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Systems and methods are disclosed herein for an aircraft seat with a dual-function linear actuator. The linear actuator may activate a first adjustable feature by moving in a first direction, and the linear actuator may activate a second adjustable feature by moving in a second direction. The linear

Systems and methods are disclosed herein for an aircraft seat with a dual-function linear actuator. The linear actuator may activate a first adjustable feature by moving in a first direction, and the linear actuator may activate a second adjustable feature by moving in a second direction. The linear actuator may include a decoupling mechanism. The decoupling mechanism may decouple the first adjustable feature and the second adjustable feature from the linear actuator in response to loss of power to the linear actuator.

대표청구항 ▼

1. An aircraft seat comprising: a dual-function linear actuator, wherein the dual-function linear actuator is configured to actuate a first adjustment mechanism, in response to translating in a first direction, and wherein the dual-function linear actuator is configured to actuate a second adjustmen

1. An aircraft seat comprising: a dual-function linear actuator, wherein the dual-function linear actuator is configured to actuate a first adjustment mechanism, in response to translating in a first direction, and wherein the dual-function linear actuator is configured to actuate a second adjustment mechanism in response to translating in a second direction; and wherein the dual-function linear actuator comprises a first link coupled to the dual-function linear actuator, a second link coupled to the first link, wherein the second link comprises an elongate slot; anda floor tracking linkage comprising a pin located within the elongate slot; and the aircraft seat further comprises a cable extending through the first link and an aft bracket. 2. The aircraft seat of claim 1, wherein the cable is configured to release a first adjustment feature in response to the dual-function linear actuator translating to a forward position. 3. The aircraft seat of claim 2, wherein the dual-function linear actuator is configured to release a second adjustment feature in response to the dual-function linear actuator translating to an aft position. 4. The aircraft seat of claim 1, further comprising a decoupling rod located at least partially within the first link or the second link.