公开(公告)号：WO2013120912A1

公开(公告)日：2013-08-22

申请号：PCT/EP2013/052903

申请日：2013-02-13

Applicant: REITER, Johannes

Inventor： REITER, Johannes

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

CPC classification number: B64C27/00 ,  B64C3/385 ,  B64C27/001 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0075 ,  B64C29/02 ,  B64C39/008 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first longitudinal wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The second wing arrangement (120) comprises at least one propulsion unit (122), wherein the second wing arrangement (120) is mounted to the fuselage (100) such that the second wing arrangement (120) is tiltable around a second longitudinal wing axis (121) of the second wing arrangement (120) and such that the second wing arrangement (120) is rotatable around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) and the second wing arrangement (120) do not rotate around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) and the second wing arrangement (120) are tilted around the respective first longitudinal wing axis (111) and the respective second longitudinal wing axis (121) with respect to its orientations in the fixed-wing flight mode and that the first wing arrangement (110) and the second wing arrangement (120) rotate around the fuselage axis (101).

Abstract translation: 本发明涉及一种飞行器，其包括机身（100），其包括机身轴线（101），第一机翼装置（110）和第二机翼装置（120）。 第一机翼装置（110）安装到机身（100），使得第一机翼装置（110）能围绕第一机翼装置（110）的第一纵向机翼轴线（111）倾斜，并且使得第一机翼装置 （110）能够围绕机身轴线（101）旋转。 第二机翼装置（120）包括至少一个推进单元（122），其中第二机翼装置（120）安装到机身（100）上，使得第二机翼装置（120）可围绕第二纵向机翼轴线 （121），并且使得所述第二机翼装置（120）能够围绕所述机身轴线（101）旋转。 第一机翼装置（110）和第二机翼装置（120）以这样的方式适配，使得在固定翼飞行模式中，第一机翼装置（110）和第二机翼装置（120）不围绕 机身轴（101）。 第一机翼装置（110）和第二机翼装置（120）进一步适于以悬停飞行模式，第一机翼装置（110）和第二机翼装置（120）围绕相应的 第一纵向翼片轴线（111）和相应的第二纵向翼片轴线（121）相对于其在固定翼飞行模式中的定向，并且第一翼形装置（110）和第二翼形装置（120）围绕机身旋转 轴（101）。

公开(公告)号：WO2010024593A3

公开(公告)日：2010-07-22

申请号：PCT/KR2009004773

申请日：2009-08-27

Applicant: LIM CHAEHO

Inventor： LIM CHAEHO

IPC: B64C29/02

CPC classification number: B64C29/0033

Abstract: The present invention concerns a VTOL (Vertical Takeoff and Landing) aircraft. The VTOL aircraft generates lift through a helicopter-shaped rotor when taking off, then flies forward. For further efficient flight at middle or low speed, the VTOL aircraft generates thrust in order to propel the fuselage by a propeller engine which is mounted on the center of the main wing or the fuselage. In addition, the VTOL aircraft can fly forward while generating rearward thrust to help propel the fuselage by turning by 90 degrees the rotors mounted on both sides of the main wings toward the flying direction.

Abstract translation: 本发明涉及一种VTOL（垂直起飞和着陆）飞机。 VTOL飞机在起飞时通过直升机形转子产生升力，然后向前飞行。 为了进一步提高中速或低速飞行的效率，VTOL飞机产生推力，以便通过安装在主机翼或机身中心的螺旋桨发动机推动机身。 此外，VTOL飞机可以向前飞行，同时产生向后推力，通过将主翼两侧的转子向飞行方向转动90度，帮助推动机身。

公开(公告)号：WO2010038922A1

公开(公告)日：2010-04-08

申请号：PCT/KR2008/006548

申请日：2008-11-06

Applicant: LIM, Chaeho

Inventor： LIM, Chaeho

IPC: B64C29/02

CPC classification number: B64C29/0025 ,  B64C27/24

Abstract: This invention is regarding a VTOL aircraft that is designed to enable it to take off by generating lift through rotary wings like a helicopter and then moving forward; and when it flies at high speeds, it is able to use jet engines so that it can generate lift through fixed wings while the rotary wings are transformed into fixed wings to generate lift by adjusting the angles between the individual wings thereby enhancing the efficiency.

