High-maneuverability cross-medium ramjet engine and aircraft

Abstract

The invention relates to the technical field of cross-medium ramjet engines and aircrafts, in particular to a high-maneuverability cross-medium ramjet engine and aircraft which comprises an engine structure, and the engine structure comprises an engine protection shell, a communication regulation and control valve pipe, a regulation and control atomizer, a ventilation valve seat and an airflow channel pipe. The rear end of the engine protection shell is provided with a communicating regulation and control valve pipe, the rear end of the communicating regulation and control valve pipe communicates with a regulation and control atomizer, the rear end of the regulation and control atomizer is provided with a ventilation valve seat, and the rear end of the ventilation valve seat communicates with an airflow channel pipe. The engine structure further comprises a powder fuel storage device, a first communication control pipe, a second communication control pipe, a combustion chamber, a combined exhaust nozzle, a closed adjusting block and a protection ring block, the regulation atomizer and the airflow channel pipe are both communicated with the combustion chamber, and the combined exhaust nozzle is arranged at the rear end of the combustion chamber. Through the arrangement of the structure, cross-medium driving work can be conveniently carried out.

Description

Technical Field

[0001] The present invention relates to the technical field of a trans-medium ramjet engine and an aircraft, in particular to a high-maneuverability trans-medium ramjet engine and an aircraft. Background Art

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

[0003] As the closest prior art, Chinese patent publication number CN109098891A relates to a cross-media ramjet engine based on solid propulsion, in which the flow channels are evenly arranged on the outer circumference of the gas generator, and the flow channels and the gas generator are integrated in design, which not only ensures the normal operation of the engine, but also ensures the streamlined shape of the gas generator. The flow channel baffle is driven by a baffle drive motor to control the closing and opening of the upper and lower flow channel baffles, thereby switching the air intake and water intake modes. The parallel flow channel is used to realize the integration of the air intake and water intake of the cross-media ramjet engine. By controlling the start, shutdown, and movement speed of the powder supply device, the fuel can be delivered, stopped, and flow control can be achieved, thereby better realizing the controllable supply of powder fuel and meeting the gas flow requirements during different modes and thrust adjustments;

[0004] At present, high-maneuverability cross-medium ramjet engines, aircraft and the structures of the above cases cannot control the flight power problem to a greater extent when in use, which will cause the problem of inability to quickly switch states. Therefore, improvements are needed to address the above problems. Summary of the invention

[0005] In view of the problems in the prior art, the present invention provides a high-maneuverability cross-medium ramjet engine and an aircraft.

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

[0007] The engine structure also includes a powder fuel storage device, a first connecting control tube, a second connecting control tube, a combustion chamber, a combined tail nozzle, a closed adjustment block and a protective ring block. The control atomizer and the airflow channel tube are connected to the combustion chamber. The rear end of the combustion chamber is provided with a combined tail nozzle. A protective ring block is fixedly connected to the combined tail nozzle. The closed adjustment block is movable by a motor in the protective ring block. The front end position of the closed adjustment block is movably hinged to the combined tail nozzle. The front end of the combustion chamber is provided with a second connecting control tube. The front end of the second connecting control tube is provided with a first connecting control tube. A powder fuel storage device is installed at the front end of the first connecting control tube. The powder fuel storage device, the first connecting control tube and the second connecting control tube are fixedly limited by the engine casing. The structural setting of the engine structure is convenient for operation. To carry out drive control work, a connecting control valve pipe and a control atomizer are arranged on the engine casing, the connecting control valve pipe can introduce atomized water through the control atomizer, so that the atomized water can reach the position of the combustion chamber, at this time, the powder fuel storage device controls the fuel to be conducted through the first connecting control pipe and the second connecting control pipe, and is guided to the combustion chamber, and ignited in the combustion chamber, and then the driving work is controlled by the combined tail nozzle, and a closing adjustment block is elastically arranged on the protection ring block, under the action of pressure, the closing adjustment block can be opened, and when there is no pressure, the closing adjustment block can be closed, which serves the purpose of protecting the structure inside the engine structure, and when the engine structure is in the air, the ventilation valve seat at this time introduces gas through the airflow channel tube, and the fuel is guided to the first connecting control pipe and the second connecting control pipe through the powder fuel storage device, and is ignited in the combustion chamber to carry out driving work.

