Unmanned aerial vehicle with tilting rotors

Abstract

The utility model discloses an unmanned aerial vehicle with tilting rotors. The unmanned aerial vehicle comprises a fuselage and wings symmetrically arranged on the left side and the right side of the fuselage. A tail supporting rod parallel to the axis of the fuselage is correspondingly mounted in the middle of each wing; the head of the tail supporting rod is hinged to a supporting foot which is arranged outside the tail supporting rod. A front steering engine used for driving the supporting feet to tilt is installed in an inner cavity of the head of the tail supporting rod. The supporting leg is provided with a supporting end and a mounting end which are oppositely arranged, and a front rotor wing is mounted at the mounting end; a rear rotor wing is arranged at the middle rear part of the tail support rod; an empennage is arranged at the tail part of the tail support rod; in the vertical take-off and landing stage, the supporting ends and the empennage form four supporting legs for supporting the fuselage; in the cruising stage, the axial direction of the supporting feet is parallel to the axial direction of the corresponding tail supporting rods. Through the cooperation of the front steering engine, the supporting legs, the front rotor wings and the empennage, the tilting function and the undercarriage function are combined into a whole, an independent undercarriage system is omitted, and therefore the structure is simplified, the weight is reduced, the resistance is reduced, and the space utilization rate is increased.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, concretely relates to a kind of unmanned plane with tilting rotor. BACKGROUND

[0002] At present, mainstream large-scale tilting rotor aircraft usually adopts independent landing gear system, which is arranged separately from tilting rotor mechanism. In the prior art, a fixed-wing aircraft is disclosed in Chinese patent document CN208377055U. The landing gear of the fixed-wing aircraft is installed at the bottom of the fuselage or the bottom of the tail strut.

[0003] If such design is applied to a miniature unmanned plane with limited structural space and load capacity, the following shortcomings will be exposed: first, the unmanned plane structure is complex and heavy, and the tilting mechanism and the landing gear system need independent driving, installation and maintenance structure, which increases the overall weight and system complexity, and the landing gear design also occupies valuable flight control channel, increasing manufacturing cost; second, the aerodynamic drag is large, and if the landing gear cannot be retracted or is exposed, it will generate significant parasitic drag during high-speed cruising, which seriously affects the range and time; third, the space utilization rate is low, and the independent landing gear retraction mechanism and the tilting system are arranged separately, which occupies a large amount of space under the wing and inside the fuselage, and may cause adverse changes in the aircraft's center of gravity.

[0004] In summary, a landing structure is needed to adapt to unmanned planes with tilting rotors. SUMMARY

[0005] The utility model discloses a kind of unmanned planes with tilting rotors, to solve the technical problem is: the landing structure of prior art cannot adapt to unmanned planes with tilting rotors.

[0006] The utility model discloses a kind of unmanned planes with tilting rotors, including fuselage and wing;

[0007] The wing is symmetrically arranged on the left and right sides of the fuselage;A tail strut parallel to the fuselage axis is installed in the middle of each wing;

[0008] The head of the tail strut is hinged with a leg, and the leg is placed outside the tail strut;A front rudder is installed in the head cavity of the tail strut for driving the leg to tilt;The leg has oppositely arranged support end and mounting end, and a front rotor is installed on the mounting end.

[0009] The rear part of the tail strut is vertically provided with a rear rotor;

[0010] The tail of the tail support rod is provided with a tail wing; the tail wing has an H-shaped structure, comprising a horizontal tail and vertical tails symmetrically arranged at the left and right ends of the horizontal tail; the horizontal tail is arranged between the two tail support rods, and the left and right ends thereof are connected with the adjacent tail support rods respectively; the vertical tail is arranged vertically, and the bottom thereof is detachably connected with a ventral fin; the supporting end of the supporting leg is matched with the ventral fin to form a supporting four-leg for supporting the fuselage during the vertical take-off and landing stage; the axial direction of the supporting leg is parallel to the axial direction of the corresponding tail support rod during the cruising stage; the tilt function and the landing gear function are combined by matching the front rudder, the supporting leg, the front rotor and the tail wing, so that the whole set of independent landing gear retraction system is omitted, and the number of parts, the structural complexity and the weight of the whole machine are reduced.

[0011] Optionally, the supporting end of the supporting leg has a U-shaped structure and is distributed at the left and right sides of the head of the corresponding tail support rod;

[0012] The outer peripheral wall of the supporting leg is conformal with the outer peripheral wall of the tail support rod to form a low-resistance shape;

[0013] The axial line of the supporting leg is located on the same straight line as the axial line of the corresponding tail support rod during the cruising stage;

[0014] An installation groove is formed in the end face of the mounting end of the supporting leg, and the motor of the front rotor is mounted in the installation groove. By adopting the above scheme, the resistance of the unmanned aerial vehicle during high-speed cruising is reduced.

