CN217836026U - Variable-pitch composite-wing unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses a compound wing unmanned aerial vehicle of feather, including fuselage, aircraft nose, wing, tail vaulting pole, fin, horizontal power unit and perpendicular power unit, fuselage tip fixedly connected with aircraft nose, fuselage both sides portion fixedly connected with wing, wing fixedly connected with tail vaulting pole, two fixedly connected with fin between the tail vaulting pole, the perpendicular power unit of fixedly connected with on the tail vaulting pole, perpendicular power unit includes first drive arrangement, perpendicular screw and feather unit, first drive arrangement output is fixed with perpendicular screw, perpendicular screw is fixed with the feather unit. The beneficial effects of the utility model are that, at the variable pitch unit of respectively installing in four positions of tail boom plate for control unmanned aerial vehicle is at the angle of attack of paddle under the rotor state, replaces the mode that the electricity was transferred and is changed current control motor speed, realizes that unmanned aerial vehicle hovers under the rotor state, control such as motor-driven.

Description

Variable-pitch composite-wing unmanned aerial vehicle

Technical Field

The utility model relates to a compound wing unmanned aerial vehicle technical field, especially a compound wing unmanned aerial vehicle of feather.

Background

The composite wing layout is a vertical take-off and landing aircraft solution combining fixed wing layout and multi-rotor wing layout, can overcome gravity and aerodynamic drag through the pulling force of a plurality of propellers like a multi-rotor wing aircraft to realize flight functions such as vertical take-off and landing, hovering, vertical climbing and descending, and can overcome gravity through aerodynamic lift like a fixed wing aircraft, and a power system overcomes aerodynamic drag to realize high-speed cruise flight.

The mode that changes the current control motor rotational speed through the electricity accent among the prior art realizes that unmanned aerial vehicle hovers under the rotor state, control such as maneuver. The control system sends control quantity according to feedback and control requirements of the sensor, and adopts a hydraulic actuation or electric mode to adjust the propeller pitch, so that the whole system has high complexity and poor reliability.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the problem, a variable pitch compound wing unmanned aerial vehicle has been designed. The aircraft comprises an aircraft body, aircraft noses, wings, tail stay bars, empennages, horizontal power units and vertical power units, wherein the aircraft nose is fixedly connected to the end part of the aircraft body, the wings are fixedly connected to the two side parts of the aircraft body, the tail stay bars are fixedly connected to the wings, the empennages are fixedly connected between the two tail stay bars, the vertical power units are fixedly connected to the tail stay bars, and the horizontal power units are fixedly connected to the end part of the aircraft body; the vertical power unit comprises a first driving device, a vertical propeller and a variable pitch unit, wherein the output end of the first driving device is fixedly provided with the vertical propeller, and the vertical propeller is fixedly provided with the variable pitch unit.

Furthermore, the vertical propeller comprises a blade, a clamping seat, a hub and a cross shaft, the hub is fixed at the output end of the first driving device, the cross shaft is fixed in the hub, the two ends of the cross shaft are rotatably connected with the clamping seat, and the blade is fixedly connected to the end of the clamping seat.

Furthermore, a notch is formed in the end of the clamping seat, and the fixing piece penetrates through the clamping frame and the paddle blade.

Furthermore, the variable pitch unit comprises an outer fixed disc, an inner rotating frame, a connecting rod, a supporting rod, a pull rod and a second driving device, the first driving device is fixed on the wing, the inner rotating frame is sleeved on an output shaft of the first driving device, the outer fixed disc is sleeved outside the inner rotating frame, the inner rotating frame and the outer fixed disc are coaxially arranged, the supporting rod is fixed on the side wall of the blade, and two ends of the connecting rod are respectively connected with the supporting rod and the inner rotating frame in a rotating mode.

Furthermore, the second driving device is fixed on the wing, the second driving device is provided with a rocker arm capable of rotating around the second driving device, the rocker arm is connected with a pull rod in a rotating mode, and the other end of the pull rod is fixed on the side wall of the outer fixing disc.

Furthermore, a deep groove ball bearing is arranged between the outer fixing disc and the inner rotating frame, and a linear bearing is arranged between the inner rotating frame and the output shaft of the first driving device.

