CN113320681A - Rotary unfolding device and unmanned aerial vehicle device - Google Patents
Rotary unfolding device and unmanned aerial vehicle device Download PDFInfo
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- CN113320681A CN113320681A CN202110735515.6A CN202110735515A CN113320681A CN 113320681 A CN113320681 A CN 113320681A CN 202110735515 A CN202110735515 A CN 202110735515A CN 113320681 A CN113320681 A CN 113320681A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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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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Abstract
The application discloses a rotary unfolding device and an unmanned aerial vehicle device, wherein the rotary unfolding device comprises a first connecting piece, a rotating assembly, a second connecting piece, a driving assembly and at least one locking assembly; the first connecting piece is used for being fixedly connected with the center position of the wing, and the second connecting piece is used for being fixedly connected with the fuselage; one end of the rotating assembly is fixedly connected with the first connecting piece, and the other end of the rotating assembly penetrates through the first connecting piece and the second connecting piece and is rotatably connected with the second connecting piece; the first connecting piece and the rotating assembly rotate synchronously; the driving assembly is arranged on one side, far away from the first connecting piece, of the second connecting piece, the driving assembly is sleeved on the rotating assembly, one end of the driving assembly is detachably and fixedly connected with the rotating assembly, and the other end of the driving assembly is fixed on the second connecting piece through the limiting piece; the locking assembly is used for locking the first connecting piece which rotates to the preset position; this application can make the wing after folding be located the fuselage top through being connected with fuselage and wing, with the fuselage basic coincidence.
Description
Technical Field
The application relates to an unmanned aerial vehicle wing folding device technical field especially relates to a rotatory device and unmanned aerial vehicle device that expandes.
Background
In recent years, the fixed-wing unmanned aerial vehicle is fast in development speed, and plays an increasingly important role in use scenes such as aerial photography, surveying and mapping, power inspection, agricultural plant protection, logistics transportation, disaster relief and the like.
As the use scenes of the unmanned aerial vehicles are more and more, the requirements on the performance and the quantity of the unmanned aerial vehicles are higher and higher, so that the unmanned aerial vehicles are larger and larger, and the number of frames needing to be moved is more; this puts new demands on the transportation launching convenience of the unmanned aerial vehicle; unmanned aerial vehicle's wing has occupied most horizontal space, dismantles or folds unmanned aerial vehicle's wing, can show the transportation demand space that reduces unmanned aerial vehicle, convenient transportation.
The wings of the fixed-wing unmanned aerial vehicle can be detached or folded; the disassembly mode has a simple structure, but the user needs training and professional skills when operating outdoors, the operation time is long, tools are needed, and the reliability is greatly influenced by human factors. The folding mode needs a folding mechanism, but has low requirements on users, short operation time, convenient operation and high reliability, and particularly, the automatic unfolding mechanism does not need user operation and is completely free from the influence of human factors of the users.
The wings in the left-right direction are folded into the front-back fuselage direction, so that the left-right and up-down sizes of the whole machine in a transportation state are minimized, and the transportation is convenient. The wing rotary folding scheme has the technical scheme that at present, a rotary mechanism is respectively arranged at the roots of the wings on the left side and the right side. The two wings respectively realize folding or unfolding through respective rotating mechanisms and rotating motion. After the scheme is used, the width of the whole machine is still wide, and two sets of rotating mechanisms are arranged.
The wings of the fixed-wing unmanned aerial vehicle are long, so that the size of the whole unmanned aerial vehicle in the left and right directions is large, the transportation space is large, and the transportation is inconvenient. The wings in the left and right directions are disassembled or folded into the front and back directions of the fuselage, so that the transportation space can be obviously reduced. The scheme of the detachable wing is inconvenient for users to operate outdoors and low in reliability. In the existing folding wing scheme, the size is still large after folding, the two wings are two independent parts, two sets of mechanisms are needed, and the reliability of the whole machine is slightly poor.
Disclosure of Invention
In order to solve the technical problem, the rotary unfolding device disclosed in the application can drive the wings to rotate around the fuselage through being connected with the fuselage and the wings, and the wings are folded along the fuselage direction, so that the folded wings are located above the fuselage and basically coincide with the fuselage, and when the unmanned aerial vehicle is in a folded state, the whole size is small, the transportation space required by the whole machine is minimum, and the transportation is convenient.
