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WO2015115913A1 - Avion polyvalent - Google Patents

Avion polyvalent Download PDF

Info

Publication number
WO2015115913A1
WO2015115913A1 PCT/NZ2015/000007 NZ2015000007W WO2015115913A1 WO 2015115913 A1 WO2015115913 A1 WO 2015115913A1 NZ 2015000007 W NZ2015000007 W NZ 2015000007W WO 2015115913 A1 WO2015115913 A1 WO 2015115913A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
wing panel
central wing
fuselage
engine
Prior art date
Application number
PCT/NZ2015/000007
Other languages
English (en)
Inventor
Graham Phillip TULLY
Paul Robert HARTLEY
Alexander James HEWSON
Original Assignee
Global Aerial Platforms Limited
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 Global Aerial Platforms Limited filed Critical Global Aerial Platforms Limited
Publication of WO2015115913A1 publication Critical patent/WO2015115913A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/32—Wings specially adapted for mounting power plant
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/04—Aircraft not otherwise provided for having multiple fuselages or tail booms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/40—Modular UAVs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/70—Constructional aspects of the UAV body
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • 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
    • B64U50/13—Propulsion using external fans or propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2211/00—Modular constructions of airplanes or helicopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/60—UAVs specially adapted for particular uses or applications for transporting passengers; for transporting goods other than weapons

