CN112520015A - Convertible aviation folding blade - Google Patents
Convertible aviation folding blade Download PDFInfo
- Publication number
- CN112520015A CN112520015A CN202011341304.6A CN202011341304A CN112520015A CN 112520015 A CN112520015 A CN 112520015A CN 202011341304 A CN202011341304 A CN 202011341304A CN 112520015 A CN112520015 A CN 112520015A
- Authority
- CN
- China
- Prior art keywords
- external
- blade
- telescopic cylinder
- outer side
- blade body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
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 a rotating shaft on the outer side of a transmission motor through a coupling. The turnover 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 blade body can be folded and stored outside in an idle state, so that the occupation of the external space of the aviation blade is greatly reduced; a lateral mounting slot for matching the blade body to mount and fix and an annular thread adjusting slot of a built-in internal thread locking ring are formed in the outer side surface of the external connecting seat, so that the blade is convenient to mount and dismount, the structural stability and firmness of the mounted blade are improved, and the blade is simple and convenient to operate; the angle can be adjusted according to the needs, and the application scope 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 strategic human activity. The aircraft is flying (sailing) in the earth atmosphere (air space), and related fields such as scientific research and education, industrial manufacturing, public transportation, professional operation, aviation movement, national defense and military, government management and the like. By the use of air space and aircraft (aeronautical vehicles), aviation activities can be subdivided into a number of independent industries and fields, typically aeronautical manufacturing, civil aviation, and the like. People can often see that the word is used from each field, and the content is extremely rich and varied.
Aircraft, also known as aircraft, that engage in flight activities are classified into lighter-than-air aircraft and heavier-than-air aircraft. The former is lifted by air static buoyancy, such as balloons and airships, and the latter is lifted by aerodynamic force generated by relative motion with air, such as airplanes and helicopters. According to whether manned, can be divided into unmanned aerial vehicle and unmanned aerial vehicle.
Aviation blade on the aircraft is the important power equipment spare part of aircraft, and traditional aviation blade single structure is fixed, and is unable folding, and it is big to lead to structural space to occupy under the idle state, accomodates very inconveniently.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: in order to solve the problem that exists among the above-mentioned background art, provide a folding blade of convertible aviation of modified, solve the aviation blade on present aircraft and be the important power equipment spare part of aircraft, traditional aviation blade single structure is fixed, and is unable folding, leads to structural space under the idle state to occupy greatly, accomodates very inconvenient problem.
The technical scheme adopted by the invention for solving the technical problems is as follows: a turnover aviation folding blade comprises an external connecting seat, an external connecting shaft and a blade body, wherein the external connecting shaft and the blade body are axially and fixedly connected with a rotating shaft outside a transmission motor through a shaft coupler, a lateral mounting bracket for movably connecting the blade body is fixedly connected to the outer side surface of the external connecting shaft, the blade body is of an L-shaped structure and is movably connected with the lateral mounting bracket through a transverse rotating shaft on two sides of the top end, an internal mounting shaft cylinder for assembling and fixing the external connecting shaft is connected inside the external connecting seat, a lateral mounting slot for matching with the blade body to mount and fix is formed in the outer side surface of the external connecting seat, an annular thread adjusting groove with a built-in internal thread locking ring is formed in the opening position of the lateral mounting slot in the outer side surface of the external connecting seat, and an external mounting seat with a built-in transverse locking bolt, the internal thread locking ring inside seted up horizontal assembly through-hole, external connection seat left side inner wall on seted up right side open-ended sphere and accomodate the groove, internally mounted shaft section of thick bamboo left end be located the sphere and accomodate inslot portion and have a spherical assembly head of body structure, the inboard arcwall face of external connection seat on have an outside telescopic cylinder of body arc structure, the inside mounting shaft section of thick bamboo lateral surface inside telescopic cylinder of body arc structure has, outside telescopic cylinder and inside telescopic cylinder between be connected through elastic bolt locking device.
