Method and system for testing performance of 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 generally relates to testing flight control surfaces, and more specifically, to methods and systems for using a linkage system with an actuator to easily, quickly, and accurately test the performance of a flight control surface system under simulated aerodynamic load conditions.

Background Art

[0002] The control surfaces of an aircraft, also referred to as flight control surfaces, are aerodynamic devices that enable the aircraft to be maneuvered to control its attitude or orientation. The control surface device can include, for example, a flight control surface, an attachment structure for attaching the flight control surface to a part of the aircraft (e.g., a wing, a tail surface), and a movement system for moving the flight control surface. An aircraft can have any number of control surface devices, including, but not limited to, rudder devices, elevator devices, spoiler devices, flap devices, and flaperon devices.

[0003] For certain aircraft, the control surface device is commanded by a control system that is not mechanically connected to the control surface device. This control system (e.g., a fly-by-wire control system) can use a flight control computer that responds to sensor inputs driven by pilot control. Typically, testing is required to ensure that the control surface devices of an aircraft and one or more control systems meet requirements and comply with regulations.

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

[0005] However, some currently available test methods and systems require the test device, test equipment, or both to be reconfigured multiple times to test multiple load conditions. Repeatedly reconfiguring the test device or equipment to test different load conditions increases complexity and can be unnecessarily time-consuming. Furthermore, existing test methods and systems may not provide the necessary level of adjustability to accurately apply loads of the desired magnitude and direction (e.g., vector) for various load conditions.

[0006] Therefore, it would be desirable to obtain methods and systems that take into account at least some of the above-mentioned problems, as well as other potential problems. [Overview of the project]

[0007] In one exemplary example, a 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 comprises a support member movably connected to the frame, an actuating member movably connected to the frame, and a load member movably connected to the actuating member, the support member, and the device. The actuating member operates to apply a load to the device when the load member is connected to the device.

[0008] In another exemplary example, a system for testing the performance of a device under different load conditions comprises a platform and a load application system. The load application system comprises several load systems mounted on the platform. Each of the several 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 actuator connected to the frame, and a load member movably connected to the actuator, the support member, and the device. The operation of the actuator applies a load to the device when the load member is connected to the device.

[0009] In yet another exemplary example, a method is provided for testing the performance of a device under different load conditions. This method includes identifying a load profile applied to the device by a linkage system including a support member, a load member, and an actuator. This method further includes determining a setpoint for the actuator of the actuator based on the load profile. This method further includes operating the actuator via the load member at a setting having a value determined to apply a load to the control surface of the device. The load applied to the control surface is determined by both the actuator setting and the geometric shape of the linkage system.

[0010] These characteristics and functions can be realized independently in various embodiments of this disclosure and may be combined in yet another embodiment, which can be understood in further detail in relation to the following description and drawings.

[0011] Novel features that may be considered characteristics of exemplary embodiments are specified in the appended claims. However, exemplary embodiments, preferred modes of use, and further objectives and features thereof will be best understood by referring to the following detailed description of exemplary embodiments of this disclosure, together with the accompanying drawings. [Brief explanation of the drawing]

[0012] [Figure 1] This is an isometric view of a test system according to an exemplary embodiment. [Figure 2] This is a side view of the test system shown in Figure 1, according to an exemplary embodiment. [Figure 3] This is a diagram of the test system shown in Figure 1, according to an exemplary embodiment, in which the control surface is in the test position. [Figure 4] This is a side view of the test system shown in Figure 3, according to an exemplary embodiment. [Figure 5] This is a diagram of the test system shown in Figure 1, according to an exemplary embodiment, in which the control surface is in the test position. [Figure 6] It is a side view of the test system of FIG. 5 according to an exemplary embodiment. [Figure 7] It is an enlarged isometric view of the load system of FIGS. 1 - 6 according to an exemplary embodiment. [Figure 8] It is a side view of the linkage system of the load system of FIG. 7 having a neutral configuration according to an exemplary embodiment. [Figure 9] It is a side view of the linkage system of the load system of FIG. 7 having a different configuration according to an exemplary embodiment. [Figure 10] It 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] It is a flowchart of a process for testing the performance of a device under different load conditions according to an exemplary embodiment. [Figure 12] It is a flowchart of a process for testing the performance of a device under different load conditions according to an exemplary embodiment. [Figure 13] It is a diagram of a process for verifying that the load applied to the control surface matches the load profile according to an exemplary embodiment. [Figure 14] It is a flowchart of a process for testing the maximum load limit of the control surface according to an exemplary embodiment. [Figure 15] It is a diagram of a method for manufacturing and maintaining an aircraft according to an exemplary embodiment. [Figure 16] It is a block diagram of an aircraft according to an exemplary embodiment.