Abstract translation: 本发明涉及一种垂直起降飞机，其设计成使其能够通过诸如直升机的旋转翼产生升力然后向前移动而起飞; 并且当它以高速飞行时，它能够使用喷气发动机，使得其可以通过固定翼产生升力，同时通过调节各个翼之间的角度将旋转翼变形成固定翼以产生升力，从而提高效率。

公开(公告)号：WO2004016504A1

公开(公告)日：2004-02-26

申请号：PCT/CN2003/000586

申请日：2003-07-22

IPC: B64C29/02

CPC classification number: B64C39/026 ,  B64C15/02 ,  B64C29/04 ,  B64D33/04

Abstract: A single pilot aircraft that can be carried and bound to a pilot, comprises a turbojet engine, two propulsion air-outlet nozzles which are arranged on either side of the turbojet engine and which can be adjusted to change the direction of the emerging airflow, a fuel tank and a set of hand operated control lever which are linked to propulsion air-outlet nozzles for varying the orientation of the propulsion air outlet nozzles.

公开(公告)号：WO1998012106A1

公开(公告)日：1998-03-26

申请号：PCT/FR1997001655

申请日：1997-09-19

Applicant: S.C.I. CHANEAC ET FILS ,  CHANEAC, André ,  CHANEAC, Jean

Inventor： S.C.I. CHANEAC ET FILS

IPC: B64C29/02

CPC classification number: B64C29/02

Abstract: The invention concerns an aircraft with vertical take-off and landing having a passenger cabin (3) remaining horizontal whatever the angle of inclination of the aircraft, characterised in that the support stands (69), (70), (71) and (72) in contact with the ground are supported each by a beam bearing a change-over flap (77), (78), (79) and (80) pivoting about an axis perpendicular to the aircraft axis and located in the vertical extension of the beam, the aircraft being vertical.

Abstract translation: 本发明涉及一种具有垂直起飞和着陆的飞行器，其中客舱（3）不依赖于飞行器的倾斜角度而保持水平，其特征在于支撑架（69），（70），（71）和（72 与所述地面接触的每一个都由支撑有一个转动翼片（77），（78），（79）和（80）的梁支撑，所述转动翼片围绕垂直于所述飞行器轴线的轴线枢转并且位于所述飞行器的垂直延伸部 梁，飞机垂直。

公开(公告)号：WO2023038684A1

公开(公告)日：2023-03-16

申请号：PCT/US2022/032845

申请日：2022-06-09

Applicant: GENERAL ATOMICS

Inventor： BEARD, Gary C. ,  AVEN, Kyle ,  ANDERSON, Rusty ,  HELMS, Keith ,  XERRI, Jason ,  ODOM, Luther E., Jr.

IPC: G05D1/06 ,  G05D1/08 ,  B64C29/02 ,  B64C39/02 ,  G05D1/02 ,  G05D1/04 ,  G05D1/10 ,  G08G5/06

Abstract: The present disclosure describes autonomous flight safety systems (AFSSs) that incorporate an autonomous flight termination unit (AFTU) enabling AFSS monitoring for various termination conditions that are used to activate a flight termination system (e.g., in the event a termination condition is detected). Such termination conditions include boundary limit detection (e.g., whether a vehicle position is outside or projected outside a planned flight envelope), as well as body instability detection (e.g., whether a pitch rate and yaw rate exceed some threshold indicative of vehicle instability). For instance, an AFTU may incorporate a three-axis gyroscope sensor and may implement instability detection processing based on information obtained via the sensor. Instability detection processing may include, for example, a BID algorithm that may be implemented by an AFTU to monitor angular rates of the vehicle, to determine if the vehicle is no longer under stable control, and to issue termination commands when termination conditions are detected.