The lateral mounting support comprises an external assembly pipe sleeved outside the external connecting shaft, a lateral movable support welded and fixed on the outer side surface of the external assembly pipe and a lateral locking bolt in threaded connection with the outer side of the external assembly pipe, the blade body penetrates through the lateral movable support and the lateral mounting support through a transverse rotating shaft and is movably connected with the external mounting pipe, and the external assembly pipe is fixedly connected with the outer side of the external connecting shaft through the lateral locking bolt.
The elastic bolt locking device comprises an internal extrusion spring inserted in the external telescopic cylinder and the internal telescopic cylinder and an internal locking bolt installed on the external telescopic cylinder, wherein the internal telescopic cylinder is internally provided with transverse adjusting through holes symmetrically arranged, and the internal locking bolt controls the external telescopic cylinder and the internal telescopic cylinder to be fixedly connected through penetrating through the transverse adjusting through holes.
And arc-shaped adjusting holes matched with the internal locking bolts are formed in the outer side of the external telescopic cylinder and the outer side of the internal telescopic cylinder.
There is no gap between the inner side surface of the spherical containing groove and the outer side connecting surface of the spherical assembling 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.
And the outer side surface of the internal thread locking ring and the outer side surface of the blade body are provided with an integral structure meshing tooth surface.
The blade body comprises an external overturning blade and an internal connecting rod of an L-shaped structure welded and fixed at the connecting top end of the external overturning blade.
The invention has the beneficial effects that:
(1) the turnover 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 blade body can be folded and stored outside in an idle state, so that the occupation of the external space of the aviation blade is greatly reduced;
(2) a lateral mounting slot for matching the blade body to mount and fix and an annular thread adjusting slot of a built-in internal thread locking ring are formed in the outer side surface of the external connecting seat, so that the blade is convenient to mount and dismount, the structural stability and firmness of the mounted blade are improved, and the blade is simple and convenient to operate;
(3) externally connecting seat internal connection internally mounted axle section of thick bamboo, cooperate elastic bolt locking device to adjust its mounting means through outside flexible cover on inside flexible section of thick bamboo, make it can change its stability and security as required, can also angle regulation as required, application scope is more extensive.
Drawings
The invention is further illustrated with reference to the following figures and examples.
Fig. 1 is a schematic structural view of the present invention.
Fig. 2 is an internal sectional view of the external connection holder of the present invention.
FIG. 3 is a partial cross-sectional view of the mounting end of the vane body of the present invention.
Detailed Description
The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic views illustrating only the basic structure of the present invention in a schematic manner, and thus show only the constitution related to the present invention.
FIG. 1, a convertible aviation folding blade shown in FIG. 2 and FIG. 3, including external connecting seat 1, pass through external connecting axle 2 and blade body 3 of shaft coupling axial fixed connection with the pivot of driving motor outside, fixedly connected with is used for the side direction installing support 4 of swing joint blade body 3 on the 2 lateral surfaces of external connecting axle, the blade body is L type structure, blade body 3 is through the horizontal pivot and the 4 swing joint of side direction installing support of top both sides, 1 internal connection of external connecting seat has the internally mounted axle section of thick bamboo 5 that is used for assembling fixed external connecting axle 2, set up the side direction installation slot 6 that is used for cooperating blade body 3 installation fixed on the external connecting seat 1 lateral surface, the annular thread adjusting groove 8 of built-in internal thread locking ring 7 is seted up to external connecting seat 1 lateral surface position in side direction installation slot 6 opening position, external connecting seat 1 lateral surface is located 6 inboard of side direction installation slot and has external The internal thread locking ring 7 has been inside seted up horizontal assembly through-hole 11, set up right side open-ended sphere on the 1 left side inner wall of external connection seat and accomodate groove 12, 5 left ends of internally mounted beam barrel are located the sphere and accomodate groove 12 inside and have a body structure spherical assembly head 13, the outside telescopic cylinder 14 of a body arc structure has on the inboard arcwall face of external connection seat 1, 5 lateral surfaces of internally mounted beam barrel have the inside telescopic cylinder 15 of a body arc structure, be connected through elastic bolt locking device between 14 and the inside telescopic cylinder 15 of an outside telescopic cylinder.