Definitions

  • the present invention relates to an aircraft and a manner of constructing an aircraft. More particularly it relates to an unmanned aerial system (UAS) and a manner of constructing same, although this should not been seen as limiting.
  • UAS unmanned aerial system
  • Aircraft generally are designed to carry out a specific task or function, whether it is to carry passengers, freight, weapons, surveillance, search and rescue, mapping, top dressing, remote sensing, long haul or short haul, speed and so on. In each case the demands on the aircraft design may be very different and these can dictate the design limitations for the aircraft. As a result specialist aircraft are constructed for specialist purposes.
  • UASs unmanned aerial systems
  • UASs can be used for a variety of purposes, many of which are similar to those of piloted aircraft but which, for whatever reason, are preferably flown without a pilot in the UAS. In some instances this couid be a function of size; some UASs are configured as miniature helicopters or aerial platforms, which are typically flown by remote control by a person in the vicinity of the UASs flight.
  • Such vehicles are often fitted with a camera or other type of remote sensing device, generally to provide quick and cost effective low level imagery over a relatively large area.
  • Such vehicles can also be used to good effect to provide surveillance of places which, for one reason or other, are difficult to access, especially by piloted aircraft.
  • UASs Due to their relatively light weight and flying capability large scale UASs can be capable of sustained flight over relatively large areas. This capability may be an advantage for tasks such as surveillance, search and rescue, border patrol, mapping and remote sensing, among others.
  • the configuration of the UAS can vary depending on what function or task it is designed to perform, leading to specialisation. This can mean that different aircraft need to be constructed or bought to address the different specialist needs. This can be costly, both in capital costs of purchasing the aircraft, but also in providing storage and storing the large scale UASs in hangers etc. when not flying.
  • a central wing panel for an aircraft having a first fuselage and a second fuselage, the central wing panel having a front, a rear and two sides, and an engine mounted on the front and/or the rear of the central wing panel, wherein the central wing panel is configured to releasably attach to both the first fuselage and the second fuselage.
  • the engine is an internal combustion engine, while in other embodiments the engine is a jet turbine engine.
  • the central wing panel includes a nacelle having a compartment.
  • the compartment is situated in the front or rear of the central wing panel and the engine is mounted on the rear or front respectively of the central wing panel.
  • Reference to a nacelle throughout this specification should be understood to mean a streamlined enclosure on an aircraft.
  • a nacelle is commonly used to enclose an engine, to store equipment or cargo etc., but may also be used to mount instruments such as a camera, remote sensing equipment, radar etc. and/or other equipment such as may be determined by the nature of the flight (e.g. search and rescue, surveillance, aerial mapping and so on).
  • the nacelle includes a compartment for storing equipment including one or more items from the group including: a camera; a remote sensing device; a radar; a GPS receiver; FTIR; a computer; a radio receiver, medical supplies, and a survival kit.
  • An advantage of using a nacelle in the central wing panel is that it may allow significantly more equipment to be carried on the aircraft (i.e. over and above what is carried in the two fuselages).
  • the nacelle may include a self-contained compartment which is releasably attached to the nacelle/central wing panel. Such an arrangement may be useful in search and rescue, for example, where the nacelle and enclosed equipment may be released from the central wing panel and dropped to the ground below.
  • the engine is mounted at the front of the central wing panel and the nacelle including the compartment is located at the rear of the central wing panel. In another embodiment the engine is mounted to the rear of the central wing panel and the nacelle including the compartment is mounted to the front of the central wing panel.
  • the central wing panel includes an engine mounted to the front of the central wing panel and another engine mounted at the rear of the central wing panel.
  • an aircraft including: two fuselages each fuselage attached to a wing that extends in a direction away from the other fuselage, each fuselage including a wing root box or wing root bed; a central wing panel having a front, a rear and two sides and including an engine mounted on the front and/or the rear of the central wing panel, wherein the wing root box or wing root bed in each fuselage is configured to releasably accept a spar joining one of the sides of the central wing panel to the adjacent fuselage and the attached wing.
  • a wing root box may be a container which is configured to accept a spar, usually from a wing, wherein the spar is locked into the wing root box.
  • a wing root box may be used to locate and fix a wing to the fuselage in situations where the wings are located against a side of the fuselage.
  • a wing root bed may be a surface of the fuselage onto which the wing and central wing panel may be fixed, the wing root bed being configured to accept a spar joining the wing to the central wing panel.
  • a wing root bed may be used in situations where the wings are attached to the upper (or lower) surfaces of the fuselages.
  • the wing root box is configured to accept an end of a spar from the adjacent wing and an end of a spar from the central wing panel.
  • the spar ends are preferably in the form of truncated triangular blocks. When inserted fully into the wing root box the two ends, which have complementary shapes, form a rectangular block which fills the wing root box.
  • a locking pin is inserted through an aperture in the side of each spar, the apertures being aligned when the spars are properly located in the wing root box.
  • the two spars are configured to fill the space in the wing root box, thus locking the fuselage, wing and central wing panel securely together (when pinned).
  • an aircraft including: a first fuselage and a second fuselage; and at least one central wing panel having a front, a rear and two sides, and including an engine mounted on the front and/or the rear of the central wing panel, wherein the central wing panel is configured to releasably attach to both the first fuselage and the second fuselage.
  • each fuselage is attached to a separate wing that extends in a direction away from the other fuselage, each fuselage including a wing root box or wing root bed, wherein the wing root box or wing root bed in each fuselage is configured to releasably accept a spar joining one of the sides of the central wing panel to the adjacent fuselage and the attached wing.
  • the aircraft includes at least two different, interchangeable, central wing panels.
  • An aircraft according to the present invention may take a number of different configurations, each designed for a specific task or function, by inserting an appropriate central wing panel into the wing root box or wing root bed.
