CN220809789U

CN220809789U - Dish-shaped rotor craft

Info

Publication number: CN220809789U
Application number: CN202322472928.7U
Authority: CN
Inventors: 李四海
Original assignee: Individual
Current assignee: Individual
Priority date: 2023-09-12
Filing date: 2023-09-12
Publication date: 2024-04-19
Anticipated expiration: 2033-09-12

Abstract

The utility model relates to a disk-shaped rotor craft, which comprises a cockpit shell, wherein two groups of rotor wing assemblies are symmetrically arranged at the upper end and the lower end of the outer periphery side of the cockpit shell; the rotor wing assembly comprises a fixed ring, a movable ring and a blade frame, wherein the blade frame comprises a bottom frame and a vertical frame, a lifting driving blade assembly is paved on the bottom frame, and the vertical frame is connected with a translation driving blade assembly; the lifting driving blade assembly comprises lifting blades, a lifting crankshaft and a lifting slip ring, wherein the end part of the lifting crankshaft is limited and inserted in the lifting slip ring, and the end part of the cockpit shell is provided with a lifting adjusting mechanism; the translation driving blade assembly comprises a translation blade, a translation crankshaft and a translation slip ring, wherein the translation crankshaft is limited and inserted in the translation slip ring, and a horizontal adjusting mechanism is arranged at the end part of the cockpit shell, so that the horizontal adjustment of the position of the aircraft in the normal standing posture can be realized; high mobility and high flexibility.

Description

Dish-shaped rotor craft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to a disk-shaped rotor wing aircraft.

Background

The aircraft is divided into two main types of fixed wings and rotary wings according to the driving mode, wherein the fixed wing aircraft generates lift force by means of pressure difference formed by air flow speed difference fixed on the upper side and the lower side of the wing. The rotary wing aircraft generates lift force by means of the rotating spiral warp, and has the advantages of low-speed cruising, fixed-point hovering, vertical taking off and landing, capability of executing tasks in a narrow space and the like compared with a fixed wing aircraft.

The traditional multi-rotor aircraft realizes hovering, front and back flying, side flying, steering and the like by controlling the motor rotation speeds of a plurality of rotors, has the characteristics of small volume, light weight, simple structure, convenient control, low cost and the like, and has been widely applied to the fields of agriculture, mapping, military, security protection, disaster relief and the like in recent years. However, the conventional multi-rotor aircraft has a certain limitation, and the multi-rotor aircraft is used as a typical under-actuated system, and the lifting force of the aircraft is perpendicular to the plane of the aircraft body in the flight process, so that the aircraft can only be realized by adjusting the posture of the aircraft body to generate a component force when the forward and backward flight, the left and right flight and other flight actions are realized.

As disclosed in the chinese patent application No. CN111559499a, the disc-shaped aircraft includes a duct that is hollow cylinder and penetrates up and down, the upper section has a duct air inlet, the lower end is connected with a gesture control cylinder, the duct is provided with an upper fan and a lower fan, the two fans rotate to generate lift required by the unmanned aerial vehicle, and the inner ring of the gesture control cylinder slides relative to the fixed ring, so as to adjust the angle deflection of the outlet airflow of the duct, generate a vector thrust effect, and adjust the gesture of the aircraft.

The structure of the rotorcraft described above has the following problems: (1) When the aircraft is required to incline, advance and retreat and horizontally translate by pushing the horizontal component of the thrust of the fan, the flying speed and the maneuverability of the aircraft are greatly limited, and the traditional multi-rotor aircraft is insufficient especially for working environments and tasks with specific flying postures. (2) The duct of the aircraft is designed in the middle of the aircraft, so that a driving bin cannot be designed in the aircraft, and space improvement of manned flight cannot be realized.

Disclosure of utility model

In order to overcome the defects of the rotor craft, the utility model aims to provide the disk-shaped rotor craft, so that the dynamic coupling of the vertical attitude and the horizontal movement of the craft is realized by changing the opening and closing size and the tilting direction of the rotor, the flexibility and the maneuverability of the craft are improved, and the manned function of the disk-shaped rotor craft is met.