In order to achieve the above object, the present application provides a rotary deployment device comprising a first connector, a rotation assembly, a second connector, a drive assembly, and at least one locking assembly;
the first connecting piece is used for being fixedly connected with the center position of the wing, and the second connecting piece is used for being fixedly connected with the fuselage;
one end of the rotating assembly is fixedly connected with the first connecting piece, and the other end of the rotating assembly penetrates through the first connecting piece and the second connecting piece and is rotatably connected with the second connecting piece; the first connecting piece and the rotating assembly rotate synchronously;
the driving assembly is arranged on one side, far away from the first connecting piece, of the second connecting piece, the driving assembly is sleeved on the rotating assembly, one end of the driving assembly is detachably and fixedly connected with the rotating assembly, and the other end of the driving assembly is fixed on the second connecting piece through a limiting piece;
the locking assembly is used for locking the first connecting piece which rotates to the preset position.
In one embodiment, the rotating assembly includes a rotating shaft and a sliding bushing; the sliding bush is arranged on the rotating shaft,
the rotating shaft is rotatably connected with the second connecting piece through the sliding bush.
In one embodiment, the driving assembly comprises a driving member and a fixed seat, and the driving member is sleeved on the fixed seat;
the fixed seat is sleeved on the rotating shaft;
one end of the driving piece is detachably and fixedly connected with the rotating assembly, and the other end of the driving piece is fixed on the second connecting piece through a limiting piece;
the limiting part is used for limiting the driving part.
In one embodiment, a groove is formed at the end part of the rotating shaft sleeved with the fixed seat;
the fixing seat is provided with an opening, and the driving piece penetrates through the opening and is matched with the groove to realize driving.
In one embodiment, the driving member is a torsion spring, and the torsion spring is sleeved on the fixed seat;
one end of the torsion spring penetrates through the opening part and is inserted into the groove, and the other end of the torsion spring is fixed on the second connecting piece through the limiting piece.
In one embodiment, the locking device further comprises a locking assembly, wherein the locking assembly is arranged at one end of the second connecting piece far away from the first connecting piece;
the locking assembly is used for locking the rotating assembly on the second connecting piece.
In one embodiment, the locking assembly includes a spacing washer and a nut;
the limiting washer is sleeved on the rotating assembly;
the nut is arranged on one side, far away from the second connecting piece, of the limiting washer and is fixedly connected with the rotating assembly.
In one embodiment, there are two of the locking assemblies;
one end of the locking component is fixedly connected with the first connecting piece, and the other end of the locking component is in sliding connection or butt joint with the second connecting piece.
In one embodiment, the locking assembly comprises a housing, a spring and a shaft pin, wherein the spring and the shaft pin are arranged in the housing, and the shaft pin can move back and forth along the axial direction of the housing;
one end of the spring is fixedly connected with the first end of the shell, and the other end of the spring is fixedly connected with the shaft pin; one end of the shaft pin, which is far away from the spring, can extend out of the shell;
one end of the shell is fixedly connected with the first connecting piece, and the other end of the shell is provided with an opening;
the shaft pin can penetrate through the opening to be in sliding connection with the through hole in the second connecting piece or abut against the second connecting piece.
The application also describes an unmanned aerial vehicle device comprising a fuselage, wings, and a rotary deployment device; the rotary unfolding device is the rotary unfolding device; the wings comprise a left wing and a right wing which are of an integrated structure;
the first connecting piece of the rotary unfolding device is fixedly connected with the central position of the wing; the second connecting piece is fixedly connected with the machine body;
the rotating assembly drives the wings to rotate around the fuselage through the first connecting piece, so that the wings rotate to form a preset angle with the fuselage, and the preset angle is 0-90 degrees.
The embodiment of the invention has the following beneficial effects:
the rotary unfolding device disclosed by the invention is connected with the fuselage and the wings, so that the wings can be driven to rotate around the fuselage and be folded along the fuselage direction, and the folded wings are positioned above the fuselage and basically coincide with the fuselage, so that the size of the whole unmanned aerial vehicle is smaller when the unmanned aerial vehicle is in a folded state, the transportation space required by the whole unmanned aerial vehicle is minimum, and the unmanned aerial vehicle is convenient to transport.
