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RU2016110050A - VERTICAL TAKEOFF AND LANDING FLIGHT AND ITS FLIGHT CONTROL METHOD - Google Patents

VERTICAL TAKEOFF AND LANDING FLIGHT AND ITS FLIGHT CONTROL METHOD Download PDF

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Publication number
RU2016110050A
RU2016110050A RU2016110050A RU2016110050A RU2016110050A RU 2016110050 A RU2016110050 A RU 2016110050A RU 2016110050 A RU2016110050 A RU 2016110050A RU 2016110050 A RU2016110050 A RU 2016110050A RU 2016110050 A RU2016110050 A RU 2016110050A
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RU
Russia
Prior art keywords
flight
mode
airplane
lifting
landing
Prior art date
Application number
RU2016110050A
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Russian (ru)
Other versions
RU2638221C2 (en
Inventor
Илья Васильевич Араксин
Сергей Михайлович Александров
Original Assignee
Открытое акционерное общество "Рикор Электроникс"
Priority date (The priority date 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 date listed.)
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Publication date
Application filed by Открытое акционерное общество "Рикор Электроникс" filed Critical Открытое акционерное общество "Рикор Электроникс"
Priority to RU2016110050A priority Critical patent/RU2638221C2/en
Publication of RU2016110050A publication Critical patent/RU2016110050A/en
Application granted granted Critical
Publication of RU2638221C2 publication Critical patent/RU2638221C2/en

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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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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)
  • Transmission Devices (AREA)

Claims (4)

1. Аппарат вертикального взлета и посадки, содержащий маршевую силовую установку для горизонтального полета в самолетном режиме, как минимум от трех отдельных подъемных силовых установок для создания тяги в вертикальной оси в режиме висения, отличающийся тем, что плоскость вращения воздушных винтов подъемных силовых установок расположена жестко закрепленной под углом от 2 до 35° к несущим плоскостям крыла или крыльев.1. The apparatus of vertical take-off and landing, containing the marching power plant for horizontal flight in airplane mode, from at least three separate lifting power plants to create traction in the vertical axis in hovering mode, characterized in that the plane of rotation of the propellers of the lifting power plants fixed at an angle from 2 to 35 ° to the bearing planes of the wing or wings. 2. Аппарат вертикального взлета и посадки по п. 1, отличающийся тем, что винты подъемных силовых установок для создания тяги в горизонтальной оси в переходном режиме жестко установлены под углом от 2 до 35° к несущим плоскостям крыла или крыльев.2. The vertical take-off and landing apparatus according to claim 1, characterized in that the screws of the lifting power plants for creating traction in the horizontal axis in the transition mode are rigidly mounted at an angle of 2 to 35 ° to the bearing planes of the wing or wings. 3. Способ управления полетом заявленного летательного аппарата, характеризующийся тем, что в момент взлета летательного аппарата в режиме висения с положительным углом тангажа от 2 до 35° для набора достаточной скорости на подъемных двигателях с целью осуществления перехода в самолетный режим полета, осуществляют наклон всего летательного аппарата вперед до угла тангажа, обеспечивающего горизонтальный полет в самолетном режиме, после достижения необходимой скорости (1,1-1,5 скорости сваливания) подъемные двигатели полностью или частично отключают.3. The flight control method of the claimed aircraft, characterized in that at the time of take-off of the aircraft in hovering mode with a positive pitch angle of 2 to 35 ° to set sufficient speed on lifting engines in order to switch to airplane flight mode, the entire aircraft is tilted the apparatus forward to the pitch angle, ensuring horizontal flight in airplane mode, after reaching the necessary speed (1.1-1.5 stall speed) lifting motors in full or in part tklyuchayut. 4. Способ по п. 3, отличающийся тем, что после перехода в самолетный режим полета используют дополнительную силовую установку.4. The method according to p. 3, characterized in that after the transition to the airplane flight mode, an additional power plant is used.
RU2016110050A 2016-03-18 2016-03-18 Vertical take-off and landing aircraft and method to control its flight RU2638221C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2016110050A RU2638221C2 (en) 2016-03-18 2016-03-18 Vertical take-off and landing aircraft and method to control its flight

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2016110050A RU2638221C2 (en) 2016-03-18 2016-03-18 Vertical take-off and landing aircraft and method to control its flight

Publications (2)

Publication Number Publication Date
RU2016110050A true RU2016110050A (en) 2017-09-21
RU2638221C2 RU2638221C2 (en) 2017-12-12

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
RU2016110050A RU2638221C2 (en) 2016-03-18 2016-03-18 Vertical take-off and landing aircraft and method to control its flight

Country Status (1)

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RU (1) RU2638221C2 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110554705A (en) * 2019-09-25 2019-12-10 深圳市飞鱼星科技有限公司 control method for changing tilting into flat flying of aircraft
CN115416849A (en) * 2022-10-11 2022-12-02 清华大学 Sectional type design and tracking control of transition instruction track of vertical take-off and landing fixed wing aircraft

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2681423C1 (en) * 2017-12-19 2019-03-06 Федеральное государственное бюджетное образовательное учреждение высшего образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева-КАИ" (КНИТУ-КАИ) Modular construction of an unmanned aerial vertical for vertical take-off and landing
RU181389U1 (en) * 2018-01-09 2018-07-11 Федеральное государственное бюджетное образовательное учреждение высшего образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева-КАИ" (КНИТУ-КАИ) MODULAR DESIGN OF THE UNMANNED AIRCRAFT VERTICAL TAKEOFF AND LANDING WITH COMBINED POWER PLANT
RU2770513C2 (en) * 2021-06-09 2022-04-18 Общество с ограниченной ответственностью "ФЛАЙТЕР" Aircraft
RU2771195C1 (en) * 2021-12-17 2022-04-28 Кирилл Николаевич Яковченко Rotary-wing unmanned aerial vehicle of tandem scheme

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2458822C1 (en) * 2011-05-18 2012-08-20 Пётр Иванович Дуров Vertical take-off and landing aircraft
RU129485U1 (en) * 2012-12-26 2013-06-27 Яков Александрович Колесник COXY SPEED HELICOPTER
RU2547950C1 (en) * 2013-12-19 2015-04-10 Общество с ограниченной ответственностью научно-производственное предприятие "Измерон-В" (ООО НПП "Измерон-В") Quadrocopter
US20160031554A1 (en) * 2014-07-30 2016-02-04 Siniger LLC Control system for an aircraft
US10046853B2 (en) * 2014-08-19 2018-08-14 Aergility LLC Hybrid gyrodyne aircraft employing a managed autorotation flight control system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110554705A (en) * 2019-09-25 2019-12-10 深圳市飞鱼星科技有限公司 control method for changing tilting into flat flying of aircraft
CN115416849A (en) * 2022-10-11 2022-12-02 清华大学 Sectional type design and tracking control of transition instruction track of vertical take-off and landing fixed wing aircraft

Also Published As

Publication number Publication date
RU2638221C2 (en) 2017-12-12

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