Further, perpendicular power pack is provided with four, every all be provided with two perpendicular power packs on the tail vaulting pole, set up in the centrobaric the place ahead of unmanned aerial vehicle in one of them perpendicular power pack on same tail vaulting pole, another perpendicular power pack sets up in the centrobaric rear of unmanned aerial vehicle.

Furthermore, the wings are symmetrically arranged along the length direction of the fuselage, and two ends of the empennage are respectively and fixedly connected with the tail parts of the different tail stay bars.

Further, a secondary wing plate is arranged above the wing.

Further, the horizontal power unit is a horizontal propeller arranged at the tail end of the machine body.

Utilize the technical scheme of the utility model a variable pitch composite wing unmanned aerial vehicle of preparation, the beneficial effect who reaches:

(1) Second drive arrangement drives the rocking arm and rotates, rocking arm and pull rod drive the whole vertical direction removal of following of external fixation dish and internal rotation frame, at the in-process that internal rotation frame removed, the connecting rod drives the grip slipper and the whole its axial emergence of edge of paddle deflects, thereby change the unmanned aerial vehicle pitch, a feather unit is respectively installed in four positions of tail boom, an angle of attack for controlling unmanned aerial vehicle paddle under the rotor state, replace the mode that the electricity was transferred and is changed the current control motor speed, realize that unmanned aerial vehicle hovers under the rotor state, control such as maneuvering.

(2) Unmanned aerial vehicle has horizontal power unit and perpendicular power unit, can realize the operation of fixed wing state and two kinds of modes of many rotor states, and the space layout has been optimized with wing and fin fixed connection respectively to the tail boom.

Drawings

Fig. 1 is a top view of a variable pitch compound wing drone according to the present invention;

fig. 2 is a perspective view of the main body of the composite-wing unmanned aerial vehicle of the present invention;

FIG. 3 is a top view of the vertical power unit of the present invention;

fig. 4 is a perspective view of the vertical power unit of the present invention;

FIG. 5 is a schematic view of the internal structure of the vertical propeller of the present invention;

FIG. 6 is a schematic view of the internal structure of the pitch unit of the present invention;

in the figure, 1, a fuselage; 2. a machine head; 3. an airfoil; 4. a tail stay bar; 5. a tail fin; 6. a horizontal power unit; 7. a vertical power unit; 71. a first driving device; 72. a vertical propeller; 721. a paddle blade; 722. a clamping seat; 723. a hub; 724. a horizontal axis; 725. opening the gap; 73. a variable pitch unit; 731. an outer fixed disk; 732. an inner rotating frame; 733. a connecting rod; 734. a support bar; 735. a pull rod; 736. a second driving device; 737. a rocker arm; 738. a deep groove ball bearing; 739. a linear bearing; 8. a minor wing panel.

Detailed Description

It is right to combine the attached drawing below to describe the utility model discloses it is compound wing unmanned aerial vehicle of feather, as shown in fig. 1 and fig. 2, including fuselage 1, aircraft nose 2, wing 3, tail vaulting pole 4, fin 5, horizontal power unit 6 and perpendicular power unit 7, 1 tip fixedly connected with aircraft nose 2 of fuselage, 1 both sides portion fixedly connected with wing 3 of fuselage, 3 fixedly connected with tail vaulting poles 4 of wing, two fixedly connected with fin 5 between the tail vaulting pole 4, fixedly connected with vertical power unit 7 on the tail vaulting pole 4, 1 tip fixedly connected with horizontal power unit 6 of fuselage. This compound wing unmanned aerial vehicle has two kinds of flight states, stationary vane state and many rotor states. The vertical power unit 7 does not work under the fixed wing state, the vertical propeller 72 of the horizontal power unit 6 overcomes aerodynamic resistance, and the wing 3 generates aerodynamic lift force to overcome gravity; in the multi-rotor state, the pulling force generated by the vertical power unit 7 is used to overcome gravity.

As shown in fig. 3 and 4, the vertical power unit 7 includes a first driving device 71, a vertical propeller 72, and a pitch unit 73, the vertical propeller 72 is fixed to an output end of the first driving device 71, and the pitch unit 7 is fixed to the vertical propeller 72. The first driving device 71 may be selected as a motor, which is activated to rotate the vertical propeller 72, so that the wing 3 generates aerodynamic lift, and the pitch unit 73 is used to change the pitch.

