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公开(公告)号：US20180327079A1
公开(公告)日：2018-11-15
申请号：US15593304
申请日：2017-05-11
CPC分类号： B64C5/06 , B64C27/82 , B64C2027/8272 , B64C2027/8281
摘要： In one embodiment, a vertical stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a vertical orientation. The airfoil structure comprises a leading edge and a trailing edge, wherein the trailing edge is configured to form a blunt shaped edge. The airfoil structure further comprises a root end and a tip end, wherein the airfoil structure is tapered from the root end to the tip end. The airfoil structure is also cambered. Finally, the airfoil structure is further configured to be mounted with a rotor, and is also further configured to house one or more internal components associated with the aircraft.
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公开(公告)号：USD891351S1
公开(公告)日：2020-07-28
申请号：US29636525
申请日：2018-02-08
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公开(公告)号：US10518865B2
公开(公告)日：2019-12-31
申请号：US15593241
申请日：2017-05-11
摘要： In one embodiment, a horizontal stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a horizontal orientation. The airfoil structure comprises a leading edge, a trailing edge, a top surface, and a bottom surface. Moreover, the airfoil structure is cambered, wherein a camber of the airfoil structure forms a concave slope on the top surface and a convex slope on the bottom surface.
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公开(公告)号：US20180362145A1
公开(公告)日：2018-12-20
申请号：US15843039
申请日：2017-12-15
摘要： In a first aspect, there is a method for improving a lift to drag ratio of a rotor blade, including providing a blade member having a leading edge and a trailing edge; providing a leading edge extension member; and coupling the leading edge extension member to a portion of the leading edge of the blade member to form the rotor blade. In a second aspect, there is a rotor blade including a blade member having a leading edge, and a trailing edge; and a leading edge extension member disposed on the leading edge of the blade member, wherein the leading edge extension member is configured to extend the chord length of at least a portion of the rotor blade. In a third aspect, there is a leading edge extension member for a rotor blade including a convex exterior surface configured to extend at least a portion of the chord length of the rotor blade.
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公开(公告)号：USD907559S1
公开(公告)日：2021-01-12
申请号：US29636493
申请日：2018-02-08
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公开(公告)号：US10604234B2
公开(公告)日：2020-03-31
申请号：US15843039
申请日：2017-12-15
IPC分类号： B64C11/18 , B64C11/24 , B64C27/473 , F03D1/06 , B64C29/00
摘要： In a first aspect, there is a method for improving a lift to drag ratio of a rotor blade, including providing a blade member having a leading edge and a trailing edge; providing a leading edge extension member; and coupling the leading edge extension member to a portion of the leading edge of the blade member to form the rotor blade. In a second aspect, there is a rotor blade including a blade member having a leading edge, and a trailing edge; and a leading edge extension member disposed on the leading edge of the blade member, wherein the leading edge extension member is configured to extend the chord length of at least a portion of the rotor blade. In a third aspect, there is a leading edge extension member for a rotor blade including a convex exterior surface configured to extend at least a portion of the chord length of the rotor blade.
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公开(公告)号：US20180327078A1
公开(公告)日：2018-11-15
申请号：US15593241
申请日：2017-05-11
CPC分类号： B64C5/02 , B64C27/06 , B64C27/82 , B64C2003/142 , B64C2027/8272 , B64C2027/8281
摘要： In one embodiment, a horizontal stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a horizontal orientation. The airfoil structure comprises a leading edge, a trailing edge, a top surface, and a bottom surface. Moreover, the airfoil structure is cambered, wherein a camber of the airfoil structure forms a concave slope on the top surface and a convex slope on the bottom surface.
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