Best Mode for Carrying Out the Invention

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

[0014] In one exemplary embodiment, a loading system includes one or more loading systems used to apply a load profile to a test device. The load profile can include, or be based on, normal operating loads, limit loads, endurance or ultimate loads, one or more other types of loads, or combinations thereof. Each loading system includes a geometric linkage system that can continuously apply a highly reproducible and predictable load to a corresponding load point of the test device. The reproducibility and predictability provided by this loading system allows for continuous and rapid load adjustment, along with the ability to remotely adjust the load profile being applied to the test device. Thus, the overall time required for testing and the complexity associated with the testing can be reduced. In particular, the methods and systems described herein enable accurate and easy reproduction of flight-equivalent hinge loads and moments within the test device. For example, the desired methods and systems herein ensure that a load having a desired vector (e.g., desired magnitude and direction) is applied.

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

[0016] The test system 100 includes a base structure 103, a platform 104, and a load application system 105. The load application system 105 and the base structure 103 are attached to or fixed to the platform 104. The platform 104 is used to support the device 102. In particular, the base structure 103 is used to attach the device 102 to the platform 104. For example, the device 102 may be attached to the platform 104 indirectly via the base structure 103. In some cases, the base structure 103 may be considered part of or integrated into the 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 exemplary examples, device 102 is a control surface device or a model thereof. In some cases, device 102 is a representation or simulation version of a control surface device.

[0018] Device 102 includes a control surface 106, a mounting structure 108, and a moving system 110. In other examples, device 102 includes a control surface 106 and either a mounting structure 108 or a moving system 110. In this figure, the moving system 110 is hidden by the mounting structure 108, and is therefore indicated by a dashed line.

[0019] The control surface 106 is a model of or represents an aircraft's flight control surface. For example, the control surface 106 may be a typical flight control surface or a representation of a part of a flight control surface that may include the trailing edge of a wing. In another example, the control surface 106 may be an actual flight control surface installed on an aircraft. The flight control surface may take the form of a rudder, elevator, flaperon, aileron, spoiler (e.g., an external spoiler, a midboard spoiler, an internal spoiler), or some other type of flight control surface. In these exemplary examples, the control surface 106 takes the form of an elevator 112, and therefore the device 102 may be referred to as an elevator device.

[0020] As described above, device 102 is attached to platform 104 via base structure 103. When control surface 106 takes the form of elevator 112 (i.e., device 102 is an elevator device), base structure 103 includes or represents a part of the aircraft to which elevator 112 will be attached. For example, base structure 103 may include, represent, or model a part of the aircraft's tail surface (e.g., horizontal stabilizer) to which elevator 112 will be connected. In other exemplary cases, base structure 103 may be at least part of or represent some other aircraft structure. For example, when control surface 106 takes the form of an aileron, flaperon, or spoiler, base structure 103 may be at least part of or represent a wing spar. When control surface 106 takes the form of a rudder, base structure 103 may be at least part of or represent 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 described above, the base structure 103 in these examples is the horizontal stabilizer, which can be displayed or modeled. Thus, the mounting structure 108 is used to attach the elevator 112 to the base structure 103 and to simulate the attachment of the elevator 112 to the horizontal stabilizer. The mounting structure 108 may include, for example, at least one of ribs, plates, fittings, hinge devices, fastener devices, beams, straps, support components, pins, posts, clamping systems or some other types of components.

[0022] The moving system 110 is connected to the control surface 106 and is used to move the control surface 106 relative to the mounting structure 108, thereby moving it relative to the base structure 103. In other exemplary cases, the moving system 110 is used to move the control surface 106 and the mounting structure 108 or a portion of the mounting structure 108 relative to the base structure 103.