[0015] Optionally, a carbon fiber rod is vertically inserted between the vertical tail and the ventral fin;

[0016] The bottom of the vertical tail is provided with a connecting protrusion, the top of the ventral fin is provided with a connecting groove matched with the connecting protrusion, and a connecting bolt is connected between the connecting protrusion and the ventral fin, and the connecting bolt extends along the thickness direction of the vertical tail. By adopting the above scheme, the vertical tail and the ventral fin are effectively connected.

[0017] Optionally, the projection area of the ventral fin in the thickness direction is 50% to 70% of the projection area of the vertical tail in the thickness direction.

[0018] Optionally, the mounting end of the supporting leg and the lower end of the tail wing are both provided with a shock-absorbing pad. By adopting the above scheme, the landing impact is absorbed, and the unmanned aerial vehicle is effectively protected.

[0019] Optionally, the tail support rod comprises a nacelle at the head and a main rod arranged at the rear end of the nacelle;

[0020] The nacelle is a hollow cavity, and the nacelle extends along the axial direction of the main rod;

[0021] The front rudder is mounted in the nacelle, and a driving end of the front rudder extends out of the nacelle and is connected to the leg through a flange.

[0022] Optionally, the main rod is internally provided with a carbon fiber rod extending in an axial direction of the main rod, and the main rod is further provided with a wire hole in communication with the inner cavity of the nacelle. By using the above scheme, the tail support rod is reinforced by the carbon fiber rod.

[0023] Optionally, ailerons are mounted outside the trailing edges of the wing tips, and movable rudders are mounted on the tail wings. Compared with the prior art, the unmanned aerial vehicle has the following beneficial effects by using the above technical scheme:

[0024] The tilt function and the landing gear function are combined by cooperation of the front rudder, the leg, the front rotor and the tail wing, a complete set of independent landing gear retraction system is omitted, and the number of parts, the structural complexity and the overall weight are significantly reduced;

[0025] During the cruising stage, the axis of the leg is located on the same straight line as the axis of the corresponding tail support rod, the outer peripheral wall of the leg is conformal to the outer peripheral wall of the main rod, and there is no exposed part, so that the wind area and the aerodynamic resistance are effectively reduced, and the flight efficiency is improved;

[0026] The simplified structure reduces the manufacturing cost, and is particularly suitable for 3D printing or light composite material manufacturing. The passive mechanical retraction mechanism has no additional actuating system, is high in reliability, and is easy to maintain.

[0027] The above description of the present disclosure and the following description of the embodiments are used to demonstrate and explain the spirit and principles of the present utility model, and provide further explanation of the patent application scope of the present utility model. BRIEF DESCRIPTION OF DRAWINGS

[0028] The specific embodiments of the present utility model will be further described in detail below with reference to the accompanying drawings.

[0029] Figure 1 Fig. 1 is a schematic view of the unmanned aerial vehicle in the vertical take-off and landing stage of the present utility model;

[0030] Figure 2 Fig. 2 is a schematic view of the unmanned aerial vehicle in the cruising stage of the present utility model;

[0031] Figure 3 Fig. 3 is an exploded schematic view of the tail support rod head and the front rotor of the present utility model;

[0032] Figure 4 Fig. 4 is a partial exploded schematic view of the tail wing of the present utility model.

[0033] BRIEF DESCRIPTION OF DRAWINGS

[0034] 1, fuselage; 2, wing; 21, aileron; 3, tail strut; 31, nacelle; 32, main rod; 321, wire hole; 4, leg; 41, mounting groove; 5, front steering gear; 6, front rotor; 7, rear rotor; 8, tail wing; 81, horizontal tail; 82, vertical tail; 821, connecting protrusion; 83, ventral fin; 831, connecting groove; 84, connecting bolt; 9, carbon fiber rod. DETAILED DESCRIPTION

[0035] The following describes the embodiments of the present application with specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the disclosure. Although the description of the present application will be introduced in combination with the preferred embodiments, this does not mean that the features of the present application are limited to the embodiments. On the contrary, the purpose of introducing the present application in combination with the embodiments is to cover other options or modifications that can be extended based on the claims of the present application. In order to provide a deep understanding of the present application, many specific details will be included in the following description. The present application can also be implemented without using these details. In addition, in order to avoid confusion or obscure the focus of the present application, some specific details will be omitted in the description. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0036] In the description of the present embodiment, it should be noted that the terms "upper", "lower", "inner", "bottom" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship commonly used when the product of the present application is used, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0037] The terms "first", "second", and the like are only used for differentiation and cannot be understood as indicating or implying relative importance.

