Patent ID: 9221545
Filing Date: 2015-12-29
Classification: B64D,F01D

Abstract:
1. An aircraft nacelle assembly, comprising: a frame; a cowl rotatably and operatively coupled to the frame with a rotatable joint, wherein the cowl is configured to rotate about a joint axis between a closed position and an open position, wherein in the closed position the cowl at least substantially covers an engine housed within the aircraft nacelle assembly, wherein in the open position the cowl at least substantially uncovers the engine, and wherein the cowl has a weight; and a biasing member operatively coupled between the frame and the cowl, wherein the biasing member includes a passive mechanism configured to apply a biasing force to the cowl, wherein the biasing member is operatively coupled to the frame with a first coupling and is operatively coupled to the cowl with a second coupling, wherein the first coupling is above a first line from the rotatable joint to the second coupling when the cowl is in the closed position, and wherein the first coupling is below a second line from the rotatable joint to the second coupling when the cowl is in the open position, wherein when the cowl is in or near the closed position, the biasing force coupled with the weight of the cowl results in a first net force that urges the cowl away from the open position, and wherein when the cowl is in or near the open position, the biasing force coupled with the weight of the cowl results in a second net force that urges the cowl away from the closed position.