CN214451837U - Synchronous deployment mechanism of non-coaxial folding wing of unmanned aerial vehicle - Google Patents
Synchronous deployment mechanism of non-coaxial folding wing of unmanned aerial vehicle Download PDFInfo
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- CN214451837U CN214451837U CN202022645256.1U CN202022645256U CN214451837U CN 214451837 U CN214451837 U CN 214451837U CN 202022645256 U CN202022645256 U CN 202022645256U CN 214451837 U CN214451837 U CN 214451837U
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Abstract
The utility model provides a synchronous deployment mechanism of coaxial folding wing of unmanned aerial vehicle non-, include: installing a base; one end of the rotating shaft is fixedly connected to the mounting base, and the wing can freely rotate around the rotating shaft; the driving torsion spring is arranged between the wing and the mounting base; the sliding rail is fixedly connected to the mounting base; and the limiting pieces are slidably mounted on the sliding rails, can be matched with the first grooves and the second grooves on the wings respectively when moving along the sliding rails, and are used for locking the positions of the wings in a compression state and a deployment state of the wings respectively. The utility model overcomes prior art's restriction can realize the expansion of non-coaxial folding wing. The left wing and the right wing are unlocked simultaneously through a single limiting sheet part, and the synchronism of the unfolding processes of the two wings is ensured. The utility model discloses a single spacing piece part realizes unblock and expandes two functions of locking, has simplified mechanical structure's complexity.
Description
Technical Field
The utility model belongs to aircraft design field relates to the unmanned air vehicle technique, concretely relates to synchronous deployment mechanism of coaxial folding wing of unmanned aerial vehicle non-.
Background
An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Unmanned aerial vehicles can be divided into military unmanned aerial vehicles and civil unmanned aerial vehicles according to the application field. At present, unmanned aerial vehicles are widely applied in various fields such as military use, civil use and the like. The military unmanned aerial vehicle has the characteristics of exquisite structure, strong concealment, convenient use, low manufacturing cost, flexible performance and the like, is mainly used for battlefield reconnaissance, electronic interference, carrying of weapons such as cluster bombs and guided missiles to execute aggressive missions, is used as a military unmanned aerial vehicle such as an aerial communication relay platform, a nuclear test sampler, nuclear explosion and nuclear radiation reconnaissance machine to serve as one member of modern aerial military strength, has the characteristics of no casualties, less use limitation, good concealment, high cost effectiveness ratio and the like, and has increasingly prominent status and effect in modern war.
Folding wing formula unmanned aerial vehicle is because its folding back is small, portable, the cylinder of being convenient for again simultaneously launches and puts in the air, and its application prospect is extensive. The synchronous unfolding mechanism of the folding wings is the key technology of the aircraft.
The existing unfolding mechanism for the folding wing of the unmanned aerial vehicle generally has coaxial rotating shafts of a left wing surface and a right wing surface and takes a single torsion spring as a power unfolding mechanism. The mechanism limits partial application scenes of the aircraft, and simultaneously, the synchronism of wing unfolding is limited by driving the symmetrical left wing and the symmetrical right wing through a single torsion spring.
Therefore, there is a need in the art for a novel folding wing synchronous deployment mechanism for drones.
SUMMERY OF THE UTILITY MODEL
The utility model provides a technical problem be: the defects of the prior art are overcome, the non-coaxial folding wing synchronous unfolding mechanism of the unmanned aerial vehicle is provided, and the synchronism of the unfolding processes of the two wings is ensured.
The utility model provides a synchronous deployment mechanism of coaxial folding wing of unmanned aerial vehicle non, include:
installing a base;
one end of each rotating shaft is fixedly connected to the mounting base, and the wings can freely rotate around the rotating shafts;
the driving torsion spring is arranged between the wing and the mounting base;
the sliding rail is fixedly connected to the mounting base;
and the limiting pieces are slidably mounted on the sliding rails, can be matched with the first grooves and the second grooves on the wings respectively when moving along the sliding rails, and are used for locking the positions of the wings in a compression state and a deployment state of the wings respectively.
Furthermore, the slide rail is of a U-shaped structure, one side of the opening is fixedly connected to the mounting base, and a slide rail space is formed between the slide rail and the mounting base.
Further, spacing piece is T type structure, including horizontal portion and vertical portion, vertical portion stretches into in the slide rail space of slide rail.
Furthermore, two ends of the transverse part of the limiting sheet are respectively provided with a locking pin which is respectively matched with the second grooves on the two wings.
Furthermore, a straight groove is respectively formed in two ends of the transverse portion of the limiting piece, and the locking pin is assembled in the straight groove and can move along the straight groove.
Further, the locking device also comprises a locking spring which is arranged in the linear groove and used for pushing the locking pin to extend out of the linear groove.
Further, the first groove and the second groove on the wing are respectively arranged on two sides of the connection end of the wing and the rotating shaft.
Further, when the limiting sheet is matched with the first groove, the wing is in a compressed state;
when the locking pin is matched with the second groove, the wing is in an unfolding and locking state.
