CN111688921A - Rolling wing aircraft - Google Patents

Abstract

The invention provides a rolling wing aircraft, which comprises an aircraft body and a plurality of rolling wings arranged on the aircraft body, wherein the rolling wings are connected with the aircraft body through rotating shafts, and each rolling wing is correspondingly provided with a first power mechanism which is arranged in the aircraft body and used for driving the aircraft body to rotate; every it still corresponds and is equipped with angle of attack adjusting part to roll the wing, angle of attack adjusting part includes adjustment disk and pull rod, pull rod one end with the adjustment disk is articulated, the other end with the paddle is articulated, the adjustment disk set up in the outside of pivot, the adjustment disk still corresponds and is equipped with power unit two that is used for adjusting its position. The rolling wing aircraft has the advantages of higher pneumatic efficiency, more flexibility, stability and low noise.

Description

Rolling wing aircraft

Technical Field

The invention belongs to the technical field of aviation, and particularly relates to a rolling wing aircraft.

Background

With the rapid development of the unmanned aerial vehicle technology in recent years, the unmanned aerial vehicle is widely applied to various industries, the aircraft has a branch developing towards middle and small sizes, and the fixed wing aircraft and the rotor aircraft are the most mainstream at present, but the two aircrafts have some obvious defects:

firstly, the flying height of the existing small and medium-sized unmanned aerial vehicle is generally 5 to 50 meters, the flying speed is about 8m/s to 15m/s, the average chord length is mostly distributed between 200mm to 300mm, the corresponding Reynolds number can be calculated to be 109492 to 511433, under the relatively low Reynolds number, the boundary layer of the wing is more easily separated, the action of viscous force is more obvious than that of inertia force, the lift-drag ratio of the wing or propeller is greatly reduced, the aerodynamic efficiency of the aircraft is obviously reduced, the low-efficiency utilization of energy is meant, the energy consumption of the unmanned aerial vehicle is larger, the endurance time is shortened, and for the micro unmanned aerial vehicle, the negative effect is more obvious. Secondly, when the speed of the fixed-wing aircraft is too low, wings stall and lose lift force, so that actions such as hovering, pivot turning, vertical take-off and landing are difficult to complete; the attitude change of the rotor craft in the flight process is completely controlled by the rotating speed of the propeller, and the rapid, sensitive and accurate attitude switching cannot be achieved. Finally, because the screw when the screw is in operation, its paddle exhibition is to perpendicular to oar axle to the rotational speed is very fast, consequently unmanned aerial vehicle often can produce sharp and harsh noise at the flight in-process, and these defects make unmanned aerial vehicle's popularization and application receive very big restriction.

Disclosure of Invention

In view of the above, the present invention provides a rolling wing aircraft to overcome the above-mentioned drawbacks in the prior art.

In order to achieve the purpose, the technical scheme of the invention is realized as follows:

a rolling wing aircraft comprises an aircraft body and a plurality of rolling wings arranged on the aircraft body, wherein the rolling wings are connected with the aircraft body through rotating shafts, and each rolling wing is correspondingly provided with a first power mechanism which is arranged in the aircraft body and used for driving the aircraft body to rotate;

the rolling wing comprises a paddle disc and paddles, the paddle disc is fixedly connected with the rotating shaft through a reserved through hole, and the paddle disc is hinged with the paddles;

every it still corresponds and is equipped with angle of attack adjusting part to roll the wing, angle of attack adjusting part includes adjustment disk and pull rod, pull rod one end with the adjustment disk is articulated, the other end with the paddle is articulated, the adjustment disk set up in the outside of pivot, the adjustment disk still corresponds and is equipped with power unit two that is used for adjusting its position.

Furthermore, every power unit one includes driving motor, driving gear, driving motor is fixed in on the aircraft body, driving motor is connected with an electronic governor, and electronic governor is connected with the signal receiver who is used for receiving the remote controller signal through flight controller, be fixed with drive gear on driving motor's the output shaft, drive gear with the driving gear meshing is connected, the driving gear is fixed in the pivot is close to the one end of aircraft body, the pivot run through in driven gear and eccentric ring through the bearing, with driven gear rotates and is connected.

