-
公开(公告)号：EP2734440B1
公开(公告)日：2015-06-10
申请号：EP12750421.5
申请日：2012-07-19
Applicant: Dirisolar
Inventor： TIXIER, Philippe
CPC classification number: B64B1/005 , B64B1/00 , B64B1/20 , B64B1/66 , B64B2201/00
-
公开(公告)号：EP2851251A1
公开(公告)日：2015-03-25
申请号：EP14185541.1
申请日：2014-09-19
Applicant: Hybrid Air Vehicles Limited
Inventor： Durham, Michael , Macey, Paul
CPC classification number: B64C25/001 , B60V1/043 , B60V1/06 , B60V1/16 , B60V3/08 , B64B2201/00
Abstract: An air cushioned landing system for an air vehicle comprises an inflatable and deflatable skirt (113) in the form of a tube having inner (101) and outer (100) walls. The inner wall defines a central plenum (116) within the skirt, the skirt including gas pockets (130) arranged to stiffen one or more regions of at least one of the inner (101) and outer (100) walls during deflation of the skirt.
Abstract translation: 用于空中交通工具的气垫着陆系统包括具有内（101）和外（100）壁的管形式的可充气和可放气的裙部（113）。 所述内壁在所述裙部内限定中央增压室（116），所述裙部包括气囊（130），所述气囊布置成在所述裙部（112）的通气期间加强所述内部（101）和外部（100）壁中的至少一个的一个或多个区域 。
-
公开(公告)号：EP2076429B1
公开(公告)日：2013-05-15
申请号：EP07873810.1
申请日：2007-10-15
Applicant: LTA Corporation
Inventor： BALASKOVIC, Pierre
CPC classification number: B64B1/06 , B64B1/10 , B64B1/12 , B64B1/30 , B64B1/34 , B64B2201/00 , B64C2201/00
-
54.发明公开Retracting Air Cushioned Landing System for Air Vehicles 有权Einfahrbares Landesystem mit LuftkissenfürLuftfahrzeuge
公开(公告)号：EP2143610A2
公开(公告)日：2010-01-13
申请号：EP09164336.1
申请日：2009-07-01
Applicant: Lockheed Martin Corporation
Inventor： Morehead, John , Greiner, Douglas , Pasman, Renee , Boyd, Robert
IPC: B60V3/08
CPC classification number: B60V3/08 , B64B1/06 , B64B1/32 , B64B2201/00
Abstract: A hybrid air vehicle (100) is disclosed in which a cover is provided for a plurality of air cushioned landing pads (206) to reduce drag when airborne. The pad is inflatable to provide an air cushioned during touchdown and deflatable during flight of the air vehicle. The cover can include a first cover portion and a second cover portion. A first cover roller of the first cover portion and a matching second cover roller of the second cover portion abut to cover the corresponding pad. The first cover roller and the second cover roller, which are separate and free from a physical linkage there between, are separable in an eyelid fashion to expose the corresponding pad. A separation gap between the first cover roller and the second cover roller is increased or decreased by roller straps to cover or expose the corresponding pad.
Abstract translation: 公开了一种混合动力飞行器（100），其中为多个气垫着陆垫（206）设置盖，以减少空降时的阻力。 该垫是可充气的，以提供在着陆期间缓冲的气垫，并在空中飞行器的飞行期间可放气。 盖可以包括第一盖部分和第二盖部分。 第一盖部分的第一覆盖辊和第二盖部分的匹配的第二盖辊邻接以覆盖相应的垫。 第一覆盖辊和第二覆盖辊分离并且不存在于其间的物理连接，可以以眼睑的方式分离以暴露相应的垫。 第一覆盖辊和第二覆盖辊之间的分离间隙由辊带增加或减小以覆盖或暴露相应的垫。
-
公开(公告)号：EP1899220A1
公开(公告)日：2008-03-19
申请号：EP05769453.1
申请日：2005-07-07
Applicant: Nimbus S.R.L.
Inventor： CAPUANI, Alfredo
IPC: B64B1/02 , B64C31/032
CPC classification number: B64C31/032 , B64B1/02 , B64B2201/00
Abstract: The aircraft (10) comprises an elongated framework (26) provided with propelling means and direction-control planes. The framework is coupled to a pneumatic chamber (16) suited to be filled with lighter-than-air gas and comprising two tubular branches (12, 14) joined to form a V-shaped profile, with an aerodinamic-lift surface (22, 24) extending therebetween.
