CN217893225U - Double-oar unmanned aerial vehicle - Google Patents

Abstract

The utility model provides a double-oar unmanned aerial vehicle, include fuselage, control system, set up in the wing unit of fuselage lateral part and set up in the rotor unit of fuselage, wing unit and rotor unit all are controlled its characterized in that by the control system: the end groove has all been seted up to the front and back end of fuselage, the rotor unit sets up to two and sets up respectively in the front and back end of fuselage, the rotor unit is connected in the vector control subassembly of sharp drive assembly drive end, is connected in the motor of the vector control subassembly other end and is fixed in the paddle of motor output including setting up sharp drive assembly, one end in the end groove, sharp drive assembly, vector control subassembly and motor all are connected with control system, sharp drive assembly is used for driving vector control subassembly business turn over end groove. The utility model discloses have and improve among the prior art unmanned aerial vehicle and can't carry out the ascending shortening of length direction, have the effect of the relatively limited problem of volume reduction degree.

Description

Double-oar unmanned aerial vehicle

Technical Field

The utility model relates to an aircraft technical field especially relates to a double-oar unmanned aerial vehicle.

Background

A drone is an unmanned aircraft that is operated with a radio remote control device and self-contained program control, or is operated autonomously, either completely or intermittently, by an onboard computer. The unmanned aerial vehicle mainly comprises a vehicle body, a program power control mechanism (control system) which is arranged on the vehicle body and connected with a remote control device, and a plurality of rotor wings or double-wing aircraft connected with the vehicle body; during the use, send a signal to procedure power control mechanism through radio remote control equipment, utilize procedure power control mechanism control rotor or wing action to accomplish unmanned aerial vehicle's the flight status such as lift, roll, every single move and driftage.

The utility model discloses a portable folding wing unmanned aerial vehicle that chinese utility model patent publication number is CN208344529U, including the central authorities body and wing, the central authorities body left and right sides all connects the wing through a mechanism of turning over, a mechanism of turning over includes articulated elements and hasp subassembly, the wing upper surface is connected to articulated elements one end, and central authorities body upper surface is connected to the other end, the wing lower surface passes through hasp subassembly locking/breaks away from central authorities body lower surface, the wing is the expansion state with the central authorities body when flight, is fold condition before launching.

Above-mentioned scheme realizes the reduction of unmanned aerial vehicle volume through turning over the wing and rolling over the mode on the body of central authorities, but this kind of folding mode can only realize reducing relatively of volume on the body width direction of central authorities, and the volume on the body length direction of central authorities is unchangeable, leads to the whole volume of unmanned aerial vehicle to reduce the degree relatively limited.

SUMMERY OF THE UTILITY MODEL

To exist not enough among the prior art, the utility model provides a double-oar unmanned aerial vehicle, it can improve among the prior art unmanned aerial vehicle can't carry out the ascending shortening of length direction, has the relatively limited problem of volume reduction degree.

According to the utility model discloses an embodiment, a double-oar unmanned aerial vehicle, it includes fuselage, control system, sets up in the wing unit of fuselage lateral part and sets up in the rotor unit of fuselage, wing unit and rotor unit all are controlled by control system, the end groove has all been seted up to the front and back end of fuselage, the rotor unit sets up to two and sets up respectively in the front and back end of fuselage, the rotor unit is connected in the vector control subassembly of linear drive subassembly drive end, is connected in the motor of the vector control subassembly other end and is fixed in the paddle of motor output including setting up linear drive subassembly, the one end in the end groove, linear drive subassembly, vector control subassembly and motor all are connected with control system, linear drive subassembly is used for driving vector control subassembly business turn over end groove.

Preferably, the vector control assembly comprises a steering engine base fixed at the driving end of the linear driving assembly, a cardan shaft with one end connected to the steering engine base, a motor base fixed at the other end of the cardan shaft, and a plurality of three linear steering engines circumferentially and uniformly distributed on the cardan shaft, the motor is fixedly connected to the motor base, two ends of each three linear steering engine are respectively connected to the steering engine base and the motor base, and each three linear steering engines are connected to the control system.

Preferably, a protective shell is covered outside the vector control assembly, and the protective shell is fixed on the linear driving assembly and is opened towards one end of the blade.

Preferably, the number of the third linear steering engines is not less than three.

