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公开(公告)号：US20160046382A1
公开(公告)日：2016-02-18
申请号：US14734505
申请日：2015-06-09
Applicant: Sikorsky Aircraft Corporation
Inventor： Mark R. Alber
Abstract: A system and method for controlling a tail-sitter aircraft, includes determining a mode of operation for the aircraft; operating each of a large turbine engine and a small turbine engine to provide total aircraft power during hover or high-power mode of operation; and selectively providing aircraft power from the small turbine engine to a plurality of rotors during a long-range endurance cruise mode of operation.
Abstract translation: 一种用于控制尾部飞行器的系统和方法，包括确定飞行器的操作模式; 操作大型涡轮发动机和小型涡轮发动机中的每一个以在悬停或高功率运行模式下提供总飞机动力; 并且在远程耐久巡航操作模式期间，选择性地将飞机动力从小型涡轮发动机提供给多个转子。
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32.发明授权公开(公告)号：US08948928B2
公开(公告)日：2015-02-03
申请号：US13866489
申请日：2013-04-19
Applicant: Sikorsky Aircraft Corporation
Inventor： Mark R. Alber , Timothy Fred Lauder , Jonathan Hartman , Bryan Clark Holasek
CPC classification number: B64C19/00 , B64C29/00 , B64C39/022 , B64C39/024 , B64C2201/024 , B64C2201/042 , B64C2201/06 , B64C2201/123 , B64C2201/148 , B64D47/00
Abstract: An electrically powered of the vertical takeoff and landing aircraft configured for use with a tether station having a continuous power source is provided including at least one rotor system. The vertical takeoff and landing aircraft additionally has an autonomous flight control system coupled to the continuous power source. The autonomous flight control system is configured to operate an electrical motor coupled to the at least one rotor system such that the vertical takeoff and landing aircraft continuously hovers above the tether station in a relative position. The vertical takeoff and landing aircraft also includes a detection system for detecting objects at a distance from the vertical takeoff and landing aircraft.
Abstract translation: 提供了一种配置成与具有连续动力源的系绳站一起使用的垂直起飞和着陆飞机的电力供应器，其包括至少一个转子系统。 垂直起飞和着陆飞机还具有耦合到连续电源的自主飞行控制系统。 自主飞行控制系统被配置为操作耦合到至少一个转子系统的电动机，使得垂直起飞和着陆飞机在相对位置连续地悬挂在系绳站上方。 垂直起降飞机还包括一个检测系统，用于检测与垂直起飞和着陆飞机相距一定距离处的物体。
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公开(公告)号：US10752353B2
公开(公告)日：2020-08-25
申请号：US15364166
申请日：2016-11-29
Applicant: Sikorsky Aircraft Corporation
Inventor： Jeffrey Parkhurst , Mark R. Alber
Abstract: An adjustable cable attachment system for a VTOL aircraft includes a VTOL airframe. A winch is operatively connected to an underside of the airframe with the aircraft in a horizontal flight mode. An adjustable cable is operatively connected to the winch to adjustably relocate a slung load with respect to the center of gravity of the aircraft to balance the aircraft. A fixed cable is operatively connected to the underside of the airframe with the aircraft in the horizontal flight mode.
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公开(公告)号：US20180244396A1
公开(公告)日：2018-08-30
申请号：US15758056
申请日：2016-08-25
Applicant: Sikorsky Aircraft Corporation
Inventor： Mark R. Alber
CPC classification number: B64D35/08 , B64C27/14 , B64C27/82 , B64C2027/8236 , B64D35/02 , B64D35/04 , F02C6/20 , F05D2220/329
Abstract: A drive system for a rotorcraft includes at least one engine, the engine including a compressor section, and a turbine section positioned rearward from the compressor section. A main rotor input shaft extends from a rotor power turbine of the turbine section and is connectable to a main rotor assembly of the rotorcraft to transfer rotational energy from the rotor power turbine to the main rotor assembly. An auxiliary input shaft extends from an auxiliary power turbine of the turbine section and is connectible to an auxiliary rotor assembly of the rotorcraft to transfer rotational energy from the auxiliary power turbine to the auxiliary rotor assembly.
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公开(公告)号：US09908615B2
公开(公告)日：2018-03-06
申请号：US15234562
申请日：2016-08-11
Applicant: Sikorsky Aircraft Corporation
Inventor： Mark R. Alber , Jeffery Parkhurst , Cody Fegely , Stephen Kubik
CPC classification number: B64C13/16 , B64C9/00 , B64C25/52 , B64C29/02 , G01C21/165
Abstract: A rotor blown wing (RBW) aircraft including an airframe, at least one rotor blown wing (RBW) having at least control selectively controllable surface, at least one rotor configured to generate and direct an airflow over the at least one RBW, and a control system operatively connected to the at least two selectively controllable control surfaces. The control system selectively controls the at least one selectively controllable control surface to change the airflow over the at least one RBW to facilitate a vertical landing.
