CN112520015B - Convertible aviation folding blade - Google Patents
Convertible aviation folding blade Download PDFInfo
- Publication number
- CN112520015B CN112520015B CN202011341304.6A CN202011341304A CN112520015B CN 112520015 B CN112520015 B CN 112520015B CN 202011341304 A CN202011341304 A CN 202011341304A CN 112520015 B CN112520015 B CN 112520015B
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- Prior art keywords
- telescopic cylinder
- external
- blade
- blade body
- lateral
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/28—Collapsible or foldable blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/24—Arrangement of propulsion plant
- B64B1/30—Arrangement of propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C27/50—Blades foldable to facilitate stowage of aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Tents Or Canopies (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
The invention relates to the technical field of aviation parts, in particular to a turnover aviation folding blade which comprises an external connecting seat, an external connecting shaft and a blade body, wherein the external connecting shaft is axially and fixedly connected with an outer side rotating shaft of a transmission motor through a coupler. The turnover type aviation folding blade is characterized in that the turnover type aviation folding blade comprises an external connecting seat, an external connecting shaft and a blade body, wherein the blade body is of an L-shaped structure and is movably connected with the external connecting shaft through a lateral mounting bracket, and the turnover type aviation folding blade can be stored outside through turnover folding in an idle state, so that the occupation of the external space of the aviation blade is greatly reduced; the outer side surface of the external connecting seat is provided with a lateral installation slot for being matched with the installation and fixation of the blade body and an annular thread adjusting groove with an internal thread locking ring, so that the structural stability and the firmness of the blade after installation are improved while the assembly and the disassembly are convenient, and the operation is simple and convenient; the angle can be adjusted according to the needs, and the application range is wider.
Description
Technical Field
The invention relates to the technical field of aviation parts, in particular to a turnover aviation folding blade.
Background
Aviation, a complex and strategically significant human activity. Refers to the flight (navigation) activities of an aircraft in the earth's atmosphere (air space), and the fields related to the flight (navigation) activities, such as scientific education, industrial manufacturing, public transportation, professional work, aviation sports, national defense and military, government management and the like. By the use of aerospace and aircraft (aircraft), aviation activities can be subdivided into a number of independent industries and fields, typically such as the aeronautical manufacturing industry, civil aviation industry, and the like. It is often seen that people use this word from their respective fields, their connotations and their abundance and variety.
Aircraft engaged in flight activities, also known as aircraft, are classified as lighter-than-air aircraft and heavier-than-air aircraft. The former relies on aerostatic buoyancy to lift off, such as a balloon, airship, etc., and the latter relies on aerodynamic lift off generated by relative motion with air, such as an aircraft, helicopter, etc. According to whether people are carried or not, the unmanned aerial vehicle can be divided into an unmanned aerial vehicle and an unmanned aerial vehicle.
Aviation blade on the aircraft is the important power equipment spare part of aircraft, and traditional aviation blade structure is single fixed, can't fold, leads to under the idle state structural space to occupy greatly, accomodates very inconvenient.
Disclosure of Invention
The invention aims to solve the technical problems that: in order to solve the problems in the prior art, an improved turnover aviation folding blade is provided, and the problems that the traditional aviation blade is single in structure and cannot be folded, so that the occupied structural space in an idle state is large and the storage is inconvenient are solved.
The technical scheme adopted for solving the technical problems is as follows: the utility model provides a convertible aviation folding blade, includes the external connection seat, passes through shaft coupling axial fixed connection's external connection axle and blade body with the transmission motor outside pivot, the external connection axle lateral surface on fixedly connected with be used for the side mounting bracket of swing joint blade body, the blade body be L type structure, the blade body through the horizontal pivot and the side mounting bracket swing joint of top both sides, external connection seat internally connected have the internally mounted axle section of thick bamboo that is used for assembling fixed external connection axle, the external connection seat lateral surface on set up and be used for the fixed side mounting slot of cooperation blade body installation, the external connection seat lateral surface be located side mounting slot open position and set up the annular thread adjustment groove of built-in internal thread locking ring, the external connection seat lateral surface be located the outside mounting slot inboard and have the externally mounted seat of built-in horizontal locking bolt, the internal thread locking ring inside set up the horizontal assembly through-hole, the external connection seat left side inner wall on set up right side open-ended spherical storage tank, the internally mounted axle section of thick bamboo left end be located spherical storage tank inside and have an organic whole structure spherical storage head, the external connection seat lateral surface have an arc-shaped interior expansion cylinder inside the arc-shaped expansion cylinder, the inside expansion cylinder has an arc-shaped expansion cylinder inside the arc-shaped expansion cylinder.