Preferably, both sides of the middle end of the machine body are provided with side grooves; the wing unit comprises a steering assembly fixed at the bottom of the side groove, wings connected to the end of the steering assembly and a telescopic assembly arranged on the steering assembly, the steering assembly and the telescopic assembly are both connected to a control system, and the telescopic assembly is used for enabling the wings to be folded on the fuselage.

Preferably, the steering assembly comprises a first linear steering engine fixed at the bottom of the side groove, a U-shaped seat fixed at the action end of the first linear steering engine, a rotary steering engine fixed at the U-shaped seat, a steering engine connecting rod fixed at the action end of the rotary steering engine and a hinge rod with one end rotatably connected to the steering engine connecting rod, the first linear steering engine and the rotary steering engine are both connected to the control system, the first linear steering engine is used for enabling the rotating connecting part of the steering engine connecting rod and the hinge rod to extend out of the side groove, and the hinge rod is fixedly connected to the wing.

Preferably, the telescopic assembly comprises a rotating seat fixed on the U-shaped seat, a second linear steering engine connected to the control system and a link ring coaxially connected to the hinge rod in a rotating mode, and two ends of the second linear steering engine are respectively connected to the rotating seat and the link ring in a rotating mode so as to drive the wing to be folded on the machine body.

Preferably, the wire casing has still been seted up to the middle-end of fuselage to be provided with and be used for judging the folding antenna of unmanned aerial vehicle flying height, folding antenna and ground control system equipment signal connection.

Preferably, the fuselage rear end still is provided with the foot rest formula fin, foot rest formula fin includes a plurality of No. four straight line steering engines that are fixed in the fuselage and connects in the rectilinear tail wing of a plurality of No. four straight line steering engines simultaneously, no. four rectilinear steering engines connect in control system, and set up and be located rectilinear tail wing in the rotor unit of fuselage rear end.

To sum up, the utility model discloses a following at least one useful technological effect:

1. through setting up the rotor unit that is located fuselage front and back end respectively, the rotor unit includes the sharp drive assembly that connects gradually, vector control subassembly, motor and paddle, sharp drive assembly, vector control subassembly and motor all link to each other with control system, in order to finish using, through control system control sharp drive assembly start, with vector control subassembly, motor and paddle towards the tank bottom direction pulling of end groove, until the paddle is close to the fuselage, thereby make unmanned aerial vehicle's whole length shorten, improve unmanned aerial vehicle among the prior art and can't carry out the shortening in the length direction, there is the problem that the volume reduction degree is relatively limited;

2. the side groove is formed in the side face of the unmanned aerial vehicle body, the steering assembly connected with the wings is arranged in the side groove, the telescopic assembly connected with the unmanned aerial vehicle body and the steering assembly is arranged at the same time, the steering assembly and the telescopic assembly are locally connected to the control system, so that when the unmanned aerial vehicle is used, the control system is used for controlling the steering assembly and the telescopic assembly to be started, the steering assembly and the telescopic assembly are controlled to rotate for a certain angle through the steering assembly, and then the wings are indirectly pulled to rotate through the telescopic assembly until the wings are close to and folded on the unmanned aerial vehicle body, so that the size of the unmanned aerial vehicle is further reduced, and the unmanned aerial vehicle is convenient to carry;

3. furthermore, a foot rest type tail wing is further arranged at the rear end of the unmanned aerial vehicle body and comprises a fourth linear steering engine and a vertical tail wing, the fourth linear steering engine is connected with the control system, and the vertical tail wing is controlled by the control system to move towards the unmanned aerial vehicle body after the unmanned aerial vehicle is used, so that the length of the whole unmanned aerial vehicle is further shortened.

Drawings

Fig. 1 is a schematic diagram of the overall structure of the embodiment of the present invention;

fig. 2 is a schematic view of a first partial cross-sectional structure of an embodiment of the present invention, primarily showing a rotor unit;

fig. 3 is a schematic view of a second partial cross-sectional structure of an embodiment of the present invention, mainly showing a wing unit;

FIG. 4 is an enlarged schematic view of the portion B of FIG. 3;

FIG. 5 is an enlarged view of the portion A of FIG. 2;

fig. 6 is a schematic structural diagram of the vector control assembly according to an embodiment of the present invention.