[0038] In the description of the present embodiment, it should also be noted that, unless otherwise explicitly specified and limited, the terms "provided with", "provided", "connected", "connected" should be broadly understood, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be connected inside two elements. For those skilled in the art, the specific meaning of the above terms in the present embodiment can be understood according to the specific circumstances.

[0039] The present application discloses a kind of unmanned aerial vehicle with tilting rotor. Please refer to Figures 1-3As shown in the drawings, the unmanned aerial vehicle comprises a fuselage 1, wings 2 and tail struts 3. The axis of the fuselage 1 extends in the front-rear direction. The wings 2 are two wings symmetrically arranged on the left and right sides of the fuselage 1. The middle part of each wing 2 is provided with a tail strut 3 parallel to the axis of the fuselage 1. That is, the tail strut 3 extends in the front-rear direction.

[0040] The head (i.e. the front end) of each tail strut 3 is hingedly provided with a leg 4. The leg 4 is arranged outside the tail strut 3. The head cavity of the tail strut 3 is provided with a front rudder 5 for driving the leg 4 to tilt. The leg 4 has oppositely arranged supporting ends and mounting ends. The mounting end of the leg 4 is provided with a front rotor 6. The middle-rear part of the tail strut 3 is vertically provided with a rear rotor 7. The tail of the tail strut 3 (i.e. the rear end) is provided with a tail wing 8. In this embodiment, the rear rotor 7 is located between the wing 2 and the tail wing 8. The front rotor 6 comprises a front blade and a front motor for driving the front blade to rotate. The front motor is mounted on the mounting end of the leg 4. The rear rotor 7 comprises a rear blade and a rear motor for driving the rear blade to rotate. The rear motor is vertically mounted on the tail strut 3.

[0041] The front rudder 5 is a prior art. The rudder controls the axial direction of the front motor to control the front blade to generate upward or forward pulling force. The existing Chinese patent document with the publication number CN103895039A discloses a screwless quick disassembly rudder output shaft structure. Therefore, the front rudder 5 will not be described in detail.

[0042] The front rudder 5 is connected to a controller in the fuselage 1 of the unmanned aerial vehicle. The front rudder 5 is adapted to drive the leg 4 to tilt according to the instructions of the controller to adapt to different working stages of the unmanned aerial vehicle.

[0043] Please refer to Figure 1 and Figure 4 As shown in the drawings, the tail wing 8 has an H-shaped structure. The tail wing 8 comprises a horizontal tail 81, vertical tails 82 and a belly fin 83. The horizontal tail 81 is arranged between the two tail struts 3, and the left and right ends thereof are connected to the adjacent tail struts 3. The vertical tails 82 are two vertical tails symmetrically arranged at the left and right ends of the horizontal tail 81. The vertical tails 82 are vertically arranged, and the bottom thereof is detachably connected to the belly fin 83. The belly fin 83 is adapted to cooperate with the vertically arranged leg 4 in the vertical take-off and landing stage to support the fuselage 1.

[0044] When the unmanned aerial vehicle needs to be in the vertical take-off and landing stage, the front rudder 5 drives the leg 4 to rotate, so that the axis of the leg 4 extends in the up-down direction to adapt to the vertical take-off and landing stage of the unmanned aerial vehicle. Therefore, in the vertical take-off and landing stage, as shown in Figure 1 the supporting end of the leg 4 is arranged downward, the supporting end of the leg 4 cooperates with the lower end of the belly fin 83 to form a supporting four-legged structure (i.e. a landing gear structure) for supporting the fuselage 1, and the mounting end of the leg 4 is vertically arranged upward. At this time, the blades of the front rotor 6 and the rear rotor 7 are all located above the tail strut 3.

[0045] When the UAV needs to be in the transition phase to the cruising phase, the front rudder 5 drives the leg 4 to rotate, so that the axis of the leg 4 is parallel to the axis of the corresponding tail strut 3, so as to adapt to the cruising phase of the UAV. Therefore, as shown in the figure, the front blade of the front rotor 6 is located in front of the tail strut 3. Preferably, in the cruising phase, the axis of the leg 4 is on the same straight line as the axis of the corresponding tail strut 3. Figure 2

[0046] Further, as shown in Figure 1 and Figure 4 , the vertical tail 82 and the ventral fin 83 are vertically inserted with the carbon fiber rod 9. The bottom of the vertical tail 82 is provided with a connecting protrusion 821. The top of the ventral fin 83 is provided with a connecting groove 831 matched with the connecting protrusion 821. The connecting protrusion 821 and the ventral fin 83 are connected with the connecting bolt 84. The connecting bolt 84 extends along the thickness direction of the vertical tail 82.

