WO2016022040A1 - Aéromobile - Google Patents

Aéromobile Download PDF

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Publication number
WO2016022040A1
WO2016022040A1 PCT/RU2014/000741 RU2014000741W WO2016022040A1 WO 2016022040 A1 WO2016022040 A1 WO 2016022040A1 RU 2014000741 W RU2014000741 W RU 2014000741W WO 2016022040 A1 WO2016022040 A1 WO 2016022040A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
electric motors
propellers
aircraft according
flight
Prior art date
Application number
PCT/RU2014/000741
Other languages
English (en)
Russian (ru)
Inventor
Дмитрий Александрович АРСЕНТЬЕВ
Original Assignee
Ардн Технолоджи Лимитед
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.)
Filing date
Publication date
Application filed by Ардн Технолоджи Лимитед filed Critical Ардн Технолоджи Лимитед
Publication of WO2016022040A1 publication Critical patent/WO2016022040A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
    • B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
    • B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into 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
    • 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
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/11—Propulsion using internal combustion piston engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors

Definitions

  • the proposed technical solution relates to the field of ultralight aviation, both manned and unmanned.
  • RU 127039 An aeromobile (aerobike) known from the patent for utility model RU 127039 published in 2013 can be chosen as the closest analogue of the proposed technical solution.
  • RU 127039 describes an aircraft of vertical take-off and landing - an aerobike (the name can be used similarly for this aircraft aircraft), including a glider, a power plant with vertical take-off and landing propellers, flight controls.
  • the aerobike is made according to the quadrocopter scheme, the power plant of which includes electric motors of the propeller drive, which are both traction screws and control screws.
  • the disadvantage of this aerobike is the insufficient control quality due to the difficulty of synchronizing the operation of all four engines, combining the functions of mid-flight and steering engines, and the difficulty of taking the aerobike out of emergency conditions in case of a failure of some engines.
  • equipping the traction propellers with steering plates see, for example, ⁇ 672465, publication 1989; RU2135393, publication 1999, aircraft such as Hoverbike) will lead to even more complication of the aircraft control circuit, which may ultimately affect its reliability .
  • the proposed technical solution will eliminate this problem and propose the design of an aircraft for vertical take-off and landing for individual use - an aeromobile, which will be characterized by a comparative simplicity of the control scheme and reliability in operation, primarily due to the conclusion from emergency conditions.
  • an aircraft of vertical take-off and landing an aeromobile including a glider, a power plant with screws for vertical take-off and landing, and flight controls.
  • the proposed aircraft is equipped with control screws flight driven by electric motors and at least two mid-flight propellers.
  • ICEs are used to drive marching propellers, for example, piston ICEs or electric motors dedicated to this function, that is, electric motors that are not flight propellers drive motors.
  • the engines of marching propellers are used.
  • At least one electric energy accumulator for example, a supercapacitor, is used to drive the generators of the mentioned electric motors of the flight control screws.
  • Electric motors can be connected to generators or the battery through a power distributor.
  • Flight control screws can be located on the sides relative to the course axis, for example, in the amount of 2 or 3 on each side, the first marching screw is located on the nose side, the second marching screw is located on the tail side.
  • the aircraft can be equipped with an on-board computer.
  • the aircraft may be a robotic and / or remotely piloted unmanned aerial vehicle or be manned.
  • a manned aircraft may be equipped with a pilot's seat or a pilot's seat and at least one passenger seat. In terms of the aircraft correspond to the dimensions of the car parking space, mainly -2.5 m X -5.5 m.
  • An aircraft is an individual vertical take-off and landing aircraft, that is, a "small" aircraft designed to carry a pilot and one or two passengers.
  • the aircraft includes typical components of an aircraft: a glider, a power plant with vertical take-off and landing propellers, and flight controls.
  • the aircraft is equipped with flight control screws ( ⁇ .. ⁇ ) driven by electric motors and at least two marching screws (P ⁇ P 2 ), driven in movement by piston internal combustion engines (Mi, M 2 ) or powerful electric motors (Mi, M 2 ), which are not flight drive propeller drive motors.
  • flight control ⁇ ..
  • the propulsion propellers (Pi, P 2).
  • Generators of electric motors flight control screws obtained mechanical energy in the normal mode (driven in rotation) of engine propellers (Pi, P 2).
  • the electric motors of the flight control screws receive electrical energy from at least one battery (ace) of electrical energy, which can be used as a supercapacitor. The most effective is to connect the electric motors of the flight control screws (p .n) to the generators or the battery (ace) through a power distributor that provides battery charging and a predetermined mode of power distribution for each of the control engines.
  • Flight control screws can be located on the sides of the course axis, for example, in the amount of two or three on each side (4 + 6 screws per aircraft), the first marching screw (Pi) is located on the nose side, the second marching screw (P 2 ) located on the side of the tail. Routine safety and flight quality is ensured through the use of navigation aids (gyroscope) and rescue equipment (parachute) electrically connected to the on-board computer.
  • the aircraft can be equipped with an on-board computer, which synchronizes the operation of both engines, taking into account the possible features of the operation of the aircraft depending on the climate, season, etc.
  • the aircraft may be a robotic and / or remotely piloted unmanned aerial vehicle or be manned.
  • a manned aircraft may be equipped with a pilot's seat or a pilot's seat and at least one passenger seat.
  • the cars correspond to the dimensions of the car parking space, mainly 2.5 m X 5.5 m (deviations from these dimensions are possible on the order of 0.5 + 1.0 m).
  • Marching engines (Mi, M2) provide the necessary lifting force and stabilization in pitch and roll.
  • Each of the electric motors of the flight control screws ( ⁇ .. ⁇ ), which are small ( ⁇ 25 cm in diameter) fans distributed around the perimeter of the structure, is connected to "their" generator, which transfers electric energy to the power distributor.
  • the power distributor transfers electrical energy directly to electric motors that drive the flight control screws (. ⁇ ), whose operating modes provide center of gravity alignment and stabilization of the aircraft in the air.
  • the distributor transfers part of the electric energy to the battery (ACE), which, depending on the flight mode, can accumulate or give off electric energy.
  • ACE battery

