CN215944861U - Wing folding mechanism of unmanned helicopter - Google Patents
Wing folding mechanism of unmanned helicopter Download PDFInfo
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- CN215944861U CN215944861U CN202120097395.7U CN202120097395U CN215944861U CN 215944861 U CN215944861 U CN 215944861U CN 202120097395 U CN202120097395 U CN 202120097395U CN 215944861 U CN215944861 U CN 215944861U
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- unmanned helicopter
- fixedly connected
- simulation cabin
- ball screw
- folding mechanism
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Abstract
The utility model discloses a wing folding mechanism of an unmanned helicopter, which comprises a simulation cabin roof, wherein the top of the simulation cabin roof is provided with an opening, the bottom of the simulation cabin roof is fixedly connected with an aluminum alloy platform, four corners of the bottom of the simulation cabin roof are fixedly connected with ball screw modules, one side of each ball screw module is in transmission connection with a gear transmission system, and one side of each ball screw module and one side of each gear transmission system are fixedly connected with servo motors. The wing folding mechanism of the unmanned helicopter has the advantages that the wings of the unmanned helicopter can be automatically and unmanned folded.
Description
Technical Field
The utility model relates to the technical field of engineering equipment, in particular to a wing folding mechanism of an unmanned helicopter.
Background
The pilotless helicopter is a vertical take-off and landing unmanned aircraft flying by radio ground remote control or/and autonomous control, belongs to a rotor aircraft in the structural form, and belongs to a vertical take-off and landing aircraft in the function. In recent decades, along with the research progress of composite materials, power systems, sensors, especially flight control and other technologies, unmanned helicopters have been developed rapidly and are becoming the focus of people's attention increasingly, and unmanned helicopters have unique flight performance and use value. Compared with the existing helicopters, the unmanned helicopters have incomparable superiority in many aspects due to the characteristics of no casualties, small volume, low cost, strong battlefield viability and the like. Compared with a fixed wing unmanned aerial vehicle, the unmanned helicopter can take off and land vertically and hover in the air, flies in any direction, has a small take-off and landing field, and does not need to be provided with a complicated and large-volume launching and recovering system like the fixed wing unmanned aerial vehicle. In military terms, unmanned helicopters can perform not only various non-destructive tasks, but also various soft and hard destructive tasks, including reconnaissance, surveillance, target interception, decoy, attack, communication relay, and the like. In the civil aspect, the unmanned helicopter has wide application prospects in the aspects of atmosphere monitoring, traffic monitoring, resource exploration, power line detection, forest fire prevention and the like.
After the unmanned helicopter lands, the wings of the unmanned helicopter are in an unfolded state but cannot be folded by self, so that the unmanned helicopter cannot enter a shelter (or other storable spaces) and needs to be folded before being stored.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a wing folding mechanism of an unmanned helicopter, which has the advantages of realizing automation and unmanned folding of wings of the unmanned helicopter and solves the problem that the wings of the existing unmanned helicopter are unfolded and cannot be folded automatically after landing, so that the wings cannot enter a shelter.
In order to achieve the purpose, the utility model provides the following technical scheme: the wing folding mechanism of the unmanned helicopter comprises a simulation cabin top, wherein an opening is formed in the top of the simulation cabin top, an aluminum alloy platform is fixedly connected to the bottom of the simulation cabin top, ball screw modules are fixedly connected to four corners of the bottom of the simulation cabin top, a gear transmission system is connected to one side of each ball screw module in a transmission mode, a servo motor is fixedly connected to one side of each ball screw module and one side of each gear transmission system, and three-phase movement mechanisms are fixedly connected to two sides of the top of the simulation cabin top.
Preferably, the bottoms of the ball screw module and the gear transmission system are fixedly connected with supporting blocks, and the number of the supporting blocks is dry.
Preferably, the number of the servo motors is two, and the two three-phase motion mechanisms are positioned on two sides of the opening.
Preferably, the opening is located at the top of the aluminium alloy platform.
Compared with the prior art, the utility model has the following beneficial effects:
1. the wing folding mechanism of the unmanned helicopter has the advantages of being capable of achieving automation and unmanned folding of the wings of the unmanned helicopter, and is worthy of popularization.
2. The supporting block is arranged to play a role in supporting the structure.
Drawings
FIG. 1 is a schematic view of the structure of the present invention.
