公开(公告)号：WO2022003672A1

公开(公告)日：2022-01-06

申请号：PCT/IL2021/050773

申请日：2021-06-24

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： ABRAMOV, Danny ,  HEICHAL, Yoav

IPC: B64C3/56 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/102 ,  B64C39/024

Abstract: A wing system is provided for an air vehicle, the air vehicle having a fuselage including a fuselage longitudinal axis. The wing system includes a set of wings, configured for transitioning between a stowed configuration and a deployed configuration. The set of wings includes a first said wing having a first wing tip, a first wing longitudinal axis, and a first pivot axis; and a second said wing having a second wing tip, a second wing longitudinal axis, and a second pivot axis. The first pivot axis and the second pivot axis are non-coaxial. In the stowed configuration, the first wing and the second wing are in overlying relationship such that at least a majority of a pressure surface of one wing is facing a suction surface of the other wing, and the first wing tip is spaced from the second wing tip by a first lateral spacing. In the deployed configuration, the first wing is oriented with respect to the second wing such that the first wing tip is spaced from the second wing tip by a second lateral spacing greater than the first lateral spacing. The transitioning includes a pivoting operation, including: pivoting the first wing about the first pivot axis between the stowed configuration and the deployed configuration; and, pivoting the second wing about the second pivot axis between the stowed configuration and the deployed configuration.

公开(公告)号：WO2022133134A2

公开(公告)日：2022-06-23

申请号：PCT/US2021/063888

申请日：2021-12-16

Applicant: DASH SYSTEMS, INC.

Inventor： IFILL, Joel Nathan ,  TAYLOR, Zach ,  LITZINGER, Jason ,  STAHLHUTH, Phil ,  BERTE, Marc

IPC: B64D1/02 ,  B64D1/12 ,  B64C39/02 ,  B64D1/08 ,  B64C27/54 ,  G05D1/10 ,  B64C2201/024 ,  B64C2201/082 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/141 ,  B64C27/02 ,  B64C27/022 ,  B64C27/028 ,  B64C39/024 ,  B64D1/14 ,  B64F5/10 ,  G05D1/105

Abstract: A method of assembling a delivery payload assembly configured to be deployed from an aircraft and travel along a flight path to a predetermined landing destination includes attaching a tail-kit assembly to a first end of a payload, the tail-kit assembly including a rotor blade assembly including a plurality of rotor blades having a central axis of rotation, and a flight control and navigation system configured to control a collective pitch angle of each of the plurality of rotor blades of the rotor blade assembly, configured to control an axial thrust force of the rotor blade assembly, the axial thrust force being at an angle with respect to the central axis of rotation of the rotor blade assembly, and configured to navigate the delivery payload assembly along the flight path to the predetermined landing destination. The method further includes removing the tail-kit assembly from the payload after the payload is delivered to the predetermined landing destination.