[0008] The aircraft comprises an aircraft structure, the lower end of which is fixedly connected to an engine structure, and the aircraft structure controls flight regulation 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 on one side of the aircraft component, and the second state adjustment component is movably hinged on the other side of the aircraft component, and the structures of the first state adjustment component and the second state adjustment component are the same.

[0010] Specifically, the aircraft components include an aircraft tail, a detection head, a support seat block, a fixed mounting frame, a combined cabin, a first propeller seat and a second propeller seat. The side ends of the detection head are fixed by the support seat block. The rear ends of the detection head and the support seat block are fixedly connected to the combined cabin. The lower end of the combined cabin is fixedly connected to a fixed mounting frame. The fixed mounting frame is used for fixed combination of an engine structure. The rear end of the combined cabin is fixedly connected to the aircraft tail. The center rear end of the aircraft tail is fixedly connected to the first propeller seat. The rear end of the first propeller seat is fixedly connected to the second propeller seat. Propellers are rotatably provided in the first propeller seat and the second propeller seat, and the propellers rotate relative to the combined cabin. A control motor is provided in the combined cabin to control the propeller to rotate in the first propeller seat and the second propeller seat.

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

[0012] Specifically, the first state adjustment component also includes a connecting wing panel, an electric-controlled hydraulic telescopic rod, a driven telescopic adjustment frame and an articulated end frame, the fixed side frame is hingedly provided with an articulated end frame, the upper end limit of the articulated end frame is connected with a connecting wing panel, the center of the connecting wing panel is hingedly provided with an electric-controlled hydraulic telescopic rod, the other end of the electric-controlled hydraulic telescopic rod is hingedly arranged with the fixed side frame, the fixed side frame is located at the lower end of the electric-controlled hydraulic telescopic rod and is provided with a driven telescopic adjustment frame, and the driven telescopic adjustment frame is hingedly arranged with the fixed side frame, and the structural setting of the aircraft structure facilitates the state switching work, and the first state adjustment component and the second state adjustment component are arranged on the aircraft component. When in water, the first state adjustment component and the second state adjustment component are retracted to reduce resistance, and when in the air, At this time, the first state adjustment component and the second state adjustment component are opened and can perform floating work. The first propeller seat and the second propeller seat are provided with propellers, which can cooperate for stable transmission in water. The fixed side frame in the first state adjustment component is supported and fixed by a fixed mounting block, and a connecting wing panel is hingedly provided on the fixed side frame through an articulated end frame. Under the telescopic cooperation of the electro-hydraulic telescopic rod, the connecting wing panel can be driven to rotate and adjust to change the angle of the connecting wing panel, and the driven telescopic adjustment frame is arranged at the lower end of the electro-hydraulic telescopic rod, which can play an auxiliary cooperation function and improve the stability of the connecting wing panel. A probe is provided in the detection head for detection and identification work. The setting of the fixed mounting frame is convenient for fixing the engine structure. An aircraft tail wing is arranged at the rear end of the combined cabin to play a supporting and protective function.

[0013] Specifically, the fixed mounting block is fixedly connected to the combined cabin, the detection head, and the support seat block. The detection head is arranged in an arc-shaped structure. The tail wing of the aircraft is symmetrically distributed in a cone shape. A mounting hole is provided in the center of the fixed mounting frame, and the mounting hole is fixedly connected to the engine structure through rivets.

[0014] Specifically, the electrically controlled hydraulic telescopic rod pushes the connecting wing plate to rotate and adjust around the hinged end frame by telescoping, and the driven telescopic adjustment frame follows the connecting wing plate to be stretched and adjusted, and the driven telescopic adjustment frame is hingedly arranged with the connecting wing plate and the fixed side frame.

[0015] Specifically, the fixed side frame is of a double-piece design, a probe is provided in the detection head, and the connecting wing plate has two forms of adjustment. The connecting wing plate can fit the fixed side frame to be in an underwater posture.