[0047] Further, the mounting end of the leg 4 and the lower end of the ventral fin 83 are both provided with shock pads, which are used to absorb the landing impact and effectively protect the UAV. The shock pads include but are not limited to rubber shock pads.

[0048] Further, the projection area of the ventral fin 83 in the thickness direction (i.e. the left-right direction in this embodiment) is 50% to 70% of the projection area of the vertical tail 82 in the thickness direction (i.e. the left-right direction in this embodiment). Preferably, the projection area of the ventral fin 83 in the thickness direction is 60% of the projection area of the vertical tail 82 in the thickness direction.

[0049] In this embodiment, the connection between the tail plane 81, the vertical tail 82 and the main rod 32 is integrally formed by 3D printing.

[0050] Further, as shown in Figure 2 and Figure 3 , the support end of the leg 4 is in a U-shaped structure and is distributed on the left and right sides of the head of the corresponding tail strut 3. The outer peripheral wall of the leg 4 is conformal with the outer peripheral wall of the tail strut 3 to form a low-resistance shape. The mounting end face of the leg 4 is provided with a mounting groove 41, and the motor of the front rotor 6 is mounted in the mounting groove 41.

[0051] In this embodiment, the bottom of the mounting groove 41 is provided with a connecting hole, and the motor of the front rotor 6 is connected with the connecting hole through a bolt, so that the motor of the front rotor 6 is mounted in the mounting groove 41.

[0052] In this embodiment, the leg 4 is a 3D printed integrally formed structure.

[0053] ​Further, the tail strut 3 comprises a nacelle 31 at the head and a main rod 32 arranged at the rear end of the nacelle 31. The nacelle 31 is a hollow cavity. The nacelle 31 extends along the axial direction of the main rod 32. The front rudder 5 is installed in the nacelle 31. The driving end of the front rudder 5 extends out of the nacelle 31 and is connected to the leg 4 through a flange. The main rod 32 is provided with a carbon fiber rod 9 extending along the axial direction of the main rod 32 to reinforce the tail strut 3.

[0054] The main rod 32 is further provided with a wire hole 321 communicating with the inner cavity of the nacelle 31. In the embodiment, the bottom of the mounting groove 41 is further provided with a first through hole, and the front end of the nacelle 31 is provided with a second through hole. The motor cable of the front rotor 6 can pass through the first through hole, the second through hole and the wire hole 321 in sequence, and finally extend into the fuselage 1 through the connecting hole in the wing 2, so as to be connected to the controller in the fuselage 1.

[0055] Further, referring to Figure 1 As shown in the figure, the wing tip of the wing 2 is provided with an aileron 21. The movable rudder surfaces are respectively arranged on the tail plane 81 and the vertical tail 82. Among them, the aileron 21 and the movable rudder surface are both prior art, so they will not be described in detail.

[0056] In the embodiment, the working principle of the unmanned aerial vehicle is as follows:

[0057] The vertical take-off and landing stage: the front rudder 5 drives the leg 4 to the vertical position, at this time, the mounting end of the leg 4 is vertically arranged downward, the support end of the leg 4 and the lower end of the ventral fin 83 form a support four leg (i.e. landing gear structure), the support four leg contacts the ground to support the unmanned aerial vehicle.

[0058] The transition to cruising stage: after the unmanned aerial vehicle takes off, the front rudder 5 drives the mounting end of the leg 4 to tilt forward, so that the support end of the leg 4 tilts backward, the support end of the leg 4 leaves the ground and is simultaneously stored to the left and right sides of the nacelle 31, so that the axis of the leg 4 and the axis of the corresponding tail strut 3 are located on the same straight line.

[0059] High-speed cruising stage: the axis of the leg 4 and the axis of the corresponding tail strut 3 are located on the same straight line, the outer peripheral wall of the leg 4 and the outer peripheral wall of the main rod 32 are conformal, forming a clean aerodynamic shape.

[0060] Landing preparation stage: the above process is performed in reverse, the front rudder 5 drives the leg 4 to be lowered to the vertical position.

