WO2019194700A1 - Tractive airscrew having foldable blades - Google Patents
Tractive airscrew having foldable blades Download PDFInfo
- Publication number
- WO2019194700A1 WO2019194700A1 PCT/RU2018/000534 RU2018000534W WO2019194700A1 WO 2019194700 A1 WO2019194700 A1 WO 2019194700A1 RU 2018000534 W RU2018000534 W RU 2018000534W WO 2019194700 A1 WO2019194700 A1 WO 2019194700A1
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- WO
- WIPO (PCT)
- Prior art keywords
- blades
- fairing
- rotation
- screw
- propeller
- Prior art date
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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
Definitions
- the invention relates to the field of aeronautics, namely to propellers with folding blades for an aircraft.
- an aircraft propeller comprising a propeller hub connected to a drive motor and air blades, as well as a propeller cowl, wherein the cowl is rotatably connected to the propeller hub together with the propeller hub, and the blades are folded and connected to the hub by hinges (RU2456206 C2, publ., 07/20/2012).
- the disadvantages of the known screw are the need for folding in the direction coinciding with the direction of flight of the device. This decision is associated with the need to use the oncoming air flow to drive the generator at the beginning of the screw folding process.
- the indicated direction of unfolding of the rotor blades determines the necessity of arranging the plane of rotation of the rotor in working condition near the housing surface on which the propulsion system of the rotor drive is installed.
- folding the blades in the direction of flight requires the use of a drive lock, which is installed after unfolding the blades.
- the technical result is to increase the reliability of the propeller, simplify the design and reduce the size of the nacelle.
- the pulling propeller with folding blades for the aircraft driven by the engine and contains a propeller hub associated with the drive motor and air blades, as well as a propeller cowling, while the cowling is connected to the propeller hub so that it can rotate together with screw hub, blades are made folding in the direction opposite to the direction of flight of the aircraft and are connected to the sleeve by means of hinges, the blades in the folded position located along the fairing on its outer surface with the possibility of rotation in the folded position together with the fairing, at least during folding of the blades and their unfolding.
- the task is also achieved by the fact that on the surface of the fairing can be made niches in the form corresponding to the shape of the air blades, with the possibility of placing in these niches folded along the fairing of the blades.
- the niches can be made in the form of through notches.
- the task is also achieved by the fact that the blades in the folded position can be located within the dimensions of the fairing in the direction of the axis of rotation of the screw.
- the task is also achieved by the fact that the geometric axis of rotation of the hinges do not intersect with the axis of rotation of the screw, and the plane of rotation of each hinge can be offset relative to the specified axis of rotation of the screw.
- the task is also achieved by the fact that the engine can be made electric and located inside the fairing.
- FIG. 1 shows a pulling screw with folded blades
- FIG. 3 shows a view of the propeller in the working position of the blades.
- the pulling screw contains a sleeve 1 connected to the drive motor 2.
- the sleeve 1 has hinges 3 with blades 4 fixed to them, while the fairing 5 of the screw sleeve 1 is connected in it with the possibility of their joint rotation.
- niches 6 On the surface of the fairing 5 can be made niches 6 in the form corresponding to the shape of the blades 4, for laying them in these niches 6 when folding.
- the niches 6 can be made through, and when folding the blades 4 are placed within the fairing 5, that is, they do not extend beyond its limits along the length after folding.
- the geometric axis of rotation of the hinges 3 are offset from the axis of rotation of the screw, that is, they do not intersect it, and the plane in which the blades 4 are rotated in the hinge 3 is offset relative to the axis of rotation of the screw.
- the plane of rotation of each pair to the mouths are located centrally symmetrical about the axis of rotation of the screw.
- the engine 2 can be made electric and is located inside the fairing 5 within its dimensions.
- the described device operates as follows. In the folded position, the blades 4 are laid along the fairing 5 and are located, for example, in the niches 6. Moreover, the entire sleeve 1 with the engine 2 and the fairing 5 with the blades 4 are located outside the housing on which the nacelle is mounted. The end of the blades 4 are directed against the direction of flight of the apparatus. When it is necessary to unfold the blades 4, the shaft of the engine 2 is rotated, and under the action of centrifugal forces, or under the influence of drive mechanisms, the blades 4 rotate in hinges 3, being installed in a plane approximately perpendicular to the axis of rotation of the screw. The blades 4 are laid out in the direction coinciding with the direction of flight. In this case, the blades 4 after the layout can reach the stops (not shown in the drawings) or in their working position a balance can be achieved between the action of the centrifugal forces on the blades 4 and the forces creating longitudinal traction.