In order to solve the problems, the disc-shaped rotor craft provided by the utility model adopts the following technical scheme:

The disc-shaped rotor craft comprises a cockpit shell with a spherical structure, wherein an annular shell is sleeved on the outer periphery of the cockpit shell, the annular shell and the cockpit shell are coaxially sleeved so that an annular flow passage which is penetrated up and down is arranged between the annular shell and the cockpit shell in a surrounding manner, two groups of rotor wing assemblies are symmetrically arranged at the upper end and the lower end of the annular flow passage, and an orientation adjusting mechanism for adjusting the orientation of the craft is arranged in the middle of the annular flow passage;

The rotor assembly comprises a fixed ring fixed at the end part of the cockpit shell, the axis of the fixed ring extends up and down, a movable ring is assembled on the fixed ring along the annular direction, the movable ring is provided with a driving structure for driving the movable ring to circumferentially rotate around the fixed ring, the rotor assembly further comprises a blade frame, the blade frame comprises a bottom frame connected with the end part of the annular flow channel, the radial inner side of the bottom frame is connected with a vertical frame which is annularly arranged and vertically extends, the bottom frame is paved with a lifting driving blade assembly, and the vertical frame is connected with a translation driving blade assembly;

The lifting driving blade assembly comprises a plurality of lifting blades paved on a chassis, supporting shafts of the lifting blades are rotatably inserted on the chassis and the movable ring, the rotation axes of the lifting blades extend along the radial direction of the movable ring, the inner ends of the supporting shafts of the lifting blades are connected with lifting crankshafts, lifting slip rings are movably assembled at the end parts of the cockpit shell, the end parts of the lifting crankshafts are limited and inserted in the lifting slip rings and move circumferentially in the lifting slip rings, and lifting adjusting mechanisms for driving the lifting slip rings to pitch up and down to drive lifting slip rings to pitch up and down so as to adjust the opening and closing angles of the lifting blades are further arranged at the end parts of the cockpit shell;

The translation drive blade subassembly is including laying a plurality of translation blade on the side bearer, and the back shaft rotation cartridge in each translation blade is on side bearer and go-between, extend from top to bottom in the axis of rotation of translation blade, the inner of translation blade back shaft still is connected with the translation bent axle, the tip activity of cockpit shell is equipped with the translation sliding ring, the spacing cartridge of translation bent axle is in the translation sliding ring to circumference removes in the translation sliding ring, the tip of cockpit shell is equipped with and is used for driving translation sliding ring horizontal migration in order to drive each translation bent axle swing, and then adjusts each translation blade angle of opening and shutting's horizontal adjustment mechanism.

Further, the fixed ring has two, along upper and lower direction interval arrangement side by side, the expansion ring is arranged between two fixed rings, around being equipped with the coil on the fixed ring, the expansion ring is the iron material, driving structure is for being used for the power supply that makes two fixed rings produce magnetic attraction to the coil power supply, the expansion ring receives coil magnetism absorption and rotates the suspension between two expansion rings.

Further, a plurality of U-shaped snap rings are annularly arranged at the rear sides of the upper end and the lower end of the cockpit shell, openings of the U-shaped snap rings extend along the radial direction of the fixing rings, the two fixing rings are respectively fixed on the upper side wall and the lower side wall of the U-shaped snap rings, the lifting slip ring is arranged above the U-shaped snap rings, and the translation slip ring is arranged below the U-shaped snap rings.

Further, the lifting adjusting mechanism comprises lifting telescopic cylinders connected between the cockpit shell and the lifting slip ring, wherein more than three lifting telescopic cylinders are uniformly distributed around the circumferential direction of the lifting slip ring.

Further, the horizontal adjusting mechanism comprises a translation telescopic cylinder connected between the cockpit shell and the horizontal slip ring, wherein more than three translation telescopic cylinders are uniformly distributed around the circumferential space of the horizontal slip ring.

