WO2021010915A1 - Véhicule aérien sans pilote multifonction doté d'un système d'hélices coaxiales contrarotatives orientables et repliables - Google Patents

Véhicule aérien sans pilote multifonction doté d'un système d'hélices coaxiales contrarotatives orientables et repliables Download PDF

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Publication number
WO2021010915A1
WO2021010915A1 PCT/TR2020/050436 TR2020050436W WO2021010915A1 WO 2021010915 A1 WO2021010915 A1 WO 2021010915A1 TR 2020050436 W TR2020050436 W TR 2020050436W WO 2021010915 A1 WO2021010915 A1 WO 2021010915A1
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WO
WIPO (PCT)
Prior art keywords
wing
aerial vehicle
landing
propulsion
propeller
Prior art date
Application number
PCT/TR2020/050436
Other languages
English (en)
Inventor
Ender ÖZYETİŞ
Servet Güçlü ÖZCAN
Dünya Rauf Levent Güner
Original Assignee
Aselsan Elektroni̇k Sanayi̇ Ve Ti̇caret Anoni̇m Şi̇rketi̇
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Application filed by Aselsan Elektroni̇k Sanayi̇ Ve Ti̇caret Anoni̇m Şi̇rketi̇ filed Critical Aselsan Elektroni̇k Sanayi̇ Ve Ti̇caret Anoni̇m Şi̇rketi̇
Publication of WO2021010915A1 publication Critical patent/WO2021010915A1/fr

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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
    • B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
    • 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
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/293—Foldable or collapsible rotors or rotor supports
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8236—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft including pusher propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/30—Supply or distribution of electrical power
    • B64U50/31—Supply or distribution of electrical power generated by photovoltaics

