Method and system for testing the performance of a flight control surface system

Abstract

To provide a method, apparatus, and system for testing a performance of a device under different load conditions.SOLUTION: A load profile to be applied to a device 102 by a linkage system 204 that includes a support member 206, a load member 208, and an actuating member 210 is identified. A value for a setting of an actuator of the actuating member 210 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 106 of the device 102 via the load member 208. The load applied to the control surface 106 is determined by both the values of the setting of the actuator and a geometry of the linkage system 204.SELECTED DRAWING: Figure 2

Description

[Technical Field]

[0001] The present disclosure relates generally to testing flight control surfaces, and more particularly to methods and systems that use linkage systems in conjunction with actuators to easily, quickly, and accurately test the performance of flight control surface systems under simulated aerodynamic loading conditions. [Background technology]

[0002] Aircraft control surfaces, also referred to as flight control surfaces, are aerodynamic devices that allow an aircraft to steer and control the attitude or orientation of the aircraft. Control surface devices may include, for example, flight control surfaces, mounting structures for attaching the flight control surfaces to portions of the aircraft (e.g., wings, tail surfaces), and movement systems for moving the flight control surfaces. An aircraft may have any number of control surface devices, including, but not limited to, rudder devices, elevator devices, spoiler devices, aileron devices, and flaperon devices.

[0003] In some 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 a flight control computer that responds to sensor inputs driven by pilot controls. Testing is typically required to ensure that an aircraft's control surface devices and one or more control systems meet requirements and comply with regulations.

[0004] Testing may be performed to demonstrate the structural integrity and performance of a control surface device. Generally, testing a control surface device involves subjecting a test device that is, represents, or simulates the control surface device in a laboratory environment to simulated aerodynamic loads.

[0005] However, some currently available test methods and systems require multiple reconfigurations of the test device, the test equipment, or both to test multiple load conditions. Repeated reconfigurations of the test device or the test equipment to test different load conditions can add complexity and be unnecessarily time-consuming. Furthermore, existing test methods and systems may not provide the level of adjustability needed to precisely apply loads at desired magnitudes and directions (e.g., vectors) for various load conditions.

[0006] It would therefore be desirable to have a method and system that takes into account at least some of the above-mentioned issues, as well as possible other issues. Summary of the Invention

[0007] In one illustrative example, an apparatus for testing the performance of a device under different load conditions includes a frame and a linkage system connected to the frame. The linkage system includes a support member movably connected to the frame, an actuation member movably connected to the frame, and a load member movably connected to the actuation member, the support member, and the device. Movement of the actuation member applies a load to the device when the load member is connected to the device.

[0008] In another illustrative example, a system for testing the performance of a device under different load conditions includes a platform and a load application system. The load application system includes a plurality of load systems mounted on the platform. Each of the plurality of load systems includes a frame and a linkage system connected to the frame. The linkage system includes a support member connected to the frame, an actuation member connected to the frame, and a load member movably connected to the actuation member, the support member, and the device. Movement of the actuation member applies a load to the device when the load member is connected to the device.

[0009] In yet another illustrative example, a method for testing the performance of a device under different load conditions is provided. The method includes identifying a load profile to be imposed on the device by a linkage system including a support member, a load member, and an actuation member. The method further includes determining an actuator setting for the actuation member based on the load profile. The method further includes operating the actuator at a setting having the determined value such that a load is imposed on a control surface of the device via the load member. The load imposed on the control surface is determined by both the actuator setting and the geometry of the linkage system.

[0010] These features and functions can be realized independently in various embodiments of the present disclosure and may be combined in yet further embodiments, further details of which can be seen in connection with the following description and drawings.

[0011] The novel features believed characteristic of the illustrative embodiments are set forth in the appended claims. However, the illustrative embodiments, preferred modes of use, and further objects and features thereof will best be understood by reference to the following detailed description of illustrative embodiments of the present disclosure, taken in conjunction with the accompanying drawings. [Brief explanation of the drawings]

[0012] [Figure 1] 1 is an isometric view of a test system in accordance with an exemplary embodiment; [Figure 2] 2 is a side view of the test system of FIG. 1 in accordance with an exemplary embodiment. [Figure 3] 2 is a diagram of the test system of FIG. 1 with the control surface in a test position in accordance with an exemplary embodiment. [Figure 4] 4 is a side view of the test system of FIG. 3 in accordance with an exemplary embodiment. [Figure 5] 2 is a diagram of the test system of FIG. 1 with the control surface in a test position in accordance with an exemplary embodiment. [Figure 6] 6 is a side view of the test system of FIG. 5 in accordance with an exemplary embodiment. [Figure 7] FIG. 7 is an enlarged isometric view of the loading system of FIGS. 1-6 in accordance with an exemplary embodiment. [Figure 8] FIG. 8 is a side view of the linkage system of the load system of FIG. 7 having a neutral configuration in accordance with an exemplary embodiment. [Figure 9] 8A-8C are side views of the linkage system of the load system of FIG. 7 having different configurations according to exemplary embodiments. [Figure 10] FIG. 8 is a side view of the linkage system of the load system of FIG. 7 having another configuration, according to an exemplary embodiment. [Figure 11] 1 is a flowchart of a process for testing the performance of a device under different load conditions, in accordance with an example embodiment. [Figure 12] 1 is a flowchart of a process for testing the performance of a device under different load conditions, in accordance with an example embodiment. [Figure 13] FIG. 10 is an illustration of a process for verifying that a load being applied to a control surface matches a load profile in accordance with an illustrative embodiment; [Figure 14] 10 is a flowchart of a process for testing maximum load limits of a control surface in accordance with an example embodiment. [Figure 15] FIG. 1 is an illustration of an aircraft manufacturing and service method in accordance with an illustrative embodiment. [Figure 16] FIG. 1 is an illustration of a block diagram of an aircraft in accordance with an illustrative embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0013] The exemplary embodiments described below provide methods and systems for accurately applying aerodynamic loads to a test device that is, represents, or simulates a control surface device in a laboratory environment. In particular, complex load profiles can be easily and accurately created in a laboratory environment without requiring reconfiguration of the test equipment or apparatus used to test the test device. Furthermore, adjustments to these load profiles can be remotely controlled. A load profile can include one or more discrete loads applied at one or more corresponding load points along the test device.

[0014] In one exemplary embodiment, the load application system includes one or more load systems used to apply a load profile to the test device. The load profile may include or be based on a normal operating load, a limit load, a yield or ultimate load, one or more other types of loads, or a combination thereof. Each load system includes a geometric linkage system that can continuously apply a highly repeatable and predictable load to a corresponding load point on the test device. The repeatability and predictability provided by the load application system, combined with the ability to remotely adjust the load profile being applied to the test device, allows for continuous and rapid load adjustment. In this manner, the overall time required for testing and the associated complexity may be reduced. In particular, the methods and systems described herein enable flight-equivalent hinge loads and moments to be accurately and easily reproduced within the test device. For example, the desired methods and systems described herein ensure that loads having desired vectors (e.g., desired magnitudes and directions) are applied.

