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公开(公告)号：US11220323B2
公开(公告)日：2022-01-11
申请号：US16297841
申请日：2019-03-11
申请人： Airbus SAS
发明人： Daniel Kierbel
IPC分类号： B64C5/10 , B64C5/02 , B64C9/02 , B64C9/06 , B64C5/06 , B64C1/26 , B64C5/00 , B64C9/00 , B64C27/82 , B64C3/56
摘要： An aircraft comprising a fixed structure, a fuselage mounted on the fixed structure and a tail unit system comprising a structural element housed inside the fuselage and mounted to be rotationally mobile relative to the fixed structure about a transverse axis of rotation parallel to a transverse axis of the aircraft. A first actuation system displaces the structural element in rotation about the transverse axis of rotation, on either side of the structural element. A horizontal tail unit has one end rotationally mobiley mounted on the structural element about a longitudinal axis of rotation parallel to a longitudinal axis of the aircraft and another end which extends out of the fuselage by passing through a window in the fuselage. For each horizontal tail unit, a second actuation system displaces the horizontal tail unit in rotation about the longitudinal axis of rotation.
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公开(公告)号：US20210371088A1
公开(公告)日：2021-12-02
申请号：US17185394
申请日：2021-02-25
发明人： Michael HÖFT , Frank NIELSEN
摘要： A leading edge structure for an aircraft flow control system includes a leading edge panel curvingly surrounding a plenum. The leading edge panel has a first side portion and a second side portion with an inner surface facing the plenum and an outer surface contacting an ambient flow. The leading edge panel includes a plurality of micro pores forming a fluid connection between the plenum and the ambient flow. An air outlet is arranged in the first or second side portion and is fluidly connected to the plenum for letting out air from the plenum into the ambient flow. The air outlet is formed as a fixed air outlet including an outlet panel extending in a fixed manner from the leading edge panel into the ambient flow, such that a rearward facing outlet opening is formed between the leading edge panel and a rear edge of the outlet panel.
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公开(公告)号：US20210371079A1
公开(公告)日：2021-12-02
申请号：US16884911
申请日：2020-05-27
申请人： THE BOEING COMPANY
摘要： An aircraft has a vertical stabilizer with a multi-spar box and a base rib assembly secured to the multi-spar box. The base rib assembly has front longitudinal lugs, rear longitudinal lugs, and opposing middle longitudinal lugs. Front clevises corresponding to the front longitudinal lugs are secured to frame members of the fuselage of the aircraft and each has a first, second, and third mounting arms. Rear clevises corresponding to the rear longitudinal lugs are secured to frame members and each has a first, second, and third mounting arms. Middle clevises corresponding to the middle longitudinal lugs are secured to frame members and each has only first and second mounting arms. Retaining members inserted through mounting holes in each longitudinal lug and mounting holes in each corresponding clevis secures the vertical stabilizer to the fuselage.
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公开(公告)号：US11161610B2
公开(公告)日：2021-11-02
申请号：US16523755
申请日：2019-07-26
申请人： INSITU, INC.
发明人： Wayne Goodrich
摘要： Systems and methods for countering an unmanned air vehicle are disclosed. An example method includes detecting a target UAV via a first component of a target acquisition system. The example method further includes, in response to detecting the target UAV, directing, by executing one or more computer-readable instructions of a launch control system in communication with the target acquisition system, an interceptor UAV to launch. The example method further includes, subsequent to the launch, tracking the target UAV via a second component of the target acquisition system, the second component carried by the interceptor UAV. The example method further includes, when the target UAV is within a target range of the interceptor UAV, deploying a disabling element from the interceptor UAV toward the target UAV.
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公开(公告)号：US11148801B2
公开(公告)日：2021-10-19
申请号：US16020116
申请日：2018-06-27
申请人： JETOPTERA, INC.
发明人： Andrei Evulet
摘要： A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.