In the drawings, wherein: 1. a body; 11. an end slot; 12. a side groove; 13. a wire slot; 14. folding the antenna; 2. a steering assembly; 21. a first linear steering engine; 22. a U-shaped seat; 23. rotating the steering engine; 24. a steering engine connecting rod; 25. a hinge rod; 3. an airfoil; 4. a telescoping assembly; 41. a rotating seat; 42. a second linear steering engine; 43. a link ring; 5. a linear drive assembly; 6. a vector control component; 61. a steering engine base; 62. a cardan shaft; 63. a motor base; 64. a third linear steering engine; 65. a protective shell; 7. a motor; 8. a paddle; 9. a foot rest type tail fin; 91. a fourth linear steering engine; 92. a vertical tail wing.

Detailed Description

The present invention will be further described with reference to fig. 1-6.

Referring to fig. 1 and 2, the embodiment of the utility model provides a double-oar unmanned aerial vehicle is proposed, including fuselage 1, control system, set up in the wing unit of 1 lateral part of fuselage and set up in the rotor unit of fuselage 1, wing unit and rotor unit all are controlled by control system to the flight of unmanned aerial vehicle is realized in the action through wing unit and rotor unit. Wherein, the foot rest type empennage 9 is arranged at the tail end of the fuselage 1, the foot rest type empennage 9 comprises a plurality of No. four linear steering engines 91 and a vertical empennage 92 which is simultaneously connected with the plurality of No. four linear steering engines 91, the No. four linear steering engines 91 are connected with a control system, and the vertical empennage 92 is positioned outside the rear section rotor wing unit of the fuselage 1; during takeoff, the unmanned aerial vehicle can be placed on the ground to form a vertical takeoff state of the unmanned aerial vehicle, and during flying, the vertical tail wing 92 forms a tail wing flying effect and can fly in a fixed wing mode; when accomodating, after contracting the rotor unit of fuselage 1 rear end, a plurality of No. four straight line steering wheel 91 of accessible are controlled simultaneously, contract whole foot rest formula fin 9 to further whole unmanned aerial vehicle's length.

End groove 11 has all been seted up at the front and back end of fuselage 1, and has all seted up side channel 12 in the middle-end both sides of fuselage 1, has seted up wire casing 13 at the middle-end upside of fuselage 1, the opening direction of wire casing 13's notch direction perpendicular to side channel 12. A folding antenna 14 is arranged at the wire slot 13, and the folding antenna 14 is in signal connection with ground control system equipment (such as a remote controller) so as to judge the flight attitude of the unmanned aerial vehicle in the states of visual flight and take-off and landing.

With reference to fig. 2 to 4, the wing unit comprises a steering assembly 2, a wing 3 and a telescopic assembly 4; the steering assembly 2 comprises a first linear steering engine 21, a U-shaped seat 22, a rotary steering engine 23, a steering engine connecting rod 24 and a hinge rod 25; the first linear steering engine 21 and the rotary steering engine 23 are connected to a control system to control the first linear steering engine 21 and the rotary steering engine 23 to act through the control system, the first linear steering engine 21 is fixed at the bottom of the side groove 12, and the U-shaped seat 22 is fixed at the acting end of the first linear steering engine 21 to move along the direction of the notch of the side groove 12 under the action of the first linear steering engine 21; the rotary steering engine 23 is fixed on the U-shaped seat 22, and the steering engine connecting rod 24 is fixed at the end part of the rotary steering engine 23; one end of the hinge rod 25 is rotatably connected to one end, far away from the rotary steering engine 23, of the steering engine connecting rod 24, and the wing 3 is fixed to the other end of the hinge rod 25; no. one straight line steering wheel 21 through control system control starts, and the rotation connecting portion that promote steering wheel connecting rod 24 and hinge rod 25 stretch out side channel 12, then, the action of the rotatory steering wheel of control system control, drive steering wheel connecting rod 24, hinge rod 25 and 3 certain angles of rotation of wing, the embodiment of the utility model provides an in 90.

The telescopic assembly 4 comprises a rotating seat 41, a second linear steering engine 42 and a link ring 43; the rotating seat 41 is fixed on the side wall of the U-shaped seat 22; the second linear steering engine 42 is connected to the control system, and two ends of the second linear steering engine are respectively connected to the rotating seat 41 and the chain link ring 43 in a rotating manner; the link ring 43 is coaxially and rotatably connected to the end of the hinge rod 25 near the wing 3.