The blade body penetrates through the lateral movable support and the lateral mounting support through the transverse rotating shaft to be movably connected, and the outer assembly pipe is fixedly connected with the outer side of the outer connecting shaft through the lateral locking bolt.
The elastic bolt locking device comprises an inner extrusion spring inserted into the outer telescopic cylinder and the inner telescopic cylinder and an inner locking bolt installed on the outer telescopic cylinder, wherein the inner telescopic cylinder is internally provided with symmetrically arranged transverse adjusting through holes, and the inner locking bolt is fixedly connected with the inner telescopic cylinder by penetrating through the transverse adjusting through holes to control the outer telescopic cylinder.
The outer sides of the outer telescopic cylinder and the inner telescopic cylinder are provided with arc-shaped adjusting holes matched with the inner locking bolts.
There is no gap between the inner side surface of the spherical storage groove and the outer side connecting surface of the spherical assembly head, and there is no gap between the inner side surface of the outer telescopic cylinder and the outer side surface of the inner telescopic cylinder.
The external side surface of the internal thread locking ring and the external side surface of the blade body are respectively provided with an integral structure engagement tooth surface.
The blade body comprises an external turning blade and an L-shaped structure internal connecting rod welded and fixed at the connecting top end of the external turning blade.
The beneficial effects of the invention are as follows:
(1) The turnover type aviation folding blade is characterized in that the turnover type aviation folding blade comprises an external connecting seat, an external connecting shaft and a blade body, wherein the blade body is of an L-shaped structure and is movably connected with the external connecting shaft through a lateral mounting bracket, and the turnover type aviation folding blade can be stored outside through turnover folding in an idle state, so that the occupation of the external space of the aviation blade is greatly reduced;
(2) The outer side surface of the external connecting seat is provided with a lateral installation slot for being matched with the installation and fixation of the blade body and an annular thread adjusting groove with an internal thread locking ring, so that the structural stability and the firmness of the blade after installation are improved while the assembly and the disassembly are convenient, and the operation is simple and convenient;
(3) The internal installation shaft barrel is connected to the inside of the external connecting seat, the installation mode of the external connection seat is adjusted by matching with the elastic bolt locking device on the internal telescopic barrel through the external telescopic barrel sleeve, so that the stability and the safety of the external connection seat can be changed as required, the angle can be adjusted as required, and the application range is wider.
Drawings
The invention will be further described with reference to the drawings and examples.
Fig. 1 is a schematic structural view of the present invention.
Fig. 2 is an internal cross-sectional view of the external connection socket of the present invention.
Fig. 3 is a partial cross-sectional view of the assembled end of the blade body of the present invention.
Detailed Description
The invention will now be described in further detail with reference to the accompanying drawings. The drawings are simplified schematic representations which merely illustrate the basic structure of the invention and therefore show only the structures which are relevant to the invention.
The utility model provides a convertible aviation folding blade that fig. 1, fig. 2 and fig. 3 show, including outer connecting seat 1, pass through shaft coupling axial fixed connection's external connection axle 2 and blade body 3 with the transmission motor outside pivot, fixedly connected with is used for the side mounting bracket 4 of swing joint blade body 3 on the external connection axle 2 lateral surface, the blade body is L type structure, the blade body 3 is through the horizontal pivot and the side mounting bracket 4 swing joint of top both sides, external connection seat 1 internal connection has an internally mounted axle section of thick bamboo 5 that is used for assembling fixed external connection axle 2, set up on the external connection seat 1 lateral surface and be used for cooperating the fixed side mounting slot 6 of blade body 3 installation, the annular thread adjustment groove 8 of built-in internal thread locking ring 7 has been seted up to external connection seat 1 lateral surface position in side mounting slot 6 opening position, the external mounting seat 10 that the internal thread locking ring 7 is inside has been seted up horizontal assembly through-hole 11, set up right side open-ended spherical storage groove 12 on the left side inner wall of external connection seat 1, the inside end of an internally mounted axle section of thick bamboo 5 is located spherical storage groove 12 internal connection 1 internal connection seat 13, an internally mounted axle section of thick bamboo 15 internal connection 15 has an integrated arc-shaped expansion cylinder 15 internal expansion joint 15, the inside expansion joint 15 is located between the arc-shaped expansion cylinder internal expansion joint 15.