[0016] Specifically, the connecting wing panel can also be away from the fixed side frame to be in a flying posture, and a groove body is provided on the first propeller seat to perform drainage work.

[0017] Beneficial effects of the present invention:

[0018] First, the present invention facilitates the state switching work through the structural setting of the aircraft structure. The first state adjustment component and the second state adjustment component are arranged on the aircraft component. When in water, the first state adjustment component and the second state adjustment component are retracted to reduce resistance. When in the air, the first state adjustment component and the second state adjustment component are opened to perform floating work. The first propeller seat and the second propeller seat are provided with propellers, which can cooperate to perform stable transmission in water. The fixed side frame in the first state adjustment component is supported and fixed by a fixed mounting block. The fixed side frame is hingedly provided with a connecting wing plate through an articulated end frame. Under the telescopic cooperation of the electric-controlled hydraulic telescopic rod, the connecting wing plate can be driven to rotate and adjust to change the angle of the connecting wing plate. The driven telescopic adjustment frame is arranged at the lower end of the electric-controlled hydraulic telescopic rod, which can play an auxiliary cooperation function and improve the stability of the connecting wing plate. A probe is arranged in the detection head to perform detection and identification work. The setting of the fixed mounting frame facilitates the fixing of the engine structure. The aircraft tail wing is arranged at the rear end of the combined cabin to play a supporting and protective function. The purpose of rapid switching is achieved through the setting of the structure.

[0019] Second, the present invention facilitates drive control work through the structural setting of the engine structure. A connecting control valve pipe and a control atomizer are arranged on the engine casing. The connecting control valve pipe can introduce atomized water through the control atomizer, so that the atomized water can reach the position of the combustion chamber. At this time, the powder fuel storage device controls the fuel to be conducted through the first connecting control pipe and the second connecting control pipe, and guides it to the combustion chamber, and ignites it in the combustion chamber. Thereafter, the driving work is controlled by the combined tail nozzle. A closing adjustment block is elastically arranged on the protective ring block. Under the action of pressure, the closing adjustment block can be opened, and when there is no pressure, the closing adjustment block can be closed, which serves the purpose of protecting the structure inside the engine structure. When the engine structure is in the air, the ventilation valve seat at this time introduces gas through the airflow channel tube, and the fuel is guided to the first connecting control pipe and the second connecting control pipe through the powder fuel storage device, and ignites it in the combustion chamber to perform driving work. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0021] Figure 1 It is a schematic diagram of the three-dimensional structure of the main body of the present invention from the front perspective;

[0022] Figure 2 It is a split diagram of the main body in the present invention;

[0023] Figure 3 It is a schematic diagram of the three-dimensional structure of the aircraft structure in the present invention from a front perspective;

[0024] Figure 4 It is a schematic diagram of the three-dimensional structure of the aircraft component in the present invention from a front perspective;

[0025] Figure 5 It is a schematic diagram of the front viewing angle stereoscopic structure of the first state adjustment component in the present invention;

[0026] Figure 6 It is a schematic diagram of the rear perspective three-dimensional structure of the first state adjustment component in the present invention;

[0027] Figure 7 It is a schematic diagram of the three-dimensional structure of the engine structure in the present invention from a front perspective;

[0028] Figure 8 It is a three-dimensional cutaway view of the engine structure in the present invention.

[0029] In the figure: 1-aircraft structure, 2-engine structure, 3-aircraft component, 4-first state adjustment component, 5-second state adjustment component, 6-aircraft tail, 7-detection head, 8-support seat block, 9-fixed mounting frame, 10-combined cabin, 11-first propeller seat, 12-second propeller seat, 13-fixed side frame, 14-fixed connecting column, 15-fixed mounting block, 16-connecting wing plate, 17-electrically controlled hydraulic telescopic rod, 18-driven telescopic adjustment frame, 19-articulated end frame, 20-engine casing, 21-connecting regulating valve pipe, 22-regulating 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 regulating block, 32-protection ring block. DETAILED DESCRIPTION

[0030] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work 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 and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequential order. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present application described here. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0032] The present invention is further described below in conjunction with the accompanying drawings.

