CN214930562U - Vertical take-off and landing unmanned aerial vehicle rotor pole folding arm structure - Google Patents
Vertical take-off and landing unmanned aerial vehicle rotor pole folding arm structure Download PDFInfo
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- CN214930562U CN214930562U CN202121648664.0U CN202121648664U CN214930562U CN 214930562 U CN214930562 U CN 214930562U CN 202121648664 U CN202121648664 U CN 202121648664U CN 214930562 U CN214930562 U CN 214930562U
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- arm structure
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Abstract
The utility model discloses a VTOL unmanned aerial vehicle rotor pole folding arm structure, include the first sleeve of being connected with first rotor pole, be connected with the second rotor pole and rotate the second sleeve of being connected with first sleeve, the first fixed block of being connected with first sleeve, be connected with the second sleeve and make first sleeve and second sleeve keep fixed locking bolt with being used for when the closure state with first fixed block complex second fixed block and second sleeve, first fixed block has lets locking bolt male first locking hole, the second fixed block has lets locking bolt male second locking hole, first sleeve and the telescopic material of second are the aluminum alloy. The utility model discloses a VTOL unmanned aerial vehicle rotor pole folding arm structure can promote fatigue, the corrosion resisting property of structure, increases life.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle, specifically speaking, the utility model relates to a VTOL unmanned aerial vehicle rotor pole folding arm structure.
Background
With the rapid development of the unmanned aerial vehicle, the functions of the unmanned aerial vehicle are more and more diversified. Vertical take-off and landing drones that do not rely on airports are gaining more attention with their convenience, safety and reliability characteristics. Through investigation, the folding structure of the rotor wing rod of the unmanned aerial vehicle is complex in the market, the manufacturing difficulty is high, the machining precision cannot be guaranteed, and the folding mechanism is not compact in motion and the aircraft does not stably move when the rotor wing rod is unfolded for work; because the folding mechanism is complex, small round corners, sharp corners and other fine characteristics can generate stress concentration points, and fatigue cracking is easy to generate in a stress environment, so that the working efficiency and the use reliability are reduced; as more gaps exist due to excessive components, the environment with the corrosion factors gathered is easier to form, and in addition, the corrosion resistance of the structural material is poor, so that the structural material is easy to corrode in a complex natural environment.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, the utility model provides a VTOL unmanned aerial vehicle rotor pole folding arm structure, the purpose improves life.
In order to realize the purpose, the utility model discloses the technical scheme who takes does: VTOL unmanned aerial vehicle rotor pole folding arm structure, include the first sleeve of being connected with first rotor pole, be connected with the second rotor pole and rotate the second sleeve of being connected with first sleeve, the first fixed block of being connected with first sleeve, be connected with the second sleeve and with first fixed block complex second fixed block and be used for making first sleeve and second sleeve keep fixed locking bolt when the closure state, first fixed block has lets locking bolt male first locking hole, the second fixed block has lets locking bolt male second locking hole, first sleeve and the telescopic material of second are the aluminum alloy.
The first fixing block is provided with an accommodating groove for the second fixing block to be embedded in, the first sleeve is rotatably connected with the second sleeve through a hinge pin, and the hinge pin and the first fixing block are oppositely arranged.
The hinge pin is made of stainless steel.
The locking bolt is a steel ball bolt.
The first fixed block is made of the same material as the first sleeve, and the first fixed block and the first sleeve are integrally formed.
The second fixed block is made of the same material as the second sleeve, and the second fixed block and the second sleeve are integrally formed.
The utility model discloses a VTOL unmanned aerial vehicle rotor pole folding arm structure can promote fatigue, the corrosion resisting property of structure, increases life.