Examples: the blade body 3 is turned over towards the external connecting seat 1, is inserted into the side mounting slot 6, then penetrates through the inside of the blade body by using the transverse locking bolt 9, and is matched with the internal thread locking ring 7 to be mounted and fixed, so that the mounting firmness and stability of the blade body are improved; the outer telescopic cylinder 14 is then inserted into the inner telescopic cylinder 15, thereby controlling the connection of the outer connection socket 1 and the inner mounting shaft cylinder 5.
Further, for easy installation and storage, the lateral mounting bracket 4 includes an outer mounting pipe 16 sleeved outside the outer connecting shaft 2, a lateral movable bracket 17 welded and fixed on the outer side surface of the outer mounting pipe 16, and a lateral locking bolt 18 screwed outside the outer mounting pipe 16, the blade body 3 penetrates through the lateral movable bracket 17 and the lateral mounting bracket 4 through a transverse rotating shaft to be movably connected, and the outer mounting pipe 16 is fixedly connected with the outer side of the outer connecting shaft 2 through the lateral locking bolt 18.
Further, for cooperation assembly and regulation, the elastic bolt locking device includes the inside extrusion spring 19 of pegging graft in outside telescopic cylinder 14 and inside telescopic cylinder 15 and installs the inside locking bolt 20 on outside telescopic cylinder 14, inside the horizontal regulation through-hole 21 of symmetry setting of seting up of inside telescopic cylinder 15, inside locking bolt 20 is through running through horizontal regulation through-hole 21 inside control outside telescopic cylinder 14 and inside telescopic cylinder 15 fixed connection, further, for cooperation elasticity shock attenuation and angle modulation, outside telescopic cylinder 14 and inside telescopic cylinder 15 outside all have seted up with inside locking bolt 20 matched with arc regulation hole 22.
Examples: when the inner locking bolt 20 is inserted into the transverse adjusting through hole 21 in the outer telescopic cylinder 14 and the inner telescopic cylinder 15, the outer telescopic cylinder 14 is fixedly connected with the inner telescopic cylinder 15, and when the inner locking bolt 20 is inserted into the arc adjusting hole 22 in the outer telescopic cylinder 14 and the inner telescopic cylinder 15, the outer telescopic cylinder 14 is elastically connected with the inner telescopic cylinder 15 through the inner extrusion spring 19.
Further, in order to improve the fitting fit, there is no gap between the inner side surface of the spherical receiving groove 12 and the outer side connecting surface of the spherical fitting head 13, and there is no gap between the inner side surface of the outer telescopic tube 14 and the outer side surface of the inner telescopic tube 15.
Further, in order to improve the stability of assembly, the external side surface of the internal thread locking ring 7 and the external side surface of the blade body 3 are provided with an integral structure engagement tooth surface, and further, in order to facilitate assembly and adjustment, the blade body 3 is composed of an external turning blade 23 and an L-shaped structure internal connecting rod 24 welded and fixed at the connecting top end of the external turning blade 23.
The turnover type aviation folding blade is characterized in that the external connecting seat 1, the external connecting shaft 2 and the blade body 3 are arranged on the outer side of the blade body 3, the blade body 3 is in an L-shaped structure, and is movably connected with the external connecting shaft 2 through the lateral mounting bracket 4, and can be folded and stored outside through turnover in an idle state, so that the occupation of the external space of the aviation blade is greatly reduced; the outer side surface of the external connecting seat 1 is provided with a lateral installation slot 6 for being matched with the installation and the fixation of the blade body 3 and an annular thread adjusting groove 8 internally provided with an internal thread locking ring 7, so that the structural stability and the firmness of the installed blade are improved while the assembly and the disassembly are convenient, and the operation is simple and convenient; the inner installation shaft barrel 5 is connected to the inner part of the outer connecting seat 1, the outer telescopic barrel 14 is sleeved on the inner telescopic barrel 15 to be matched with the elastic bolt locking device to adjust the installation mode of the outer telescopic barrel, so that the stability and the safety of the outer telescopic barrel can be changed according to the needs, the angle can be adjusted according to the needs, and the application range is wider.
