CN-121990161-A - Split type cross-medium aircraft

CN121990161ACN 121990161 ACN121990161 ACN 121990161ACN-121990161-A

Abstract

The invention discloses a split type cross-medium aircraft, which relates to the technical field of cross-medium aircraft and comprises an air-based unit, a water-based unit, a docking system and a controller, wherein the air-based unit comprises a fuselage, a flat vertical tail, two telescopic wings and two tilting rotor systems, each tilting rotor system comprises a tilting driving part, a first nacelle shell, a rotor driving part and a foldable rotor mechanism, the tilting driving part is fixed at one end of the telescopic wing far away from the fuselage, the tilting driving part is used for driving the first nacelle shell to tilt relative to the telescopic wings, the rotor driving part is fixed in the first nacelle shell and is used for driving the foldable rotor mechanism to rotate, and the water-based unit comprises a boat body, a thrust paddle system and a buoyancy adjusting system. The split type cross-medium aircraft solves the problems of large instantaneous load, high power demand and limited appearance of the fixed wing layout, overcomes the defects of high energy consumption, short range and low load of the multi-rotor layout, and adapts to diversified operation demands.

Inventors

ZHAO QIJUN
LIN MUYANG
CHEN ZHE
LI YAN
SHI XIAOCHUN

Assignees

南京启直航空科技有限公司

Dates

Publication Date: 20260508
Application Date: 20260408

Claims (10)

