WO2017180020A1 - Aircraft - Google Patents
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- WO2017180020A1 WO2017180020A1 PCT/RU2016/000860 RU2016000860W WO2017180020A1 WO 2017180020 A1 WO2017180020 A1 WO 2017180020A1 RU 2016000860 W RU2016000860 W RU 2016000860W WO 2017180020 A1 WO2017180020 A1 WO 2017180020A1
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- Prior art keywords
- aircraft
- fan wheel
- jet engine
- mode
- blade
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
Definitions
- the present invention relates to the field of aircraft (LA) and can serve as an alternative to a helicopter fleet.
- Aircraft are known, disclosed, for example, in patents RU 2495795, published April 10, 2005 and RU 2348567, published March 10, 2009, the hull of which is made in the form of bodies of revolution. Moreover, the cockpit, control systems, landing systems are located inside the hull.
- the aim of the present invention is to provide an aircraft in which a sparing mode of operation of the blades of the fan wheel (VK) is provided, unlike the blades of a helicopter, since a swash plate is not used and a larger number of blades of the fan wheel (VK) reduce the voltage in the blades.
- the technical result consists in increasing the reliability of the operation of the aircraft, as well as its safety and maneuverability.
- the aircraft contains a housing made in the form of a disk-shaped body of revolution, in which, as the propulsors connected to the housing, an annular fan wheel that creates the main lifting force and an air-jet engine (WFD) of opposite rotation are used, moreover the annular fan wheel (VK) has controllable blade vanes, while the aircraft also contains a first blade apparatus directing air flow to the blade vanes of the VK and a second vane apparatus, which ensures the rectification of the air flow discharged by the VC, and the lenticular housing has the ability to accommodate the cockpit, control system, landing system and fan wheel drive, the jet engine is configured to provide two functions, including generating electricity for the fan drive wheels, control systems and electricity consumers installed on board the aircraft apparatus, and is also configured to provide additional lifting thrust at the start mode or hovering mode using a rotary nozzle with the provision of further marching thrust.
- WFD air-jet engine
- the principle of equality of the momentum of the moment of force of the fan wheel and the jet engine is used, controlled by the on-board computer with a coaxial arrangement of propulsion devices (for example, as in a helicopter). Flight control is additionally carried out by pitch and roll control windows, by passing air from the dorsal region to the dorsal region.
- the fan wheel is driven by three drives, each mounted on a three-pointed star-shaped power beam in the body of the aircraft.
- drives their installation is carried out either on the power ring or, for example, 4 drives - on the X-shaped beam.
- Figure 1 shows a General view of the aircraft.
- the proposed aircraft has the appearance of a "flying saucer.”
- the apparatus has a circular disk-shaped body, in which an annular fan wheel 2 with controlled vanes-blades located between the inner and outer rims of the VK, creating the main lifting force, and an opposite-rotation air-jet engine (WFD) are used as a propeller 4 - coaxial circuit, a guide vane apparatus 1, which improves the parameters of the air flow entering the VK, a second straightening vane apparatus 3, which organizes the air flow after the VC, a round cranial fuselage (in figure It is presented as flat), in which there is a pilot cabin 7 (2 pilots are shown in the figure), control systems, landing systems 8 (telescopic racks), fan wheel drive (PVC) 6.
- WFD opposite-rotation air-jet engine
- WFD 4 has two functions: generating electricity for PVC and for control systems, as well as other consumers of electricity, and the creation of additional lifting thrust at the starting or hovering mode and with the help of a rotary nozzle, which creates a thrust of marching mode. To ensure exchange rate stability, the principle of equality is used.
- Impulse moment of force VK and WFD controlled by the on-board computer. Controlled mismatch of rotation allows you to choose the course of flight.
- Other flight control functions are provided by the pitch and roll control windows 6 by air bypass from the dorsal region to the dorsal region or by other special control methods.
- the proposed flight of the aircraft is as follows: 1) the aircraft is initially located on the ground with the help of retractable landing gears 8, 2) the WFD 4 is launched with a rotary nozzle 5, with the thrust vector set vertically, 3) upon receipt of the necessary electric power of the PVC, which can be both gear and hydraulic type (in the figure their number is 3 pcs.) they spin the fan wheel 2, while the WFD 4 and VK 2 rotations, carried out in opposite directions, are controlled by the control system, ensuring equal TVO torques.