Drawings
The description includes the following figures, the contents shown are respectively:
fig. 1 is a schematic view of a folding arm structure of a rotor rod of a vertical take-off and landing unmanned aerial vehicle in a closed state;
fig. 2 is a schematic view of the rotor rod folding arm structure of the vertical take-off and landing unmanned aerial vehicle of the present invention in an open state;
figure 3 is a schematic view of the rotor mast in the deployed state;
figure 4 is a schematic view of the rotor mast in a collapsed state;
labeled as: 1. a first sleeve; 2. a second sleeve; 3. a first fixed block; 4. a second fixed block; 5. a first rotor bar; 6. a second rotor bar; 7. a hinge pin; 8. and locking the bolt.
Detailed Description
The following detailed description of the embodiments of the present invention will be given with reference to the accompanying drawings, for the purpose of helping those skilled in the art to understand more completely, accurately and deeply the conception and technical solution of the present invention, and to facilitate its implementation.
It should be noted that, in the following embodiments, the "first" and "second" do not represent an absolute distinction relationship in structure and/or function, nor represent a sequential execution order, but merely for convenience of description.
As shown in fig. 1 to 4, the utility model provides a VTOL unmanned aerial vehicle rotor pole folding arm structure, include the first sleeve 1 of being connected with first rotor pole 5, be connected with second rotor pole 6 and rotate the second sleeve 2 of being connected with first sleeve 1, the first fixed block 3 of being connected with first sleeve 1, be connected with second sleeve 2 and with first fixed block 3 complex second fixed block 4 and be used for making first sleeve 1 and second sleeve 2 keep fixed locking bolt 8 when closed state, first fixed block 3 has and lets locking bolt 8 male first locking hole, second fixed block 4 has and lets locking bolt 8 male second locking hole, the material of first sleeve 1 and second sleeve 2 is the aluminum alloy.
Specifically, as shown in fig. 1 to 4, a first sleeve 1 is fixedly connected to one end of a first rotor rod 5 in the length direction, a second sleeve 2 is fixedly connected to one end of a second rotor rod 6 in the length direction, the first sleeve 1 and the second sleeve 2 are both cylinders with hollow interiors, the first sleeve 1 is rotatably connected to the second sleeve 2 through a hinge pin 7, a first fixing block 3 is fixedly connected to the first sleeve 1, the first fixing block 3 is located outside the first sleeve 1, the second fixing block 4 is fixedly connected to the second sleeve 2, the second fixing block 4 is located outside the second sleeve 2, the hinge pin 7 and the first fixing block 3 are arranged oppositely, and the hinge pin 7 and the first fixing block 3 are located on opposite sides of the first sleeve 1. The first fixing block 3 is provided with a containing groove for the second fixing block 4 to be embedded in, and the shape of the containing groove is matched with that of the second fixing block 4.
As shown in fig. 1 to 4, in this embodiment, the length of the first fixing block 3 is greater than the length of the second fixing block 4, the second fixing block 4 is a rectangular block structure, the receiving groove is a rectangular groove disposed on a side surface of the first fixing block 3, the first locking hole is a through hole penetrating the first fixing block 3 along the length direction of the first fixing block 3, the length direction of the first locking hole is spatially perpendicular to the axis of the first sleeve 1, the second locking hole is a through hole penetrating the second fixing block 4 along the length direction of the second fixing block 4, and the length direction of the second locking hole is spatially perpendicular to the axis of the second sleeve 2. When folding arm was in the closure state, first sleeve 1 and second sleeve 2 were in coaxial state, and in the storage tank of first fixed block 3 was embedded to second fixed block 4, first locking hole and second locking hole intercommunication just were in coaxial state, and locking bolt 8 inserts simultaneously in first locking hole and the second locking hole, realizes first sleeve 1 and second sleeve 2's relatively fixed, and the rotor pole is in the state of expanding. After the locking bolt 8 is drawn out of the first locking hole and the second locking hole, the first sleeve 1 and the second sleeve 2 can rotate relatively, and then the folding arm can be switched from a closed state to an open state, so that the folding of the rotor rod is realized. Therefore, the two sleeves are driven to rotate, and the rotor wing rod is unfolded or folded.
In this embodiment, the hinge pin 7 is made of stainless steel, and the sleeves are rotatably connected through pin holes reserved in the first sleeve 1 and the second sleeve 2, and the rotor rod is unfolded or folded through the rotation of the first sleeve 1 and the second sleeve 2.
