| 发明名称 | Flutter control actuator | ||
| 摘要 | A method and apparatus for controlling an angular parameter between a base member and a control surface of an aircraft is disclosed. An estimate is obtained of an angular rate of the control surface with respect to an inertial frame of the aircraft using a rate sensor. A residual angular rate that is a difference between a commanded angular rate and the estimate of the angular rate of the control surface is determined. The residual angular rate is used to control the angular parameter of the control surface or the angular parameter of the base member. | ||
| 申请公布号 | US9611031(B2) | 申请公布日期 | 2017.04.04 |
| 申请号 | US201414224183 | 申请日期 | 2014.03.25 |
| 申请人 | ROSEMOUNT AEROSPACE INC. | 发明人 | McCall Hiram |
| 分类号 | B64C13/16;B64D45/00 | 主分类号 | B64C13/16 |
| 代理机构 | Cantor Colburn LLP | 代理人 | Cantor Colburn LLP |
| 主权项 | 1. A method of controlling an angular parameter between a base member and a control surface of an aircraft, comprising: obtaining an estimate of an angular rate of the control surface with respect to an inertial frame using a rate sensor; determining, via a summing unit, a residual angular rate that is a difference between a commanded angular rate and the estimate of the angular rate of the control surface; and using the residual angular rate to control the base member to control the angular parameter of the control surface; and wherein determining the residual angular rate further comprises subtracting a set rate related to an extremum limit of the estimated angle between the control surface and the base member from the commanded angular rate of the control surface. | ||
| 地址 | Burnsville MN US | ||