- the air flow passing through the guide vanes 1 is sucked in by a fan wheel 2 with installed adjustable vanes, similar to shortened rotor blades of the helicopter (the number of vanes is determined experimentally) in the “lift” mode and passing through the air vanes of the second vanes 3, creates aircraft lift together with the WFD 4, 4) when climbing, landing gear 8 is removed and a negative aircraft pitch is set to start the marching movement, 5) to select of the required marching mode, the nozzle is rotated 5 to 90 ° to the axis of the aircraft; 6) aircraft maneuvering is carried out: along the course - by mismatching the torque of the WFD, by pitch - by opening-closing the front control windows 9 and by turning the nozzle 5, by roll - by opening-closing left or right pair of windows 9 of the aircraft.
- the rotation of the fan wheel occurs around the cockpit structure, i.e. the cockpit is located in the central part of the aircraft.
- the use of this invention provides a more sparing mode of operation of VK blades, in contrast to helicopter blades, since a swash plate is not used and a larger number of VK blades reduce stress in the blades.
- the blades are located inside the rim of the fan wheel and the hull of the aircraft and cannot be destroyed when the aircraft comes into contact with trees, houses, power lines, etc.
- it is easier to organize the evacuation of the flight crew (there are no chopping blades of the helicopter ) and the device itself is capable of parachuting, providing a non-rigid landing, while the controlled blades VK 2 can be installed in a transverse air flow position.
- the device of the proposed device allows you to install standard rescue parachutes.
- the streamlined shape of the "flying saucer" and the rotary nozzle make it possible to obtain speeds more substantial than those of helicopters.
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
ОПИСАНИЕ DESCRIPTION
ЛЕТАТЕЛЬНЫЙ АППАРАТ AIRCRAFT
Область техники Technical field
Настоящее изобретение относится к области летательных аппаратов (ЛА) и может служить альтернативой вертолетному парку. The present invention relates to the field of aircraft (LA) and can serve as an alternative to a helicopter fleet.
Уровень техники State of the art
Известны летательные аппараты, раскрытые, например, в патентах RU 2495795, опубликован 10.04.2005 и RU 2348567, опубликован 10.03.2009, корпуса которых выполнены в виде тел вращения. Причём внутри корпуса размещены кабина пилотов, системы управления, системы посадки. Aircraft are known, disclosed, for example, in patents RU 2495795, published April 10, 2005 and RU 2348567, published March 10, 2009, the hull of which is made in the form of bodies of revolution. Moreover, the cockpit, control systems, landing systems are located inside the hull.
Известные ЛА обладают рядом существенных недостатков, а именно, имеют ненадёжную и сложную конструкцию. Known aircraft have a number of significant drawbacks, namely, they have an unreliable and complex design.
Раскрытие изобретения Disclosure of invention
Целью настоящего изобретения является создание летательного аппарата, в котором обеспечивается щадящий режим работы лопаток вентиляторного колеса (ВК) в отличие от лопастей вертолета, так как не применяется автомат перекоса и большее количество лопаток вентиляторного колеса (ВК) уменьшают напряжения в лопатках. The aim of the present invention is to provide an aircraft in which a sparing mode of operation of the blades of the fan wheel (VK) is provided, unlike the blades of a helicopter, since a swash plate is not used and a larger number of blades of the fan wheel (VK) reduce the voltage in the blades.
Технический результат заключается в повышении надёжности при эксплуатации летательного аппарата, а также его безопасности, маневренности. The technical result consists in increasing the reliability of the operation of the aircraft, as well as its safety and maneuverability.
