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11. 发明申请

US20190002134A1 PAYLOAD ADAPTER RING 审中-公开
公开(公告)号：US20190002134A1
公开(公告)日：2019-01-03
申请号：US16063580
申请日：2015-12-18
申请人： AIRBUS DEFENCE AND SPACE S.A.
发明人： Joaquín Martín Llorente
IPC分类号： B64G1/64
摘要： Lightweight spacecraft dispenser (1), which consists of a ring structure with several payload ports (2), the surface (3) of the ring structure being at least partially spherical.

12. 发明授权

US09983393B2 Catoptric imaging device for drill measuring 有权
公开(公告)号：US09983393B2
公开(公告)日：2018-05-29
申请号：US15146474
申请日：2016-05-04
申请人： AIRBUS DEFENCE AND SPACE, S.A.
发明人： Fernando Enrique Esteban Finck , David Gomez Esteban , Francisco José León Arevalo , Luis Granero Montagud , Martín Sanz Sabater , Vicente Mico Serrano , Javier Garcia Monreal
IPC分类号： G02B17/02 , H04N5/369 , G01M13/00 , G01B11/12 , G01B11/24 , G02B5/136 , G02B23/24 , G01N21/954
CPC分类号： G02B17/026 , G01B11/12 , G01B11/24 , G01M13/00 , G01N21/954 , G01N2021/9548 , G02B5/136 , G02B23/24 , H04N5/369
摘要： A catoptric imaging device for drill measuring comprising a laser guide, an imaging unit for converting optical image into image information, and processing the image information to obtain a drill measure, a catoptric assembly including a first conical surface, and a second surface including a frustoconical surface, wherein the first surface is arranged relative to the laser guide to reflect a cone beam onto an cross section of the drill to be measured, and wherein the smallest diameter of the frustoconical surface is larger than the largest diameter of the first surface to receive the cone beam reflections and reflect them towards the imaging unit, and wherein the imaging unit is arranged to receive an optical image from the frustoconical surface reflections to obtain a drill measure.

13. 发明授权

US09878797B2 Alignment and safety device for the cowls of aircraft engine nacelles 有权
公开(公告)号：US09878797B2
公开(公告)日：2018-01-30
申请号：US14869314
申请日：2015-09-29
申请人： Airbus Defence and Space S.A.
发明人： Juan Carlos Ambite Iglesias
IPC分类号： B64B1/24 , B64D27/00 , B64D29/00 , B64D31/00 , B64D33/00 , B64D35/00 , B64D29/08 , B64D29/06
CPC分类号： B64D29/08 , B64D29/06
摘要： The disclosure herein provides an alignment and safety device for the cowls of the nacelle of an aircraft engine formed by first and second parts to be arranged opposite of each other at the lower edges of the cowls that include first and second alignment arms configured with a portion arranged to enter inside the inner space of the nacelle covered by the opposite cowl. One of the parts includes a blocking member configured to be interposed between the cowls after being unlatched to facilitate their opening operation and also when they return to the closed position from an open position if they are misaligned to facilitate its alignment and subsequent latching applying a force F on the blocking member.

14. 发明申请

US20180025814A1 DEVICE AND METHOD FOR CABLE ASSEMBLY 审中-公开
公开(公告)号：US20180025814A1
公开(公告)日：2018-01-25
申请号：US15656135
申请日：2017-07-21
申请人： AIRBUS DEFENCE AND SPACE S.A.
发明人： Juan TORRES MORENO , Alberto PEREZ BARTHELEMY , Josef Ignacio HÖTZ ORDOÑO , Tamara RAMOS SANTANA , Jose Carlos DIAZ CRUZ
IPC分类号： H01B13/012
摘要： A cable (1) assembly device for producing cabling including: a support surface (2) on which the cable assembly is carried out (1), cable (1) fastening and guide elements (3), said fastening and guide elements (3) comprising a vacuum element for joining it to said support surface (2), a feeder (4) of the cable to be assembled, a computation means that includes a cabling diagram in its memory and the location of the fastening and guide elements (3) on the support surface (2), a storage module (5) for cable (1) fastening and guide elements (3), positioning means (6) of the fastening and guide elements (3) on the support surface (2).

