A motion control system for controlling an image projected from an underwater projection system in a water feature includes a chassis, a mirror support coupled to the chassis, a mirror member on the mirror support, a first drive member, and a second drive member. The mirror member is configured to reflect the image projected from the underwater projection system in the water feature. The first drive member is coupled to the chassis and configured to rotate the mirror support relative to the chassis about a first axis to move the reflected image in the water feature. The second drive member is coupled to the chassis and a fixed mount and is configured to rotate the chassis and the mirror support about a second axis to move the reflected image in the water feature.

A motion control system for controlling an image projected from an underwater projection system in a water feature includes a chassis, a mirror support coupled to the chassis, a mirror member on the mirror support, a first drive member, and a second drive member. The mirror member is configured to reflect the image projected from the underwater projection system in the water feature. The first drive member is coupled to the chassis and configured to rotate the mirror support relative to the chassis about a first axis to move the reflected image in the water feature. The second drive member is coupled to the chassis and a fixed mount and is configured to rotate the chassis and the mirror support about a second axis to move the reflected image in the water feature.

Dual-input mechanical bypass linkage apparatus and methods are disclosed. An example dual-input mechanical bypass linkage apparatus includes a primary link and a secondary link spaced apart from the primary link. The dual-input mechanical bypass linkage apparatus further includes a first extension link extending between the primary link and the secondary link. The first extension link is coupled to the primary link, to the secondary link and to a first input link. The first input link is coupled to a first actuator. The primary link is coupled to a second input link. The second input link is coupled to a second actuator. The dual-input mechanical bypass linkage apparatus further includes a second extension link spaced apart from the first extension link and extending between the primary link and the secondary link. The second extension link is coupled to the primary link, to the secondary link and to an output link.

Dual-input mechanical bypass linkage apparatus and methods are disclosed. An example dual-input mechanical bypass linkage apparatus includes a primary link and a secondary link spaced apart from the primary link. The dual-input mechanical bypass linkage apparatus further includes a first extension link extending between the primary link and the secondary link. The first extension link is coupled to the primary link, to the secondary link and to a first input link. The first input link is coupled to a first actuator. The primary link is coupled to a second input link. The second input link is coupled to a second actuator. The dual-input mechanical bypass linkage apparatus further includes a second extension link spaced apart from the first extension link and extending between the primary link and the secondary link. The second extension link is coupled to the primary link, to the secondary link and to an output link.

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.

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.

Some embodiments provide a motion control system controlling an image projected from an underwater projection system in a water feature, pool, or spa. The system includes a rotatable base and a mirror support member hingedly coupled to the rotatable base. A first motor is coupled to the rotatable base and is configured to rotate the mirror support member in a first plane. A second motor is coupled to the rotatable base and a fixed mount, wherein the second motor is configured to rotate the rotatable base relative to the fixed mount thereby rotating the mirror support member in a second plane.

Some embodiments provide a motion control system controlling an image projected from an underwater projection system in a water feature, pool, or spa. The system includes a rotatable base and a mirror support member hingedly coupled to the rotatable base. A first motor is coupled to the rotatable base and is configured to rotate the mirror support member in a first plane. A second motor is coupled to the rotatable base and a fixed mount, wherein the second motor is configured to rotate the rotatable base relative to the fixed mount thereby rotating the mirror support member in a second plane.

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.

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.