CN114919742A

CN114919742A - Multi-rotor aircraft

Info

Publication number: CN114919742A
Application number: CN202210746080.XA
Authority: CN
Inventors: 陈华; 李全贵; 吴林波; 陈子毓
Original assignee: Individual
Current assignee: Individual
Priority date: 2022-06-28
Filing date: 2022-06-28
Publication date: 2022-08-19

Abstract

The invention discloses a multi-rotor aircraft, which belongs to the technical field of rotor aircraft and comprises a cabin and a gliding wing, wherein the gliding wing comprises a fixed wing plate and a turnover wing plate, the fixed wing plate is arranged at the top of the cabin, and a space for air circulation is formed between the fixed wing plate and the top of the cabin; the orientation of connection in order to change self chord wing is rotated at fixed pterygoid lamina's both ends to upset pterygoid lamina, and the symmetry is being equipped with the rotor on the last airfoil of upset pterygoid lamina and the lower airfoil, and the axis of rotor is parallel with the chord wing of upset pterygoid lamina, and the rotor mirror image on two upset pterygoid laminas sets up. Except can switch between horizontal flight and lift, two kinds of states of hovering, have that flying speed is fast concurrently, the journey is longer and the energy consumption is low, but advantages such as VTOL and hover are out, after converting to the state of hovering, through the rotatory differential of rotor in pairs that the control mirror image set up, can also fly to unmanned aerial vehicle all around the same, use more extensively, it is more nimble convenient.

Description

Multi-rotor aircraft

Technical Field

The invention relates to the technical field of rotor crafts, in particular to a multi-rotor craft.

Background

Rotorcraft fall mainly into two main categories: the system comprises a propeller helicopter with or without a fixed wing plate, an unmanned aerial vehicle and the like, and a propeller airplane with a fixed wing plate; the former has small floor area, convenient and flexible use, can vertically take off, land and hover, but has slow flying speed and shorter voyage. The fixed wing plate can bring a large part of lift force to the aircraft through the fixed wing plate, so that the energy consumption for lifting the loading capacity of the elevator is reduced, the flight speed and the flight range can be improved, but the fixed wing plate occupies a large area, needs a large take-off distance, cannot vertically take off, land and hover, needs to be designed and planned in advance, cannot be temporarily changed, and is poor in convenience and flexibility and practicability.

Therefore, the market gradually provides a multi-rotor aircraft with the advantages of the two aircrafts, such as '201310242971.2', the invention patent named as 'multi-rotor wing multi-propeller helicopter' discloses a multi-wing helicopter which can be switched between two modes of flight and lifting, and comprises a cabin, a tail wing positioned at the tail part of the cabin and at least three pairs of wings positioned at two sides of the cabin, wherein the front edges of two pairs of wings are provided with rotors and respectively positioned at the upper half part and the lower half part of the cabin, the other pair of wings is arranged on the cabin below the tail wing, the wings are rotatably connected with the cabin, the direction of the rotation axis of the rotors is changed by rotating the wings, when the rotation axis of the rotors faces forwards, the flight state of the aircraft with a fixed wing plate is realized, the flight speed is high, the flight energy consumption is low, and when the rotation axis of the rotors faces upwards, the lifting function of the helicopter is realized, the functions of vertical lifting and hovering are realized, and the lifting is more flexible. However, the multi-wing helicopter in the above patent still has many problems: firstly, the balance is poor, especially when the two forms are switched; and secondly, after the lifting state is converted, the lifting is only carried out, and the lifting can not move forwards, backwards or leftwards and rightwards in the lifting state.

Disclosure of Invention

The present invention is to solve the above-mentioned technical problems, and an object of the present invention is to provide a multi-rotor aircraft that can switch between two states of horizontal flight, elevation and hovering, and can fly forward, backward, leftward and rightward as an unmanned aerial vehicle after being converted into the hovering state.

