FIELD

This disclosure relates generally to testing flight control surfaces and, more particularly, to methods and systems that use linkage systems with actuators to easily, quickly, and accurately test the performance of flight control surface systems under simulated aerodynamic load conditions.

BACKGROUND

Aircraft control surfaces, also referred to as flight control surfaces, are aerodynamic devices that allow an aircraft to be maneuvered to control the attitude or (orientation of the aircraft. A control surface device may include, for example, the flight control surface, an attachment structure for attaching the flight control surface to a portion of the aircraft (e.g., a wing, a tail), and a movement system for moving the flight control surface. An aircraft may have any number of control surface devices such as, but not limited to, rudder devices, elevator devices, spoiler devices, aileron devices, and flaperon devices.

With certain types of aircraft, control surface devices are commanded by a control system that is not mechanically connected to the control surface devices. This control system (e.g., a fly by wire control system) may use flight control computers that respond to sensor input driven by pilot controls. Typically, testing is required to ensure that the control surface devices and one or more control systems on an aircraft meet requirements and comply with regulations.

Testing may be performed to demonstrate the structural integrity and performance of the control surface device. Generally, testing a control surface device includes applying simulated aerodynamic loads to a test device that is, represents, or simulates a control surface device in a lab environment.

But some currently available testing methods and systems require multiple reconfigurations of the test device, testing equipment, or both in order to test multiple load conditions. Reconfiguring a test device or testing equipment repeatedly to test different load conditions may involve more complexity and take more time than desired. Further, existing testing methods and systems may not provide the level of adjustability needed to accurately apply loads with the desired magnitudes and directions (e.g., vectors) for a variety of load conditions.

Therefore, it would be desirable to have a method and system that take into account at least some of the issues discussed above, as well as other possible issues.

SUMMARY

In one illustrative example, an apparatus for testing a performance of a device under different load conditions includes a frame and a linkage system connected to the frame. The linkage system comprises a support member movably connected to the frame; an actuating member movably connected to the frame; and a load member that is movably connected to the actuating member, the support member, and the device. Operation of the actuating member when the load member is connected to the device loads the device.

In another illustrative example, a system for testing a performance of a device under different load conditions comprises a platform and a load application system. The load application system comprises a plurality of load systems attached to the platform. Each of the plurality of load systems comprises a frame and a linkage system connected to the frame. The linkage system comprises a support member connected to the frame; an actuating member connected to the frame; and a load member that is movably connected to the actuating member, the support member, and the device. Operation of the actuating member when the load member is connected to the device loads the device.

In yet another illustrative example, a method for testing a performance of a device under different load conditions is provided. The method includes identifying 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. The method further includes determining a value for a setting of an actuator of the actuating member based on the load profile. The method further includes operating the actuator 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.

The features and functions can be achieved independently in various embodiments of the present disclosure or may be combined in yet other embodiments in which further details can be seen with reference to the following description and drawings.