[0023] In these exemplary examples, the moving system 110 includes a hydraulic actuator system. In other exemplary examples, the moving system 110 may include any number of moving devices. For example, the moving system 110 may include at least one of a hydraulic actuator, an electromechanical actuator, a motor device, a track system, a reaction link, an electro-hydraulic servo valve, or several other types of moving devices. In some cases, the moving system 110 may also include one or more other components for connecting the moving system 110 to the control surface 106, the mounting structure 108, or both. For example, the moving 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 several other types of components.

[0024] In these examples, the platform 104 used to support the device 102 may include any number of beams, barrels, structural components, fastening devices, or combinations thereof. Similarly, a base structure 103, which is part of or can be attached to the platform 104, may also include any number of beams, barrels, structural components, fastening devices, or combinations thereof. In some exemplary examples, a support system 114, which is part of or can be attached to the platform 104, helps to provide additional support to the base structure 103. The support system 114 may include, for example, supports 115 and supports 117.

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

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

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

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

[0029] In another example, the load application system 105 is controlled to apply various load profiles at each of several test positions. For example, at a given test position relative to the control surface 106, each of the load systems 116 can apply a load to the control surface 106 (or a discrete load to the control surface 106) based on a selected load profile. This load application can be repeated for various load profiles at a given test position (which may be a position angled away from the neutral position relative to the control surface 106). For example, the discrete load applied by the load system 116 can be progressively increased until the control surface 106 is blown back towards the neutral position (e.g., downward, upward, or sideways) to reach a "blowback" state. This blowback state occurs when the maximum load limit is reached. Thus, the maximum load limit for the control surface 106, the mounting structure 108, the moving system 110, or a combination thereof can be determined for each of the several test positions.

[0030] Figure 1 shows the control surface 106 in the 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 downwards relative to the base structure 103, positions angled upwards 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 (tensile load or compressive load) is applied to the control surface 106.

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

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

[0033] Figure 2 is a side view of the test system 100 of Figure 1 according to an exemplary embodiment. In this exemplary example, the support 115 is not shown so that the various components of the load system 124 of the load application system 105 are more clearly visible. 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 actuator member 210. The support member 206 and the actuator member 210 are movably connected to the frame 202. The load member 208 is movably connected to the support member 206 and the actuator 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] The movement of the control surface 106 causes the linkage system 204 to move. In particular, the movement of the control surface 106 from the neutral position 134 causes the load member 208 connected to the control surface 106 to move. Next, the support member 206 and the operating member 210 are moved relative to the frame 202. In this way, the configuration of the linkage system 204 changes as the control surface 106 moves.

[0036] However, the linkage system 204 is connected to the frame 202 and the control surface 106 so that the load member 208 is always maintained at an angle perpendicular to the control surface 106 or within a selected tolerance perpendicular to the control surface 106. The selected tolerance may be, for example, about 3 degrees, about 5 degrees, about 10 degrees, or other angular ranges from the vertical. Maintaining this right or near right angle helps to reduce or eliminate unwanted load vectors applied to the control surface 106, outside of the desired load profile applied to the control surface 106. In particular, maintaining this right or near right angle helps to ensure that the load profile actually applied to the control surface 106 accurately represents the load profile or load conditions to be tested.

[0037] As illustrated, 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, load member 208, and actuator member 210 relative to each other and to the frame 202. In the neutral configuration 212, no load is applied to the control surface 106, and all loads react through the frame 202.

[0038] As the control surface 106 moves from the neutral position 134, the load system 124 can load the device 102 at the corresponding load point 132 via the connection between the load member 208 and the control surface 106. In this exemplary example, the load systems 118, 120, and 122 in Figure 1 are operated simultaneously with and similar to the load system 124, thereby applying a load profile to the device 102.

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

[0040] Figure 3 shows the test system 100 of Figure 1 with the control surface 106 in the test position, according to an exemplary embodiment. The control surface 106 is shown at the test position 300, where 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 by approximately 37.5 degrees relative to the neutral position 134 shown in Figure 1-2.