In order to achieve the purpose, the invention provides the following scheme: the invention discloses a multi-rotor aircraft, which comprises a cabin and a gliding wing, wherein the gliding wing comprises a fixed wing plate and a turnover wing plate, the fixed wing plate is installed at the top of the cabin, and a space for air circulation is formed between the fixed wing plate and the top of the cabin; the upset pterygoid lamina rotates to be connected the orientation of the both ends of fixed pterygoid lamina in order to change self chord, the symmetry is being equipped with the rotor on the last airfoil of upset pterygoid lamina and the lower airfoil, the axis of rotor with the chord of upset pterygoid lamina is parallel, two on the upset pterygoid lamina the rotor mirror image sets up.

Preferably, the top of the rear edge of the fixed wing plate is provided with a tail wing for keeping the balance of the cabin, and the top of the front edge of the fixed wing plate is provided with a cab.

Preferably, a rotating shaft and a rotating mechanism for driving the rotating shaft to rotate are arranged in the fixed wing plate, and the rotating shaft is fixedly connected with the turnover wing plate.

Preferably, the rotating mechanism comprises a driving pulley, a driven pulley and a driving device for driving the driving pulley to rotate, the driving device is fixed in the fixed wing plate, the driven pulley is fixed on the rotating shaft, and the driving pulley and the driven pulley are connected through a driving belt.

Preferably, the turnover wing plate comprises a first folding section and a second folding section, the first folding section is rotatably connected with the fixed wing plate, the second folding section is hinged with the first folding section, the hinge axis of the first folding section is parallel to the chord of the first folding section and the chord of the second folding section, and the rotor wing is arranged on the first folding section.

Preferably, the lower wing surface of the first folding section and the lower wing surface of the second folding section are hinged through hinges, the upper wing surface of the turnover wing plate is provided with a telescopic cylinder mounting groove, and a movable end and a telescopic cylinder hinged to the folding sections are mounted in the telescopic cylinder mounting groove.

Preferably, the upset pterygoid lamina includes first exhibition receipts section and second exhibition receipts section, first exhibition receipts section with fixed pterygoid lamina rotates to be connected, the leading edge of second exhibition receipts section with the leading edge of first exhibition receipts section is articulated, the second exhibition receipts section with the hinge axis of first exhibition receipts section is perpendicular with both chords, the rotor sets up on the first exhibition receipts section.

Preferably, a sliding groove and a pushing and lifting cylinder mounting groove are formed in the end of the first unfolding and folding section, a guide sleeve is hinged in the sliding groove, a guide rod hinged to the end of the second unfolding and folding section is connected in the guide sleeve in a sliding mode, and a hinge point of the guide rod is located between the front edge and the rear edge of the second unfolding and folding section; the pushing cylinder mounting groove is located between the sliding groove and the front edge of the second unfolding and folding section, and a movable end and a pushing cylinder hinged to the second unfolding and folding section are mounted in the cylinder mounting groove.

Preferably, a rotor protective cylinder is arranged outside the rotor, and the rotor protective cylinder is fixed on the turnover wing plate.

Preferably, the fixed wing plate is provided with a landing gear with adjustable height, the fixed wing plate is provided with a hanging bracket capable of being grabbed and released, and the engine room is detachably connected with the fixed wing plate through the hanging bracket.

Compared with the prior art, the invention has the following technical effects:

1. the multi-rotor aircraft has the gliding wings, has all the advantages of all aircraft with the wings during horizontal flight, can provide a large part of lift force for the aircraft, reduces the energy consumption for hoisting the loading capacity of a hoist, improves the flight speed, increases the flight range, and eliminates the defects of low speed and shorter flight range of a helicopter; through the overturning of the overturning wing plate and the rotor wing on the overturning wing plate, the helicopter has the advantages of small occupied area, convenience and flexibility in use, capability of vertically taking off and landing, hovering and the like, and the defect of large takeoff distance is eliminated; the mated rotor that the mirror image set up on the wing board of overturning simultaneously, mutually support, adjust the differential and can also make the aircraft under the state of hovering have the ability that unmanned aerial vehicle was preceding, back, left and right flown, and rotor mutually supports and can also adjust the balance of aircraft at the flight in-process, makes the aircraft balance effectual, uses more extensively, and is nimble more convenient.