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Patent Agency Ranking
公开(公告)号：US20170351270A1
公开(公告)日：2017-12-07
申请号：US15601235
申请日：2017-05-22
Applicant: Sikorsky Aircraft Corporation
Inventor： Matthew T. Luszcz , David L. Adams , Mark R. Alber
CPC classification number: F41G5/18 , B64C27/10 , B64C27/57 , B64C27/82 , B64C29/0033 , B64C2027/8236 , G05D1/0094
Abstract: A flight control system for an aircraft includes a flight control computer operatively interconnected with a main rotor system and a translational thrust system of the aircraft. A selectively enabled integrated target and flight control system arranged in communication with the flight control computer. The integrated target flight and control system is configured to control pitch attitude and heading of the aircraft. When the integrated target and flight control system is enabled, at least partial operation of the aircraft is controlled in response to a pilot input via the flight control computer.
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公开(公告)号：US20170297699A1
公开(公告)日：2017-10-19
申请号：US15335523
申请日：2016-10-27
Applicant: Sikorsky Aircraft Corporation
Inventor： Mark R. Alber , Jeffrey Parkhurst
CPC classification number: B64C29/02 , B64C3/16 , B64C11/30 , B64C11/50 , B64D27/10 , B64D27/24 , B64D2027/026 , Y02T50/64
Abstract: A tail-sitter aircraft is provided and includes a fuselage having first and second axisymmetric sides, first collectively controllable prop-rotors, which are formed to define a first pair of rotor disks and which are respectively supported at the first axisymmetric side of the fuselage, and second collectively controllable prop-rotors, which are formed to define a second pair of rotor disks and which are respectively supported at the second axisymmetric side of the fuselage.
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公开(公告)号：US20170197712A1
公开(公告)日：2017-07-13
申请号：US15313504
申请日：2015-05-19
Applicant: Sikorsky Aircraft Corporation
Inventor： Mark R. Alber
Abstract: An aircraft includes a fuselage and a wing extending from each lateral side of the fuselage. A nacelle is pivotably se cured to each wing. The nacelle has a rotor located thereat, with the rotor having a rotor tip path plane defined by rotation of the rotor about a rotor axis of rotation. When the rotor tip path plane is changed relative to the wing, the nacelle pivots relative to the wing about a nacelle hinge axis to reduce flapping required by the rotor. A method of operating an aircraft includes changing a rotor tip path plane orientation relative to a wing of the aircraft. The rotor disposed at a nacelle, with the nacelle pivotably secured to the wing. The nacelle is pivoted relative to the wing to reduce an overall tip path plane change requirement of the rotor.
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公开(公告)号：US20170158312A1
公开(公告)日：2017-06-08
申请号：US15234562
申请日：2016-08-11
Applicant: Sikorsky Aircraft Corporation
Inventor： Mark R. Alber , Jeffery Parkhurst , Cody Fegely , Stephen Kubik
CPC classification number: B64C13/16 , B64C9/00 , B64C25/52 , B64C29/02 , G01C21/165
Abstract: A rotor blown wing (RBW) aircraft including an airframe, at least one rotor blown wing (RBW) having at least control selectively controllable surface, at least one rotor configured to generate and direct an airflow over the at least one RBW, and a control system operatively connected to the at least two selectively controllable control surfaces. The control system selectively controls the at least one selectively controllable control surface to change the airflow over the at least one RBW to facilitate a vertical landing.
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公开(公告)号：US09567105B2
公开(公告)日：2017-02-14
申请号：US14722921
申请日：2015-05-27
Applicant: Sikorsky Aircraft Corporation
Inventor： Mark R. Alber
CPC classification number: B64C29/02 , B64C39/024 , B64C2201/021 , B64C2201/088 , B64C2201/127 , B64C2201/165 , B64C2201/18 , B64D47/00 , B64D47/08 , H01Q1/42
Abstract: An aircraft is provided and includes a single sensor and wings extending outwardly in opposite directions from a fuselage. Each wing includes a main section, an engine section supported on the main section and tail surfaces extending transversely relative to the main section. The single sensor is mountable to one of the tail surfaces with a field of view (FOV) representable as a spherical wedge having a dihedral angle exceeding 180°.
Abstract translation: 设有飞机并且包括单个传感器和从机身向相反方向向外延伸的翼。 每个翼包括主部分，支撑在主部分上的发动机部分和相对于主部分横向延伸的尾部表面。 单个传感器可安装到一个尾部表面，其视场（FOV）可表示为具有超过180°的二面角的球形楔形物。
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