Furthermore, the number of the rolling wings is three, the included angle between the three rolling wings is 120 degrees, the three rolling wings are circumferentially arranged on a side plate of the aircraft body, each rolling wing corresponds to one power mechanism II and one power mechanism I, the power mechanism I extends out of a through hole reserved in the side plate through the rotating shaft and is connected with the rolling wing, and the power mechanism II is connected with the rolling wing through an eccentric circular ring;

each paddle disk is symmetrically provided with 4 connecting rods, the tail end of each connecting rod is connected with one paddle, a through hole corresponding to the rotating shaft is formed in each paddle disk, and the rotating shaft penetrates through the through hole and is fixedly connected with the paddle disk;

each paddle is correspondingly provided with two paddle disks.

Furthermore, the end of the connecting rod is fixed with a bearing through a reserved through hole, the paddle is provided with a square hole corresponding to the connecting rod, the paddle is fixedly provided with a bolt along the length direction, and the bolt penetrates through the square hole and the bearing inner ring to enable the connecting rod to be connected with the paddle in a rotating mode.

Furthermore, the power mechanism II comprises a steering engine, a control gear, a driven gear and an eccentric ring, the steering engine is mounted on the aircraft body and is electrically connected with a signal receiver, an output shaft of the steering engine is fixedly connected with the control gear, the driven gear is rotationally connected to the rotating shaft, the control gear is meshed with the driven gear, the eccentric ring is fixed on one side, close to the rolling wings, of the driven gear, the axis of the eccentric ring deviates from the axis of the driven gear, and the eccentric ring is fixedly connected with the inner ring of the adjusting disc;

the utility model discloses a hydraulic power mechanism, including pull rod, paddle, adjusting disk, bolt, through-hole, tertiary mounting hole, pull rod, adjusting disk, power unit, actuating lever, pull rod one end is fixed with the bearing, open on the paddle have with the quad slit that the pull rod corresponds, the paddle along length direction open have with the through-hole that bearing inner ring, quad slit correspond, the pull rod through run through the bolt through-hole and bearing inner ring articulate in on the paddle, the adjusting disk is the bearing, open on the adjusting disk outer loop have with the corresponding recess of pull rod, follow on the adjusting disk the recess vertical direction corresponds and is equipped with tertiary mounting hole, the pull rod runs through the bolt tertiary mounting hole of reserving with the pull rod other end with the adjusting disk is articulated, the adjusting disk inner ring with eccentric ring keeps away from the one end.

Furthermore, a plurality of hexagon mounting panels are arranged on the aircraft body from top to bottom, a triangle support is fixed between two adjacent hexagon mounting panels, side plates are vertically fixed on the side faces of the hexagon mounting panels, each side plate is parallel to one side of the triangle support, and each side plate corresponds to one rolling wing, a second power mechanism and a first power mechanism.

Furthermore, driving motor with triangle-shaped support threaded connection, the steering wheel is fixed in on the curb plate, the output shaft of steering wheel passes through the through-hole that the curb plate was reserved stretches out the aircraft body, with from control gear fixed connection, driven gear passes through the bearing and rotates connect in stretching out in the outside pivot of aircraft body, with control gear meshing connects, is located curb plate upper portion all open on the hexagon mounting panel with the bar opening that the action wheel corresponds.

Furthermore, be located curb plate upper portion still open on the hexagon mounting panel with the bar opening that driving motor corresponds, still open on the curb plate and be used for the dismouting driving motor's dismouting hole, the dismouting hole with last installation screw of driving motor corresponds the setting.

Further, aircraft body bottom still is fixed with the base, the base includes three sill bars and three spinal branch vaulting poles, three the sill bar end to end connection forms the tripod, every bracing piece one end with the intersect fixed connection of sill bar, the other end with be located the bottom hexagon mounting panel fixed connection.

Furthermore, the electronic speed regulator, the flight controller and the signal receiver are all arranged on the hexagonal mounting plate at the bottom of the aircraft body.

