WO2019054896A1 - Rotorcraft - Google Patents
Rotorcraft Download PDFInfo
- Publication number
- WO2019054896A1 WO2019054896A1 PCT/RU2018/000270 RU2018000270W WO2019054896A1 WO 2019054896 A1 WO2019054896 A1 WO 2019054896A1 RU 2018000270 W RU2018000270 W RU 2018000270W WO 2019054896 A1 WO2019054896 A1 WO 2019054896A1
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- WO
- WIPO (PCT)
- Prior art keywords
- wings
- wing
- rotor
- fuselage
- rotating
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/24—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
Definitions
- the invention relates to the field of aeronautics, namely to aircraft with rotors.
- a disadvantage of the known rotary-wing is the presence of an unbalanced inertia force acting along the fuselage at the moments of intersection of the trajectories of rotating wings in the front and rear points. This force is equal to twice the centrifugal force acting on the wing. This phenomenon of inertial force at two points of the trajectory is used in Lanchester's mechanisms when balancing piston internal combustion engines.
- the disadvantages of the known rotary wing are the impossibility of placing one of the wings of each rotor in the position of maximum aerodynamic efficiency when it is fixed, since the wings of one rotor rotate in one direction and when moving the wings in a fixed position, one of the wings is set back. That is, it does not fully perform the function of the wing in horizontal flight, which reduces the performance of the rotor wing in terms of payload.
- the technical result of the claimed invention is to increase the efficiency of use of the aircraft.
- the task is achieved by the fact that in the rotary wing containing the fuselage, the wings mounted on the rotors with the ability to rotate and create at least lifting thrust, according to the invention, the rotors are arranged in series along the fuselage, on the axis of rotation of each rotor mounted two wings rotating opposite directions in different planes, and the angular position of each wing as it rotates is synchronized with the angular position of the other wings, while the oppositely rotating pair of wings of one rotor ahoditsya oppositely rotating in opposite pair of the other rotor wings with the ability to balance the centrifugal forces and moments of the four rotating wings.
- the task is also achieved by the fact that it may contain a propeller to create thrust during horizontal flight.
- the task is achieved by the fact that the wings can be installed with the possibility of their fixation relative to the fuselage in a predetermined position during horizontal flight.
- each wing can be equipped with an autonomous drive from an electric machine.
- FIG. 1 shows rotary wing rotary wing
- FIG. 2 - the same, in a different position of the wings;
- FIG. 3 rotary wing, front view
- FIG. 4 - rotorcraft, side view
- FIG. 5 rotary wing, isometric with fixed wings.
- the described rotary wing contains the fuselage 1, wings 2, 3, 4 and 5, mounted respectively on rotors 6 and 7, which are arranged in series along the fuselage 1.
- rotors 6 and 7 On the axis of rotation of the rotor 6, a pair of wings 2 and 3 is installed, and on the axis of rotation of the rotor 7 - a pair of wings 4 and 5.
- Wing 2 rotates in antiphase of wing 3, and wing 4 in antiphase of wing 5.
- each rotor 6 and 7 the wings rotate in opposite directions, balancing the moment and centrifugal forces on each rotor 6 and 7
- the oppositely rotating pair of wings 2 and 3 of the rotor 6 are located in otivofaze oppositely rotating pair of wings 4 and 5 of the rotor 7, with balancing centrifugal forces and moments of all four rotating wings 2-5.
- the angular position of each wing 2-5 when rotated, is synchronized with the angular position of the other wings.
- a rotary wing may contain a propulsor (not shown in the drawings) to create thrust during horizontal flight, or a horizontal thrust is created by rotating wings.
- the wings 2-5 can be installed with the possibility of their fixation relative to the fuselage 1 in a predetermined position during the horizontal flight of the rotor wing.
- Each wing 2-5 can be equipped with an autonomous drive from an electric machine (not shown in the drawings).
- Rotary wing works as follows. During takeoff, vertical flight or flight in helicopter mode, wings 2-5 are rotated in such a way that wings 2 and 3 of the rotor 6 rotate in opposite directions in parallel planes and the points of intersection of their rotation trajectory, in plan, are located on an imaginary longitudinal axis of the fuselage 1, that is, in a vertical plane passing through the longitudinal axis of the fuselage 1. The wings 3 and 4 of the other rotor 7 also rotate in opposite directions and the points of intersection of their rotation paths are also located in the plan on the same imaginary axis. fuselage b 1.