Further, the outer end of the chassis is fixedly connected with the ring shell so as to coaxially sleeve the ring shell and the cockpit shell, the orientation adjusting mechanism comprises a plurality of adjusting blades rotationally assembled on the outer wall of the cockpit shell, the rotation axes of the adjusting blades extend along the radial direction of the annular flow channel, the adjusting blades are uniformly distributed along the circumferential direction of the annular flow channel at intervals, and the inner ends in the adjusting blades are connected with gesture adjusting controllers for controlling the opening and closing angles of the adjusting blades.

Further, the rotation directions of the lifting blades in the two rotor wing assemblies are opposite, and the opening and closing inclination directions of the two blades are opposite.

Further, the bottom of the cockpit shell is connected with an elevator which extends up and down and is communicated with the inside of the cockpit shell, and the periphery of the elevator is connected with supporting feet.

The beneficial effects of the utility model are as follows: compared with the prior art, the rotor craft related by the utility model realizes the manned requirement of the disc-shaped craft by designing the cockpit shell in the actual working process; in addition, an outer ring shell is sleeved outside the cockpit shell, a circumferential flow channel is formed between the outer ring shell and the cockpit shell, the outer ring shell is vertically symmetrically arranged through two groups of rotor wing assemblies, and the movable ring is driven to rotate through the driving structure, so that horizontal blades and lifting blades in the rotor wing assemblies are driven to rotate; the lifting blades adjust the opening and closing angles through the movement of the lifting slide rails, lifting operation of the aircraft is realized through different gas flow rates when the lifting blades rotate, and the translation blades realize the increase of the opening and closing angles of the blades at corresponding positions and the decrease of the opening and closing angles of the translation blades at the other side through the translation movement of the translation slide rails, so that the translation blades at different positions in the circumferential direction stir different amounts of air in the horizontal direction for a single time, air pressure difference is generated, and the position horizontal adjustment of the aircraft in the normal standing position can be realized; high mobility and high flexibility. Simultaneously, the direction of the aircraft is adjusted through the direction adjusting mechanism, so that the cockpit shell can be prevented from synchronously rotating relative to the rotor wing assembly, and the operation experience of a pilot is influenced. The device has the advantages of simple integral structure, convenient adjustment, compact structure, no site limitation and attractive appearance, and a driver can independently finish the operations such as lifting, steering, translation, deflection and the like of the aircraft in the driving cabin.

Drawings

In order to more clearly illustrate the technical solution of the embodiments of the present utility model, the following briefly describes the drawings that are required to be used in the embodiments:

FIG. 1 is a schematic structural view of an embodiment of a disk-shaped rotorcraft of the present utility model;

FIG. 2 is a front semi-sectional view of FIG. 1;

FIG. 3 is a schematic illustration of the structure of FIG. 1 with the ring housing and adjustment vanes removed;

FIG. 4 is a front semi-sectional view of FIG. 3;

FIG. 5 is an enlarged view of a portion of FIG. 4 at A;

FIG. 6 is a cross-sectional view of the assembled structure of the blade holder and the stationary, movable and slip rings of FIG. 3;

FIG. 7 is a schematic illustration of the translational drive blade assembly of FIG. 5;

fig. 8 is a schematic view of the lifting blade of fig. 5.

Reference numerals illustrate: 1-a cockpit shell 1; 2-support feet 2; 3-elevator 3; 4-rotor assemblies 4; a 5-U-shaped clasp 5; 6-a fixing ring 6; 7-a movable ring 7; 8-coil 8; 9-blade frame 9; 10-a chassis 10; 11-a stand 11; 12-lift drive blade assembly 12; 13-a translational drive blade assembly 13; 14-translating the blade 14; 15-translating the crankshaft 15; 16-a translational slip ring 16; 17-ring groove 17; 18-dished bumps 18; 19-translation telescopic cylinder 19; 20-lifting blade 20; 21-lifting the crankshaft 21; 22-lifting slip ring 22; 23-lifting telescopic cylinder 23; 24-gyroscope 24; 25-cab 25; 26-a ring housing 26; 27-a circumferential flow channel 27; 28-adjusting the vanes 28.