[0015] 1 is an isometric view of a test system 100, according to an exemplary embodiment. Test system 100 is used to test the performance of device 102 under simulated aerodynamic loads. Test system 100 may be used to test device 102 in a lab environment or other type of test environment.

[0016] Test system 100 includes a base structure 103, a platform 104, and a load application system 105. Load application system 105 and base structure 103 are attached to or fixed to platform 104. Platform 104 is used to support device 102. In particular, base structure 103 is used to attach device 102 to platform 104. For example, device 102 may be attached to platform 104 indirectly via base structure 103. In some cases, base structure 103 may be considered part of or integrated into platform 104.

[0017] Device 102, which may also be referred to as a test device, may include any number of components, systems, or combinations thereof. In these illustrative examples, device 102 is a control surface device or a model thereof. In some cases, device 102 is a representation or simulated version of a control surface device.

[0018] The device 102 includes a control surface 106, a mounting structure 108, and a movement system 110. In other examples, the device 102 includes the control surface 106 and either the mounting structure 108 or the movement system 110. In this illustration, the movement system 110 is shown with a dashed line because it is obscured by the mounting structure 108.

[0019] Control surface 106 is a model of or represents a flight control surface of an aircraft. For example, control surface 106 may be a representation of a typical flight control surface or a portion of a flight control surface, which may include a wing trailing edge. In another example, control surface 106 may be an actual flight control surface installed on the aircraft. The flight control surface may take the form of a rudders, elevators, flaperons, ailerons, spoilers (e.g., outboard spoilers, midboard spoilers, inboard spoilers), or some other type of flight control surface. In these illustrative examples, control surface 106 takes the form of elevator 112, and therefore device 102 may be referred to as an elevator device.

[0020] As described above, the device 102 is mounted to the platform 104 via the base structure 103. When the control surface 106 takes the form of an elevator 112 (i.e., the device 102 is an elevator device), the base structure 103 includes or represents a portion of the aircraft to which the elevator 112 will be mounted. For example, the base structure 103 may include, represent, or model a portion of the aircraft's tail surface (e.g., a horizontal stabilizer) to which the elevator 112 will be connected. In other illustrative examples, the base structure 103 may be or represent at least a portion of some other aircraft structure. For example, when the control surface 106 takes the form of an aileron, flaperon, or spoiler, the base structure 103 may be or represent at least a portion of a wing spar. When the control surface 106 takes the form of a rudder, the base structure 103 may be or represent at least a portion of a rudder spar.

[0021] The mounting structure 108 includes one or more components or systems for attaching the control surface 106 to the base structure 103. For example, the mounting structure 108 may include one or more components or systems for attaching the elevator 112 to the horizontal stabilizer of an aircraft. As noted above, the base structure 103 is, and may represent or model, the horizontal stabilizer in these examples. Thus, the mounting structure 108 is used to attach the elevator 112 to the base structure 103 and simulate the attachment of the elevator 112 to the horizontal stabilizer. The mounting structure 108 may include, for example, but is not limited to, at least one of a rib, a plate, a fitting, a hinge device, a fastener device, a beam, a strap, a support component, a pin, a post, a clamping system, or some other type of component.

[0022] Movement system 110 is connected to control surface 106 and is used to move control surface 106 relative to mounting structure 108, and thereby relative to base structure 103. In other illustrative examples, movement system 110 is used to move control surface 106 and mounting structure 108 or a portion of mounting structure 108 relative to base structure 103.

[0023] In these illustrative examples, movement system 110 includes a hydraulic actuator system. In other illustrative examples, movement system 110 may include any number of movement devices. For example, movement system 110 may include at least one of a hydraulic actuator, an electromechanical actuator, a motor device, a track system, a reaction link, an electrohydraulic servo valve, or some other type of movement device. In some cases, movement system 110 may also include one or more other components for connecting movement system 110 to control surface 106, mounting structure 108, or both. For example, movement system 110 may include at least one of a rib, a plate, a fitting, a hinge device, a fastener device, a beam, a strap, a support component, a pin, a post, a clamping system, or some other type of component.

[0024] In these examples, platform 104 used to support device 102 may include any number of beams, barrels, structural components, fastening devices, or combinations thereof. Base structure 103, which may be part of or attached to platform 104, may likewise include any number of beams, barrels, structural components, fastening devices, or combinations thereof. In some illustrative examples, support system 114, which may be part of or attached to platform 104, serves to provide additional support to base structure 103. Support system 114 may include, for example, support 115 and support 117.

[0025] Load-application system 105 of test system 100 includes one or more load systems. For example, load-application system 105 may include multiple load systems 116. In one illustrative example, load systems 116 include load system 118, load system 120, load system 122, and load system 124.

[0026] Each of loading systems 116 is connected to device 102. In particular, in these illustrative examples, each of loading systems 116 is connected to control surface 106 of device 102. Loading systems 116 are used to impart various load profiles to device 102 to test the performance of at least one of control surface 106, mounting structure 108, or movement system 110. For example, loading systems 116 may be used to simulate aerodynamic loads that device 102 would experience during flight.

[0027] The load systems 116 may impart a load profile to the control surface 106, and thereby the device 102, with each load system 116 applying a discrete load to a corresponding load point on the control surface 106. In particular, load system 118, load system 120, load system 122, and load system 124 may apply a discrete load to a corresponding load point 126, a corresponding load point 128, a corresponding load point 130, and a corresponding load point 132, respectively. In some cases, each of the load systems 116 applies the same (within a selected tolerance) discrete load to the control surface 106. In other cases, at least one of the load systems 116 may apply a different load to the control surface 106 than another one of the load systems 116.

[0028] The performance of the device 102 under various aerodynamic loading conditions may be tested in different ways. In one example, the load application system 105 is controlled to apply a selected load profile to the control surface 106. While this selected load profile is applied to the control surface 106 and thereby the device 102, the motion system 110 is used to move the control surface 106 relative to the mounting structure 108, and thereby the base structure 103, through a plurality of test locations. For example, the motion system 110 may rotate or sweep the control surface 106 through a range of test locations while each of the load systems 116 applies a load to the control surface 106 (or applies discrete loads to the control surface 106) based on the selected load profile. In this manner, the performance of the control surface 106 at each of the test locations may be tested under the selected load profile.