Further, still include unlocking device, set up on the installation base for promote spacing piece moves along the slide rail.
Further, the unlocking device is a spring, a motor or a fire work product.
Compared with the prior art, the utility model beneficial effect be:
(1) the utility model overcomes prior art's restriction, can realize the expansion of non-coaxial folding wing.
(2) The utility model discloses a single spacing piece part is simultaneously to left and right wing unblock, guarantees the synchronism of two wings expansion processes.
(3) The utility model discloses a single spacing piece part realizes unblock and expandes two functions of locking, has simplified mechanical structure's complexity.
Drawings
The above and other objects, features and advantages of the present disclosure will become more apparent by describing in greater detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout.
Fig. 1 is an exploded view of the components of the present invention.
Fig. 2 is a front view of the wing in a compressed state.
Fig. 3 is a front view of the wing of the present invention in the unfolded state.
Reference numerals:
the device comprises an installation base 1, wings 2, a rotating shaft 3, limiting pieces 4, sliding rails 5, locking pins 6, locking springs 7, a driving torsion spring 8 and an unlocking device 9.
Detailed Description
Preferred embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While the preferred embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
The utility model provides a synchronous deployment mechanism of coaxial folding wing of unmanned aerial vehicle non-, includes:
installing a base;
one end of each rotating shaft is fixedly connected to the mounting base, and the left wing and the right wing can freely rotate around the rotating shafts respectively;
the driving torsion spring is arranged between the wing and the mounting base;
the sliding rail is fixedly connected to the mounting base;
and the limiting pieces are slidably mounted on the sliding rails, can be matched with the first grooves and the second grooves on the wings respectively when moving along the sliding rails, and are used for locking the positions of the wings in a compression state and a deployment state of the wings respectively.
Preferably, the slide rail is of a U-shaped structure, one side of the opening is fixedly connected to the mounting base, and a slide rail space is formed between the slide rail and the mounting base. Preferably, the limiting piece is of a T-shaped structure and comprises a transverse portion and a vertical portion, and the vertical portion extends into the sliding rail space of the sliding rail and can slide along the sliding rail space.
Preferably, two ends of the transverse part of the limiting sheet are respectively provided with a locking pin for being matched with the second groove on the wing. Specifically, a straight groove is respectively seted up at the horizontal portion both ends of spacing piece, and the assembly of locking pin can be along in a straight groove removal.
Further preferably, the locking device comprises a locking spring which is arranged in the linear groove and used for pushing the locking pin to extend out of the linear groove.
Preferably, the first slot and the second slot on the wing are respectively arranged on two sides of the connection end of the wing and the rotating shaft. Specifically, when the limiting sheet is matched with the first groove, the wing is in a compressed state; when the locking pin is matched with the second groove, the wing is in an unfolding and locking state.
Further, still include unlocking device, set up on the installation base for promote spacing piece moves along the slide rail. The unlocking device can be a spring, a motor or a fire work product and the like.
To facilitate understanding of the solution and effects of the embodiments of the present invention, a specific application example is given below. It will be understood by those skilled in the art that this example is merely for the purpose of facilitating understanding of the invention, and that any specific details thereof are not intended to limit the invention in any way.
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Referring to fig. 1, a non-coaxial folding wing synchronous unfolding mechanism for an unmanned aerial vehicle comprises: the wing unlocking device comprises an installation base 1, a wing 2, a rotating shaft 3, a limiting sheet 4, a sliding rail 5, a locking pin 6, a locking spring 7, a driving torsion spring 8 and an unlocking device 9.
The mounting base 1 provides a fixed base for the whole mechanism, and the pair of rotating shafts 3 are fixedly connected to the mounting base 1. The left wing 2 and the right wing 2 can respectively rotate freely around a pair of rotating shafts 3, and the wings 2 and the mounting base 3 are driven by a driving torsion spring 8. For example, the driving torsion spring 8 is sleeved on the rotating shaft 3, and two ends of the driving torsion spring 8 are respectively connected to the mounting base 1 and the wing 2 to provide driving force for unfolding the wing 2.
The slide rail 5 is fixedly connected to the mounting base 1. In this embodiment, the slide rail 5 is a U-shaped structure, and one side of the opening is fixedly mounted on the mounting base 1, and a slide rail space is formed between the opening and the mounting base 1.
In this embodiment, spacing piece 4 is T type structure, including horizontal portion and vertical portion, and vertical portion can slide along the slide rail space in stretching into the slide rail space of slide rail 5. The unlocking device 9 is arranged at one end of the sliding rail 5 and used for driving the limiting piece 4 to move along the sliding rail 5. The unlocking device 9 can be a spring, a motor, an initiating explosive device and other different driving devices. In this embodiment, the unlocking device 9 is a spring.