Detailed Description

In order to make the technical purpose, technical scheme and beneficial effect of the present utility model more clear, the technical scheme of the present utility model is further described below with reference to the accompanying drawings and specific embodiments. It should be understood that the particular embodiments described herein are illustrative only and are not intended to limit the utility model, i.e., the embodiments described are merely some, but not all, of the embodiments of the utility model. The components of the embodiments of the present utility model generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

As shown in fig. 1 to 8, the disk-shaped rotary wing aircraft according to the embodiment of the present utility model includes a cockpit shell 1 having a disk-shaped structure, wherein the cockpit shell 1 is hollow at the inside, has an opening at the bottom, a lift car 3 inserted into the cabin is connected to the opening, a cockpit 25 is disposed inside the cockpit shell 1 on the peripheral side of the lift car 3, and an opening/closing door is provided between the cockpit 25 and the lift car 3. The bottom circumference side at elevator 3 is provided with round supporting legs 2, and supporting legs 2 are used for supporting cockpit shell 1 above ground, and during the in-service use, with elevator 3's inner box decline to ground, the driver gets into the inner box, then elevator 3 rises, gets into in the cabin, and the driver can get into inside the aircraft.

The outer peripheral side of the cockpit shell 1 is connected with a ring shell 26, the ring shell 26 and the cockpit shell 1 are coaxially sleeved so that a ring-shaped flow passage 27 which is vertically communicated is arranged between the ring shell 26 and the cockpit shell, and the ring shell 26 and the cockpit shell are surrounded for gas circulation.

Two sets of rotor assemblies 4 are symmetrically arranged at the positions of the ports at the two ends of the annular flow channel 27 at the upper end and the lower end of the cockpit, the structures of the two sets of rotor assemblies 4 are consistent and symmetrical, the rotor assemblies 4 at the upper side are taken as an example, as shown in the figure, the rotor assemblies 4 comprise fixed rings 6 fixed at the end part of the cockpit shell 1, the axes of the fixed rings 6 extend up and down, movable rings 7 are assembled on the fixed rings 6 along annular direction, and the movable rings 7 are provided with driving structures for driving the movable rings 7 to rotate around the fixed rings 6 in the circumferential direction. Specifically, the two fixed rings 6 are arranged side by side along the vertical direction at intervals, the movable ring 7 is arranged between the two fixed rings 6, a plurality of groups of coils 8 are wound on the fixed rings 6, the movable ring 7 is made of iron, the driving structure is a power supply for supplying power to the coils 8 so that the two fixed rings 6 generate magnetic attraction, and the movable ring 7 is magnetically adsorbed by the coils 8 to rotate and suspend between the two movable rings 7. When the movable ring 7 is required to rotate, the power supply supplies power to the coils 8, the coils 8 generate magnetism after being electrified, the two coils 8 absorb the movable ring 7, and the movable ring 7 is suspended between the two fixed rings 6 by adjusting the size of the magnetic attraction force, so that the problems of abrasion, noise and the like caused by rotation of the movable ring 7 can be effectively avoided. Meanwhile, the coils 8 of different groups are arranged end to end in sequence to form a rotating magnetic field, the movable ring 7 receives electromagnetic force in the rotating magnetic field, the electromagnetic force forms torque on the rotor, and the movable ring 7 can circumferentially rotate between the fixed rings 6.

The fixed ring 6, the movable ring 7, the coil 8 and the like are combined to form the magnetic suspension motor.

The magnetic suspension motor is composed of an upper layer structure, a middle layer structure and a lower layer structure. The stator comprises an upper stator, a lower stator and a middle rotor, wherein the upper stator and the lower stator are fixed rings 6, the middle rotor is movable rings 7, the upper stator is provided with three annular magnetic steels, coils 8 are wound on the magnetic steels, the magnetic steels and the coils 8 are fixed below the fixed rings 6, the first coil 8 is arranged below the outer edge of the fixed rings 6 and is called a direct current motor coil 8, the second coil 8 is arranged at a middle position and is called an electromagnetic suspension iron core coil 8, and the third coil 8 is arranged on the inner side and is called a generator coil 8. The middle layer structure is a rotor, the rotor is an annular iron steel plate, three U-shaped grooves are respectively formed in the upper side and the lower side, and permanent magnets are inlaid in the inner walls of the U-shaped grooves. The lower layer stator structure is the same as the upper layer stator structure, the upper layer stator and the lower layer stator are oppositely arranged, the coil 8 is opposite, the rotor is arranged between the upper layer stator and the lower layer stator, the coil 8 arranged on the upper layer stator and the lower layer stator is respectively inserted into the double-sided U-shaped grooves of the rotor, the U-shaped clamping ring 5 is fixedly connected with the motor shell of the upper layer stator and the lower layer stator, and the middle layer rotor can be suspended due to magnetic force generated by the upper layer stator and the lower layer stator.

