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    PREFERRED BREAK POINTS AND PATHS IN AIRFRAMES FOR BALLISTIC PARACHUTE SYSTEMS
    2.
    发明申请
    PREFERRED BREAK POINTS AND PATHS IN AIRFRAMES FOR BALLISTIC PARACHUTE SYSTEMS 审中-公开

    公开(公告)号：WO2020076419A2

    公开(公告)日：2020-04-16

    申请号：PCT/US2019/047098

    申请日：2019-08-19

    Applicant: KITTY HAWK CORPORATION

    Inventor： QIAN, Amy ,  VANDER LIND, Damon

    Abstract: A preferred break point is provided in the airframe, where there is a ballistic parachute system which includes a rocket which sits in a rocket canister and a canopy which sits in a canopy canister. The airframe includes a composite material and covers the ballistic parachute system. The preferred break point is located in the airframe over the opening of the rocket canister. A preferred break path is provided in the airframe located at least partially over the opening of the rocket canister and at least partially over the opening of the canopy canister.

    BIMODAL PARACHUTE DEPLOYMENT SYSTEM
    4.
    发明申请
    BIMODAL PARACHUTE DEPLOYMENT SYSTEM 审中-公开
    双模式PARACHUTE部署系统

    公开(公告)号：WO2018080876A1

    公开(公告)日：2018-05-03

    申请号：PCT/US2017/057252

    申请日：2017-10-18

    Applicant: KITTY HAWK CORPORATION

    Inventor： VANDER LIND, Damon ,  ROBERTSON, Cameron

    IPC: B64D17/80

    Abstract: A parachute deployment system is disclosed. In various embodiments, the system includes an interface configured to receive sensor information; a parachute load limiting device; and a parachute load limiting device state controller. The parachute load limiting device state controller sets a state of the parachute load limiting device to a state associated with a corresponding amount of load based at least in part on the sensor information.

    Abstract translation: 公开了一种降落伞展开系统。 在各种实施例中，该系统包括配置成接收传感器信息的接口; 降落伞载荷限制装置; 和降落伞负载限制装置状态控制器。 至少部分基于传感器信息，降落伞负载限制设备状态控制器将降落伞负载限制设备的状态设置为与相应的负载量相关联的状态。

    BISTABLE PITCH PROPELLER SYSTEM WITH BIDIRECTIONAL PROPELLER ROTATION
    5.
    发明申请
    BISTABLE PITCH PROPELLER SYSTEM WITH BIDIRECTIONAL PROPELLER ROTATION 审中-公开
    带双向螺旋桨旋转的双涡轮螺旋桨系统

    公开(公告)号：WO2018026397A1

    公开(公告)日：2018-02-08

    申请号：PCT/US2017/022126

    申请日：2017-03-13

    Applicant: KITTY HAWK CORPORATION

    Inventor： VANDER LIND, Damon ,  REICHERT, Todd

    IPC: B64C11/30 ,  B64C11/32 ,  B64C11/40 ,  B64C11/42 ,  B64C11/44

    CPC classification number: B64C11/325 ,  B64C11/18 ,  B64C11/343 ,  B64C11/46 ,  B64C27/08 ,  B64C27/467 ,  B64C27/80 ,  B64C29/02 ,  B64C2201/108

    Abstract: A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion, of the blade and a second structure coupled to the blade when the bia.de is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

    Abstract translation: 螺旋桨包括可自由旋转的刀片。 当叶片处于旋转运动范围的第一端处的第一位置时，第一止动件定位成机械地接合叶片的第一部分和联接到叶片的第一结构中的一个或两个。 第二止动件定位成当偏置件在限定的旋转范围的第二端处于第二位置时机械地接合叶片的第二部分和联接至叶片的第二结构中的一个或两个。 当螺旋桨沿第一方向旋转时，叶片抵抗第一止动件旋转到第一位置，而当螺旋桨沿第二方向旋转时，叶片抵抗第二止动件旋转到第二位置。

    BISTABLE PITCH PROPELLER SYSTEM WITH UNIDIRECTIONAL PROPELLER ROTATION
    7.
    发明申请
    BISTABLE PITCH PROPELLER SYSTEM WITH UNIDIRECTIONAL PROPELLER ROTATION 审中-公开
    具有单向螺旋桨旋转的双柔性螺旋桨系统

    公开(公告)号：WO2018026398A1

    公开(公告)日：2018-02-08

    申请号：PCT/US2017/022332

    申请日：2017-03-14

    Applicant: KITTY HAWK CORPORATION

    Inventor： VANDER LIND, Damon ,  REICHERT, Todd

    IPC: B64C11/30 ,  B64C11/20 ,  B64C11/32 ,  B64C11/44

    Abstract: A propeller includes a blade free to rotate about a longitudinal axis of the blade. The propeller also includes a mechanical stop positioned to engage mechanically a first portion of the blade and/or a first structure coupled mechanically to the blade when the blade is in a first position. The propeller also includes a magnetic stop positioned to engage magnetically a second portion of the blade and/or a second structure coupled mechanically to the blade when the blade is in a second position. The blade rotates to the first position against the mechanical stop when the propeller is rotated at a first rotational speed and the blade rotates to the second position against the magnetic stop when the propeller is rotated at a second rotational speed in a same direction as when the blade is in the first position.

