CN112389633A - Folding wing unmanned aerial vehicle's folding mechanism - Google Patents
Folding wing unmanned aerial vehicle's folding mechanism Download PDFInfo
- Publication number
- CN112389633A CN112389633A CN202011413572.4A CN202011413572A CN112389633A CN 112389633 A CN112389633 A CN 112389633A CN 202011413572 A CN202011413572 A CN 202011413572A CN 112389633 A CN112389633 A CN 112389633A
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- folding
- wing
- installed part
- right wing
- left wing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention discloses a folding mechanism of a folding wing unmanned aerial vehicle, wherein a right wing folding installation piece is arranged at the top of a folding piece installation shaft seat, the left wing folding installation piece is installed with a left wing together through four installation holes on the left wing folding installation piece by screws, the right wing folding installation piece is installed with a right wing together through four installation holes on the right wing folding installation piece by screws, an inner shaft of the folding piece installation shaft seat penetrates out from a shaft hole between the left wing folding installation piece and the right wing folding installation piece, and the left wing folding installation piece and the right wing folding installation piece can rotate around the inner shaft of the folding piece installation shaft seat. The cost is greatly saved.
Description
Technical Field
The invention relates to a folding mechanism, in particular to a folding mechanism of a folding wing unmanned aerial vehicle, and belongs to the technical field of folding unmanned aerial vehicles.
Background
At present, cluster unmanned aerial vehicles become hot spots, most of the cluster unmanned aerial vehicles are launched in modes of ejection, tube ejection, air ejection and the like, and in order to meet requirements of tube ejection and air ejection, most of the cluster unmanned aerial vehicles adopt foldable wings and empennages.
The folding wings are quickly folded and unfolded through the design of the folding mechanism, most of the folding mechanisms are driven by double springs, each spring drives one wing, and the wings are unfolded under the action of the spring elasticity, so that the folding mechanism is simple in structure and high in unfolding speed, but the double-spring drive has the problems of large occupied space, time and labor waste in installation, poor unfolding synchronism and the like; in addition, part of research is to integrate the wings and the folding mechanism, and the whole wings and the folding mechanism are required to be replaced together when the wings and the folding mechanism are damaged slightly, so that great resource waste is caused, and the cost is not saved.
Disclosure of Invention
The invention aims to provide a folding mechanism of a folding wing unmanned aerial vehicle, which aims to solve the problems that most of the existing folding mechanisms in the background technology are driven by double springs, each spring drives one wing, and the wings are driven to be unfolded under the action of the spring elasticity, so that the folding mechanism is simple in structure and high in unfolding speed, but the double spring drive has large occupied space, wastes time and labor in installation, and is poor in unfolding synchronism and the like; in addition, part of research is to integrate the wings and the folding mechanism, and the whole wings and the folding mechanism are required to be replaced together when the wings and the folding mechanism are damaged slightly, so that great resource waste is caused, and the problem of cost saving is not facilitated.
In order to achieve the purpose, the invention provides the following technical scheme: a folding mechanism of a folding wing unmanned aerial vehicle comprises a left wing folding mounting piece, a right wing folding mounting piece, a folding piece mounting shaft seat, a folding mechanism gland, a locking pin spring, a driving torsion spring, a right wing and a left wing, wherein the right wing folding mounting piece is arranged at the top of the folding piece mounting shaft seat, the left wing folding mounting piece is fixedly mounted at the top of the right wing folding mounting piece, the left wing folding mounting piece is mounted with the left wing through four mounting holes on the left wing folding mounting piece by screws, the right wing folding mounting piece is mounted with the right wing through four mounting holes on the right wing folding mounting piece, an inner shaft of the folding piece mounting shaft seat penetrates out of a shaft hole between the left wing folding mounting piece and the right wing folding mounting piece, the left wing folding mounting piece and the right wing folding mounting piece are distributed up and down, and the left wing folding mounting piece and the right wing folding mounting piece can rotate around the inner shaft of the folding mounting, and the folding mechanism gland is clamped through a folding mechanism gland arranged at the top of the folded piece mounting shaft seat, the folding mechanism gland is fixedly connected with the folded piece mounting shaft seat through screws, and the folded piece mounting shaft seat is fixedly arranged at the corresponding position of the machine body through screws.