As shown in fig. 5, the vertical propeller 72 includes a blade 721, a holder 722, a hub 723 and a cross shaft 724, the hub 723 is fixed at an output end of the first driving device 71, the cross shaft 724 is fixed in the hub 723, two ends of the cross shaft 724 are rotatably connected with the holder 722, and the blade 721 is fixedly connected with an end of the holder 722. A notch 725 is formed at the end of the clamping seat 722, and a fixing member passes through the clamping frame and the blade 721. When installing unmanned aerial vehicle, the flabellum passes through the mounting with grip slipper 722 and is fixed together to the mounting can be installed as required and tear out, provides convenience for whole unmanned aerial vehicle's installation and dismantlement. In the fixed pitch state, the clamping seat 722 and the transverse shaft 724 are kept relatively static, in the variable pitch state, the clamping seat 722 and the transverse shaft 724 rotate relatively, and a bearing is sleeved outside the transverse shaft 724 to provide guarantee for the rotation between the clamping seat 722 and the transverse shaft 724.

As shown in fig. 6, the pitch control unit 73 includes an outer fixed disk 731, an inner rotating frame 732, a connecting rod 733, a supporting rod 734, a pull rod 735, and a second driving device 736, the first driving device 71 is fixed to the wing 3, the inner rotating frame 732 is sleeved on an output shaft of the first driving device 71, the outer fixed disk 731 is sleeved outside the inner rotating frame 732, the inner rotating frame 732 and the outer fixed disk 731 are coaxially arranged, the supporting rod 734 is fixed to a side wall of the blade 721, and two ends of the connecting rod 733 are respectively rotatably connected to the supporting rod 734 and the inner rotating frame 732. The second driving device 736 is fixed to the wing 3, the second driving device 736 has a rocker arm 737 capable of rotating around the second driving device 736, the rocker arm 737 is rotatably connected with a pull rod 735, and the other end of the pull rod 735 is fixed to the side wall of the outer fixed disk 731. The second driving device 736 can be selected as a steering engine, the steering engine is provided with a rocker arm 737, the steering engine drives the rocker arm 737 to rotate after being started, the rocker arm 737 drives a pull rod 735 to move along the vertical direction, the outer fixed disk 731 and the inner rotating frame 732 are further integrally moved along an output shaft of the first driving device 71, in the moving process of the inner rotating frame 732, because two ends of the pull rod 735 are rotatably connected with a support rod 734 and an inner rotating frame 732 respectively, the pull rod 735 drives a clamping seat 722 and a paddle 722 to integrally rotate along the axial direction of the clamping seat and the paddle 722, the angle adjustment of the paddle 722 is realized, pure mechanical variable pitch is realized through a connecting rod 733, electric regulation participation is not needed, and the pitch changing process of the propeller is simplified.

A deep groove ball bearing 738 is arranged between the outer fixing disc 731 and the inner rotating frame 732, and a linear bearing 739 is arranged between the inner rotating frame 732 and the output shaft of the first driving device 71. When the vertical propeller 72 integrally rotates, the first driving device 71 is started to drive the inner rotating frame 732 to rotate, and the outer fixing plate 731 is kept fixed in the rotating process of the inner rotating frame 732 because the deep groove ball bearings 738 are arranged between the inner rotating frame 732 and the outer fixing plate 731.

Perpendicular power pack 7 is provided with four, every all be provided with two perpendicular power pack 7 on the tail vaulting pole 4, set up in the centrobaric the place ahead of unmanned aerial vehicle in one of them perpendicular power pack 7 on same tail vaulting pole 4, another perpendicular power pack 7 sets up in the centrobaric rear of unmanned aerial vehicle. The positions of the four vertical power units 7 and the gravity center of the aircraft have distances in the front-back direction and the left-right direction, namely a rolling force arm and a pitching force arm, and the required rolling control torque and pitching control torque can be provided by changing the tension difference in the rolling direction and the pitching direction generated by the tension of the four vertical power propellers;

the wings 3 are symmetrically arranged along the length direction of the fuselage 1, and two ends of the empennage 5 are respectively and fixedly connected with the tail parts of the different tail stay bars 4. 4 middle parts of tail vaulting pole and wing 3 fixed connection, 4 afterbody and fin 5 fixed connection of tail vaulting pole have improved unmanned aerial vehicle's structural performance.