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Transmission Devices (AREA)
Abstract
The invention relates to the field of aeronautics, specifically to airscrews having folding blades for an aircraft. The technical effect is to raise the operating reliability of an airscrew, simplify construction and reduce the dimensions of a motor nacelle. The essence of the invention consists in that a tractive airscrew driven by an engine comprises a screw hub connected to a drive engine and air blades, as well as a screw hub fairing. The fairing is connected to the screw hub so as to be capable of rotating together with the screw hub; the blades are foldable in the direction counter to the direction of flight of the aircraft and are connected to the hub by means of hinges, the blades in the folded position being arranged along the fairing on its outer surface so as to be capable of rotating in the folded position together with the fairing at least during folding and unfolding of the blades.
Description
Тянущий воздушный винт со складывающимися лопастями. Pulling propeller with folding blades.
Область техники Technical field
Изобретение относится к области воздухоплавания, а именно к воздушным винтам со складывающимися лопастями для летательного аппарата. The invention relates to the field of aeronautics, namely to propellers with folding blades for an aircraft.
Предшествующий уровень техники State of the art
Известен тянущий воздушный винт летательного аппарата, содержащий втулку винта, связанную с приводным двигателем и воздушными лопастями, а также обтекатель втулки винта, при этом обтекатель соединен с втулкой винта с возможностью его вращения вместе с втулкой винта, а лопасти выполнены складывающимися и связаны с втулкой посредством шарниров (RU2456206 С2, опуб., 20.07.2012). Known is an aircraft propeller comprising a propeller hub connected to a drive motor and air blades, as well as a propeller cowl, wherein the cowl is rotatably connected to the propeller hub together with the propeller hub, and the blades are folded and connected to the hub by hinges (RU2456206 C2, publ., 07/20/2012).
Недостатками известного винта являются необходимость его складывания в направлении, совпадающем с направлением полета аппарата. Такое решение связано с необходимостью использования набегающего потока воздуха для привода в действие генератора в начале процесса раскладывания винта. При этом указанное направление раскладывания лопастей винта определяет необходимость расположения плоскости вращения винта в рабочем состоянии вблизи корпусной поверхности, на которой установлена силовая установка привода винта. Кроме того, складывание лопастей в направлении полета требует использования приводного фиксатора, устанавливаемого после раскладывания лопастей. The disadvantages of the known screw are the need for folding in the direction coinciding with the direction of flight of the device. This decision is associated with the need to use the oncoming air flow to drive the generator at the beginning of the screw folding process. In this case, the indicated direction of unfolding of the rotor blades determines the necessity of arranging the plane of rotation of the rotor in working condition near the housing surface on which the propulsion system of the rotor drive is installed. In addition, folding the blades in the direction of flight requires the use of a drive lock, which is installed after unfolding the blades.
Раскрытие изобретения Disclosure of invention
Техническим результатом является повышение надежности работы воздушного винта, упрощение конструкции и снижение габаритов мотогондолы. The technical result is to increase the reliability of the propeller, simplify the design and reduce the size of the nacelle.
Поставленная задача достигается тем, что тянущий воздушный винт со складывающимися лопастями для летательного аппарата, приводимый двигателем и содержит втулку винта, связанную с приводным двигателем и воздушными лопастями, а также обтекатель втулки винта, при этом обтекатель соединен с втулкой винта с возможностью его вращения вместе с втулкой винта, лопасти выполнены
складывающимися в направлении против направления полета летательного аппарата и связаны с втулкой посредством шарниров, причем лопасти в сложенном положении расположены вдоль обтекателя на его внешней поверхности с возможностью их вращения в сложенном положении вместе с обтекателем, по меньшей мере, во время складывания лопастей и их раскладывания. This object is achieved in that the pulling propeller with folding blades for the aircraft, driven by the engine and contains a propeller hub associated with the drive motor and air blades, as well as a propeller cowling, while the cowling is connected to the propeller hub so that it can rotate together with screw hub, blades are made folding in the direction opposite to the direction of flight of the aircraft and are connected to the sleeve by means of hinges, the blades in the folded position located along the fairing on its outer surface with the possibility of rotation in the folded position together with the fairing, at least during folding of the blades and their unfolding.
