公开(公告)号：GB201420955D0

公开(公告)日：2015-01-07

申请号：GB201420955

申请日：2014-11-25

Applicant: PLUMB NICK

公开(公告)号：WO2011066031A2

公开(公告)日：2011-06-03

申请号：PCT/US2010/048323

申请日：2010-09-09

Applicant: AEROVIRONMENT, INC. ,  MIRALLES, Carlos, Thomas ,  PLUMB, Nick ,  TAU, Shuo ,  OLSEN, Nathan

Inventor： MIRALLES, Carlos, Thomas ,  PLUMB, Nick ,  TAU, Shuo ,  OLSEN, Nathan

IPC: B64C9/34 ,  B64C13/18 ,  B64C3/38 ,  B64C13/28

CPC classification number: B64C13/28 ,  B64C3/44 ,  B64C3/50 ,  B64C3/56 ,  B64C5/12 ,  B64C9/02 ,  B64C9/08 ,  B64C9/18 ,  B64C11/00 ,  B64C13/18 ,  B64C39/024 ,  B64C2009/005 ,  B64C2201/021 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/14 ,  B64C2201/145 ,  B64C2201/146

Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100,400,1000,1500) configured to control pitch, roll, and/or yaw via airfoils (141,142,1345,1346) having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns (621,622). Embodiments include one or more rudder elements (1045, 1046,1145, 1146,1245, 1345, 1346,1445, 1446,1545, 1546) which may be rotatably attached and actuated by an effector member (1049,1149,1249,1349) disposed within the fuselage housing (1001) and extendible in part to engage the one or more rudder elements.

Abstract translation: 一种包括飞行器或无人驾驶飞行器（UAV）（100,400,1000,1500）的系统，其被配置为经由具有弹性安装的后缘的机身（141,142,1345,1346）经由机身（141,142,1345,1346）来控制俯仰，滚动和/或偏航， 房屋偏转执行器喇叭（621,622）。 实施例包括一个或多个舵元件（1045,1046,1145,1146,1245,1345,1346,1445,1446,1545,1546），其可以由效应构件（1049,1149,1249,1349）可旋转地附接和致动， 设置在机身壳体（1001）内并且部分地可扩展以接合一个或多个方向舵元件。

公开(公告)号：WO2011066031A3

公开(公告)日：2011-08-11

申请号：PCT/US2010048323

申请日：2010-09-09

Applicant: AEROVIRONMENT INC ,  MIRALLES CARLOS THOMAS ,  PLUMB NICK ,  TAU SHUO ,  OLSEN NATHAN

Inventor： MIRALLES CARLOS THOMAS ,  PLUMB NICK ,  TAU SHUO ,  OLSEN NATHAN

IPC: B64C9/34 ,  B64C3/38 ,  B64C13/18 ,  B64C13/28

CPC classification number: B64C13/28 ,  B64C3/44 ,  B64C3/50 ,  B64C3/56 ,  B64C5/12 ,  B64C9/02 ,  B64C9/08 ,  B64C9/18 ,  B64C11/00 ,  B64C13/18 ,  B64C39/024 ,  B64C2009/005 ,  B64C2201/021 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/14 ,  B64C2201/145 ,  B64C2201/146

Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100,400,1000,1500) configured to control pitch, roll, and/or yaw via airfoils (141,142,1345,1346) having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns (621,622). Embodiments include one or more rudder elements (1045, 1046,1145, 1146,1245, 1345, 1346,1445, 1446,1545, 1546) which may be rotatably attached and actuated by an effector member (1049,1149,1249,1349) disposed within the fuselage housing (1001) and extendible in part to engage the one or more rudder elements.

Abstract translation: 一种包括被配置成经由翼型件（141,142,1345,1346）来控制俯仰，滚转和/或偏航的飞行器或无人飞行器（UAV）（100,400,1000,1500）的系统，所述翼型具有弹性安装的后缘， （621,622）。 实施例包括一个或多个方向舵元件（1045,1046,1145,1146,1245,1345,1346,1445,1446,1545,1545），其可以可旋转地附接并由执行器构件（1049,1149,1249,1349）致动， 设置在机身外壳（1001）内并且可部分延伸以接合一个或多个方向舵元件。