CN218877558U - Wind-resistant unmanned aerial vehicle - Google Patents
Wind-resistant unmanned aerial vehicle Download PDFInfo
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- CN218877558U CN218877558U CN202222885281.6U CN202222885281U CN218877558U CN 218877558 U CN218877558 U CN 218877558U CN 202222885281 U CN202222885281 U CN 202222885281U CN 218877558 U CN218877558 U CN 218877558U
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- 230000000087 stabilizing effect Effects 0.000 claims abstract description 23
- 238000009434 installation Methods 0.000 claims abstract description 12
- 239000003381 stabilizer Substances 0.000 claims abstract description 12
- 230000001105 regulatory effect Effects 0.000 claims description 9
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 230000001174 ascending effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002146 bilateral effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
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Abstract
The utility model provides an anti-wind unmanned aerial vehicle, including fuselage and wing, the wing sets up in the fuselage middle section, the fuselage rear end is provided with the propulsion rotor, be provided with motor power in the fuselage, motor power's pivot with impel the rotor and be connected, impel the rotor through motor power drive and rotate, the wing sets up respectively in the fuselage both sides, wing middle part lower extreme is provided with the stabilizer bar, the both ends of stabilizer bar are provided with stabilizing motor, stabilizing motor sets up downwards and is provided with stabilizing rotor in the pivot, stabilizing rotor slope installation, be provided with the battery in the fuselage. Through the installation angle that changes 4 rotors, certain angle of internal inclination for the lift that 4 rotors produced has certain contained angle with the horizontal plane, and a component can be decomposed out at the horizontal direction to the lift this moment, only needs less anti-wind appearance angle just can resist the environment wind speed, and then promotes control response speed, promotes the anti-wind ability, reinforcing flight stability and security.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle field especially relates to an anti-wind unmanned aerial vehicle.
Background
At present in the unmanned aerial vehicle field, unmanned aerial vehicle uses the mode of VTOL to take off mostly, and the flight mode is comparatively single, and VTOL fixed wing unmanned aerial vehicle is taking off perpendicularly and the vertical landing in-process in the industry of present, and wind resistance ability is relatively poor, has following several disadvantages under certain environment wind speed condition: 1. the wind-resistant flight attitude is too large; 2. the wind-resistant flight stability is poor; 3. poor wind resistance (wind resistance 4 grade wind); 4. the wind-resistant flight safety is low; 5. the adaptability to wind environment is poor. Patent 2019100930982 as already published provides a tilt rotor unmanned aerial vehicle, wherein a technical scheme of mounting rotors on wings is disclosed, but in the scheme, the mounting angle of the rotors is vertical to the horizontal plane during takeoff, the mounting angle becomes horizontal during flying, an inward inclination design of the rotors is not disclosed, the wind resistance performance is poor during lifting, a larger wind resistance posture angle is needed to be used for replacing stability, the safety is not high, and flight accidents are easy to occur. Therefore, the problem that the wind-resistant flying stability of the existing unmanned aerial vehicle is not high is solved.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an anti-wind unmanned aerial vehicle, through the angle of installation that changes 4 rotors, the certain angle of introversion, make the lift that 4 rotors produced have certain contained angle with the horizontal plane, lift can break out a component at the horizontal direction this moment, horizontal wind speed in the partial environment can be resisted to this horizontal component, simultaneously in anti-wind attitude control, only need less anti-wind attitude angle just can resist the ambient wind speed, and then promote control response speed, promote anti-wind ability, reinforcing flight stability and security.
The utility model provides an anti-wind unmanned aerial vehicle, including fuselage and wing, the wing sets up in the fuselage middle section, the fuselage rear end is provided with the propulsion rotor, be provided with motor power in the fuselage, motor power's pivot with impel the rotor and be connected, impel the rotor through motor power drive and rotate, the wing sets up respectively in the fuselage both sides, wing middle part lower extreme is provided with the stabilizer bar, the both ends of stabilizer bar are provided with stabilizing motor, stabilizing motor sets up downwards and is provided with stabilizing rotor in the pivot, stabilizing rotor slope installation, be provided with the battery in the fuselage.
The further improvement is that: the stabilizer bar rear end is provided with the rotation interface, it has auxiliary support rod to spin on the rotation interface, the last auxiliary fin that is provided with of auxiliary support rod.
The further improvement is that: all be provided with the regulating plate on wing and the supplementary fin, the regulating plate bears the weight of wing body coupling rather than through the pivot, adjusts the windage of wing and supplementary fin through the angle of adjustment regulating plate.
The further improvement lies in that: the installation angle of the stable rotor wing is inwards inclined 3~6 degrees, and the installation angle is the included angle between the plane of the paddle disc and the horizontal plane.
The working principle is as follows: when unmanned aerial vehicle takes off, stabilize the motor and begin work after receiving the signal of taking off, drive and stabilize the rotor and rotate, produce lift and drive the fuselage and take off to because when stabilizing rotor and horizontal plane and have certain installation angle, the lift line of left side rotor lift and right side rotor lift becomes a triangle-shaped, under this state, the holistic stability enhancement of handling of unmanned aerial vehicle. Impel the rotor after reaching the prediction height and begin work, drive unmanned aerial vehicle and move forward, and the same reason progressively weakens the output who stabilizes the rotor during descending, and the fuselage slowly falls down under the effect of gravity.