Поставленная задача достигается также тем, что на поверхности обтекателя могут быть выполнены ниши по форме, соответствующей форме воздушных лопастей, с возможностью размещения в указанных нишах сложенных вдоль обтекателя лопастей. The task is also achieved by the fact that on the surface of the fairing can be made niches in the form corresponding to the shape of the air blades, with the possibility of placing in these niches folded along the fairing of the blades.
Поставленная задача достигается также тем, что ниши могут быть выполнены в виде несквозных выемок. The task is also achieved by the fact that the niches can be made in the form of through notches.
Поставленная задача достигается также тем, что лопасти в сложенном положении могут быть расположены в пределах габаритов обтекателя в направлении оси вращения винта. The task is also achieved by the fact that the blades in the folded position can be located within the dimensions of the fairing in the direction of the axis of rotation of the screw.
Поставленная задача достигается также тем, что геометрические оси поворота шарниров не пересекаются с осью вращения винта, а плоскость поворота каждого шарнира может быть смещена относительно указанной оси вращения винта. The task is also achieved by the fact that the geometric axis of rotation of the hinges do not intersect with the axis of rotation of the screw, and the plane of rotation of each hinge can be offset relative to the specified axis of rotation of the screw.
Поставленная задача достигается также тем, что двигатель может быть выполнен электрическим и расположен внутри обтекателя. The task is also achieved by the fact that the engine can be made electric and located inside the fairing.
Краткое описание чертежей Brief Description of the Drawings
Изобретение поясняется при помощи чертежей. The invention is illustrated using the drawings.
На фиг. 1 показан тянущий винт со сложенными лопастями; In FIG. 1 shows a pulling screw with folded blades;
На фиг. 2 - то же, с лопастями в рабочем положении для создания тяги летательного аппарата. In FIG. 2 - the same, with the blades in the working position to create thrust of the aircraft.
На фиг. 3 показан вид на воздушный винт в рабочем положении лопастей. In FIG. 3 shows a view of the propeller in the working position of the blades.
Лучший вариант осуществления изобретения The best embodiment of the invention
Тянущий винт содержит втулку 1, связанную с приводным двигателем 2. Втулка 1 имеет шарниры 3 с закрепленными на них лопастями 4, при этом обтекатель 5 втулки 1 винта соединен в ней с возможностью их совместного вращения. The pulling screw contains a sleeve 1 connected to the drive motor 2. The sleeve 1 has hinges 3 with blades 4 fixed to them, while the fairing 5 of the screw sleeve 1 is connected in it with the possibility of their joint rotation.
На поверхности обтекателя 5 могут быть выполнены ниши 6 по форме, соответствующей форме лопастей 4, для укладывания их в указанные ниши 6 при складывании. При этом ниши 6 могут быть выполнены несквозными, и лопасти 4 при складывании размещаются в пределах обтекателя 5, то есть не выходят за его пределы по длине после складывания.
Геометрические оси поворота шарниров 3 смещены от оси вращения винта, то есть не пересекают ее, а плоскость, в которой осуществляют поворот лопасти 4 в шарнире 3, смещена относительно оси вращения винта. При этом, как показано на чертежах, при четном количестве лопастей плоскости поворота каждой пары до пастей расположены центрально-симметрично относительно оси вращения винта. On the surface of the fairing 5 can be made niches 6 in the form corresponding to the shape of the blades 4, for laying them in these niches 6 when folding. In this case, the niches 6 can be made through, and when folding the blades 4 are placed within the fairing 5, that is, they do not extend beyond its limits along the length after folding. The geometric axis of rotation of the hinges 3 are offset from the axis of rotation of the screw, that is, they do not intersect it, and the plane in which the blades 4 are rotated in the hinge 3 is offset relative to the axis of rotation of the screw. Moreover, as shown in the drawings, with an even number of blades, the plane of rotation of each pair to the mouths are located centrally symmetrical about the axis of rotation of the screw.
