-
公开(公告)号：WO2019213315A1
公开(公告)日：2019-11-07
申请号：PCT/US2019/030273
申请日：2019-05-01
Applicant: MODERN TECHNOLOGY SOLUTIONS, INC.
Abstract: A method for extracting a person or package from a ground point involves dropping a pod, connected to a tether, with parachute and radio from an aircraft, connected by tether line to the fixed-wing aircraft, tracking descent of the pod to an extraction point, maneuvering the fixed wing aircraft into a circular orbit creating a gravity well, donning the parachute with harness by a subject to be extracted, and altering path and speed of the fixed-wing aircraft to gradually increase tension in the tether to lift the subject in the harness from the ground point, and to accelerate the subject to an altitude and path to carry the subject in the harness to a predetermined altitude over a second ground point.
-
公开(公告)号：WO2019145704A1
公开(公告)日：2019-08-01
申请号：PCT/GB2019/050179
申请日：2019-01-23
Applicant: IQBAL, Kamran , SULAMAN, Shahzad Ul Hussan
Inventor： IQBAL, Kamran , SULAMAN, Shahzad Ul Hussan
CPC classification number: B64C39/08 , B64C29/0025 , B64C29/0033 , B64C29/02 , B64C29/04 , B64C39/026
Abstract: An aircraft comprising a fore thrust means arranged to produce thrust along a first thrust axis, and an aft thrust means arranged to produce thrust along a second thrust axis, wherein the fore thrust means is associated with a fore fixed wing,wherein the aft thrust means is associated with an aft fixed wing, and wherein the first and second thrust axes are offset, such that differential thrust between the fore and aft thrust means causes rotation of the fore and aft thrust means about a lateral axis of the aircraft.
-
公开(公告)号：WO2019062257A1
公开(公告)日：2019-04-04
申请号：PCT/CN2018/094442
申请日：2018-07-04
Applicant: 清华大学
Abstract: 一种基于倾转涵道的双升力涵道垂直起降飞机，包括机身（10）、两个机翼（9）、N个倾转涵道风扇（1、2）、两个升力涵道风扇（5、7）及两个涵道罩（6、13），其中N为偶数。机翼（9）对应设置在机身（10）的中后部的两侧且每一机翼（9）由侧部向外伸展而成。N个倾转涵道风扇（1、2）分为N/2组，每组倾转涵道风扇（1、2）对应安装在机身（10）的两侧，每个倾转涵道风扇（1、2）通过对应的连接件与机身（10）转动连接。两个升力涵道风扇（5、7）嵌入安装在两个机翼（9）中。两个涵道罩（6、13）安装在两个升力涵道风扇（5、7）的上部并可打开或关闭。
-
公开(公告)号：WO2018236295A1
公开(公告)日：2018-12-27
申请号：PCT/TR2017/000109
申请日：2017-10-19
Applicant: TURAN, Ali
Inventor： TURAN, Ali
Abstract: Making drones travel greater distances and stay in mid-air for longer time periods, by making them use the wings at their horizontal movements enabled by developing drones with foldable wings to consume less energy, which can depart from and land to small fields without demanding big fields at their departure and landing because of their wings.
-
公开(公告)号：WO2018194214A1
公开(公告)日：2018-10-25
申请号：PCT/KR2017/005533
申请日：2017-05-26
Applicant: (주)창성에프티
Inventor： 유창범
Abstract: 본 발명의 실시예에 따른 가변 피치 프로펠러를 이용한 고정익 드론은, 선단으로부터 후단으로 길이 방향으로 형성되는 몸체부와, 상기 몸체부의 양측에 고정익 형태로 형성되는 날개부와, 상기 몸체부의 후단에 형성되어 피치가 가변되는 복수의 블레이드로 구성되는 프로펠러를 회전시키는 회전부와, 이착륙모드인 경우 상기 복수의 블레이드를 제1 피치로 가변하여 회전시켜 상기 몸체부의 후단으로부터 선단으로 추진력을 발생시켜 상기 몸체부를 지면으로부터 수직방향으로 이동시키고, 비행모드인 경우 상기 복수의 블레이드를 제2 피치로 가변하여 회전시켜 상기 몸체부의 선단으로부터 후단으로 추진력을 발생시켜 상기 몸체부를 지면으로부터 수평방향으로 이동시키는 제어부를 포함한다.
-
Patent Agency Ranking
公开(公告)号：WO2018152258A1
公开(公告)日：2018-08-23
申请号：PCT/US2018/018253
申请日：2018-02-14
Applicant: AMAZON TECHNOLOGIES, INC.
Abstract: Described is an apparatus and method of an aerial vehicle, such as an unmanned aerial vehicle ("UAV") that can operate in either a vertical takeoff and landing (VTOL) orientation or a horizontal flight orientation. The aerial vehicle includes a plurality of propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll) when in the VTOL orientation. The aerial vehicle also includes a ring wing that surrounds the propulsion mechanisms and provides lift to the aerial vehicle when the aerial vehicle is operating in the horizontal flight orientation.