2. The turnover wing plate can be folded, the size of the aircraft in the width direction can be reduced, the floor area can be reduced, the width of a permitted road during landing can be reduced, and the turnover wing plate is more flexible and convenient to use.

3. The turnover wing plate can be unfolded and folded, so that the width of the aircraft can be reduced, the occupied area is reduced, the width of the cabin can be reduced, the change of the gravity center of the whole turnover wing plate in the front-back direction of the cabin is small, the influence on the balance of the whole aircraft is small, and the control is good.

4. The cabin and the fixed wing plate can be quickly disassembled through the hanging bracket, so that the cabin can be quickly replaced.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.

FIG. 1 is a schematic view of a flight state of an unmanned multi-rotor aircraft with four rotors;

FIG. 2 is a schematic view of the flight regime of a manned, multi-rotor aircraft with eight rotors;

FIG. 3 is a schematic structural view of the rotating mechanism;

FIG. 4 is a schematic view of a multi-rotor aircraft in a hovering, lifting state after folding of the inverted wing panels;

FIG. 5 is a schematic view of the mechanism for effecting folding of the inverted wing;

FIG. 6 is a schematic view of a multi-rotor aircraft in a hovering, lifting state after the inverted wing plate is raised;

FIG. 7 is a schematic view of a mechanism for lifting the flap plate;

FIG. 8 is a schematic view of the pylon with the nacelle quick assembly and disassembly jaws closed;

fig. 9 is a schematic view of the hanger and nacelle quick-release jaws open.

Description of reference numerals: 1. a nacelle; 2. a fixed wing plate; 3. turning the wing plate; 4. a rotor; 5. a tail fin; 6. a landing gear; 7. a hanger; 8. a rotating shaft; 9. a driving pulley; 10. a driven pulley; 11. a drive device; 12. a drive belt; 101. a passenger cabin or cargo compartment; 102. a cockpit; 103. clamping a cabin pile; 104. a claw; 105. a connecting rod; 106. a guide sleeve; 107. a spring; 108. opening and closing the driving cylinder; 109. a piston rod; 110. a boom; 301. a first folded section; 302. a second folding section; 303. a hinge; 304. a telescopic cylinder mounting groove; 305. a telescopic cylinder; 306. folding the ear plate; 311. a first unfolding and folding section; 312. a second unfolding and folding section; 313. a chute; 314. a pushing cylinder mounting groove; 315. a guide sleeve; 316. a guide bar; 317. a lifting cylinder; 318. pushing and lifting the lug plate; 401. a rotor wing shroud; 402. a fixed mount; 601. a telescopic cylinder rod; 602. and a lifting driving cylinder.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The embodiment discloses a multi-rotor aircraft, as shown in fig. 1 to 9, comprising a cabin 1 and a gliding wing, wherein the gliding wing comprises a fixed wing plate 2 and two overturning wing plates 3; wherein the fixed wing panel 2 is mounted on the top of the nacelle 1 and has a distance from the top of the nacelle 1, the distance being such that the circulating air provides a lifting thrust to the fixed wing panel 2 and thus to the aircraft during flight of the nacelle 1. Two upset pterygoid lamina 3 rotate respectively and connect at the both ends of fixed pterygoid lamina 2, can change the orientation of its self chord through rotating upset pterygoid lamina 3, set up at least a pair of rotor 4 on every upset pterygoid lamina 3, and the axis of rotor 4 is parallel with the chord of upset pterygoid lamina 3. The two rotors 4 of each pair of rotors 4 are symmetrically arranged on the upper wing surface and the lower wing surface of the turn-over wing plate 3, while the rotors 4 of the two turn-over wing plates 3 are arranged in mirror image, as shown in fig. 1 and 2, for two pairs of rotors 4 and four pairs of rotors 4, respectively. When there are two pairs of rotors 4, referring to fig. 1, the upper right and lower left are left rotors, and the upper left and lower right are right rotors, so that the torques generated by the rotation of the four rotors 4 cancel each other out. By rotating the overturning wing plate 3, the axis orientation of the rotor 4 is changed, and the two states of flying, lifting and hovering can be switched.