The utility model discloses an unmanned aerial vehicle device, wing and the rotatory device that expandes through the integrative structure that sets up for the wing can coincide basically with the fuselage when folding, makes unmanned aerial vehicle also be when arranging in the carrier about the complete machine under the transportation state with the top and bottom size less, is showing and is reducing the transportation space, convenient transportation.
Drawings
In order to more clearly illustrate the technical solutions and advantages of the embodiments of the present application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic illustration of an exploded view of a rotary deployment device as provided herein;
FIG. 2 is a schematic view of the assembled structure of the rotary deployment device;
FIG. 3 is a schematic view of an assembled structure of the driving assembly;
FIG. 4 is an assembled view of the first connector;
FIG. 5 is a schematic view of an assembled structure of the second connecting member;
FIG. 6 is a schematic structural view of the locking assembly;
fig. 7 is a schematic structural view of the drone with the wings in the deployed state;
fig. 8 is a schematic structural view of the drone with the wings in a folded state;
wherein the reference numerals in the figures correspond to: 1-a first connecting piece, 101-a first opening, 2-a rotating component, 201-a rotating shaft, 2011-a groove, 202-a sliding bush, 3-a second connecting piece, 301-a second opening, 4-a driving component, 401-a driving component, 402-a fixed seat, 4021-an opening part, 5-a locking component, 501-a shell, 502-a spring, 503-a shaft pin, 6-a locking component, 601-a limiting washer, 602-a nut, 7-a fuselage, 8-a wing and 9-a limiting component.
Detailed Description
To make the objects, technical solutions and advantages of the present application more clear, the present application will be further described in detail with reference to the accompanying drawings.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. The terms "comprising" and "having," as well as any variations thereof, are intended to cover non-exclusive inclusions. In different embodiment variants, identical components have the same reference numerals.
Example 1
As shown in fig. 1-5, the present application provides a rotary deployment device comprising a first linkage 1, a rotation assembly 2, a second linkage 3, a drive assembly 4, and at least one locking assembly 5;
the first connecting piece 1 is used for being fixedly connected with the central position of a wing 8, and the second connecting piece 3 is used for being fixedly connected with a fuselage 7;
one end of the rotating assembly 2 is fixedly connected with the first connecting piece 1, and the other end of the rotating assembly passes through the first connecting piece 1 and the second connecting piece 3 and is rotatably connected with the second connecting piece 3; the first connecting piece 1 and the rotating assembly 2 rotate synchronously;
the driving component 4 is arranged on one side of the second connecting piece 3 far away from the first connecting piece 1, the driving component 4 is sleeved on the rotating component 2, one end of the driving component 4 is detachably and fixedly connected with the rotating component 2, and the other end of the driving component 4 is fixed on the second connecting piece 3 through a limiting piece 9;
the locking assembly 5 is used for locking the first connecting piece 1 which rotates to a preset position; this application can drive wing 8 and rotate around fuselage 7 through being connected with fuselage 7 and wing 8, folds in the same direction as fuselage 7 direction for wing 8 after folding is located the fuselage top, coincides basically with fuselage 7, makes unmanned aerial vehicle when fold condition, and whole quick-witted size is less, and the required transportation space of complete machine is minimum, and convenient transportation.
The preset position may be a position when the wing 8 is fully deployed, and specifically may be a position where the wing 8 and the fuselage 7 form an included angle of 90 °.
In the embodiment of the present specification, preferably, the first connecting member 1 may be a connecting disc; the second connecting member 3 may be a connecting disc;
specifically, as shown in fig. 4, the first connecting member 1 may be fixedly connected to a rib of the wing 8 by a screw; as shown in fig. 5, the second connecting member 3 may be fixedly connected to the body frame of the body 7 by screws.
Specifically, the first connecting piece 1 is covered on the second connecting piece 3, and the first connecting piece 1 and the second connecting piece 3 can move freely.
In the present embodiment, as shown in fig. 1, the rotating assembly 2 includes a rotating shaft 201 and a sliding bush 202; the sliding bush 202 is disposed on the rotating shaft 201;
the rotating shaft 201 is rotatably connected to the second connecting member 3 through the sliding bush 202.