In this embodiment, locking bolt 8 is the steel ball bolt, can directly realize two telescopic openings and closings, convenient operation with the steel ball bolt. When the rotor pole expandes, through the locking of locking bolt 8, take off locking bolt 8 and can realize the recovery of rotor pole.
In this embodiment, the material of the first fixing block 3 is the same as that of the first sleeve 1, and the first fixing block 3 and the first sleeve 1 are integrally formed. The material of the second fixed block 4 is the same as that of the second sleeve 2, and the second fixed block 4 and the second sleeve 2 are integrally formed. The first sleeve 1 and the second sleeve 2 are made of aluminum alloy materials with the trade name of 7075-T7351, have excellent fatigue performance and corrosion resistance, can meet the durability to stress environment and corrosion environment in the using process, and prolong the service life. And the surfaces of the first sleeve 1 and the second sleeve 2 are provided with oxide film layers formed after anodization, so that the corrosion resistance can be further improved.
The invention has been described above by way of example with reference to the accompanying drawings. Obviously, the specific implementation of the present invention is not limited by the above-described manner. Various insubstantial improvements are made by adopting the method conception and the technical proposal of the utility model; or without improvement, the above conception and technical solution of the present invention can be directly applied to other occasions, all within the protection scope of the present invention.
Claims (6)
1. VTOL unmanned aerial vehicle rotor pole folding arm structure, its characterized in that: including the first sleeve of being connected with first rotor pole, be connected with the second rotor pole and rotate the second sleeve of being connected with first sleeve, the first fixed block of being connected with first sleeve, be connected with the second sleeve and with first fixed block complex second fixed block and be used for making first sleeve and second sleeve keep fixed locking bolt when the closure state, first fixed block has lets the first locking hole of locking bolt male, the second fixed block has lets the second locking hole of locking bolt male, first sleeve and the telescopic material of second are the aluminum alloy.
2. The VTOL UAV rotor mast folding arm structure of claim 1, wherein: the first fixing block is provided with an accommodating groove for the second fixing block to be embedded in, the first sleeve is rotatably connected with the second sleeve through a hinge pin, and the hinge pin and the first fixing block are oppositely arranged.
3. The VTOL UAV rotor mast folding arm structure of claim 2, wherein: the hinge pin is made of stainless steel.
4. The VTOL UAV rotor mast folding arm structure of any of claims 1-3, characterized in that: the locking bolt is a steel ball bolt.
5. The VTOL UAV rotor mast folding arm structure of any of claims 1-3, characterized in that: the first fixed block is made of the same material as the first sleeve, and the first fixed block and the first sleeve are integrally formed.
6. The VTOL UAV rotor mast folding arm structure of any of claims 1-3, characterized in that: the second fixed block is made of the same material as the second sleeve, and the second fixed block and the second sleeve are integrally formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121648664.0U CN214930562U (en) | 2021-07-20 | 2021-07-20 | Vertical take-off and landing unmanned aerial vehicle rotor pole folding arm structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121648664.0U CN214930562U (en) | 2021-07-20 | 2021-07-20 | Vertical take-off and landing unmanned aerial vehicle rotor pole folding arm structure |
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| Publication Number | Publication Date |
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| CN214930562U true CN214930562U (en) | 2021-11-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202121648664.0U Active CN214930562U (en) | 2021-07-20 | 2021-07-20 | Vertical take-off and landing unmanned aerial vehicle rotor pole folding arm structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114671006A (en) * | 2022-04-15 | 2022-06-28 | 上海新云彩航空科技有限责任公司 | Aircraft rotor support arm folding mechanism and aircraft rotor support arm |
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2021
- 2021-07-20 CN CN202121648664.0U patent/CN214930562U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114671006A (en) * | 2022-04-15 | 2022-06-28 | 上海新云彩航空科技有限责任公司 | Aircraft rotor support arm folding mechanism and aircraft rotor support arm |
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