Switching from a horizontal flight state to a lifting and hovering state:

when the aircraft is in a horizontal flight state, the center planes of the overturning wing plates 3 and the fixed wing plates 2 coincide, the rotation axes of the rotor wings 4 arranged on the overturning wing plates 3 are consistent with the front and back directions of the aircraft, the rotor wings 4 rotate to provide forward power, the overturning wing plates 3 and the fixed wing plates 2 jointly form gliding wings at the moment, and air flow gives upward lift force to the overturning wing plates 3 and the fixed wing plates 2 through the gliding wings in the flight process, so that the flight consumption is reduced, and the flight speed can be obviously improved under the action of the gliding wings. When switching over, then reduce the rotational speed of rotor 4 in advance, after will the certain speed, rotate upset pterygoid lamina 3 and make the rotation axis of rotor 4 up, provide the ability that continues to slide by fixed pterygoid lamina 2 in 3 upset processes of upset pterygoid lamina, in order to avoid cabin 1 to lose lift, after upset pterygoid lamina 3 overturns the completion completely, when the rotation axis of rotor 4 was up completely promptly, then all provide ascending lift by rotor 4, thereby realize hovering, can realize going up and down through the rotational speed that changes rotor 4. Certainly, by adjusting the rotating speeds of different rotors 4, the aircraft in a hovering state can also realize the flight state of a four-wing unmanned aerial vehicle, namely when the rotating speed of the rotor 4 positioned in front of the turnover wing plate 3 is higher than that of the rotor 4 positioned behind, the whole cabin 1 can be flown backwards, otherwise, the whole cabin can be flown forwards; when the rotating speed of the rotor 4 on the right side overturning wing plate 3 of the cabin 1 is higher than that of the rotor 4 on the left side overturning wing plate 3, the whole cabin 1 flies to the left, otherwise, the whole cabin can fly to the right. Meanwhile, no matter in a horizontal flight state or a hovering state, the four rotors 4 can adjust the rotating speed according to the state of the cabin 1, so that the cabin 1 is kept balanced, and the balance capability of the aircraft is greatly improved.

Switching from a lifting state to a hovering state:

when the elevating status, the axis orientation of rotor 4 this moment, through starting rotor 4, can make the aircraft promote, after cabin 1 promotes the take the altitude, change the speed difference of front and back rotor 4, make cabin 1 fly forward, when cabin 1 has certain speed (fixed pterygoid lamina 2 has sufficient lift can guarantee that cabin 1 slides promptly), it makes rotor 4 axis forward to rotate upset pterygoid lamina 3 this moment, the lift that can make cabin 1 glide is temporarily provided by fixed pterygoid lamina 2 this moment, simultaneously also can adjust the differential of rotor 4 and assist cabin 1 and continue to fly forward, overturn completely until upset pterygoid lamina 3, rotor 4 axis is forward completely, then provide forward power by rotor 4, accomplish flight status switching.

In the present embodiment, as shown in fig. 1 to 9, two tail wings 5 are provided at the top of the rear edge of the fixed wing plate 2, and the tail wings 5 can keep the balance of the nacelle 1 during flight, thereby improving the flight stability of the aircraft. Further, the top of the front edge of the nacelle 1 may be provided with a cockpit 102 for a person to pilot. The cockpit 102 may not be provided, and the operation system may operate to realize unmanned driving.

Further, in the present embodiment, as shown in fig. 1 to 9, a cabin or a cargo compartment 101 for carrying people or cargo is provided on the nacelle 1.

Further, in this embodiment, as shown in fig. 1 to 9, a rotating shaft 8 and a rotating mechanism are disposed in the fixed wing plate 2, two ends of the rotating shaft 8 are respectively fixedly connected to the two rotating turning wing plates 3, and the rotating shaft 8 can drive the two rotating turning wing plates 3 to synchronously rotate under the driving of the rotating mechanism, specifically referring to fig. 3. Preferably, the rotating shaft 8 is rotatably connected with the fixed wing 2 through a bearing.