[0029] In another example, the load application system 105 is controlled to apply a different load profile at each of a plurality of test locations. For example, at a given test location for the control surface 106, each of the load systems 116 may apply a load to the control surface 106 (or may apply a discrete load to the control surface 106) based on a selected load profile. This loading may be repeated for different load profiles at a given test location (which may be a position angled away from a neutral position for the control surface 106). For example, the discrete load applied by the load system 116 may be incrementally increased until a "blowback" condition is reached in which the control surface 106 is blown back (e.g., downward, upward, or sideways) toward the neutral position. This blowback condition occurs when a maximum load limit is reached. In this manner, a maximum load limit for the control surface 106, the mounting structure 108, the motion system 110, or a combination thereof may be determined for each of a plurality of test locations.

[0030] 1, the control surface 106 is shown in a neutral position 134. In this example, the neutral position 134 is a test position in which the control surface 106 is angled at approximately 0 degrees relative to the base structure 103. Other test positions for the control surface 106 may include positions angled downward relative to the base structure 103, positions angled upward relative to the base structure 103, or both. When the control surface 106 is in the neutral position 134, no load is applied to the control surface 106. When the control surface 106 is moved from the neutral position 134 into a test position, a load (either a tensile load or a compressive load) is applied to the control surface 106.

[0031] In these illustrative examples, test system 100 also includes a remote control unit 136. Remote control unit 136 may be comprised of hardware, software, firmware, or a combination thereof. In one illustrative example, remote control unit 136 includes a computer or processor capable of remotely communicating with load-application system 105. For example, remote control unit 136 may include a computer that communicates wirelessly (e.g., via one or more wireless communication links) with load-application system 105 to remotely control the loads applied to control surface 106 by each of load systems 116.

[0032] Thus, the test system 100 can be used to easily and accurately test the structural integrity of the device 102 against various aerodynamic load conditions. Additionally, the device 102 can be tested to ensure there is no jamming, excessive friction, or excessive deflection when various simulated aerodynamic loads are applied to the device 102. When the device 102 is an aircraft system, the test system 100 can be used to perform these tests based, for example, on maximum load limits expected during nominal operation of the device 102 in the aircraft, loads above normal operating loads, loads for corners or extreme flight conditions, or a combination thereof.

[0033] 2 is a side view of the test system 100 of FIG. 1 in accordance with an exemplary embodiment. In this illustrative example, the support 115 is not shown so that the various components of the load system 124 of the load-application system 105 can be more clearly seen. The load system 124 includes a frame 202 and a linkage system 204. The frame 202 is fixed to the platform 104.

[0034] The linkage system 204 includes a support member 206, a load member 208, and an actuation member 210. The support member 206 and the actuation member 210 are movably connected to the frame 202. The load member 208 is movably connected to the support member 206 and the actuation member 210. Furthermore, the load member 208 is movably connected to the device 102. In particular, the load member 208 is movably connected to the control surface 106 of the device 102.

[0035] Movement of the control surface 106 causes movement of the linkage system 204. In particular, the control surface 106 moving from the neutral position 134 causes movement of the load member 208 connected to the control surface 106, which in turn causes movement of the support member 206 and the actuation member 210 relative to the frame 202. Thus, as the control surface 106 moves, the configuration of the linkage system 204 changes.

[0036] However, if the load member 208 is perpendicular to or parallel to the control surface 106, In contrast right angle Being A linkage system 204 connects the frame 202 and the control surface 106 such that the angle is always maintained within a selected tolerance. The selected tolerance may be, for example, about 3 degrees, about 5 degrees, about 10 degrees, or some other angle range from perpendicular. Maintaining this perpendicular or near perpendicular angle helps reduce or eliminate undesired load vectors being imposed on the control surface 106 outside of the desired load profile to be imposed on the control surface 106. In particular, maintaining this perpendicular or near perpendicular angle helps ensure that the load profile actually imposed on the control surface 106 accurately represents the load profile or loading conditions to be tested.

[0037] As shown, the control surface 106 is in the neutral position 134. When the control surface 106 is in the neutral position 134, the linkage system 204 has a neutral configuration 212. The neutral configuration 212 is defined by the positions of the support member 206, the load member 208, and the actuation member 210 relative to each other and relative to the frame 202. In the neutral configuration 212, no load is applied to the control surface 106, and all loads are reacted through the frame 202.

[0038] As control surface 106 moves from neutral position 134, loading system 124 may apply a load to device 102 via connections between loading members 208 and control surface 106 at corresponding load points 132. In this illustrative example, loading systems 118, 120, and 122 of FIG. 1 are operated simultaneously with and similar to loading system 124, thereby imparting a load profile to device 102.

[0039] Each of loading systems 118, 120, 122, and 124 applies a discrete load to device 102, thereby imposing a load profile on device 102. The discrete load applied to device 102 by a given loading system is a function of the configuration of that loading system's actuator (e.g., the actuator associated with actuating member 210 of loading system 124) and the "geometry" of that loading system's linkage system. The "geometry" of the linkage system includes, for example, the orientation of each of support member 206, load member 208, and actuating member 210 relative to each other and relative to the length of these three members (support member 206, load member 208, and actuating member 210). Furthermore, this "geometry" may include how and where support member 206 and actuating member 210 are connected to frame 202.

[0040] 3 is a diagram of the test system 100 of FIG. 1 with the control surface 106 in a test position, according to an exemplary embodiment. The control surface 106 is shown in test position 300, in which the control surface 106 is angled upward relative to the mounting structure 108 and, thereby, the base structure 103. In this example, the control surface 106 is angled downward approximately 37.5 degrees relative to the neutral position 134 shown in FIGS. 1-2.

[0041] In one illustrative example, once the control surface 106 is in the test position 300, the test system 100 may be used to apply one or more load profiles to the control surface 106. For example, an initial load profile may be applied to the control surface 106. The initial load profile may be an initial load condition of zero load or a predetermined minimum load. The test system 100 may then sweep through one or more additional load profiles, increasing the load applied to the control surface 106 until a maximum load limit is reached.

[0042] 4 is a side view of the test system 100 of FIG. 3 in accordance with an exemplary embodiment. The support 115 is not shown so that the load system 124 can be more clearly seen. When the control surface 106 is in the test position 300, the linkage system 204 has a configuration 400. In configuration 400, the angle between the load member 208 and the control surface 106 is maintained within a selected tolerance of 90 degrees. In other words, the angle between the load member 208 and the control surface 106 is a right angle or nearly a right angle.

[0043] During a load test at the test location 300, the linkage system 204 maintains the configuration 400 until the maximum load limit is reached. The maximum load limit may be considered reached when the linkage system 204 moves out of the configuration 400. For example, the maximum load limit may be reached when the control surface 106 stalls or is overloaded, such that the control surface 106 is pushed back into or toward the neutral position 134 of FIGS. 1-2.

