Cross-medium aircraft

Abstract

The invention relates to the technical field of aircrafts, and discloses a cross-medium aircraft which comprises a functional module, a power module, a control module, a comprehensive module and a submerging module, the power module is divided into a front power mechanism and a rear power mechanism, the control module is arranged between the front power mechanism and the rear power mechanism and used for controlling the lift force directions of the front power mechanism and the rear power mechanism so as to control the flight attitude of the aircraft, and the front power mechanism and the rear power mechanism are in the structural form of hinge-free rotors. Lift force is provided for the aircraft; the other side of the front power mechanism is connected with the functional module, and the functional module is used for carrying functional equipment for working of the aircraft and can carry different modules such as a reconnaissance photoelectric ball, a high-energy explosive and a relay communication cabin according to the requirements of task execution. Through modular design, the structure of an aircraft and the structure of an underwater vehicle are integrated, and the problems that a cross-medium flight structure is complex and huge, and the function is single are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and specifically to a trans-medium aircraft. Background Art

[0002] A trans-medium aircraft is a device that has both the functions of flying in the air and navigating underwater, and belongs to the categories of both aircraft and navigators. Due to its functions, this device also has the characteristics of fast air mobility and underwater stealth navigation. On the one hand, in the air flight state, it has high speed and low resistance, with an absolute speed advantage compared to underwater navigation and is more energy-efficient. Compared with an underwater aircraft with the same energy reserve, it has a longer movement radius and shorter maneuvering time, which to a certain extent expands the operation radius of the device, meaning more diverse uses; on the other hand, compared with traditional aircraft, it has the advantages of underwater stealth and intermittent flight to extend the operation time. When the aircraft operates over water, to ensure its own lift, it needs to continuously use energy to drive a propeller or other power equipment to output kinetic energy, and the hovering time of the aircraft greatly restricts the operation task scenarios of the aircraft.

[0003] Therefore, we propose a trans-medium aircraft to solve the above problems. Summary of the Invention

[0004] (1) Technical Problems to be Solved

[0005] In view of the deficiencies of the prior art, the present invention provides a trans-medium aircraft. Through modular design, it integrates the structures of an air vehicle and a submersible in water, and solves the problems of complex and large structure and single function of trans-medium flight.

[0006] (2) Technical Solutions

[0007] To achieve the purpose of modularization and integration of the above trans-medium aircraft, the present invention provides the following technical solutions: A trans-medium aircraft, comprising: a function module, a power module, a control module, a comprehensive module, and a submersible module;

[0008] The power module is divided into a front power mechanism and a rear power mechanism. The control module is arranged between the front power mechanism and the rear power mechanism and is used to manipulate the lift direction of the front power mechanism and the rear power mechanism, thereby controlling the flight attitude of the aircraft. The structural forms of the front power mechanism and the rear power mechanism are hinge-less rotors, which provide lift for the aircraft;

[0009] The other side of the front power mechanism is connected to the function module. The function module is used to carry functional equipment for the operation of the aircraft, and different modules such as a reconnaissance optoelectronic sphere, a high-energy explosive, and a relay communication cabin can be carried according to the requirements of the mission to be executed;

[0010] The other side of the rear power mechanism is connected to the integrated module. The integrated module includes an energy system, a transmission system, and a flight control and navigation system, and is used to drive the front power mechanism, the rear power mechanism, and the submersible module to work. The submersible module is connected to the integrated module and mainly provides power for the aircraft to dive and navigate in water.

[0011] As a further optimization of the present invention: The front power mechanism includes a first motor and a first blade. The output end of the first motor is connected to the first blade and is used to drive the first blade to rotate.

[0012] As a further optimization of the present invention: The integrated module includes a first housing. The energy system includes a battery and a second motor located inside the first housing. The first motor, the second motor, and the battery are electrically connected. The transmission system includes a rotating shaft, and the rotating shaft is connected to the output shaft of the second motor.

[0013] As a further optimization of the present invention: The rear power mechanism includes a first ratchet and a second blade. The second motor is connected to the second blade through the rotating shaft and the first ratchet and is used to control the second blade to rotate.