The upper and lower stator electromagnetic levitation iron core coils 8 are electrified with direct current to generate a magnetic field, so that the rotor is in a levitation state; the upper and lower layers of direct current motor coils 8 are connected with direct current to generate a magnetic field to drive the rotor to rotate, the permanent magnet magnetic field on the rotor cuts the generator coils 8 to generate current in the generator coils 8, and the generated electric energy is stored in a battery for recycling.

The rotor wing assembly 4 further comprises a blade frame 9, wherein the blade frame 9 comprises a bottom frame 10 which is arranged at the end part of the annular flow channel 27 and fixedly connected to the outer side of the movable ring 7, a vertical frame 11 which is arranged in an annular way and vertically extends is fixedly connected to the radial inner side of the bottom frame 10, a lifting driving blade assembly 12 is paved on the bottom frame 10, and a translation driving blade assembly 13 is connected to the vertical frame 11. Meanwhile, in order to achieve the fixation of the ring cover 26, the outer end of the chassis 10 and the end edge of the ring cover 26 are welded and fixed.

The lift driving vane assembly 12 includes a plurality of lift vanes 20 laid on the chassis 10, the supporting shaft of each lift vane 20 is rotatably inserted on the chassis 10 and the movable ring 7, the rotation axis of the lift vane 20 extends along the radial direction of the movable ring 7, the inner end of the supporting shaft of the lift vane 20 is connected with a lift crankshaft 21, the lift crankshaft 21 is biased to one side of the supporting shaft of the lift vane 20, the two are circumferentially parallel, when the lift crankshaft 21 swings up and down, the supporting shaft can rotate relatively, the end of the cockpit shell 1 is movably provided with a lift slip ring 22, the end of the lift crankshaft 21 is limitedly inserted in the lift slip ring 22 and moves circumferentially in the lift slip ring 22, in particular, the outer side wall of the lift slip ring 22 is provided with a ring groove 17, the cross section of the ring groove 17 is in an inverted T-shaped groove structure, the end of the lift crankshaft 21 is provided with a lug 18 for being inserted into the ring groove 17 and limiting and anti-disengaging with the ring groove 17, and when the movable ring 7 rotates, the position of the lift slip ring 22 is fixed, since the supporting shaft in each lift lug is inserted on the movable ring 7 and 10, the chassis 10 and each lift slip ring 20 rotates synchronously, and the lift slip ring 21 moves circumferentially in the ring 17.

In order to realize the adjustment of the opening and closing angles of the lifting blades 20, the end part of the cockpit shell 1 is also provided with a lifting adjusting mechanism for driving the lifting slip ring 22 to pitch up and down to drive the lifting slip ring 22 to pitch up and down so as to adjust the opening and closing angles of the lifting blades 20; specifically, the lifting adjusting mechanism comprises lifting telescopic cylinders 23 connected between the cockpit shell 1 and the lifting slip ring 22, and three lifting telescopic cylinders 23 are uniformly distributed around the circumferential direction of the lifting slip ring 22. When the aircraft is required to ascend or descend, the driver controls each lifting telescopic cylinder 23 to synchronously stretch and retract, so that the lifting sliding rings 22 are vertically translated to the relative positions, at the moment, the lifting crankshafts 21 of each lifting blade 20 synchronously swing, so that each lifting blade 20 synchronously opens and closes to the same angle, the magnetic suspension motor works to drive the movable ring 7 to rotate, the lifting blades 20 can be driven to rotate, and then a pressure difference is formed between the upper rotor wing assembly 4 and the lower rotor wing assembly 4, so that the ascending and descending operation of the aircraft is realized. When the aircraft is tilted, the aircraft needs to be aligned, at this time, the expansion and contraction amount of the lifting and contracting cylinder 23 on one side of the yaw direction is increased, and the crankshaft of the lifting and contracting blade 20 in this direction is pushed down or lifted up, so that the opening of the upgrade blade is increased, the airflow velocity per unit time is increased, and the opening of the lifting and contracting blade 20 at other positions in the circumferential direction of the movable ring 7 is kept unchanged or reduced, so that a pressure difference is generated on the circumferential surface, and the attitude of the aircraft is gradually adjusted to the upright attitude. That is, the lifting and telescoping cylinder 23 controls the position of the lifting and telescoping slip ring 22, so that the operations of lifting, hovering, yaw attitude correction and the like of the aircraft can be adjusted.

