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    HARDWARE-BASED WEIGHT AND RANGE LIMITATION SYSTEM, APPARATUS AND METHOD
    1.
    发明申请
    HARDWARE-BASED WEIGHT AND RANGE LIMITATION SYSTEM, APPARATUS AND METHOD 审中-公开
    基于硬件的重量和范围限制系统，装置和方法

    公开(公告)号：WO2013103403A2

    公开(公告)日：2013-07-11

    申请号：PCT/US2012/058323

    申请日：2012-10-01

    Applicant: AURORA FLIGHT SCIENCES CORPORATION

    Inventor： WASHINGTON, Tom ,  HISAM, Thorsten ,  GOMEZ, Martin

    IPC: G06F17/00

    CPC classification number: B64C13/18 ,  B64C2201/145 ,  B64D45/00 ,  G05D1/0055 ,  G08G5/0021 ,  G08G5/0039 ,  G08G5/006

    Abstract: The present disclosure endeavors to provide systems, methods and apparatus for ensuring aircraft compliance with governmental guidelines, such as, for example, MRCR Category II compliance. A hardware-based system may be employed to reduce range and/or payload below predetermined ranges and a payload capacities. Also provided herein are hardware-based systems, methods, and apparatus for restricting a system's range to predetermined range and/or the payload to a predetermined limit using, for example, a Application-Specific Integrated Circuit (ASIC) installed in the flight control system.

    Abstract translation: 本公开努力提供用于确保飞机遵守政府准则的系统，方法和装置，例如MRCR II类合规。 可以采用基于硬件的系统来减小低于预定范围和有效载荷容量的范围和/或有效载荷。 本文还提供了基于硬件的系统，方法和装置，其使用例如安装在飞行控制系统中的专用集成电路（ASIC）将系统的范围限制到预定范围和/或有效负载到预定极限 。

    HYBRID PROPULSION VERTICAL TAKE-OFF AND LANDING AIRCRAFT
    2.
    发明申请
    HYBRID PROPULSION VERTICAL TAKE-OFF AND LANDING AIRCRAFT 审中-公开
    混合推进垂直起飞和着陆飞机

    公开(公告)号：WO2017123699A1

    公开(公告)日：2017-07-20

    申请号：PCT/US2017/013105

    申请日：2017-01-12

    Applicant: AURORA FLIGHT SCIENCES CORPORATION

    Inventor： GIANNINI, Francesco ,  GOMEZ, Martin ,  COTTRELL, Dan ,  LEDE, Jean-Charles ,  ROBERTS, Tom ,  SCHAEFER, Carl, Jr. ,  COLAS, Dorian ,  WHIPPLE, Brian ,  NUHFER, Tim ,  HUNTER, Herb ,  GROHS, Jonathon ,  PETULLO, Steve

    IPC: B64C3/38 ,  B64C5/04 ,  B64C5/16 ,  B64C29/00 ,  B64C39/12 ,  B64D27/02 ,  B64D27/24

    CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C5/04 ,  B64C5/16 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/048 ,  B64D27/24 ,  B64D29/02 ,  B64D2027/026 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/64

    Abstract: A hybrid propulsion aircraft (100) is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine (112) that drives one or more generators (116) through a gearbox (132). The generator (116) provides AC power to a plurality of ducted fans (108, 110), each being driven by an electric motor (506). The ducted fans (108, 110) may be integrated with the hybrid propulsion aircraft's wings (104, 106). The wings (104, 106) can be pivotally attached to the fuselage (102), thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft (100) mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft (100) offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.

    Abstract translation: 描述了具有分布式电力推进系统的混合动力推进飞行器（100）。 分布式电力推进系统包括通过齿轮箱（132）驱动一个或多个发电机（116）的涡轮轴发动机（112）。 发电机（116）向多个管道式风机（108,110）提供AC电力，每个管道式风机由电动机（506）驱动。 管道风扇（108,110）可以与混合动力推进飞机的机翼（104,106）集成。 机翼（104,106）可枢转地附接到机身（102），从而允许垂直起飞和着陆。 混合动力推进飞行器（100）的设计减轻了从垂直飞行向水平飞行过渡期间传统上遇到的不期望的瞬态行为。 此外，混合动力推进飞机（100）提供快速，恒定高度的过渡，而不需要爬升或俯冲转换。 与其他垂直起降飞机相比，它还提高了悬停和前进飞行的效率，并且比传统的旋翼飞行器具有更高的前进最大速度。

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