CN114872884A

CN114872884A - Power device and aircraft

Info

Publication number: CN114872884A
Application number: CN202210515556.9A
Authority: CN
Inventors: 陈伟
Original assignee: Individual
Current assignee: Individual
Priority date: 2022-05-11
Filing date: 2022-05-11
Publication date: 2022-08-09

Abstract

The invention discloses a power device and an aircraft, wherein the power device comprises an annular duct, and at least one group of fans rotating in opposite directions are arranged in the annular duct; the fan includes the flabellum, and the flabellum rotates and sets up in annular duct, and the both ends of flabellum are equipped with first rotor and second rotor respectively, and the inner wall and the outer wall of annular duct are equipped with first stator and second stator respectively, and first stator and second stator mutually support with first rotor and second rotor respectively to order about the flabellum at annular duct internal rotation. The first stator and the second stator are respectively matched with the first rotor and the second rotor, so that the fan blades are driven to rotate in the annular duct, the traditional hub is omitted, the gas circulation area of the annular duct is greatly increased, the problems of gas flow leakage in blade top gaps and influence on the stability of a gas field are solved, the gas flow resistance is reduced, the gas flow is more uniform, the working stability of the aircraft is ensured, and the noise of the aircraft is reduced.

Description

Power device and aircraft

Technical Field

The invention relates to the technical field of aerospace, in particular to a power device and an aircraft.

Background

With the development of science and technology, the variety of aircrafts is increasing, such as fixed wing aircrafts, four-rotor aircrafts, ducted fan aircrafts and the like. In numerous aircraft kinds, use the duct aircraft of duct as power, because of it has the duct and for the mode of parcel screw for the flight of this aircraft is safer, can reduce the pneumatic interference of paddle and make pneumatic efficiency higher, but the duct aircraft work in narrow and small environment such as indoor, mine hole simultaneously for the duct aircraft becomes the key of people's research.

At present, the power device of the ducted aircraft generally works in a mode that a motor of a central shaft drives a hub to drive blades to rotate, and the mode has certain defects: the existence of the central shaft and the hub occupies a larger air circulation space of the duct, the turbulence inside the duct is serious, the airflow resistance is larger, and the thrust of the aircraft is influenced; boundary layer separation and secondary flow often exist at the joint of the hub and the blade, so that the energy conversion effect is influenced, and the working efficiency of the blade is reduced; in order to prevent the blade tips of the blades from rubbing against the duct, a gap is usually left between the blade tips and the duct, namely a blade tip gap, and when the air conditioner runs, high-pressure air on the pressure surface of the blades bypasses the blade tip gap and flows into the suction surface of the blades, so that not only is flow leakage generated and flow loss caused, but also the stability of an air field is damaged, and finally the efficiency of the whole air conditioner is reduced.

Disclosure of Invention

The invention aims to provide a power device and an aircraft, which solve the problems in the prior art.

In order to achieve the above object, in one aspect, the present invention adopts the following technical solutions: a power device comprises an annular duct, wherein at least one group of fans rotating in opposite directions are arranged in the annular duct; the fan comprises fan blades, the fan blades are rotatably arranged in the annular duct, a first rotor and a second rotor are arranged at two ends of each fan blade respectively, a first stator and a second stator are arranged on the inner wall and the outer wall of the annular duct respectively, and the first stator and the second stator are matched with the first rotor and the second rotor respectively to order about the fan blades to rotate in the annular duct.

As an alternative of the invention, the annular duct is provided with an air inlet and an air outlet, the air outlet being provided with a flow guiding device for adjusting the air flow direction of the air outlet to control the flight direction of the power plant.

As an alternative of the present invention, the flow guiding device comprises a plurality of angle-adjustable flow guiding plates, and the plurality of flow guiding plates are used for adjusting the air flow direction of the air outlet.

As an alternative of the invention, the air intake is provided with an auxiliary adjusting device for adjusting the intake air flow of the air intake to assist in controlling the flight direction of the power plant.