- each wing 2-5 can be performed with the most effective aerodynamic profile, which is especially important when using rotating wings 2-5 as bearing planes in aircraft mode when they are fixed relative to the fuselage 1 in a predetermined position. That is, when using the declared scheme of the aircraft, each wing 2-5 during horizontal flight in aircraft mode is set to a position in which its aerodynamic profile fully corresponds to the direction of flight. That is, each aerodynamic bearing surface is used as efficiently as possible with both vertical and horizontal flight. No need carry with them ballast elements that are effective only in one flight mode, but useless in another mode.
- the horizontal flight of the declared rotary-wing aircraft can be carried out both in a helicopter version with rotating wings 2-5, and in an aircraft version with a propulsor creating horizontal thrust and fixing each wing 2-5 in a predetermined position with a different sweep wing.
- the use of the claimed invention will improve the efficiency of flight due to the most efficient use of each aerodynamic element.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
Description
Винтокрыл Rotary wing
Область техники Technical field
Изобретение относится к области воздухоплавания, а именно к летательным аппаратам с несущими винтами. The invention relates to the field of aeronautics, namely to aircraft with rotors.
Предшествующий уровень техники Prior art
Известен винтокрыл, содержащий фюзеляж, движитель, для создания тяги преимущественно, при горизонтальном полете, крылья, установленные на роторах с возможностью вращения и создания подъемной тяги и возможностью их фиксации в заданном положении при горизонтальном полете (см. US2009/0014599 А1, опуб., 15.01.2009). Known rotary wing containing the fuselage, the propeller to create thrust mainly during horizontal flight, the wings mounted on the rotors with the ability to rotate and create a lifting thrust and the possibility of fixing them in a predetermined position during horizontal flight (see US2009 / 0014599 A1, publ., 01/15/2009).
Недостатком известного винтокрыла является наличие неуравновешенной силы инерции, действующей вдоль фюзеляжа в моменты пересечения траекторий вращающихся крыльев в передней и задней точках. Эта сила равна удвоенной центробежной силе, действующей на крыло. Указанное явление возникновения силы инерции в двух точках траектории используется в механизмах Ланчестера при уравновешивании поршневых двигателей внутреннего сгорания. A disadvantage of the known rotary-wing is the presence of an unbalanced inertia force acting along the fuselage at the moments of intersection of the trajectories of rotating wings in the front and rear points. This force is equal to twice the centrifugal force acting on the wing. This phenomenon of inertial force at two points of the trajectory is used in Lanchester's mechanisms when balancing piston internal combustion engines.
Известен винтокрыл, содержащий фюзеляж, движитель, для создания тяги преимущественно, при горизонтальном полете, крылья, установленные на роторах с возможностью вращения и создания подъемной тяги и возможностью их фиксации в заданном положении при горизонтальном полете (см. US4793572 А, опуб., 27.12.1988). Known rotary wing containing the fuselage propulsion to create thrust mainly in horizontal flight, the wings mounted on the rotors with the ability to rotate and create a lifting thrust and the possibility of fixing them in a predetermined position during horizontal flight (see US4793572 A, published, 27.12. 1988).
Недостатками известного винтокрыла являются невозможность расположения одного из крыльев каждого ротора в положении максимальной аэродинамической эффективности при его фиксации, так как крылья одного ротора вращаются в одну сторону и при перемещении крыльев в фиксированное положение одно из крыльев устанавливается задней (во время вращения) частью вперед. То есть оно не вьшолняет в полной мере функции крыла в горизонтальном полете, что снижает показатели винтокрыла в части полезной нагрузки. The disadvantages of the known rotary wing are the impossibility of placing one of the wings of each rotor in the position of maximum aerodynamic efficiency when it is fixed, since the wings of one rotor rotate in one direction and when moving the wings in a fixed position, one of the wings is set back. That is, it does not fully perform the function of the wing in horizontal flight, which reduces the performance of the rotor wing in terms of payload.
