CN209814262U - Fixed wing VTOL unmanned aerial vehicle wing - Google Patents
Fixed wing VTOL unmanned aerial vehicle wing Download PDFInfo
- Publication number
- CN209814262U CN209814262U CN201920153844.8U CN201920153844U CN209814262U CN 209814262 U CN209814262 U CN 209814262U CN 201920153844 U CN201920153844 U CN 201920153844U CN 209814262 U CN209814262 U CN 209814262U
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- pipe clamp
- wing
- fixed
- fixed wing
- pipe
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Abstract
The utility model provides a fixed wing VTOL unmanned aerial vehicle wing, includes fixed wing, carbon pipe, rotor screw mounting and carry subassembly, rotor screw mounting connects in carbon pipe one end, carry the relevant position that the subassembly was fixed on the fixed wing, the carbon pipe passes through the carry subassembly to be fixed on the fixed wing, carry the subassembly and play the effect of fixing the carbon pipe on the fixed wing, the utility model discloses simple structure does not need to dismantle the carbon pipe of fixing on the fixed wing, just can not occupy transporting fixed wing VTOL unmanned aerial vehicle of unnecessary space, simultaneously, the dismantlement and the reinstallation of the carbon pipe of also being convenient for have reduced the transportation, have dismantled the work degree of difficulty when installing and maintaining, and labour saving and time saving has greatly improved work efficiency.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field, concretely relates to fixed wing VTOL unmanned aerial vehicle wing.
Background
Unmanned aerial vehicle is in the domestic development level change day by day, and it has flexible, the reaction is quick, unmanned flight, operation requirement advantage such as low, and fixed wing VTOL unmanned aerial vehicle compromises fixed wing unmanned aerial vehicle's high-speed flight ability, the ability of navigating for a long time and multiaxis unmanned aerial vehicle's VTOL ability, consequently, more and more appear in people's daily life and work.
The existing fixed-wing VTOL unmanned aerial vehicle is roughly divided into three forms: tilting power type, tail seat type and composite wing type. Wherein, the vertical take-off and landing scheme of composite wing is based on conventional fixed wing unmanned aerial vehicle, increase multiaxis power rotor, fly according to the multiaxis mode under vertical take-off and landing and low-speed state, produce ascending pulling force through a plurality of rotor propellers and overcome gravity and aerodynamic drag and fly, its wing part is by connecting on the carbon tube with the solid vertical fixation in conventional fixed wing unmanned aerial vehicle's of a plurality of rotor propellers wing, when transporting unmanned aerial vehicle like this, because the influence of carbon tube length, can occupy very big space, be difficult for the transportation, if dismantle the carbon tube, although can solve the transportation problem, nevertheless install again when needing to dismantle and using, it wastes time and energy to need to use the hand tool, the work efficiency is underneath.
SUMMERY OF THE UTILITY MODEL
The utility model discloses an overcome not enough of above technique, provide a novel fixed wing VTOL unmanned aerial vehicle wing.
The utility model discloses a concrete technical scheme as follows:
the utility model provides a fixed wing VTOL unmanned aerial vehicle wing, includes fixed wing, carbon pipe, rotor screw mounting and carry the subassembly, rotor screw mounting is connected in carbon pipe one end, carry the relevant position that the subassembly was fixed on the fixed wing, the carbon pipe passes through the carry subassembly to be fixed on the fixed wing, carry the subassembly and play the effect of fixing the carbon pipe on the fixed wing.
Preferably, the mounting assembly is composed of a first pipe clamp and a second pipe clamp, and is a clamp type pipe clamp, the first pipe clamp comprises a first pipe clamp base and a first pipe clamp clamping portion, the first pipe clamp base is fixed on the corresponding position of the fixed wing through a screw, and the first pipe clamp base and the first pipe clamp clamping portion are connected through a rotating shaft, so that the first pipe clamp clamping portion can horizontally rotate relative to the base; the second pipe clamp comprises a second pipe clamp base and a second pipe clamp clamping portion, the second pipe clamp base is fixed to the corresponding position of the fixed wing through screws, the second pipe clamp clamping portion is semi-closed, and a carbon tube is fastened in a closed mode through a shoe-shaped bolt at an opening.