As an alternative of the present invention, the stator further includes a power supply device, and the power supply device is connected with a driving circuit, and the driving circuit is respectively connected with the coils of the first stator and the second stator.

As an alternative of the invention, the power supply device comprises a power battery pack, the power battery pack is connected with the driving circuit, the power battery pack is connected with a generator, and an exhaust port and a radiator of the generator both extend into the annular duct.

On the other hand, the invention adopts the following technical scheme: the aircraft comprises the power device, a cabin and a power cabin, wherein the annular duct is arranged between the cabin and the power cabin, and a support framework is connected between the cabin and the power cabin.

As an alternative of the present invention, the nacelle is a cylindrical structure, the power compartment is a dish-shaped structure, the outer wall of the nacelle is provided with a first stator, and the inner wall of the power compartment is provided with a second stator.

As an alternative scheme of the invention, a parachute cabin is arranged at the top of the cabin, and an auxiliary adjusting device is arranged on the outer wall of the parachute cabin.

As an alternative of the present invention, the auxiliary adjusting means includes a plurality of movable wings and fixed wings for adjusting the inflow rate of the air inlet, the fixed wings being disposed above the air inlet to prevent the parachute of the parachute bay from being sucked into the annular duct when the parachute is opened.

As an alternative of the invention, the supporting framework comprises a plurality of layers of horizontal supporting rods, and two ends of each horizontal supporting rod are respectively connected with the engine room and the power cabin.

As an alternative of the invention, the top of the nacelle is higher than the top of the power cabin, and a rigid pull rope is connected between the top of the nacelle and the top of the power cabin.

As an alternative of the invention, the bottom of the engine room is provided with a telescopic undercarriage, and the bottom of the power cabin is provided with a diagonal brace.

The invention has the beneficial effects that:

1. the annular duct is internally provided with at least one group of fans rotating in opposite directions, the opposite rotation can offset the reaction force of the unidirectional rotation of a single fan to achieve torque self-balance, and the annular duct can provide jet-type airflow along the direction of the annular duct to provide larger thrust for an aircraft.

2. According to the invention, the first rotor and the second rotor are respectively arranged at two ends of the fan blade, and the first stator and the second stator are respectively matched with the first rotor and the second rotor, so that the fan blade is driven to rotate in the annular duct.

3. The invention has simple and compact structure, convenient parking, high safety and fast navigation speed, reduces the sizes of a rotor wing and a tail compared with a helicopter with the same load, and improves the working efficiency and the endurance of a power device; compared with a multi-shaft rotorcraft with the same load, the size of the aerocraft and the size of the rotor wing are reduced by 50%, the power efficiency, the navigational speed and the navigational range are greatly improved, the safety is greatly improved, and the risk of exposed rotor wings and crash is avoided.

Drawings

FIG. 1 is a schematic structural diagram of an embodiment of the present invention.

In the figure: 1-a ring duct; 2-fan blades; 3-a first rotor; 4-a second rotor; 5-a first stator; 6-a second stator; 7-a flow guide plate; 8-a power battery pack; 9-a generator; 10-a heat sink; 11-a nacelle; 12-a power compartment; 13-parachute bay; 14-a movable wing; 15-fixed wing; 16-horizontal support bar; 17-a rigid pull cord; 18-telescoping landing gear; 19-diagonal brace rod.

Detailed Description

Examples

As shown in fig. 1, the present embodiment provides a power device, which is applied to ducted aircraft, such as unmanned aerial vehicles, helicopters, etc. The power device comprises an annular duct 1, wherein at least one group of fans rotating in opposite directions are arranged in the annular duct 1. The top and the bottom of the annular duct 1 are respectively provided with an air inlet and an air outlet, the fan sucks air into the annular duct 1 through the air inlet, and meanwhile, the air outlet exhausts air downwards to generate upward thrust to the aircraft, so that flight power is provided for the aircraft. Because the annular duct 1 is internally provided with at least one group of fans rotating in opposite directions, namely the annular duct 1 is internally provided with at least one air inlet fan and one pressure fan, the air inlet fan and the pressure fan are horizontally arranged up and down, the air inlet fan is close to the air inlet, the air inlet fan is positioned above the pressure fan, the rotating directions of the air inlet fan and the pressure fan are opposite, the air inlet fan and the pressure fan can offset torsion generated to the aircraft, the balance of the aircraft is maintained, and the vertical lifting of the aircraft is realized. When the power of the air inlet fan and the power of the pressure fan are increased in specific application, and when the thrust generated by the air inlet fan and the pressure fan to the aircraft is greater than the gravity of the aircraft, the aircraft vertically ascends away from the ground; when the power of the air inlet fan and the pressure fan is reduced and the thrust of the aircraft is smaller than the gravity of the aircraft, the aircraft vertically descends; when the thrust of the aircraft is equal to the gravity of the aircraft, the aircraft keeps a hovering state.