Раскрытие изобретения DISCLOSURE OF INVENTION
Техническим результатом заявленного изобретения является повышение эффективности использования летательного аппарата. Поставленная задача достигается тем, что в винтокрыле, содержащем фюзеляж, крылья, установленные на роторах с возможностью вращения и создания, по меньшей мере, подъемной тяги, согласно изобретению, роторы расположены последовательно вдоль фюзеляжа, на оси вращения каждого ротора установлены два крыла, вращающиеся в противоположных направлениях в разных плоскостях, а угловое положение каждого крыла при его вращении синхронизировано с угловым положением остальных крыльев, при этом противоположно вращающаяся пара крыльев одного ротора находится в противофазе противоположно вращающейся паре крыльев другого ротора с возможностью уравновешивания центробежных сил и моментов всех четырех вращающихся крыльев. The technical result of the claimed invention is to increase the efficiency of use of the aircraft. The task is achieved by the fact that in the rotary wing containing the fuselage, the wings mounted on the rotors with the ability to rotate and create at least lifting thrust, according to the invention, the rotors are arranged in series along the fuselage, on the axis of rotation of each rotor mounted two wings rotating opposite directions in different planes, and the angular position of each wing as it rotates is synchronized with the angular position of the other wings, while the oppositely rotating pair of wings of one rotor ahoditsya oppositely rotating in opposite pair of the other rotor wings with the ability to balance the centrifugal forces and moments of the four rotating wings.
Поставленная задача достигается также тем, что он может содержать движитель для создания тяги при горизонтальном полете. The task is also achieved by the fact that it may contain a propeller to create thrust during horizontal flight.
Поставленная задача достигается также тем, что крылья могут быть установлены с возможностью их фиксации относительно фюзеляжа в заданном положении при горизонтальном полете. The task is achieved by the fact that the wings can be installed with the possibility of their fixation relative to the fuselage in a predetermined position during horizontal flight.
Поставленная задача достигается также тем, что каждое крыло может быть снабжено автономным приводом от электрической машины. The task is also achieved by the fact that each wing can be equipped with an autonomous drive from an electric machine.
Краткое описание чертежей Brief Description of the Drawings
Изобретение поясняется при помощи чертежей. The invention is illustrated using the drawings.
На фиг. 1 показан винтокрыл с вращающимися крыльями; FIG. 1 shows rotary wing rotary wing;
На фиг. 2 - то же, в другом положении крыльев; FIG. 2 - the same, in a different position of the wings;
На фиг. 3 - винтокрыл, вид спереди; FIG. 3 - rotary wing, front view;
На фиг. 4 - винтокрыл, вид сбоку; FIG. 4 - rotorcraft, side view;
На фиг. 5 - винтокрыл, изометрия с фиксированными крыльями. FIG. 5 - rotary wing, isometric with fixed wings.
Лучший вариант осуществления изобретения The best embodiment of the invention
Описываемый винтокрыл содержит фюзеляж 1, крылья 2, 3, 4 и 5, установленные, соответственно, на роторах 6 и 7, которые расположены последовательно вдоль фюзеляжа 1. На оси вращения ротора 6 установлена пара крыльев 2 и 3, а на оси вращения ротора 7 - пара крыльев 4 и 5. Крыло 2 вращается в противофазе крылу 3, а крыло 4 - в противофазе крылу 5. То есть, на каждом роторе 6 и 7 крылья вращаются в противоположных направлениях, уравновешивая момент и центробежные силы на каждом роторе 6 и 7. При этом противоположно вращающаяся пара крыльев 2 и 3 ротора 6 находятся в противофазе противоположно вращающейся паре крыльев 4 и 5 ротора 7 с возможностью уравновешивания центробежных сил и моментов всех четырех вращающихся крыльев 2-5. Для этого угловое положение каждого крыла 2-5 при его вращении синхронизировано с угловым положением остальных крыльев. The described rotary wing contains the fuselage 1, wings 2, 3, 4 and 5, mounted respectively on rotors 6 and 7, which are arranged in series along the fuselage 1. On the axis of rotation of the rotor 6, a pair of wings 2 and 3 is installed, and on the axis of rotation of the rotor 7 - a pair of wings 4 and 5. Wing 2 rotates in antiphase of wing 3, and wing 4 in antiphase of wing 5. That is, on each rotor 6 and 7 the wings rotate in opposite directions, balancing the moment and centrifugal forces on each rotor 6 and 7 In this case, the oppositely rotating pair of wings 2 and 3 of the rotor 6 are located in otivofaze oppositely rotating pair of wings 4 and 5 of the rotor 7, with balancing centrifugal forces and moments of all four rotating wings 2-5. For this, the angular position of each wing 2-5, when rotated, is synchronized with the angular position of the other wings.
