CN214729611U

CN214729611U - Folding fixed wing unmanned aerial vehicle that can take off and land perpendicularly

Info

Publication number: CN214729611U
Application number: CN202121018303.8U
Authority: CN
Inventors: 王旭; 龙之清; 张校
Original assignee: Chengdu Aeronautic Polytechnic
Current assignee: Chengdu Aeronautic Polytechnic
Priority date: 2021-05-13
Filing date: 2021-05-13
Publication date: 2021-11-16
Anticipated expiration: 2031-05-13

Abstract

The utility model discloses a but folding fixed wing unmanned aerial vehicle of VTOL, including the fuselage with establish first wing and the second wing in the fuselage both sides, the first wing trailing edge outside and the second wing trailing edge outside respectively are equipped with two ailerons, and department symmetric connection has first rotor mechanism and second rotor mechanism in the middle of the fuselage both sides, and both ends symmetry is equipped with third rotor mechanism and fourth rotor mechanism around the fuselage. The scheme adopts a mode of combining the advantages of the fixed-wing unmanned aerial vehicle and the rotor unmanned aerial vehicle, designs the folding fixed-wing unmanned aerial vehicle capable of taking off and landing vertically, and solves the problems that the fixed-wing unmanned aerial vehicle cannot take off and land vertically and the cruise time of the rotor unmanned aerial vehicle is short in the prior art; the utility model discloses an unmanned aerial vehicle both possesses rotor unmanned aerial vehicle can the VTOL, advantages such as control accuracy height, also possesses fixed wing unmanned aerial vehicle cruise time long, lift-drag ratio advantage such as big.

Description

Folding fixed wing unmanned aerial vehicle that can take off and land perpendicularly

Technical Field

The utility model relates to an unmanned aerial vehicle field, concretely relates to but folding fixed wing unmanned aerial vehicle of VTOL.

Background

The fixed-wing unmanned aerial vehicle is widely applied to the military field due to large lift-drag ratio, high efficiency and long cruising time; the rotor unmanned aerial vehicle has the characteristics of capability of taking off and landing vertically, accurate control, no geographic limitation and the like, and is widely applied to the civil field. However, both of these drones have significant disadvantages, the fixed wing drone cannot take off and land vertically, and the rotor drone has short cruising time, which all limit the further development and application of both drones.

SUMMERY OF THE UTILITY MODEL

Not enough to the above among the prior art, the utility model provides a but folding fixed wing unmanned aerial vehicle of VTOL to solve the unable VTOL of fixed wing unmanned aerial vehicle among the prior art, the problem that rotor unmanned aerial vehicle cruise time is short.

In order to solve the technical problem, the utility model discloses a technical scheme does:

the utility model provides a but folding fixed wing unmanned aerial vehicle of VTOL, includes the fuselage and establishes first wing and the second wing in the fuselage both sides, and the first wing trailing edge outside and the second wing trailing edge outside respectively are equipped with two ailerons, and the department symmetric connection has first rotor mechanism and second rotor mechanism in the middle of the fuselage both sides, and both ends symmetry is equipped with third rotor mechanism and fourth rotor mechanism around the fuselage.

Furthermore, one end of the first wing is connected to the front end of the fuselage, and one end of the second wing is connected to the rear end of the fuselage.

Furthermore, the first wing is movably connected to the front end of the upper side of the airplane body through a first rotating shaft, and the second wing is movably connected to the rear end of the lower side of the airplane body through a second rotating shaft.

Further, the first rotor mechanism includes a first link; one end of the first connecting rod is movably connected to the side face of the machine body through a fifth rotating shaft, and the other end of the first connecting rod is fixedly provided with a first motor; a rotating shaft of the first motor is provided with a first rotor wing; the second rotor mechanism comprises a second connecting rod; one end of the second connecting rod is movably connected to the side face of the machine body through a sixth rotating shaft, a second motor is fixedly arranged at the other end of the second connecting rod, and a second rotor wing is installed on a rotating shaft of the second motor.

Further, third rotor mechanism includes the third rotor, and the third rotor is installed in the pivot of third motor, and the third motor passes through third pivot swing joint in fuselage front end, and fourth rotor mechanism includes the fourth rotor, and the fourth rotor is installed in the pivot of fourth motor, and the fourth motor passes through fourth pivot swing joint in fuselage rear end.

Furthermore, the third rotating shaft is positioned in front of the first rotating shaft, and the fourth rotating shaft is positioned behind the second rotating shaft.

