IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0736891
(2013-01-08)
|
등록번호 |
US-8544793
(2013-10-01)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
11 |
초록
▼
The adjustable angle inlet for turbojet engines provides for the adjustment of the nacelle inlet as the angle of attack of the aircraft changes. The adjustable inlet system thus assures that the nacelle inlet is always oriented directly into the relative wind as the angle of attack of the aircraft c
The adjustable angle inlet for turbojet engines provides for the adjustment of the nacelle inlet as the angle of attack of the aircraft changes. The adjustable inlet system thus assures that the nacelle inlet is always oriented directly into the relative wind as the angle of attack of the aircraft changes, e.g., during takeoff, landing, and high-G maneuvers where the aircraft reaches relatively high angles of attack. The adjustable angle inlet is adaptable to most turbojet-powered airplanes, but is particularly well suited for use with aircraft having their engines mounted on lateral pylons on the rear of the fuselage. The system operates according to signals received from an angle of attack sensor. The sensor controls an actuator, which rotates a shaft that is connected to the pivotally mounted inlet of the engine nacelle.
대표청구항
▼
1. An adjustable angle inlet for a turbojet engine of a turbojet powered aircraft, the aircraft including an airframe, the adjustable angle inlet comprising a turbojet engine nacelle having: a fixed main portion;an up-limit pin and a clown-limit pin extending from the inlet portion of the nacelle, e
1. An adjustable angle inlet for a turbojet engine of a turbojet powered aircraft, the aircraft including an airframe, the adjustable angle inlet comprising a turbojet engine nacelle having: a fixed main portion;an up-limit pin and a clown-limit pin extending from the inlet portion of the nacelle, each of the pins engaging a corresponding slot defined in the airframe of the aircraft; andan inlet portion pivotally attached to the fixed main portion about a lateral axis. 2. The adjustable angle inlet for a turbojet engine according to claim 1, further comprising an actuator disposed external to the nacelle, the actuator communicating mechanically with the inlet portion of the nacelle. 3. The adjustable angle inlet for a turbojet engine according to claim 2, further comprising: a pivot shaft extending laterally from the inlet portion of the nacelle;a pinion gear mounted on the pivot shaft, the actuator selectively rotating the pinion gear. 4. The adjustable angle inlet for a turbojet engine according to claim 3, further comprising: mutually opposed first and second cylinders disposed within the actuator;a piston disposed within each of the cylinders; anda toothed rack extending from each of the pistons, each of the racks engaging the pinion gear of the pivot shaft. 5. The adjustable angle inlet for a turbojet engine according to claim 2, wherein the actuator is hydraulically powered. 6. The adjustable angle inlet for a turbojet engine according to claim 1, wherein the inlet portion of the nacelle extends forward of the fixed main portion, the inlet portion being angularly adjustable relative to the fixed main portion according to the angle of attack of the turbojet powered aircraft, the adjustable angle inlet further comprising an engine mount pylon immovably affixed to and extending from the airframe of the turbojet powered aircraft, the turbojet engine nacelle being mounted on the pylon. 7. An adjustable angle inlet for a turbojet engine of a turbojet powered aircraft, the aircraft including an airframe, the adjustable angle inlet comprising a turbojet engine nacelle, having: a fixed main portion;an inlet portion pivotally mounted forward of the fixed main portion, the inlet portion being angularly adjustable relative to the fixed main portion about a lateral axis;an up-limit pin and a down-limit pin extending from the inlet portion of the nacelle, each of the pins engaging a corresponding slot defined in the airframe of the aircraft; andan actuator disposed external to the nacelle, the actuator communicating mechanically with the inlet portion of the nacelle. 8. The adjustable angle inlet for a turbojet engine according to claim 7, further comprising a pivot shaft extending laterally from the inlet portion of the nacelle, the pivot shaft including a pinion gear mounted thereon, the actuator selectively rotating the pinion gear. 9. The adjustable angle inlet for a turbojet engine according to claim 8, further comprising: mutually opposed first and second cylinders disposed within the actuator;a piston disposed within each of the cylinders; anda toothed rack extending from each of the pistons, each of the racks engaging the pinion gear of the pivot shaft. 10. The adjustable angle inlet for a turbojet engine according to claim 7, wherein the actuator is hydraulically powered. 11. The adjustable angle inlet for a turbojet engine according to claim 7, further comprising an engine mount pylon immovably affixed to and extending from the airframe of the turbojet powered aircraft, the turbojet engine nacelle being disposed upon the pylon, the inlet portion being angularly adjustable relative to the fixed main portion according to the angle of attack of the turbojet powered aircraft. 12. An adjustable angle inlet for a turbojet engine of a turbojet powered aircraft, the aircraft including an airframe, the adjustable angle inlet comprising: an engine mount pylon immovably affixed to and extending from the airframe of the turbojet powered aircraft;a turbojet engine nacelle disposed upon the pylon, the nacelle having:a fixed main portion; andan inlet portion extending forward of the fixed main portion;an actuator adapted for mounting within the airframe;a shaft extending from the actuator through the pylon to the nacelle, the inlet portion of the nacelle being pivotally connected to the shaft so that rotation of the shaft angularly adjusts the inlet portion relative to the fixed main portion;an up-limit pin and a down-limit pin extending from the inlet portion of the nacelle, each of the pins engaging a corresponding slot defined in the airframe of the aircraft; andmeans for rotating the shaft in order to adjust the angle of the inlet portion to align the inlet portion with airflow as the aircraft's angle of attack changes. 13. The adjustable angle inlet for a turbojet engine according to claim 12, wherein said actuator comprises: first and second double-acting hydraulic cylinders, each of the hydraulic cylinders having a piston and a rack gear extending from the piston, the rack gears extending towards each other axially and retracting away from each other, the rack gears being laterally spaced and facing each other;a pinion gear mounted on said shaft, the pinion gear being mounted between the rack gears of the first and second hydraulic cylinders, the pinion gear engaging the rack gears so that said shaft rotates clockwise when hydraulic fluid is forced on one side of the pistons, and rotates counterclockwise when hydraulic fluid is forced on the opposite side of the pistons, thereby angularly adjusting the inlet portion of said nacelle.
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