As a preferred technical solution of the present invention, a driving torsion spring is disposed between the left wing folding mounting member and the right wing folding mounting member, two torsion arms of the torsion spring are respectively locked at a slot position of the left wing folding mounting member and a slot position of the right wing folding mounting member, and the torsion force of the torsion spring is transmitted to the left wing and the right wing through the left wing folding mounting member and the right wing folding mounting member.
As a preferred technical scheme of the invention, the top end of the left wing folding mounting part and the top end of the right wing folding mounting part are both provided with locking pin holes, locking pins are fixedly mounted inside the locking pin holes, and locking pin springs are fixedly sleeved outside the locking pins.
As a preferred technical solution of the present invention, the locking pin is specifically used as follows:
when the left wing and the right wing are in the unfolding state, the locking pin is just in the locking pin holes of the folding mounting parts of the left wing and the right wing, and the locking pin spring is in the unfolding state and can lock the unfolding state of the left wing and the right wing.
As a preferred technical scheme of the invention, when the left wing and the right wing need to be folded, the operation is as follows:
through the drag hook or wear the acting as go-between in advance and pull up the fitting up pin, withdraw from right wing folding installed part locking pinhole, it can begin to fold to remove the locking, and the fitting up pin spring is in compression state this moment, when treating left wing and right wing expand once more, can impress the fitting up pin in the fitting up pin hole of right wing folding installed part fast after arriving the expansion state, realizes locking.
Compared with the prior art, the invention has the beneficial effects that:
1. the invention relates to a folding mechanism of a folding wing unmanned aerial vehicle, which is characterized in that after the unmanned aerial vehicle launches a cylinder, wings do not have the limit constraint of a cylinder wall and can be unfolded rapidly under the torsion action of a driving torsion spring, when the wings are unfolded in place, rubber stoppers arranged on a machine body enable the wings to buffer and decelerate until the wings stop moving, the wings are unfolded completely at the moment, locking pin holes in a left wing folding installation part and a right wing folding installation part are in a coaxial alignment state, a locking pin moves towards a locking pin hole of the right wing folding installation part under the elastic force action of a locking pin spring, finally, the front half section of the locking pin is positioned in the right wing folding installation part, and the rear half section of the locking pin is still left in the left wing folding installation.
2. The folding mechanism of the folding wing unmanned aerial vehicle adopts a single torsional spring driving mode to realize folding and unfolding, has the advantages of simple structure, convenience in installation, small occupied space and better synchronism, adopts an embedded cylindrical pin design, has simple structure and reliable locking, adopts a separated structural design, can quickly replace a problem part when a certain part of the folding mechanism or a wing has a problem, and greatly saves the cost.
Drawings
FIG. 1 is a schematic semi-sectional view of the present invention;
FIG. 2 is a schematic top view of the present invention;
FIG. 3 is a schematic perspective view of the present invention;
FIG. 4 is a schematic view of the present invention installed with a wing;
FIG. 5 is a schematic structural view of the on-board wing in an open state according to the present invention;
fig. 6 is a schematic view of the folded state structure of the upper wing of the present invention.
In the figure: 1. a left wing fold mount; 2. a right wing folding mount; 3. the folding piece is provided with a shaft seat; 4. a folding mechanism gland; 5. a locking pin; 6. a locking pin spring; 7. a drive torsion spring; 8. a right wing; 9. and a left wing.
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.
Referring to fig. 1 to 6, the present invention provides a folding mechanism of a folding wing drone, which comprises: a folding mechanism of a folding wing unmanned aerial vehicle comprises a left wing folding mounting piece 1, a right wing folding mounting piece 2, a folding piece mounting shaft seat 3, a folding mechanism gland 4, a locking pin 5, a locking pin spring 6, a driving torsion spring 7, a right wing 8 and a left wing 9, wherein the top of the folding piece mounting shaft seat 3 is provided with the right wing folding mounting piece 2, the top of the right wing folding mounting piece 2 is fixedly provided with the left wing folding mounting piece 1, the left wing folding mounting piece 1 is mounted with the left wing 9 through four mounting holes on the left wing folding mounting piece 1 by screws, the right wing folding mounting piece 2 is mounted with the right wing 8 through four mounting holes on the right wing folding mounting piece 2 by screws, an inner shaft of the folding piece mounting shaft seat 3 penetrates out of a shaft hole between the left wing folding mounting piece 1 and the right wing folding mounting piece 2, wherein the left wing folding mounting piece 1 and the right wing folding mounting piece 2 are distributed up, folding installed part 1 of left wing and the folding installed part 2 of right wing all can be around the interior rotation of folded piece installation axle bed 3, and through setting up 4 screens of folding mechanism gland at 3 tops of folded piece installation axle bed, folding mechanism gland 4 is connected fixedly through screw and folded piece installation axle bed 3, and folded piece installation axle bed 3 is fixed in fuselage relevant position through the screw installation.