[0044] 5 is a diagram of the test system 100 of FIG. 1 with the control surface 106 in a test position 500. In this illustrative example, the test position 500 is one in which the control surface 106 is angled downward relative to the mounting structure 108 and, thereby, the base structure 103. In this example, the control surface 106 is angled upward approximately 33 degrees relative to the neutral position 134 of FIG. 1.

[0045] Once the control surface 106 is in the test position 500, the test system 100 may be used to apply one or more load profiles to the control surface 106. For example, an initial load profile may be applied to the control surface 106. The initial load profile may be an initial load condition of zero load or minimum load. The test system 100 may then sweep through one or more additional load profiles, increasing the load applied to the control surface 106 until a maximum load limit is reached.

[0046] 6 is a side view of the test system of FIG. 5 in accordance with an exemplary embodiment. Support 115 is not shown so that load system 124 can be more clearly seen. When control surface 106 is in test position 500, linkage system 204 has configuration 600. Even in configuration 600, the angle between load member 208 and control surface 106 is maintained within a selected tolerance of 90 degrees.

[0047] During a load test at test location 500, linkage system 204 maintains configuration 600 until a maximum load limit is reached. The maximum load limit may be considered reached when linkage system 204 moves out of configuration 600. For example, the maximum load limit may be reached when control surface 106 stalls or is overloaded, such that control surface 106 is pushed back into or toward neutral position 134 of FIGS. 1-2 .

[0048] 7 is an enlarged isometric view of the load system 124 of FIGS. 1-6, in accordance with an exemplary embodiment. This view more clearly shows the frame 202 and linkage system 204. The linkage system 204 is shown having a neutral configuration 212 that corresponds to the neutral position 134 of the control surface 106 as shown in FIGS. 1-2.

[0049] Frame 202 has a first side 700 and a second side 701, which are on opposite sides of frame 202. Frame 202 may be a monolithic integrated structure or may be comprised of two or more components connected together. Frame 202 includes frame portion 702 on first side 700 and frame portion 703 on second side 701. Frame 202 further includes frame portion 704 connecting frame portion 702 and frame portion 703. In one illustrative example, frame portion 702 and frame portion 703 are vertical portions, and frame portion 704 is a horizontal portion connecting those portions.

[0050] Linkage system 204 is connected to frame 202 via joint 705 and joint 706. Support member 206, load member 208, and actuation member 210 of linkage system 204 are connected together via joint 708. Joint 708 may include one or more joints. For example, joint 708 may be "multijoint." Joint 705, joint 706, and the one or more joints, including joint 708, each provide at least one rotational degree of freedom.

[0051] Support member 206 of linkage system 204 is movably connected to frame portion 702 at first side 700 via joint 705. Joint 705 can be a hinge-type joint or a rotatable joint. In this illustrative example, joint 705 provides three rotational degrees of freedom (e.g., via a spherical bearing). Actuating member 210 is movably connected to frame portion 703 at second side 701 of frame 202 via joint 706. Thus, support member 206 and actuating member 210 are connected to opposite sides of frame 202. Similar to joint 705, joint 706 can be a hinge-type joint or a rotatable joint.

[0052] The load member 208 is movably connected to both the support member 206 and the actuation member 210 via a joint 708. In this example, the joint 708 may be a multi-joint including a hinge-type joint and a spherical bearing. In this illustrative example, the joint 705 provides one rotational degree of freedom to the load member 208. The load member 208 is also associated with a connector 710, which is used to connect the load member 208 to the control surface 106 of FIGS. 1-6 at a joint (not shown) that provides at least one rotational degree of freedom. This joint may be yet another hinge-type joint or a rotatable joint. For example, the joint may include a spherical bearing. Depending on the embodiment, the connector 710 may be integrated as part of the load member 208 or as a separate component connected to the load member 208.

[0053] In one or more examples, the load member 208 is associated with a load measuring device 712. The load measuring device 712 may include, for example, without limitation, at least one of a load cell, a load pin, a strain gauge, or some other type of device for measuring load or strain. The load measuring device 712 may be associated with the load member 208 by being indirectly or directly attached, secured, or connected to the load member 208. Alternatively, the load measuring device 712 may be integrated as part of the load member 208. The load measuring device 712 is used to measure the load applied to the control surface 106 by the load member 208.

[0054] The actuation member 210 is associated with an actuator 714. The actuator 714 may be associated with the actuation member 210 by being indirectly or directly attached, fixed or connected to the actuation member 210. Alternatively, the actuator 714 may be associated with the actuation member 210 by being integrated as part of the actuation member 210.

[0055] In this illustrative example, actuator 714 is a hydraulic actuator. In other examples, actuator 714 may be an electric actuator or some other type of actuator. Actuator 714 may be operated via a single setting (or parameter). When actuator 714 takes the form of a hydraulic actuator, this setting may be a pressure setting (i.e., a hydraulic pressure setting). This pressure setting may be controlled to control the load applied to control surface 106 by load member 208. The actual load applied to control surface 106 is a function of the pressure setting and the geometry of linkage system 204.

[0056] Thus, varying the pressure setting of the actuator 714 without varying the geometry of the linkage system 204 (i.e., without moving the control surface 106 and thereby moving the linkage system 204) may change the discrete load applied to the control surface 106 by the load member 208. Similarly, by having two different values ​​for the pressure setting of the actuator 714, a constant load may be maintained for two different positions of the control surface 106 (i.e., two different geometries of the linkage system 204). As another example, the load applied to the control surface 106 may be changed by moving the control surface 106, thereby changing the geometry of the linkage system 204, but not the pressure setting of the actuator 714.

[0057] Linkage system 204 can use a single pressure setting of actuator 714 to impart a desired load profile to corresponding load points on control surface 106. Specifically, the lengths of support member 206, load member 208, and actuation member 210, and the locations of joints 705 and 706, can be selected such that a single pressure setting of actuator 714 can be used to apply an appropriate load to control surface 106 based on the selected load profile. Based on the selected load profile, the pressure setting required to apply the appropriate load to a particular geometry of linkage system 204 can be determined via mathematical analysis tools.

[0058] The settings for the actuators 714 may be adjusted physically at the actuators 714 or may be controlled remotely. For example, the remote control unit 136 of FIG. 1 may be used to control the pressure settings of the actuators 714. The loads exerted by the load members 208 based on the pressure settings of the actuators 714 simulate the aerodynamic loads on the control surface 106.