And a secondary wing plate 8 is connected above the wing 3. In order to change the state that the wings 3 output the yawing moment and the rolling moment through the wings 3 under the high-speed flying state of the aircraft and simultaneously facilitate the adjustment of the yawing moment and the rolling moment, the wings 3 on each side of the fuselage 1 are hinged with a pair of auxiliary wing plates 8.

The horizontal power unit 6 is a horizontal propeller arranged at the tail end of the machine body 1. The horizontal propeller can be driven by an internal combustion engine or an electric motor, and the power equipment of the horizontal propeller can be arranged in the space inside the machine body 1 in order to save space and optimize space layout.

Above-mentioned technical scheme has only embodied the utility model discloses technical scheme's preferred technical scheme, some changes that this technical field's technical personnel probably made to some parts wherein have all embodied the utility model discloses a principle belongs to within the protection scope of the utility model.

Claims (10)

1. The variable-pitch compound wing unmanned aerial vehicle is characterized by comprising a body (1), a nose (2), wings (3), tail support rods (4), an empennage (5), a horizontal power unit (6) and a vertical power unit (7), wherein the nose (2) is fixedly connected to the end part of the body (1), the wings (3) are fixedly connected to the two side parts of the body (1), the tail support rods (4) are fixedly connected to the wings (3), the empennage (5) is fixedly connected between the two tail support rods (4), the vertical power unit (7) is fixedly connected to the tail support rods (4), and the horizontal power unit (6) is fixedly connected to the end part of the body (1);

the vertical power unit (7) comprises a first driving device (71), a vertical propeller (72) and a variable pitch unit (73), wherein the vertical propeller (72) is fixed at the output end of the first driving device (71), and the variable pitch unit (73) is fixed on the vertical propeller (72).

2. A variable pitch compound wing drone according to claim 1, wherein the vertical propeller (72) comprises blades (721), a holder (722), a hub (723) and a cross shaft (724), the hub (723) is fixed at the output end of the first driving device (71), the cross shaft (724) is fixed in the hub (723), the holder (722) is rotatably connected at both ends of the cross shaft (724), and the blades (721) are fixedly connected at the ends of the holder (722).

3. A variable pitch compound wing drone according to claim 2, wherein the holder (722) has a cut (725) at its end, and a fixing member passes through the holder and the blade (721).

4. The unmanned aerial vehicle with the variable pitch composite wings as claimed in claim 3, wherein the variable pitch unit (73) comprises an outer fixed disk (731), an inner rotating frame (732), a connecting rod (733), a supporting rod (734), a pull rod (735) and a second driving device (736), the first driving device (71) is fixed to the wing (3), the inner rotating frame (732) is sleeved on an output shaft of the first driving device (71), the outer fixed disk (731) is sleeved outside the inner rotating frame (732), the inner rotating frame (732) and the outer fixed disk (731) are coaxially arranged, the supporting rod (734) is fixed to a side wall of the blade (721), and two ends of the connecting rod (733) are respectively connected to the supporting rod (734) and the inner rotating frame (732) in a rotating manner.

5. A variable pitch compound wing drone according to claim 4, wherein the second drive means (736) is fixed to the wing (3), the second drive means (736) having a rocker arm (737) rotatable thereabout, the rocker arm (737) being rotatably connected to a tie rod (735), the other end of the tie rod (735) being fixed to the outer fixed disk (731) side wall.

6. A pitch-controlled compound wing drone according to claim 5, characterised in that between the external fixed disk (731) and the internal turret (732) there are deep groove ball bearings (738), between the internal turret (732) and the output shaft of the first driving device (71) there are linear bearings (739).

7. A pitch-controlled compound wing drone according to claim 1, characterized in that there are four vertical power units (7), each tail stay (4) has two vertical power units (7), one vertical power unit (7) of the same tail stay (4) is located in front of the center of gravity of the drone, and the other vertical power unit (7) is located behind the center of gravity of the drone.

8. A pitch-controlled compound wing unmanned aerial vehicle according to claim 1, wherein the wings (3) are symmetrically arranged along the length direction of the fuselage (1), and two ends of the tail wing (5) are respectively fixedly connected with the tail parts of the tail stay bars (4).

9. A pitch controlled compound wing drone according to claim 1, characterised in that a flap (8) is provided above the wing (3).

10. A pitch-controlled compound wing drone according to claim 1, characterised in that the horizontal power unit (6) is a horizontal propeller arranged at the end of the fuselage (1).

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