Specifically, the fan includes flabellum 2, flabellum 2 passes through the bearing rotation and sets up in annular duct 1, and the both ends of flabellum 2 are equipped with first rotor 3 and second rotor 4 respectively, annular duct 1's inner wall and outer wall are equipped with first stator 5 and second stator 6 respectively, first stator 5 and second stator 6 mutually support with first rotor 3 and second rotor 4 respectively to order about flabellum 2 at the 1 internal rotation of annular duct. The coils of the first stator 5 and the second stator 6 are supplied with electric energy, the first stator 5 and the second stator 6 generate alternate excitation magnetic fields and act on the first rotor 3 and the second rotor 4, so that the fan blades 2 are driven to rotate in the annular duct 1 to provide power for the aircraft. At least one group of fans rotating in opposite directions are arranged in the annular duct 1, the opposite rotation can offset the reaction force of the unidirectional rotation of a single fan to achieve torque self-balance, and jet type airflow along the direction of the annular duct 1 can be provided to provide larger thrust for an aircraft.

According to the invention, the first rotor 3 and the second rotor 4 are respectively arranged at two ends of the fan blade 2, the first stator 5 and the second stator 6 are respectively matched with the first rotor 3 and the second rotor 4, so that the fan blade 2 is driven to rotate in the annular duct 1, the traditional hub is omitted, the gas circulation area of the annular duct 1 is greatly increased, the problems of gas flow leakage of blade top gaps and influence on the stability of a gas field are solved, the gas flow resistance is reduced, the gas flow is more uniform, the working stability of the aircraft is ensured, and the noise of the aircraft is reduced.

In this embodiment, the air outlet is provided with a flow guiding device, and the flow guiding device is used for adjusting the airflow direction of the air outlet so as to control the flight direction of the power device. Preferably, the flow guiding device comprises a plurality of angle-adjustable flow guiding plates 7, and the flow guiding plates 7 are used for adjusting the air flow direction of the air outlet. The air outlet is equidistantly provided with a plurality of movable guide plates 7, and the air flow direction of the air outlet is changed by adjusting the angle of the guide plates 7, so that the aircraft can obtain the capability of turning left, right, forward, backward and rotationally, and the control of the flight direction of the aircraft is realized. By adjusting the angle of the guide plate 7, most of high-pressure high-speed air flow is sprayed to one direction, and the problem of slow navigational speed of the aircraft can be solved. Further, the air inlet is provided with an auxiliary adjusting device, and the auxiliary adjusting device is used for adjusting the air inlet flow of the air inlet so as to assist in controlling the flight direction of the aircraft.

The power device further comprises a power supply device, the power supply device is connected with a driving circuit, and the driving circuit is respectively connected with the coils of the first stator 5 and the second stator 6. The driving circuit controls the first stator 5 and the second stator 6 to generate alternate excitation magnetic fields to drive the first rotor 3 and the second rotor 4 to drive the fan blades 2 to rotate. The power supply device comprises a power battery pack 8, the power battery pack 8 is connected with a driving circuit, the power battery pack 8 is connected with a generator 9, the generator 9 can adopt a gasoline engine, and an exhaust port and a radiator 10 of the generator 9 both extend into the annular duct 1. The power device adopts oil-electricity hybrid power, the gasoline engine generates electricity to charge the power battery pack 8, and the power battery pack 8 drives the air inlet fan and the pressure fan to rotate, so that flight power is provided for the aircraft. The invention adopts the oil-electricity hybrid power to solve the problems of heavy weight, small electric quantity and short voyage of the pure power battery.