The translation driving vane assembly 13 comprises a plurality of translation vanes 14 paved on the side frame, the supporting shafts in the translation vanes 14 are rotatably inserted on the side frame and the movable ring 7, the rotating axes of the translation vanes 14 extend up and down, the bottom ends of the supporting shafts of the translation vanes 14 are also connected with translation crankshafts 15, the translation crankshafts 15 are eccentrically arranged on one sides of the supporting shafts of the translation vanes 14, the translation crankshafts 15 are arranged in parallel, the translation crankshafts 15 can swing circumferentially relative to the supporting shafts, in the swinging process, the supporting shafts can be driven to rotate, the opening and closing angles of the translation vanes 14 are further adjusted, the end part of the cockpit shell 1 is movably provided with a translation sliding ring 16, the upper end of the translation sliding ring 16 is provided with a circle of annular groove 17, the annular groove 17 is integrally in an inverted T-shaped structure, the end part of the corresponding translation crankshaft 15 is provided with a disc-shaped lug 18 in the limiting inserting annular groove 17, is inserted in the translation sliding ring 16 in the up and down direction, and moves circumferentially in the translation sliding ring 16.

In order to realize the horizontal movement of the aircraft, in this embodiment, a horizontal adjustment mechanism for driving the translational slip ring 16 to horizontally move to drive each translational crankshaft 15 to swing and further adjust the opening and closing angles of each translational blade 14 is provided at the end of the cockpit shell 1. The main principle is that the opening and closing angles of each translation blade 14 in the circumferential direction are adjusted, and the air pressure in the set direction is smaller than the air pressure on the opposite side due to the fact that the angles are different, so that the aircraft can be driven to move transversely. The horizontal adjusting mechanism comprises three translational telescopic cylinders 19 connected between the cockpit shell 1 and the horizontal slip ring, and the translational telescopic cylinders 19 are uniformly distributed around the circumferential direction of the horizontal slip ring at intervals. For example, when the aircraft needs to move horizontally forward, the translational slip ring 16 is pulled to the rear side, at this time, the translational crank 15 is synchronously swung and the swing amplitude is different, so that the front translational vane 14 is driven to be opened outwards, more air is stirred, the rear translational vane 14 is reversely swung to the inner side, an air flow mode that the front stirring air volume is large and the rear stirring air volume is small is gradually formed, and the translational vane 14 is guided to move horizontally forward through the air pressure difference formed by the air volume in the circumferential rotation process. Lateral translation and rearward movement are the same.

When the aircraft needs to be adjusted to move in the deviated posture, the power difference in the horizontal direction of the upper end and the lower end of the aircraft can be caused by adjusting the movement amplitude of the translational slip ring 16 in the upper rotor assembly 4 and the translational slip ring 16 in the lower rotor assembly 4, so that the deviated posture of the aircraft can be moved.