Указанный технический результат достигается тем, что летательный аппарат, содержит корпус, выполненный в виде дискообразного тела вращения, в котором в качестве соединенных с корпусом движителей используются кольцевое вентиляторное колесо, создающее главную подъемную силу, и воздушно-реактивный двигатель (ВРД) противоположного вращения, причём кольцевое вентиляторное колесо (ВК) имеет управляемые лопатки-лопасти, при этом летательный аппарат также содержит первый лопаточный аппарат, направляющий воздушный поток на лопатки-лопасти ВК, и второй лопаточный аппарат, обеспечивающий выпрямление воздушного потока, отбрасываемого ВК, причём чечевицеобразный корпус имеет возможность размещения кабины пилотов, системы управления, системы посадки и привода вентиляторного колеса, воздушно- реактивный двигатель выполнен с возможностью обеспечения двух функций, включающих генерирование электроэнергии для привода вентиляторного колеса, систем управления и потребителей электроэнергии, установленных на борту летательного аппарата, а также выполнен с возможностью обеспечения дополнительной подъемной тяги на стартовом режиме или режиме висения при помощи поворотного сопла с обеспечением в дальнейшем тяги маршевого режима. The specified technical result is achieved in that the aircraft contains a housing made in the form of a disk-shaped body of revolution, in which, as the propulsors connected to the housing, an annular fan wheel that creates the main lifting force and an air-jet engine (WFD) of opposite rotation are used, moreover the annular fan wheel (VK) has controllable blade vanes, while the aircraft also contains a first blade apparatus directing air flow to the blade vanes of the VK and a second vane apparatus, which ensures the rectification of the air flow discharged by the VC, and the lenticular housing has the ability to accommodate the cockpit, control system, landing system and fan wheel drive, the jet engine is configured to provide two functions, including generating electricity for the fan drive wheels, control systems and electricity consumers installed on board the aircraft apparatus, and is also configured to provide additional lifting thrust at the start mode or hovering mode using a rotary nozzle with the provision of further marching thrust.
В заявленном изобретении для обеспечения режима курсовой устойчивости используется принцип равенства импульса момента силы вентиляторного колеса и воздушно-реактивного двигателя, контролируемого бортовым компьютером при соостной схеме расположения движителей (например, как в вертолете). Управление полетом дополнительно осуществляются окнами управления тангажом и креном, посредством перепуска воздуха из надфюзеляжной области в подфюзеляжную. In the claimed invention, to ensure exchange rate stability, the principle of equality of the momentum of the moment of force of the fan wheel and the jet engine is used, controlled by the on-board computer with a coaxial arrangement of propulsion devices (for example, as in a helicopter). Flight control is additionally carried out by pitch and roll control windows, by passing air from the dorsal region to the dorsal region.
В одном из вариантов выполнения заявленного изобретения привод вентиляторного колеса осуществляется посредством трех приводов, установленных каждый на трехконечной звездообразной силовой балке в корпусе летательного аппарата. In one embodiment of the claimed invention, the fan wheel is driven by three drives, each mounted on a three-pointed star-shaped power beam in the body of the aircraft.
В другом из вариантов при потребности разместить большее количество In another of the options, if necessary, place more
приводов их установка осуществляется или на силовом кольце или, например, 4 привода - на Х-образной балке. drives their installation is carried out either on the power ring or, for example, 4 drives - on the X-shaped beam.
Краткое описание чертежей Brief Description of the Drawings
На фиг.1 показан общий вид летательного аппарата. Figure 1 shows a General view of the aircraft.
Осуществление изобретения The implementation of the invention
Предлагаемый ЛА имеет облик «летающей тарелки». Аппарат имеет круглый дискообразный корпус, в котором в качестве движителя используются кольцевое вентиляторное колесо 2 с управляемыми лопатками-лопастями, расположенными между внутренним и внешним ободами ВК, создающее главную подъемную силу, и воздушно- реактивный двигатель (ВРД) противоположного вращения 4 - соосная схема, направляющий лопаточный аппарат 1, улучшающий параметры воздушнго потока, поступающего на ВК, второй спрямляющий лопаточный аппарат 3, организующий воздушный поток после ВК, круглый чечевидный фюзеляж (на рисунке представлен как плоский), в котором расположены кабина пилотов 7 (на рисунке указаны 2 пилота), системы управления, системы посадки 8 (телескопические стойки), привод вентиляторного колеса (ПВК) 6. ВРД 4 имеет две функции: генерирование электроэнергии для ПВК и для систем управления, а также других потребителей электроэнергии и создание дополнительной подъемной тяги на стартовом режиме или режиме висения и при помощи поворотного сопла, создающего тягу маршевого режима. Для обеспечения режима курсовой устойчивости используется принцип равенства импульса момента силы ВК и ВРД, контролируемого бортовым компьютером. Управляемое рассогласование вращения позволяет выбирать курс полета. Другие функции управления полетом осуществляется окнами управления 6 тангажом и креном перепуском воздуха из надфюзеляжной области в подфюзеляжную или иными специальными способами управления. The proposed aircraft has the appearance of a "flying saucer." The apparatus has a circular disk-shaped body, in which an annular fan wheel 2 with controlled vanes-blades located between the inner and outer rims of the VK, creating the main lifting force, and an opposite-rotation air-jet engine (WFD) are used as a propeller 4 - coaxial circuit, a guide vane apparatus 1, which improves the parameters of the air flow entering the VK, a second straightening vane apparatus 3, which organizes the air flow after the VC, a round cranial fuselage (in figure It is presented as flat), in which there is a pilot cabin 7 (2 pilots are shown in the figure), control systems, landing systems 8 (telescopic racks), fan wheel drive (PVC) 6. WFD 4 has two functions: generating electricity for PVC and for control systems, as well as other consumers of electricity, and the creation of additional lifting thrust at the starting or hovering mode and with the help of a rotary nozzle, which creates a thrust of marching mode. To ensure exchange rate stability, the principle of equality is used. Impulse moment of force VK and WFD, controlled by the on-board computer. Controlled mismatch of rotation allows you to choose the course of flight. Other flight control functions are provided by the pitch and roll control windows 6 by air bypass from the dorsal region to the dorsal region or by other special control methods.
