公开(公告)号：US20220324572A1

公开(公告)日：2022-10-13

申请号：US17587905

申请日：2022-01-28

Applicant: Saeid A. ALZAHRANI

Inventor： Saeid A. ALZAHRANI

IPC: B64D5/00 ,  B64C39/02 ,  B64D7/00

Abstract: Techniques and systems are provided for the deployment of small Unmanned Aircraft Systems (sUAS) and Loitering Munitions (LM) from an airborne Small Tactical Unmanned Aircraft System (STUAS).

公开(公告)号：US20170369162A1

公开(公告)日：2017-12-28

申请号：US15372667

申请日：2016-12-08

Applicant: Saeid A. ALZAHRANI

Inventor： Saeid A. ALZAHRANI

IPC: B64C29/00 ,  B64C3/38 ,  B64C39/02 ,  B64C25/22 ,  B64C27/52

CPC classification number: B64C29/0033 ,  B64C3/38 ,  B64C25/22 ,  B64C27/52 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/162

Abstract: A multi-mode unmanned aerial vehicle includes an elongated fuselage, a right and left fixed wing extending from a respective right and left side of the elongated fuselage, a right and left tilt wing attached at a first side to a free end of the respective right and left fixed wing, a right and left duct attached to a second side of the respective right and left tilt wing, a right and left winglet attached to the respective right and left duct opposite to the right and left tilt wing, a tilt tail located within a curved guide slot at a rear end of the elongated fuselage, a rear duct attached to the tilt tail, a tilting mechanism, and an integrated autonomous flight control system.

公开(公告)号：US20170369161A1

公开(公告)日：2017-12-28

申请号：US15195238

申请日：2016-06-28

Applicant: Saeid A. ALZAHRANI

Inventor： Saeid A. ALZAHRANI

IPC: B64C29/00 ,  B64C25/32 ,  B64C23/06 ,  B64C9/00 ,  B64C5/02 ,  B64C27/52 ,  B64C3/38

CPC classification number: B64C29/0033 ,  B64C3/38 ,  B64C5/02 ,  B64C9/00 ,  B64C23/065 ,  B64C25/32 ,  B64C27/52

Abstract: A multi-mode aerial vehicle hybrid wing includes a fixed wing configured to extend from a side of an elongated fuselage and double over its longitudinal axis, a tilt wing attached at a first side to a free end of the fixed wing wherein the tilt wing is rotatable ninety degrees about its axis, and a duct attached to a second side of the tilt wing. The duct includes a plurality of pivotal control surfaces positioned at a top entrance of the duct, dual counter-rotating rotors positioned at an underside of the duct, a plurality of cross stators positioned at a back entrance of the duct, and a plurality of stator pivotal control surfaces within each of the cross stators of the duct. The multi-mode aerial vehicle hybrid wing also includes a winglet attached to the duct opposite to the tilt wing.