Definitions

  • This invention is related to a VTOL/VSTOL/CTOL capable dual hybrid (electric/internal combustion powered and fixed wing cruise vertical takeoff/landing) unmanned aerial vehicle with conventional internal combustion or electric powered silent flight capability, thanks to tiltable 4x2 coaxial counter rotating, folding propeller systems which are mounted on two removable ,pods.
  • unmanned aerial vehicles used for vertical takeoff and landing.
  • These may be a“helicopter type” having one or more main rotors and some form of tail rotors,“tilt rotor type” which can change the angle of engines or propellers,“tilt wing type” which changes the direction of wings together with the wing mounted engines/propellers, tail sitter type which take off vertically along longitidunal axis, whose thrust is provided by longitudinal thrust group after takeoff.
  • Hybrid systems have been developed in recent years with the addition of electric motors for vertical take - off at least at 3 or 4 stations to fixed - wing air vehicles in unmanned aircraft.
  • Tilt - rotor type systems generally have large motors that can be tilted or propeller groups that can be tilted by means of the shaft running along the wing connected to the single motor located in the center. Tilt - rotor systems do not have an effective reverse thrust capability for very short runway landings. Due to the extra weight of the propulsion system installed in the wing in the tilt - rotor systems, and its effects on the structure of the wing and on the balance and control characteristics of the aircraft, the wing span cannot be kept wide enough.. This increases aerodynamic losses and shortens the flight time. Tilt - wing type systems have mechanisms that can be tilted together with the wing. Wind resistance at the takeoff is relatively low. Similar to tilt - rotor type systems, They have a relatively short flight time because of the aerodynamic losses due to their short wingspan.
  • Tail - sitter type systems can only do vertical takeoff and landing they have problems in terms of control and safety.
  • longitudinal thrust motors and vertical thrust motors are different from each other.
  • Vertical thrust motors with at least 3 or 4 units become idle after take-off, propeller groups that remain in a position perpendicular to the direction of flight increase the drag force.
  • 3 or 4 vertical take - off propulsion motors / propellers if one of the vertical propulsion units fails, the mission cannot be completed so that the sortie ends with an emergency landing or loss of aircraft. Since vertical takeoff propulsion systems with electric motors are not generally used in horizontal flight, systems with internal combustion main propulsion engines are not capable of silent operation. If an electrical system is used in addition to the main propulsion engine, the range of the system and endurance decreases.
  • the application numbered US20160288903A1 in the prior art refers to a system that has an aerodynamically driven propulsion steering system, capable of short - distance landing take - off, vertical landing take - off and / or conventional landing take - off.
  • the thrust system of the application can switch between different flight modes. Thanks to its design, the system has features such as high lift capacity, low drag, low weight, good stability at low and high speeds, and low noise.
  • Another application CN106586001 A in prior art relates to the technical field of unmanned aerial vehicles and particularly relates to an unmanned aerial vehicle with a tailed flying wing configuration, which has a plurality of working modes such as vertical take - off and landing / short - distance take - off and landing / conventional take - off and landing / low - speed forward flight / high - speed forward flight and the like.
  • the said unmanned aerial vehicle has propulsion systems consisting of two 360 - degrees rotating fans, one fixed fan which is powered by an internal combustion engine, and one fixed fan, which is positioned on the back of the aircraft, that is basically built into the air vehicle body designed as a flying wing.
  • an unmanned aerial vehicle with internal combustion or electric propulsion capable of silent flight, capable of prolonged flight, with tiltable coaxial counter - rotation propeller, with dual hybrid structure, (electric / internal combustion and fixed - wing conventional flight / vertical takeoff / landing) capable of vertical takeoff/landing (VTOL), very short runway takeoff/landing (VSTOL), conventional takeoff/landing (CTOL) and which can continue its duty in case of failure of any propulsion unit has not been revealed.
  • the invention relates to an unmanned aerial vehicle with internal combustion or electric propulsion, silent flight capability, removable double pod mounted, with tilting 4x2 coaxial counterrotating, folding propeller systems, with dual hybrid (electric / internal combustion and fixed - wing flight / landing) capable of vertical take-off/landing (VTOL), very short runway take-off/landing (VSTOL), conventional take-off/landing (CTOL).
  • dual hybrid electric / internal combustion and fixed - wing flight / landing
  • VTOL vertical take-off/landing
  • VSTOL very short runway take-off/landing
  • CTOL conventional take-off/landing
  • the coaxial - counter - rotating propeller groups can be held in a horizontal or vertical position by a tilting mechanism, but also at a desired angle.
  • the generator of the internal combustion motor and solar panels can charge the batteries of the electric motors. In this way, in certain parts of the flight, the internal combustion engine can be stopped and electric powered flight portion can be increased. • In case of an internal combustion engine failure, it is possible to return to base by performing an electric powered flight for up to an hour with the front electric motors. This feature is not available in other hybrid systems that cannot tilt their engines.
  • the system can perform VSTO - Very Short Take - off and very short runway landings in high altitude and hot weather conditions where vertical takeoff and landing can be difficult.
  • the front propeller groups are operated in horizontal position to support take off and climb.
  • the front electric motors are closed while the rear electric motor group produces effective reverse thrust, reducing the landing distance.
  • the drag force encountered in horizontal flight is less than the other hybrid (fixed - wing aircraft capable of vertical takeoff / landing) systems.
  • the folding propeller groups were made to be opened by electric motor rotation and closed by airflow. Thus, they provide less drag force than other hybrid systems when they are placed in a horizontal streamlined position when not in use, such as in modes where the aircraft is cruising with internal combustion engine power only.
  • Each vertical / horizontal tilting station in the system has coaxial propeller groups with counter - rotation. In this way, the system can continue to operate even if one of the electric motors or propellers is disabled or failed. If two propellers / motors are disabled, the system can continue to operate in certain combinations and can execute emergency vertical landings in each failure combination. Even if all of the electric motors (8 units) are disabled, the system can perform conventional landing on a runway.
  • the propeller groups with coaxial counter - rotation provide more thrust per unit station than systems with 4 vertical propulsion groups.
  • the counter - rotating propeller system is more compact than the propulsion systems that have the same number of single structures, without coaxial counter - rotation motors and propellers. This is advantageous by producing less aerodynamic drag force, especially when the vertical thrust units are not in use such as in cruise phase.
  • the invention is an aerial vehicle comprising at least two semi - elliptical wings extending on either side of a main body, a tail extending between the wings, a pusher type fuselage propeller positioned at the rear of the main body, a propulsion element located in the main body and powering the fuselage propeller and able to perform very short runway takeoff/landing, conventional takeoff/landing, and vertical takeoff/landing.
  • Air vehicle is further comprising, • wing compartments that are mounted on the wings,