Be provided with between folding installed part 1 of left wing and the folding installed part 2 of right wing drive torsional spring 7, the draw-in groove position at folding installed part 1 of left wing and the draw-in groove position card of the folding installed part 2 of right wing die respectively of the two place torque arms of torsional spring 7, transmit on left wing 9 and right wing 8 torsion of torsional spring 7 through folding installed part 1 of left wing and the folding installed part 2 of right wing.
The locking pin holes are formed in the top end of the left wing folding mounting piece 1 and the top end of the right wing folding mounting piece 2, the locking pins 5 are fixedly mounted inside the locking pin holes, the locking pin springs 6 are fixedly sleeved outside the locking pins 5, mature calculation formulas are provided for size selection of the driving torsion springs 7, and the locking pin springs can be determined according to the unfolding time and the loading state.
When the left wing 9 and the right wing 8 are in the expansion state, the fitting pin 5 is just in the fitting pin hole of the folding installed part 1 of left wing and the folding installed part 2 of right wing, the fitting pin spring 6 is in the expansion state, the expansion state of lockable left wing 9 and right wing 8, when left wing 9 and right wing 8 need be folded, through the drag hook or the stay wire of wearing in advance with the fitting pin 5 pull-up, withdraw from the 2 fitting pin holes of the folding installed part 2 of right wing, it can begin to fold to relieve the locking, the fitting pin spring 6 is in the compression state this moment, when waiting for left wing 9 and right wing 8 to expand once more, can impress fitting pin 5 in the fitting pin hole of the folding installed part 2 of right wing fast after arriving the expansion state, realize locking.
When the unmanned aerial vehicle is not launched, wings are in a folded state and cling to the inner wall of a launching tube, the expansion of a left wing 9 and a right wing 8 is limited by the inner wall of the tube, at the moment, a driving torsion spring 7 is in a torsion limit compression state, the torsion of two torsion arms is also maximum, after the unmanned aerial vehicle launches the tube, the wings can be rapidly expanded under the action of the torsion of the driving torsion spring 7 without limiting constraint of the tube wall, when the wings are expanded in place, a rubber stop block arranged on a machine body enables the wings to buffer and decelerate until the wings stop moving, at the moment, the wings are completely expanded, locking pin holes in a left wing folding installation part 1 and a right wing folding installation part 2 are in a coaxial alignment state, a locking pin 5 moves towards a locking pin hole of the right wing folding installation part 2 under the elastic force of a locking pin spring 6, and finally the front half section of the locking pin 5 is positioned in, the second half section is still left in the folding installation part 1 of the left wing, and the limiting and locking of the left wing and the right wing are realized.
In the description of the present invention, it is to be understood that the indicated orientations or positional relationships are based on the orientations or positional relationships shown in the drawings and are only for convenience in describing the present invention and simplifying the description, but are not intended to indicate or imply that the indicated devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are not to be construed as limiting the present invention.
In the present invention, unless otherwise explicitly specified or limited, for example, it may be fixedly attached, detachably attached, or integrated; can be mechanically or electrically connected; the terms may be directly connected or indirectly connected through an intermediate, and may be communication between two elements or interaction relationship between two elements, unless otherwise specifically limited, and the specific meaning of the terms in the present invention will be understood by those skilled in the art according to specific situations.
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 invention, the scope of which is defined in the appended claims and their equivalents.
