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    Remotely controlled methods and systems for actuating boundary layer transition devices in a wind tunnel model
    4.
    发明授权
    Remotely controlled methods and systems for actuating boundary layer transition devices in a wind tunnel model 有权

    公开(公告)号：US10656048B2

    公开(公告)日：2020-05-19

    申请号：US15474714

    申请日：2017-03-30

    Applicant: The Boeing Company

    Inventor： Frederick T. Calkins ,  Dan J. Clingman ,  Robert Griffiths

    IPC: G01M9/02 ,  G01M9/04 ,  G01M9/08 ,  G01M9/06 ,  H02N2/02

    Abstract: A system reproduces aerodynamic boundary layer transition conditions in a wind tunnel test environment under ambient to cryogenic temperature conditions. The system includes a test component disposed in the test environment that defines an exterior surface. A trip dot is mounted on the test component and has a first state, in which a distal surface of the trip dot is at a first elevation relative to the exterior surface of the test component, and a second state, in which the distal surface of the trip dot is at a second elevation relative to the exterior surface of the test component. An actuator is operably coupled to the trip dot and configured to transition the trip dot between first and second states. A controller remotely causes the actuator to transition the trip dot between the first and second states.

    Piezoelectric thrust vector control for dual-mode unmanned aerial vehicle
    6.
    发明授权
    Piezoelectric thrust vector control for dual-mode unmanned aerial vehicle 有权

    公开(公告)号：US11427306B2

    公开(公告)日：2022-08-30

    申请号：US16359342

    申请日：2019-03-20

    Applicant: The Boeing Company

    Inventor： Roger D. Bernhardt ,  Dan J. Clingman

    IPC: B64C29/00 ,  B64C15/02 ,  B64C29/04 ,  B64C39/02 ,  F04D13/06 ,  F04D13/12 ,  F04D15/00 ,  B64D27/18

    Abstract: A ducted-fan unmanned aerial vehicle (UAV) capable of low-energy high-rate maneuvers for both vertical roll control and horizontal pitch control. The UAV includes ducted fans which are with respective piezoelectric-actuated thrust vectoring flaps. Thrust vector control is achieved by controlling the angular positions of a plurality of thrust vector flaps pivotably coupled at respective outlets of a plurality of ducts having fan rotors at the inlets. Each thrust vectoring flap has only one degree of freedom in the frame of reference of the UAV, namely, rotation about a single axis that is perpendicular to the axis of the duct. The angular position of the flap is controlled by sending electrical signals to a piezoelectric actuator (e.g., a piezoelectric bimorph actuator) having a voltage sufficient to cause the piezoelectric actuator to bend.

    VORTEX GENERATORS RESPONSIVE TO AMBIENT CONDITIONS
    9.
    发明申请
    VORTEX GENERATORS RESPONSIVE TO AMBIENT CONDITIONS 有权
    VORTEX发电机响应环境条件

    公开(公告)号：US20160083083A1

    公开(公告)日：2016-03-24

    申请号：US14491916

    申请日：2014-09-19

    Applicant: THE BOEING COMPANY

    Inventor： Anat Bordoley ,  Brian J. Tillotson ,  Michael Chih-Huan Wang ,  Dan J. Clingman

    IPC: B64C21/10 ,  B64C13/02 ,  B64C23/06

    CPC classification number: B64C21/10 ,  B64C13/02 ,  B64C23/06 ,  B64C2230/06 ,  Y02T50/162

    Abstract: A deployable vortex generator attached to a lifting surface includes a vane moveable relative to the lifting surface. The vane moves from a deployed position to a retracted position in response to a change in ambient conditions. In the deployed position, the vane acts on the air flow to create vortices. In the retracted position, the vane is closely aligned with the free stream velocity.

    Abstract translation: 附接到提升表面的可展开的涡流发生器包括相对于提升表面可移动的叶片。 响应于环境条件的变化，叶片从展开位置移动到缩回位置。 在展开位置，叶片作用在空气流上以产生涡流。 在缩回位置，叶片与自由流速度紧密对齐。

    REMOTELY CONTROLLED METHODS AND SYSTEMS FOR ACTUATING BOUNDARY LAYER TRANSITION DEVICES IN A WIND TUNNEL MODEL
    10.
    发明申请
    REMOTELY CONTROLLED METHODS AND SYSTEMS FOR ACTUATING BOUNDARY LAYER TRANSITION DEVICES IN A WIND TUNNEL MODEL 审中-公开

    公开(公告)号：US20180283983A1

    公开(公告)日：2018-10-04

    申请号：US15474714

    申请日：2017-03-30

    Applicant: The Boeing Company

    Inventor： Frederick T. Calkins ,  Dan J. Clingman ,  Robert Griffiths

    IPC: G01M9/02 ,  G01M9/06

    Abstract: A system reproduces aerodynamic boundary layer transition conditions in a wind tunnel test environment under ambient to cryogenic temperature conditions. The system includes a test component disposed in the test environment that defines an exterior surface. A trip dot is mounted on the test component and has a first state, in which a distal surface of the trip dot is at a first elevation relative to the exterior surface of the test component, and a second state, in which the distal surface of the trip dot is at a second elevation relative to the exterior surface of the test component. An actuator is operably coupled to the trip dot and configured to transition the trip dot between first and second states. A controller remotely causes the actuator to transition the trip dot between the first and second states.

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