[0041] In one exemplary example, with the control surface 106 at 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] Figure 4 is a side view of the test system 100 of Figure 3 according to an exemplary embodiment. The support 115 is not shown so that the load system 124 is more clearly visible. When the control surface 106 is in the test position 300, the linkage system 204 has 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 short, the angle between the load member 208 and the control surface 106 is right or nearly right.

[0043] During the load test at test position 300, the linkage system 204 maintains configuration 400 until the maximum load limit is reached. If the linkage system 204 moves away from configuration 400, it can be assumed that the maximum load limit has been reached. For example, the maximum load limit may be reached if the control surface 106 malfunctions or is overloaded, such as when the control surface 106 is pushed back into or toward the neutral position 134 in Figure 1-2.

[0044] Figure 5 shows the test system 100 of Figure 1 with the control surface 106 at the test position 500. In this exemplary example, the test position 500 is such that 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 by approximately 33 degrees relative to the neutral position 134 in Figure 1.

[0045] When the control surface 106 is at 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 one or more additional load profiles to increase the load applied to the control surface 106 until a maximum load limit is reached.

[0046] Figure 6 is a side view of the test system of Figure 5 according to an exemplary embodiment. The support 115 is not shown so that the load system 124 is more clearly visible. When the control surface 106 is in the test position 500, the linkage system 204 has configuration 600. Even in configuration 600, the angle between the load member 208 and the control surface 106 is maintained within a selected tolerance of 90 degrees.

[0047] During the load test at test position 500, the linkage system 204 maintains configuration 600 until the maximum load limit is reached. If the linkage system 204 moves away from configuration 600, it can be assumed that the maximum load limit has been reached. For example, the maximum load limit may be reached if the control surface 106 malfunctions or is overloaded, such as when the control surface 106 is pushed back into or toward the neutral position 134 in Figure 1-2.

[0048] Figure 7 is an enlarged isometric view of the load system 124 of Figure 1-6, according to an exemplary embodiment. In this figure, the frame 202 and the linkage system 204 are shown more clearly. As shown in Figure 1-2, the linkage system 204 is illustrated having a neutral configuration 212 corresponding to the neutral position 134 of the control surface 106.

[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 consist of two or more components connected together. Frame 202 includes frame portion 702 on the first side 700 and frame portion 703 on the second side 701. Furthermore, frame 202 includes frame portion 704 connecting frame portions 702 and 703. In one exemplary example, frame portions 702 and 703 are vertical portions, and frame portion 704 is a horizontal portion connecting those portions.

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

[0051] The support member 206 of the linkage system 204 is movably connected to the frame portion 702 on the first side 700 via a joint 705. The joint 705 may be a hinged joint or a rotatable joint. In this exemplary example, the joint 705 provides three degrees of rotational freedom (e.g., via a spherical bearing). The actuator 210 is movably connected to the frame portion 703 on the second side 701 of the frame 202 via a joint 706. Thus, the support member 206 and the actuator 210 are connected to opposite sides of the frame 202. Similar to the joint 705, the joint 706 may be a hinged joint or a rotatable joint.

[0052] The load member 208 is movably connected to both the support member 206 and the actuating member 210 via a joint 708. In this example, the joint 708 may be articulated, including a hinged joint and a spherical bearing. In this exemplary example, the joint 705 provides the load member 208 with one rotational degree of freedom. 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 Figure 1-6 in a joint (not shown) that provides at least one rotational degree of freedom. This joint may be yet another hinged 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, at least one of several other types of devices for measuring load or strain, such as a load cell, load pin, strain gauge, or, for example, a load cell, load pin, strain gauge, or several other types of devices for measuring load or strain. The load measuring device 712 may be associated with the load member 208 by being attached, fixed or connected to the load member 208 indirectly or directly. 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 actuating member 210 is associated with the actuator 714. The actuator 714 may be associated with the actuating member 210 by being attached, fixed, or connected to the actuating member 210 indirectly or directly. Alternatively, the actuator 714 may be associated with the actuating member 210 by being integrated as part of the actuating member 210.

[0055] In this exemplary 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 the control surface 106 by the load member 208. The actual load applied to the control surface 106 is a function of the pressure setting and the geometry of the linkage system 204.