Further, in the present embodiment, as shown in fig. 1 to 9, the turning mechanism includes a driving pulley 9, a driven pulley 10, and a driving device 11. The driving device 11 is fixed in the fixed wing plate 2, and the output shaft of the driving device 11 is fixedly connected with the driving pulley 9, preferably, the driving device 11 can select an electric motor, a hydraulic motor and a pneumatic motor. The driven pulley 10 is fixed on the rotating shaft 8, and the driving pulley 9 and the driven pulley 10 are connected through a driving belt 12. When wanting rotatory upset pterygoid lamina 3, only need drive driving pulley 9 through drive arrangement 11 and rotate, can drive driven pulley 10 through drive belt 12 and rotate to it is rotatory to drive pivot 8, finally makes two upset pterygoid laminas 3 rotate. Of course, the rotating mechanism may also adopt other setting manners, which is only an optimal manner, and actually, as long as the rotating shaft 8 can be driven to rotate, other mechanisms may be adopted, such as a driving gear disposed on the driving device 11, a driven gear disposed on the rotating shaft 8, the driving gear and the driven gear being engaged, and a worm disposed on an output shaft of the driving device 11, and the worm drives the worm to rotate.

In this embodiment, as shown in fig. 1 to 9, the inverted wing panel 3 includes a first folded section 301 and a second folded section 302, the first folded section 301 is rotatably connected to the fixed wing panel 2, and the rotor 4 is disposed on the first folded section 301. The second folded section 302 is hinged to the first folded section 301 with the hinge axis parallel to the chord of the two, so that the second folded section 302 can be folded towards the first folded section 301. After second folding section 302 can be folded towards first folding section 301 direction, can reduce aircraft width direction size, reduce area, the width of the road of allowwing when reducing to descend, use more nimble, convenient. During specific lifting, the turnover wing plate 3 is firstly in a vertical state from a horizontal state device, the rotor 4 turns upwards from the forward direction, then the second folding section 302 rotates 90 degrees towards the first folding section 301, and the second folding section 302 is folded forwards or backwards, so that the width of the aircraft is reduced. It should be noted that the length of the second folded section 302 is no greater than the length of the nacelle 1, so that after folding forward or backward, the entire aircraft is kept in balance.

Further, in this embodiment, as shown in fig. 1 to 9, a lower wing surface of the first folding section 301 and a lower wing surface of the second folding section 302 are hinged by a hinge 303, an upper wing surface of the inverted wing plate 3 is provided with a telescopic cylinder mounting groove 304, a telescopic cylinder 305 is mounted in the telescopic cylinder mounting groove 304, and a movable end of the telescopic cylinder 305 is hinged to the second folding section 302. The second folding section 302 can be folded forwards and retracted backwards through the extension and contraction of the movable end of the telescopic cylinder 305. Preferably, the second folding section 302 is provided with a folding ear plate 306, and the movable end of the telescopic cylinder 305 is hinged with the folding ear plate 306. The telescopic cylinder 305 may be a hydraulic telescopic cylinder, a pneumatic telescopic cylinder, or an electric telescopic cylinder.

In this embodiment, as shown in fig. 1 to 9, the inverted wing plate 3 includes a first expanding and contracting section 311 and a second expanding and contracting section 312, the first expanding and contracting section 311 is rotatably connected to the fixed wing plate 2, and the rotor 4 is disposed on the first expanding and contracting section 311. The leading edge of the second expanding and contracting section 312 is hinged to the leading edge of the first expanding and contracting section 311, and the hinge axis of the second expanding and contracting section 312 and the first expanding and contracting section 311 is perpendicular to the chord of the first expanding and contracting section and the second expanding and contracting section 312, so that the second expanding and contracting section 312 can be lifted upwards. The purpose of the lift-up is also to reduce the width dimension of the aircraft and thus reduce the floor space, but this way enables the width dimension of the nacelle 1 to be reduced while the center of gravity of the entire tilt wing 3 is not greatly changed compared to the fore-aft direction of the nacelle 1, and the balance of the entire aircraft is slightly affected and controlled. When the specific lifting is carried out, the first unfolding and folding section 311 needs to drive the second unfolding and folding section 312 to rotate together, namely, the overturning wing plate 3 overturns integrally at first, the rotor 4 faces upwards, and then the second unfolding and folding section 312 rotates upwards to lift.