The utility model discloses beneficial effect: 1. the wind resistance of the unmanned aerial vehicle in the vertical take-off and landing process is improved; 2. the wind resistance control response speed is improved; 3. the flight attitude angle in the wind resisting process is reduced; 4. the safety of the unmanned aerial vehicle in the vertical take-off and landing process is improved; 5. the flight stability of the unmanned aerial vehicle in the process of high air speed in the flight environment is improved; 6. the environmental suitability of the unmanned aerial vehicle is enhanced.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Figure 2 is the utility model discloses a stabilize rotor lift schematic diagram.
Figure 3 is the utility model discloses a stabilize rotor installation angle force diagram.
Wherein: 1-a fuselage, 2-wings, 3-a propelling rotor wing, 4-a stabilizer bar, 5-a stabilizing motor, 6-a stabilizing rotor wing, 7-a rotating interface, 8-an auxiliary support rod, 9-an auxiliary empennage and 10-an adjusting plate.
Detailed Description
In order to deepen the understanding of the present invention, the present invention will be described in detail with reference to the following embodiments, which are only used to explain the present invention, and do not constitute limitations to the scope of the present invention.
As shown in fig. 1, this embodiment provides an anti-wind unmanned aerial vehicle, including fuselage 1 and wing 2, wing 2 sets up in 1 middle section of fuselage, 1 rear end of fuselage is provided with propulsion rotor 3, be provided with motor power in the fuselage 1, motor power's pivot is connected with propulsion rotor 3, drives through motor power and impels rotor 3 and rotate, wing 2 sets up respectively in 1 both sides of fuselage, 2 middle part lower extremes of wing are provided with stabilizer bar 4, the both ends of stabilizer bar 4 are provided with stabilizing motor 5, stabilizing motor 5 sets up and is provided with in the pivot and stabilizes rotor 6, the installation of 6 slopes of stabilizing rotor, and four stabilizing rotor 6 work produce ascending lift, take off and descend for the fixed wing unmanned aerial vehicle that hangs down and provide lift. A storage battery is arranged in the machine body 1. The stabilizer bar 4 rear end is provided with rotary joint 7, it has auxiliary support rod 8 to spin on rotary joint 7, be provided with supplementary fin 9 on the auxiliary support rod 8. All be provided with regulating plate 10 on wing 2 and the supplementary fin 9, regulating plate 10 bears the weight of the wing body coupling rather than through the pivot, adjusts wing 2 and the windage of supplementary fin 9 through the angle of adjustment regulating plate 10.
As shown in fig. 2, when the stabilizing rotor 6 has a certain mounting angle with the horizontal plane, the lift lines of the left stabilizing rotor 6 and the right stabilizing rotor 6 form a triangle, and in this state, the overall acceptance stability of the unmanned aerial vehicle is enhanced.
As shown in fig. 3, when the stabilizing rotor 6 has a certain mounting angle with the horizontal plane, the lift force of the stabilizing rotor 6 (the upward lift force generated by the rotor) generates two components in the vertical and horizontal plane directions: hovering lift (providing vertical upward lift for the unmanned aerial vehicle) and lateral component forces (due to bilateral symmetry of the four rotors, the lateral component forces generated by the four rotors cancel each other out in a windless environment). When the environment horizontal wind speed exists, the four stable rotor wings 6 adjust the lateral component force through rotating speed adjustment, and then part of wind power is offset. Meanwhile, due to the existence of lateral force, the attitude control response is quicker.
Through actual test experience, stabilize 6 erection angles of rotor between 3 degrees ~6 degrees, it is more effective to the promotion of holistic anti-wind ability, gesture stability, suitable erection angle can be chooseed for use to different models.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited thereto, and various changes can be made without departing from the gist of the present invention within the scope of knowledge possessed by those skilled in the art.
Claims (4)
1. The utility model provides an anti-wind unmanned aerial vehicle, includes fuselage (1) and wing (2), wing (2) set up in fuselage (1) middle section, fuselage (1) rear end is provided with and impels rotor (3), be provided with motor power in fuselage (1), motor power's pivot with impel rotor (3) and be connected, impel rotor (3) to rotate through motor power drive, wing (2) set up respectively in fuselage (1) both sides, its characterized in that: wing (2) middle part lower extreme is provided with stabilizer bar (4), the both ends of stabilizer bar (4) are provided with stabilizing motor (5), stabilizing motor (5) set up downwards and are provided with in the pivot and stabilize rotor (6), stabilize rotor (6) slope installation, be provided with the battery in fuselage (1).
2. A wind-resistant drone according to claim 1, characterised in that: stabilizer bar (4) rear end is provided with rotary joint (7), rotary joint (7) top spin has connect auxiliary stay pole (8), be provided with auxiliary fin (9) on auxiliary stay pole (8).
3. A wind-resistant drone according to claim 2, characterised in that: all be provided with regulating plate (10) on wing (2) and supplementary fin (9), regulating plate (10) bear the weight of the wing body coupling rather than through the pivot, adjust the windage of wing (2) and supplementary fin (9) through the angle of adjustment regulating plate (10).
4. The wind-resistant drone of claim 1, wherein: the installation angle of the stabilizing rotor wing (6) is inward inclined by 3~6 degrees, and the installation angle is the included angle between the plane of the paddle disk and the horizontal plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222885281.6U CN218877558U (en) | 2022-10-31 | 2022-10-31 | Wind-resistant unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222885281.6U CN218877558U (en) | 2022-10-31 | 2022-10-31 | Wind-resistant unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218877558U true CN218877558U (en) | 2023-04-18 |
Family
ID=85938605
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222885281.6U Active CN218877558U (en) | 2022-10-31 | 2022-10-31 | Wind-resistant unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218877558U (en) |
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2022
- 2022-10-31 CN CN202222885281.6U patent/CN218877558U/en active Active
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