专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

WO2017123699A1 HYBRID PROPULSION VERTICAL TAKE-OFF AND LANDING AIRCRAFT 审中-公开
标题翻译：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
申请人： AURORA FLIGHT SCIENCES CORPORATION
发明人： 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分类号： B64C3/38 , B64C5/04 , B64C5/16 , B64C29/00 , B64C39/12 , B64D27/02 , B64D27/24
CPC分类号： 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
摘要： 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.
摘要翻译：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。

2. 发明申请

WO2013112206A1 RAIL RECOVERY SYSTEM FOR AIRCRAFT 审中-公开
标题翻译：航空雷达恢复系统
公开(公告)号：WO2013112206A1
公开(公告)日：2013-08-01
申请号：PCT/US2012/055729
申请日：2012-09-17
申请人： AURORA FLIGHT SCIENCES CORPORATION
发明人： GUNDLACH, Jay , BOURVEN, Jean-Marie , GIANNINI, Francesco , PETULLO, Steve , CLANCY, Tom
IPC分类号： B64C25/68 , B64F1/02
CPC分类号： B64C25/68 , B64C39/024 , B64C2201/182 , B64F1/02
摘要： The present invention's side-arm recovery system enables large Unmanned Aircraft Systems (UASs) to operate from small vessels or from ground sites with a minimal footprint. The side-arm recovery system allows arresting an UAS independent of a runway. On the ground or on a ship, the system makes use of a specialized crane system that includes capture and energy absorption devices. A fuselage-mounted top hook snags a horizontal cable and the arresting forces act in the plane of symmetry through the central structure of the UAS. After the capture energy is absorbed, the recovery system safely lowers the aerial vehicle to a ground handling cart. The same system can be combined into a launcher and retriever system which further reduces the footprint by eliminating the need for a separate launcher.
摘要翻译：本发明的侧臂回收系统使得大型无人驾驶飞行器系统（UAS）能够从小型船舶或地面站点以最小的占地面积运行。侧臂恢复系统可以阻止UAS独立于跑道。在地面或船上，系统利用包括捕获和能量吸收装置的专用起重机系统。机身安装的顶钩钩住水平电缆，并且阻力通过UAS的中心结构作用在对称平面内。捕获能量被吸收后，恢复系统将飞行器安全地降低到地面搬运车。相同的系统可以组合成发射器和猎犬系统，通过消除对单独的发射器的需要进一步减小占地面积。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式