1. A split type medium-crossing aircraft is characterized by comprising an air-based unit, a water-based unit, a docking system and a controller, wherein the air-based unit comprises a fuselage, a vertical fin, two telescopic wings and two tilting rotor systems, the two telescopic wings are symmetrically fixed on two sides of the fuselage, one tilting rotor system is installed at one end, far away from the fuselage, of each telescopic wing, the tilting rotor system comprises a tilting driving part, a first nacelle shell, a rotor driving part and a foldable rotor mechanism, the tilting driving part is fixed on one end, far away from the fuselage, of the telescopic wings, the tilting driving part is used for driving the first nacelle shell to tilt relative to the telescopic wings, the rotor driving part is fixed in the first nacelle shell and is used for driving the foldable rotor mechanism to rotate, the vertical fin is fixed on the upper part of the tail end of the fuselage, the water-based unit comprises a boat body, a thrust propeller system and a buoyancy adjusting system, the fuselage can be detachably arranged on the boat body through the docking system, the propeller driving part is arranged on the boat body, the buoyancy adjusting system is connected with the boat body, and the buoyancy adjusting system is used for achieving the buoyancy system.
2. The split type cross-medium aircraft according to claim 1, wherein the tilting driving component is a tilting driving motor, a connecting block is fixed on one side of the first nacelle shell, the connecting block is fixedly sleeved on a power output shaft of the tilting driving motor, an axial direction of the power output shaft of the tilting driving motor is consistent with a length direction of the telescopic wing, and an axial direction of the first nacelle shell is perpendicular to an axial direction of the power output shaft of the tilting driving motor.
3. The split type cross-medium aircraft of claim 1, wherein the foldable rotor mechanism comprises a first hub and a plurality of foldable rotor assemblies sequentially arranged along the circumference of the first hub, the rotor driving component is used for driving the first hub to rotate, the first hub is located outside one end of the first nacelle shell, and the foldable rotor assemblies are connected with the controller.
4. The split type cross-medium aircraft according to claim 3, wherein the rotor driving component is a rotor driving motor, the first hub is fixedly sleeved on a power output shaft of the rotor driving motor, and an axial direction of the power output shaft of the rotor driving motor is consistent with an axial direction of the first nacelle shell.
5. The split type cross-medium aircraft according to claim 3, wherein the foldable rotor assembly comprises a folding driving motor and rotor blades, the folding driving motor is fixed on the outer wall of the first hub and connected with the controller, one end of each rotor blade is fixedly sleeved on a power output shaft of the folding driving motor, the axial direction of the power output shaft of the folding driving motor is perpendicular to the axial direction of the first hub, and the length direction of each rotor blade is perpendicular to the axial direction of the power output shaft of the folding driving motor.
6. The split type cross-medium aircraft according to claim 1, wherein the thrust system comprises two thrust mechanisms symmetrically arranged on two sides of the tail of the hull, the thrust mechanisms comprise a second nacelle shell, a thrust driving part, a second hub and a plurality of variable-diameter blades, the second nacelle shell is fixed on one side of the tail of the hull, the axial direction of the second nacelle shell is consistent with the length direction of the hull, the thrust driving part is fixed on the rear end of the second nacelle shell, the second hub is fixedly sleeved on a power output shaft of the thrust driving part, the second hub is positioned outside the rear end of the second nacelle shell, the axial direction of the power output shaft of the thrust driving part is consistent with the axial direction of the second nacelle shell, the variable-diameter blades are sequentially fixed on the outer wall of the second hub along the circumferential direction, and the thrust driving part and the variable-diameter blades are connected with the variable-diameter controllers respectively, and the variable-diameter blades can be adjusted.
7. The split type cross-medium aircraft according to claim 1, wherein the buoyancy adjusting system comprises two buoyancy adjusting mechanisms symmetrically arranged on two sides of the middle of the hull, the buoyancy adjusting mechanisms comprise an air bag, a high-pressure air storage part, a first pipeline, a second pipeline and an air extraction part, the air bag is fixed on one side of the middle of the hull, the high-pressure air storage part and the air extraction part are both fixed on the hull, the high-pressure air storage part is communicated with a first opening of the air bag through the first pipeline, a first valve is arranged on the first pipeline, the air extraction part is connected with a second opening of the air bag through the second pipeline, and the first valve, the second valve and the air extraction part are all connected with the controller.
8. The split type cross-medium aircraft according to claim 1, wherein the water-based unit further comprises two horizontal tail wings and two vertical tail wings, the two horizontal tail wings are symmetrically fixed to two sides of the tail end of the hull, and the two vertical tail wings are symmetrically fixed to two sides of the upper surface of the tail end of the hull.
9. The split type cross-medium aircraft of claim 1, wherein the docking system comprises a first docking mechanism and a second docking mechanism, a front portion of the hull upper surface is provided with a first groove that mates with the fuselage front structure, a rear portion of the hull upper surface is provided with a second groove that mates with the fuselage rear structure, the fuselage front is detachably mounted in the first groove of the hull by the first docking mechanism, the fuselage rear is detachably mounted in the second groove of the hull by the second docking mechanism, and both the first docking mechanism and the second docking mechanism are connected with the controller.
10. The split type cross-medium aircraft according to claim 9, wherein the first docking mechanism comprises a first upper docking assembly and a first lower docking assembly, the first upper docking assembly comprises a plurality of first upper guide rails which are parallel to each other and are sequentially arranged at intervals, the first upper guide rails are fixed on the lower surface of the front part of the aircraft body, the length direction of the first upper guide rails is consistent with the length direction of the aircraft body, the first lower docking assembly comprises a plurality of first lower guide rails which are parallel to each other and are sequentially arranged at intervals, the first lower guide rails are fixed in the first grooves, the length direction of the first lower guide rails is consistent with the length direction of the aircraft body, a first lower guide groove is formed between any two adjacent first lower guide rails, each first upper guide rail can be inserted into one first lower guide groove, one side of the first upper guide rails is provided with a first strip-shaped clamping groove, the first clamping groove does not penetrate through the length direction of the first upper guide rail, two first lower guide rails are sequentially arranged at intervals, the first clamping groove is close to the first strip-shaped part is fixedly connected with one side of the first strip-shaped part, and the first strip-shaped part is sequentially connected with the first strip-shaped part in a driving manner, and the first strip-shaped part is sequentially arranged along the length direction of the first strip-shaped part is sequentially; The second docking mechanism comprises a second upper docking assembly and a second lower docking assembly, the second upper docking assembly comprises a plurality of second upper guide rails which are mutually parallel and sequentially arranged at intervals, the second upper guide rails are fixed on the lower surface of the rear part of the body, the length direction of the second upper guide rails is consistent with the length direction of the body, the second lower docking assembly comprises a plurality of second lower guide rails which are mutually parallel and sequentially arranged at intervals, the second lower guide rails are fixed in the second grooves, the length direction of the second lower guide rails is consistent with the length direction of the boat body, a second lower guide groove is formed between any two second lower guide rails, each second upper guide rail can be inserted into one second lower guide groove, one side of each second upper guide rail is provided with a second strip-shaped clamping groove, each second strip-shaped clamping groove does not penetrate through the two ends of the second upper guide rails, the second lower guide rails are close to one side of each second strip-shaped clamping groove, each second strip-shaped clamping groove is provided with a second linear expansion joint part, and each second linear expansion joint part is sequentially connected with each second linear expansion joint part, and each second linear expansion joint part is arranged at one side of the second linear expansion joint part, and each linear expansion joint part is sequentially connected with each second linear expansion joint part.