As shown in fig. 1, the present embodiment further provides an aircraft, which includes the above power plant, and further includes a nacelle 11 and a power cabin 12, where the annular duct 1 is disposed between the nacelle 11 and the power cabin 12, and a support framework is connected between the nacelle 11 and the power cabin 12. The nacelle 11 may be disposed inside the power pod 12, or the power pod 12 may be disposed inside the nacelle 11, the annular duct 1 is formed by a gap between the nacelle 11 and the power pod 12, and the nacelle 11 and the power pod 12 are connected by a support frame, thereby ensuring structural stability of the aircraft.

Preferably, the nacelle 11 is a cylindrical structure, the power compartment 12 is a disc-shaped structure, the first stator 5 is arranged on the outer wall of the nacelle 11, and the second stator 6 is arranged on the inner wall of the power compartment 12. The cabin 11 is located in the centre of the aircraft and has a large space for passengers or cargo etc. A power pod 12 is provided in the peripheral annular region of the nacelle 11 for storing the generator 9, an oil tank, the power battery pack 8, sensors and the like.

In this embodiment, the top of the nacelle 11 is provided with a parachute cabin 13, and the outer wall of the parachute cabin 13 is provided with an auxiliary adjusting device. The parachute cabin 13 is a lifesaving trajectory, plays an emergency rescue role, and can pop up a parachute to enable the aircraft to slowly land. The auxiliary adjusting device is arranged on the outer wall of the parachute cabin 13 and can adjust the air inlet flow of the air inlet. Specifically, supplementary adjusting device includes four activity wings 14 and four stationary vanes 15, and stationary vane 15 fixed mounting is in the outer wall of parachute cabin 13, and activity wing 14 movable mounting is in the outer wall of parachute cabin 13, and activity wing 14 and stationary vane 15 all set up in the air inlet top to be close to the air inlet, the air inlet flow of the adjustable air inlet of activity wing 14 and stationary vane 15 provides supplementary steering effect for the aircraft. The fixed wings 15 shield a portion of the air inlet to prevent the parachute from being sucked into the circular duct 1 by the parachute cords when the parachute is opened.

The top of the cabin 11 is higher than the top of the power cabin 12, and the height of the cabin 11 is 1.2-1.5 times of the height of the power cabin 12, so that a driver can view the surrounding environment. Both the power pod 12 and the nacelle 11 are closed structures so that the aircraft can stay on the water. The bottom in cabin 11 is equipped with flexible undercarriage 18, makes things convenient for the aircraft to descend, and this aircraft is little to the place requirement of taking off and land, can take off and land in places such as earth, meadow, the surface of water, naval vessel, roof, special place. The supporting framework comprises a plurality of layers of horizontal supporting rods 16, the horizontal supporting rods 16 penetrate through the annular duct 1, and two ends of each horizontal supporting rod 16 are respectively connected with the engine room 11 and the power cabin 12. The bottom of the power cabin 12 is provided with an inclined stay bar 19, a rigid stay rope 17 is connected between the top of the cabin 11 and the top of the power cabin 12, and the structural stability of the cabin 11 and the power cabin 12 can be enhanced by the multiple layers of horizontal support bars 16, the inclined stay bar 19 and the rigid stay rope 17, so that the overall structural stability of the aircraft is ensured, and the weight of the aircraft is reduced.

The aircraft has the functions of 360-degree omnidirectional maneuvering, vertical take-off and landing and horizontal cruising, and has the advantages of simple and compact structure, light weight, simple and convenient control, convenient parking, high safety and high cruising speed. Compared with a helicopter with the same load, the size of a rotor wing and a tail is reduced, and the working efficiency and the endurance of the power device are improved; compared with a multi-shaft rotorcraft with the same load, the size of the aerocraft and the size of the rotor wing are reduced by 50%, the power efficiency, the navigational speed and the navigational range are greatly improved, the safety is greatly improved, and the risk of exposed rotor wings and crash is avoided.