Compared with the prior art, the invention has the following advantages:

(1) the rolling wings are arranged on the side plates of the aircraft body in a centrosymmetric manner, the rotating angular speeds and the directions are the same, and compared with the similar four-axis aircraft, the three rolling wings reduce the dead weight of the aircraft and simplify a control circuit while realizing mutual offset of additional torques, so that the aircraft obtains unsteady dynamic high lift force by utilizing an unsteady effect generated when blades perform cycloidal motion, and the aerodynamic efficiency is higher under the condition of low Reynolds number.

(2) The second power mechanism controls the blades to do cycloidal motion through gear transmission, so that the pull rod is driven to change the instantaneous attack angle of each blade, the 360-degree omnidirectional vector change of the thrust on the plane of the paddle disc is realized in a very short time, and the overall flexibility is improved;

by adopting gear transmission, the device has the advantages of higher reliability, good stability, simple structure and sensitive response.

(3) The rotating speed of the rolling wing is low, the paddle is parallel to the unfolding direction of the rotating shaft, and the noise is low.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:

fig. 1 is a schematic view of a rolling-wing aircraft according to an embodiment of the invention;

FIG. 2 is a schematic view of a roll wing according to an embodiment of the present invention;

FIG. 3 is a partially enlarged view of a roll wing according to an embodiment of the present invention;

fig. 4 is a schematic view of a second power mechanism and a first power mechanism according to the embodiment of the invention;

fig. 5 is a schematic view of a second power mechanism and a first power mechanism according to the embodiment of the invention;

FIG. 6 is a schematic view of an adjusting plate and a pull rod according to the embodiment of the invention;

FIG. 7 is a partially enlarged schematic view of an adjusting plate according to an embodiment of the present invention;

fig. 8 is a schematic view of an aircraft body according to an embodiment of the invention.

Description of reference numerals:

1-rolling wings; 11-a paddle disk; 111-a via; 112-a connecting rod; 113-a bearing; 12-a blade; 121-primary mounting holes; 122-secondary mounting holes; 123-square hole; 15-a bolt; 16-a groove; 2-an aircraft body; 21-a base; 22-hexagonal mounting plate; 221-strip-shaped through openings; 23-side plate; 231-a disassembly hole; 24-triangular brackets; 3, a second power mechanism; 31-a steering engine; 311-control gear; 32-a driven gear; 321-eccentric circular ring; 33-a pull rod; 34-a regulating disk; 341-three-level mounting holes; 4, a first power mechanism; 41-driving motor; 411-a drive gear; 42-a drive gear; 43-rotating shaft.

Detailed Description

It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.

The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.

As shown in fig. 1, 2 and 5, a rolling-wing 1 aircraft comprises an aircraft body 2 and a plurality of rolling wings 1 mounted on the aircraft body 2, wherein the rolling wings 1 are connected with the aircraft body 2 through a rotating shaft 43, and each rolling wing 1 is correspondingly provided with a power mechanism one 4 mounted inside the aircraft body 2 and used for driving the aircraft body to rotate;

the rolling wing 1 comprises a paddle disk 11 and a paddle 12, wherein the paddle disk 11 is fixedly connected with the rotating shaft 43 through a reserved through hole 111, and the paddle disk 11 is hinged with the paddle 12;

every it still corresponds and is equipped with angle of attack adjusting part to roll wing 1, angle of attack adjusting part includes adjusting disk 34 and pull rod 33, pull rod 33 one end with adjusting disk 34 is articulated, the other end with paddle 12 is articulated, adjusting disk 34 set up in the outside of pivot 43, adjusting disk 34 still corresponds and is equipped with power unit two 3 that is used for adjusting its position.