[0059] FIG. 8 is a side view of linkage system 204 of load system 124 of FIG. 7 having a neutral configuration, according to an exemplary embodiment. In particular, linkage system 204 is illustrated in neutral configuration 212 of FIGS. 2 and 7. Connector 800 is used to connect support member 206 to frame portion 702 of frame 202 of FIG. 7 to form joint 705. Connector 800 can be part of support member 206 or a separate component connected to support member 206. Connector 802 is used to connect actuating member 210 to frame portion 703 of frame 202 of FIG. 7 to form joint 706. Furthermore, connector 802 can be part of actuating member 210 or a separate component connected to actuating member 210.

[0060] 9 is a side view of linkage system 204 of load system 124 having different configurations, according to an exemplary embodiment. In particular, linkage system 204 having configuration 400 of FIG. 4 is illustrated.

[0061] 10 is a side view of linkage system 204 of load system 124 having yet another configuration, according to an exemplary embodiment. In particular, linkage system 204 having configuration 600 of FIG. 6 is illustrated.

[0062] The illustrations of test system 100 and the various components of test system 100 in Figures 1-10 are not meant to suggest physical or architectural limitations to the manner in which illustrative embodiments may be implemented. Other components in addition to or in place of the illustrated components may be used. Some components may be optional.

[0063] 11 is a flowchart of a process for testing the performance of a device under different load conditions according to an example embodiment. The process 1100 shown in FIG. 11 can be performed, for example, using the test system 100 described in FIGS. 1-10.

[0064] Process 1100 may begin by identifying (step 1102) a load profile to be imposed on a device by a linkage system including a support member, a load member, and an actuation member. The device may be, for example, device 102 of FIG. 1. In some illustrative examples, the device includes a control surface, such as a rudder, elevator, flaperon, aileron, spoiler, or some other type of control surface. The linkage system may be part of a load application system, such as, for example, load application system 105 of FIG. 1. The load application system may include one or more load systems, each including a linkage system, such as, for example, linkage system 204 of FIG. 2.

[0065] Process 1100 further includes determining a setting for an actuator associated with the actuating member based on the load profile (step 1104). When the actuator is a hydraulic actuator, step 1104 includes determining a pressure setting for the hydraulic actuator. The pressure setting can be controlled manually or remotely.

[0066] Process 1100 further includes operating the actuator at a setting having a determined value such that a load is applied to a control surface of the device via a load member of the linkage system, the load applied to the control surface being determined by the actuator setting and the geometry of the linkage system (step 1106), with the process then terminating. In step 1106, operating the actuator may include, for example, supplying energy to the actuator at a value determined for the actuator setting. The geometry of the linkage system includes how the actuating member, support member, and linkage system are oriented relative to each other and relative to the lengths of these three members. Furthermore, the geometry may include how the actuating member and support member are connected to the frame of the linkage system (i.e., the locations on the frame to which the actuating member is connected and the locations on the frame to which the support member is connected).

[0067] Step 1106 is performed to apply a resistive tensile load to the control surface while it is in a test position angled away from the frame. Step 1108 is performed to apply a resistive tensile load to the control surface while it is in a test position angled towards the frame. Resistive Compression Load is applied to the control surface.

[0068] In some illustrative examples, steps 1102-1106 may be repeated multiple times for different load profiles while the control surface of the device is in a given test position. In other illustrative examples, the control surface may be moved through multiple test positions while a load is applied to the control surface.

[0069] 12 is a flowchart of a process for testing the performance of a device under different load conditions, according to an example embodiment. The process 1200 shown in FIG. 12 can be performed, for example, using the test system 100 described in FIGS. 1-10.

[0070] Process 1200 may begin by identifying a set of test conditions (step 1202) for testing a control surface using a set of load systems. As used herein, a "set" of items may include one or more items. Thus, a set of test conditions may be one or more test conditions, and a set of load systems may be one or more load systems. In these illustrative examples, the test conditions are a combination of a test location for the control surface and a load profile for the control surface.

[0071] The test positions can be, for example, angular deflections of the control surface. In one illustrative example, the set of test positions can include a sweep of positions between maximum deflection in one direction (e.g., −30 degrees from the neutral position) and maximum deflection in another direction (e.g., +30 degrees from the neutral position). In another example, the maximum deflection in either direction can be between about 10 degrees and about 60 degrees away from the neutral position.

[0072] In these illustrative examples, the load profile includes a set of discrete loads applied at a corresponding set of load points on the control surface. The set of discrete loads would be applied to the control surface by a set of load systems in a load application system, such as load application system 105 of FIG. 1. Each load system in the load application system may be implemented in a manner similar to load system 124 described in FIGS. 1-6. Each load system includes a frame and a linkage system. The linkage system for each load system may be implemented in a manner similar to linkage system 204 described in FIGS. 7-10. As one example, each linkage system includes an actuating member connected to the frame, a support member connected to the frame, and a load member connected to the actuating member, the support member, and the control surface.

[0073] Thus, a load profile may include a load applied at a corresponding load point on the control surface by each loading system of a set of loading systems. In these illustrative examples, each loading system may be configured to apply the same load to the control surface for a given load profile. In other cases, one loading system may be configured to apply a different load than at least one other loading system.

[0074] In step 1202, each test condition is a unique combination of test location and load profile. For example, two test conditions may have the same test location but two different load profiles. In another example, two test conditions may have the same load profile but two different test locations.

[0075] Process 1200 then includes determining, for each identified set of test conditions, actuator settings for each of a set of loading systems (step 1204). In step 1204, for each test condition, actuator settings are determined based on the load profile for that test condition. This determination is made based on the geometry of the linkage system in each loading system. For each loading system, the actuator is part of the actuating member of that loading system's linkage system.

[0076] Step 1204 considers that the actual load profile applied to the control surface is a function of both the actuator settings and the geometry of the linkage system. The linkage system geometry varies at different locations on the control surface. In other words, the orientation of the load members, actuation members, and support members of the linkage system relative to one another varies at different locations on the control surface. Thus, the actuator settings of a particular load system for a particular load profile (and thus a particular test location) can be determined (e.g., calculated using mathematical analysis tools) based on the loads applied to the control surface by the load system according to the load profile and the known linkage system geometry at the test location according to that load profile. In some illustrative examples, the actuator settings can be constant for multiple different load profiles.

[0077] A test condition is then selected from the set of test conditions (step 1206). A control surface is positioned according to a test location for the selected test condition (step 1208). In these illustrative examples, step 1208 includes moving the control surface to deflect an edge (e.g., a wing trailing edge) of the control surface. In some cases, if the control surface is already in a test location, step 1208 may be performed by simply leaving the control surface in its current position.

[0078] Next, the actuators of each loading system are energized using the actuator settings corresponding to the load profile of the selected test condition to apply a load profile to the control surface (step 1210). In step 1210, each loading system applies a discrete load at a corresponding load point on the control surface. As noted above, the discrete load applied to the control surface is a function of the actuator settings and the geometry of the loading system's linkage system.