Claims (5)
1. The utility model provides a folding wing unmanned aerial vehicle's folding mechanism, includes folding installed part of left wing (1), folding installed part of right wing (2), folded piece installation axle bed (3), folding mechanism gland (4), fitting pin (5), fitting pin spring (6), drive torsional spring (7), right wing (8) and left wing (9), its characterized in that, the top of folded piece installation axle bed (3) is equipped with folding installed part of right wing (2), the top fixed mounting of folding installed part of right wing (2) has folding installed part of left wing (1), folding installed part of left wing (1) is in the same place through four screws for the mounting hole on folding installed part of left wing (1) and installation of left wing (9), folding installed part of right wing (2) is in the same place through four screws for the mounting hole on folding installed part of right wing (2) and installation of right wing (8), the interior axle of folded piece installation (3) is from folding installed part of left wing (1) and folding installed part of right wing (8), (the folding installed part of right 2) The shaft hole in the middle of wearing out, wherein left wing folding installed part (1) and right wing folding installed part (2) are upper and lower and distribute, and left wing folding installed part (1) and right wing folding installed part (2) all can be around the interior rotation of folded piece installation axle bed (3), and through setting up folding mechanism gland (4) screens at folded piece installation axle bed (3) top, folding mechanism gland (4) are connected fixedly through screw and folded piece installation axle bed (3), folded piece installation axle bed (3) are fixed in fuselage relevant position through the screw installation.
2. The folding mechanism of folding wing drone according to claim 1, characterized in that: be provided with between folding installed part (1) of left wing and the folding installed part (2) of right wing drive torsional spring (7), two torsion arms of torsional spring (7) are dead at the draw-in groove position of the folding installed part of left wing (1) and the draw-in groove position card of the folding installed part of right wing (2) respectively, transmit the torsion of torsional spring (7) to left wing (9) and right wing (8) through the folding installed part of left wing (1) and the folding installed part of right wing (2).
3. The folding mechanism of folding wing drone according to claim 1, characterized in that: the locking pinhole has all been seted up on the top of the folding installed part of left wing (1) and the top of the folding installed part of right wing (2), the inside fixed mounting in locking pinhole has fitting pin (5), fitting pin spring (6) have been cup jointed to the external fixation of fitting pin (5).
4. The folding mechanism of folding wing drone according to claim 3, characterized in that: the specific use method of the locking pin (5) is as follows:
when the left wing (9) and the right wing (8) are in the unfolded state, the locking pin (5) is just in the locking pin holes of the left wing folding installation piece (1) and the right wing folding installation piece (2), the locking pin spring (6) is in the unfolded state, and the unfolded state of the left wing (9) and the right wing (8) can be locked.
5. The folding mechanism of folding wing drone according to claim 1, characterized in that: when the left wing (9) and the right wing (8) need to be folded, the operation is as follows:
through the drag hook or wear the acting as go-between in advance and pull up fitting pin (5), withdraw from right wing folding installed part (2) locking pinhole, remove the locking and can begin to fold, fitting pin spring (6) are in compression state this moment, when treating that left wing (9) and right wing (8) expand once more, can impress fitting pin (5) in the fitting pin pinhole of right wing folding installed part (2) fast after arriving the expansion state, realize locking.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011413572.4A CN112389633A (en) | 2020-12-03 | 2020-12-03 | Folding wing unmanned aerial vehicle's folding mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011413572.4A CN112389633A (en) | 2020-12-03 | 2020-12-03 | Folding wing unmanned aerial vehicle's folding mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112389633A true CN112389633A (en) | 2021-02-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011413572.4A Pending CN112389633A (en) | 2020-12-03 | 2020-12-03 | Folding wing unmanned aerial vehicle's folding mechanism |
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| CN (1) | CN112389633A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114194377A (en) * | 2021-12-31 | 2022-03-18 | 中国航天空气动力技术研究院 | Unmanned aerial vehicle wing twists reverse expansion structure |
| CN114802709A (en) * | 2022-06-29 | 2022-07-29 | 西安羚控电子科技有限公司 | Wing surface unfolding mechanism and folding wing flying device |
-
2020
- 2020-12-03 CN CN202011413572.4A patent/CN112389633A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114194377A (en) * | 2021-12-31 | 2022-03-18 | 中国航天空气动力技术研究院 | Unmanned aerial vehicle wing twists reverse expansion structure |
| CN114194377B (en) * | 2021-12-31 | 2024-03-15 | 中国航天空气动力技术研究院 | Unmanned aerial vehicle wing twists reverse expansion structure |
| CN114802709A (en) * | 2022-06-29 | 2022-07-29 | 西安羚控电子科技有限公司 | Wing surface unfolding mechanism and folding wing flying device |
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