15. 发明申请

US20170203831A1 PROPELLER DEVICE FOR AIRCRAFT, SPACECRAFT OR WATERCRAFT 审中-公开
公开(公告)号：US20170203831A1
公开(公告)日：2017-07-20
申请号：US15262208
申请日：2016-09-12
申请人： Airbus Defence and Space S.A.
发明人： Jesús LÓPEZ FERRER , Eugenio GARRIDO CORRALEJO
IPC分类号： B64C11/28 , B63H1/14 , B63H1/22 , B64C39/02 , B64C11/14
CPC分类号： B64C11/28 , B63B2035/009 , B63B2748/00 , B63H1/14 , B63H1/22 , B63H1/28 , B64C11/14 , B64C39/024
摘要： A propeller device for aircraft, spacecraft or watercraft comprising two or more blades and a spinner. The blades are arranged on a hub so that they can be in a deployed or a retracted position. The spinner comprises first, second and third movable portions configured for allowing deploying or retracting the blades and for keeping the blades deployed or retracted.

16. 发明授权

US09656759B2 Collapsible securing system for securing medical oxygen cylinders for aircraft passenger seats 有权
公开(公告)号：US09656759B2
公开(公告)日：2017-05-23
申请号：US14932741
申请日：2015-11-04
申请人： Airbus Defence and Space S.A.
发明人： Jose Luis De La Fuente Carnero , Victor Julian Sanchez Barreda
IPC分类号： A62B9/04 , B64D25/00 , F16M13/02 , A62B25/00
CPC分类号： B64D25/00 , A62B9/04 , A62B25/005 , F16M13/02
摘要： A collapsible securing system for securing medical oxygen cylinders for passenger seats including: (i) a base configured such as to be positioned on the passenger seat; (ii) an intermediate securing structure for oxygen cylinders connected to the base by three legs; (iii) a gripping structure, connected to the intermediate securing structure by at least one pivot in common with the intermediate securing structure, and (iv) a fitting system comprising the seatbelt and two straps secured from one end the gripping structure and from the other end thereof to the fitting of the seatbelt to the passenger seat.

17. 发明申请

US20170113804A1 TWO-PHASE TYPE HEAT TRANSFER DEVICE FOR HEAT SOURCES OPERATING AT A WIDE TEMPERATURE RANGE 审中-公开
公开(公告)号：US20170113804A1
公开(公告)日：2017-04-27
申请号：US15331232
申请日：2016-10-21
申请人： Airbus Defence and Space S.A.
发明人： Ana BLANCO MAROTO , Francisco Jose REDONDO CARRACEDO , Alejandro TORRES SEPULVEDA , Donatas MISHKINIS , Juan MARTINEZ MARTIN
IPC分类号： B64D15/02 , B64C3/00 , B64D29/00 , F28D15/02
摘要： A two-phase type heat transfer device (10) for heat sources operating at a wide temperature range. The heat transfer device (10) includes an evaporator (21) collecting heat from a heat source, a condenser (21) providing heat to a cold sink by a first working fluid passing through liquid and vapor transport lines (25, 27) that connect the evaporator (21) and the condenser (23). The evaporator (21) is arranged inside a saddle (31) configured for avoiding that the temperature of the first working fluid in the evaporator (21) is greater than its critical point. The invention also refers to aircraft ice protection systems using the heat transfer device (10).

