发明名称 |
Feedback-stabilized aerodynamically overbalanced lifting/control surface for aircraft |
摘要 |
An airfoil of an aircraft is provided with one or more control flaps which are pivotally mounted on the airfoil in an aeromechanically unstable manner. The trailing edges of the control flaps are provided with one or more control tab zones which include trailing portions that deform in response to application of electrical current, heat or pressure thereto. The pitch of the airfoil is constantly controlled by selectively deforming the control tab zones in response to measured signals indicative of variations in fluid pressure acting upon, or motion of the unstable control flaps. The impetus for moving the control system is thus derived from the air-stream through which the aircraft moves. The control system can also be utilized in watercraft, with the operating impetus being derived from the water stream through which the craft moves.
|
申请公布号 |
US5366176(A) |
申请公布日期 |
1994.11.22 |
申请号 |
US19930048864 |
申请日期 |
1993.04.16 |
申请人 |
UNITED TECHNOLOGIES CORP. |
发明人 |
LOEWY, ROBERT G.;MIAO, WEN-LIU |
分类号 |
B64C3/44;B64C9/10;B64C13/50;(IPC1-7):B64C9/10 |
主分类号 |
B64C3/44 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|