公开(公告)号：WO2022051132A1

公开(公告)日：2022-03-10

申请号：PCT/US2021/047303

申请日：2021-08-24

Applicant: BETA AIR, LLC

Inventor： DONOVAN, Sean, Richard ,  VERNA, Raffaello ,  WIEGMAN, Herman ,  LOHE, Braedon, Andrew

IPC: H01M50/20 ,  H01M50/204 ,  H01M50/207 ,  H01M50/209 ,  H01M6/42 ,  B64C29/02

Abstract: A power source assembly for an electric eVTOL aircraft comprising a battery pack. The battery pack further comprising an end panel, a plurality of high energy density battery modules, wherein each module comprises a plurality of battery units, further comprising a plurality of battery cells electronically coupled together, a cell retainer disposed in a predetermined arrangement comprising two columns, a protective wrapping of thermally insulating material woven between columns of battery units, and a terminal electronically disposed on the end panel electronically connected to each of the plurality of high energy density battery modules.

公开(公告)号：WO2021157343A1

公开(公告)日：2021-08-12

申请号：PCT/JP2021/001700

申请日：2021-01-19

Applicant: 株式会社ＳＵＢＡＲＵ

Inventor： 北　光一

IPC: B64C27/08 ,  B64C27/26 ,  B64C27/28 ,  B64C29/02

Abstract: 乗員や貨物等が水平性を保ったまま垂直離着陸と水平高速飛行を両立させることが可能で、軽量化や低コスト、信頼性の向上が可能な垂直離着陸機を提供する。　垂直離着陸と水平飛行とを行うことが可能な垂直離着陸機１において、乗員及び／又は貨物を搭載可能なキャビン２と、垂直離着陸時にキャビン２の前後に配置される回転翼３と、回転翼３を包囲する保護部材４と、保護部材４同士を連結する連結部材５と、キャビン２に対して連結部材５を回動可能に取り付けるためのヒンジ部６と、を備え、連結部材５がキャビン２に対して回動することで回転翼３と固定翼４Ａ～４Ｄとがキャビン２周りに回動して垂直離着陸と水平飛行とを行う。

公开(公告)号：WO2021024370A1

公开(公告)日：2021-02-11

申请号：PCT/JP2019/030856

申请日：2019-08-06

Applicant: 株式会社エアロネクスト

Inventor： 鈴木陽一

IPC: B64C29/02

Abstract: 【課題】ホバリングから水平飛行への効率的かつ安全な移行を可能にした飛行体を提供する。 【解決手段】本発明による飛行体は、翼部と当該翼部に設けられた回転翼とを備える飛行部と、前記飛行部を支持する機体部と、少なくともホバリング時において前記翼部が前記回転翼の回転中心軸に対して負の迎角を維持可能となるように前記翼部及び前記回転翼を変位可能に接続する接続部とを備えている。かかる構成により、ホバリング時から水平飛行移行へと安全に移行することができる。

公开(公告)号：WO2021000028A1

公开(公告)日：2021-01-07

申请号：PCT/BR2019/050247

申请日：2019-07-03

Applicant: FILHO, Alberto Carlos Pereira

Inventor： FILHO, Alberto Carlos Pereira

IPC: B64C29/00 ,  B64C29/02 ,  B64C29/04 ,  B64C39/00

Abstract: Idealiza um inovador veículo voador tipo casulo de decolagem e pouso vertical, que pertence ao campo dos artigos para transporte aéreo, de uso preferencial para o transporte individual, mas opcionalmente pode ser configurado para o transporte de duas pessoas, cujo grande inconveniente dos produtos para o mesmo fim encontrados no estado da técnica é o fato de deixar o usuário exposto e desprotegido; diferentemente o objeto do presente pedido compreende um veículo de voo propulsado, com estrutura e invólucro aerodinâmico, em forma de uma capsula ogival, confeccionado em material leve, confiável, seguro e facilmente controlável, com capacidade de decolar, pousar verticalmente e pairar, voar e manobrar a grandes distâncias e altitudes; constituído por uma capsula em forma de casulo (1) composta de base (2), cabeçote (3) porta de entrada (4) com parabrisa (4A) e um suporte para fixação do moto propulsor.