas reaches the position of the combustion chamber 28, and the powder fuel storage 25 guides the fuel through the first connecting control pipe 26 and the second connecting control pipe 27 to the combustion chamber 28, where it reacts and is processed, thereby driving the aircraft structure 1 to move and complete the work.

[0046] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A high-mobility, cross-medium ramjet engine, characterized by: The engine structure (2) comprises an engine shell (20), a communication control valve pipe (21), a control atomizer (22), a ventilation valve seat (23) and an airflow channel pipe (24), the rear end of the engine shell (20) is provided with the communication control valve pipe (21), the rear end of the communication control valve pipe (21) is provided with the control atomizer (22), the rear end of the control atomizer (22) is provided with the ventilation valve seat (23), and the rear end of the ventilation valve seat (23) is provided with the airflow channel pipe (24); The engine structure (2) further comprises a powder fuel storage (25), a first communication control pipe (26), a second communication control pipe (27), a combustion chamber (28), a combined tail nozzle (29), a closed adjusting block (31) and a protection ring block (32), the control atomizer (22) and the airflow channel pipe (24) are provided in communication with the combustion chamber (28), the rear end of the combustion chamber (28) is provided with the combined tail nozzle (29), the combined tail nozzle (29) is fixedly connected with the protection ring block (32) inside, the protection ring block (32) is movably connected with the closed adjusting block (31) through a motor, the front end of the closed adjusting block (31) is movably connected with the combined tail nozzle (29), the front end of the combustion chamber (28) is provided with the second communication control pipe (27), the front end of the second communication control pipe (27) is provided with the first communication control pipe (26), the front end of the first communication control pipe (26) is provided with the powder fuel storage (25), and the powder fuel storage (25), the first communication control pipe (26) and the second communication control pipe (27) are fixedly positioned by the engine shell (20).

2. An aircraft employing the high-mobility, trans-medium, ramjet engine of claim 1, characterized by: The aircraft structure (1) comprises an aircraft structure (1), the lower end of which is fixedly connected with the engine structure (2), and the aircraft structure (1) controls flight adjustment through the engine structure (2).

3. The aircraft of claim 2, wherein: The aircraft structure (1) comprises an aircraft component (3), a first state adjusting component (4) and a second state adjusting component (5), one side of the aircraft component (3) is movably connected with the first state adjusting component (4), the other side of the aircraft component (3) is movably connected with the second state adjusting component (5), and the first state adjusting component (4) and the second state adjusting component (5) have the same structure.

4. The aircraft of claim 3, wherein: The aircraft component (3) comprises an aircraft tail wing (6), a probe head (7), a support seat block (8), a fixed mounting frame (9), a combined engine nacelle (10), a first propeller seat (11) and a second propeller seat (12), the side end of the probe head (7) is fixed through the support seat block (8), the rear end of the probe head (7) and the support seat block (8) is fixedly connected with the combined engine nacelle (10), the lower end of the combined engine nacelle (10) is fixedly connected with the fixed mounting frame (9), the fixed mounting frame (9) is used for fixed combination of the engine structure (2), the rear end of the combined engine nacelle (10) is fixedly connected with the aircraft tail wing (6), the central rear end of the aircraft tail wing (6) is fixedly connected with the first propeller seat (11), the rear end of the first propeller seat (11) is fixedly connected with the second propeller seat (12), the first propeller seat (11) and the second propeller seat (12) are rotatably provided with propellers, and the propellers rotate relative to the combined engine nacelle (10), and the combined engine nacelle (10) is provided with a control motor to control the rotation of the propellers in the first propeller seat (11) and the second propeller seat (12).

5. The aircraft of claim 4, wherein: The first state adjusting component (4) comprises a fixed side frame (13), a fixed connecting column (14) and a fixed mounting block (15), the center of the fixed mounting block (15) is fixedly connected with the fixed connecting column (14), the lower end of the fixed connecting column (14) is fixedly connected with the fixed side frame (13), and the fixed side frame (13) is fixedly connected with the fixed mounting block (15) through the fixed connecting column (14).

6. The aircraft of claim 5, wherein: The first state adjusting component (4) further comprises a connecting wing plate (16), an electric control hydraulic telescopic rod (17), a driven telescopic adjusting frame (18) and a hinged end frame (19), the fixed side frame (13) is hingedly provided with the hinged end frame (19), the upper end of the hinged end frame (19) is limitingly connected with the connecting wing plate (16), the center of the connecting wing plate (16) is hingedly provided with the electric control hydraulic telescopic rod (17), the other end of the electric control hydraulic telescopic rod (17) is hingedly provided with the fixed side frame (13), and the fixed side frame (13) is provided with the driven telescopic adjusting frame (18) at the lower end position of the electric control hydraulic telescopic rod (17), and the driven telescopic adjusting frame (18) is hingedly provided with the fixed side frame (13).

7. The aircraft of claim 6, wherein: The fixed mounting block (15) is fixedly connected with the combined engine nacelle (10), the probe head (7) and the support seat block (8), the probe head (7) is provided in a circular arc structure, the aircraft tail wing (6) is symmetrically distributed in a conical shape, the center of the fixed mounting frame (9) is provided with a mounting hole, and the mounting hole is fixedly connected with the engine structure (2) through a rivet.

8. The aircraft of claim 7, wherein: The electric control hydraulic telescopic rod (17) is telescoped to push the connecting wing plate (16) to rotate and adjust around the hinged end frame (19), the driven telescopic adjusting frame (18) is driven to stretch and adjust with the connecting wing plate (16), and the driven telescopic adjusting frame (18), the connecting wing plate (16) and the fixed side frame (13) are all hingedly provided.

9. The aircraft of claim 8, wherein: The fixed side frame (13) is a double piece design, the probe head (7) is provided with a probe, the connecting wing plate (16) has two shape adjustments, the connecting wing plate (16) can be attached to the fixed side frame (13) to be in a water attitude.

10. The aircraft of claim 9, wherein: The connecting wing plate (16) can also be away from the fixed side frame (13) to be in a flying attitude, the first propeller seat (11) is provided with a groove body, which can perform drainage work.

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