Two ends of the transverse part of the limiting sheet 4 are respectively provided with a locking pin 6 which is used for being matched with the grooves A or B on the two wings 2. Specifically, the lock pin 6 and the lock spring 7 are fitted in a linear groove on the stopper piece 4. The grooves A and B on the wing 2 are respectively used for locking the position of the wing 2 through the locking pin 6 of the limiting piece 4 in a compression state and an expansion state.
When the wing 2 is in a compressed state, the torsion spring 8 is driven to be in a compressed and screwed state, and the limiting sheet 4 is matched with the groove A on the wing 2 to lock the whole mechanism, as shown in fig. 2.
In the process of unfolding the wing 2, the limiting piece 4 is driven by the unlocking device 9 to axially move along the sliding rail 5 until the limiting piece 4 is completely separated from the groove A on the wing 2. At this time, the wing 2 is unlocked and can be driven to rotate and unfold by driving the torsion spring 8.
After the wing 2 is completely unfolded, the limiting sheet 4 is matched with the groove B on the wing 2, and meanwhile, the locking pin 6 in the limiting sheet 4 is ejected out under the driving force of the locking spring 7 to completely lock the wing 2, as shown in fig. 3.
It will be understood by those skilled in the art that the foregoing description of the embodiments of the invention is for the purpose of illustrating the beneficial effects of the embodiments of the invention only and is not intended to limit the embodiments of the invention to any of the examples given.
While various embodiments of the present invention have been described above, the above description is intended to be illustrative, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (10)
1. The utility model provides a synchronous deployment mechanism of non-coaxial folding wing of unmanned aerial vehicle which characterized in that includes:
installing a base;
one end of each rotating shaft is fixedly connected to the mounting base, and the wings can freely rotate around the rotating shafts;
the driving torsion spring is arranged between the wing and the mounting base;
the sliding rail is fixedly connected to the mounting base;
and the limiting pieces are slidably mounted on the sliding rails, can be matched with the first grooves and the second grooves on the wings respectively when moving along the sliding rails, and are used for locking the positions of the wings in a compression state and a deployment state of the wings respectively.
2. The non-coaxial folding wing synchronous unfolding mechanism for the unmanned aerial vehicle as claimed in claim 1, wherein the slide rail is of a U-shaped structure, one side of the opening is fixedly connected to the mounting base, and a slide rail space is formed between the slide rail and the mounting base.
3. The non-coaxial folding wing synchronous unfolding mechanism of an unmanned aerial vehicle according to claim 2, wherein the limiting piece is of a T-shaped structure and comprises a transverse portion and a vertical portion, and the vertical portion extends into a sliding rail space of the sliding rail.
4. The non-coaxial folding wing synchronous unfolding mechanism for the unmanned aerial vehicle as claimed in claim 3, wherein two ends of the transverse portion of the limiting piece are respectively provided with a locking pin which is matched with the second grooves on the two wings.
5. The non-coaxial folding wing synchronous unfolding mechanism for the unmanned aerial vehicle as claimed in claim 4, wherein a straight groove is formed in each of two ends of the transverse portion of the limiting piece, and the locking pin is assembled in the straight groove and can move along the straight groove.
6. The unmanned aerial vehicle non-coaxial folding wing synchronous unfolding mechanism according to claim 5, further comprising a locking spring arranged in the linear groove and used for pushing the locking pin to extend out of the linear groove.
7. The unmanned aerial vehicle non-coaxial folding wing synchronous unfolding mechanism according to claim 1, wherein the first groove and the second groove on the wing are respectively arranged on two sides of the connecting end of the wing and the rotating shaft.
8. The non-coaxial folding wing synchronous unfolding mechanism for the unmanned aerial vehicle as claimed in claim 4, wherein when the limiting piece is matched with the first groove, the wing is in a compressed state;
when the locking pin is matched with the second groove, the wing is in an unfolding and locking state.
9. The non-coaxial folding wing synchronous unfolding mechanism for unmanned aerial vehicles according to claim 1, further comprising an unlocking device arranged on the mounting base and used for pushing the limiting piece to move along the sliding rail.
10. The unmanned aerial vehicle non-coaxial folding wing synchronous unfolding mechanism of claim 9, wherein said unlocking device is a spring, a motor or a pyrotechnic product.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022645256.1U CN214451837U (en) | 2020-11-16 | 2020-11-16 | Synchronous deployment mechanism of non-coaxial folding wing of unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022645256.1U CN214451837U (en) | 2020-11-16 | 2020-11-16 | Synchronous deployment mechanism of non-coaxial folding wing of unmanned aerial vehicle |
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| CN214451837U true CN214451837U (en) | 2021-10-22 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112319797A (en) * | 2020-11-16 | 2021-02-05 | 中国航天空气动力技术研究院 | Synchronous deployment mechanism of non-coaxial folding wing of unmanned aerial vehicle |
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- 2020-11-16 CN CN202022645256.1U patent/CN214451837U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112319797A (en) * | 2020-11-16 | 2021-02-05 | 中国航天空气动力技术研究院 | Synchronous deployment mechanism of non-coaxial folding wing of unmanned aerial vehicle |
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