Abstract

La présente invention se rapporte au domaine de l'aviation ultralégère, et permet d'améliorer la qualité de commande d'un aéronef en vol. Cet aéromobile comprend un planeur, une installation motrice avec des hélices de décollage et d'atterrissage vertical, et des moyens de commande de vol. l'aéromobile comprend des hélices de commande de vol avec un actionneur à moteurs électriques et des hélices de manœuvre avec de préférence un actionneur à moteur à combustion interne.
PCT/RU2014/000741 2014-08-05 2014-10-02 Aéromobile WO2016022040A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU2014132187 2014-08-05
RU2014132187 2014-08-05

Publications (1)

Publication Number Publication Date
WO2016022040A1 true WO2016022040A1 (fr) 2016-02-11

Family

ID=55264208

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU2014/000741 WO2016022040A1 (fr) 2014-08-05 2014-10-02 Aéromobile

Country Status (1)

Country Link
WO (1) WO2016022040A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2196703C2 (ru) * 1997-01-04 2003-01-20 Херманн КЮНКЛЕР Летательный аппарат с фюзеляжем, выполненным по существу в виде аэростатического подъемного тела, двигательная установка и способ управления летательным аппаратом
US6745977B1 (en) * 2003-08-21 2004-06-08 Larry D. Long Flying car
RU98394U1 (ru) * 2010-07-14 2010-10-20 Федеральное государственное учреждение "46 Центральный научно-исследовательский институт Министерства обороны Российской Федерации" Комбинированный беспилотный летательный аппарат
RU2458822C1 (ru) * 2011-05-18 2012-08-20 Пётр Иванович Дуров Аппарат вертикального взлета и посадки
US20130311008A1 (en) * 2011-07-19 2013-11-21 Zee.Aero Inc. Personal Aircraft
RU142287U1 (ru) * 2014-03-05 2014-06-27 Михаил Юрьевич Артамонов Система стабилизации конвертоплана

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2196703C2 (ru) * 1997-01-04 2003-01-20 Херманн КЮНКЛЕР Летательный аппарат с фюзеляжем, выполненным по существу в виде аэростатического подъемного тела, двигательная установка и способ управления летательным аппаратом
US6745977B1 (en) * 2003-08-21 2004-06-08 Larry D. Long Flying car
RU98394U1 (ru) * 2010-07-14 2010-10-20 Федеральное государственное учреждение "46 Центральный научно-исследовательский институт Министерства обороны Российской Федерации" Комбинированный беспилотный летательный аппарат
RU2458822C1 (ru) * 2011-05-18 2012-08-20 Пётр Иванович Дуров Аппарат вертикального взлета и посадки
US20130311008A1 (en) * 2011-07-19 2013-11-21 Zee.Aero Inc. Personal Aircraft
RU142287U1 (ru) * 2014-03-05 2014-06-27 Михаил Юрьевич Артамонов Система стабилизации конвертоплана

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