Preferably, the first pipe clamp base of the first pipe clamp is provided with a limit position for limiting the rotation angle of the first pipe clamp clamping part, and the limit angle is 90 degrees.
The technical effects of the utility model:
the utility model provides a pair of fixed wing VTOL unmanned aerial vehicle wing, simple structure need not dismantle the carbon pipe of fixing on the fixed wing, just can not occupy the transportation to fixed wing VTOL unmanned aerial vehicle of unnecessary space, simultaneously, the dismantlement and the reinstallation of the carbon pole of also being convenient for have reduced the transportation, have dismantled the work degree of difficulty when installing and maintaining, and labour saving and time saving has greatly improved work efficiency.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic view of the transportation state of the present invention.
Fig. 3 is a schematic structural view of the first pipe clamp of the present invention.
Fig. 4 is a schematic structural view of the second pipe clamp of the present invention.
In the figure: 1. a fixed wing; 2. a carbon tube; 3. a prop-rotor mount; 4. mounting the component; 41. a first pipe clamp; 42. a second pipe clamp; 411. a first pipe clamp base; 412. a first pipe clamp holding portion; 413. limiting; 421. a second pipe clamp base; 422. a second pipe clamp holding portion; 423. shoe-shaped gold ingot bolt.
Detailed Description
The present invention will be further explained with reference to the accompanying drawings.
The utility model provides a fixed wing VTOL unmanned aerial vehicle wing, includes stationary vane 1, carbon pipe 2, rotor propeller mounting 3 and carry subassembly 4, rotor propeller mounting 3 is connected in carbon pipe 2 one end, carry subassembly 4 and fix the relevant position on stationary vane 1, carbon pipe 2 is fixed on stationary vane 1 through carry subassembly 4, carry subassembly 4 and play the effect of fixing carbon pipe 2 on stationary vane 1.
The mounting assembly 4 is composed of a first pipe clamp 41 and a second pipe clamp 42, and is a clamp type pipe clamp, the first pipe clamp 41 includes a first pipe clamp base 411 and a first pipe clamp clamping portion 412, the first pipe clamp base is fixed on the corresponding position of the fixed wing 1 by screws, and the first pipe clamp base and the first pipe clamp clamping portion are connected by a rotating shaft, so that the first pipe clamp clamping portion can horizontally rotate relative to the first pipe clamp base.
The second pipe clamp 42 includes a second pipe clamp base 421 fixed on the corresponding position of the fixed wing 1 by a screw, and a second pipe clamp clamping portion 422 in a semi-closed shape, and an opening is closed by a gold-ingot bolt 423 to fasten the carbon tube 2.
The base 411 of the first pipe clamp 41 is provided with a limit 413 for limiting the rotation angle of the clamping part 422, and the limit angle is 90 degrees.
Example 1
Before the fixed wing vertical take-off and landing unmanned aerial vehicle is transported, a first steel-ingot bolt for fastening a carbon tube on a second tube clamping part is loosened, the axis of the carbon tube is taken as an axis, the carbon tube is rotated by 180 degrees to drive a rotor propeller to change from upward to downward, the first tube clamp clamping part can rotate, then a part of the carbon tube fastened by a second tube clamp is moved out from the opening edge of the second tube clamping part, the rotating shaft of the first tube clamp is taken as the axis and rotates by 90 degrees, at the moment, the carbon tube and the fixed wing are in a relatively parallel angle from a mutually vertical angle, the problem of transportation difficulty caused by occupation of redundant space due to vertical installation of the carbon tube and the fixed wing can be avoided, when the unmanned aerial vehicle needs to be reused, the carbon tube only needs to rotate by 90 degrees in a rotating direction, enters the second tube clamping part from the opening, and then the axis of the carbon tube is taken as the axis and rotates by 180 degrees to drive the rotor, the carbon tube is thoroughly fastened again by screwing up the shoe-shaped gold ingot screw, and the wing is restored to a normal working and using state.