Specifically, the sliding bush 202 is sleeved on the rotating shaft 201 and fixedly connected with the rotating shaft 201;
in the embodiment of the present specification, a first opening 101 is formed in the first connecting member 1, and the first connecting member is sleeved on the rotating assembly 2 through the first opening 101;
a second opening 301 is formed in the second connecting piece 3, and the second connecting piece 3 is sleeved on the rotating assembly 2 through the second opening 301 and is rotatably connected with the rotating assembly 2;
specifically, the second connecting member 3 is sleeved on the sliding bush 202 through the second opening 301, and the third connecting member 3 is rotatably connected with the sliding bush 202;
in the embodiment of the present disclosure, as shown in fig. 2 and fig. 3, the driving assembly 4 includes a driving member 401 and a fixing seat 402, where the driving member 401 is sleeved on the fixing seat 402;
the fixed seat 402 is sleeved on the rotating shaft 201;
one end of the driving piece 401 is detachably and fixedly connected with the rotating assembly 2, and the other end is fixed on the second connecting piece 3 through a limiting piece;
the limiting part 9 is used for limiting the driving part 401.
Specifically, in the embodiment of the present specification, a groove 2011 is formed at an end of the rotating shaft 201 that is sleeved with the fixing seat 402;
an opening 4021 is formed in the fixing seat 402, and the driving piece 401 penetrates through the opening 4021 to be matched with the groove 2011 to achieve driving.
Specifically, after the rotating shaft 201 is inserted into the fixing seat 402, the groove 2011 corresponds to the position of the opening 4021.
Specifically, the limiting part 9 can be a limiting screw, the limiting part 9 is fixedly disposed on one side of the second connecting part 3 away from the first connecting part 1, one end of the driving part 401 is relatively fixed to the position of the second connecting part 3 through the limiting part 9, and the other end of the driving part is inserted into the groove 2011 of the rotating shaft 201 and is detachably and fixedly connected with the rotating shaft 201.
In the embodiment of the present disclosure, preferably, the driving member 401 is a torsion spring, and the torsion spring is sleeved on the fixing seat 402;
one end of the torsion spring passes through the opening 4021 and is inserted into the groove 2011, and the other end of the torsion spring is fixed on the second connecting piece 3 through a limiting piece.
In the embodiment of the specification, the locking device further comprises a locking assembly 6, wherein the locking assembly 6 is arranged at one end of the second connecting piece 3 far away from the first connecting piece 1;
the locking assembly 6 is used to lock the rotating assembly 2 to the second connecting member 3.
Specifically, as shown in fig. 1, the locking assembly 6 includes a limit washer 601 and a nut 602;
the limiting gasket sleeve 601 is arranged on the rotating component 2; the limiting washer 601 is used for limiting the rotating assembly 2;
the nut 602 is disposed on a side of the limiting washer 601 away from the second connector 3, and the nut 602 is fixedly connected to the rotating assembly 2.
In the embodiment of the present specification, the locking assemblies 5 are provided in two;
one end of the locking component 5 is fixedly connected with the first connecting piece 1, and the other end of the locking component is in sliding connection or abutting connection with the second connecting piece 3.
Specifically, the first connecting piece 1 is used as an initial position when driving the wing 8 to be in the unfolding position; the stopping position is taken as an example for explanation when the first connecting piece 1 drives the wing 8 to be in the folding position;
when the first connecting piece 1 rotates to the initial position along with the rotating shaft 201, the locking assembly 5 is connected with the second connecting piece 3 in a sliding manner, specifically, the locking assembly 5 is inserted into a locking hole in the second connecting piece 3, so that the positions of the first connecting piece 1 and the second connecting piece 3 are relatively fixed;
when the first connecting piece 1 rotates to the stop position along with the rotating shaft 201, the locking assembly 5 abuts against the second connecting piece 3, specifically, one end of the locking assembly 5 abuts against one side surface of the second connecting piece 3 close to the first connecting piece 1.