[0033] Example

[0034] like Figure 1-8As shown, the high maneuverability cross-medium ramjet engine and aircraft of the present invention include an engine structure 2, the engine structure 2 includes an engine casing 20, a communication regulating valve pipe 21, a regulating atomizer 22, a ventilation valve seat 23 and an airflow channel pipe 24, the rear end of the engine casing 20 is provided with a communication regulating valve pipe 21, the rear end of the communication regulating valve pipe 21 is connected with a regulating atomizer 22, the rear end of the regulating atomizer 22 is provided with a ventilation valve seat 23, and the rear end of the ventilation valve seat 23 is connected with an airflow channel pipe 24;

[0035] The engine structure 2 also includes 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 adjustment block 31 and a protective ring block 32. The control atomizer 22 and the airflow channel pipe 24 are both connected to the combustion chamber 28. The rear end of the combustion chamber 28 is provided with a combined tail nozzle 29. A protective ring block 32 is fixedly connected to the combined tail nozzle 29. The closed adjustment block 31 is movable by controlling the motor in the protective ring block 32. The front end position of the closed adjustment block 31 is movably hinged with the combined tail nozzle 29. The front end of the combustion chamber 28 is provided with a second communication control pipe 27. The front end of the second communication control pipe 27 is provided with a first communication control pipe 26. The front end of the first communication control pipe 26 is installed with a powder fuel storage 25. The powder fuel storage 25, the first communication control pipe 26 and the second communication control pipe 27 are fixedly limited by the engine casing 20. The engine casing 20 in the engine structure 2 is provided with a communication control valve pipe 21, a control atomizer 22, a ventilation valve seat 23, an airflow channel pipe 2 4, the connecting regulating valve pipe 21, regulating atomizer 22 and ventilation valve seat 23, air flow channel pipe 24 are used separately. When at the bottom of the water, the connecting regulating valve pipe 21 and regulating atomizer 22 are started, the ventilation valve seat 23 and air flow channel pipe 24 are closed, and the water body is conducted through the connecting regulating valve pipe 21 and regulating atomizer 22, and atomized at the same time, and discharged to the combustion chamber 28, and the powder fuel storage 25 introduces fuel, so that the fuel is conducted through the first connecting control pipe 26 and the second connecting control pipe 27 to reach the combustion chamber 28. On the combustion chamber 28, the combustion reaction is controlled, and the wake can push the closed adjustment block 31 to move to ensure uniform emission performance. When in the air, the ventilation valve seat 23 and the airflow channel tube 24 are started, the connecting control valve tube 21 and the regulating atomizer 22 are closed, and the gas reaches the combustion chamber 28 position. The powder fuel storage 25 discharges the fuel to the combustion chamber 28 through the first connecting control tube 26 and the second connecting control tube 27, and reacts and processes in the combustion chamber 28, thereby driving work and driving the aircraft structure 1 to move.

[0036] The aircraft comprises an aircraft structure 1, the lower end of which is fixedly connected with an engine structure 2, and 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 structures of the first state adjustment component 4 and the second state adjustment component 5 are the same.

[0038] The aircraft component 3 includes an aircraft tail 6, a detection head 7, a support seat block 8, a fixed mounting frame 9, a combined cabin 10, a first propeller seat 11 and a second propeller seat 12. The side end of the detection head 7 is fixed by the support seat block 8. The rear ends of the detection head 7 and the support seat 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. The fixed mounting frame 9 is used for fixed combination of the engine structure 2. The rear end of the combined cabin 10 is fixedly connected to the aircraft tail 6. The center rear end of the aircraft tail 6 is fixedly connected to the first propeller seat 11. The rear end of the first propeller seat 11 is fixedly connected to the second propeller seat 12. Propellers are rotatably arranged in the first propeller seat 11 and the second propeller seat 12, and the propellers rotate relative to the combined cabin 10. A control motor is arranged in the combined cabin 10 to control the propellers to rotate in the first propeller seat 11 and the second propeller seat 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 center of the fixed mounting block 15 is fixedly connected to the fixed connecting column 14, the lower end of the fixed connecting column 14 is fixedly connected to the fixed side frame 13, and the fixed side frame 13 is fixedly connected to the fixed mounting block 15 via the fixed connecting column 14.

