A blocker door actuation system for use in an aircraft thrust reverser is provided. The blocker door actuation system may comprise a rack, a gear, a gear housing, a screw shaft, and a link. The blocker door actuation system may be mounted to a translating sleeve in an aircraft nacelle. In response t
A blocker door actuation system for use in an aircraft thrust reverser is provided. The blocker door actuation system may comprise a rack, a gear, a gear housing, a screw shaft, and a link. The blocker door actuation system may be mounted to a translating sleeve in an aircraft nacelle. In response to the thrust reverser being activated and the translating sleeve moving aft, the blocker door actuation system may move the blocker door from a stowed position to a deployed position in a fan air duct.
대표청구항▼
1. A thrust reverser system, comprising: a translating sleeve;a blocker door actuation system comprising, a gear,a threaded shaft rotatably received within the gear,a rack mounted to a cascade and configured to provide a travel path for the gear; anda blocker door rotatably coupled to the threaded s
1. A thrust reverser system, comprising: a translating sleeve;a blocker door actuation system comprising, a gear,a threaded shaft rotatably received within the gear,a rack mounted to a cascade and configured to provide a travel path for the gear; anda blocker door rotatably coupled to the threaded shaft, wherein the blocker door is actuated from a stowed position to a deployed position in response to the translating sleeve moving aft, wherein the threaded shaft is configured to translate substantially perpendicular to a centerline of the thrust reverser system in response to the translating sleeve moving aft. 2. The thrust reverser system of claim 1, further comprising a gear housing. 3. The thrust reverser system of claim 2, wherein the translating sleeve comprises and inner sleeve and an outer sleeve. 4. The thrust reverser system of claim 3, wherein the gear housing is coupled to the inner sleeve. 5. The thrust reverser system of claim 1, further comprising a cascade and a rack, the rack being at least one of integrally formed in and coupled to the cascade. 6. The thrust reverser system of claim 5, wherein the gear rotatably translates along the rack in response to the translating sleeve moving aft. 7. The thrust reverser system of claim 1, wherein the gear is a pinion gear. 8. The thrust reverser system of claim 1, wherein the blocker door actuation system comprises a link, and wherein the link is coupled to the blocker door on a forward portion of the blocker door. 9. The thrust reverser system of claim 1, wherein the blocker door actuation system comprises a link, and wherein the link is coupled to a blocker door to minimize the travel required to translate the blocker door from the stowed position to the deployed position. 10. An aircraft nacelle, comprising: a translating sleeve;a blocker door actuation system comprising a gear and a screw shaft, the screw shaft oriented perpendicular to a centerline of the aircraft nacelle, the blocker door actuation system coupled to the translating sleeve;a rack configured to rotatably guide the gear; anda blocker door operatively coupled to the blocker door actuation system and configured to translate from a stowed position to a deployed position in response to the translating sleeve moving aft. 11. The aircraft nacelle of claim 10, wherein the blocker door actuation system further comprises a link comprising a first end and a second end. 12. The aircraft nacelle of claim 11, wherein the first end of the link is rotatably coupled to the screw shaft. 13. The aircraft nacelle of claim 11, wherein the second end of the link is rotatably coupled to the blocker door. 14. The aircraft nacelle of claim 10, wherein the translating sleeve comprises an inner sleeve and an outer sleeve, the translating sleeve defining a chamber between the inner sleeve and the outer sleeve that is configured to house a cascade in the stowed position. 15. The aircraft nacelle of claim 14, wherein the blocker door actuation system further comprising a gear housing configured to house the gear. 16. The aircraft nacelle of claim 15, wherein the gear housing is fixed to the inner sleeve. 17. A blocker door actuation system, comprising: a rack coupled to a cascade in a thrust reverser;a gear configured to rotatably translate along the rack;a gear housing configured to house the gear;a screw shaft threadably installable within the gear and configured to translate within the gear in response to gear translating along the rack, wherein the screw shaft is oriented perpendicular to the rack; anda link rotatably coupled to a blocker door and coupled to the screw shaft. 18. The blocker door actuation system of claim 17, wherein the gear housing is attached to a translating sleeve.
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이 특허에 인용된 특허 (12)
Timms Richard H. (San Diego County CA), Aircraft thrust reverser mechanism.
Baudu Pierre Andre Marcel,FRX ; Gonidec Patrick,FRX ; Rouyer Pascal Gerard,FRX ; Vauchel Guy Bernard,FRX, Synchronizing control system for aircraft jet engine thrust reversers.
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