Further, first rotor and second rotor size structure are all the same, and third rotor and fourth rotor size structure are all the same.

The utility model has the advantages that: the scheme combines the advantages of the fixed-wing unmanned aerial vehicle and the rotor unmanned aerial vehicle, designs the folding fixed-wing unmanned aerial vehicle capable of taking off and landing vertically, and solves the problems that the fixed-wing unmanned aerial vehicle cannot take off and land vertically and the rotor unmanned aerial vehicle has short cruising time in the prior art; the utility model discloses an unmanned aerial vehicle both possesses rotor unmanned aerial vehicle can the VTOL, advantages such as control accuracy height, also possesses fixed wing unmanned aerial vehicle cruise time long, lift-drag ratio advantage such as big.

Drawings

Fig. 1 is the overall structure schematic diagram of the unmanned aerial vehicle that this application provided.

Fig. 2 schematically shows a top view of the drone in fig. 1.

Figure 3 schematically shows a side view of the drone in figure 1.

Fig. 4 is the overall structure schematic diagram of unmanned aerial vehicle fold condition that this application provided.

Wherein, 1, a machine body; 21. a first airfoil; 22. a second airfoil; 31. a first rotor; 32. a second rotor; 33. a third rotor; 34. a fourth rotor; 41. a first motor; 42. a second motor; 43. A third motor; 44. a fourth motor; 51. a first link; 52. a second link; 61. a first rotating shaft; 62. a second rotating shaft; 63. a third rotating shaft; 64. a fourth rotating shaft; 65. a fifth rotating shaft; 66. and a sixth rotating shaft.

Detailed Description

The principles and features of the present invention are described below in conjunction with the following drawings, the examples given are only intended to illustrate the present invention and are not intended to limit the scope of the present invention.

In this application, the place ahead of fuselage front end department when unmanned aerial vehicle flies, the great one side of wing upper surface crookedness is the place ahead, during the use, observes the cross sectional shape of wing and can distinguish.

As shown in fig. 1 to 3, but the folding fixed wing unmanned aerial vehicle of VTOL that this scheme provided includes fuselage 1, in implementation, can be through the upside front end of first pivot 61 with first wing 21 swing joint at fuselage 1, through the downside rear end of second pivot 62 with second wing 22 swing joint at fuselage 1, after the wing sets up asymmetric structure, can conveniently fold, when using the wing, it is perpendicular to with the fuselage to rotate the wing, when not using the wing, can fold the wing, high durability and convenient use, save space, the wing of setting can provide lift for unmanned aerial vehicle when unmanned aerial vehicle flies, improve unmanned aerial vehicle's duration. Two ailerons can be respectively arranged on the outer side of the trailing edge of the first wing 21 and the outer side of the trailing edge of the second wing 22, and the ailerons can be operated to turn the unmanned aerial vehicle or make roll maneuver. In addition, can locate first rotor mechanism of symmetric connection and second rotor mechanism in the middle of 1 both sides of fuselage, both ends symmetry sets up third rotor mechanism and fourth rotor mechanism around fuselage 1, and the rotor mechanism of setting provides power for unmanned aerial vehicle, can let unmanned aerial vehicle realize the VTOL and improve the accurate control to unmanned aerial vehicle.

In implementation, one end of a first link 51 belonging to the first rotor mechanism may be movably connected to the middle of one side of the fuselage 1 through a fifth rotating shaft 65, and the other end of the first link 51 is fixedly provided with a first motor 41; a first rotor 31 is installed on a rotating shaft of the first motor 41; one end of a second link 52 belonging to the second rotor mechanism may be movably connected to the middle of the other side of the fuselage 1 through a sixth rotating shaft 66, a second motor 42 is fixedly disposed at the other end of the second link 52, and a second rotor 32 is mounted on the rotating shaft of the second motor 42.

In practice, the third rotor 33 belonging to the third rotor mechanism may be installed on the rotating shaft of the third motor 43, the third motor 43 may be movably connected to the front end of the fuselage 1 through the third rotating shaft 63, the fourth rotor 34 belonging to the fourth rotor mechanism may be installed on the rotating shaft of the fourth motor 44, and the fourth motor 44 may be movably connected to the rear end of the fuselage 1 through the fourth rotating shaft 64.

In practice, the third rotating shaft 63 is located in front of the first rotating shaft 61, and the fourth rotating shaft 64 is located behind the second rotating shaft 62. Make first rotor 31 and second rotor 32 size structure homogeneous phase the same, make third rotor 33 and the homogeneous phase of the 34 size structure of fourth rotor the same, improve unmanned aerial vehicle flight smoothness.

