A fuel distribution system for an aircraft having wing and fuselage fuel tanks. The system includes sensors for indicating the level of fuel in each tank and at least one selectively controllable pump for moving fuel between the fuselage tank and one or more wing tanks. A controller is configured to monitor sensed fuel levels in the wing and fuselage tanks and selectively control the pump to shift fuel between the fuselage tank and the one or more wing tanks to maintain the aircraft's longitudinal center of gravity within preselected limits.

A fuel distribution system for an aircraft having wing and fuselage fuel tanks. The system includes sensors for indicating the level of fuel in each tank and at least one selectively controllable pump for moving fuel between the fuselage tank and one or more wing tanks. A controller is configured to monitor sensed fuel levels in the wing and fuselage tanks and selectively control the pump to shift fuel between the fuselage tank and the one or more wing tanks to maintain the aircraft's longitudinal center of gravity within preselected limits.

A method, vehicle, and system for calculating the location of a center of mass of the vehicle and transferring fuel to move the location of the center of mass are provided. The location of the center of mass of the vehicle is determined by measuring or calculating forces acting on the vehicle that counteract the gravitational forces on the vehicle. The location of the center of mass is calculated by determining on a moment arm of the gravitational force that counteracts the moment arms of the other forces acting on the vehicle. Fuel can be transferred among differently-located fuel tanks in the vehicle to move the location of the center of mass to a position in which at least some of the other forces acting on the vehicle are reduced, which may increase the speed and/or efficiency of the vehicle.

A method, vehicle, and system for calculating the location of a center of mass of the vehicle and transferring fuel to move the location of the center of mass are provided. The location of the center of mass of the vehicle is determined by measuring or calculating forces acting on the vehicle that counteract the gravitational forces on the vehicle. The location of the center of mass is calculated by determining on a moment arm of the gravitational force that counteracts the moment arms of the other forces acting on the vehicle. Fuel can be transferred among differently-located fuel tanks in the vehicle to move the location of the center of mass to a position in which at least some of the other forces acting on the vehicle are reduced, which may increase the speed and/or efficiency of the vehicle.

A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist.

A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist.

A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist.

A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist.

An actuator includes a brushless DC motor, an output device, a reduction system coupled between the brushless DC motor and the output device, and a contactless position sensor configured to sense a position of the output device.

An actuator includes a brushless DC motor, an output device, a reduction system coupled between the brushless DC motor and the output device, and a contactless position sensor configured to sense a position of the output device.