The Boeing Company

Gregory John Hughes

John Scott Finigan

James D Edgerton

Aron Whittemore Dreyfoos

Andres Ramos

A method, apparatus, and system for testing a performance of a device under different load conditions is provided. A load profile to be applied to the device by a linkage system that includes a support member, a load member, and an actuating member is identified. A value for a setting of an actuator of the actuating member is determined based on the load profile. The actuator is operated with the setting having the value determined such that a load is applied to a control surface of the device via the load member. The load applied to the control surface is determined by both the value for the setting of the actuator and a geometry of the linkage system.

Method and system for testing performance of flight control surface systems

There is provided a flight control test simulator system and method. The system has a flight control assembly with at least one actuator and with a flight controller configured to actuate the at least one actuator. The system further has an aerodynamic load simulator coupled to the flight control assembly and configured to adjustably induce a simulated continuous aerodynamic load on the flight control assembly. The aerodynamic load simulator has a continuously adjustable spring rate constant assembly configured to adjust the spring rate constant of the induced simulated continuous aerodynamic load over a range of predetermined flight profiles.

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Gregory John Hughes