[0056] Therefore, by deflecting the pressure setting of the actuator 714 without deflecting the geometry of the linkage system 204 (i.e., without moving the control surface 106, and thereby without moving the linkage system 204), it is possible to 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 can be maintained for two different positions on the control surface 106 (i.e., two different geometric shapes of the linkage system 204). As another example, the load applied to the control surface 106 is 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] The linkage system 204 can use a single pressure setting of the actuator 714 to impart a desired load profile to the corresponding load points on the control surface 106. Specifically, the lengths of the support member 206, the load member 208, and the actuating member 210, as well as the positions of the joints 705 and 706, can be selected so that a single pressure setting of the actuator 714 can be used to apply an appropriate load to the control surface 106 based on the selected load profile. Based on the selected load profile, the pressure setting required to apply an appropriate load to a particular geometric shape of the linkage system 204 can be determined via a mathematical analysis tool.

[0058] The settings for actuator 714 can be adjusted physically on actuator 714 or controlled remotely. For example, the remote control unit 136 in Figure 1 can be used to control the pressure setting of actuator 714. The load applied by the load member 208 based on the pressure setting of actuator 714 simulates the aerodynamic load on the control surface 106.

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

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

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

[0062] The test system 100 and its various components shown in Figure 1-10 are not intended to imply any physical or architectural limitations on how the exemplary embodiment may be carried out. Other components may be used in addition to or instead of the illustrated components. Some components may be optional.

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

[0064] Process 1100 may begin by identifying the load profile applied to the device by a linkage system including support members, load members, and actuating members (step 1102). The device may be, for example, device 102 in Figure 1. In some exemplary cases, the device includes control surfaces such as rudders, elevators, flaperons, ailerons, spoilers, or some other types of control surfaces. The linkage system may be part of a load application system, such as load application system 105 in Figure 1. The load application system may include one or more load systems, each including a linkage system such as linkage system 204 in Figure 2.

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

[0066] Process 1100 further includes operating an actuator with a setting having a value determined to apply a load to the control surface of a 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), after which the process terminates. In step 1106, operating the actuator may include, for example, supplying energy to the actuator with 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 with respect 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 position on the frame to which the actuating member is connected, and the position on the frame to which the support member is connected).

[0067] A resistive tensile load is applied to the control surface when step 1106 is performed and the control surface is in a test position angled away from the frame. A resistive compressive tensile load is applied to the control surface when step 1108 is performed and the control surface is in a test position angled toward the frame.

[0068] In some exemplary cases, 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 exemplary cases, the control surface may be moved between multiple test positions while a load is applied to it.

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

[0070] Process 1200 may begin by identifying a set of test conditions for testing a control surface using a set of load systems (step 1202). 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 exemplary examples, the test conditions are a combination of a test location relative to the control surface and a load profile relative to the control surface.

[0071] The test positions could be, for example, the angular deflection of a control surface. In one exemplary example, a set of test positions might include a sweep of positions between the maximum deflection in one direction (e.g., -30 degrees from the neutral position) and the maximum deflection in another direction (e.g., +30 degrees from the neutral position). In another example, the maximum deflection in either direction could be between approximately 10 degrees and 60 degrees from the neutral position.

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

[0073] Therefore, a load profile may include the loads applied by each load system of a set of load systems at corresponding load points on the control surface. In these exemplary examples, each load system may be configured to apply the same load to the control surface for a given load profile. In other cases, one load system may be configured to apply a load different from at least one other load system.

[0074] In process 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] Subsequently, process 1200 includes determining the setpoints for each actuator in a set of load systems for each identified set of test conditions (step 1204). In step 1204, for each test condition, the actuator setpoint is determined based on the load profile of that test condition. This determination is based on the geometry of the linkage system in each load system. For each load system, the actuator is part of the working member of the linkage system of that load system.

[0076] Step 1204 considers that the actual load profile applied to the control surface is a function of both the actuator setpoint and the geometry of the linkage system. The geometry of the linkage system differs depending on the different location on the control surface. In short, the orientation of the load member, actuating member, and support member of the linkage system relative to each other differs for each different location on the control surface. Therefore, the actuator setpoint of a particular load system for a particular load profile (and thus a particular test location) can be determined based on the load applied to the control surface by the load system according to the load profile, and the known geometry of the linkage system at the test location corresponding to that load profile (for example, it can be calculated using a mathematical analysis tool). In some exemplary cases, the actuator setpoint may be constant for several different load profiles.