In addition, in order to realize the installation of the rotor assembly 4 on the cockpit shell 1, a plurality of U-shaped snap rings are annularly arranged at the rear sides of the upper end and the lower end of the cockpit shell 1, the opening of the U-shaped snap ring 5 extends along the radial direction of the fixed ring 6, the two fixed rings 6 are respectively fixed on the upper side wall and the lower side wall of the U-shaped snap ring 5, the lifting slip ring 22 is arranged above the U-shaped snap ring 5, and the translation slip ring 16 is arranged below the U-shaped snap ring 5. And the inner end of the blade frame 9 is connected to the movable ring 7 through the support shaft of the horizontal blade, so that the movable ring 7 and the rotor assembly 4 can rotate circumferentially relative to the cockpit shell 1.

In addition, an orientation adjusting mechanism for adjusting the orientation of the aircraft is arranged in the middle of the circumferential flow channel 27, specifically, the orientation adjusting mechanism comprises a plurality of adjusting blades 28 rotationally assembled on the outer wall of the cockpit shell 1, the eastern rotation axes of the adjusting blades 28 extend along the radial direction of the circumferential flow channel 27, the adjusting blades 28 are uniformly distributed along the circumferential direction of the circumferential flow channel 27 at intervals, the inner ends of the adjusting blades 28 are connected with gesture adjusting controllers for controlling the opening and closing angles of the adjusting blades 28, meanwhile, a gyroscope 24 (not shown in the drawing) is suspended in the cockpit shell 1, the structure and the working principle of the gyroscope 24 are consistent with those of the prior art, the gyroscope 24 is not specifically described in the embodiment, the gyroscope is mainly used for deflection detection of the aircraft, the gyroscope 24 is uniformly distributed along the circumferential direction of the cockpit shell 1, and the gyroscope 24 is connected with the gesture adjusting controllers for detection so as to sample the gesture of each gyroscope 24. In the actual operation process, in order to avoid the circumferential rotation of the cockpit shell 1 relative to the rotor assembly 4, the gesture adjustment controller controls the opening of the adjustment blade 28, so that when the adjustment blade 28 is blown by the airflow entering the circumferential flow channel 27, the rotation direction of the adjustment blade 28 is opposite to the rotation direction of the lifting blade 20, the circumferential position of the cockpit shell 1 relative to the rotor assembly 4 can be fixed, when the steering is needed, the adjustment blade 28 is correspondingly adjusted, the opening and closing angle is increased or reduced, the air volume in unit time in the circumferential flow channel 27 is changed, the balance state is damaged, the adjustment blade 28 drives the cockpit shell 1 to circumferentially rotate relative to the rotor assembly 4, and after the adjustment blade 28 is rotated to a certain direction, the purpose of adjusting the direction of the aircraft is achieved.

In addition, in order to make the moment that two rotor assemblies 4 produced relative cockpit shell 1 when rotating cause cockpit shell 1 to rotate from top to bottom, the rotation direction of lift blade 20 in two rotor assemblies 4 is opposite, and the tilting direction that opens and shuts of two blades is opposite to counter the moment that two rotor assemblies 4 produced, guarantee the stability of gesture in the flight of aircraft.

Preferably, two levers may be provided in the cab 25 for convenience of control, one of which controls the opening and closing of the translation blades 14 and the other of which controls the opening and closing angle adjustment of the lifting blades 20. The transmission mode between the control rod and the corresponding slip ring can be designed arbitrarily according to actual needs by a person skilled in the art, for example, the control rod can be used for controlling the telescopic actions of each telescopic cylinder through a mechanical link mechanism and the like, the trigger switch of the controller can also be controlled by the control rod, and the telescopic actions of different telescopic cylinders are corresponding to the trigger switch and the like, so that the control rod is not particularly limited.

Working principle: when the aircraft rises vertically, the power supply works, drives the movable ring 7 to rotate circumferentially, drives the blade frames 9 of the two rotor wing assemblies 4 to rotate, simultaneously controls the lifting slip ring 22 on the upper side to rise, the lifting slip ring 22 on the lower side to descend, the opening and closing angle of the lifting blades 20 on the upper side is adjusted to a set position, and the opening and closing angle of the lifting blades 20 on the upper side is larger than that on the lower side, so that an air pressure difference is formed when the lifting blades and the blade frames 9 on the lower side rotate, and the aircraft can be driven to rise. When the vertical descending is performed, the vertical ascending operation is reversed.

