利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

350 条记录 (耗时 0.015 秒)

    AERONEF A ALIMENTATION EN ENERGIE HYBRIDE
    51.
    发明授权
    AERONEF A ALIMENTATION EN ENERGIE HYBRIDE 有权
    具有混合能源动力飞机

    公开(公告)号：EP2296970B1

    公开(公告)日：2012-02-01

    申请号：EP09766033.6

    申请日：2009-05-14

    申请人： Snecma

    发明人： FOUCAULT, Alain ,  JUCHAULD, Etienne ,  PIERROT, Arnaud ,  ROUSSELIN, Stéphane

    IPC分类号： B64D27/24

    CPC分类号： B64D27/24 ,  B64C2201/042 ,  B64D2027/026 ,  B64D2041/005 ,  B64D2211/00 ,  Y02T50/64 ,  Y02T90/36 ,  Y02T90/44

    摘要： The invention relates to an aircraft powered by hybrid power that comprises: an outer structure (12 to 20); electric equipment (34); internal combustion propulsion means (40); and a means for supplying power to the propulsion means; characterised in that the aircraft further comprises: a plurality of converters for directly converting light energy into electric power (24), arranged on at least a portion of the outer surface of the outer structure; a means (32) for comparing the electric power generated by said converters with the instantaneous consumption of said electric equipment (34); a means (36) for recovering excess electric power if there is any; and a means (38) for supplying said propulsion means (40) with additional power from said excess electric power if there is any.

    AIRSHIP AND METHOD OF OPERATION
    54.
    发明授权
    AIRSHIP AND METHOD OF OPERATION 有权
    飞艇工作程序

    公开(公告)号：EP1519873B1

    公开(公告)日：2007-10-24

    申请号：EP03737791.8

    申请日：2003-06-25

    申请人： 21st Century Airships Inc.

    发明人： COLTING, Hokan

    IPC分类号： B64B1/00

    CPC分类号： B64B1/34 ,  B64B1/02 ,  B64B1/32 ,  B64C21/02 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  Y02T50/166

    摘要： An airship (20) has a generally spherical shape and has an internal envelope (24) for containing a lifting gas such as Helium or Hydrogen. The airship has a propulsion and control system (36, 38) that permits it to be flown to a desired loitering location, and to be maintained in that location for a period of time. In one embodiment the airship may achieve neutral buoyancy when the internal envelope is as little as 7 % full of lifting gas, and may have a service ceiling of about 60,000 ft. The airship has an equipment module (180) that can include either communications equipment, or monitoring equipment, or both. The airship can be remotely controlled from a ground station. The airship has a solar cell array and electric motors (44, 46) of the propulsion and control system are driven by power obtained from the array. The airship also has an auxiliary power unit (52) that can be used to drive the electric motors. The airship can have a pusher propeller that assists in driving the airship and also moves the point of flow separation of the spherical airship further aft. In one embodiment the airship can be refuelled at altitude to permit extended loitering.

    FLUGGERÄT MIT EINER MEHRZAHL VON HUB- UND SCHUBROTOREN
    56.
    发明授权
    FLUGGERÄT MIT EINER MEHRZAHL VON HUB- UND SCHUBROTOREN 有权
    具有中心和推力转子的NUMBER飞行大队

    公开(公告)号：EP1483526B1

    公开(公告)日：2006-10-25

    申请号：EP03711921.1

    申请日：2003-03-05

    申请人： Wobben, Aloys

    发明人： Wobben, Aloys

    IPC分类号： F16L37/44

    CPC分类号： B64C39/024 ,  B64C27/20 ,  B64C29/00 ,  B64C39/022 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/165 ,  B66F19/00

    摘要： The invention relates to an aircraft comprising a number of lifting rotors and propulsion rotors, provided with an electric motor for each rotor and with a power inverter for each motor. The aim of the invention is to provide an aircraft that has a higher load capacity. To this end, connecting bars are provided between the motors. The invention is based on the finding that connecting bars of this type, when they are arranged in the form of a lattice, enable a light yet stabile structure of the aircraft that, correspondingly, can carry heavier loads.

    Drohne
    58.
    发明公开
    Drohne 有权

    公开(公告)号：EP1674819A1

    公开(公告)日：2006-06-28

    申请号：EP05026655.0

    申请日：2005-12-07

    申请人： LFK-Lenkflugkörpersysteme GmbH

    发明人： Gleich, Peter ,  Maier, Franz

    IPC分类号： F42B15/00 ,  B64C39/02 ,  B64C27/26 ,  B64C27/28

    CPC分类号： B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  F42B15/105

    摘要： Es wird ein Kleinflugkörper mit einem Rumpf (Airframe), Mitteln zur Steuerung und einem Antrieb vorgeschlagen, bei dem im Rumpf ein Propeller-Elektroantrieb, eine Energieversorgung, eine TV-Kamera, eine Datenübertragungs- und Lenkelektronik sowie ein Gefechtskopf bzw. ein Wirksystem integriert und am Rumpf klapp-bzw. faltbare Flügel, Ruder und Propeller angeordnet sind.
    Der Kleinflugkörper kann für die Bekämpfung unterschiedlicher Ziele oder für unterschiedliche Missionen mit verschiedenen Wirksystemen bestückt werden.