-
Patent Agency Ranking
公开(公告)号：EP1175332A4
公开(公告)日：2003-10-22
申请号：EP00953628
申请日：2000-04-11
Applicant: PROVITOLA ANTHONY I
Inventor： PROVITOLA ANTHONY I
CPC classification number: B64G1/401 , B64B1/08 , B64B1/58 , B64B2201/00 , B64C39/001 , B64G1/002 , B64G1/005 , B64G1/402
Abstract: An airship/spacecraft, which, in a preferred embodiment, uses its lifting gas (64) as fuel for thrusters, which may be of the turbo-type or rocket type, or both, to achieve transition to space flight. The airship aspect has gas retaining structures (61) that can withstand internal and external pressure and can change in volume and shape. The gas retaining structures (61) may be compartmentalized with a folded diaphragm membrane (63) and also configured as pressure vessels. The spacecraft aspect provides control, power, services, and space for missions of the airship/spacecraft. The best mode includes a turbo-rocket thruster in which the turbine compressor is used to intake and compress a gaseous fuel for combustion with a stored oxidizer injected into the compressed gaseous fuel stream. The compressor stage (6) is driven by the turbine stage (7), which is driven by burning gaseous fuel passing across the turbine blades (13). The burned gases are then expanded through an exhaust nozzle and thereby ejected to produce reaction thrust.
-
公开(公告)号：EP1211173A3
公开(公告)日：2002-11-27
申请号：EP02075630.0
申请日：1996-10-24
Applicant: Bothe, Hans-Jurgen
Inventor： Bothe, Hans-Jurgen
CPC classification number: B64C39/00 , B64B1/06 , B64B1/08 , B64B1/18 , B64B1/32 , B64B1/34 , B64B2201/00 , B64C27/52 , B64C29/00 , B64C29/0033 , B64C39/10 , B64C2001/0063 , B64C2001/0072 , B64C2001/0081 , Y02T50/12 , Y02T50/43
Abstract: A hybrid aircraft having VTOL R-VTOL and S-STOL capabilities having a lifting body hull (1) and four wing sections (20) arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor (21) assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers from the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system. The frame is formed of a plurality of curved elongate segments arranged in series orthogonal to the long axis of the hull and connected by means of torsion members. A turbo-electric drive system can be used to drive the aircraft. An advanced hybrid aircraft is also described having about 8 to 12 high speed fans in place of the propeller-rotors.
-
公开(公告)号：EP1211172A3
公开(公告)日：2002-11-27
申请号：EP02075573.2
申请日：1996-10-24
Applicant: Bothe, Hans-Jurgen
Inventor： Bothe, Hans-Jurgen
CPC classification number: B64C39/00 , B64B1/06 , B64B1/08 , B64B1/18 , B64B1/32 , B64B1/34 , B64B2201/00 , B64C27/52 , B64C29/00 , B64C29/0033 , B64C39/10 , B64C2001/0063 , B64C2001/0072 , B64C2001/0081 , Y02T50/12 , Y02T50/43
Abstract: A hybrid aircraft having VTOL R-VTOL and S-STOL capabilities having a lifting body hull (1) and four wing sections (20) arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor (21) assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers from the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system. The frame is formed of a plurality of curved elongate segments arranged in series orthogonal to the long axis of the hull and connected by means of torsion members. A turbo-electric drive system can be used to drive the aircraft. An advanced hybrid aircraft is also described having about 8 to 12 high speed fans in place of the propeller-rotors.
-
公开(公告)号：EP1211173A2
公开(公告)日：2002-06-05
申请号：EP02075630.0
申请日：1996-10-24
Applicant: Bothe, Hans-Jurgen
Inventor： Bothe, Hans-Jurgen
CPC classification number: B64C39/00 , B64B1/06 , B64B1/08 , B64B1/18 , B64B1/32 , B64B1/34 , B64B2201/00 , B64C27/52 , B64C29/00 , B64C29/0033 , B64C39/10 , B64C2001/0063 , B64C2001/0072 , B64C2001/0081 , Y02T50/12 , Y02T50/43
Abstract: A hybrid aircraft having VTOL R-VTOL and S-STOL capabilities having a lifting body hull (1) and four wing sections (20) arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor (21) assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers from the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system. The frame is formed of a plurality of curved elongate segments arranged in series orthogonal to the long axis of the hull and connected by means of torsion members. A turbo-electric drive system can be used to drive the aircraft. An advanced hybrid aircraft is also described having about 8 to 12 high speed fans in place of the propeller-rotors.
-
公开(公告)号：EP1211172A2
公开(公告)日：2002-06-05
申请号：EP02075573.2
申请日：1996-10-24
Applicant: Bothe, Hans-Jurgen
Inventor： Bothe, Hans-Jurgen
CPC classification number: B64C39/00 , B64B1/06 , B64B1/08 , B64B1/18 , B64B1/32 , B64B1/34 , B64B2201/00 , B64C27/52 , B64C29/00 , B64C29/0033 , B64C39/10 , B64C2001/0063 , B64C2001/0072 , B64C2001/0081 , Y02T50/12 , Y02T50/43
Abstract: A hybrid aircraft having VTOL R-VTOL and S-STOL capabilities having a lifting body hull (1) and four wing sections (20) arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor (21) assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers from the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system. The frame is formed of a plurality of curved elongate segments arranged in series orthogonal to the long axis of the hull and connected by means of torsion members. A turbo-electric drive system can be used to drive the aircraft. An advanced hybrid aircraft is also described having about 8 to 12 high speed fans in place of the propeller-rotors.
-
-
-
-
-
-
-
-
-
Search Results
388
records
(took 0.032 seconds)
