公开(公告)号：US20150240659A1

公开(公告)日：2015-08-27

申请号：US14279663

申请日：2014-05-16

Applicant: U.S. Army Research Laboratory ATTN: RDRL-LOC-I

Inventor： Robert P. Thornburgh

IPC: F01D25/06 ,  F01D5/14

CPC classification number: F01D5/147 ,  B29D99/0028 ,  B64C9/08 ,  B64C27/72 ,  B64C2027/7222 ,  F01D5/282 ,  F03D1/0675 ,  F05D2220/36 ,  Y02E10/721 ,  Y02T50/32 ,  Y02T50/34 ,  Y02T50/44 ,  Y02T50/672 ,  Y02T50/673

Abstract: Embodiments of the present invention include various airfoils constructions, such as airfoils and rotor blades having a continuous trailing-edge flap. According to an embodiment, an airfoil is comprised of a load-bearing structure in the forward portion of the airfoil; a skin to maintain the airfoil shape; a tapered composite structure having one or more actuators extending from the load-bearing structure toward the trailing edge, and joining the skin in the vicinity of the trailing edge; and a core extending from the load-bearing structure connecting the tapered composite structure to the load-bearing structure. In this airfoil, the tapered composite structure tapers from being relatively thick near the core to being relatively thin near the trailing edge. And the one or more actuators are configured to deflect the trailing edge so as to deform the shape of the airfoil cross-section.

Abstract translation: 本发明的实施例包括各种翼型结构，例如具有连续后缘翼片的翼型件和转子叶片。 根据实施例，翼型件在翼型件的前部中由承载结构构成; 保持翼面形状的皮肤; 锥形复合结构，其具有从所述承载结构朝向所述后缘延伸的一个或多个致动器，并且将所述皮肤接合在所述后缘附近; 以及从连接锥形复合结构到承载结构的承载结构延伸的芯。 在这种翼型件中，锥形复合结构在芯部附近变得相对较粗，在后缘附近变得较薄。 并且一个或多个致动器构造成使后缘偏转以使翼型截面的形状变形。