[0079] In some cases, step 1210 involves leaving the actuator setting unchanged. In other cases, step 1210 involves changing the actuator setting. For example, when the actuator is a hydraulic actuator, step 1210 may be performed by increasing or decreasing the pressure setting on the hydraulic actuator.

[0080] Next, process 1200 includes verifying that the discrete loads being applied to the control surfaces by each load system match the load profile of the selected test condition within a selected tolerance (step 1212). A determination is then made as to whether the current test condition is the final test condition (step 1214). If the current test condition is the final test condition, process 1200 ends. If not, process 1200 returns to step 1206 above.

[0081] Thus, as illustrated by process 1200, a control surface may be tested under various test conditions using a single setting for a single actuator in each loading system of a set of loading systems. For example, the control surface may be swept through a range of positions under various loading conditions without having to adjust the configuration of a large or complex installation.

[0082] 13 is a diagram of a process for verifying that a load being applied to a control surface matches a load profile, according to an example embodiment. Process 1300 may be an example of one way in which step 1212 of FIG. 12 may be performed. In some cases, process 1300 may be implemented, at least in part, using a computer that is part of a test system, such as test system 100 described in FIGS. 1-10.

[0083] Process 1300 includes generating a measurement of a load being applied to a control surface by a loading system at a load point (step 1302). Step 1302 may be performed, for example, using a load measuring device associated with a load member of the loading system's linkage system. The load measuring device may include, for example, but not limited to, at least one of a load cell, a load pin, a strain gauge, or some other type of device for measuring load or strain. A determination is then made (step 1304) whether the measured load is within a selected tolerance of the load to be applied at the load point based on the selected load profile. If the measured load is within the selected tolerance of the load to be applied, the process ends. Otherwise, settings for the loading system's actuators are adjusted (step 1306), and the process then returns to step 1302 above.

[0084] 14 is a flowchart of a process for testing the maximum load limits of a control surface, according to an example embodiment. Process 1400 can be performed using a test system, such as test system 100 shown in FIGS. 1-10, to test the maximum load limits of a control surface.

[0085] Process 1400 may begin by moving the control surface into a test position (step 1402), which is angled away from the neutral position of the control surface. The actuators of each of a set of loading systems are energized to impart a load profile to the control surface (step 1404). In other illustrative examples, step 1404 may be performed before moving the control surface into the test position.

[0086] A determination is then made as to whether the control surface has reached its maximum load limit (step 1406). In step 1406, the control surface may be considered to have reached its maximum load limit if it has blown back toward the neutral position (e.g., blown downward, upward, or to the side). If the control surface has reached its maximum load limit, the process ends.

[0087] If not, the energy supply to the actuators of each of the set of loading systems is adjusted to change the load profile applied to the control surface (step 1408), and the process then returns to step 1406 above. For step 1408, in these examples, the load profile may be adjusted such that the load being applied to the control surface by each of the set of loading systems increases. As one particular example, when the actuators of each loading system are hydraulic actuators, the pressure setpoint of the actuators may be increased.

[0088] An exemplary embodiment of the present disclosure may be described with reference to aircraft manufacturing and service method 1500 shown in Figure 15 and aircraft 1600 shown in Figure 16. Referring initially to Figure 15, an aircraft manufacturing and service method is illustrated in accordance with an exemplary embodiment. During pre-production, aircraft manufacturing and service method 1500 includes specification and design 1502 of aircraft 1600 in Figure 16 and material procurement 1504.

[0089] During production, component and subassembly manufacturing 1506 and system integration 1508 of the aircraft 1600 of Figure 16 takes place. The aircraft 1600 of Figure 16 then undergoes certification and delivery 1510 before being placed into service 1512. While in customer service 1512, the aircraft 1600 of Figure 16 is scheduled for routine maintenance and service 1514, which may include modification, reconfiguration, refurbishment, and other maintenance and service.

[0090] Each process of aircraft manufacturing and service method 1500 may be performed or carried out by a system integrator, a third party, and / or an operator. In these examples, the operator may be a customer. As used herein, a system integrator may include, but is not limited to, any number of aircraft manufacturers and major system subcontractors; a third party may include, but is not limited to, any number of vendors, subcontractors, and suppliers; and an operator may be an airline, a leasing company, a military organization, a service organization, etc.

[0091] Referring now to Figure 16, a diagram of an aircraft is shown in which illustrative embodiments may be implemented. In this example, aircraft 1600 is manufactured by aircraft manufacturing and service method 1500 in Figure 15 and may include an airframe 1602 having a number of systems 1604 and an interior 1606. Examples of systems 1604 include, but are not limited to, one or more of propulsion system 1608, electrical system 1610, hydraulic system 1612, environmental system 1614, and flight control system(s) 1616. Any number of other systems may be included. While an aerospace example is shown, various illustrative embodiments may be applied to other industries, such as the automotive industry.

[0092] Apparatus and methods embodied herein may be employed during at least one stage of aircraft manufacturing and service method 1500 of Figure 15. In particular, test system 100 of Figures 1-10 may be used to test flight control surfaces during one or more of the stages of aircraft manufacturing and service method 1500. For example, without limitation, test system 100 may be used during at least one of specification and design 1502, component and subassembly manufacturing 1506, system integration 1508, certification and delivery 1510, routine maintenance and service 1514, or some other stage of aircraft manufacturing and service method 1500. Still further, test system 100 may be used to test device 102 of Figure 1, which may be a component of aircraft 1600 or a representation of a component thereof. For example, device 102 may be considered part of flight control system(s) 1616. In some cases, device 102 may be one of systems 1604 of aircraft 1600 controlled by or commanded by flight control system(s) 1616 .

[0093] In one illustrative example, components or subassemblies produced in component and subassembly manufacturing 1506 in Figure 15 may be fabricated or manufactured in a similar manner to components or subassemblies produced while aircraft 1600 in service 1512 in Figure 15 . In yet another example, one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during production stages, such as component and subassembly manufacturing 1506 and system integration 1508 in Figure 15 . One or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during aircraft 1600 in service 1512 and / or during maintenance and service 1514 in Figure 15 . The use of several different illustrative embodiments facilitates significant efficiencies and / or significant cost savings in the assembly of aircraft 1600.

[0094] The flowcharts and block diagrams in the various depicted embodiments illustrate the architecture, functionality, and operation of some possible implementations of apparatuses and methods in the illustrative embodiments. As such, each block in the flowcharts or block diagrams may represent a module, a segment, a function, and / or a portion of an operation or step.