Example 2
The first pipe clamp base 411 of the first pipe clamp 41 is provided with a limit 413 for limiting the rotation angle of the first pipe clamp clamping part 422, and the limit angle is 90 degrees, so that when the wing is changed from a normal working and using state to a state convenient for transportation, the rotation of the carbon tube is limited to 90 degrees, and the problem caused by the fact that the carbon tube and the propeller exceed the range of the fixed wing again due to the fact that the rotation angle exceeds is avoided.
The utility model provides a pair of fixed wing VTOL unmanned aerial vehicle wing, simple structure need not dismantle the carbon pipe of fixing on the fixed wing, just can not occupy the transportation to fixed wing VTOL unmanned aerial vehicle of unnecessary space, simultaneously, the dismantlement and the reinstallation of the carbon pole of also being convenient for have reduced the transportation, have dismantled the work degree of difficulty when installing and maintaining, and labour saving and time saving has greatly improved work efficiency. It should be noted that the above-mentioned preferred embodiments are only for illustrating the technical concepts and features of the present invention, and the purpose thereof is to enable those skilled in the art to understand the contents of the present invention and to implement the present invention accordingly, and the protection scope of the present invention cannot be limited thereby. All equivalent changes and modifications made according to the spirit of the present invention should be covered by the protection scope of the present invention.
Claims (3)
1. The utility model provides a fixed wing VTOL unmanned aerial vehicle wing which characterized in that: including stationary vane, carbon pipe, rotor screw mounting and carry subassembly, rotor screw mounting is connected in carbon pipe one end, carry the relevant position that the subassembly was fixed on the stationary vane, the carbon pipe passes through the carry subassembly to be fixed on the stationary vane, carry the subassembly and play the effect of fixing the carbon pipe on the stationary vane.
2. The wing of a fixed-wing VTOL UAV of claim 1, wherein: the mounting assembly is composed of a first pipe clamp and a second pipe clamp and is a clamp type pipe clamp, the first pipe clamp comprises a first pipe clamp base and a first pipe clamp clamping portion, the first pipe clamp base is fixed on the corresponding position of the fixed wing through a screw, and the first pipe clamp base and the first pipe clamp clamping portion are connected through a rotating shaft, so that the first pipe clamp clamping portion can horizontally rotate relative to the first pipe clamp base; the second pipe clamp comprises a second pipe clamp base and a second pipe clamp clamping portion, the second pipe clamp base is fixed to the corresponding position of the fixed wing through screws, the second pipe clamp clamping portion is semi-closed, and a carbon tube is fastened in a closed mode through a shoe-shaped bolt at an opening.
3. A fixed wing vtol drone wing according to claim 2, characterized in that: the base of the first pipe clamp is provided with a limit for limiting the rotation angle of the clamping part, and the limit angle is 90 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920153844.8U CN209814262U (en) | 2019-01-29 | 2019-01-29 | Fixed wing VTOL unmanned aerial vehicle wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920153844.8U CN209814262U (en) | 2019-01-29 | 2019-01-29 | Fixed wing VTOL unmanned aerial vehicle wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209814262U true CN209814262U (en) | 2019-12-20 |
Family
ID=68872376
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920153844.8U Expired - Fee Related CN209814262U (en) | 2019-01-29 | 2019-01-29 | Fixed wing VTOL unmanned aerial vehicle wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209814262U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022121444A1 (en) * | 2020-12-11 | 2022-06-16 | 上海法兰曼航空服务有限公司 | Hybrid light manned aircraft having fixed wings and rotor wings, and aircraft |
-
2019
- 2019-01-29 CN CN201920153844.8U patent/CN209814262U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022121444A1 (en) * | 2020-12-11 | 2022-06-16 | 上海法兰曼航空服务有限公司 | Hybrid light manned aircraft having fixed wings and rotor wings, and aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210811 Address after: 150001 No. 2, floor 9, unit 13, No. 1055, Changjiang Road, Daowai District, Harbin, Heilongjiang Province Patentee after: Heilongjiang Yulong Aviation Technology Co.,Ltd. Address before: 150001 UAV business department, 5 / F, building 13, advertising industrial park, 469 Xianfeng Road, Nangang District, Harbin, Heilongjiang Province Patentee before: Harbin Bit Model Technology Development Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191220 Termination date: 20220129 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |