Wing tip aileron actuation system

A flight vehicle comprising:

• first and second wings configured to be contained within a housing when in a stowed position and extend outward from the housing when in a deployed position;
• an actuator;
• a bell crank having a first end connected to the actuator, a pivot point at a second end, and first and second arms extending outward from the second end with the first arm having a first fork and the second arm having a second fork;
• a first pivot pin rotatable with the first wing between the stowed position and the deployed position, the first pivot pin having an opening that is aligned with and adjacent to the first fork;
• a first lever pin within the opening in the first pivot pin and extending out from the opening in the first pivot pin to be located within the first fork on the first arm, the first lever pin rotatable with the first wing and the first pivot pin so that the first lever pin is disengaged from the first fork when in the stowed position and is engaged with the first fork when in the deployed position;
• a first wing tip shaft within the first wing and connected to the first lever pin at a first end and to a first aileron at a second end, the first wing tip shaft configured to rotate to control the first aileron when the first fork of the bell crank moves the first lever pin within the first pivot pin;
• a second pivot pin rotatable with the second wing between the stowed position and the deployed position, the second pivot pin having an opening that is aligned with and adjacent to the second fork;
• a second lever pin within the opening in the second pivot pin and extending out from the opening in the second pivot pin to be located within the second fork on the second arm, the second lever pin rotatable with the second wing and second pivot pin so that the second lever pin is disengaged from the second fork when in the stowed position and is engaged with the second fork when in the deployed position;
• and
• a second wing tip shaft within the second wing and connected to the second lever pin at a first end and to a second aileron at a second end, the second wing tip shaft configured to rotate to control the second aileron when the second fork of the bell crank moves the second lever pin within the second pivot pin.