Example (b): the blade body 3 is turned over towards the outer connecting seat 1, inserted into the lateral mounting slot 6, and then penetrates through the lateral mounting slot by using a transverse locking bolt 9, and is matched with an internal thread locking ring 7 for mounting and fixing, so that the mounting firmness and stability of the blade body are improved; the outer telescopic tube 14 is then inserted into the inner telescopic tube 15, thereby controlling the connection of the outer connecting socket 1 and the inner mounting shaft tube 5.
Further, for convenient installation and storage, the lateral mounting bracket 4 comprises an external mounting pipe 16 sleeved outside the external connecting shaft 2, a lateral movable bracket 17 welded and fixed on the outer side surface of the external mounting pipe 16, and a lateral locking bolt 18 screwed outside the external 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 external mounting pipe 16 is fixedly connected with the outer side of the external connecting shaft 2 through the lateral locking bolt 18.
Further, for cooperation assembly and regulation, elastic bolt locking device is including pegging graft inside extrusion spring 19 in outside telescopic cylinder 14 and inside telescopic cylinder 15 and installing the inside locking bolt 20 on outside telescopic cylinder 14, inside telescopic cylinder 15 is inside to be offered the horizontal adjusting through-hole 21 that the symmetry set up, inside locking bolt 20 is through running through horizontal adjusting through-hole 21 outside telescopic cylinder 14 of inside control and inside telescopic cylinder 15 fixed connection, furthermore, for cooperation elasticity shock attenuation and angle modulation, arc regulation hole 22 with inside locking bolt 20 matched with has all been offered in outside telescopic cylinder 14 and the inside telescopic cylinder 15 outside.
Example (b): when the internal locking bolt 20 is inserted into the transverse adjusting through hole 21 in the external telescopic cylinder 14 and the internal telescopic cylinder 15, the external telescopic cylinder 14 is fixedly connected with the internal telescopic cylinder 15, and when the internal locking bolt 20 is inserted into the arc adjusting hole 22 in the external telescopic cylinder 14 and the internal telescopic cylinder 15, the external telescopic cylinder 14 is elastically connected with the internal telescopic cylinder 15 through the internal extrusion spring 19.
Further, in order to improve the fitting property, there is no gap between the inner surface of the spherical housing groove 12 and the outer surface of the spherical fitting head 13, and there is no gap between the inner surface of the outer telescopic cylinder 14 and the outer surface of the inner telescopic cylinder 15.
Further, in order to improve the assembling stability, the outer side surface of the internal thread locking ring 7 and the outer side surface of the blade body 3 are provided with an integral structure engaging tooth surface, and further, in order to facilitate the assembling and the adjusting, 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 aviation folding blade is composed of an external connecting seat 1, an external connecting shaft 2 and a blade body 3, wherein the blade body 3 is of an L-shaped structure and is movably connected with the external connecting shaft 2 through a lateral mounting bracket 4, and the blade can be folded and stored outside in an idle state, so that the occupation of the external space of the aviation blade is greatly reduced; a lateral mounting slot 6 for matching the blade body 3 to mount and fix and an annular thread adjusting slot 8 internally provided with an internal thread locking ring 7 are formed in the outer side surface of the external connecting seat 1, so that the blade is convenient to mount and dismount, the structural stability and firmness after being mounted are improved, and the operation is simple and convenient; externally connecting 1 internal connection internally mounted axle section of thick bamboo 5 of connecting, cooperate elastic bolt locking device to adjust its mounting means through 14 cover of outside telescopic tube on inside telescopic tube 15, make it can change its stability and security as required, can also adjust the angle as required, application scope is more extensive.