Предполагаемый полет ЛА осуществляется следующим образом: 1) первоначально ЛА находится на земле при помощи выдвижных стоек-шасси 8, 2) запускается ВРД 4 с поворотным соплом 5, с выставленном вертикально вектором тяги, 3) при получении необходимой электрической мощности ПВК, которые могут быть как шестеренчатого, так и гидравлического типа (на рисунке их количество - 3 шт.) производят раскрутку вентиляторного колеса 2 , при этом вращения ВРД 4 и ВК 2, осуществляемые в противоположные стороны, контролируются системой управления, обеспечивая равенство моментов вращения. Воздушный поток, проходя через направляющий лопаточный аппарат 1 , засасывается вентиляторным колесом 2 с установленными регулируемыми лопатками, подобными укороченным лопастям несущего винта вертолета (количество лопаток-лопастей определяется экспериментально) в режиме «подъем» и проходя через спрямляющие воздушный поток лопатки второго лопаточного аппарата 3, создает подъемную силу ЛА совместно с ВРД 4, 4) при наборе высоты убираются стойки-шасси 8 и устанавливается отрицательный тангаж ЛА для начала маршевого движения, 5) для выбора необходимого маршевого режима осуществляется поворот сопла 5 до 90° к оси ЛА, 6) маневрирование ЛА осуществляется: по курсу - рассогласованием вращательного момента вращения ВРД, по тангажу - открытием-закрытием передних окон управления 9 и поворотом сопла 5, по крену - открытием-закрытием левой или правой пары окон 9 летательного аппарата. The proposed flight of the aircraft is as follows: 1) the aircraft is initially located on the ground with the help of retractable landing gears 8, 2) the WFD 4 is launched with a rotary nozzle 5, with the thrust vector set vertically, 3) upon receipt of the necessary electric power of the PVC, which can be both gear and hydraulic type (in the figure their number is 3 pcs.) they spin the fan wheel 2, while the WFD 4 and VK 2 rotations, carried out in opposite directions, are controlled by the control system, ensuring equal TVO torques. The air flow passing through the guide vanes 1 is sucked in by a fan wheel 2 with installed adjustable vanes, similar to shortened rotor blades of the helicopter (the number of vanes is determined experimentally) in the “lift” mode and passing through the air vanes of the second vanes 3, creates aircraft lift together with the WFD 4, 4) when climbing, landing gear 8 is removed and a negative aircraft pitch is set to start the marching movement, 5) to select of the required marching mode, the nozzle is rotated 5 to 90 ° to the axis of the aircraft; 6) aircraft maneuvering is carried out: along the course - by mismatching the torque of the WFD, by pitch - by opening-closing the front control windows 9 and by turning the nozzle 5, by roll - by opening-closing left or right pair of windows 9 of the aircraft.
Причём согласно фиг. 1 вращение вентиляторного колеса происходит вокруг конструктива кабины пилотов, т.е. кабина пилотов расположена в центральной части ЛА. Moreover, according to FIG. 1, the rotation of the fan wheel occurs around the cockpit structure, i.e. the cockpit is located in the central part of the aircraft.
