Aircraft nacelle assemblies include a frame, a cowl coupled to the frame, and a biasing member (including a passive mechanism) coupled between the frame and the cowl. The cowl is configured to move between a closed position and an open position. The passive mechanism is configured to provide a biasi
Aircraft nacelle assemblies include a frame, a cowl coupled to the frame, and a biasing member (including a passive mechanism) coupled between the frame and the cowl. The cowl is configured to move between a closed position and an open position. The passive mechanism is configured to provide a biasing force to the cowl. 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 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.
대표청구항▼
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 substantiall
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; anda 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. 2. The aircraft nacelle assembly of claim 1, wherein the frame includes a cowl support and a fan case that is spaced inward from the cowl support, wherein the cowl is rotatably and operably coupled to the cowl support, and wherein the biasing member is operatively coupled between the cowl and the fan case. 3. The aircraft nacelle assembly of claim 1, wherein the first net force causes a first net torque on the cowl about the joint axis that urges the cowl away from the open position, and wherein the second net force causes a second net torque on the cowl about the joint axis that urges the cowl away from the closed position. 4. The aircraft nacelle assembly of claim 1, wherein the cowl in the closed position encloses the biasing member within the aircraft nacelle assembly. 5. The aircraft nacelle assembly of claim 1, wherein the joint axis is substantially horizontal when the aircraft nacelle assembly is in a predetermined position associated with maintenance of an associated engine housed within the aircraft nacelle assembly. 6. The aircraft nacelle assembly of claim 1, wherein the cowl is configured to be moved manually to the open position from the closed position with a force that is less than 80 lbs. 7. The aircraft nacelle assembly of claim 1, wherein the biasing member includes a telescoping cover enclosing the passive mechanism. 8. The aircraft nacelle assembly of claim 1, wherein the biasing member includes a locking mechanism that is configured to selectively and temporarily fix a length of the biasing member so that the cowl is temporarily restricted from moving about the joint axis. 9. The aircraft nacelle assembly of claim 1, wherein the biasing member does not utilize electric or hydraulic powered actuators. 10. The aircraft nacelle assembly of claim 1, wherein the cowl is further configured to move to a neutral position that is between the closed position and the open position, and wherein when the cowl is in the neutral position, the biasing force coupled with the weight of the cowl results in a net torque on the cowl about the joint axis that is neither away from the open position nor away from the closed position. 11. The aircraft nacelle assembly of claim 1, wherein the biasing member is under compression during a full extent of movement of the cowl between the closed position and the open position. 12. The aircraft nacelle assembly of claim 1, wherein the aircraft nacelle assembly includes two or more biasing members, wherein each biasing member applies a substantially equal force to the cowl when the cowl is in the closed position, and wherein each biasing member applies a substantially equal force to the cowl when the cowl is in the open position. 13. The aircraft nacelle assembly of claim 1, wherein the rotatable joint is a hinge. 14. An aircraft nacelle assembly, comprising: a cowl support;a fan case;a cowl rotatably and operatively coupled to the cowl support with a rotatable joint, wherein the cowl is configured to rotate about a joint axis between a closed position, a neutral position, and an open position, wherein in the closed position the cowl substantially covers an engine housed within the aircraft nacelle assembly, wherein in the neutral position the cowl partially uncovers the engine, wherein in the open position the cowl at least substantially uncovers the engine, and wherein the cowl has a weight; anda biasing member operatively coupled between the fan case and the cowl, wherein the biasing member includes a spring configured to apply a biasing force to the cowl, wherein the biasing member is operatively coupled to the fan case 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 torque on the cowl about the joint axis that urges the cowl away from the open position, 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 torque on the cowl about the joint axis that urges the cowl away from the closed position, wherein when the cowl is in the neutral position, the biasing force coupled with the weight of the cowl results in a third net torque on the cowl about the joint axis that neither urges the cowl away from the open position nor urges the cowl away from the closed position, wherein the biasing member includes a telescoping cover enclosing the spring and a locking mechanism that is configured to selectively and temporarily fix a length of the biasing member so that the cowl is temporarily restricted from moving about the joint axis, wherein the biasing member is enclosed within the aircraft nacelle assembly when the cowl is in the closed position, and wherein the aircraft nacelle assembly facilitates manual opening and closing of the cowl by an operator grasping and manipulating a region of the cowl that is distal to the joint axis. 15. The aircraft nacelle assembly of claim 14, wherein the joint axis is substantially horizontal when the aircraft nacelle assembly is in a predetermined position associated with maintenance of the engine. 16. The aircraft nacelle assembly of claim 14, wherein the biasing member does not utilize electric or hydraulic powered actuators. 17. The aircraft nacelle assembly of claim 14, wherein the biasing member is under compression during a full extent of movement of the cowl between the closed position and the open position. 18. The aircraft nacelle assembly of claim 14, wherein the aircraft nacelle assembly includes two or more biasing members, wherein each biasing member applies a substantially equal force to the cowl when the cowl is in the closed position, and wherein each biasing member applies a substantially equal force to the cowl when the cowl is in the open position. 19. The aircraft nacelle assembly of claim 14, wherein the rotatable joint is a hinge.
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이 특허에 인용된 특허 (13)
Dalebout William T. (Logan UT) Measom S. Ty (Logan UT) Watterson Scott R. (Logan UT), Adjustable incline system for exercise equipment.
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