[0014] As a further optimization of the present invention: The control module further includes a second housing and a servo and an elevator inside the second housing. The servo is connected to the elevator. The elevator is connected to the first blade and the second blade. The servo controls the tilting states of the first blade and the second blade through the elevator, changes the pulling force direction by plane tilting, and further controls the flight attitude of the whole machine, and controls the heading, pitch, and roll of the aircraft; The first blade and the second blade share the elevator and the servo, so the angles of the two tilting planes generated are exactly the same.

[0015] As a further optimization of the present invention: The submersible module includes a second ratchet and a propeller. The second motor is also connected to the propeller through the rotating shaft and the second ratchet and is used to control the propeller to rotate.

[0016] As a further optimization of the present invention: A rudder surface is further provided on the propeller, and the submersible attitude of the aircraft is controlled through the deflection direction of the rudder surface.

[0017] As a further optimization of the present invention: A duct is further provided on the propeller, and the duct is used to guide the water flow to reduce the noise generated by the propeller.

[0018] As a further optimization of the present invention: An electromagnetic pin is further provided on the functional module. The functional module is connected to the aircraft through the electromagnetic pin and can carry different modules such as a reconnaissance optoelectronic sphere, a high-energy explosive, and a relay communication cabin according to the needs of the mission.

[0019] As a further optimization of the present invention: placing grooves are further provided on the first housing and the second housing. When the first blade and the second blade are in the submersible state, they are located in the placing grooves, reducing the influence of the first blade and the second blade on the water flow. The first housing and the second housing form a closed section, reducing the resistance generated during flight and protecting the attitude control module and the integrated module from being invaded by sand, stones, water vapor, and at the same time blocking the intrusion of water during submergence.

[0020] (III) Advantageous Effects

[0021] Compared with the prior art, the present invention provides a cross-media aircraft, having the following advantageous effects:

[0022] 1. By providing blades and propellers, the speed of the aircraft and the concealment of the submersible can be combined, improving the practicality of the aircraft;

[0023] 2. By modularizing the aircraft design, it can be quickly assembled and disassembled, facilitating portability and enabling multi-task capabilities;

[0024] 3. The functional module and the aircraft can be quickly separated by electromagnetic pins, enabling the aircraft to have the ability to be recycled and reused. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic internal structure diagram of the present invention;

[0026] Figure 2 It is a schematic modular structure diagram of the present invention;

[0027] Figure 3 It is a schematic flight state structure diagram of the present invention

[0028] Figure 4 It is a schematic submersible state structure diagram of the present invention.

[0029] In the figure: 1. Functional module; 2. Front power mechanism; 3. Control module; 4. Rear power mechanism; 5. Integrated module; 6. Submersible module; 7. First blade; 8. Swashplate; 9. Servo; 10. First housing; 11. First ratchet; 12. Navigation system; 13. First motor; 14. Battery; 15. Second housing; 16. Duct; 17. Propeller; 18. Rudder surface; 19. Second motor; 20. Rotating shaft; 21. Second blade; 22. Second ratchet; 23. Electromagnetic pin. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0030] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0031] Please refer to Figures 1-4 , a cross-media aircraft, comprising: a function module 1, a power module, a control module 3, an integrated module 5, and a submersible module 6; the power module is divided into a front power mechanism 2 and a rear power mechanism 4, and the control module 3 is disposed between the front power mechanism 2 and the rear power mechanism 4 for manipulating the lift directions of the front power mechanism 2 and the rear power mechanism 4, thereby controlling the flight attitude of the aircraft. The structural forms of the front power mechanism 2 and the rear power mechanism 4 are hinge-less rotors, which provide lift for the aircraft; the other side of the front power mechanism 2 is connected to the function module 1, and the function module 1 is used to carry the functional devices for the operation of the aircraft, and different modules such as a reconnaissance optoelectronic sphere, a high-energy explosive, and a relay communication cabin can be carried according to the requirements of the mission; the other side of the rear power mechanism 4 is connected to the integrated module 5, and the integrated module 5 includes an energy system, a transmission system, and a flight control and navigation system 12 for driving the front power mechanism 2, the rear power mechanism 4, and the submersible module 6 to work. The submersible module 6 is connected to the integrated module 5 and mainly provides power for the aircraft to dive and navigate in water.

