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61. 发明专利

IL230249A Autonomous emergency descending and landing of aircraft 未知
公开(公告)号：IL230249A
公开(公告)日：2016-08-31
申请号：IL23024913
申请日：2013-12-31
申请人： ISRAEL AEROSPACE IND LTD , OHAD ROZENBERG
发明人： OHAD ROZENBERG
IPC分类号： B64C20060101

62. 发明专利

HK1213934A1 用於降低拖曳的可剝離的膜組件和塗層未知
公开(公告)号：HK1213934A1
公开(公告)日：2016-07-15
申请号：HK16101758
申请日：2016-02-18
申请人： PRC-DESOTO INT INC
发明人： ROPER TODD M TM , BOWMAN MARK P MP , RAKIEWICZ EDWARD F EF
IPC分类号： C09D20060101 , B64C20060101 , F15D20060101

63. 发明专利

IL234536A Centrifugal de-clutch 未知
公开(公告)号：IL234536A
公开(公告)日：2016-06-30
申请号：IL23453614
申请日：2014-09-08
申请人： ZEE AERO INC
IPC分类号： B64C20060101 , B64D20060101 , F16D20060101
摘要： A mechanical mechanism is used to prevent a rotor of an aircraft from rotating when the rotor is not in use. The mechanical mechanism disengages when the speed of the rotor exceeds a speed threshold and the mechanism reengages when the speed of the rotor is below the speed threshold.

64. 发明专利

HK1211270A1 氣流截斷裝置未知
公开(公告)号：HK1211270A1
公开(公告)日：2016-05-20
申请号：HK15112167
申请日：2015-12-09
申请人： TAMARACK AEROSPACE GROUP INC
发明人： GUIDA NICHOLAS R
IPC分类号： B64C20060101

65. 发明专利

HK1206694A1 MULTIPLE CONTROLLABLE AIRFLOW MODIFICATION DEVICES 未知
公开(公告)号：HK1206694A1
公开(公告)日：2016-01-15
申请号：HK15107484
申请日：2015-08-04
申请人： TAMARACK AEROSPACE GROUP INC
发明人： GUIDA NICHOLAS R
IPC分类号： B64C20060101

66. 发明专利

IL241201D0 Foldable wings for an unmanned air vehicle 未知
公开(公告)号：IL241201D0
公开(公告)日：2015-11-30
申请号：IL24120115
申请日：2015-09-06
申请人： UNISION AIR LTD , MOSHE KAHLON , AMIT MORAG
IPC分类号： B64C20060101

67. 发明专利

IL226696A Method and system for determining a region of interest for an imaging device based on instrument landing system 未知
公开(公告)号：IL226696A
公开(公告)日：2015-11-30
申请号：IL22669613
申请日：2013-06-02
申请人： ELBIT SYSTEMS LTD
IPC分类号： B64C20060101 , B64D20060101 , G05D20060101 , G08B20060101 , G08G20060101

68. 发明专利

HK1202846A1 AUTOPILOT SYSTEM, COMPONENTS AND METHODS 未知
公开(公告)号：HK1202846A1
公开(公告)日：2015-10-09
申请号：HK15103393
申请日：2015-04-06
申请人： MERLIN TECHNOLOGY INC
发明人： ALBION NICOLAS , FEIFEL MARC , MARVIN MARK , MERCER JOHN
IPC分类号： B64C20060101 , G05D20060101
摘要： A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

69. 发明专利

IL239205D0 Vertical takeoff and landing aircraft 未知
公开(公告)号：IL239205D0
公开(公告)日：2015-07-30
申请号：IL23920515
申请日：2015-06-04
申请人： DELOREAN AEROSPACE LLC
IPC分类号： B64C20060101
摘要： The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. By moving the rotor units, the aircraft can transition from a hover mode to a transition mode and then to a forward flight mode and back.

70. 发明专利

IL238633D0 An airplane wing, an airplane and a flap system 未知
公开(公告)号：IL238633D0
公开(公告)日：2015-06-30
申请号：IL23863315
申请日：2015-05-04
申请人： FOKKER AEROSTRUCTURES BV , ADRIANUS MARINUS FRANCISCUS BASTIAANSEN , MICHEL SCHOONHOVEN
IPC分类号： B64C20060101
摘要： An airplane wing comprises a main wing and a flap system that has a flap at the trailing edge of the main wing. An elongate flap track member is connected to the main wing in such a manner that it can be moved substantially in its longitudinal direction and is guided by supporting bearing elements relative to the main wing between a forward retracted position and a rearward extended position. The flap is rotatably connected to the rear end of the flap track member in such a manner that it can rotate about a rotation axis that extends substantially parallel to the trailing edge of the main wing, so that the flap moves together with the flap track member when the flap track member is moved and so that the flap can be rotated about the rotation axis mechanically independently of the movement of the flap track member. The flap system comprises an actuator system having two actuators. The first actuator is connected to the main wing and has an engagement member that engages the flap or the flap track member for moving the flap together with the flap track member so that the flap track member is move able between its retracted position and its extended position. The second actuator is connected to the flap track member so that the second actuator moves together with the flap track member when the flap track member is moved by means of the first actuator. The second actuator has an engagement member that engages the flap for rotating the flap about the rotation axis.

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