In light of the foregoing description of the preferred embodiment of the present invention, many modifications and variations will be apparent to those skilled in the art without departing from the spirit and scope of the invention. The technical scope of the present invention is not limited to the content of the specification, and must be determined according to the scope of the claims.
Claims (7)
1. The utility model provides a blade is folded in convertible aviation, includes external connection seat (1), passes through external connection axle (2) and blade body (3) that shaft coupling axial fixity is connected with the pivot in the drive motor outside, characterized by: the outer side surface of the external connecting shaft (2) is fixedly connected with a lateral mounting bracket (4) used for movably connecting a blade body (3), 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 two sides of the top end, an internal mounting shaft barrel (5) used for assembling and fixing the external connecting shaft (2) is connected inside the external connecting base (1), a lateral mounting slot (6) used for being matched with the blade body (3) to mount and fix is formed in the outer side surface of the external connecting base (1), an annular thread adjusting groove (8) with a built-in internal thread locking ring (7) is formed in the opening position of the lateral mounting slot (6) in the outer side surface of the external connecting base (1), and an external mounting base (10) with a built-in transverse locking bolt (9) is arranged on the inner side of the lateral mounting slot (6) in the, internal thread locking ring (7) inside seted up horizontal assembly through-hole (11), external connection seat (1) left side inner wall on seted up right side open-ended sphere and accomodate groove (12), internally mounted axle section of thick bamboo (5) left end be located sphere and accomodate groove (12) inside have integrative structure spherical assembly head (13), external connection seat (1) inboard arcwall face on have outside flexible section of thick bamboo (14) of integrative arc structure, internally mounted axle section of thick bamboo (5) lateral surface inside flexible section of thick bamboo (15) of integrative arc structure have, outside flexible section of thick bamboo (14) and inside flexible section of thick bamboo (15) between be connected through elastic bolt locking device.
2. The flip aerial folding blade of claim 1, wherein: the lateral mounting support (4) comprises an external assembly pipe (16) sleeved on the outer side of the external connecting shaft (2), a lateral movable support (17) welded and fixed on the outer side surface of the external assembly pipe (16) and a lateral locking bolt (18) in threaded connection with the outer side of the external assembly pipe (16), the blade body (3) penetrates through the lateral movable support (17) through a transverse rotating shaft and is movably connected with the lateral mounting support (4), and the external assembly pipe (16) is fixedly connected with the outer side of the external connecting shaft (2) through the lateral locking bolt (18).
3. The flip aerial folding blade of claim 1, wherein: the elastic bolt locking device comprises an internal extrusion spring (19) inserted in an external telescopic cylinder (14) and an internal telescopic cylinder (15) and an internal locking bolt (20) installed on the external telescopic cylinder (14), wherein the internal telescopic cylinder (15) is internally provided with transverse adjusting through holes (21) which are symmetrically arranged, and the internal locking bolt (20) is fixedly connected with the internal telescopic cylinder (15) by internally controlling the external telescopic cylinder (14) through penetrating through the transverse adjusting through holes (21).
4. A flip aerial folding blade according to claim 3 wherein: and arc-shaped adjusting holes (22) matched with the inner locking bolts (20) are formed in the outer sides of the outer telescopic cylinder (14) and the inner telescopic cylinder (15).
5. The flip aerial folding blade of claim 1, wherein: there is no gap between the inner side surface of the spherical containing groove (12) and the outer side connecting surface of the spherical assembling 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. The flip aerial folding blade of claim 1, wherein: and the outer side surface of the internal thread locking ring (7) and the outer side surface of the blade body (3) are provided with an integral structure meshing tooth surface.