Двигатель 2 может быть выполнен электрическим и расположен внутри обтекателя 5 в пределах его габаритов. The engine 2 can be made electric and is located inside the fairing 5 within its dimensions.
Описываемое устройство работает следующим образом. В сложенном положении лопасти 4 уложены вдоль обтекателя 5 и расположены, например, в нишах 6. При этом вся втулка 1 с двигателем 2 и обтекатель 5 с лопастями 4 расположены вне пределов корпуса, на котором крепится мотогондола. Конца лопастей 4 направлены против направления полета аппарата. В момент необходимости раскладывания лопастей 4 приводится во вращение вал двигателя 2, и под действием центробежных сил, или под влиянием приводных механизмов, лопасти 4 поворачиваются в шарнирах 3, устанавливаясь в плоскости, примерно перпендикулярной оси вращения винта. Лопасти 4 раскладываются в направлении, совпадающем с направлением полета. При этом лопасти 4 после раскладки могут дойти до упоров (на чертежах не показаны) или в рабочем их положении может быть достигнут баланс между действием на лопасти 4 центробежных сил и сил, создающих продольную тягу. The described device operates as follows. In the folded position, the blades 4 are laid along the fairing 5 and are located, for example, in the niches 6. Moreover, the entire sleeve 1 with the engine 2 and the fairing 5 with the blades 4 are located outside the housing on which the nacelle is mounted. The end of the blades 4 are directed against the direction of flight of the apparatus. When it is necessary to unfold the blades 4, the shaft of the engine 2 is rotated, and under the action of centrifugal forces, or under the influence of drive mechanisms, the blades 4 rotate in hinges 3, being installed in a plane approximately perpendicular to the axis of rotation of the screw. The blades 4 are laid out in the direction coinciding with the direction of flight. In this case, the blades 4 after the layout can reach the stops (not shown in the drawings) or in their working position a balance can be achieved between the action of the centrifugal forces on the blades 4 and the forces creating longitudinal traction.
Промышленная применимость Industrial applicability
В рабочем положении винта, после раскладки лопастей 4, плоскость их вращения находится на максимальном расстоянии от корпуса крепления мотогондолы по сравнению с ближайшими аналогами. Это позволяет улучшить аэродинамику аппарата при заданных габаритах складывающихся лопастей и, соответственно, мотогондолы и обтекателя, а также максимально полезно использовать габариты мотогондолы. Отсутствие необходимости применения приводных фиксаторов лопастей в рабочем положении упрощает конструкцию, ее надежность.
In the working position of the screw, after the layout of the blades 4, the plane of their rotation is at a maximum distance from the mount of the engine nacelle in comparison with the closest analogues. This allows you to improve the aerodynamics of the apparatus with the given dimensions of the folding blades and, accordingly, the nacelle and fairing, as well as the most useful use of the dimensions of the nacelle. The lack of need for the use of drive clamps of the blades in the working position simplifies the design, its reliability.
Claims
1. Тянущий воздушный винт со складывающимися лопастями для летательного аппарата, приводимый двигателем и содержащий втулку винта, связанную с приводным двигателем и воздушными лопастями, а также обтекатель втулки винта, при этом обтекатель соединен с втулкой винта с возможностью его вращения вместе с втулкой винта, лопасти выполнены складывающимися в направлении против направления полета летательного аппарата и связаны с втулкой посредством шарниров, причем лопасти в сложенном положении расположены вдоль обтекателя на его внешней поверхности с возможностью их вращения в сложенном положении вместе с обтекателем, по меньшей мере, во время складывания лопастей и их раскладывания. 1. A pulling propeller with folding blades for an aircraft driven by an engine and comprising a propeller hub associated with a drive motor and air blades, as well as a propeller cowl, wherein the cowl is rotatably connected to the propeller hub together with the propeller hub, propeller blades made folding in the direction opposite to the direction of flight of the aircraft and are connected to the sleeve by means of hinges, and the blades in the folded position are located along the fairing on its outer surfaces with the possibility of their rotation in the folded position together with the fairing, at least during folding of the blades and their unfolding.
2. Тянущий винт по п. 1, отличающийся тем, что на поверхности обтекателя выполнены ниши по форме, соответствующей форме воздушных лопастей, с возможностью размещения в указанных нишах сложенных вдоль обтекателя лопастей. 2. The pulling screw according to claim 1, characterized in that niches are made on the surface of the fairing in a shape corresponding to the shape of air blades, with the possibility of placing blades folded along the fairing in said niches.
