Abstract: A method of determining a center of gravity of an aircraft in flight by comparing actual control surface actuator displacements to expected control surface actuator displacements. And a method of fuel/load management based on an offset of the center of gravity from a preferred center of gravity and a handling qualities factor.

Abstract: A method of determining a center of gravity of an aircraft in flight by comparing actual control surface actuator displacements to expected control surface actuator displacements. And a method of fuel/load management based on an offset of the center of gravity from a preferred center of gravity and a handling qualities factor.

Abstract: A control system having a first loop configured to provide a longitudinal blowback value of a rotor blade during flight and a second loop associated with the first loop, the second loop being configured to provide a design maximum total flapping value and a lateral flapping value. A method includes calculating a flight control limit from the design maximum total flapping value and the lateral flapping value. An upper longitudinal cyclic control limit is calculated by adding the flight control limit to the longitudinal blowback value. A lower longitudinal cyclic control limit is calculated by subtracting the flight control limit from the longitudinal blowback value.

Abstract: A control system having a first loop configured to provide a longitudinal blowback value of a rotor blade during flight and a second loop associated with the first loop, the second loop being configured to provide a design maximum total flapping value and a lateral flapping value. A method includes calculating a flight control limit from the design maximum total flapping value and the lateral flapping value. An upper longitudinal cyclic control limit is calculated by adding the flight control limit to the longitudinal blowback value. A lower longitudinal cyclic control limit is calculated by subtracting the flight control limit from the longitudinal blowback value.

Abstract: A control system having a first loop configured to provide a longitudinal blowback value of a rotor blade during flight and a second loop associated with the first loop, the second loop being configured to provide a design maximum total flapping value and a lateral flapping value. A method includes calculating a flight control limit from the design maximum total flapping value and the lateral flapping value. An upper longitudinal cyclic control limit is calculated by adding the flight control limit to the longitudinal blowback value. A lower longitudinal cyclic control limit is calculated by subtracting the flight control limit from the longitudinal blowback value.

Abstract: A control system having a first loop configured to provide a longitudinal blowback value of a rotor blade during flight and a second loop associated with the first loop, the second loop being configured to provide a design maximum total flapping value and a lateral flapping value. A method includes calculating a flight control limit from the design maximum total flapping value and the lateral flapping value. An upper longitudinal cyclic control limit is calculated by adding the flight control limit to the longitudinal blowback value. A lower longitudinal cyclic control limit is calculated by subtracting the flight control limit from the longitudinal blowback value.

Abstract: A structural connector for connecting a horizontal member to a vertical member comprises an integral body from a single casting having a vertically oriented first sleeve portion and a horizontally oriented second sleeve portion. The first sleeve portion is integral with the second sleeve portion. The first sleeve portion has a tapered bore adapted to be slip fit around a tapered outside surface of the vertical member. The second sleeve has an outside diameter adapted to be slip fit within an interior bore of the horizontal member.