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公开(公告)号：US20210107645A1
公开(公告)日：2021-04-15
申请号：US17067397
申请日：2020-10-09
发明人： Jacob S. Izraelevitz , Brett A. Kennedy , Amanda R. Bouman , Daniel Pastor Moreno , Matthew James Lindsay Anderson , Paul M. Nadan , Joel W. Burdick
IPC分类号： B64C39/02 , B64D27/24 , B64C5/06 , B64C1/30 , B64C27/32 , B64C1/06 , B64C25/32 , B64F1/04 , B64D47/08
摘要： A ballistically launched foldable multirotor vehicle has a central body frame. A battery is located in an upper vertical location of the vehicle and positions a center of mass of the vehicle to provide aerodynamic stability during a launch. Fins are attached to the central body frame such that aerodynamic forces on the fins shift an aerodynamic center (AC) of the vehicle downward below the center of mass of the vehicle. Three or more foldable arms are attached to the central body frame via a hinge and exist in two states—a closed state where the foldable arms are parallel to a central body axis, and an open state (after launch) where the foldable arms extend radially outward perpendicular to the central body axis. Rotors mounted to each foldable arm are controlled by a motor to enable flight.
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公开(公告)号：US20210053670A1
公开(公告)日：2021-02-25
申请号：US16544117
申请日：2019-08-19
申请人： Bell Textron Inc.
发明人： Martin Landry
摘要： An embodiment is an aircraft, including at least a fuselage, a tail rotatably coupled to the fuselage, the tail coupled at an aft of the fuselage, and a tail actuator coupled to the fuselage and the tail, the tail actuator to transition the tail between an extended position and a retracted position.
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公开(公告)号：US20210009264A1
公开(公告)日：2021-01-14
申请号：US17040896
申请日：2019-04-12
发明人： Sung Ho Chang , Yu Shin Kim , Seong Wook Choi , Young Shin Kang , Am Cho
摘要： The flying object according to one embodiment comprises: a main body; a main wing formed on a side surface of the main body; a duct-shaped first propulsion part which is provided outside the main wing and can be tilted; a second propulsion part arranged behind the main body; horizontal tail wings formed on both side surfaces of the second propulsion part; and a control part for controlling the movement of the first propulsion part, second propulsion part, and horizontal tail wings, wherein the control part controls the second propulsion part and the horizontal tail wings according to the tilt angle of the first propulsion part.
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公开(公告)号：US20200039632A1
公开(公告)日：2020-02-06
申请号：US16589875
申请日：2019-10-01
摘要： The present disclosure relates to an aerial vehicle with a horizontal tailplane disposed along a bottom edge of a vertical tailfin. Namely, the aerial vehicle includes an empennage attached to the fuselage via a tail boom and a tail coupling. The empennage includes a vertical tailfin that extends below the tail coupling. The empennage also includes a tube arranged along a leading edge of the vertical tailfin and below the tail coupling of the aerial vehicle. The empennage additionally includes one or more rotating actuators and a horizontal tailplane. The horizontal tailplane is coupled to the tail via the tube and includes a continuous leading edge and a cutout. The one or more rotating actuators are configured rotate the horizontal tailplane about an axis of the tube. At least a portion of the vertical tailfin is configured to pass through the cutout.
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公开(公告)号：US20190337630A1
公开(公告)日：2019-11-07
申请号：US16512730
申请日：2019-07-16
摘要： An aircraft is provided including a fuselage that extends along a longitudinal direction between a forward end and an aft end. A boundary layer ingestion fan is mounted to the fuselage at the aft end and is configured for ingesting boundary layer airflow off the surface of the fuselage. The fuselage defines a profile proximate the boundary layer ingestion fan that is optimized for ingesting a maximum amount of boundary layer air and improving propulsive efficiency of the aircraft. More specifically, the fuselage defines a cross sectional profile upstream of the boundary layer ingestion fan that has more cross sectional area in a top half relative to a bottom half as defined relative to a centerline of the boundary layer ingestion fan.
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