3. Тянущий винт по п. 2, отличающийся тем, что ниши выполнены в виде несквозных выемок. 3. The pulling screw according to claim 2, characterized in that the niches are made in the form of through notches.
4. Тянущий винт по п. 1, отличающийся тем, что лопасти в сложенном положении расположены в пределах габаритов обтекателя в направлении оси вращения винта. 4. The pulling screw according to claim 1, characterized in that the blades in the folded position are located within the dimensions of the fairing in the direction of the axis of rotation of the screw.
5. Тянущий винт по п. 1, отличающийся тем, что геометрические оси поворота шарниров не пересекаются с осью вращения винта, а плоскость поворота каждого шарнира смещена относительно указанной оси вращения винта. 5. The pulling screw according to claim 1, characterized in that the geometric axis of rotation of the hinges do not intersect with the axis of rotation of the screw, and the plane of rotation of each hinge is offset relative to the specified axis of rotation of the screw.
6. Тянущий винт по п. 1, отличающийся тем, что двигатель выполнен электрическим и расположен внутри обтекателя.
6. The pulling screw according to claim 1, characterized in that the engine is electric and located inside the fairing.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2018112386A RU2709944C2 (en) | 2018-04-06 | 2018-04-06 | Propeller with folding blades |
| RU2018112386 | 2018-04-06 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2019194700A1 true WO2019194700A1 (en) | 2019-10-10 |
Family
ID=68101064
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/RU2018/000534 WO2019194700A1 (en) | 2018-04-06 | 2018-08-14 | Tractive airscrew having foldable blades |
Country Status (2)
| Country | Link |
|---|---|
| RU (1) | RU2709944C2 (en) |
| WO (1) | WO2019194700A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112607003A (en) * | 2020-11-25 | 2021-04-06 | 常州市长昊机械有限公司 | Easily accomodate formula aviation blade |
| US11713687B1 (en) | 2022-03-17 | 2023-08-01 | General Electric Company | Flapping hinge for a fan blade |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11465737B1 (en) | 2019-03-13 | 2022-10-11 | Joby Aero, Inc. | Conformal pylon/boom prop-rotors |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2456206C2 (en) * | 2010-07-22 | 2012-07-20 | Олег Николаевич Гаршин | Airscrew with automatically unfolding and rotary blades |
| US20160347441A1 (en) * | 2015-06-01 | 2016-12-01 | Northrop Grumman Systems Corporation | Deployable propeller |
| GB2550916A (en) * | 2016-05-30 | 2017-12-06 | Kapeter Luka | Propeller-hub assembly enabling a folding of a propeller blades during flight and VTOL aircraft comprising the same |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3957229A (en) * | 1973-08-09 | 1976-05-18 | Davis Harry C | Convertible auxiliary turbine for aircraft |
-
2018
- 2018-04-06 RU RU2018112386A patent/RU2709944C2/en not_active IP Right Cessation
- 2018-08-14 WO PCT/RU2018/000534 patent/WO2019194700A1/en active Application Filing
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2456206C2 (en) * | 2010-07-22 | 2012-07-20 | Олег Николаевич Гаршин | Airscrew with automatically unfolding and rotary blades |
| US20160347441A1 (en) * | 2015-06-01 | 2016-12-01 | Northrop Grumman Systems Corporation | Deployable propeller |
| GB2550916A (en) * | 2016-05-30 | 2017-12-06 | Kapeter Luka | Propeller-hub assembly enabling a folding of a propeller blades during flight and VTOL aircraft comprising the same |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112607003A (en) * | 2020-11-25 | 2021-04-06 | 常州市长昊机械有限公司 | Easily accomodate formula aviation blade |
| CN112607003B (en) * | 2020-11-25 | 2023-06-20 | 常州市长昊机械有限公司 | Easily accomodate formula aviation blade |
| US11713687B1 (en) | 2022-03-17 | 2023-08-01 | General Electric Company | Flapping hinge for a fan blade |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2018112386A (en) | 2019-10-08 |
| RU2709944C2 (en) | 2019-12-23 |
| RU2018112386A3 (en) | 2019-10-08 |
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