  • This modular form of construction allows a single aerial platform, i.e. the wings, two fuselages having a wing root box or wing root bed, and a tail plane, to be adapted to different payloads and different propulsion devices, by inserting each side of an appropriately configured central wing panel between the two fuselages and joining it to the adjacent fuselage and wing on each side using a wing root box in, or wing root bed on, each fuselage.
  • an advantage of this is that the capital cost and storage costs and requirements for a single aerial platform and a plurality of central wing panels may be significantly less than the capital costs and storage costs for a plurality of specialist aircraft.
  • the aircraft is an unmanned aerial system (UAS).
  • the central wing panel is connected to a frame of the aircraft by one or more mounting bolts and/or camber pins.
  • the mounting bolts and/or camber pins are connected to a spar of the aircraft.
  • the central wing panel includes a nacelle having a compartment.
  • the central wing panel includes a nacelle including a compartment on one side of the central wing panel and an engine mounted on the other side of the central wing panel.
  • the central wing panel is locked in the wing root box or wing root bed such that the engine is at the front of the central wing panel. In this configuration the engine is in a "pull" mode.
  • references to front, rear, top, bottom and side of an aircraft or central wing panel throughout this specification should be understood to refer to the usual meanings of these terms when applied to an aircraft, or an aircraft fitted with a central wing panel, when sitting on the ground (or in normal flight).
  • the central wing panel is locked in the wing root box or wing root bed such that the engine is at the rear of the central wing panel. In this configuration the engine is in a "push" mode.
  • the central wing panel includes two engines mounted in a push-pull arrangement.
  • the engine mounted at the front of the central wing panel when attached to the aircraft is configured to pull the aircraft forward, and the engine mounted at the rear is configured to push the aircraft forward.
  • the engine is a turbo-prop engine.
  • the engine is a jet turbine engine.
  • the step of releasably attaching each side of the central wing panel to the adjacent wing includes locating an end of a spar from the side of the central wing panel into a wing root box in, or wing root bed on, the fuselage.
  • Figure 1 shows a schematic plan view of a central wing panel for an aircraft according to one embodiment of the present invention
  • Figure 2 shows a schematic plan view of part of an aircraft according to one embodiment of the present invention
  • Figure 3 shows a schematic plan view of part of an aircraft according to the embodiments shown in Fig.s 1 and 2;
  • Figure 4 shows a schematic plan view of a central wing panel for an aircraft according to another embodiment of the present invention.
  • Figure 5 shows a schematic plan view of a central wing panel for an aircraft according to yet another embodiment of the present invention
  • Figure 6 shows a schematic plan view of a connection according to one embodiment of the present invention.
  • a central wing panel is generally indicated by arrow 1 in Fig.1.
  • the central wing panel is configured for use with an aircraft, in the form of an unmanned aerial system (UAS) having two fuselages, as generally indicated by arrow 2 in Fig. 2.
  • UAS unmanned aerial system
  • the central wing panel 1 has a front 3, a rear 4, and two sides 5 and 6.
  • Each of the sides 5 and 6 is configured to engage with a spar (not shown) in a fuselage of the aircraft 2.
  • the front end 3 of the central wing panel is in the form of a nacelle 8 inside of which is a compartment (not shown) configured to carry equipment and/or additional fuel.
  • the central wing panel 1 is configured to fit into a space between the two fuselages 12 and 13 as generally indicated by arrow 9 in Fig. 2 and the imaginary dashed lines 10 and 11.
  • the first fuselage 12 is connected to a wing 14 (only part shown in Fig. 2) and the second fuselage 13 is connected to a wing 15 (only part shown in Fig. 2).
  • the wing span of the UAS is 8 m.
  • the UAS includes an elevated tail 16 connecting the two fuselages.
  • Fig. 3 shows a plan view of an aircraft, generally indicated by arrow 17, in which the central wing panel 1 has been located within a wing root box (27 in Fig.6) and releasably attached to each of the two fuselages 12, 13.
  • a central wing panel according to another embodiment of the present invention is generally indicated by arrow 18 in Fig. 4.
  • the central wing panel has an internal combustion engine 19 mounted at the front 20 of the central wing panel, and another internal combustion engine 21 mounted at the rear 22.
  • FIG. 5 Another embodiment of a central wing panel is generally indicated by arrow 23 in Fig. 5.
  • a single internal combustion engine 24 is mounted at the front 25 of the central wing panel.
  • a significant advantage of the aircraft and central wing panels of the present invention is that the combination allows for different configurations of the aircraft to be created by releasing the central wing panel from the aircraft (where fitted), removing the central wing panel from the wing root box or bed, inserting a different central wing panel into the central wing box or bed and releasably connecting each side of the different central wing panel to the fuselages.
  • the UAS includes a wing root box 27 in the fuselage 12.
  • the adjacent wing 14 includes a spar 28, an end of which is in the form of a truncated triangular block 28a.
  • the end of the spar 28a is located within the wing root box 27.
  • the central wing panel 1 includes a spar 29, an end of which is in the form of a truncated triangular block 28a, the shape being complementary to the shape of the end of the wing spar 28a, so that when both spar ends, 28a and 29a, are located within the wing root box 27, they fill the space within the wing root box.
  • a camber pin 30 is inserted through an aperture 31 in the side of each spar end, 28a and 29a, the apertures being aligned when the spars are properly located in the wing root box as shown in Fig. 6.
  • the two spars are configured to fill the space in the wing root box, thus locking the fuselage, wing and central wing panel securely together (when pinned).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un avion polyvalent bifuselage (17) qui comprend un panneau de voilure central (1) qui est attaché de manière libérable à chacun des fuselages (12, 13) et qui est situé entre eux. Le panneau de voilure central comprend une nacelle (8) qui a un compartiment à des fins de stockage de divers équipements et un moteur (7) qui est monté sur l'avant et/ou l'arrière du panneau de voilure central. Lors de l'utilisation, l'avion comprend plusieurs panneaux de voilure centraux interchangeables, configurés tel qu'il est déterminé par la nature de la tâche devant être effectuée par l'avion. De préférence, l'avion est un drone/système aérien sans pilote. Les panneaux de voilure centraux peuvent être configurés de sorte que la nacelle et/ou le compartiment peuvent être largués en cours de vol. Dans certains modes de réalisation, le contenu du compartiment peut être largué en cours de vol.
PCT/NZ2015/000007 2014-01-30 2015-01-29 Avion polyvalent WO2015115913A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NZ61491514 2014-01-30
NZ614915 2014-01-30