Description

Split type cross-medium aircraft Technical Field The invention relates to the technical field of cross-medium aircrafts, in particular to a split type cross-medium aircraft. Background The cross-medium aircraft integrates the concepts of the submarine aircraft and the aircraft, has the functions of the submarine aircraft and the capability of freely crossing the water-air interface, and has important application value due to the characteristic. Performing a complete mission across a medium aircraft typically involves four states of motion, air cruising, underwater navigation, water entry and water exit. The overall layout of the cross-medium aircraft is more, and the cross-medium aircraft can be roughly divided into a multi-rotor type and a fixed-wing type. For multi-rotor layout cross-medium aircraft, low-speed high-torque water propellers are usually used for propulsion in water, and air propellers are relied on in the air. The buoyancy of the aircraft is slightly greater than the gravity, and when all motors are stopped, the aircraft can float on the water surface and serve as an intermediate state of medium transition. When the air propeller works, the aircraft can take off from the conventional water surface and fly in the air. Due to the lack of the fixed wings, the aircraft has high energy consumption, short range and low load. For a fixed wing layout of a medium-crossing aircraft, a sweepback layout is usually adopted, and a dive scheme is usually adopted during medium transition. The aircraft has the advantages that the aircraft is high in structural strength and skin materials, high in speed is required to be obtained instantaneously in water outlet, the power requirement is high, and the cross-section appearance of the aircraft is strictly limited. Meanwhile, the existing cross-medium aircraft adopts an integrated structure, all functional modules related to the air flight and underwater diving are integrated into a whole, independent disassembly and independent work of each functional module cannot be realized, the use flexibility is reduced, and the operation requirements of diversification are difficult to adapt. Disclosure of Invention In order to solve the technical problems, the invention provides a split type cross-medium aircraft, which solves the problems of large instantaneous load, high power demand and limited appearance of a fixed wing layout, overcomes the defects of high energy consumption, short range and low load of a multi-rotor wing layout, and adapts to diversified operation demands. In order to achieve the above object, the present invention provides the following solutions: The invention provides a split type cross-medium aircraft, which comprises an air-based unit, a water-based unit, a docking system and a controller, wherein the air-based unit comprises a fuselage, a vertical fin, two retractable wings and two tilting rotor systems, the two retractable wings are symmetrically fixed on two sides of the fuselage, one tilting rotor system is arranged at one end of each retractable wing, which is far away from the fuselage, the tilting rotor system comprises a tilting driving part, a first nacelle shell, a rotor driving part and a foldable rotor mechanism, the tilting driving part is fixed on one end of the retractable wings, which is far away from the fuselage, the tilting driving part is used for driving the first nacelle shell to tilt relative to the retractable wings, the rotor driving part is fixed in the first nacelle shell and is used for driving the foldable rotor mechanism to rotate, the vertical fin is fixed on the upper part of the fuselage, the water-based unit comprises a tilting propeller body, a thrust propeller system and a buoyancy adjusting system, the fuselage can be detachably arranged on the upper part of the docking system, the boat body can be connected with the buoyancy adjusting system, and the buoyancy adjusting system can be arranged on the boat body, the buoyancy adjusting system can be connected with the propeller driving part, the buoyancy adjusting system and the buoyancy adjusting system. Preferably, the tilting driving component is a tilting driving motor, a connecting block is fixed on one side of the first nacelle shell, the connecting block is fixedly sleeved on a power output shaft of the tilting driving motor, the axial direction of the power output shaft of the tilting driving motor is consistent with the length direction of the telescopic wing, and the axial direction of the first nacelle shell is perpendicular to the axial direction of the power output shaft of the tilting driving motor. Preferably, the foldable rotor mechanism comprises a first hub and a plurality of foldable rotor assemblies which are sequentially arranged along the circumference of the first hub, the rotor driving component is used for driving the first hub to rotate, the first hub is located outside one end of the first nacelle shell, and the foldable rotor assembl