    摘要翻译： 小飞机（无人机），机身，控制装置和推进电驱动。 机身包括推进电驱动，能量供应，电视摄像机，数据传输和指导电子，综合作战头和操作系统以及机身铰链翼型。

    RING-WING AIRCRAFT
    59.
    发明授权
    RING-WING AIRCRAFT 有权
    RINGFLÜGELFLUGZEUG

    公开(公告)号：EP1289831B1

    公开(公告)日：2003-12-10

    申请号：EP01921639.9

    申请日：2001-04-20

    申请人： BAE SYSTEMS plc

    发明人： WARSOP, Clyde ,  WOODS, Mike ,  HENDERSON, James ,  LOCK, Gary, School of Engineering

    IPC分类号： B64C39/02 ,  B64C39/06

    CPC分类号： B64C39/062 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/162

    摘要： This invention relates to ring-wing aircraft and is suited particularly, although not exclusively, to use in micro-unmanned air vehicles (UAV's) with ring-wings. An aircraft (10) according to the invention comprises a ring-wing (11) defining a duct (16) with a longitudinally-extending central axis (31), propulsion means (15) located within the duct and moveable aerofoils (13, 18) for controlling the aircraft in flight, the ring-wing being truncated obliquely at one end, that end being the rear (11b) when in horizontal flight, to form a ring-wing with opposed sides of unequal length. This arrangement produces centre of mass offset from the central axis of the ring-wing, the pendulum effect will ensure that the aircraft will roll so that its centre of mass will always be at the lowest height possible when the aircraft is airborne. Therefore the aircraft has a preferred orientation, and the control surfaces can be oriented with respect to this preferred orientation. In addition, the oblique truncation at the rear keeps the centre of mass towards the front of the aircraft thereby giving improved stability in all three axes.

    RING-WING AIRCRAFT
    60.
    发明公开
    RING-WING AIRCRAFT 有权
    RING-WING飞机

    公开(公告)号：EP1289831A1

    公开(公告)日：2003-03-12

    申请号：EP01921639.9

    申请日：2001-04-20

    申请人： BAE SYSTEMS plc

    发明人： WARSOP, Clyde ,  WOODS, Mike,School of Engineering ,  HENDERSON, James ,  LOCK, Gary,School of Engineering

    IPC分类号： B64C39/02 ,  B64C39/06

    CPC分类号： B64C39/062 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/162

    摘要： This invention relates to ring-wing aircraft and is suited particularly, although not exclusively, to use in micro-unmanned air vehicles (UAV's) with ring-wings. An aircraft (10) according to the invention comprises a ring-wing (11) defining a duct (16) with a longitudinally-extending central axis (31), propulsion means (15) located within the duct and moveable aerofoils (13, 18) for controlling the aircraft in flight, the ring-wing being truncated obliquely at one end, that end being the rear (11b) when in horizontal flight, to form a ring-wing with opposed sides of unequal length. This arrangement produces centre of mass offset from the central axis of the ring-wing, the pendulum effect will ensure that the aircraft will roll so that its centre of mass will always be at the lowest height possible when the aircraft is airborne. Therefore the aircraft has a preferred orientation, and the control surfaces can be oriented with respect to this preferred orientation. In addition, the oblique truncation at the rear keeps the centre of mass towards the front of the aircraft thereby giving improved stability in all three axes.

    摘要翻译： 本发明涉及环翼飞机，特别适用于具有环翼的微型无人驾驶飞行器（UAV），尽管不是唯一的。 根据本发明的飞行器（10）包括限定具有纵向延伸的中心轴线（31）的管道（16）的环翼（11），位于管道内的推进装置（15）以及位于管道内的可移动翼面（13,18 ）用于控制飞行中的飞行器，环翼在一端倾斜地截断，该端在水平飞行时是后部（11b），以形成具有不等长度的相对侧的环翼。 这种布置会产生偏离环翼中心轴线的质量中心，摆动效应将确保飞机在滚转时使其质心始终处于飞机悬空时的最低高度。 因此，飞机具有优选的定向，并且控制表面可以相对于该优选的定向取向。 另外，后部的倾斜截断使质心保持在飞机的前部，从而提高了所有三个轴的稳定性。