In the figure: the device comprises a simulation cabin roof 1, an aluminum alloy platform 2, an opening 3, a servo motor 4, a ball screw module 5, a support block 6, a gear transmission system 7 and a three-way movement mechanism 8.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front", "rear", "both ends", "one end", "the other end", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted", "provided", "connected", and the like are to be construed broadly, such as "connected", which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The parts of the simulation cabin roof 1, the aluminum alloy platform 2, the opening 3, the servo motor 4, the ball screw module 5, the supporting block 6, the gear transmission system 7, the three-way movement mechanism 8 and the like are all universal standard parts or parts known by the technical staff, and the structure and the principle of the parts are known by the technical staff or conventional experimental methods.
Referring to fig. 1, the wing folding mechanism of the unmanned helicopter comprises a simulation cabin roof 1, wherein the top of the simulation cabin roof 1 is provided with an opening 3, the bottom of the simulation cabin roof 1 is fixedly connected with an aluminum alloy platform 2, four corners of the bottom of the simulation cabin roof 1 are fixedly connected with ball screw modules 5, one side of each ball screw module 5 is in transmission connection with a gear transmission system 7, one side of each ball screw module 5 and one side of each gear transmission system 7 are fixedly connected with a servo motor 4, and two sides of the top of the simulation cabin roof 1 are fixedly connected with a three-phase movement mechanism 8;
the bottoms of the ball screw module 5 and the gear transmission system 7 are fixedly connected with supporting blocks 6, and the number of the supporting blocks 6 is dry;
the number of the servo motors 4 is two, and the two three-phase motion mechanisms 8 are positioned on two sides of the opening 3;
the opening 3 is positioned at the top of the aluminum alloy platform 2;
by arranging the supporting block 6, the structure is supported.
Unmanned helicopter descends behind aluminum alloy platform 2, and servo motor 4 drive ball screw module 5 operates, causes aluminum alloy platform 2 to drive unmanned aerial vehicle and descends, arrives two wings and can fall on the disc of income hatch both sides three-way motion 8 completely, and three-way motion 8 moves, and its orbit is the circular arc, can fold the wing to the tail machine and drag.
In summary, the following steps: this unmanned helicopter wing folding mechanism uses through the cooperation that sets up simulation cabin top 1, aluminum alloy platform 2, opening 3, servo motor 4, ball screw module 5, supporting shoe 6, gear transmission system 7 and three-way motion 8, has solved current unmanned helicopter after the landing, and its wing is the state of expanding, but unable folding by oneself to can't get into the problem among the shelter.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (4)
1. The utility model provides an unmanned helicopter wing folding mechanism, includes simulation cabin roof (1), its characterized in that: the simulation cabin top (1) is provided with an opening (3), the bottom of the simulation cabin top (1) is fixedly connected with an aluminum alloy platform (2), four corners of the bottom of the simulation cabin top (1) are fixedly connected with ball screw modules (5), one side of each ball screw module (5) is in transmission connection with a gear transmission system (7), one side of each ball screw module (5) and one side of each gear transmission system (7) are fixedly connected with a servo motor (4), and two sides of the top of the simulation cabin top (1) are fixedly connected with a three-phase movement mechanism (8).
2. The wing folding mechanism of an unmanned helicopter of claim 1, wherein: the bottoms of the ball screw module (5) and the gear transmission system (7) are fixedly connected with supporting blocks (6).
3. The wing folding mechanism of an unmanned helicopter of claim 1, wherein: the number of the servo motors (4) is two, and the two three-phase motion mechanisms (8) are positioned on two sides of the opening (3).
4. The wing folding mechanism of an unmanned helicopter of claim 1, wherein: the opening (3) is positioned at the top of the aluminum alloy platform (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120097395.7U CN215944861U (en) | 2021-01-14 | 2021-01-14 | Wing folding mechanism of unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120097395.7U CN215944861U (en) | 2021-01-14 | 2021-01-14 | Wing folding mechanism of unmanned helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215944861U true CN215944861U (en) | 2022-03-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202120097395.7U Active CN215944861U (en) | 2021-01-14 | 2021-01-14 | Wing folding mechanism of unmanned helicopter |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112722236A (en) * | 2021-01-14 | 2021-04-30 | 西安天成益邦电子科技有限公司 | Wing folding mechanism of unmanned helicopter |
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2021
- 2021-01-14 CN CN202120097395.7U patent/CN215944861U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112722236A (en) * | 2021-01-14 | 2021-04-30 | 西安天成益邦电子科技有限公司 | Wing folding mechanism of unmanned helicopter |
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