Further, in this embodiment, as shown in fig. 1 to fig. 9, an end of the first expanding and contracting section 311 is provided with a sliding groove 313 and a pushing and lifting cylinder installation groove 314, a guide sleeve 315 is hinged in the sliding groove 313, a guide rod 316 is slidably connected in the guide sleeve 315, the guide rod 316 is hinged to an end of the second expanding and contracting section 312, and a hinge point between the guide rod 316 and the second expanding and contracting section 312 is located between a front edge and a rear edge of the second expanding and contracting section 312. The pushing and lifting cylinder mounting groove 314 is located between the sliding groove 313 and the front edge of the second unfolding and folding section 312, a pushing and lifting cylinder 317 is mounted in the pushing and lifting cylinder mounting groove 314, the movable end of the pushing and lifting cylinder 317 is hinged with the second unfolding and folding section 312, preferably, a pushing and lifting lug plate 318 is arranged on the second unfolding and folding section 312, and the movable end of the pushing and lifting cylinder 317 is hinged with the pushing and lifting lug plate 318. The lifting cylinder 317 can adopt a hydraulic telescopic cylinder, a pneumatic telescopic cylinder or an electric telescopic cylinder.

In this embodiment, as shown in fig. 1 to 9, a rotor casing 401 is provided outside the rotor 4, and the rotor casing 401 is fixed to the swing wing plate 3. Preferably, rotor shroud 401 is fixed to tilt wing 3 by a mount 402, and rotor 4 is rotatably attached to mount 402.

In this embodiment, as shown in fig. 1 to 9, the landing gear 6 is provided on the fixed wing plate 2. The undercarriage 6 is fixed on the lower wing surface of the fixed wing plate 2 through a lifting device, the lifting device comprises a lifting driving cylinder 602 fixed on the lower wing surface of the fixed wing plate 2, a telescopic cylinder rod 601 of the lifting driving cylinder 602 is fixedly connected with the undercarriage 6, and the length of the undercarriage 6 can be changed through the extension and retraction of the telescopic cylinder rod 601, so that the function of the undercarriage 6 is realized. The lifting driving cylinder 602 may be a hydraulic telescopic cylinder, a pneumatic telescopic cylinder or an electric telescopic cylinder.

In the present embodiment, as shown in fig. 1 to 9, the nacelle 1 and the fixed wing panel 2 are detachably connected by the pylon 7 so that the nacelle 1 can be replaced. Specifically, the hanger 7 includes a nacelle pile 103, a jaw 104, a link 105, a guide bush 106, a spring 107, an opening/closing cylinder 108, a piston rod 109, and a boom 110. The nacelle clamping pile 103 is fixed on the nacelle 1, the suspender 110 is fixed on the lower wing surface of the fixed wing plate 2, the suspender 110 is connected with the guide sleeve 106 in a sliding way, the guide sleeve 106 is hinged with the clamping jaw 104 through the connecting rod 105, the guide sleeve 106 can move up and down along the axis of the suspender 110, and the guide sleeve 106 is provided with a spring 107. An opening and closing driving cylinder 108 is installed on the bottom surface inside the fixed wing plate 2, a piston rod 109 of the opening and closing driving cylinder 108 is fixedly connected with a guide sleeve 106, the guide sleeve 106 can be driven by the piston rod 109 to move up and down along a hanger rod 110, the guide sleeve 106 moves up and down, a spring 107 is further compressed, the guide sleeve 106 drives a jaw 104 to open through a connecting rod 105, the fixed wing plate 2 descends to a proper position, the piston rod 109 can drive the guide sleeve 106 to move down, the guide sleeve 106 drives the jaw 104 to close through the connecting rod 105, the jaw 104 tightly holds an upper cabin clamping pile 103 of the cabin 1, a convex edge of the upper cabin clamping pile 103 of the cabin 1 is embedded into a closed loop in the jaw 104, the spring 107 tightly presses the guide sleeve 106 downwards, a conical inclined surface of the lower portion of the guide sleeve 106 is also attached to a conical surface of the upper portion of the jaw 104, and the hanger 7 is firmly fixed with the cabin 1 and cannot be separated.