  • front propulsion groups located in the front part of the wing compartments, which provide forward or upward thrust depending on their positioning
  • rear propulsion groups located in the rear part of the wing compartments, which provide backward or upward thrust depending on their positioning
  • tilting mechanisms located at the tips of the wing compartment that move the front and rear propulsion groups between the vertical and horizontal axis
  • Figure 1 is a front perspective view of the aerial vehicle of the invention.
  • Figure 2 is a detailed view of the wing compartment mounted on the wings of the aerial vehicle of the invention.
  • Figure 3 is a detailed view of the front propulsion group in the wing compartment.
  • Figure 4 shows the wing compartment with the propulsion groups in the vertical position with the wing propellers open.
  • Figure 5 shows the condition of the front and rear propulsion groups in the case of very short runway take - off and electrically assisted climbing and cruise.
  • Figure 6 shows the condition of the front and rear propulsion groups in the case of very short runway landing.
  • Figure 7 shows the integrated wing - tail configuration and folded wings.
  • Figure 8 shows the solar panels placed on the wing and tail sections of the aerial vehicle.
  • Figure 9 is the view of the aerial vehicle with propulsion groups in horizontal position and wing propellers closed. i.e in the case of conventional take off cruise and landing phases with internal combustion engine only.
  • Figure 10 is the view of the aerial vehicle with propulsion groups positioned for a very short runway landing.
  • Figure 1 1 is the view of the aerial vehicle with propulsion groups positioned for very short runway take - off and electrically assisted climbing and cruise.
  • the invention shown in Figure 1 is a fixed wing hybrid type (fixed wing with VTOL capability), hybrid drive (internal combustion/electric) unmanned aerial vehicle (1 ), which can perform vertical takeoff and landing, very short takeoff and landing, and conventional takeoff and landing, by utilizing electric powered propulsion systems with tiltable coaxial counter rotating propeller systems.
  • this small UAV class aerial vehicle (1 ) there are semi - elliptical wings (3) with a folding structure and a positive dihedral angle. Between the two wings (3) is the tail (4) part integrated into the wings (3).
  • the main fuselage where the wings (3) are fixed (2) there is a propulsion element with a pusher type fuselage propeller (5) and preferably an internal combustion engine payloads (8) such as EO / IR (electro - optical / infrared), ADS - B (automatic dependent surveillance - broadcasting), AIS (automatic identification system), etc. are carried in the main body (2).
  • the main body (2) also has front - controlled inward - retractable landing gear (9), preferably with 3 wheels. At the ends of the wings (3), the winglets (10) are formed.
  • both wings (3) Approximately in the middle section of both wings (3) are two wing compartments (1 1 ), which are given a detail view in Figure 2 and can be mounted on the aerial vehicle (1 ) from the mounting point (17).
  • the mounting point (17) on the wing compartment (1 1 ) allows the wing compartment (1 1 ) to be secured to the bottom of the wing (3).
  • Electric - powered front and rear propulsion groups (12, 13) are available in each of these compartments (1 1 ).
  • Each propulsion group can be positioned vertically and horizontally according to the wing compartment (1 1 ) by means of a tilting mechanism (22). It is also possible to bring the propulsion groups to the desired angle within the specified position range.
  • the front and rear propulsion groups (12, 13) are in a horizontal position while the propellers (18) in the front and rear propulsion groups (12, 13) are stopped, similar to Figure 2 and Figure 9, and the propeller blades (6) produce less drag force against the direction of flight. If additional thrust force is required during the climbing and cruise stages, the front propulsion group (12) continues to operate in a horizontal position as shown in Figure 5 and Figure 1 1. Thus, flight can be carried out in high altitude conditions.
  • the main internal combustion propulsion element is turned off, and the electric motors (16) perform a silent flight for a while with the energy provided by the power supply (14) and the solar panels (7) placed on the tail (4) and the wing (3). If the propulsion element of the internal combustion engine fails and cannot be restarted during flight, the aerial vehicle (1 ) can continue flying using only the electric - powered front propulsion group (12). The aerial vehicle (1 ) can return to the base according to the power supply (14) and if the remaining power supply (14) is sufficient it may perform a vertical landing, but if not, a very short runway landing or conventional landing can be performed.
  • all front and rear propulsion groups (12, 13) are operated with the front - rear order while in horizontal position and brought to the vertical position.
  • the propulsion element can be activated when the aerial vehicle (1 ) is landing on a ship, in other cases it can be turned off or operated at idling.
  • Very short runway take - off can be made with electric support by operating the front propulsion groups (12) in horizontal position. Since the thrust capacity of the vertical propulsion units is much greater than that of the main internal combustion propulsion element in the main body (2) and the propeller (5), the extra thrust provided by the front propulsion groups (12) makes it possible to perform a very short runway take - off.
  • Conventional takeoff, conventional climbing, and conventional flight can be done in the appropriate length tracks by keeping front propulsion groups (12) closed in a horizontal position.
  • the aerial vehicle (1 ) has an avionics battery that drives avionics systems, and preferably 4 power sources (14) that drive electric motors (16) which can back each other up in pairs.
  • the battery and power supplies (14) can be charged with a generator connected to the drive element, as well as solar panels (7) integrated into the wings (3) and tail (4).
  • Power supplies for vertical landing (14) can be recharged in a short time according to generator capacity. In this way, the flight time can be extended by adding electric - powered silent flight phases.
  • the aerial vehicle (1 ) is able to perform vertical take - off, conventional take - off, very short runway take - off, conventional climbing, electric - assisted climbing, conventional cruise, electric - powered cruise, silent cruise, very short runway landing, conventional landing, and vertical landing modes and capabilities.
  • the aircraft (1 ) contains a folding point (19) which is formed on the wing (3) and folds correctly on its own from the tip of the wing (3) in the direction of the main body (2) in order not to take up space, while the wings (3) are kept ready for flight in restricted storage areas such as ships, etc.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Electric Propulsion And Braking For Vehicles (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un véhicule aérien (1), muni d'une voilure fixe (3), d'hélices coaxiales orientables et contrarotatives, de systèmes de propulsion électrique et d'un entraînement hybride (combustion électrique/interne), qui peut effectuer un décollage et un atterrissage verticaux, un décollage et un atterrissage très courts, et un décollage et un atterrissage classiques à l'aide de systèmes de propulsion électrique munis de systèmes d'hélices coaxiales contrarotatives orientables. Différents modes de vol peuvent être réalisés dans différentes situations grâce à des compartiments d'aile (11) dotés de groupes de propulsion électrique avant et arrière (12, 13) qui peuvent être attachés aux ailes (3) et retirés de celles-ci.
PCT/TR2020/050436 2019-07-12 2020-05-20 Véhicule aérien sans pilote multifonction doté d'un système d'hélices coaxiales contrarotatives orientables et repliables WO2021010915A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR2019/10431A TR201910431A2 (tr) 2019-07-12 2019-07-12 Eği̇lebi̇len eş eksenli̇, karşit dönüşlü, katlanir pervaneli̇, çok fonksi̇yonlu bi̇r i̇nsansiz hava araci
TR2019/10431 2019-07-12