18. 发明申请

US20160318049A1 MACHINE FOR MIXING AND SUCCESSIVELY APPLYING SEALANT MATERIAL 审中-公开
标题翻译：混合和成型应用密封材料的机器
公开(公告)号：US20160318049A1
公开(公告)日：2016-11-03
申请号：US15135335
申请日：2016-04-21
申请人： Airbus Defence and Space S.A.
发明人： Fernando Enrique ESTEBAN FINCK , Cristóbal LEÓN CAMPOS , Daniel RICO IGLESIAS
IPC分类号： B05B7/12 , B05B7/24 , B05B7/04
CPC分类号： B05B7/12 , B05B7/0408 , B05B7/24 , G05D11/132
摘要： A machine (21) for mixing and applying continuously a bi-component sealing material formed by mixing a base and a hardener in a pre-established ratio that is used, for example, in joining areas of structural elements of aircraft structures. Their metering chambers (25, 25′) are configured with a volumetric ratio between them adapted to the volumetric ratio of mixture of the base and the hardener and the pushing device (31) comprises means for actuating the pistons (33, 33′) allowing different displacement speeds and control means so that the outflow of said metering chambers (25, 25′) is that required for the base and hardener can reach the mixing head (43) in a pre-established weight ratio.
摘要翻译：一种机器（21），用于连续地混合并施加双组分密封材料，所述双组分密封材料通过以例如在飞机结构的结构元件的接合区域中以预先确定的比率混合基底和固化剂而形成。它们的计量室（25,25'）被构造成它们之间的体积比适应于基座和硬化剂的混合物的体积比，并且推动装置（31）包括用于致动活塞（33,33'）的装置，不同的位移速度和控制装置，使得所述计量室（25,25'）的流出是基座和固化剂所需要的量可以以预定的重量比到达混合头（43）。

19. 发明申请

US20160311554A1 CONTACT DETECTING SYSTEM AND METHOD FOR AIR REFUELING TANKER EQUIPPED WITH AIR REFUELING BOOM SYSTEM 审中-公开
标题翻译：空气补给装置系统和空气净化装置的检测系统及方法
公开(公告)号：US20160311554A1
公开(公告)日：2016-10-27
申请号：US15138724
申请日：2016-04-26
申请人： Airbus Defence and Space S.A.
发明人： Jose Luis Marcos Montes , Francisco Jose Lagares Carrasco , Guillaume Angibaud
IPC分类号： B64D39/04
CPC分类号： B64D39/04 , B64D39/06
摘要： A contact detecting system for an air refueling tanker equipped with an air refueling boom, the system comprising a boom refueling nozzle comprising a valve to allow the exit of fuel, a latch to engage the refueling nozzle, a first contact detecting mechanism configured to transmit a signal when the refueling nozzle is in a contact position, a second contact detecting mechanism configured to detect the position of the latch and to transmit a signal when the latch is latched, and a third contact detecting mechanism configured to detect the position of the valve and to transmit a signal when the valve is open. The system further comprises a computing device configured to receive the signals from the first, second and third contact detecting mechanisms and to provide an output signal of the contact status of the refueling nozzle.
摘要翻译：一种用于装备有空气加油斗的空中加油车的接触检测系统，该系统包括一个起重臂加油喷嘴，该起重臂加油喷嘴包括一个允许燃料排出的阀，一个与加油喷嘴接合的闩锁;一个第一接触检测机构，信号，当加油喷嘴处于接触位置时，第二接触检测机构构造成检测闩锁的位置并且当闩锁被锁定时传递信号;以及第三接触检测机构，其构造成检测阀的位置，以及当阀门打开时传送信号。该系统还包括被配置为从第一，第二和第三接触检测机构接收信号并且提供加油喷嘴的接触状态的输出信号的计算装置。

20. 发明授权

US12006072B2 Multiple hold-down and release device for spacecraft, and methods for releasing a spacecraft from a dispenser of a launcher and for installing a multiple hold-down and release device for spacecraft 有权
公开(公告)号：US12006072B2
公开(公告)日：2024-06-11
申请号：US17617862
申请日：2019-06-12
申请人： AIRBUS DEFENCE AND SPACE S.A.
发明人： Eugenio Grande Saez
IPC分类号： B64G1/64
CPC分类号： B64G1/641 , B64G1/645 , B64G1/643
摘要： A multiple hold-down and release device for spacecraft includes a central structure including a central section with a cylindrical inner hole, an inner axial shaft insertable into the inner hole. A release bolt aligns with the inner axial shaft. A main bushing is partially arranged inside the inner hole and axially guided by guiding bushings on the main bushing and the inner hole. The main bushing includes a protrusion and internal retainer spring. Arms protruding from the central section are axially preloaded by a pusher opposite the central section. Connecting levers each connect to the end of the corresponding arm by the pusher. Hold-down assemblies on the periphery of the device each include a hold-down support and a fastener with conical contact surfaces, a torsion spring around a torsion spring shaft, and articulated with the corresponding hold-down support by the corresponding torsion spring shaft.

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