[0095] The flowcharts and block diagrams in the various depicted embodiments illustrate the architecture, functionality, and operation of some possible implementations of apparatuses and methods in example embodiments. For example, in some cases, two blocks shown in succession may be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending on the functionality involved. Also, other blocks may be added in addition to the blocks shown in a flowchart or block diagram. As used herein, the phrase "at least one of" used in connection with listed items means that various combinations of one or more of the listed items may be used, and that only one of the listed items may be required. An item may be a specific object, article, step, operation, process, or category. In other words, "at least one of" means that any combination of items or some items from the list may be used, but not all of the listed items may be required. For example, without limitation, "at least one of item A, item B, or item C" or "at least one of item A, item B, and item C" may mean, e.g., "item A," "item A and item B," "item B," "item A, item B, and item C," "item B and item C," or "item A and item C." In some cases, "at least one of item A, item B, or item C" or "at least one of item A, item B, and item C" may mean, without limitation, "two item A, one item B, and ten item C," "four item B and seven item C," or some other suitable combination.

[0096] Clause 1. An apparatus for testing the performance of a device (102) under different load conditions, comprising: A frame (202); a linkage system (204) connected to the frame (202); and a linkage system (204) a support member (206) movably connected to the frame (202); an actuating member (210) movably connected to the frame (202); a load member (208) movably connected to the actuation member (210), the support member (206), and the device (102); wherein operation of the actuation member (210) applies a load to the device (102) when the load member (208) is connected to the device (102).

[0097] Clause 2. The apparatus of clause 1, wherein a load member (208) is connected to the device (102) such that movement of the device (102) causes corresponding movement of the linkage system (204).

[0098] Clause 3. The load member (208) 3. The apparatus of clause 1 or 2, comprising a load measuring device (712) for measuring the load applied to the device (102) by the load member (208).

[0099] Clause 4. An apparatus described in any one of clauses 1 to 3, wherein the actuating member (210), the support member (206), and the load member (208) are movably connected together via joints, and the actuating member (210) and the support member (206) are connected to opposite sides of the frame (202).

[0100] Clause 5. An apparatus described in any one of clauses 1 to 4, wherein the support member (206) is movably connected to a first side of the frame (202) at a first joint (705) and the actuating member (210) is movably connected to a second side of the frame (202) at a second joint (706).

[0101] Clause 6. The actuating member (210) and wherein a first position of the first joint (705) relative to the frame (202) and a second position of the second joint (706) relative to the frame (202) are selected such that controlling a single pressure setting on the actuator (714) is sufficient to apply a load to the device (102) based on a selected load profile.

[0102] Clause 7. The load member (208) is attached to the load member (208) at any test position of the device (102). In contrast Right angles Kotono Selected Tolerance error The apparatus described in clause 5, wherein the first length of the support member (206), the second length of the load member (208), the third length of the actuating member (210), the first position of the first joint (705) relative to the frame (202), and the second position of the second joint (706) relative to the frame (202) are selected to reliably maintain the angle within the frame (202).

[0103] Clause 8. The actuating member (210) Actuators(714) 8. The apparatus of any one of clauses 1 to 7, comprising:

[0104] Article 9. The apparatus of clause 8, further comprising a remote control unit (136) in communication with the hydraulic actuator (714), the remote control unit (136) controlling a pressure setting of the hydraulic actuator (714) to control the load applied by the load member (208) to the control surface (106) of the device (102).

[0105] Article 10. a platform (102) on which a frame (202) is mounted; a base structure (103) attached to the platform (102), the base structure (103) on which the device (102) is attached; 10. The apparatus of any one of clauses 1 to 9, further comprising:

[0106] Article 11. A load application system (105) comprising a plurality of load systems (116), wherein a frame (202) and a linkage system (204) form the load systems (118, 120, 122, 124) of the plurality of load systems (116). 11. The apparatus of clause 10, further comprising:

[0107] Clause 12. An apparatus according to any one of clauses 1 to 11, wherein the device (102) comprises a control surface (106), a movement system (110), and a mounting structure (108).

[0108] Clause 13. A system (100) for testing the performance of a device (102) under different load conditions, comprising: a platform (102); a load application system (105) including a plurality of load systems (116) attached to the platform (102); each of the plurality of load systems (116) A frame (202); a linkage system (204) connected to the frame (202); and a linkage system (204) a support member (206) connected to the frame (202); an actuating member (210) connected to the frame (202); a load member (208) movably connected to the actuation member (210), the support member (206), and the device (102); wherein operation of the actuation member (210) applies a load to the device (102) when the load member (208) is connected to the device (102).

[0109] Clause 14. A method for testing the performance of a device (102) under different load conditions, comprising: Identifying (1102) a load profile to be applied to the device (102) by a linkage system (204) including a support member (206), a load member (208), and an actuation member (210); determining (1104) a setting for an actuator (714) of the actuating member (210) based on the load profile; operating (1106) the actuator (714) at a setting having a determined value such that a load is applied to the control surface (106) of the device (102) via the load member (208); wherein the load applied to the control surface (106) is determined by values ​​of both the actuator (714) setting and the linkage system (204) geometry.

[0110] Article 15. measuring (1212) the load applied to the control surface (106) using the load measuring device (712) of the linkage system (204) to verify that the load applied to the device (102) matches the identified load profile within a selected tolerance; 15. The method of clause 14, further comprising:

[0111] Clause 16. Operating (1106) the actuator (714) energizing (1210) the actuator (714) based on the determined value for the setting; 16. The method of claim 14 or 15, comprising: a) transferring a load from the actuating member (210) to the control surface (106) via a load member (208).

[0112] Clause 17. The actuator (714) is a hydraulic actuator, and determining the setpoint (1104) comprises: Calculating pressure settings for hydraulic actuators based on load profiles 17. The method according to clause 16, comprising:

[0113] Clause 18. Operating (1106) the actuator (714) Remotely controlling the settings of the actuator (714) 18. The method of any one of clauses 14 to 17, comprising:

[0114] Article 19. moving (1402) the control surface (106) of the device (102) into a test position before applying a load to the control surface (106); 19. The method of any one of clauses 14 to 18, further comprising:

[0115] Article 20. Determining the set value Calculating actuator (714) settings based on the identified load profile and linkage system (204) geometry. 20. The method of any one of clauses 14 to 19, comprising:

[0116] Article 21. moving (1402) the control surface (106) of the device (102) into a test position, thereby moving the linkage system (204) connected to the control surface (106) into a configuration that maintains a right angle between the load member (208) of the linkage system (204) and the control surface (106) within a selected tolerance; 21. The method of any one of clauses 14 to 20, further comprising:

[0117] Article 22. Moving (1402) the control surface (106) of the device (102) from a neutral position into a test position. 22. The method of any one of clauses 14 to 21, further comprising:

[0118] Clause 23. A linkage system (204) is connected to the frame (202) and operates the actuator (714) (1106); applying a resistive tensile load to the control surface (106) of the device (102) as a test position for the control surface (106) is angled away from the frame (202); 23. The method of claim 22, comprising:

[0119] Clause 24. A linkage system (204) is connected to the frame (202) and operates the actuator (714) (1106); Resistance is applied to the control surface (106) of the device (102) when the test position for the control surface (106) is angled in a direction toward the frame (202). Compression Load To put 23. The method of claim 22, comprising:

[0120] The description of various exemplary embodiments has been presented for purposes of illustration and description and is not intended to be exhaustive or to limit the embodiments to the disclosed form. Numerous modifications and variations will be apparent to those skilled in the art. Furthermore, various exemplary embodiments may offer different features as compared to other preferred embodiments. The selected embodiment or embodiments have been chosen and described to provide the best explanation of the principles and practical applications of the embodiments and to enable others skilled in the art to understand the disclosure of the various embodiments with various modifications suitable for the particular applications envisioned.

Claims

1. 1. An apparatus for testing the performance of a device (102) under different load conditions, comprising: A frame (202); a linkage system (204) connected to the frame (202); wherein the linkage system (204) a support member (206) having a first end movably connected to the frame (202); an actuating member (210) having a first end movably connected to the frame (202); a load member (208) having a first end movably connected to the second end of the actuating member (210) and the second end of the support member (206), and a second end configured to be movably connected to the device (102); Equipped with the second end of the actuating member (210), the second end of the support member (206), and the first end of the load member (208) are movably connected together via a joint; The apparatus wherein movement of the actuating member (210) applies a load to the device (102) when the load member (208) is connected to the device (102).

2. 2. The apparatus of claim 1, wherein the load member is connected to the device such that movement of the device causes a corresponding movement of the linkage system, or the load member comprises a load measuring device for measuring a load applied to the device by the load member.

3. An apparatus as described in claim 1 or 2, wherein the support member (206) is movably connected to a first side of the frame (202) at a first joint (705), and the actuating member (210) is movably connected to a second side of the frame (202) at a second joint (706).

4. the actuating member (210) comprises an actuator (714), and a first position of the first joint (705) relative to the frame (202) and a second position of the second joint (706) relative to the frame (202) are selected such that controlling a single pressure setting on the actuator (714) is sufficient to load the device (102) based on a selected load profile; or 4. The apparatus of claim 3, wherein the first length of the support member (206), the second length of the load member (208), the third length of the actuating member (210), the first position of the first joint (705) relative to the frame (202), and the second position of the second joint (706) relative to the frame (202) are selected to ensure that the load member (208) maintains an angle that is within a selected tolerance of being perpendicular to the load member (208) at any test position of the device (102).

5. The actuating member (210) Hydraulic Actuator (714) 5. The apparatus of claim 1, further comprising a remote control unit (136) in communication with the hydraulic actuator (714), the remote control unit (136) controlling a pressure setting of the hydraulic actuator (714) to control a load applied by the load member (208) to a control surface (106) of the device (102).

6. a platform (102) to which the frame (202) is attached; a base structure (103) attached to the platform (102), the base structure (103) on which the device (102) is attached; a load application system (105) comprising a plurality of load systems (116), wherein the frame (202) and the linkage system (204) form load systems (118, 120, 122, 124) of the plurality of load systems (116); The apparatus of claim 1 , further comprising:

7. The apparatus of any one of claims 1 to 6, wherein the device (102) comprises a control surface (106), a movement system (110), and a mounting structure (108).

8. A system (100) for testing the performance of a device (102) under different load conditions, comprising: a platform (102); a load application system (105) comprising a plurality of load systems (116) attached to the platform (102); each of the plurality of load systems (116) A frame (202); a linkage system (204) connected to the frame (202); wherein the linkage system (204) a support member (206) having a first end connected to the frame (202); an actuating member (210) having a first end connected to the frame (202); a load member (208) having a first end movably connected to the second end of the actuating member (210) and the second end of the support member (206), and a second end configured to be movably connected to the device (102); Equipped with the second end of the actuating member (210), the second end of the support member (206), and the first end of the load member (208) are movably connected together via a joint; A system (100) in which movement of the actuating member (210) applies a load to the device (102) when the load member (208) is connected to the device (102).

9. A method for testing the performance of a device (102) under different load conditions, comprising: identifying (1102) a load profile to be applied to the device (102) by a linkage system (204) including a support member (206), a load member (208), and an actuation member (210), each of which has one end movably connected together via a joint, the other end of the load member (208) being movably connected to the device (102); determining (1104) a value for a setting of an actuator (714) of the actuating member (210) based on the load profile; operating (1106) the actuator (714) at the setting having the determined value such that a load is applied to the control surface (106) of the device (102) via the load member (208); wherein the load applied to the control surface (106) is determined by both the value of the setting of the actuator (714) and the geometry of the linkage system (204).

10. measuring (1212) the load applied to the control surface (106) using a load measuring device (712) of the linkage system (204) to verify that the load applied to the device (102) matches the identified load profile within a selected tolerance.

10. The method of claim 9, further comprising: operating the actuator based on the determined value for the setting; and wherein operating the actuator comprises providing energy to the actuator based on the determined value for the setting, and wherein the load is transmitted from the actuating member to the control surface via the load member.

11. the actuator (714) is a hydraulic actuator, and determining (1104) the value of the setting comprises: calculating a pressure setting for the hydraulic actuator based on the load profile; The method of claim 10, comprising:

12. operating (1106) the actuator (714) includes remotely controlling the settings of the actuator (714); or The method further includes moving (1402) the control surface (106) of the device (102) into a test position before applying the load to the control surface (106).

12. The method according to any one of claims 9 to 11.

13. determining the value of the setting includes calculating the value of the setting of the actuator (714) based on the identified load profile and the geometry of the linkage system (204); or the method further comprising moving (1402) the control surface (106) of the device (102) into a test position, thereby moving the linkage system (204) connected to the control surface (106) into a configuration in which an angle between a load member (208) of the linkage system (204) and the control surface (106) maintains a right angle within a selected tolerance.

13. The method according to any one of claims 9 to 12.

14. Moving the control surface (106) of the device (102) from a neutral position into a test position (1402).

14. The method of any one of claims 9 to 13, further comprising:

15. The linkage system (204) is connected to the frame (202), and operating the actuator (714) (1106) applying a resistive tensile load to the control surface (106) of the device (102) when the test position relative to the control surface (106) is angled away from the frame (202); or applying a resistive compressive load to the control surface (106) of the device (102) when the test position relative to the control surface (106) is angled in a direction toward the frame (202); 15. The method of claim 14, comprising:

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