[0032] The front power mechanism 2 includes a motor one 13 and a blade one 7, and the output end of the motor one 13 is connected to the blade one 7 for driving the blade one 7 to rotate; the integrated module 5 includes a housing one 10, and the energy system includes a battery 14 and a motor two 19 located in the housing one 10. The motor one 13, the motor two 19, and the battery 14 are electrically connected. The transmission system includes a rotating shaft 20, and the rotating shaft 20 is connected to the output shaft of the motor two 19; the rear power mechanism 4 includes a ratchet one 11 and a blade two 21, and the motor two 19 is connected to the blade two 21 through the rotating shaft 20 and the ratchet one 11 for controlling the rotation of the blade two 21.

[0033] The control module 3 further includes a housing two 15 and a servo 9 and an swashplate 8 in the housing two 15. The servo 9 is connected to the swashplate 8, and the swashplate 8 is connected to the blade one 7 and the blade two 21. The servo 9 simultaneously controls the tilt states of the blade one 7 and the blade two 21 through the swashplate 8, changes the pulling force direction by plane tilting, thereby controlling the flight attitude of the whole machine, and controlling the heading, pitch, and roll of the aircraft; the blade one 7 and the blade two 21 share the swashplate 8 and the servo 9, so the angles of the two swashplate planes generated are exactly the same.

[0034] The submersible module 6 includes a ratchet two 22 and a propeller 17. The motor two 19 is also connected to the propeller 17 through a rotating shaft 20 and the ratchet two 22 to control the rotation of the propeller 17. A rudder surface 18 is also provided on the propeller 17. The submersible attitude of the aircraft is controlled by the deflection direction of the rudder surface 18. A duct 16 is also provided on the propeller 17. The duct 16 is used to guide the water flow to reduce the noise generated by the propeller 17.

[0035] An electromagnetic pin 23 is also provided on the function module 1. The function module 1 is connected to the aircraft through the electromagnetic pin 23 and can carry different modules such as a reconnaissance optoelectronic sphere, a high-energy explosive, and a relay communication module according to the needs of the mission.

[0036] Placement grooves are also provided on the housing one 10 and the housing two 15. When the blade one 7 and the blade two 21 are in the submersible state, they are located in the placement grooves to reduce the influence of the blade one 7 and the blade two 21 on the water flow. The housing one 10 and the housing two 15 form a sealed section to reduce the resistance generated during flight and protect the attitude control module 3 and the integrated module 5 from being invaded by sand, gravel, water vapor, and at the same time block the intrusion of water during submergence.

[0037] Working principle:

[0038] Embodiment 1: Flight mode

[0039] The control module 3 and the power module provide power and control the flight attitude of the aircraft. The motor one 13 drives the blade one 7 to rotate under the output electric energy of the power battery 14. The blade one 7 is fully unfolded under the action of centrifugal force. The rotor of the motor one 13 at the head is directly connected to the blade one 7. The power motor two 19 in the middle of the fuselage drives the blade two 21 to rotate through the rotating shaft 20 and the friction ratchet one 11. The blade one 7 and the blade two 21 rotate in opposite directions to cancel the anti-torque generated by their own rotation. The swashplate 8 is driven by the servo 9 to control the plane formed by the rotation of the blade one 7 and the blade two 21 to tilt. By changing the direction of the pulling force through the plane tilt, the flight attitude of the whole machine is controlled, and the heading, pitch, and roll of the aircraft are controlled. The blade one 7 and the blade two 21 share the swashplate 8 and the servo 9. Therefore, the angles of the two tilted planes generated by the blade one 7 and the blade two 21 are exactly the same. The housing one 10 and the housing two 15 form a sealed section to reduce the resistance generated during flight and protect the attitude control module 3 and the integrated module 5 from being invaded by sand, gravel, water vapor, and at the same time block the intrusion of water during submergence. The power motor two 19 is connected to the propeller 17 through the rotating shaft 20 and the friction ratchet two 22. Because the friction ratchet two 22 only transmits force in one-way rotation, during flight, the power motor two 19 does not output torque to the propeller 17.

[0040] Embodiment 2: Flight to submersible

[0041] The flight control and navigation system 12 controls the attitude of the whole aircraft to the water entry mode, outputs a stop rotation instruction to the power motor 13, outputs a reverse rotation instruction to the power motor 19, the blade 7 and the blade 21 stop rotating, and under the action of gravity and resistance, they reach the contracted state, and the propeller 17 starts to rotate under the output of the power motor 19; the aircraft switches to the submersible mode, and the propeller 17 provides the navigation power, and the control surface 18 controls the submersible attitude by deflection; the duct 16 reduces the noise generated by the propeller 17 during submersible navigation.