As shown in fig. 1, 4 and 5, each of the first power mechanisms 4 includes a driving motor 41 and a driving gear 42, the driving motor 41 is fixed on the aircraft body 2, the driving motor 41 is connected with an electronic governor, the electronic governor is connected with a signal receiver for receiving a signal of a remote controller through a flight controller, a driving gear 411 is fixed on an output shaft of the driving motor 41, the driving gear 411 is engaged with the driving gear 42, the driving gear 42 is fixed at one end of the rotating shaft 43 close to the aircraft body 2, and the rotating shaft 43 penetrates through the driven gear 32 and the eccentric ring 321 through a bearing 113 and is rotatably connected with the driven gear 32. When the aircraft maintains the original attitude, the driving motor 41 drives the driving gear 42 to rotate through the driving gear 411, the driving gear 42 drives the rotating shaft 43 to rotate so as to drive the rolling wing 1 to rotate, and the driving gear 42 and the driven gear 32 both maintain relative rest.

As shown in fig. 1, 2 and 5, there are three rolling wings 1, the included angle between three rolling wings 1 is 120 degrees, the three rolling wings are circumferentially installed on a side plate 23 of the aircraft body 2, each rolling wing 1 corresponds to one power mechanism two 3 and one power mechanism 4, the power mechanism one 4 extends out of a through hole 111 reserved in the side plate 23 through the rotating shaft 43 and is connected with the rolling wing 1, the power mechanism two 3 is connected with the rolling wing 1 through an eccentric ring 321, the three rolling wings 1 are distributed in an equilateral triangle, the included angle between two adjacent rotating shafts 43 is 120 degrees, the angular velocity direction is the same when each rolling wing 1 rotates, that is, from a top view, the upper half of the revolution direction of each rolling wing 1 is from the driving gear 42 corresponding to the rolling wing 32, so that stable lift force can be generated, the additional torques on the vertical plane generated by the rolling wings 1 at three positions according to "right hand rule" can be cancelled each other, due to the central symmetry special stable layout, the aircraft can take off stably even if the aircraft is separated from the flight controller;

each paddle disk 11 is symmetrically provided with 4 connecting rods 112, the tail end of each connecting rod 112 is connected with one paddle blade 12, the paddle disk 11 is provided with a through hole 111 corresponding to the rotating shaft 43, and the rotating shaft 43 penetrates through the through hole 111 and is fixedly connected with the paddle disk 11;

two paddles 11 are provided for each paddle 12.

As shown in fig. 2 and 3, a bearing 113 is fixed at the end of the connecting rod 112 through a reserved through hole 111, a square hole 123 corresponding to the connecting rod 112 is formed in the blade 12, a bolt 15 is fixedly installed on the blade 12 along the length direction, and the bolt 15 penetrates through the square hole 123 and the inner ring of the bearing 113, so that the connecting rod 112 is rotatably connected with the blade 12.

As shown in fig. 4 to 7, the second power mechanism 3 includes a steering engine 31, a control gear 311, a driven gear 32, and an eccentric ring 321, the steering engine 31 is installed on the aircraft body 2 and electrically connected to a signal receiver, an output shaft of the steering engine 31 is fixedly connected to the control gear 311, the driven gear 32 is rotatably connected to the rotating shaft 43, the control gear 311 is engaged with the driven gear 32, the eccentric ring 321 is fixed to one side of the driven gear 32 close to the roller wing 1, an axis of the eccentric ring 321 deviates from an axis of the driven gear 32, and the eccentric ring 321 is fixedly connected to an inner ring of the adjusting disc 34;

