公开(公告)号：US20170174342A1

公开(公告)日：2017-06-22

申请号：US14737702

申请日：2015-06-12

Applicant: Deng Huang

Inventor： Deng Huang

IPC: B64C29/00 ,  B64C39/08 ,  B64C29/02

CPC classification number: B64C29/0033 ,  B64C29/02 ,  B64C39/08 ,  B64C2201/088 ,  B64C2201/102

Abstract: A tilt wing aircraft has a spaced plurality of wings mounted on a fuselage to pivot in unison about corresponding ones of a parallel plurality of tilt axes, between an upright position and a cruise position. In the cruise position the wings are disposed edge to edge with a gap less than the width of any of the plurality of wings, as measured at the fuselage. A plurality of power units are mounted on one or more of the wings to rotate in unison with them between a vertical propulsion position and a forward propulsion position. Said plurality of power units can rotate into the vertical propulsion position as the wings rotate into the upright position. The wings are placed in an upright position with the power units positioned to provide vertical propulsion. When powered, the power units can create a downdraft between the wings in order to lift the fuselage. The wings and the power units are rotated to reduce their angles of attack and facilitate forward motion of the fuselage.

公开(公告)号：USD1048790S1

公开(公告)日：2024-10-29

申请号：US29947176

申请日：2024-06-13

Applicant: Deng Huang

Designer： Deng Huang

Abstract: FIG. 1 is a top perspective view of a rose straw cover showing my new design.
FIG. 2 is a bottom perspective view thereof.
FIG. 3 is a front view thereof.
FIG. 4 is a rear view thereof.
FIG. 5 is a left side view thereof.
FIG. 6 is a right side view thereof.
FIG. 7 is a top view thereof; and,
FIG. 8 is a bottom view thereof.
The broken lines illustrate portions of the rose straw cover that form no part of the claimed design.

公开(公告)号：US20230382521A1

公开(公告)日：2023-11-30

申请号：US18202350

申请日：2023-05-26

Applicant: Deng Huang

Inventor： Deng Huang

IPC: B64C29/00 ,  B64C27/24 ,  B64U10/20

CPC classification number: B64C29/0008 ,  B64C27/24 ,  B64U10/20

Abstract: An aerial vehicle pertinent to the present application has a rotor system that operates in both a vertical-take-off-landing (VTOL) and a cruise mode. There are boom structures which support rotors and the tail. Tiltable rotors are located at the front ends of the booms. The rear rotors are placed under an upward rise in the booms, which allows for reduced in-flight drag and eliminates the need for collapsible rotors when said rotors are not actively operational.