In the description of the present invention, the terms "mounted," "connected," "fixed," and the like are to be understood broadly and may be fixedly connected, detachably connected, or integrated; may be a mechanical or electrical connection; either directly or indirectly through intervening media, either internally or in any other relationship. Those skilled in the art will understand the specific meaning of the above terms in the present invention. Furthermore, the particular features, structures, etc. described in the examples can be included in at least one implementation and can be combined by one skilled in the art without conflicting therewith. The protection scope of the present invention is not limited to the above specific examples, and embodiments that can be imagined by those skilled in the art without creative efforts based on the basic technical concept of the present invention belong to the protection scope of the present invention.

Claims

1. A power device comprises an annular duct (1), and is characterized in that at least one group of fans rotating in opposite directions are arranged in the annular duct (1); the fan includes flabellum (2), flabellum (2) rotate to set up in annular duct (1), and the both ends of flabellum (2) are equipped with first rotor (3) and second rotor (4) respectively, the inner wall and the outer wall of annular duct (1) are equipped with first stator (5) and second stator (6) respectively, first stator (5) and second stator (6) mutually support with first rotor (3) and second rotor (4) respectively to order about flabellum (2) at annular duct (1) internal rotation.

2. A power plant according to claim 1, characterized in that the annular duct (1) is provided with an air inlet and an air outlet, the air outlet being provided with flow guiding means for adjusting the direction of the air flow at the air outlet for controlling the flight direction of the power plant.

3. A power plant according to claim 2, characterized in that the air guiding device comprises a plurality of angle-adjustable air guiding plates (7), and a plurality of air guiding plates (7) are used for adjusting the air flow direction of the air outlet.

4. The power plant of claim 2, wherein the air intake is provided with an auxiliary adjustment device for adjusting the intake air flow of the air intake to assist in controlling the direction of flight of the power plant.

5. A power plant according to claim 1, characterized by further comprising a power supply device to which a driving circuit is connected, said driving circuit being connected to the coils of the first stator (5) and the second stator (6), respectively; the power supply device comprises a power battery pack (8), the power battery pack (8) is connected with a driving circuit, the power battery pack (8) is connected with a generator (9), and an exhaust port and a radiator (10) of the generator (9) extend into the annular duct (1).

6. An aircraft, characterized in that, includes the power device of any one of claims 1-5, and further includes a cabin (11) and a power cabin (12), the annular duct (1) is disposed between the cabin (11) and the power cabin (12), and a supporting framework is connected between the cabin (11) and the power cabin (12).

7. The aircraft of claim 6, characterized in that the nacelle (11) is of a cylindrical configuration, the power pod (12) is of a dished configuration, the outer wall of the nacelle (11) being provided with the first stator (5) and the inner wall of the power pod (12) being provided with the second stator (6).

8. The aircraft according to claim 6, characterized in that the top of said nacelle (11) is provided with a parachute bay (13), the outer wall of said parachute bay (13) being provided with auxiliary adjustment means.

9. The aircraft according to claim 8, characterized in that said auxiliary adjustment means comprise a plurality of movable wings (14) and fixed wings (15), said movable wings (14) and fixed wings (15) being capable of adjusting the intake air flow of the air intake, said fixed wings (15) being arranged above the air intake in order to prevent the parachute of the parachute bay (13) from being sucked into the annular duct (1) when opening the parachute.

10. The aircraft of claim 6, characterized in that the supporting framework comprises a plurality of layers of horizontal supporting rods (16), wherein both ends of the horizontal supporting rods (16) are respectively connected with the cabin (11) and the power cabin (12); the top of the cabin (11) is higher than the top of the power cabin (12), and a rigid pull rope (17) is connected between the top of the cabin (11) and the top of the power cabin (12); the bottom of the cabin (11) is provided with a telescopic undercarriage (18), and the bottom of the power cabin (12) is provided with an inclined stay bar (19).