a bearing 113 is fixed at one end of the pull rod 33, a square hole 123 corresponding to the pull rod 33 is formed in the paddle 12, a through hole 111 corresponding to an inner ring and the square hole 123 of the bearing 113 is formed in the paddle 12 along the length direction, the pull rod 33 is hinged to the paddle 12 by penetrating a bolt 15 through the through hole 111 and the inner ring of the bearing 113, the adjusting plate 34 is the bearing 113, a groove 16 corresponding to the pull rod 33 is formed in an outer ring of the adjusting plate 34, a third-stage mounting hole 341 is correspondingly formed in the adjusting plate 34 along the vertical direction of the groove 16, the pull rod 33 penetrates through the third-stage mounting hole 341 and the through hole 111 reserved at the other end of the pull rod 33 through the bolt 15 and is hinged to the adjusting plate 34, and the inner ring of the adjusting plate 34 is fixedly connected with one end, far away from the power mechanism one 4, of the eccentric circular ring 321. When the posture of the aircraft needs to be changed, an operator controls the steering engine 31 to rotate by using a remote controller, the steering engine 31 drives the driven gear 32 to rotate through the control gear 311, so that the eccentric ring 321 drives the adjusting disc 34 to rotate around the center of the rotating shaft 43, and the position of the whole eccentric ring mechanism is changed. The pull rod 33 reflects the position change on each blade 12 of the cycloidal-propeller mechanism, and the motion track of each blade 12 in a circle is changed through the change of the pushing (pulling) force, so that the omnidirectional vector change of the thrust of the rolling wing 1 is realized. Because the adjusting disk 34 is fixedly connected with the aoo driven gear 32 through the eccentric ring 321, the vibration of the rolling wings 1 cannot be caused when the control gear 311 drives the driven gear 32 to rotate, and the aircraft is more stable when the motion is changed.

As shown in fig. 1 and 8, a plurality of hexagonal mounting plates 22 are arranged above and below the aircraft body 2, a triangular support 24 is fixed between two adjacent hexagonal mounting plates 22, side plates 23 are vertically fixed to the side surfaces of the hexagonal mounting plates 22, each side plate 23 is arranged in parallel to one side of the triangular support 24, and each side plate 23 corresponds to one rolling wing 1, a second power mechanism 3 and a first power mechanism 4.

As shown in fig. 1 and 8, the driving motor 41 is in threaded connection with the triangular bracket 24, the steering gear 31 is fixed on the side plate 23, an output shaft of the steering gear 31 extends out of the aircraft body 2 through a through hole 111 reserved in the side plate 23, and is fixedly connected with the slave control gear 311, the slave gear 32 is rotatably connected with the rotating shaft 43 extending out of the aircraft body 2 through a bearing 113, and is meshed with the control gear 311, and the hexagonal mounting plate 22 on the upper portion of the side plate 23 is provided with strip-shaped through holes 221 corresponding to the driving wheel, so that the hexagonal mounting plate 22 is prevented from shielding the driving gear 42.

As shown in fig. 1 and 8, the hexagonal mounting plate 22 positioned above the side plate 23 is further provided with a strip-shaped through hole 221 corresponding to the driving motor 41, the side plate 23 is further provided with a mounting and dismounting hole 231 for mounting and dismounting the driving motor 41, and the mounting and dismounting hole is provided corresponding to a mounting screw hole on the driving motor 41. When the driving motor 41 needs to be disassembled, the whole aircraft body 2 does not need to be disassembled, and the screwdriver only needs to be stretched into the disassembling space to unscrew the screw used for fixing the driving motor 41, so that the motor can be taken out from the strip-shaped through hole 221.

As shown in fig. 1 and 8, a base 21 is further fixed at the bottom of the aircraft body 2, the base 21 includes three bottom rods and three support rods, the three bottom rods are connected end to form a tripod, one end of each support rod is fixedly connected with an intersection point of the bottom rods, and the other end of each support rod is fixedly connected with the hexagonal mounting plate 22 located at the bottom. Base 21 makes the aircraft landing more steady, reduces unmanned aerial vehicle simultaneously and collides with the unnecessary loss of production with other objects.

As shown in fig. 1 and 8, the electronic governor, the flight controller, and the signal receiver are mounted on the hexagonal mounting plate 22 at the bottom of the aircraft body 2. Because all heavy-weight equipment such as a polonium lithium power supply, an electronic speed regulator, a flight controller, a receiver and the like are placed at the lower layer of the rack platform and are concentrated at the central position, the overall gravity center of the aircraft is positioned below the power generating surface of the aircraft, so that the aircraft has better stability, and the additional torque of the aircraft in the attitude change can be reduced to a certain extent.

