| 摘要 |
<p>Control and method for adjusting the geometry of an inlet duct leading to an auxilary power unit in the tailcone of an aircraft. Therefor a closed loop control system is provided. Under this control system the flow area of the inlet duct is varied by opening and closing a duct door. The control assures that the position of the door is such that the delta P across the engine will not inhibit the starting of the engine in flight.</p> |