7. The flip aerial folding blade of claim 1, wherein: the blade body (3) is composed of an external overturning blade (23) and an L-shaped structure internal connecting rod (24) welded and fixed at the connecting top end of the external overturning 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112520015A true CN112520015A (en) | 2021-03-19 |
| CN112520015B CN112520015B (en) | 2023-06-20 |
Family
ID=74993547
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011341304.6A Active CN112520015B (en) | 2020-11-25 | 2020-11-25 | Convertible aviation folding blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112520015B (en) |
Citations (27)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB499932A (en) * | 1938-05-03 | 1939-01-31 | Hans Reissner | Improvements in or relating to screw propellers, particularly for aircraft |
| US4732540A (en) * | 1985-07-22 | 1988-03-22 | Aerospatiale Societe Nationale Industrielle | Integrated hub-mast and gyroplane rotor head comprising it |
| US5782606A (en) * | 1995-12-22 | 1998-07-21 | Eurocopter France | Device for folding a rotorcraft rotor blade |
| US6126398A (en) * | 1998-05-28 | 2000-10-03 | Eurocopter Deutschland Gmbh | Two-piece rotor blade for a bearingless rotor of a helicopter |
| US20040026564A1 (en) * | 2002-03-11 | 2004-02-12 | Michel Romani | Method and apparatus for folding/unfolding the blades of a rotary-wing aircraft rotor |
| CN204937484U (en) * | 2015-09-07 | 2016-01-06 | 李嘉伟 | A kind of foldable propeller easy to assemble for miniature self-service aviation aircraft |
| WO2016124068A1 (en) * | 2015-02-02 | 2016-08-11 | 上海坚柏国际贸易有限公司 | Mobile phone shell capable of being changed into unmanned aerial vehicle |
| CN205573521U (en) * | 2016-04-22 | 2016-09-14 | 马渝皓 | Navy, army and air force triphibian concept car |
| CN205989811U (en) * | 2016-08-17 | 2017-03-01 | 李弈星 | A kind of unmanned plane folding wing |
| CN106621383A (en) * | 2015-11-04 | 2017-05-10 | 许美兰 | Aircraft stable flying system |
| CN206782019U (en) * | 2017-05-09 | 2017-12-22 | 南京航空航天大学 | It is a kind of can VTOL the amphibious airship of air-sea |
| CN206885352U (en) * | 2017-05-09 | 2018-01-16 | 昊翔电能运动科技(昆山)有限公司 | Unmanned vehicle mounting structure for propeller |
| EP3315400A1 (en) * | 2016-10-25 | 2018-05-02 | AeroMobil R&D, s. r. o. | Folding propeller |
| CN108082479A (en) * | 2017-12-18 | 2018-05-29 | 中山市雅乐思商住电器有限公司 | A kind of portable agricultural formula unmanned plane |
| CN207701460U (en) * | 2018-01-04 | 2018-08-07 | 张家港市三利密封合金材料有限公司 | A kind of impeller stretching blade with split type grafting |
| CN208515804U (en) * | 2018-06-21 | 2019-02-19 | 河南天腾航空科技有限公司 | A kind of novel unmanned plane propeller arrangement |
| EP3464061A1 (en) * | 2016-05-30 | 2019-04-10 | Luka Kapeter | Propeller-hub assembly with folding blades for vtol aircraft |
| CN209025791U (en) * | 2018-10-29 | 2019-06-25 | 内蒙古工业大学 | A kind of novel wind motor combined blade |
| CN209040893U (en) * | 2018-11-28 | 2019-06-28 | 西安中捷飞工贸有限责任公司 | A kind of aero-turbine rotor blade with shield |
| CN209492698U (en) * | 2018-12-14 | 2019-10-15 | 南京天禄航空科技有限公司 | A kind of folded wing of unmanned plane |
| CN110356542A (en) * | 2019-07-23 | 2019-10-22 | 安徽卓尔航空科技有限公司 | One kind having adjustable high-efficiency aerodynamic force propeller |