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

[0078] Next, the load profile is applied to the control surface by using the actuator's setpoint corresponding to the load profile of the selected test conditions, thereby supplying energy to the actuators of each load system (step 1210). In step 1210, each load system applies a discrete load at the corresponding load point on the control surface. As described above, the discrete load applied to the control surface is a function of the actuator's setpoint and the geometric shape of the linkage system of the load systems.

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

[0080] Next, process 1200 includes verifying that the discrete loads applied to the control surface by each load system match the load profile of the selected test condition within the selected tolerance (step 1212). Then, a decision is 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. Otherwise, process 1200 returns to step 1206 above.

[0081] Therefore, as illustrated by process 1200, the control surface can be tested under various test conditions using a single setting for a single actuator in each load system of a set of load systems. For example, the control surface can sweep a range of positions under various load conditions without the need to adjust the configuration of large or complex equipment.

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

[0083] Process 1300 includes generating a measurement of the load applied to the control surface by the load system at the load point (step 1302). Step 1302 may be performed, for example, using a load measuring device associated with the load member of the linkage system of the load system. The load measuring device may include, for example, at least one of a load cell, load pin, strain gauge, or several other types of devices for measuring load or strain. Next, a determination is made as to whether the measured load is within a selected tolerance of the load that will be applied at the load point, based on a selected load profile (step 1304). If the measured load is within the selected tolerance of the load that will be applied, the process ends. Otherwise, the settings for the actuator of the load system are adjusted (step 1306), and the process then returns to step 1302 above.

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

[0085] Process 1400 may be initiated by moving the control surface into a test position that is angled away from the neutral position of the control surface (step 1402). A load profile is applied to the control surface by supplying energy to each actuator of a set of load systems (step 1404). In other exemplary examples, step 1404 may be performed before moving the control surface into the test position.

[0086] Subsequently, a determination is 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 is blown back towards the neutral position (for example, blown downwards, upwards, or sideways). If the control surface has reached its maximum load limit, the process terminates.

[0087] Otherwise, the energy supply to each actuator of a set of load 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 so that the load applied to the control surface by each load system of the set of load systems increases. In one particular example, when the actuators of each load system are hydraulic actuators, the pressure setpoints of the actuators may increase.

[0088] Exemplary embodiments of this disclosure may be described in relation to the aircraft manufacturing and maintenance method 1500 shown in Figure 15 and the aircraft 1600 shown in Figure 16. Referring first to Figure 15, the aircraft manufacturing and maintenance method is illustrated according to an exemplary embodiment. In the pre-manufacturing stage, the aircraft manufacturing and maintenance method 1500 includes the specifications and design 1502 of the aircraft 1600 shown in Figure 16, and the procurement of materials 1504.

[0089] During the manufacturing phase, the components and subassemblies of the aircraft 1600 shown in Figure 16 are manufactured 1506 and system integration is performed 1508. Subsequently, the aircraft 1600 shown in Figure 16 undergoes certification and delivery 1510 and is put into operation 1512. During customer operation 1512, the aircraft 1600 shown in Figure 16 is scheduled for periodic maintenance and upkeep 1514 (which may include modifications, reconfigurations, refurbishments, and other maintenance and upkeep).

[0090] Each process of the Aircraft Manufacturing and Maintenance Method 1500 may be carried out or performed by a system integrator, a third party, and / or an operator. In these embodiments, the operator may be a customer. In this specification, 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, leasing company, military organization, service organization, etc.

[0091] Referring now to Figure 16, a diagram of an aircraft on which an exemplary embodiment may be implemented is shown. In this example, the aircraft 1600 may include a fuselage 1602 having several systems 1604 and interior 1606, manufactured by the aircraft manufacturing and maintenance method 1500 of Figure 15. Examples of systems 1604 include, but are not limited to, one or more of the 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. Although an example from the aerospace industry is shown, various exemplary embodiments may be applied to other industries, such as the automotive industry.