When hovering, the thrust generated by the pressure difference of the rotor wing assemblies 4 at the upper side and the lower side is ensured to be equal to the weight of the aircraft, and therefore hovering can be realized.

During translation, the translation slip ring 16 is driven to horizontally and reversely move, the opening degree of the translation blade 14 in the moving direction is increased, the opening degree of the translation blade 14 at the other side is reduced, an air pressure difference is formed between the two, and the aircraft can move in a translation mode.

In the aircraft, the principle and structure of the transmission and feedback modes of the adjustment control signals for each action part and the gesture direction are consistent with the prior art, and detailed description is not made. The posture controller can adopt an inverted pendulum controller, or can adopt other modes of detecting the horizontal posture through a level meter and then adopting the controller to control.

Of course, in other embodiments, the driving structure may be designed to adopt a form of driving a gear mechanism by a driving motor and driving the movable ring 7 to rotate by the gear mechanism.

Finally, what should be said is: the above embodiments are only for illustrating the technical solution of the present utility model, and any equivalent replacement of the present utility model and modification or partial replacement without departing from the spirit and scope of the present utility model should be covered in the scope of the claims of the present utility model.

Claims

1. The disk-shaped rotor craft is characterized by comprising a cockpit shell with a spherical structure, wherein a ring shell is sleeved on the outer periphery of the cockpit shell, the ring shell and the cockpit shell are coaxially sleeved so that a ring-shaped flow channel which is vertically communicated is arranged between the ring shell and the cockpit shell in a surrounding manner, two groups of rotor wing assemblies are symmetrically arranged at the upper end and the lower end of the ring-shaped flow channel, and an orientation adjusting mechanism for adjusting the orientation of the craft is arranged in the middle of the ring-shaped flow channel;

2. The disc-shaped rotary wing aircraft according to claim 1, wherein two fixed rings are arranged side by side at intervals along the up-down direction, the movable ring is arranged between the two fixed rings, a coil is wound on the fixed rings, the movable ring is made of iron, the driving structure is a power supply for supplying power to the coil so that the two fixed rings generate magnetic attraction force, and the movable ring is rotationally suspended between the two movable rings by magnetic attraction of the coil.

3. The disc-shaped rotor craft according to claim 2, wherein a plurality of U-shaped snap rings are circumferentially arranged at the rear sides of the upper and lower ends of the cockpit shell, the openings of the U-shaped snap rings extend in the radial direction of the fixing rings, the two fixing rings are respectively fixed on the upper and lower side walls of the U-shaped snap rings, the lifting slip ring is arranged above the U-shaped snap rings, and the translational slip ring is arranged below the U-shaped snap rings.

4. The disc rotor craft of claim 2 wherein the lift adjustment mechanism comprises lift telescoping cylinders connected between the cockpit shell and the lift slip ring, the lift telescoping cylinders being of three or more and being spaced circumferentially about the lift slip ring.

5. The disc rotor aircraft of claim 2, wherein the horizontal adjustment mechanism comprises translational telescopic cylinders connected between the cockpit shell and the horizontal slip ring, the translational telescopic cylinders being distributed at equal intervals around the circumference of the horizontal slip ring.

6. The disc rotor craft according to any one of claims 1-5, wherein the outer end of the chassis is fixedly connected to the ring casing to coaxially fit the ring casing and the cockpit casing, the orientation adjustment mechanism includes a plurality of adjustment blades rotatably mounted on the outer wall of the cockpit casing, the rotation axes of the adjustment blades extend in the radial direction of the circumferential flow path, the adjustment blades are uniformly distributed at intervals in the circumferential direction of the circumferential flow path, and the inner ends in the adjustment blades are connected with attitude adjustment controllers for controlling the opening and closing angles of the adjustment blades.

7. The disc rotor craft of any of claims 1-5 wherein the lift blades in both rotor assemblies are rotated in opposite directions and the blades are tilted in opposite directions.

8. The disc rotor craft according to any of claims 1-5, characterized in that the bottom of the cockpit shell is connected with an elevator extending up and down and communicating with the interior of the cockpit shell, the elevator being connected with support feet on its peripheral side.