    Abstract translation: 螺旋桨包括刀片，该刀片围绕刀片的纵向轴线自由旋转。 螺旋桨还包括机械挡块，该机械挡块被定位成机械地接合叶片的第一部分和/或当叶片处于第一位置时机械地联接到叶片的第一结构。 螺旋桨还包括磁性止动件，磁性止动件定位成当叶片处于第二位置时磁力地接合叶片的第二部分和/或机械地联接至叶片的第二结构。 当螺旋桨以第一旋转速度旋转时，叶片抵抗机械止动件旋转到第一位置，并且当螺旋桨以与第二旋转速度相同的方向旋转时，叶片抵抗磁性止动件旋转到第二位置 刀片处于第一位。

    DISTRIBUTED PARACHUTE SYSTEM
    8.
    发明申请
    DISTRIBUTED PARACHUTE SYSTEM 审中-公开
    分布式分布式系统

    公开(公告)号：WO2018080877A1

    公开(公告)日：2018-05-03

    申请号：PCT/US2017/057254

    申请日：2017-10-18

    Applicant: KITTY HAWK CORPORATION

    Inventor： ROBERTSON, Cameron ,  VANDER LIND, Damon

    IPC: B64D17/80 ,  B64D17/00 ,  B64D17/62 ,  B64D17/72 ,  B64D17/76 ,  B64D25/00

    Abstract: A distributed parachute system is disclosed. In various embodiments, a parachute is at least partially deployed along one or more dimensions. A deployment mechanism configured to deploy the parachute is provided. The distributed parachute system is configured to be deployed in an aircraft that comprises a channel oriented along the one or more dimensions.

    Abstract translation: 披露了一种分布式降落伞系统。 在各种实施例中，降落伞沿着一个或多个维度至少部分地展开。 提供配置为部署降落伞的展开机构。 分布式降落伞系统被配置为部署在包括沿着一个或多个维度定向的通道的飞机中。

    MULTI-ROCKET PARACHUTE DEPLOYMENT SYSTEM
    9.
    发明申请
    MULTI-ROCKET PARACHUTE DEPLOYMENT SYSTEM 审中-公开
    多火箭分布式部署系统

    公开(公告)号：WO2018013368A1

    公开(公告)日：2018-01-18

    申请号：PCT/US2017/040420

    申请日：2017-06-30

    Applicant: KITTY HAWK CORPORATION

    Inventor： ROBERTSON, Cameron ,  ROOP, Joseph ,  REICHERT, Todd ,  VANDER LIND, Damon

    IPC: B64D25/00 ,  B64D17/00 ,  B64D17/72 ,  B64D17/62

    Abstract: Techniques to deploy a parachute are disclosed. In various embodiments, a first projectile is configured to be propelled in a first direction, causing the parachute to be deployed. A second projectile configured to be propelled in a second direction is coupled to a line tethered to the parachute in such a way that a force in a direction opposite the first direction is applied to the line of the parachute when the second projectile is propelled in the second direction.

    Abstract translation: 披露了部署降落伞的技术。 在各种实施例中，第一抛射体被配置为沿第一方向推进，使得降落伞展开。 构造成在第二方向上推进的第二抛射体以这样的方式联接到拴系到降落伞上的线，即当第二抛射体在第一方向上被推进时，沿着与第一方向相反的方向的力被施加到降落伞的线 第二方向。

    SHORT TAKEOFF AND LANDING VEHICLE WITH FORWARD SWEPT WINGS
    10.
    发明申请
    SHORT TAKEOFF AND LANDING VEHICLE WITH FORWARD SWEPT WINGS 审中-公开

    公开(公告)号：WO2021072070A1

    公开(公告)日：2021-04-15

    申请号：PCT/US2020/054778

    申请日：2020-10-08

    Applicant: KITTY HAWK CORPORATION

    Inventor： SINHA, Pranay ,  VANDER LIND, Damon

    IPC: B64C11/46 ,  B64C27/22 ,  B64C27/28 ,  B64C29/00 ,  B64C11/28 ,  B64C27/26 ,  B64C27/52 ,  B64C27/82

    Abstract: A short takeoff and landing (STOL) vehicle which comprises a tail having a surface and a fuselage having a surface, where the tail and the fuselage have a continuity of surfaces where the surface of the tail is directly coupled to the surface of the fuselage. The vehicle further includes a forward-swept wing having a trailing edge and a rotor that is attached to the trailing edge of the forward-swept wing via a pylon, where the rotor has a maximum downward angle from horizontal that is less than or equal to 60° and the STOL vehicle takes off and lands using at least some lift from the forward-swept wing and at least some lift from the rotor.

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