In the operation process of the invention, the change of the attitude is mainly realized by the change of the rotating speed of each rolling wing 1 and the change of the resultant force direction thereof, so the control mode of the invention is different from that of the traditional aircraft. Selecting the opposite surface of the paddle disk 11 of the rear rolling wing 1 as the flying direction, connecting the steering engine 31 to a signal receiver through a Y line in one-to-three same direction, carrying out neutral fine adjustment before the flying to enable the lifting force direction of each rolling wing 1 to be vertically upward, controlling the operation of the driving motor 41 through a remote controller accelerator to drive the rolling wings 1 to rotate so as to take off, and controlling the flying height of the rolling wings by the size of the accelerator; the position of the power mechanism II 3 is changed relatively by rotating the steering engine 31, so that the attack angle of the paddle 12 is changed, and each rolling wing 1 mechanism generates the same clockwise or same anticlockwise yawing moment by taking the corresponding rotating shaft 43 as a force arm, so that the integral yawing of the aircraft is realized; through the differential change of the adjacent rolling wings 1, the lifting forces on the two sides are unequal, so that the rolling of the whole aircraft is realized; the lifting force of the rear rolling wing 1 is changed by adjusting the rotating speed of the rear rolling wing 1, so that the pitching of the aircraft is realized. In addition, each rolling wing 1 can generate omnidirectional vector thrust, so that the attack angle of each blade 12 is adjusted through the power mechanism two 3, and the forward and backward movement of the aircraft can be realized under the condition that the attitude of the aircraft is not changed.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.

Claims (10)

1. A rolling-wing aircraft, characterized in that: the aircraft comprises an aircraft body (2) and a plurality of rolling wings (1) arranged on the aircraft body (2), wherein the rolling wings (1) are connected with the aircraft body (2) through rotating shafts (43), and each rolling wing (1) is correspondingly provided with a power mechanism I (4) which is arranged in the aircraft body (2) and used for driving the aircraft body to rotate;

the rolling wing (1) comprises a paddle disk (11) and paddles (12), the paddle disk (11) is fixedly connected with the rotating shaft (43) through a reserved through hole (111), and the paddle disk (11) is hinged with the paddles (12);

every it still corresponds and is equipped with angle of attack adjustment assembly to roll wing (1), angle of attack adjustment assembly includes adjusting disk (34) and pull rod (33), pull rod (33) one end with adjusting disk (34) are articulated, the other end with paddle (12) are articulated, adjusting disk (34) set up in the outside of pivot (43), adjusting disk (34) still correspond and are equipped with power unit two (3) that are used for adjusting its position.

2. A rolling-wing aircraft according to claim 1, wherein: every power unit (4) include driving motor (41), driving gear (42), driving motor (41) are fixed in on aircraft body (2), driving motor (41) are connected with an electronic governor, and electronic governor is connected with the signal receiver who is used for receiving the remote controller signal through flight controller, be fixed with drive gear (411) on the output shaft of driving motor (41), drive gear (411) with driving gear (42) meshing is connected, driving gear (42) are fixed in pivot (43) are close to the one end of aircraft body (2), pivot (43) run through bearing (113) in driven gear (32) and eccentric ring (321), with driven gear (32) rotate and are connected.

3. A rolling-wing aircraft according to claim 1, wherein: the aircraft is characterized in that the number of the rolling wings (1) is three, the included angle between the three rolling wings (1) is 120 degrees, the three rolling wings are circumferentially arranged on a side plate (23) of the aircraft body (2), each rolling wing (1) corresponds to one power mechanism II (3) and one power mechanism I (4), the power mechanism I (4) extends out of a through hole (111) reserved in the side plate (23) through the rotating shaft (43) and is connected with the rolling wings (1), and the power mechanism II (3) is connected with the rolling wings (1) through an eccentric circular ring (321);

4 connecting rods (112) are symmetrically arranged on each paddle disk (11), the tail end of each connecting rod (112) is connected with one paddle blade (12), a through hole (111) corresponding to the rotating shaft (43) is formed in each paddle disk (11), and the rotating shaft (43) penetrates through the through hole (111) and is fixedly connected with the paddle disk (11);

each paddle (12) is correspondingly provided with two paddle disks (11).