Винтокрыл может содержать движитель (на чертежах не показан) для создания тяги при горизонтальном полете, либо горизонтальная тяга создается вращающимися крыльями. A rotary wing may contain a propulsor (not shown in the drawings) to create thrust during horizontal flight, or a horizontal thrust is created by rotating wings.
Крылья 2-5 могут быть установлены с возможностью их фиксации относительно фюзеляжа 1 в заданном положении при горизонтальном полете винтокрыла. The wings 2-5 can be installed with the possibility of their fixation relative to the fuselage 1 in a predetermined position during the horizontal flight of the rotor wing.
Каждое крыло 2-5 может быть снабжено автономным приводом от электрической машины (на чертежах не показаны). Each wing 2-5 can be equipped with an autonomous drive from an electric machine (not shown in the drawings).
Винтокрыл работает следующим образом. При взлете, вертикальном полете или полете в режиме вертолета крылья 2-5 приводятся во вращение таким образом, что крылья 2 и 3 ротора 6 вращаются в противоположные стороны в параллельных плоскостях и точки пересечения их траектории вращения, в плане, расположены на воображаемой продольной оси фюзеляжа 1, то есть в вертикальной плоскости, проходящей через продольную ось фюзеляжа 1. Крылья 3 и 4 другого ротора 7 вращаются также в противоположные стороны и точки пересечения их траекторий вращения также расположены в плане на той же воображаемой оси фюзеляжа 1. При этом момент пересечения указанных траекторийобоих пар крыльев при их вращении совпадает по времени, а направление концов пары крыльев 2 и 3 противоположно направлению концов пары крыльев 4 и 5 в моменты пересечения их траекторий вращения с воображаемой продольной осью фюзеляжа 1. Rotary wing works as follows. During takeoff, vertical flight or flight in helicopter mode, wings 2-5 are rotated in such a way that wings 2 and 3 of the rotor 6 rotate in opposite directions in parallel planes and the points of intersection of their rotation trajectory, in plan, are located on an imaginary longitudinal axis of the fuselage 1, that is, in a vertical plane passing through the longitudinal axis of the fuselage 1. The wings 3 and 4 of the other rotor 7 also rotate in opposite directions and the points of intersection of their rotation paths are also located in the plan on the same imaginary axis. fuselage b 1. At this, the moment of intersection of the indicated paths of the pairs of wings when they rotate coincides in time, and the direction of the ends of the pair of wings 2 and 3 is opposite to the direction of the ends of the pair of wings 4 and 5 at the moments of intersection of their rotational trajectories with the imaginary longitudinal axis of the fuselage 1.
Промышленная применимость Industrial Applicability
Таким образом, указанное условие синхронизированного вращения всех крыльев 2-5 позволяет полностью уравновесить как центробежные силы, так и реактивные моменты, действующие на фюзеляж 1. При этом каждое крыло 2-5 может быть выполнено с наиболее эффективным аэродинамическим профилем, что особенно важно при использовании вращающихся крыльев 2-5 в качестве несущих плоскостей в самолетном режиме при их фиксации относительно фюзеляжа 1 в заданном положении. То есть при использовании заявленной схемы летательного аппарата каждое крыло 2-5 при горизонтальном полете в самолетном режиме устанавливается в положение, при котором его аэродинамический профиль полностью соответствует направлению полета. То есть каждая аэродинамическая несущая поверхность используется максимально эффективно как при вертикальном, так и при горизонтальном полете. При этом нет необходимости возить с собой балластные элементы, эффективные только при одном режиме полета, но бесполезные при другом режиме. Thus, the specified condition of synchronized rotation of all wings 2-5 allows to fully balance both centrifugal forces and reactive moments acting on the fuselage 1. In this case, each wing 2-5 can be performed with the most effective aerodynamic profile, which is especially important when using rotating wings 2-5 as bearing planes in aircraft mode when they are fixed relative to the fuselage 1 in a predetermined position. That is, when using the declared scheme of the aircraft, each wing 2-5 during horizontal flight in aircraft mode is set to a position in which its aerodynamic profile fully corresponds to the direction of flight. That is, each aerodynamic bearing surface is used as efficiently as possible with both vertical and horizontal flight. No need carry with them ballast elements that are effective only in one flight mode, but useless in another mode.