[0061] Overall, the utility model discloses a front rudder, support foot, front rotor and tail wing cooperate, combine the tilting function and landing gear function, save a complete set of independent landing gear retraction system, significantly reduce the number of parts, structural complexity and the whole machine weight.In the cruising stage, the axis of support foot and the axis of corresponding tail strut are on the same straight line, the outer peripheral wall of support foot and the outer peripheral wall of main rod are conformal, without any exposed components, effectively reduce the wind area and aerodynamic drag, improve the flight efficiency.Structure simplification reduces the manufacturing cost, especially suitable for 3D printing or light composite material manufacturing.Passive mechanical retraction mechanism, without additional actuating system, high reliability, easy maintenance.

[0062] The above embodiment only illustrates the principle and effect of the utility model, and is not used to limit the utility model. Any person skilled in the art can modify or change the above embodiment without departing from the spirit and scope of the utility model. Therefore, all equivalent modifications or changes completed by those skilled in the art without departing from the spirit and technical thought disclosed by the utility model should be covered by the claims of the utility model.

Claims

1. An unmanned aerial vehicle having tilting rotors, characterized by, The aircraft comprises a fuselage (1) and wings (2); The wings (2) are symmetrically arranged on the left and right sides of the fuselage (1); a tail strut (3) parallel to the axis of the fuselage (1) is arranged at the middle of each wing (2); The head of the tail strut (3) is hingedly connected with a leg (4) arranged outside the tail strut (3); the inner cavity of the head of the tail strut (3) is arranged with a front rudder (5) for driving the leg (4) to tilt; the leg (4) has oppositely arranged supporting ends and mounting ends, and the mounting ends are arranged with front rotors (6); The middle and rear part of the tail strut (3) is vertically arranged with a rear rotor (7); The tail of the tail strut (3) is arranged with a tail wing (8); the tail wing (8) has an H-shaped structure, comprising a horizontal tail (81) and vertical tails (82) symmetrically arranged at the left and right ends of the horizontal tail (81); the horizontal tail (81) is arranged between the two tail struts (3), and the left and right ends thereof are connected with the adjacent tail struts (3); the vertical tail (82) is vertically arranged, and the bottom thereof is detachably connected with a ventral fin (83); the supporting end of the leg (4) is matched with the ventral fin (83) to form a supporting quadruped for supporting the fuselage (1) during the vertical take-off and landing stage; the axial direction of the leg (4) is parallel to the axial direction of the corresponding tail strut (3) during the cruising stage.

2. The drone of claim 1, wherein, The supporting end of the leg (4) has a U-shaped structure and is distributed on the left and right sides of the head of the corresponding tail strut (3); The outer peripheral wall of the leg (4) is conformal with the outer peripheral wall of the tail strut (3) to form a low-resistance shape; The axial direction of the leg (4) is parallel to the axial direction of the corresponding tail strut (3) during the cruising stage; The mounting end surface of the leg (4) is arranged with a mounting groove (41), and the motor of the front rotor (6) is arranged in the mounting groove (41).

3. The drone of claim 1, wherein, A carbon fiber rod (9) is vertically inserted between the vertical tail (82) and the ventral fin (83); The bottom of the vertical tail (82) is arranged with a connecting protrusion (821), and the top of the ventral fin (83) is arranged with a connecting groove (831) matched with the connecting protrusion (821); a connecting bolt (84) is connected between the connecting protrusion (821) and the ventral fin (83), and the connecting bolt (84) extends along the thickness direction of the vertical tail (82).

4. The drone of claim 1, wherein, The projection area of the ventral fin (83) in the thickness direction is 50%-70% of the projection area of the vertical tail (82) in the thickness direction.

5. The drone of claim 1, wherein, The mounting end of the leg (4) and the lower end of the tail wing (8) are both arranged with a shock pad.

6. The drone of claim 1, wherein, The tail strut (3) comprises a nacelle (31) at the head and a main rod (32) arranged at the rear end of the nacelle (31); The nacelle (31) is a hollow cavity, and the nacelle (31) extends along the axial direction of the main rod (32); The front rudder (5) is installed in the nacelle (31), and the driving end thereof extends out of the nacelle (31) and is connected with the leg (4) through a flange.

7. The drone of claim 6, wherein, The main rod (32) is provided with a carbon fiber rod (9) extending along the axial direction of the main rod (32), and the main rod (32) is further provided with a wire hole (321) in communication with the inner cavity of the nacelle (31).

8. The drone of claim 1, wherein, The wing tip trailing edge outer side of the wing (2) is provided with ailerons (21), and the tail wing (8) is provided with a movable rudder surface.

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