公开(公告)号：US20060032971A1

公开(公告)日：2006-02-16

申请号：US11042666

申请日：2005-01-24

Applicant: G. Baldwin

Inventor： G. Baldwin

IPC: B64C27/22

CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

Abstract: A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

Abstract translation: 公开的飞行技术包括具有第一端和第二端的悬挂结构，升降单元和有效载荷单元。 提升单元包括机舱和尾巴，并且枢转地联接到悬架结构的第一端，并且有效载荷单元耦合到结构的第二端。 因此，尾巴可以相对于有效载荷单元枢转地联接，这有利地允许尾巴呈现对于特定飞行方式所需的取向。 在垂直飞行或悬停期间，尾巴可以以与悬挂结构基本平行的方向从提升单元悬挂，并且使得抵抗来自提升单元的降洗的阻力最小化。 在水平飞行期间，尾翼可以与悬架结构正交，向后延伸，在该方向上可以产生俯仰和偏转力矩以控制和稳定水平飞行。 还公开了有利的变型和方法。

公开(公告)号：US20050109874A1

公开(公告)日：2005-05-26

申请号：US10931801

申请日：2004-08-31

Applicant: G. Baldwin

Inventor： G. Baldwin

IPC: B64C11/00 ,  B64C17/04 ,  B64C27/28 ,  B64C29/00 ,  B64C31/036 ,  B64C15/12

CPC classification number: B64C17/04 ,  B64C11/001 ,  B64C27/28 ,  B64C29/0033 ,  B64C31/036

Abstract: A disclosed vertical lift flying craft includes a lift unit that, during operation, develops a force including an upward component. A payload unit suspends from the lift unit. The payload unit suspends from the lift unit in such a way as to impart lateral stability while remaining capable of horizontal flight, without incurring the adverse effects of a downward pitching moment. In addition to a lift unit and a payload unit, the vertical lift flying craft includes a pair of bearings and a suspension structure, which cooperate to suspend the payload unit from the lift unit. Other systems and methods are also disclosed.

Abstract translation: 所公开的垂直升降飞行器包括提升单元，其在操作期间产生包括向上分量的力。 有效载荷单元从电梯单元暂停。 有效载荷单元以提供侧向稳定性的方式从升降机单元悬挂，同时保持能够水平飞行，而不会产生向下的俯仰时刻的不利影响。 除了升降机单元和有效载荷单元之外，垂直升降飞行器还包括一对轴承和悬挂结构，它们协作以将有效负载单元从升降单元悬挂下来。 还公开了其它系统和方法。

公开(公告)号：US20070114325A1

公开(公告)日：2007-05-24

申请号：US11479833

申请日：2006-06-30

Applicant: G. Baldwin

Inventor： G. Baldwin

IPC: B64C27/00

CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

Abstract: A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimzes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

Abstract translation: 公开的飞行技术包括具有第一端和第二端的悬挂结构，升降单元和有效载荷单元。 提升单元包括机舱和尾巴，并且枢转地联接到悬架结构的第一端，并且有效载荷单元耦合到结构的第二端。 因此，尾巴可以相对于有效载荷单元枢转地联接，这有利地允许尾巴呈现对于特定飞行方式所需的取向。 在垂直飞行或悬停期间，尾巴可以以与悬挂结构基本平行的方向从提升单元悬挂并且最小化来自提升单元的降洗阻力。 在水平飞行期间，尾翼可以与悬架结构正交，向后延伸，在该方向上可以产生俯仰和偏转力矩以控制和稳定水平飞行。 还公开了有利的变型和方法。