[0040] The first state adjustment component 4 also includes a connecting wing panel 16, an electrically-controlled hydraulic telescopic rod 17, a driven telescopic adjustment frame 18 and an articulated end frame 19. The fixed side frame 13 is hingedly provided with an articulated end frame 19. The upper end limit of the articulated end frame 19 is connected to the connecting wing panel 16. The center of the connecting wing panel 16 is hingedly provided with an electrically-controlled hydraulic telescopic rod 17. The other end of the electrically-controlled hydraulic telescopic rod 17 is hingedly provided with the fixed side frame 13. The fixed side frame 13 is located at the lower end of the electrically-controlled hydraulic telescopic rod 17 and is provided with a driven telescopic adjustment frame 18. The driven telescopic adjustment frame 18 is hingedly provided with the fixed side frame 13. The aircraft structure 1 performs attitude adjustment work, wherein the aircraft component 3 in the aircraft structure 1 performs supporting work. The side ends of the aircraft component 3 are provided with the first state adjustment component 4 and the second state adjustment component 5, which can perform flight adjustment work. When in the flight state, the first state adjustment component 4 and the second state adjustment component 5 at this time When the component 5 is opened, the flight assistance function can be performed. The detection head 7 in the aircraft component 3 performs sensing detection through the probe. The support seat block 8, the detection head 7 and the combined cabin 10 are fixed. A fixed mounting frame 9 is provided at the lower end of the combined cabin 10, and the engine structure 2 is supported and fixed by the fixed mounting frame 9. An aircraft tail 6 is provided at the rear end of the combined cabin 10 to maintain balance, and the combined cabin 10 can control the rotation of the propeller through a motor. The propeller rotates in the first propeller seat 11 and the second propeller seat 12 to perform auxiliary power control in water. When flying, the fixed side frame 13, the fixed connecting column 14, and the fixed mounting block 15 are fixed at this time, and the electrically controlled hydraulic telescopic rod 17 is telescopically adjusted to push 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 cooperate with the adjustment to maintain stable performance.

[0041] The fixed mounting block 15 is fixedly connected to the combined cabin 10, the detection head 7, and the support seat block 8. The detection head 7 is arranged in an arc-shaped structure, and the aircraft tail 6 is symmetrically distributed in a cone shape. A mounting hole is provided in the center of the fixed mounting frame 9, and the mounting hole is fixedly connected to the engine structure 2 by rivets.

[0042] The electrically controlled hydraulic telescopic rod 17 pushes the connecting wing plate 16 to rotate and adjust around the hinged end frame 19 by telescoping, and the driven telescopic adjustment frame 18 follows the connecting wing plate 16 to be stretched and adjusted, and the driven telescopic adjustment frame 18 is hingedly arranged with the connecting wing plate 16 and the fixed side frame 13.

[0043] The fixed side frame 13 is of a double-piece design, a probe is provided in the detection head 7, and the connecting wing plate 16 has two forms of adjustment. The connecting wing plate 16 can fit the fixed side frame 13 and is in an underwater posture.

[0044] The connecting wing plate 16 can also be away from the fixed side frame 13 to be in a flying posture. A groove is provided on the first propeller seat 11 to perform drainage work.

