The Boeing Company

John Scott Finigan

Gregory John Hughes

Norman Englund

James D Edgerton

Andres Ramos

Aron Whittemore Dreyfoos

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.

Flight control test simulator system and method

A force compliant mechanism () for a force control system () includes a housing (). A force compliant volute spring member () that has an input end () and an output end () is disposed within the housing (). A force actuator input shaft () operates in response to a force induced thereon. An output shaft () is coupled to the output end () and to a test object (). A force transducer () is in operative coupling with the force actuator input shaft () and generates a force signal in response to the induced force. A method of reducing force transients and increasing stability within a force control system () includes applying a force on a test object (). A force actuator () is decoupled from the test object (). The overall stiffness of the force control system is reduced and dynamic energy is absorbed via a force compliant member () coupled to the test object () and the force actuator ().

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Edgewood, WA, United States of America

John Scott Finigan