Использование данного изобретения обеспечивает более щадящий режим работы лопаток ВК в отличие от лопастей вертолета, так как не применяется автомат перекоса и большее количество лопаток ВК уменьшают напряжения в лопатках. При этом лопатки- лопасти находятся внутри обода вентиляторного колеса и корпуса летательного аппарата и не могут разрушиться при соприкосновении ЛА с деревьями, домами, линиями электропередач и пр. Кроме того, в случае аварийной ситуации в полете проще организовать эвакуацию летного состава (нет секущих лопастей вертолета), а сам аппарат способен парашютировать, обеспечивая нежесткую посадку, при этом управляемые лопатки ВК 2 могут быть установлены в поперечном воздушному потоку положении. Устройство предлагаемого аппарата позволяет устанавливать стандартные парашюты спасения. Обтекаемая форма «летающей тарелки» и поворотное сопло позволяют получить скорости более существенные, чем у вертолетов. The use of this invention provides a more sparing mode of operation of VK blades, in contrast to helicopter blades, since a swash plate is not used and a larger number of VK blades reduce stress in the blades. In this case, the blades are located inside the rim of the fan wheel and the hull of the aircraft and cannot be destroyed when the aircraft comes into contact with trees, houses, power lines, etc. In addition, in case of emergency in flight, it is easier to organize the evacuation of the flight crew (there are no chopping blades of the helicopter ), and the device itself is capable of parachuting, providing a non-rigid landing, while the controlled blades VK 2 can be installed in a transverse air flow position. The device of the proposed device allows you to install standard rescue parachutes. The streamlined shape of the "flying saucer" and the rotary nozzle make it possible to obtain speeds more substantial than those of helicopters.
Claims
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2016113740 | 2016-04-11 | ||
| RU2016113740A RU2617014C1 (en) | 2016-04-11 | 2016-04-11 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2017180020A1 true WO2017180020A1 (en) | 2017-10-19 |
Family
ID=58642882
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/RU2016/000860 Ceased WO2017180020A1 (en) | 2016-04-11 | 2016-12-09 | Aircraft |
Country Status (2)
| Country | Link |
|---|---|
| RU (1) | RU2617014C1 (en) |
| WO (1) | WO2017180020A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN110588974A (en) * | 2019-09-30 | 2019-12-20 | 合肥中科重明科技有限公司 | A high-efficiency propulsion device based on ground rotation energy storage |
| CN111377059A (en) * | 2020-05-19 | 2020-07-07 | 重庆宇矛航空科技有限公司 | High-lifting-force wingless aircraft power system |
| US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2668541C1 (en) * | 2017-10-12 | 2018-10-01 | Светослав Владимирович Занегин | Flying vehicle |
| RU2708775C1 (en) * | 2018-12-17 | 2019-12-11 | Николай Борисович Болотин | Helicopter |
| RU2714090C1 (en) * | 2018-12-17 | 2020-02-11 | Николай Борисович Болотин | Rotorcraft |
| RU2759060C1 (en) * | 2020-12-18 | 2021-11-09 | Сергей Федорович Таранов | Reusable transport apparatus |
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| US6575401B1 (en) * | 2001-08-07 | 2003-06-10 | Howard J. Carver | Vertical-lift and horizontal flight aircraft |
| US20070215748A1 (en) * | 2006-03-20 | 2007-09-20 | Robbins Brent A | VTOL UA V with lift fans in joined wings |
| RU2365522C1 (en) * | 2008-01-21 | 2009-08-27 | Кравченко Виктор Александрович | Flying source |
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2016
- 2016-04-11 RU RU2016113740A patent/RU2617014C1/en active IP Right Revival
- 2016-12-09 WO PCT/RU2016/000860 patent/WO2017180020A1/en not_active Ceased
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6575401B1 (en) * | 2001-08-07 | 2003-06-10 | Howard J. Carver | Vertical-lift and horizontal flight aircraft |
| US20070215748A1 (en) * | 2006-03-20 | 2007-09-20 | Robbins Brent A | VTOL UA V with lift fans in joined wings |
| RU2365522C1 (en) * | 2008-01-21 | 2009-08-27 | Кравченко Виктор Александрович | Flying source |
| RU2530906C1 (en) * | 2013-10-18 | 2014-10-20 | Общество с ограниченной ответственностью "ФАН ФЛАЙТ" | Drone |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN110588974A (en) * | 2019-09-30 | 2019-12-20 | 合肥中科重明科技有限公司 | A high-efficiency propulsion device based on ground rotation energy storage |
| CN110588974B (en) * | 2019-09-30 | 2021-04-27 | 中国科学院力学研究所 | A high-efficiency propulsion device based on ground rotation energy storage |
| CN111377059A (en) * | 2020-05-19 | 2020-07-07 | 重庆宇矛航空科技有限公司 | High-lifting-force wingless aircraft power system |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2617014C1 (en) | 2017-04-19 |
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