| US20190329867A1 (en) * | 2018-04-26 | 2019-10-31 | Bell Helicopter Textron Inc. | Blade fold Method and Apparatus for A Tilt Rotor Hub |
| US20190389569A1 (en) * | 2018-06-22 | 2019-12-26 | Bell Helicopter Textron Inc. | Blade fold method and apparatus for a tilt rotor hub |
| CN209875645U (en) * | 2019-03-27 | 2019-12-31 | 张家港沙龙精密管业有限公司 | High-strength precision steel pipe with elastic limiting easy-to-assemble and disassemble mechanism |
| CN210221429U (en) * | 2019-07-23 | 2020-03-31 | 铜陵熙成塑料制品有限公司 | Air permeability detector with telescopic air pressure detection mechanism |
| CN111059390A (en) * | 2019-11-12 | 2020-04-24 | 江苏嘉恒管业科技发展有限公司 | Rigid-flexible alloy pipe with built-in elastic locking mechanism and connection mode thereof |
| CN211766239U (en) * | 2019-12-31 | 2020-10-27 | 常州市长昊机械有限公司 | Assembly part for airplane cabin door |
-
2020
- 2020-11-25 CN CN202011341304.6A patent/CN112520015B/en active Active
Patent Citations (27)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB499932A (en) * | 1938-05-03 | 1939-01-31 | Hans Reissner | Improvements in or relating to screw propellers, particularly for aircraft |
| US4732540A (en) * | 1985-07-22 | 1988-03-22 | Aerospatiale Societe Nationale Industrielle | Integrated hub-mast and gyroplane rotor head comprising it |
| US5782606A (en) * | 1995-12-22 | 1998-07-21 | Eurocopter France | Device for folding a rotorcraft rotor blade |
| US6126398A (en) * | 1998-05-28 | 2000-10-03 | Eurocopter Deutschland Gmbh | Two-piece rotor blade for a bearingless rotor of a helicopter |
| US20040026564A1 (en) * | 2002-03-11 | 2004-02-12 | Michel Romani | Method and apparatus for folding/unfolding the blades of a rotary-wing aircraft rotor |
| WO2016124068A1 (en) * | 2015-02-02 | 2016-08-11 | 上海坚柏国际贸易有限公司 | Mobile phone shell capable of being changed into unmanned aerial vehicle |
| CN204937484U (en) * | 2015-09-07 | 2016-01-06 | 李嘉伟 | A kind of foldable propeller easy to assemble for miniature self-service aviation aircraft |
| CN106621383A (en) * | 2015-11-04 | 2017-05-10 | 许美兰 | Aircraft stable flying system |
| CN205573521U (en) * | 2016-04-22 | 2016-09-14 | 马渝皓 | Navy, army and air force triphibian concept car |
| EP3464061A1 (en) * | 2016-05-30 | 2019-04-10 | Luka Kapeter | Propeller-hub assembly with folding blades for vtol aircraft |
| CN205989811U (en) * | 2016-08-17 | 2017-03-01 | 李弈星 | A kind of unmanned plane folding wing |
| EP3315400A1 (en) * | 2016-10-25 | 2018-05-02 | AeroMobil R&D, s. r. o. | Folding propeller |
| CN206885352U (en) * | 2017-05-09 | 2018-01-16 | 昊翔电能运动科技(昆山)有限公司 | Unmanned vehicle mounting structure for propeller |
| CN206782019U (en) * | 2017-05-09 | 2017-12-22 | 南京航空航天大学 | It is a kind of can VTOL the amphibious airship of air-sea |
| CN108082479A (en) * | 2017-12-18 | 2018-05-29 | 中山市雅乐思商住电器有限公司 | A kind of portable agricultural formula unmanned plane |
| CN207701460U (en) * | 2018-01-04 | 2018-08-07 | 张家港市三利密封合金材料有限公司 | A kind of impeller stretching blade with split type grafting |
| US20190329867A1 (en) * | 2018-04-26 | 2019-10-31 | Bell Helicopter Textron Inc. | Blade fold Method and Apparatus for A Tilt Rotor Hub |
| CN208515804U (en) * | 2018-06-21 | 2019-02-19 | 河南天腾航空科技有限公司 | A kind of novel unmanned plane propeller arrangement |