[0092] The apparatus and methods embodied herein can be employed in at least one stage of the aircraft manufacturing and maintenance method 1500 shown in Figure 15. In particular, the test system 100 shown in Figure 1-10 may be used to test a flight control surface during one or more stages of the aircraft manufacturing and maintenance method 1500. For example, but not limited to, the test system 100 may be used during specification and design 1502, manufacturing of components and subassemblies 1506, system integration 1508, certification and delivery 1510, periodic maintenance and servicing 1514, or at least one of several other stages of the aircraft manufacturing and maintenance method 1500. Furthermore, the test system 100 may be used to test the device 102 shown in Figure 1, which may be a component of the aircraft 1600 or a representation of such a component. For example, the device 102 may be considered part of a flight control system 1616. In some cases, device 102 may be one of the systems 1604 of an aircraft 1600 controlled or commanded by a flight control system 1616.

[0093] In one exemplary example, the components or subassemblies manufactured in the manufacturing 1506 of the components and subassemblies in Figure 15 may be manufactured in a similar manner to the components or subassemblies manufactured during the operational period 1512 of the aircraft 1600 in Figure 15. In yet another embodiment, one or more embodiments of devices, embodiments of methods, or combinations thereof may be used in manufacturing stages such as the manufacturing 1506 of the components and subassemblies in Figure 15 and system integration 1508. One or more embodiments of devices, embodiments of methods, or combinations thereof may be used during the operational period 1512 of the aircraft 1600 in Figure 15 and / or during maintenance and servicing 1514. By using several different exemplary embodiments, it is possible to significantly streamline and / or significantly reduce the cost of assembling the aircraft 1600.

[0094] The flowcharts and block diagrams in the various embodiments shown illustrate the architecture, functionality, and operation of several possible embodiments of the apparatus and method in the exemplary embodiments. Therefore, each block in the flowchart or block diagram may represent a module, segment, function, and / or part of an operation or step.

[0095] The flowcharts and block diagrams in the various embodiments shown illustrate the architecture, functionality, and operation of several possible embodiments of the apparatus and method in the exemplary embodiments. For example, in some cases, two blocks shown consecutively may be executed substantially simultaneously, depending on the related function, and sometimes in reverse order. In addition, other blocks may be added in addition to those shown in the flowchart or block diagram. In this specification, the expression "at least one of" used with the enumerated items means that one or various combinations of the enumerated items may be used, and only one of the enumerated items may be required. An item may be a specific object, article, step, action, process, or category. In other words, "at least one of" means that any combination of items or some items from the enumerated may be used, but not all of the enumerated items may be required. For example, non-restrictively, "at least one of item A, item B, or item C" or "at least one of item A, item B, and item C" could mean, for example, "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" could non-restrictively mean "two items A, one item B, and ten items C," "four items B, seven items C," or any other preferred combination.

[0096] Clause 1. Apparatus for testing the performance of a device (102) under different load conditions, Frame (202), A linkage system (204) connected to the frame (202) and The linkage system (204) is equipped with A support member (206) is movably connected to the frame (202), A movable member (210) connected to the frame (202), A load member (208) is movably connected to the operating member (210), the support member (206), and the device (102). The device is equipped with such that when the load member (208) is connected to the device (102), the operation of the operating member (210) applies a load to the device (102).

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

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

[0099] Clause 4. The apparatus according to any one of Clauses 1 to 3, wherein the actuating member (210), the support member (206), and the load member (208) are connected together movably via a joint, and the actuating member (210) and the support member (206) are connected to the opposite side of the frame (202).

[0100] Clause 5. The apparatus according to any one of Clauses 1 to 4, wherein a support member (206) is movably connected to a first side of a frame (202) at a first joint (705), and an operating member (210) is movably connected to a second side of a frame (202) at a second joint (706).

[0101] Clause 6. The operating member (210) The apparatus according to Clause 5, wherein a first position of the first joint (705) to the frame (202) and a second position of the second joint (706) to the frame (202) are selected such that controlling a single pressure setting for the actuator (714) is sufficient to load the device (102) based on a selected load profile.