[0045] The working principle is as follows: when in use, the aircraft structure 1 is fixed to the engine structure 2, the engine structure 2 plays a driving function, the aircraft structure 1 performs attitude adjustment work, wherein the aircraft component 3 in the aircraft structure 1 performs support work, and the side end of the aircraft component 3 is provided with a first state adjustment component 4 and a second state adjustment component 5, which can perform flight adjustment work. When in the flight state, the first state adjustment component 4 and the second state adjustment component 5 are opened, and the flight auxiliary function can be performed. The detection head 7 in the aircraft component 3 performs induction detection through the probe, the support seat block 8, the detection head 7 and the combined cabin 10 are fixed, and the combined cabin 10 is fixed. A fixed mounting frame 9 is provided at the lower end of the cabin 10, and the engine structure 2 is supported and fixed by the fixed mounting frame 9. An aircraft tail 6 is provided at the rear end of the combined cabin 10 to maintain balance, and the combined cabin 10 can control the rotation of the propeller through a motor, and the propeller rotates in the first propeller seat 11 and the second propeller seat 12 to perform auxiliary power control in water. When flying, the fixed side frame 13, the fixed connecting column 14, and the fixed mounting block 15 are fixed, and the electric-controlled hydraulic telescopic rod 17 is telescopically adjusted to push 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 The driven telescopic adjustment frame 18 is driven to cooperate with the adjustment to maintain stable performance. A connecting and regulating valve pipe 21, a regulating atomizer 22, a ventilation valve seat 23, and an air flow channel pipe 24 are arranged on the engine casing 20 in the engine structure 2. The connecting and regulating valve pipe 21, the regulating atomizer 22 and the ventilation valve seat 23 and the air flow channel pipe 24 are used separately. When at the bottom of the water, the connecting and regulating valve pipe 21 and the regulating atomizer 22 are started, and the ventilation valve seat 23 and the air flow channel pipe 24 are closed. The water body is conducted through the connecting and regulating valve pipe 21 and the regulating atomizer 22, and atomization is performed at the same time, and the water is discharged to the combustion chamber 28. The powder fuel storage 25 introduces the fuel The fuel is conducted through the first connecting control tube 26 and the second connecting control tube 27 to the combustion chamber 28 to control the combustion reaction. The wake can push the closed regulating block 31 to move to ensure uniform emission performance. When in the air, the ventilation valve seat 23 and the airflow channel tube 24 are started, the connecting regulating valve tube 21 and the regulating atomizer 22 are closed, and the gas reaches the combustion chamber 28. The powder fuel storage 25 guides the fuel through the first connecting control tube 26 and the second connecting control tube 27 to the combustion chamber 28 for reaction processing in the combustion chamber 28, thereby driving the aircraft structure 1 to move and complete the work.

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

Claims

1. A high-mobility cross-medium ramjet engine, characterized by: The invention comprises an engine structure (2), wherein the engine structure (2) comprises an engine casing (20), a communicating regulating valve pipe (21), a regulating atomizer (22), a ventilation valve seat (23) and an airflow channel pipe (24), wherein the rear end of the engine casing (20) is provided with a communicating regulating valve pipe (21), the rear end of the communicating regulating valve pipe (21) is connected to the regulating atomizer (22), the rear end of the regulating atomizer (22) is provided with a ventilation valve seat (23), and the rear end of the ventilation valve seat (23) is connected to the airflow channel pipe (24); The engine structure (2) further comprises a powder fuel storage (25), a first connecting control pipe (26), a second connecting control pipe (27), a combustion chamber (28), a combined tail nozzle (29), a closed regulating block (31) and a protective ring block (32); the regulating atomizer (22) and the air flow channel pipe (24) are both connected to the combustion chamber (28); a combined tail nozzle (29) is provided at the rear end of the combustion chamber (28); a protective ring block (32) is fixedly connected to the combined tail nozzle (29); a motor is provided in the protective ring block (32) The movement of the closing adjustment block (31) is controlled. The front end of the closing adjustment block (31) is movably hinged with the combined tail nozzle (29). The front end of the combustion chamber (28) is provided with a second communication control pipe (27). The front end of the second communication control pipe (27) is provided with a first communication control pipe (26). The front end of the first communication control pipe (26) is provided with a powder fuel storage (25). The powder fuel storage (25), the first communication control pipe (26) and the second communication control pipe (27) are fixed and limited by the engine casing (20).

2. An aircraft, using the high maneuverability cross-medium ramjet engine as claimed in claim 1, characterized in that: The invention comprises an aircraft structure (1), the lower end of which is fixedly connected to an engine structure (2), and the aircraft structure (1) controls flight adjustment through the engine structure (2).

