RU94017618A - Combination vertical take-off and landing rotary-wing aircraft and method of conversion of rotary-wing flying vehicle into aircraft configuration - Google Patents

Combination vertical take-off and landing rotary-wing aircraft and method of conversion of rotary-wing flying vehicle into aircraft configuration

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Publication number
RU94017618A
RU94017618A RU94017618/11A RU94017618A RU94017618A RU 94017618 A RU94017618 A RU 94017618A RU 94017618/11 A RU94017618/11 A RU 94017618/11A RU 94017618 A RU94017618 A RU 94017618A RU 94017618 A RU94017618 A RU 94017618A
Authority
RU
Russia
Prior art keywords
aircraft
rotary
blade
wing
rotor
Prior art date
Application number
RU94017618/11A
Other languages
Russian (ru)
Other versions
RU2092392C1 (en
Inventor
И.С. Говор
М.В. Дмитриев
Original Assignee
Научно-производственная фирма "Новые технологии - товары потребления"
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 Научно-производственная фирма "Новые технологии - товары потребления" filed Critical Научно-производственная фирма "Новые технологии - товары потребления"
Priority to RU94017618A priority Critical patent/RU2092392C1/en
Publication of RU94017618A publication Critical patent/RU94017618A/en
Application granted granted Critical
Publication of RU2092392C1 publication Critical patent/RU2092392C1/en

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Abstract

FIELD: aeronautical engineering. SUBSTANCE: combination vertical take-off and landing aircraft possess properties of helicopter and aircraft. Method of conversion of rotary-wing flying vehicle into aircraft configuration makes it possible to exclude drag of main rotor at aircraft modes of flight. Combination vertical take-off and landing aircraft has all main components of aircraft and helicopter. It is made by single-rotor lay-out with steering rotor and tractor propeller and single-blade main rotor with mass balance weight. Conversion of combination vertical take-off and landing flying vehicle from rotary-wing configuration into aircraft configuration is effected in horizontal flight through bracing the blade and shifting it to feathered pitch followed by approach of blade and mass balance weight with fuselage; in course of approach, blade and mass balance weight get coupled with fuselage, thus forming common aerodynamic lines. EFFECT: enhanced reliability. 3 cl, 3 dwg

Claims (1)

Предложены комбинированный самолет вертикального взлета и посадки (СВВП), обладающий свойствами вертолета и самолета, и способ преобразования винтокрылого летательного аппарата в самолетную конфигурацию, позволяющий исключить лобовое сопротивление несущего винта на самолетных режимах полета. СВВП содержит все основные элементы самолета и вертолета и выполнен по одновинтовой схеме с рулевым и тянущим винтами и убирающимся в полете однолопастным несущим винтом с весовым балансиром. Преобразование СВВП из винтокрылой конфигурации в самолетную осуществляется в горизонтальном полете путем торможения и перевода лопасти несущего винта в флюгерное положение с последующим сближением лопасти и весового балансира с фюзеляжем, в процессе которого лопасть и весовой балансир смыкаются с конструкцией фюзеляжа, образуя с ним общие аэродинамические обводы.A combined vertical take-off and landing aircraft (VTOL), which has the properties of a helicopter and an airplane, and a method for converting a rotary-wing aircraft into an aircraft configuration, which allows to exclude the rotor drag in aircraft flight modes, are proposed. VTOL contains all the basic elements of an airplane and a helicopter and is made according to a single-rotor scheme with a steering and pulling propellers and a single-blade rotor retractable in flight with a weight balancer. VTOL is converted from a rotorcraft to a plane in horizontal flight by braking and transferring the rotor blade to the vane position, followed by the rapprochement of the blade and the weight balancer with the fuselage, during which the blade and weight balancer are connected to the fuselage structure, forming common aerodynamic contours with it.
RU94017618A 1994-05-17 1994-05-17 Method of conversion of rotary-wing aircraft into aeroplane configuration and combined vertical take-off and landing rotary-wing aircraft for realization of this method RU2092392C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU94017618A RU2092392C1 (en) 1994-05-17 1994-05-17 Method of conversion of rotary-wing aircraft into aeroplane configuration and combined vertical take-off and landing rotary-wing aircraft for realization of this method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU94017618A RU2092392C1 (en) 1994-05-17 1994-05-17 Method of conversion of rotary-wing aircraft into aeroplane configuration and combined vertical take-off and landing rotary-wing aircraft for realization of this method

Publications (2)

Publication Number Publication Date
RU94017618A true RU94017618A (en) 1996-07-27
RU2092392C1 RU2092392C1 (en) 1997-10-10

Family

ID=20155909

Family Applications (1)

Application Number Title Priority Date Filing Date
RU94017618A RU2092392C1 (en) 1994-05-17 1994-05-17 Method of conversion of rotary-wing aircraft into aeroplane configuration and combined vertical take-off and landing rotary-wing aircraft for realization of this method

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RU (1) RU2092392C1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2810886C1 (en) * 2023-06-13 2023-12-29 Федеральное государственное бюджетное образовательное учреждение высшего образования "Воронежский государственный технический университет" Unmanned aerial vehicle

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2230688C1 (en) * 2003-08-08 2004-06-20 Демин Александр Павлович Multi-purpose heavier-than-air flying vehicle
FR2916418B1 (en) * 2007-05-22 2009-08-28 Eurocopter France FAST HYBRID HELICOPTER WITH EXTENDABLE HIGH DISTANCE.
FR2916419B1 (en) * 2007-05-22 2010-04-23 Eurocopter France HIGH FREQUENCY FAST HYBRID HELICOPTER WITH OPTIMIZED SUSTENTATION ROTOR.
RU2661277C1 (en) * 2017-03-14 2018-07-13 Дмитрий Сергеевич Дуров Unmanned carrier-based convertible rotorcraft
RU2653953C1 (en) * 2017-06-01 2018-05-15 Дмитрий Сергеевич Дуров Unmanned high-speed helicopter-airplane
RU2658736C1 (en) * 2017-06-13 2018-06-22 Дмитрий Сергеевич Дуров Multirotor high-speed helicopter-aircraft
RU2684160C1 (en) * 2017-11-20 2019-04-04 Дмитрий Сергеевич Дуров Deck-based aircraft unmanned anti-submarine complex (dauac)
RU2706295C2 (en) * 2018-03-12 2019-11-15 Дмитрий Сергеевич Дуров Anti-ship missile system with flying rockets robot-carrier and method for use thereof

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2810886C1 (en) * 2023-06-13 2023-12-29 Федеральное государственное бюджетное образовательное учреждение высшего образования "Воронежский государственный технический университет" Unmanned aerial vehicle

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Publication number Publication date
RU2092392C1 (en) 1997-10-10

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