Tailored structural actuation system
AssigneeRaytheon Company
InventorAlexander E. Chavez
Life of this patent
Estimating the term…
Abstract
A device may include a locking assembly configured for coupling with an aileron of an aircraft, the locking assembly includes a lock configured for coupling with the aileron. The locking assembly may include a lock mechanism operatively coupled with the lock and in communication with an accelerometer, where the lock mechanism is configured to transition the lock from a locked configuration to a released configuration. The lock mechanism opens the lock based on a specified acceleration measured with the accelerometer, and the lock frees the aileron to a dynamic configuration. A device may include a tailored aileron deployment system including a biasing member coupled with the aileron, in the released configuration the biasing member controls movement of the aileron in the dynamic configuration.
Claims20
A tailored aileron deployment system assembly comprising:
- a locking assembly configured for coupling with an aileron of an aircraft, the locking assembly includes a lock configured for coupling with the aileron;
- an accelerometer configured to measure acceleration of the aircraft and detect gravitational forces;
- a lock mechanism operatively coupled with the lock and in communication with the accelerometer, wherein the lock mechanism is configured to transition the lock from a locked configuration to a released configuration;
- in the locked configuration, the lock retains the aileron in a static configuration;
- and
- in the released configuration, the lock mechanism opens the lock based on a specified acceleration measured with the accelerometer, and the lock frees the aileron to a dynamic configuration;
- and
- a biasing member coupled with the aileron, in the released configuration the biasing member controls movement of the aileron in the dynamic configuration.
A tailored aileron deployment system comprising:
- an aileron coupled with a trailing edge of a wing on an aircraft;
- the aileron having a stowed configuration and a rotation configuration;
- wherein in the stowed configuration the aileron continuously extends from the trailing edge of the aircraft wing and the aileron is statically retained;
- wherein in the rotation configuration, the aileron configured to move relative to the trailing edge of the aircraft wing;
- a locking assembly in communication with the aileron, a locking mechanism positioned proximate to a wing tip of the aircraft wing, the locking assembly including:
- a lock having a locked configuration and a released configuration;
- wherein in the locked configuration, the lock is configured to engage and retain the aileron in the stowed configuration;
- wherein in the released configuration the lock is disengaged from the aileron and the aileron enters the rotation configuration;
- a biasing member coupled with the aileron, the biasing member configured to control movement of the aileron in the released configuration;
- and
- an accelerometer configured to measure an acceleration of the aircraft.
A method for controlling movement of an aileron, the method comprising:
- retaining the aileron in a stowed position with a locking mechanism, the locking mechanism operatively coupled with the aileron;
- wherein in the stowed position the aileron extends continuously from a trailing end of an aircraft wing and the aileron is statically retained;
- measuring acceleration with an accelerometer;
- wherein the accelerometer is operatively coupled with the locking mechanism;
- wherein the accelerometer detects gravitational forces;
- transitioning the locking mechanism from a locked configuration to an unlocked configuration when the accelerometer detects a gravitational force at least equal to a threshold gravitational force;
- releasing the aileron from the stowed position to a released position when the locking mechanism is in the unlocked configuration;
- wherein in the released position the aileron moves according to applied forces;
- and
- controlling the movement of the aileron with a biasing member coupled with the aileron, the biasing member extending from a position proximate to a fuselage to the aileron.
Dependencies are inferred from the claim text.