When the flight is finished, the first linear steering engine 21 is controlled to be started through the control system, and the rotary connecting part of the steering engine connecting rod 24 and the hinge rod 25 is pushed to extend out of the side groove 12; then the control system controls the rotary steering engine 23 to start, so that the wings 3 rotate for 90 degrees; then, the second linear steering engine 42 is controlled by the control system to be shortened, the hinge rod 25 and the wings 3 rotate simultaneously, and the wings 3 are pulled to be folded on the side face of the unmanned aerial vehicle body 1, so that the folding work of the two wings 3 is completed, the overall transverse size of the unmanned aerial vehicle is reduced, and the unmanned aerial vehicle is convenient to carry. The retractable wing 3 can effectively avoid the door plate effect when the unmanned aerial vehicle takes off.

Referring to fig. 2, 5 and 6, in the embodiment of the present invention, two rotor units are provided and are respectively disposed at the front and rear ends of the fuselage 1, and the rotor unit located at the rear end of the fuselage 1 is located in the foot stool type empennage 9. The rotor wing unit comprises a linear driving component 5, a vector control component 6, a motor 7 and a blade 8 which are connected in sequence, the linear driving component 5 is arranged in an end slot 11, and the blade 8 is fixed at the output end of the motor 7; linear drive subassembly 5, vector control subassembly 6 and motor 7 all connect in control system to do corresponding action by control system control, under control system's control promptly, through linear drive effect of linear drive subassembly 5, make vector control subassembly 6, motor 7 and paddle 8 move towards 1 tip extending direction of fuselage, make paddle 8 move predetermined position, the flight finishes, reverse movement, thereby realize the effect that the unmanned aerial vehicle organism shortens.

Specifically, the linear driving assembly 5 is a linear steering engine fixed in the end groove 11, and the linear steering engine is connected with the control system.

The vector control assembly 6 comprises a steering engine base 61, a universal shaft 62, a motor base 63 and a plurality of third linear steering engines 64; the steering engine base 61 is fixed at the driving end of the linear driving component 5 so as to be pushed to move; one end of the universal shaft 62 is connected to the steering engine base 61, the other end of the universal shaft extends towards the notch direction of the end groove 11, the motor base 63 is fixed to the other end of the universal shaft 62, and the motor 7 is fixed to the motor base 63; no. three straight line steering wheel 64 is connected in control system, and a plurality of No. three straight line steering wheel 64 are no less than three to circumference equipartition is in the outside of cardan shaft 62, and the both ends of No. three straight line steering wheel 64 are connected respectively in steering wheel base 61 and motor base 63, utilize control system to a plurality of No. three straight line steering wheel 64's control, make a plurality of No. three straight line steering wheel 64's extension length differ, thereby indirectly make the angle of paddle 8 obtain corresponding change.

When the flight finishes, start through control system control sharp drive assembly 5 for the effect end shrink drives vector control assembly 6 and contracts in end groove 11, and until paddle 8 is close to in fuselage 1, thereby reduce the whole length of unmanned aerial vehicle, improve among the prior art that unmanned aerial vehicle can't carry out the ascending shortening of length direction, have the volume to reduce the relatively limited problem of degree, portable. Through the test, the volume of the container before storage is 0.04m ³ 0.012m after storage ³ . The length before storage is 1m, and the length after storage is 0.5m.

When the unmanned aerial vehicle is used, the unmanned aerial vehicle is placed firstly, the control system controls the fourth linear steering engine 91 to act, and the vertical tail wing 92 extends out and is vertically placed on the ground; then the control system controls the linear driving component 5 to start, so that the action end of the linear driving component 5 extends, and the vector control component 6, the motor 7 and the paddle 8 are pushed out simultaneously until the paddle 8 reaches the working distance; and then the control system controls the blades 8 to rotate, so that the unmanned aerial vehicle vertically takes off. In the flight process, the control system controls the three-line steering engines 64 to stretch out and draw back in different degrees, so that the motor 7 and the blades 8 form state changes of required angles, the change of the flight mode of the unmanned aerial vehicle is completed, the two blades 8, the two wings 3 and the foot stool type empennage 9 are matched, and the flight control of yaw and pitching is completed.

The utility model discloses in, be equipped with protective housing 65 at vector control subassembly 6's outside cover, protective housing 65 is fixed in sharp drive assembly 5 to the one end opening towards paddle 8, in order to form the guard action to vector control subassembly 6.

The utility model discloses in, control system includes executive program such as current PLC controller, singlechip, microprocessor, and the field technician can know how to select control system in the common general knowledge that combines in the field on the basis of this application file is disclosed.