[0042] Embodiment 3: From submersible navigation to flight

[0043] The flight control and navigation system 12 controls the attitude of the whole aircraft to the submersible navigation mode, and the control surface 18 deflects downward to provide the maximum kinetic energy for the aircraft to leap out of the water; after leaping out of the water, the flight control and navigation system 12 outputs a start rotation instruction to the power motor 13, outputs a reverse rotation instruction to the power motor 19, the blade 7 and the blade 21 start to rotate and reach the fully deployed state under the action of centrifugal force, and the propeller 17 stops rotating, and the aircraft switches to the flight mode.

[0044] Embodiment 4: Combat mode

[0045] When performing a combat mission, the mission segment of the functional module 1 can be separated from the aircraft body through the electromagnetic pin 23, and the aircraft can be recovered by entering the water or landing on the field according to the real-time battlefield environment.

[0046] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirits of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A cross-medium aircraft, characterized in that, It includes: A function module (1), a power module, a control module (3), an integrated module (5), and a submersible module (6); The power module is divided into a front power mechanism (2) and a rear power mechanism (4). The control module (3) is arranged between the front power mechanism (2) and the rear power mechanism (4) and is used to manipulate the lift direction of the front power mechanism (2) and the rear power mechanism (4), thereby controlling the flight attitude of the aircraft. The other side of the front power mechanism (2) is connected to the function module (1), and the function module (1) is used to carry the functional equipment for the operation of the aircraft. The other side of the rear power mechanism (4) is connected to the integrated module (5). The integrated module (5) includes an energy system, a transmission system, and a navigation system (12). The energy system is used to drive the front power mechanism (2), the rear power mechanism (4), and the submersible module (6) to work. The submersible module (6) is connected to the integrated module (5).

2. The cross-medium aircraft according to claim 1, wherein: The front power mechanism (2) includes a first motor (13) and a first blade (7). The output end of the first motor (13) is connected to the first blade (7) and is used to drive the first blade (7) to rotate.

3. The cross-medium aircraft according to claim 2, characterized in that: The integrated module (5) includes a first housing (10). The energy system includes a battery (14) and a second motor (19) located inside the first housing (10). The first motor (13), the second motor (19), and the battery (14) are electrically connected. The transmission system includes a rotating shaft (20), and the rotating shaft (20) is connected to the output shaft of the second motor (19).

4. The cross-medium aircraft according to claim 3, characterized in that: The rear power mechanism (4) includes a first ratchet (11) and a second blade (21). The second motor (19) is connected to the second blade (21) through the rotating shaft (20) and the first ratchet (12) and is used to control the rotation of the second blade (21).

5. The cross-medium aircraft according to claim 4, wherein: The control module (3) further includes a second housing (15), a servo (9), and an swashplate (8) inside the second housing (15). The servo (9) is connected to the swashplate (8), and the swashplate (8) is connected to the first blade (7) and the second blade (21). The servo (9) simultaneously controls the tilt states of the first blade (7) and the second blade (21) through the swashplate (8).

6. The cross-medium aircraft according to claim 4, characterized in that: The submersible module (6) includes a second ratchet (22) and a propeller (17). The second motor (19) is also connected to the propeller (17) through the rotating shaft (20) and the second ratchet (22) and is used to control the rotation of the propeller (17).

7. The cross-media aircraft according to claim 6, wherein: A rudder surface (18) is further arranged on the propeller, and the submersible attitude of the aircraft is controlled through the deflection direction of the rudder surface (18).

8. The cross-medium aircraft according to claim 6, characterized in that: A duct (16) is further arranged on the propeller (17), and the duct (16) is used to guide the water flow to reduce the noise generated by the propeller (17).

9. The cross-medium aircraft according to claim 1, characterized in that: An electromagnetic pin (23) is further arranged on the function module (1), and the function module (1) is connected to the aircraft through the electromagnetic pin (23).

10. A cross-medium aircraft according to claim 5, characterized in that: Placement grooves are further arranged on the first housing (10) and the second housing (15). When the first blade (7) and the second blade (21) are in the submersible state, they are located in the placement grooves.

Images