Specifically, as shown in fig. 6, the locking assembly 5 includes a housing 501, a spring 502 and a shaft pin 503, the spring 502 and the shaft pin 503 are both disposed in the housing 501, and the shaft pin 503 can reciprocate along the axial direction of the housing 501;
one end of the spring 502 is fixedly connected with a first end of the shell 501, and the other end of the spring is fixedly connected with the shaft pin 503; the end of the pin 503 remote from the spring 502 can extend out of the housing 501;
one end of the outer shell 501 is fixedly connected with the first connecting piece 1, and the other end of the outer shell is provided with an opening;
the axle pin 503 can pass through the opening to be slidably connected with the through hole of the second connector 3 or abut against the second connector 3.
Example 2
The application provides an unmanned aerial vehicle device, which comprises a fuselage 7, wings 8 and a rotary unfolding device; the rotary unfolding device is the rotary unfolding device in the embodiment; the wings 8 comprise a left wing and a right wing which are of an integral structure;
specifically, the rotary unfolding device is positioned above the fuselage 7, and a first connecting piece 1 of the rotary unfolding device is fixedly connected with the central position of the wing 8; the second connecting piece 3 is fixedly connected with the machine body 7;
the left wing and the right wing are identical in structural shape, and the central position of the wing 8 is the center of the connecting position of the left wing and the right wing;
the rotating assembly 2 drives the wing 8 to rotate around the fuselage 7 through the first connecting piece 1, so that the wing 8 rotates to form a preset angle with the fuselage 7, and the preset angle is 0-90 degrees.
Specifically, as shown in fig. 7, when the wings 8 of the unmanned aerial vehicle are in the deployed position, the wings 8 and the fuselage 7 form an angle of 90 °, so that the unmanned aerial vehicle can normally run;
specifically, as shown in fig. 8, when the wings 8 of the unmanned aerial vehicle are in a folded state, the wings 8 are located above the fuselage 7 and substantially coincide with the fuselage 7; make 8 folding back unmanned aerial vehicle's of wing horizontal size less, and can place unmanned aerial vehicle in the carrier this moment, after unmanned aerial vehicle launches, 8 automatic expandes of wing.
Specifically, when the drone is stored in the vehicle, the wing 8 is in a folded state, at which time the driving member 401 is compressed; after the unmanned aerial vehicle leaves the carrier, the driving piece 401 drives the first connecting piece 1 to rotate, so that the rotating shaft 201 drives the first connecting piece 1 to rotate, and further the rotation of the wing 8 is driven to be unfolded, and the wing 8 is unfolded to a flying state.
The utility model discloses an unmanned aerial vehicle device, wing and the rotatory device that expandes through the integrative structure that sets up for the wing can coincide basically with the fuselage when folding, makes unmanned aerial vehicle also be when arranging in the carrier about the complete machine under the transportation state with the top and bottom size less, is showing and is reducing the transportation space, convenient transportation.
The above disclosure is only one preferred embodiment of the present application, and certainly does not limit the scope of the present application, which is therefore intended to cover all modifications and equivalents of the claims.
Claims (10)
1. A rotary deployment device characterized by: comprises a first connecting piece (1), a rotating component (2), a second connecting piece (3), a driving component (4) and at least one locking component (5);
the first connecting piece (1) is fixedly connected with the center of the wing (8), and the second connecting piece (3) is fixedly connected with the fuselage (7);
one end of the rotating assembly (2) is fixedly connected with the first connecting piece (1), and the other end of the rotating assembly penetrates through the first connecting piece (1) and the second connecting piece (3) and is rotatably connected with the second connecting piece (3); the first connecting piece (1) and the rotating component (2) rotate synchronously;
the driving assembly (4) is arranged on one side, far away from the first connecting piece (1), of the second connecting piece (3), the driving assembly (4) is sleeved on the rotating assembly (2), one end of the driving assembly (4) is detachably and fixedly connected with the rotating assembly (2), and the other end of the driving assembly (4) is fixed on the second connecting piece (3) through a limiting piece (9);
the locking assembly (5) is used for locking the first connecting piece (1) which rotates to a preset position.
2. The rotary deployment device of claim 1, wherein: the rotating assembly (2) comprises a rotating shaft (201) and a sliding bush (202); the sliding bush (202) is arranged on the rotating shaft (201),
the rotating shaft (201) is rotatably connected with the second connecting piece (3) through the sliding bush (202).