Горизонтальный полет заявленного винтокрыла может осуществляться как в вертолетном варианте с вращающимися крыльями 2-5, так и в самолетном варианте с движителем, создающим горизонтальную тягу, и фиксированием каждого крыла 2-5 в заданном положении при различной стреловидностикрыла. The horizontal flight of the declared rotary-wing aircraft can be carried out both in a helicopter version with rotating wings 2-5, and in an aircraft version with a propulsor creating horizontal thrust and fixing each wing 2-5 in a predetermined position with a different sweep wing.
Таким образом, использование заявленного изобретения позволит повысить эффективность полета за счет максимально эффективного использования каждого аэродинамического элемента. Thus, the use of the claimed invention will improve the efficiency of flight due to the most efficient use of each aerodynamic element.
Claims
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2017132301A RU2661262C1 (en) | 2017-09-15 | 2017-09-15 | Rotary-wing aircraft |
| RU2017132301 | 2017-09-15 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2019054896A1 true WO2019054896A1 (en) | 2019-03-21 |
Family
ID=62917266
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/RU2018/000270 Ceased WO2019054896A1 (en) | 2017-09-15 | 2018-04-25 | Rotorcraft |
Country Status (2)
| Country | Link |
|---|---|
| RU (1) | RU2661262C1 (en) |
| WO (1) | WO2019054896A1 (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4793572A (en) * | 1986-02-06 | 1988-12-27 | John Mecca | Vertical launch and hovering space shuttle |
| US20090014599A1 (en) * | 2006-03-27 | 2009-01-15 | The Government Of The Us, As Represented By The Secretary Of The Navy | Convertible aerial vehicle with contra-rotating wing/rotors and twin tilting wing and propeller units |
| RU2500578C1 (en) * | 2012-07-02 | 2013-12-10 | Сергей Николаевич ПАВЛОВ | Rotary-wing aircraft |
| US20140312177A1 (en) * | 2013-04-18 | 2014-10-23 | Rajesh Gaonjur | Coaxial rotor/wing aircraft |
| RU2598105C1 (en) * | 2015-08-28 | 2016-09-20 | Дмитрий Сергеевич Дуров | Multirotor unmanned high-speed helicopter |
-
2017
- 2017-09-15 RU RU2017132301A patent/RU2661262C1/en not_active IP Right Cessation
-
2018
- 2018-04-25 WO PCT/RU2018/000270 patent/WO2019054896A1/en not_active Ceased
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4793572A (en) * | 1986-02-06 | 1988-12-27 | John Mecca | Vertical launch and hovering space shuttle |
| US20090014599A1 (en) * | 2006-03-27 | 2009-01-15 | The Government Of The Us, As Represented By The Secretary Of The Navy | Convertible aerial vehicle with contra-rotating wing/rotors and twin tilting wing and propeller units |
| RU2500578C1 (en) * | 2012-07-02 | 2013-12-10 | Сергей Николаевич ПАВЛОВ | Rotary-wing aircraft |
| US20140312177A1 (en) * | 2013-04-18 | 2014-10-23 | Rajesh Gaonjur | Coaxial rotor/wing aircraft |
| RU2598105C1 (en) * | 2015-08-28 | 2016-09-20 | Дмитрий Сергеевич Дуров | Multirotor unmanned high-speed helicopter |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2661262C1 (en) | 2018-07-13 |
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