The principle and the implementation mode of the invention are explained by applying a specific example, and the description of the above embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.

Claims

1. A multi-rotor aircraft, comprising a cabin and a gliding wing, wherein the gliding wing comprises a fixed wing plate and a turnover wing plate, the fixed wing plate is arranged at the top of the cabin, and a distance for air circulation is arranged between the fixed wing plate and the top of the cabin; the upset pterygoid lamina rotates to be connected the orientation of the both ends of fixed pterygoid lamina in order to change self chord, the symmetry is being equipped with the rotor on the last airfoil of upset pterygoid lamina and the lower airfoil, the axis of rotor with the chord of upset pterygoid lamina is parallel, two on the upset pterygoid lamina the rotor mirror image sets up.

2. The multi-rotor aircraft as claimed in claim 1, wherein the fixed wing panel has a tail wing at the top of its trailing edge for balancing the nacelle, and a cab at the top of its leading edge.

3. A multi-rotor aircraft according to claim 2, wherein a shaft and a rotating mechanism for driving the shaft to rotate are provided in the stationary wing plate, and the shaft is fixedly connected to the tilt wing plate.

4. A multi-rotor aircraft according to claim 3, wherein the rotary mechanism includes a drive pulley, a driven pulley and a drive device for driving the drive pulley to rotate, the drive device being fixed within the stationary wing plate, the driven pulley being fixed to the rotatable shaft, the drive pulley and the driven pulley being connected by a drive belt.

5. A rotorcraft according to claim 1, wherein said flap panel includes a first folded section pivotally connected to said fixed panel and a second folded section hinged to said first folded section with an axis parallel to the chord of said first folded section, said rotors being disposed on said first folded section.

6. The multi-rotor aircraft as claimed in claim 5, wherein the lower wing surface of the first folding section and the lower wing surface of the second folding section are hinged by a hinge, the upper wing surface of the turnover wing plate is provided with a telescopic cylinder mounting groove, and a telescopic cylinder with a movable end hinged to the folding section is mounted in the telescopic cylinder mounting groove.

7. A multi-rotor aircraft according to claim 1, wherein the flap panel includes a first deployment section and a second deployment section, the first deployment section being pivotally connected to the fixed panel, a leading edge of the second deployment section being hinged to a leading edge of the first deployment section, the second deployment section being hinged to the first deployment section with an axis perpendicular to a chord of the first deployment section, the rotor being disposed on the first deployment section.

8. The multi-rotor aircraft according to claim 7, wherein the first deploying and retracting segment end is provided with a sliding groove and a pushing and lifting cylinder installation groove, a guide sleeve is hinged in the sliding groove, a guide rod hinged with the second deploying and retracting segment end is connected in the guide sleeve in a sliding mode, and a hinge point of the guide rod is located between the front edge and the rear edge of the second deploying and retracting segment; the pushing cylinder mounting groove is located between the sliding groove and the front edge of the second unfolding and folding section, and a movable end and a pushing cylinder hinged to the second unfolding and folding section are mounted in the cylinder mounting groove.

9. A multi-rotor aircraft according to claim 1, wherein rotor shrouds are provided externally to the rotors, said rotor shrouds being secured to the rotor wings.

10. A multi-rotor aircraft according to claim 9, wherein the fixed wing panel is provided with a height-adjustable landing gear, the fixed wing panel is provided with a cradle which can be grasped and released, and the nacelle is detachably connected to the fixed wing panel via the cradle.