4. A rolling-wing aircraft according to claim 3, wherein: the terminal of connecting rod (112) is fixed with bearing (113) through-hole (111) of reserving, paddle (12) go up open have with quad slit (123) that connecting rod (112) correspond, paddle (12) have bolt (15) along length direction fixed mounting, bolt (15) run through in quad slit (123) and bearing (113) inner circle make connecting rod (112) with paddle (12) rotate and are connected.

5. A rolling-wing aircraft according to claim 1, wherein: the second power mechanism (3) comprises a steering engine (31), a control gear (311), a driven gear (32) and an eccentric ring (321), the steering engine (31) is installed on the aircraft body (2) and is electrically connected with a signal receiver, an output shaft of the steering engine (31) is fixedly connected with the control gear (311), the driven gear (32) is rotatably connected to the rotating shaft (43), the control gear (311) is meshed with the driven gear (32), the eccentric ring (321) is fixed to one side, close to the rolling wing (1), of the driven gear (32), the axis of the eccentric ring (321) deviates from the axis of the driven gear (32), and the eccentric ring (321) is fixedly connected with the inner ring of the adjusting disc (34);

a bearing (113) is fixed at one end of the pull rod (33), a square hole (123) corresponding to the pull rod (33) is formed in the paddle (12), a through hole (111) corresponding to the inner ring and the square hole (123) of the bearing (113) is formed in the paddle (12) along the length direction, a bolt (15) penetrates through the through hole (111) and the inner ring of the bearing (113) to be hinged to the paddle (12), the adjusting disc (34) is a bearing (113), a groove (16) corresponding to the pull rod (33) is formed in the adjusting disc (34), a third-stage mounting hole (341) is correspondingly formed in the adjusting disc (34) along the vertical direction of the groove (16), and the pull rod (33) penetrates through the third-stage mounting hole (341) and the through hole (111) reserved at the other end of the pull rod (33) through the bolt (15) to be hinged to the adjusting disc (34), the inner ring of the adjusting disc (34) is fixedly connected with one end, far away from the power mechanism I (4), of the eccentric circular ring (321).

6. A rolling-wing aircraft according to claim 1, wherein: aircraft body (2) are equipped with a plurality of hexagon mounting panels (22) from top to bottom, are fixed with triangle-shaped support (24) between two adjacent hexagon mounting panels (22), the side vertical fixation of hexagon mounting panel (22) has curb plate (23), every curb plate (23) all with one side parallel arrangement of triangle-shaped support (24), every curb plate (23) all correspond one and roll wing (1), power unit two (3), power unit (4).

7. A rolling-wing aircraft according to claim 6, wherein: driving motor (41) with triangle-shaped support (24) threaded connection, steering wheel (31) are fixed in on curb plate (23), the output shaft of steering wheel (31) passes through-hole (111) that curb plate (23) were reserved stretch out aircraft body (2), with from control gear (311) fixed connection, driven gear (32) rotate through bearing (113) connect in stretch out on aircraft body (2) outside pivot (43), with control gear (311) meshing is connected, is located curb plate (23) upper portion all open on hexagonal mounting panel (22) with bar opening (221) that the action wheel corresponds.

8. A rolling-wing aircraft according to claim 6, wherein: be located curb plate (23) upper portion still open on hexagonal mounting panel (22) with bar through-hole (221) that driving motor (41) correspond, still open on curb plate (23) and be used for the dismouting hole (231) of driving motor (41), the dismouting empty with installation screw on driving motor (41) corresponds the setting.

9. A rolling-wing aircraft according to claim 6, wherein: aircraft body (2) bottom still is fixed with base (21), base (21) include three sill bars and three spinal branch vaulting poles, three the sill bar end to end connection forms the tripod, every with bracing piece one end with the intersect fixed connection of sill bar, the other end with be located the bottom hexagon mounting panel (22) fixed connection.

10. A rolling-wing aircraft according to claim 6, wherein: the electronic speed regulator, the flight controller and the signal receiver are all arranged on the hexagonal mounting plate (22) at the bottom of the aircraft body (2).

Images