公开(公告)号：WO1994026589A1

公开(公告)日：1994-11-24

申请号：PCT/US1994004722

申请日：1994-04-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  FLEMMING, Robert, J., Jr. ,  ROSEN, Kenneth, M. ,  SHEEHY, Thomas, W.

IPC: B64C27/20

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162

Abstract: An unmanned aerial vehicle (UAV) (100) having a toroidal fuselage (120) and a rotor assembly (170) including counter-rotating rotors coaxially mounted with respect to the toroidal fuselage incorporates ancillary aerodynamic structures (18) having a cambered airfoil profile to provide a nose-down pitching moment to counteract the nose-up pitching moment generated by airflow over the toroidal fuselage during forward translational flight of the UAV. The ancillary aerodynamic structures are symmetrically mounted in combination with the lateral sides of the toroidal fuselage so that the centers of lift are located aftwardly of the fuselage axis of the toroidal fuselage in forward translational flight modes. In a first embodiment, the ancillary aerodynamic structures (18) are fixedly mounted in combination with the toroidal fuselage (10) at a predetermined angle of incidence. In a second embodiment, the ancillary aerodynamic structures (19) are rotatably mounted in combination with the toroidal fuselage (10') to provide variable incidence ancillary aerodynamic structures for the UAV.

Abstract translation: 具有环形机身（120）的无人驾驶飞行器（100）和包括相对于环形机身同轴安装的反向旋转转子的转子组件（170）包括具有弧形翼型轮廓的辅助空气动力结构（18） 提供一个俯仰俯仰的时刻，以抵消在无人机前向平移飞行期间通过环形机身产生的气流俯仰时刻。 辅助空气动力学结构与环形机身的侧面对称地安装，使得升降中心位于远端机构的机身轴线的前方向前平移飞行模式。 在第一实施例中，辅助空气动力结构（18）以预定的入射角度与环形机身（10）组合地固定安装。 在第二实施例中，辅助空气动力学结构（19）可旋转地与环形机身（10'）组合安装，以为UAV提供可变入射辅助气动结构。

公开(公告)号：EP0696983A1

公开(公告)日：1996-02-21

申请号：EP94915945.0

申请日：1994-04-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： FLEMMING, Robert, J., Jr. ,  ROSEN, Kenneth, M. ,  SHEEHY, Thomas, W.

IPC: B64C27 ,  B64C39

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162

Abstract: An unmanned aerial vehicle (UAV) (100) having a toroidal fuselage (120) and a rotor assembly (170) including counter-rotating rotors coaxially mounted with respect to the toroidal fuselage incorporates ancillary aerodynamic structures (18) having a cambered airfoil profile to provide a nose-down pitching moment to counteract the nose-up pitching moment generated by airflow over the toroidal fuselage during forward translational flight of the UAV. The ancillary aerodynamic structures are symmetrically mounted in combination with the lateral sides of the toroidal fuselage so that the centers of lift are located aftwardly of the fuselage axis of the toroidal fuselage in forward translational flight modes. In a first embodiment, the ancillary aerodynamic structures (18) are fixedly mounted in combination with the toroidal fuselage (10) at a predetermined angle of incidence. In a second embodiment, the ancillary aerodynamic structures (19) are rotatably mounted in combination with the toroidal fuselage (10') to provide variable incidence ancillary aerodynamic structures for the UAV.

公开(公告)号：EP0696983B1

公开(公告)日：1997-03-26

申请号：EP94915945.3

申请日：1994-04-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： FLEMMING, Robert, J., Jr. ,  ROSEN, Kenneth, M. ,  SHEEHY, Thomas, W.

IPC: B64C27/20 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162

Abstract: An unmanned aerial vehicle (UAV) (100) having a toroidal fuselage (120) and a rotor assembly (170) including counter-rotating rotors coaxially mounted with respect to the toroidal fuselage incorporates ancillary aerodynamic structures (18) having a cambered airfoil profile to provide a nose-down pitching moment to counteract the nose-up pitching moment generated by airflow over the toroidal fuselage during forward translational flight of the UAV. The ancillary aerodynamic structures are symmetrically mounted in combination with the lateral sides of the toroidal fuselage so that the centers of lift are located aftwardly of the fuselage axis of the toroidal fuselage in forward translational flight modes. In a first embodiment, the ancillary aerodynamic structures (18) are fixedly mounted in combination with the toroidal fuselage (10) at a predetermined angle of incidence. In a second embodiment, the ancillary aerodynamic structures (19) are rotatably mounted in combination with the toroidal fuselage (10') to provide variable incidence ancillary aerodynamic structures for the UAV.