3. The aircraft according to claim 2, characterized in that: The aircraft structure (1) comprises an aircraft component (3), a first state adjustment component (4) and a second state adjustment component (5); one side of the aircraft component (3) is movably hinged with the first state adjustment component (4), and the other side of the aircraft component (3) is movably hinged with the second state adjustment component (5); and the structures of the first state adjustment component (4) and the second state adjustment component (5) are the same.

4. The aircraft according to claim 3, characterized in that: The aircraft component (3) comprises an aircraft tail wing (6), a detection head (7), a support seat block (8), a fixed mounting frame (9), a combined engine cabin (10), a first propeller seat (11) and a second propeller seat (12); the side end of the detection head (7) is fixed by the support seat block (8); the rear ends of the detection head (7) and the support seat block (8) are fixedly connected to the combined engine cabin (10); the lower end of the combined engine cabin (10) is fixedly connected to the fixed mounting frame (9); the fixed mounting frame (9) is used for fixed assembly with the engine structure (2); The rear end of the combined engine cabin (10) is fixedly connected to an aircraft tail wing (6); the center rear end of the aircraft tail wing (6) is fixedly connected to a first propeller seat (11); the rear end of the first propeller seat (11) is fixedly connected to a second propeller seat (12); propellers are rotatably arranged in the first propeller seat (11) and the second propeller seat (12); the propellers rotate relative to the combined engine cabin (10); a control motor is arranged in the combined engine cabin (10) to control the propellers to rotate in the first propeller seat (11) and the second propeller seat (12).

5. The aircraft according to claim 4, characterized in that: The first state adjustment 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 to the fixed connecting column (14); the lower end of the fixed connecting column (14) is fixedly connected to the fixed side frame (13); and the fixed side frame (13) is fixedly connected to the fixed mounting block (15) via the fixed connecting column (14).

6. The aircraft according to claim 5, characterized in that: The first state adjustment component (4) also includes a connecting wing plate (16), an electric-controlled hydraulic telescopic rod (17), a driven telescopic adjustment frame (18) and an articulated end frame (19); the fixed side frame (13) is hingedly provided with an articulated end frame (19); the upper end of the articulated end frame (19) is limitedly connected to the connecting wing plate (16); the center of the connecting wing plate (16) is hingedly provided with an electric-controlled hydraulic telescopic rod (17); the other end of the electric-controlled hydraulic telescopic rod (17) is articulated with the fixed side frame (13); the fixed side frame (13) is provided with a driven telescopic adjustment frame (18) at the lower end of the electric-controlled hydraulic telescopic rod (17); and the driven telescopic adjustment frame (18) is articulated with the fixed side frame (13).

7. The aircraft according to claim 6, characterized in that: The fixed mounting block (15) is fixedly connected to the combined cabin (10), the detection head (7), and the support seat block (8); the detection head (7) is arranged in an arc-shaped structure; the aircraft tail wing (6) is symmetrically distributed in a cone shape; a mounting hole is provided at the center of the fixed mounting frame (9), and the mounting hole is fixedly connected to the engine structure (2) via rivets.

8. The aircraft according to claim 7, characterized in that: The electrically controlled hydraulic telescopic rod (17) pushes the connecting wing plate (16) to rotate and adjust around the hinged end frame (19) by telescoping, and the driven telescopic adjustment frame (18) follows the connecting wing plate (16) to be stretched and adjusted, and the driven telescopic adjustment frame (18) is hingedly arranged with the connecting wing plate (16) and the fixed side frame (13).

9. The aircraft according to claim 8, characterized in that: The fixed side frame (13) is of a double-piece design, a probe is arranged inside the detection head (7), and the connecting wing plate (16) has two forms of adjustment. The connecting wing plate (16) can fit the fixed side frame (13) to be in an underwater posture.

10. The aircraft according to claim 9, characterized in that: The connecting wing plate (16) can also be away from the fixed side frame (13) to be in a flying posture, and a groove body is provided on the first propeller seat (11) to perform drainage work.

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