| US20190389569A1 (en) * | 2018-06-22 | 2019-12-26 | Bell Helicopter Textron Inc. | Blade fold method and apparatus for a tilt rotor hub |
| CN209025791U (en) * | 2018-10-29 | 2019-06-25 | 内蒙古工业大学 | A kind of novel wind motor combined blade |
| CN209040893U (en) * | 2018-11-28 | 2019-06-28 | 西安中捷飞工贸有限责任公司 | A kind of aero-turbine rotor blade with shield |
| CN209492698U (en) * | 2018-12-14 | 2019-10-15 | 南京天禄航空科技有限公司 | A kind of folded wing of unmanned plane |
| CN209875645U (en) * | 2019-03-27 | 2019-12-31 | 张家港沙龙精密管业有限公司 | High-strength precision steel pipe with elastic limiting easy-to-assemble and disassemble mechanism |
| CN110356542A (en) * | 2019-07-23 | 2019-10-22 | 安徽卓尔航空科技有限公司 | One kind having adjustable high-efficiency aerodynamic force propeller |
| CN210221429U (en) * | 2019-07-23 | 2020-03-31 | 铜陵熙成塑料制品有限公司 | Air permeability detector with telescopic air pressure detection mechanism |
| CN111059390A (en) * | 2019-11-12 | 2020-04-24 | 江苏嘉恒管业科技发展有限公司 | Rigid-flexible alloy pipe with built-in elastic locking mechanism and connection mode thereof |
| CN211766239U (en) * | 2019-12-31 | 2020-10-27 | 常州市长昊机械有限公司 | Assembly part for airplane cabin door |
Non-Patent Citations (1)
| Title |
|---|
| 王术波: "基于ADRC迭代学习控制的四旋翼无人机姿态控制", 航空学报 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112520015B (en) | 2023-06-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103552686B (en) | A kind of compound type duct aerial reconnaissance machine people | |
| CN106081057A (en) | A kind of stable multiaxis unmanned plane | |
| CN102229357B (en) | Empennage with installing angle and adjustable horizontal tail | |
| CN110481769B (en) | Unmanned aerial vehicle device based on coaxial double rotors | |
| CN204506376U (en) | Dwelling in a kind of land, water and air three, nobody investigates device | |
| CN105083521A (en) | Airship | |
| CN111532429B (en) | Miniature fixed wing unmanned aerial vehicle capable of being adsorbed on plane | |
| CN102910285A (en) | Rotor aircraft | |
| CN210852883U (en) | Four rotor unmanned aerial vehicle of collapsible arm | |
| CN112520015A (en) | Convertible aviation folding blade | |
| CN208484828U (en) | A kind of Fixed Wing AirVehicle of energy VTOL | |
| WO2020000690A1 (en) | Fixed-wing unmanned aerial vehicle and empennage thereof | |
| CN211685663U (en) | Three-axis nacelle | |
| CN110871883B (en) | Wing folding and unfolding mechanism of cylinder-jet unmanned aerial vehicle | |
| US11855387B2 (en) | Plug-in assembly structure and an unmanned aerial vehicle with composite wing | |
| CN209795808U (en) | Simple folding tail wing | |
| CN208181415U (en) | Multi-rotor unmanned aerial vehicle fuselage box | |
| CN113212735B (en) | Air-jet unmanned aerial vehicle | |
| CN110481771A (en) | Can VTOL Fixed Wing AirVehicle and UAV system | |
| CN2772962Y (en) | Special aerobat with circular wing | |
| CN110435878A (en) | Single layer displacement coaxial construction for unmanned plane | |
| CN220374795U (en) | Economical unmanned aerial vehicle structure | |
| CN112874771A (en) | Deformation can vert four rotor unmanned aerial vehicle | |
| CN207791148U (en) | A kind of unmanned plane and UAV system | |
| CN2789130Y (en) | Propeller thrust ring wing aerobat |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |