CN210707882U - Wing opening mechanism for folding wing unmanned aerial vehicle - Google Patents
Wing opening mechanism for folding wing unmanned aerial vehicle Download PDFInfo
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- CN210707882U CN210707882U CN201921103770.3U CN201921103770U CN210707882U CN 210707882 U CN210707882 U CN 210707882U CN 201921103770 U CN201921103770 U CN 201921103770U CN 210707882 U CN210707882 U CN 210707882U
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Abstract
The utility model belongs to the technical field of portable folding wing aircraft, a section of thick bamboo shoot unmanned aerial vehicle, intelligent ammunition etc., especially relate to a folding wing unmanned aerial vehicle is with opening wing mechanism. The wing opening mechanism comprises: the vortex spring box is used for transferring kinetic energy released by the deformation of the vortex spring to the wing, generating the kinetic energy for unfolding the wing, installing the vortex spring and the vortex spring rotating shaft and realizing the locking when the wing is unfolded. The beneficial effects of the utility model are that, owing to adopt above-mentioned technical scheme, the utility model discloses it is many to have utilized plane spiral spring stored energy, can store for a long time, and can be approximate invariable torque output's characteristics design and form, has compact structure and is small and exquisite, has reduced unmanned vehicles's volume to can improve unmanned vehicles inner space's make full use of. Constant torque output, flexible and reliable rotation, high unfolding speed and durability.
Description
Technical Field
The utility model belongs to the technical field of portable folding wing aircraft, a section of thick bamboo shoot unmanned aerial vehicle, intelligent ammunition etc., especially relate to a folding wing unmanned aerial vehicle is with opening wing mechanism.
Background
At present, most of the existing portable folding wing unmanned aerial vehicles stay in a folded state when being stored, and the wings are unfolded before taking off. The unmanned aerial vehicle has the advantages in the aspect of storage space, few products for controlling the unfolding wings in the take-off process exist, few products for controlling the unfolding wings in the take-off process are complex in structure, the size of the unmanned aerial vehicle is greatly increased, or more space in the unmanned aerial vehicle is occupied, and the weight of the unmanned aerial vehicle is indirectly increased. For example with a tension spring. Especially at individual soldier's portable type folding wing unmanned aerial vehicle, intelligent ammunition etc. need a large amount, and long-term storage is reserve, under the application condition of taking at any time, more needs a convenience, reliable structure.
Disclosure of Invention
It is a primary object of embodiments of the present disclosure to provide a wing opening mechanism for a folded wing unmanned aerial vehicle that solves any of the above and other potential problems of the prior art.
In order to achieve the above object, an embodiment of the present disclosure discloses a wing opening mechanism for a folding wing unmanned aerial vehicle, the wing opening mechanism including: the vortex spring box is used for transmitting kinetic energy released by the deformation of the vortex spring to the wing, generating the kinetic energy for unfolding the wing, installing the vortex spring and the vortex spring rotating shaft and realizing the locking when the wing is unfolded;
the vortex spring box is provided with 2 sunk grooves, 2 vortex springs are respectively arranged in the 2 sunk grooves, and the end part of a long circular hole of each vortex spring is respectively and fixedly connected with the side wall of the vortex spring box through a vortex spring fixing screw;
one end of each of the 2 vortex spring rotating shafts is respectively inserted into the central position of the corresponding vortex spring, the hook ends of the 2 vortex springs are respectively inserted into the grooves in the middle of the corresponding vortex spring rotating shafts, and the other ends of the 2 vortex spring rotating shafts are respectively fixedly connected with the wings through wing fixing screws.
According to the embodiment of the disclosure, the wing opening mechanism further comprises a cushion block structure for preventing the left wing and the right wing from colliding with each other when the wings are folded up and down in a staggered manner.
According to the embodiment of the disclosure, the wing opening mechanism further comprises a limiting device, and the limiting device comprises a limiting lug and a unfolding chute;
the limiting lugs are arranged on one sides of the 2 volute spring rotating shafts and the fixed end parts of the wings;
the 2 unfolding sliding grooves matched with the limiting lugs are symmetrically arranged on the outer side edge, close to the sinking groove, of the volute spring box; the wing unfolding angle is limited by the limit lug sliding along the unfolding sliding groove.
According to the embodiment of the present disclosure, the rotation angle limit is a circular arc, and the circular arc angle thereof is not greater than 90 °.
According to the embodiment of the disclosure, the volute spring is composed of a single plate spring or a plurality of plate springs.
According to the embodiment of the disclosure, the wing opening mechanism further comprises a locking mechanism for preventing the resilience of the wing, the locking mechanism comprises a locking spring pin and a locking spring pin hole, the locking spring pin is arranged on the wing, and the locking spring pin hole is arranged on the scroll box.
According to this disclosed embodiment, the cushion structure is including increasing the cushion and increasing the stopper, it sets up between the junction of one of them volute spring pivot and wing to increase the cushion, it sets up to increase the stopper and is being equipped with increase cushion one end the border position of volute spring box, just it still is equipped with the trompil hole that is used for losing weight on the stopper to increase.
According to the embodiment of the disclosure, the vortex spring rotating shaft, the vortex spring box and the end cover are all made of aluminum alloy.
According to an embodiment of the present disclosure, the volute spring is made of stainless steel.
According to the embodiment of the disclosure, the vortex spring box is rectangular, and 2 the sunk grooves are symmetrically arranged on the vortex spring box.
The utility model provides a folding wing unmanned aerial vehicle, folding wing unmanned aerial vehicle's wing adopts foretell wing opening mechanism to install on the fuselage to realize the expansion of wing.
The beneficial effects of the utility model are that, owing to adopt above-mentioned technical scheme, the utility model discloses the structure has utilized plane volute spiral spring stored energy many, can store for a long time, and can be approximate invariable torque output's characteristics design and form, has compact structure and is small and exquisite, has reduced unmanned vehicles's volume to can improve unmanned vehicles inner space's make full use of. Constant torque output, flexible and reliable rotation, high unfolding speed and durability.
Drawings
Fig. 1 is an explosion diagram of a wing opening mechanism for a folding wing unmanned aerial vehicle according to the present invention.
Fig. 2 is a side view of the technical structure shaft (position when the wing is unfolded) of the present invention.
Fig. 3 is a three-dimensional view of the technical structure of the invention (position when the wing is deployed).
Fig. 4 is a view of the technical structure of the present invention in a folded state (right wing not shown).
In the figure:
1. wing set screws; 2. a left wing; 3. a spiral spring shaft; 4. a volute spring; 5. A volute spring box 7 and an end cover; 8. a shaft end fixing screw; 9. a right wing heightening cushion block; 10. a right wing; 11. the locking spring pin is characterized by comprising a locking spring pin body 12, a long through hole 13, a locking spring pin hole 14, a limiting lug 15, an end part of the long through hole 16, a sinking groove 17 and a rotation angle limiting.
Detailed Description
The technical scheme of the invention is further explained by combining the attached drawings.
As shown in fig. 1 to 4, an embodiment of the present disclosure discloses a wing opening mechanism for a folding wing unmanned aerial vehicle, including: the vortex spring box is used for transmitting kinetic energy released by the deformation of the vortex spring to the wing, generating the kinetic energy for unfolding the wing, installing the vortex spring and the vortex spring rotating shaft and realizing the locking when the wing is unfolded;
the vortex spring box is provided with 2 sunk grooves, 2 vortex springs are respectively arranged in the 2 sunk grooves, and the end part of a long circular hole of each vortex spring is respectively and fixedly connected with the side wall of the vortex spring box through a vortex spring fixing screw;
one end of each of the 2 vortex spring rotating shafts is respectively inserted into the central position of the corresponding vortex spring, the hook ends of the 2 vortex springs are respectively inserted into the grooves in the middle of the corresponding vortex spring rotating shafts, and the other ends of the 2 vortex spring rotating shafts are respectively fixedly connected with the wings through wing fixing screws.
According to the embodiment of the disclosure, the wing opening mechanism further comprises a cushion block structure for preventing the left wing and the right wing from colliding with each other when the wings are folded up and down in a staggered manner.
According to the embodiment of the disclosure, the wing opening mechanism further comprises a limiting device, and the limiting device comprises a limiting lug and a unfolding chute;
the limiting lugs are arranged on one sides of the 2 volute spring rotating shafts and the fixed end parts of the wings;
the 2 unfolding sliding grooves matched with the limiting lugs are symmetrically arranged on the outer side edge, close to the sinking groove, of the volute spring box; the wing unfolding angle is limited by the limit lug sliding along the unfolding sliding groove.
According to the embodiment of the present disclosure, the rotation angle limit is a circular arc, and the circular arc angle thereof is not greater than 90 °.
According to the embodiment of the disclosure, the volute spring is composed of a single plate spring or a plurality of plate springs.
According to the embodiment of the disclosure, the wing opening mechanism further comprises a locking mechanism for preventing the resilience of the wing, the locking mechanism comprises a locking spring pin and a locking spring pin hole, the locking spring pin is arranged on the wing, and the locking spring pin hole is arranged on the scroll box.
According to this disclosed embodiment, the cushion structure is including increasing the cushion and increasing the stopper, it sets up between the junction of one of them volute spring pivot and wing to increase the cushion, it sets up to increase the stopper and is being equipped with increase cushion one end the border position of volute spring box, just it still is equipped with the trompil hole that is used for losing weight on the stopper to increase.
According to the embodiment of the disclosure, the vortex spring rotating shaft, the vortex spring box and the end cover are all made of aluminum alloy.
According to an embodiment of the present disclosure, the volute spring is made of stainless steel.
According to the embodiment of the disclosure, the vortex spring box is rectangular, and 2 the sunk grooves are symmetrically arranged on the vortex spring box.
The utility model relates to an assembling method of a wing opening mechanism for a folding wing unmanned aerial vehicle, which is characterized in that 2 sinking grooves 16 are symmetrically arranged on a rectangular vortex spring box 5 in the left and right direction; 2 scroll springs 4 are respectively placed in 2 sunk grooves 16 on a rectangular scroll spring box 5, and the end parts of the long round holes of the 2 scroll springs 4 are respectively fixedly connected with the side wall of the scroll spring box 5 through scroll spring fixing screws 6 (as shown in fig. 2 and 3); then, the hook grooves of the 2 volute spring rotating shafts 3 are connected with the hooks at the other ends of the 2 volute springs 4, N rings of energy are rotated to store energy, the limiting lugs 14 on the volute spring rotating shafts 3 are placed in the rotating angle limiting grooves 17 of the volute spring box 5, and the volute spring rotating shafts are axially limited by shaft end fixing screws 8 penetrating through the end covers 7; the assembled complete wing opening mechanism is arranged on the machine body, the wings are respectively arranged on 2 vortex spring rotating shafts 3,
when the folding wing is folded, the wing is rotated by a certain angle to be folded by applying torque outside, and the volute spring 4 is deformed to store energy in the rotating process.
When the machine body is too small, the axial distance between the 2 sunken grooves 16 is shortened, in order to prevent the wing from being folded up and down in a staggered manner, the left wing and the right wing collide with each other, a cushion block structure is arranged on one of the volute spring rotating shafts 3, the cushion block structure comprises a height increasing cushion block and a height increasing limiting block, the height increasing cushion block is arranged between the joint of one of the volute spring rotating shafts and the wing, the height increasing limiting block is arranged at the edge position of the volute spring box at one end provided with the height increasing cushion block, and a long through hole for reducing weight is further formed in the height increasing limiting block; the heightening limiting block is detachable and split, as shown in fig. 4, and is not detached in the drawing.
In order to prevent the wings from rebounding when being collided and unfolded rapidly, the wing opening mechanism further comprises a locking mechanism for preventing the wings from rebounding, the locking mechanism comprises a locking spring pin and a locking spring pin hole, the locking spring pin is arranged on the wings, and the locking spring pin hole is formed in the volute spring box.
In the description of the present application, it is to be understood that the terms "first", "second", and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any number of technical features indicated. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.
In this application, unless expressly stated or limited otherwise, the terms "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections, removable connections, or integral combinations thereof; may be an electrical connection; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
In the specification of the present invention, a large number of specific details are explained. It is understood, however, that embodiments of the invention may be practiced without these specific details. In some instances, well-known methods, systems, and techniques have not been shown in detail in order not to obscure an understanding of this description.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, system, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, systems, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not substantially depart from the scope of the embodiments of the present invention, and are intended to be covered by the claims and the specification.
Claims (10)
1. A wing opening mechanism for a folding wing unmanned aerial vehicle, characterized in that the wing opening mechanism comprises: the vortex spring box is used for transmitting kinetic energy released by the deformation of the vortex spring to the wing, generating the kinetic energy for unfolding the wing, installing the vortex spring and the vortex spring rotating shaft and realizing the locking when the wing is unfolded;
the vortex spring box is provided with 2 sunk grooves, 2 vortex springs are respectively arranged in the 2 sunk grooves, and the end part of a long circular hole of each vortex spring is respectively and fixedly connected with the side wall of the vortex spring box through a vortex spring fixing screw;
one end of each of the 2 vortex spring rotating shafts is respectively inserted into the central position of the corresponding vortex spring, the hook ends of the 2 vortex springs are respectively inserted into the grooves in the middle of the corresponding vortex spring rotating shafts, and the other ends of the 2 vortex spring rotating shafts are respectively fixedly connected with the wings through wing fixing screws.
2. The wing opening mechanism for the folding wing unmanned aerial vehicle as claimed in claim 1, wherein the wing opening mechanism further comprises a cushion block structure for preventing the left wing and the right wing from colliding with each other when the wings are folded up and down alternately.
3. The wing opening mechanism for the folding wing unmanned aerial vehicle according to claim 1 or 2, characterized in that the wing opening mechanism further comprises a limiting device, and the limiting device comprises a limiting lug and a unfolding chute;
the limiting lugs are arranged on one sides of the 2 volute spring rotating shafts and the fixed end parts of the wings;
the 2 unfolding sliding grooves matched with the limiting lugs are symmetrically arranged on the outer side edge, close to the sinking groove, of the volute spring box; the wing unfolding angle is limited by the limiting lug sliding along the rotating angle limiting groove.
4. The wing opening mechanism for the folding wing unmanned aerial vehicle as claimed in claim 3, wherein the rotation angle limiting groove is in the shape of an arc having an angle of not more than 90 °.
5. The wing opening mechanism for the folding wing unmanned aerial vehicle according to claim 1 or 2, wherein the volute spring is composed of a single plate spring or a plurality of plate springs.
6. The wing opening mechanism for the folding wing unmanned aerial vehicle of claim 5, characterized in that the wing opening mechanism further comprises a locking mechanism for preventing the wing from rebounding, wherein the locking mechanism comprises a locking spring pin and a locking spring pin hole, the locking spring pin is arranged on the wing, and the locking spring pin hole is arranged on the volute spring box.
7. The wing opening mechanism for the folding wing unmanned aerial vehicle as claimed in claim 2, wherein the cushion block structure comprises a height increasing cushion block and a height increasing limiting block, the height increasing cushion block is arranged between a joint of one of the scroll spring rotating shafts and the wing, the height increasing limiting block is arranged at an edge position of the scroll spring box provided with one end of the height increasing cushion block, and a long through hole for reducing weight is further arranged on the height increasing limiting block.
8. The wing opening mechanism for the folding wing unmanned aerial vehicle as claimed in claim 3, wherein the vortex spring rotating shaft, the vortex spring box and the end cover are made of aluminum alloy.
9. The wing opening mechanism for a folding wing unmanned aerial vehicle of claim 3, wherein the volute spring is made of stainless steel.
10. The wing opening mechanism for the folding wing unmanned aerial vehicle as claimed in claim 1, wherein the scroll spring box is rectangular, and 2 of the sunken grooves are symmetrically arranged on the scroll spring box.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921103770.3U CN210707882U (en) | 2019-07-15 | 2019-07-15 | Wing opening mechanism for folding wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921103770.3U CN210707882U (en) | 2019-07-15 | 2019-07-15 | Wing opening mechanism for folding wing unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN210707882U true CN210707882U (en) | 2020-06-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921103770.3U Active CN210707882U (en) | 2019-07-15 | 2019-07-15 | Wing opening mechanism for folding wing unmanned aerial vehicle |
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| CN (1) | CN210707882U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110217392A (en) * | 2019-07-15 | 2019-09-10 | 北京晶品特装科技有限责任公司 | A kind of folding wings unmanned plane is with opening wing mechanism |
| CN112977801A (en) * | 2021-02-26 | 2021-06-18 | 珠海天晴航空航天科技有限公司 | Unmanned aerial vehicle with rotatable wings |
-
2019
- 2019-07-15 CN CN201921103770.3U patent/CN210707882U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110217392A (en) * | 2019-07-15 | 2019-09-10 | 北京晶品特装科技有限责任公司 | A kind of folding wings unmanned plane is with opening wing mechanism |
| CN112977801A (en) * | 2021-02-26 | 2021-06-18 | 珠海天晴航空航天科技有限公司 | Unmanned aerial vehicle with rotatable wings |
| CN112977801B (en) * | 2021-02-26 | 2023-01-31 | 珠海天晴航空航天科技有限公司 | Unmanned aerial vehicle with rotatable wings |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | "change of name, title or address" |
Address after: Room 603, building 5, No.1, Chaoqian Road, science and Technology Park, Changping District, Beijing Patentee after: Beijing Jingpin special decoration technology Co., Ltd Address before: 102299, Beijing, Changping District, a road on the front of a macro science and Technology Park, building 5, 6 floor Patentee before: BEIJING JINGPINTEZHUANG SCIENCE AND TECHNOLOGY Co.,Ltd. |
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| CP03 | "change of name, title or address" |