发明名称 Self-centering bearing for aircraft control surfaces
摘要 <p>A control surface assembly includes: a control surface member; a shaft attached to the control surface member; a control system connected with the shaft; and a bearing. The shaft has a longitudinal axis defining an axis of rotation for the control surface member. The control system is configured to induce rotation in the shaft about the axis of rotation such that the control surface member rotates between a first preselected position and a second rotated position. The bearing includes a first member (12), a second member (16) and a resilient intermediate member (14) positioned between and attached to the first (12) and second members (16). The first member (12) is attached to the shaft (26), and the second member (16) is adapted for non-releasable fixed attachment to the vehicle during operation of the vehicle. In response to rotation induced by the control system during operation, the first member (12), the shaft (26) and the control surface member (16) rotate about the axis of rotation from the preselected to the rotated position, the second member (16) remains fixed relative to the vehicle, and the intermediate member undergoes angular deflection and biases the first member (12), shaft (26) and control surface member (16) to rotate toward the preselected position, such that disabling of the control system causes the control surface member to return to the preselected position. &lt;IMAGE&gt;</p>
申请公布号 EP1048563(A2) 申请公布日期 2000.11.02
申请号 EP20000303568 申请日期 2000.04.27
申请人 LORD CORPORATION 发明人 DONOVAN, NEIL J.
分类号 B64C9/02;F16F1/393;(IPC1-7):B64C9/02;F16F1/38 主分类号 B64C9/02
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