Publications (1)

Publication Number Publication Date
WO2015115913A1 true WO2015115913A1 (fr) 2015-08-06

Family

ID=53757391

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/NZ2015/000007 WO2015115913A1 (fr) 2014-01-30 2015-01-29 Avion polyvalent

Country Status (1)

Country Link
WO (1) WO2015115913A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106628201A (zh) * 2016-12-09 2017-05-10 北京奇正数元科技股份有限公司 多动力组合更换适应不同起降方式不同任务载荷的无人机
US20180354617A1 (en) * 2015-06-12 2018-12-13 Sunlight Photonics Inc. Modular aircraft assembly for airborne and ground transport
CN111003210A (zh) * 2019-12-26 2020-04-14 中国航空工业集团公司西安飞机设计研究所 一种可更换中翼无人飞行验证机
CN114555467A (zh) * 2019-08-16 2022-05-27 埃姆普里萨有限公司 具有降低的声音特征的无人飞行器
WO2022263879A1 (fr) 2021-06-15 2022-12-22 Sia "Fixar-Aero" Véhicule aérien sans pilote à rotor à angle fixe hybride ayant des capacités de décollage et d'atterrissage verticaux
KR20230143529A (ko) * 2022-04-05 2023-10-12 연세대학교 산학협력단 날개형상 단면을 갖는 다층구조 비행체
CN117799834A (zh) * 2024-01-24 2024-04-02 上海奥科赛通用航空有限公司 一种四动力舱复合功能舱的固定翼飞机
EP4371892A1 (fr) * 2022-11-18 2024-05-22 Thales Aéronef sans équipage comprenant deux radars

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2650049A (en) * 1949-06-20 1953-08-25 Harlan D Fowler Transport airplane construction
RU2151716C1 (ru) * 1996-07-24 2000-06-27 Товарищество с ограниченной ответственностью "КОПРОКОН" Самолет
DE10151759A1 (de) * 2001-10-17 2002-07-11 Holger Lorenz Flugzeug
FR2967971A1 (fr) * 2010-11-26 2012-06-01 Centre Nat Etd Spatiales Vehicule aerien pour lancement aeroporte d'une charge

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2650049A (en) * 1949-06-20 1953-08-25 Harlan D Fowler Transport airplane construction
RU2151716C1 (ru) * 1996-07-24 2000-06-27 Товарищество с ограниченной ответственностью "КОПРОКОН" Самолет
DE10151759A1 (de) * 2001-10-17 2002-07-11 Holger Lorenz Flugzeug
FR2967971A1 (fr) * 2010-11-26 2012-06-01 Centre Nat Etd Spatiales Vehicule aerien pour lancement aeroporte d'une charge

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11034443B2 (en) * 2015-06-12 2021-06-15 Sunlight Aerospace Inc. Modular aircraft assembly for airborne and ground transport
US20180354617A1 (en) * 2015-06-12 2018-12-13 Sunlight Photonics Inc. Modular aircraft assembly for airborne and ground transport
CN106628201B (zh) * 2016-12-09 2023-08-08 北京奇正数元科技股份有限公司 多动力组合更换适应不同起降方式不同任务载荷的无人机
CN106628201A (zh) * 2016-12-09 2017-05-10 北京奇正数元科技股份有限公司 多动力组合更换适应不同起降方式不同任务载荷的无人机
CN114555467A (zh) * 2019-08-16 2022-05-27 埃姆普里萨有限公司 具有降低的声音特征的无人飞行器
EP4013681A4 (fr) * 2019-08-16 2023-08-30 Embraer, S.A. Aéronef sans pilote à signatures acoustiques réduites
CN114555467B (zh) * 2019-08-16 2024-05-03 埃姆普里萨有限公司 具有降低的声音特征的无人飞行器
CN111003210A (zh) * 2019-12-26 2020-04-14 中国航空工业集团公司西安飞机设计研究所 一种可更换中翼无人飞行验证机
WO2022263879A1 (fr) 2021-06-15 2022-12-22 Sia "Fixar-Aero" Véhicule aérien sans pilote à rotor à angle fixe hybride ayant des capacités de décollage et d'atterrissage verticaux
KR20230143529A (ko) * 2022-04-05 2023-10-12 연세대학교 산학협력단 날개형상 단면을 갖는 다층구조 비행체
KR102693021B1 (ko) 2022-04-05 2024-08-06 연세대학교 산학협력단 날개형상 단면을 갖는 다층구조 비행체
EP4371892A1 (fr) * 2022-11-18 2024-05-22 Thales Aéronef sans équipage comprenant deux radars
FR3142176A1 (fr) * 2022-11-18 2024-05-24 Thales Aéronef sans équipage comprenant deux radars
CN117799834A (zh) * 2024-01-24 2024-04-02 上海奥科赛通用航空有限公司 一种四动力舱复合功能舱的固定翼飞机

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