Unmanned aerial vehicle in this embodiment mainly has three kinds of states, and first state is fold condition, as shown in fig. 4, at this moment, first wing 21 and second wing 22 rotate respectively around first pivot 61 and second pivot 62 to the position of coinciding with fuselage 1, and first rotor mechanism and second rotor mechanism rotate respectively around fifth pivot 65 and sixth pivot 66 to the position parallel with the fuselage, and when fold condition, unmanned aerial vehicle occupies minimum space, conveniently carries and transports.

The second state is a vertical take-off and landing state, in this state, the first wing 21 and the second wing 22 rotate to the position perpendicular to the fuselage 1 around the first rotating shaft 61 and the second rotating shaft 62, respectively, and the third motor 43 and the fourth motor 44 rotate to the position where the motor axis is perpendicular to the upper surface of the fuselage 1 around the third rotating shaft 63 and the fourth rotating shaft 64, respectively, and at this time, when the four rotors rotate simultaneously, the maximum lift force is provided for the unmanned aerial vehicle.

The third state is a flat flight state of the unmanned aerial vehicle, in this state, the first wing 21 and the second wing 22 continue to be unfolded and keep perpendicular to the fuselage, the third motor 43 and the fourth motor 44 rotate around the third rotating shaft 63 and the fourth rotating shaft 64 respectively to a position where the motor axes are parallel to the fuselage 1, wherein the third rotor 33 driven by the third motor 43 provides forward pulling force for the unmanned aerial vehicle, the fourth rotor 34 driven by the fourth motor 44 provides forward pushing force for the unmanned aerial vehicle, and the first rotor 31, the second rotor 32 and the two wings maintain the lift force of the unmanned aerial vehicle for keeping the height.

The above description is only for the preferred embodiment of the present invention, and is not intended to limit the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included within the protection scope of the present invention.

Claims

1. The utility model provides a but folding fixed wing unmanned aerial vehicle of VTOL, its characterized in that includes fuselage (1) and establishes first wing (21) and second wing (22) of fuselage (1) both sides, first wing (21) trailing edge outside with second wing (22) trailing edge outside respectively is equipped with two ailerons, department symmetric connection has first rotor mechanism and second rotor mechanism in the middle of fuselage (1) both sides, both ends symmetry is equipped with third rotor mechanism and fourth rotor mechanism around fuselage (1).

2. The VTOL foldable fixed wing UAV according to claim 1, wherein the first wing (21) is connected to the front end of the fuselage at one end, and the second wing (22) is connected to the rear end of the fuselage at one end.

3. The VTOL folding fixed wing UAV (unmanned aerial vehicle) of claim 2, wherein the first wing (21) is movably connected to the front end of the upper side of the fuselage (1) through a first rotating shaft (61), and the second wing (22) is movably connected to the rear end of the lower side of the fuselage (1) through a second rotating shaft (62).

4. A VTOL foldable fixed-wing drone according to claim 3, characterized in that the first rotor mechanism comprises a first link (51); one end of the first connecting rod (51) is movably connected to the side face of the machine body (1) through a fifth rotating shaft (65), and the other end of the first connecting rod (51) is fixedly provided with a first motor (41); a first rotor (31) is arranged on a rotating shaft of the first motor (41); the second rotor mechanism includes a second link (52); second connecting rod (52) one end is in through sixth pivot (66) swing joint fuselage (1) side, fixed second motor (42) that are equipped with on second connecting rod (52) the other end, install second rotor (32) in the pivot of second motor (42).

5. The VTOL folding fixed wing UAV of claim 4, wherein the third rotor mechanism comprises a third rotor (33), the third rotor (33) is installed on a rotating shaft of a third motor (43), the third motor (43) is movably connected to the front end of the airframe (1) through a third rotating shaft (63), the fourth rotor mechanism comprises a fourth rotor (34), the fourth rotor (34) is installed on a rotating shaft of a fourth motor (44), and the fourth motor (44) is movably connected to the rear end of the airframe (1) through a fourth rotating shaft (64).

6. A VTOL foldable fixed wing drone according to claim 5, characterized in that the third rotation shaft (63) is located in front of the first rotation shaft (61) and the fourth rotation shaft (64) is located behind the second rotation shaft (62).

7. A VTOL foldable fixed-wing drone according to claim 6, characterized in that the first rotor (31) and the second rotor (32) are all the same size structure, the third rotor (33) and the fourth rotor (34) are all the same size structure.