With the above-described preferred embodiments according to the present invention as an illustration, the above-described descriptions can be used by persons skilled in the relevant art to make various changes and modifications without departing from the scope of the technical idea of the present invention. The technical scope of the present invention is not limited to the description, but must be determined according to the scope of claims.
Claims (7)
1. The utility model provides a convertible aviation folding blade, includes external connection seat (1), passes through shaft coupling axial fixed connection's external connection axle (2) and blade body (3) with driving motor outside pivot, characterized by: the utility model is characterized in that a lateral mounting bracket (4) for movably connecting a blade body (3) is fixedly connected to the outer side face of the external connecting shaft (2), the blade body (3) is of an L-shaped structure, the blade body (3) is movably connected with the lateral mounting bracket (4) through a transverse rotating shaft at the two sides of the top end, an internal mounting shaft barrel (5) for assembling and fixing the external connecting shaft (2) is connected to the inner side of the external connecting shaft (1), a lateral mounting slot (6) for being matched with the blade body (3) to be mounted and fixed is arranged on the outer side face of the external connecting shaft (1), an annular thread adjusting groove (8) for internally arranging an internal thread locking ring (7) is arranged at the opening position of the lateral mounting slot (6), an external mounting seat (10) for internally arranging a transverse locking bolt (9) is arranged at the inner side of the lateral mounting slot (6), a spherical mounting groove (12) is arranged on the left inner side wall of the external connecting shaft (1), a spherical mounting groove (12) is arranged at the inner side of the spherical mounting groove (12), the outer connecting seat (1) is provided with an outer telescopic cylinder (14) with an integrated arc structure on the inner arc surface, the outer side surface of the inner installation shaft cylinder (5) is provided with an inner telescopic cylinder (15) with an integrated arc structure, and the outer telescopic cylinder (14) and the inner telescopic cylinder (15) are connected through an elastic bolt locking device.
2. A roll-over aeronautical folding blade according to claim 1, wherein: the side direction installing support (4) including cup joint outside dress pipe (16) in the outside of external connection axle (2), welded fastening lateral movable support (17) on the lateral surface of outside dress pipe (16) and threaded connection lateral locking bolt (18) in the outside of outside dress pipe (16), blade body (3) run through lateral movable support (17) and side direction installing support (4) swing joint through horizontal pivot, outside dress pipe (16) through lateral locking bolt (18) and outside fixed connection in outside external connection axle (2).
3. A roll-over aeronautical folding blade according to claim 1, wherein: the elastic bolt locking device comprises an inner extrusion spring (19) inserted into the outer telescopic cylinder (14) and the inner telescopic cylinder (15) and an inner locking bolt (20) arranged on the outer telescopic cylinder (14), wherein symmetrically arranged transverse adjusting through holes (21) are formed in the inner telescopic cylinder (15), and the inner locking bolt (20) is used for fixedly connecting the outer telescopic cylinder (14) with the inner telescopic cylinder (15) by penetrating through the transverse adjusting through holes (21).
4. A flip aeronautical folding blade according to claim 3, wherein: the outer sides of the outer telescopic cylinder (14) and the inner telescopic cylinder (15) are respectively provided with an arc-shaped adjusting hole (22) matched with the inner locking bolt (20).
5. A roll-over aeronautical folding blade according to claim 1, wherein: there is no gap between the inner side surface of the spherical storage groove (12) and the outer side connecting surface of the spherical assembly head (13), and there is no gap between the inner side surface of the outer telescopic cylinder (14) and the outer side surface of the inner telescopic cylinder (15).
6. A roll-over aeronautical folding blade according to claim 1, wherein: the external side surface of the internal thread locking ring (7) and the external side surface of the blade body (3) are respectively provided with an integral structure engagement tooth surface.
7. A roll-over aeronautical folding blade according to claim 1, wherein: the blade body (3) consists of an external turning blade (23) and an L-shaped structure internal connecting rod (24) welded and fixed at the connecting top end of the external turning blade (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011341304.6A CN112520015B (en) | 2020-11-25 | 2020-11-25 | Convertible aviation folding blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011341304.6A CN112520015B (en) | 2020-11-25 | 2020-11-25 | Convertible aviation folding blade |
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| CN112520015A CN112520015A (en) | 2021-03-19 |
| CN112520015B true CN112520015B (en) | 2023-06-20 |
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| CN112520015A (en) | 2021-03-19 |
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