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WO2021010915A1 true WO2021010915A1 (fr) 2021-01-21

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PCT/TR2020/050436 WO2021010915A1 (fr) 2019-07-12 2020-05-20 Véhicule aérien sans pilote multifonction doté d'un système d'hélices coaxiales contrarotatives orientables et repliables

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TR (1) TR201910431A2 (fr)
WO (1) WO2021010915A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2022029435A1 (fr) * 2020-08-06 2022-02-10 Vertical Aerospace Group Limited Ensemble de rotor de véhicule volant
CN114476040A (zh) * 2021-04-26 2022-05-13 徐倩倩 一种折叠转桨实现姿态调整的无人机

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20160116736A (ko) * 2015-03-31 2016-10-10 주식회사 샘코 컨버터블 윙 타입 하이브리드 무인 항공기
US9783288B1 (en) * 2016-12-07 2017-10-10 Kitty Hawk Corporation Lift fan position lock mechanism
US20180178899A1 (en) * 2016-12-27 2018-06-28 Korea Advanced Institute Of Science And Technology Aircraft capable of vertical take-off and landing, vertical and horizontal flight and on-air energy generation
US20190009895A1 (en) * 2017-05-08 2019-01-10 Pinnacle Vista, LLC Multi-copter lift body aircraft with tilt rotors
WO2019109622A1 (fr) * 2017-12-06 2019-06-13 Guangdong Kang Yun Technologies Limited Optimisation de la direction de l'hélice dans la conception d'un drone à l'aide d'un réseau de capteurs embarqué

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20160116736A (ko) * 2015-03-31 2016-10-10 주식회사 샘코 컨버터블 윙 타입 하이브리드 무인 항공기
US9783288B1 (en) * 2016-12-07 2017-10-10 Kitty Hawk Corporation Lift fan position lock mechanism
US20180178899A1 (en) * 2016-12-27 2018-06-28 Korea Advanced Institute Of Science And Technology Aircraft capable of vertical take-off and landing, vertical and horizontal flight and on-air energy generation
US20190009895A1 (en) * 2017-05-08 2019-01-10 Pinnacle Vista, LLC Multi-copter lift body aircraft with tilt rotors
WO2019109622A1 (fr) * 2017-12-06 2019-06-13 Guangdong Kang Yun Technologies Limited Optimisation de la direction de l'hélice dans la conception d'un drone à l'aide d'un réseau de capteurs embarqué

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2022029435A1 (fr) * 2020-08-06 2022-02-10 Vertical Aerospace Group Limited Ensemble de rotor de véhicule volant
GB2597786B (en) * 2020-08-06 2024-04-10 Vertical Aerospace Group Ltd Flying vehicle rotor arrangement
CN114476040A (zh) * 2021-04-26 2022-05-13 徐倩倩 一种折叠转桨实现姿态调整的无人机
CN114476040B (zh) * 2021-04-26 2024-05-17 远超航空科技(成都)有限公司 一种折叠转桨实现姿态调整的无人机

Also Published As

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