Finally, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the present invention can be modified or replaced by other means without departing from the spirit and scope of the present invention, which should be construed as limited only by the appended claims.

Claims (9)

1. The utility model provides a double-oar unmanned aerial vehicle, includes fuselage (1), control system, sets up in the wing unit of fuselage (1) lateral part and sets up in the rotor unit of fuselage (1), wing unit and rotor unit all are controlled its characterized in that by control system: end slot (11) have all been seted up to the front and back end of fuselage (1), the rotor unit sets up to two and sets up respectively in the front and back end of fuselage (1), the rotor unit is including setting up linear drive subassembly (5), the vector control subassembly (6) that one end was connected in linear drive subassembly (5) drive end in end slot (11), connecting in motor (7) of the vector control subassembly (6) other end and being fixed in paddle (8) of motor (7) output, linear drive subassembly (5), vector control subassembly (6) and motor (7) all are connected with control system, linear drive subassembly (5) are used for driving vector control subassembly (6) business turn over end slot (11).

2. A twin-paddle drone according to claim 1 and characterised in that: the vector control assembly (6) comprises a steering engine base (61) fixed at the driving end of the linear driving assembly (5), a universal shaft (62) with one end connected to the steering engine base (61), a motor base (63) fixed at the other end of the universal shaft (62) and a plurality of three linear steering engines (64) circumferentially and uniformly distributed on the universal shaft (62), the motor (7) is fixedly connected to the motor base (63), two ends of the three linear steering engines (64) are respectively connected to the steering engine base (61) and the motor base (63), and the three linear steering engines (64) are connected to the control system.

3. A twin-paddle drone according to claim 2, characterised in that: the vector control assembly (6) is covered with a protective shell (65) on the outer side, and the protective shell (65) is fixed to the linear driving assembly (5) and is opened towards one end of the paddle (8).

4. A twin-paddle drone according to claim 2, characterised in that: the number of the third linear steering engines (64) is not less than three.

5. A twin-paddle drone according to claim 1, characterised in that: two sides of the middle end of the machine body (1) are provided with side grooves (12); the wing unit is including being fixed in turning to subassembly (2) of side slot (12) bottom, connecting in turning to wing (3) of subassembly (2) tip and setting up in flexible subassembly (4) that turn to subassembly (2), turn to subassembly (2) and flexible subassembly (4) and all connect in control system, flexible subassembly (4) are used for making wing (3) fold in fuselage (1).

6. A twin-paddle unmanned aerial vehicle as claimed in claim 5, wherein: steering component (2) including being fixed in a straight line steering wheel (21) of side slot (12) tank bottom, be fixed in U-shaped seat (22) of a straight line steering wheel (21) effect end, be fixed in rotatory steering wheel (23) of U-shaped seat (22), be fixed in steering wheel connecting rod (24) and one end rotation connection in hinge lever (25) of steering wheel connecting rod (24) of rotatory steering wheel (23) effect end, straight line steering wheel (21) and rotatory steering wheel (23) all connect in control system, just straight line steering wheel (21) are used for making the rotation connecting portion of steering wheel connecting rod (24) and hinge lever (25) stretch out side slot (12), hinge lever (25) fixed connection in wing (3).

7. A twin-paddle drone according to claim 6, characterised in that: the telescopic component (4) comprises a rotating seat (41) fixed on the U-shaped seat (22), a second linear steering engine (42) connected to the control system and a link ring (43) coaxially connected to the hinge rod (25) in a rotating mode, and two ends of the second linear steering engine (42) are respectively connected to the rotating seat (41) and the link ring (43) in a rotating mode so as to drive the wing (3) to be folded in the machine body (1).

8. A twin-paddle drone according to claim 1, characterised in that: wire casing (13) have still been seted up to the middle-end of fuselage (1) to be provided with and be used for judging folding antenna (14) of unmanned aerial vehicle flying height, folding antenna (14) and ground control system equipment signal connection.

9. A twin-paddle drone according to claim 1, characterised in that: fuselage (1) rear end still is provided with foot posture fin (9), foot posture fin (9) include a plurality of No. four straight line steering wheel (91) that are fixed in fuselage (1) and connect in rectilinear steering wheel's (91) a plurality of No. four rectilinear steering wheel's rectilinear fin (92) simultaneously, no. four rectilinear steering wheel (91) are connected in control system, and set up and lie in rectilinear fin (92) in the rotor unit of fuselage (1) rear end.

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