3. The rotary deployment device of claim 2, wherein: the driving assembly (4) comprises a driving part (401) and a fixed seat (402), and the driving part (401) is sleeved on the fixed seat (402);
the fixed seat (402) is sleeved on the rotating shaft (201);
one end of the driving piece (401) is detachably and fixedly connected with the rotating assembly (2), and the other end of the driving piece is fixed on the second connecting piece (3) through a limiting piece;
the limiting part (9) is used for limiting the driving part (401).
4. The rotary deployment device of claim 2, wherein: a groove (2011) is formed in the end part, sleeved with the fixed seat (402), of the rotating shaft (201);
an opening part (4021) is arranged on the fixed seat (402), and the driving part (401) penetrates through the opening part (4021) to be matched with the groove (2011) to realize driving.
5. The rotary deployment device of claim 4, wherein: the driving piece (401) is a torsion spring, and the torsion spring is sleeved on the fixed seat (402);
one end of the torsion spring penetrates through the opening part (4021) and is inserted into the groove (2011), and the other end of the torsion spring is fixed on the second connecting piece (3) through a limiting piece.
6. The rotary deployment device of claim 1, wherein: the locking device further comprises a locking assembly (6), wherein the locking assembly (6) is arranged at one end, far away from the first connecting piece (1), of the second connecting piece (3);
the locking assembly (6) is used for locking the rotating assembly (2) on the second connecting piece (3).
7. The rotary deployment device of claim 6, wherein: the locking assembly (6) comprises a limiting washer (601) and a nut (602);
the limiting washer (601) is sleeved on the rotating assembly (2);
the nut (602) is arranged on one side, far away from the second connecting piece (3), of the limiting washer (601) and is fixedly connected with the rotating assembly (2).
8. The rotary deployment device of claim 1, wherein: the number of the locking assemblies (5) is two;
one end of the locking component (5) is fixedly connected with the first connecting piece (1), and the other end of the locking component is connected with or abutted against the second connecting piece (3) in a sliding manner.
9. The rotary deployment device of claim 8, wherein: the locking assembly (5) comprises a shell (501), a spring (502) and a shaft pin (503), wherein the spring (502) and the shaft pin (503) are both arranged in the shell (501), and the shaft pin (503) can move back and forth along the axial direction of the shell (501);
one end of the spring (502) is fixedly connected with the first end of the shell (501), and the other end of the spring is fixedly connected with the shaft pin (503); one end of the shaft pin (503) far away from the spring (502) can extend out of the shell (501);
one end of the shell (501) is fixedly connected with the first connecting piece (1), and the other end of the shell is provided with an opening;
the shaft pin (503) can pass through the opening to be in sliding connection with the through hole on the second connecting piece (3) or abut against the second connecting piece (3).
10. An unmanned aerial vehicle device, its characterized in that: comprises a fuselage (7), wings (8) and a rotary unfolding device; the rotary deployment device is the rotary deployment device of any one of claims 1-9; the wings (8) comprise a left wing and a right wing which are of an integral structure;
the first connecting piece (1) of the rotary unfolding device is fixedly connected with the central position of the wing (8); the second connecting piece (3) is fixedly connected with the machine body (7);
the rotating assembly (2) drives the wings (8) to rotate around the fuselage (7) through the first connecting piece (1), so that the wings (8) rotate to a preset angle with the fuselage (7), and the preset angle is 0-90 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110735515.6A CN113320681B (en) | 2021-06-30 | 2021-06-30 | Rotatory expansion device and unmanned aerial vehicle device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110735515.6A CN113320681B (en) | 2021-06-30 | 2021-06-30 | Rotatory expansion device and unmanned aerial vehicle device |
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| CN113320681A true CN113320681A (en) | 2021-08-31 |
| CN113320681B CN113320681B (en) | 2023-05-05 |
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| 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 |
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| US20130146716A1 (en) * | 2011-12-13 | 2013-06-13 | The Boeing Company | Mechanisms for Deploying and Actuating Airfoil-Shaped Bodies on Unmanned Aerial Vehicles |
| WO2020022972A2 (en) * | 2017-12-27 | 2020-01-30 | Roketsan Roket Sanayii Ticaret A.S | Wing deployment mechanism |
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| CN113320681B (en) | 2023-05-05 |
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