-
公开(公告)号：WO2018145675A1
公开(公告)日：2018-08-16
申请号：PCT/CZ2018/050004
申请日：2018-02-08
Applicant: NEW SPACE TECHNOLOGIES S.R.O.
Inventor： DRSTICKA, Martin
Abstract: Tail sitter aircraft, comprising a fuselage (4) and a pair of wings (5), each wing having a leading edge (50) and a trailing edge (55), wherein each of the wings (5) is provided with a propeller propulsion unit and a plurality of control tabs (21, 22, 23) arranged at the trailing edge (55) side, the plurality of control tabs comprising at least two pivotally attached control tabs (21, 22, 23) for controlling the direction of the air flowing from the propeller propulsion unit, the plurality of control tabs (21, 22, 23) being interconnected with a an actuating mechanism (20) for controlling the swinging of at least one of the control tabs (21, 22, 23).
-
58.发明申请
公开(公告)号：WO2017210595A3
公开(公告)日：2017-12-07
申请号：PCT/US2017/035742
申请日：2017-06-02
Applicant: AEROVIRONMENT, INC.
Inventor： WON, Henry Thome , LINDSEY, Quentin
Abstract: Systems, devices, and methods for an aircraft having a fuselage (110); a wing (120) extending from both sides of the fuselage; a first pair of motors (132b, 133b) disposed at a first end of the wing; and a second pair of motors (142b, 143b) disposed at a second end of the wing; where each motor is angled (381, 382, 391, 392) to provide a component of thrust by a propeller (134, 135, 144, 145) attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.
-
公开(公告)号：WO2017155348A1
公开(公告)日：2017-09-14
申请号：PCT/KR2017/002608
申请日：2017-03-10
Applicant: 한국항공우주연구원
Inventor： 정진덕
Abstract: 일 실시예에 따른 수직 방향으로 이착륙되는 비행체는 주익, 상기 주익에 배치되어서 동력을 공급하는 동력 공급부, 상기 주익에 배치되어서 비행모드를 제어하는 제어부, 상기 주익에 배치되고, 상기 동력 공급부로부터 동력을 전달 받아 회전하는 로터, 및 상기 동력 공급부로부터 동력을 전달 받아 회전하고, 상기 주익의 일 측에서 배치되는 가변 추력부를 포함할 수 있다. 또한, 상기 제어부는 상기 로터와 상기 가변 추력부를 제어하며 상기 로터는 상기 제어부에 의해 상기 주익에 대하여 평행하게 배치되고, 상기 가변 추력부는 상기 제어부에 의해 상기 주익에 대하여 평행 및 수직 방향으로 전환될 수 있다. 전진 비행시에는 상기 로터 저장고로 로터를 승강시켜고 덮개로 덮어서 공기저항을 감소시켜서 고속 순항이 가능한 비행체이고, 주익 상부에 유동장 박리가 생키면 덮개의 부분적인 개방으로 박리를 절감해서 결과적으로 적은 동력으로 전진 비행이 가능한 비행체이다.
Abstract translation:
车辆，其起飞和降落垂直于根据一个实施例的翼，被布置在所述翼电源单元，用于提供电力，用于控制飞行模式被设置在翼的控制单元，布置在所述翼 以及可变推力部分，其通过接收来自电源部分的动力而旋转并设置在机翼的一侧。 此外，所述控制单元控制所述转子和所述可变推力部和转子可以并行地通过由控制单元以可变推力单元到机翼转换成并行，控制单元被布置成相对于与垂直方向相对于所述翼 有。 在向前飞行有能够进行高速通过降低空气阻力巡航车辆的覆盖有盖子，并解除转子到转子水库，作为结果，通过在翼的流动分离更少的功率上减少分层作为绿色kimyeon盖的部分开口 。
-
60.发明申请
公开(公告)号：WO2017123346A9
公开(公告)日：2017-07-20
申请号：PCT/US2016/065148
申请日：2016-12-06
Applicant: AAI CORPORATION
Inventor： WILLFORD, Neal H.
Abstract: A technique is directed to operating an unmanned aerial vehicle (UAV) having a fuselage defining a flight direction of the UAV and wing-plate assemblies that propel the UAV in the flight direction defined by the fuselage. The technique involves providing, while the flight direction defined by fuselage of the UAV points vertically from a takeoff location on the ground, thrust from propulsion units of the wing plate assemblies to fly the UAV along a vertical takeoff path. The technique further involves maneuvering, after the UAV flies along the vertical takeoff path, the UAV to align the flight direction along a horizontal flight path that is perpendicular to the vertical takeoff path. The technique further involves providing, after the UAV flies along the horizontal flight path, thrust from the propulsion units of the wing-plate assemblies to land the UAV along a vertical landing path.
-
-
-
-
-
-
-
-
-
Search Results
141
records
(took 0.018 seconds)