[0102] Clause 7. The apparatus according to Clause 5, wherein the first length of the support member (206), the second length of the load member (208), the third length of the actuarial 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 within a selected tolerance range that is perpendicular to the load member (208) at any test position of the device (102).

[0103] Clause 8. The operating member (210) Actuator (714) The apparatus described in any one of the clauses 1 to 7, comprising:

[0104] Article 9. The apparatus according to Clause 8, further comprising a remote control unit (136) that communicates with a hydraulic actuator (714), wherein the remote control unit (136) controls the pressure setting of the hydraulic actuator (714) to control the load applied to the control surface (106) of the device (102) by the load member (208).

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

[0106] Article 11. A load application system (105) comprising multiple load systems (116), wherein a frame (202) linkage system (204) forms load systems (118, 120, 122, 124) of the multiple load systems (116). The apparatus described in Clause 10, further comprising:

[0107] Clause 12. The apparatus described in any one of Clauses 1 to 11, wherein the device (102) comprises a control surface (106), a moving 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, Platform (102), A load application system (105) including multiple load systems (116) attached to a platform (102) and Each of the multiple load systems (116) is equipped with, Frame (202), A linkage system (204) connected to the frame (202) and The linkage system (204) is equipped with A support member (206) connected to the frame (202), An operating member (210) connected to the frame (202), A load member (208) is movably connected to the operating member (210), the support member (206), and the device (102). The system (100) is equipped with such that when the load member (208) is connected to the device (102), the operation of the actuarial member (210) applies a load to the device (102).

[0109] Clause 14. A method for testing the performance of a device (102) under different load conditions, Identifying the load profile applied to the device (102) by a linkage system (204) including a support member (206), a load member (208), and an operating member (210) (1102), Based on the load profile, the set value of the actuator (714) of the working member (210) is determined (1104), The actuator (714) is operated (1106) with a setting that has been determined to apply a load to the control surface (106) of the device (102) via the load member (208). A method comprising the following, wherein the load applied to the control surface (106) is determined by both the settings of the actuator (714) and the geometric shape of the linkage system (204).

[0110] Article 15. To verify that the load applied to the device (102) matches a load profile identified within a selected tolerance, the load applied to the control surface (106) is measured (1212) using the load measuring device (712) of the linkage system (204). The method described in Clause 14, further including the method described in Clause 14.

[0111] Clause 16. Operating the actuator (714) (1106) Energy is supplied to the actuator (714) (1210) based on a value determined for the setting. The method according to clause 14 or 15, wherein the load is transmitted from the actuator (210) to the control surface (106) via the load member (208).

[0112] Clause 17. The actuator (714) is a hydraulic actuator, and the setting value is determined by (1104), Calculate the pressure setpoint of the hydraulic actuator based on the load profile. The method described in Article 16, including the method described in Article 16.

[0113] Clause 18. Operating the actuator (714) (1106) Remote control of the actuator (714) settings. The method described in any one of the clauses 14 to 17, including the method described in any one of the clauses 14 to 17.

[0114] Article 19. Before applying a load to the control surface (106), move the control surface (106) of the device (102) into the test position (1402). The method described in any one of clauses 14 to 18, further including the method described in any one of clauses 14 to 18.

[0115] Clause 20. Determining the set value, The setpoint of the actuator (714) is calculated based on the identified load profile and the geometry of the linkage system (204). The method described in any one of the clauses 14 to 19, including the method described in any one of the clauses 14 to 19.

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

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

[0118] Clause 23. The 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) when the test position relative to the control surface (106) is angled away from the frame (202). The method described in Article 22, including the method described in Article 22.

[0119] Clause 24. The linkage system (204) is connected to the frame (202) and operates the actuator (714) (1106), When the test position relative to the control surface (106) is angled toward the frame (202), a resistive compressive tension load is applied to the control surface (106) of the device (102). The method described in Article 22, including the method described in Article 22.

[0120] The descriptions of various exemplary embodiments are presented for illustrative and explanatory purposes only and are not intended to be exhaustive or limit to the embodiments disclosed. Numerous modifications and variations will be obvious to those skilled in the art. Furthermore, various exemplary embodiments may offer different features compared to other preferred embodiments. One or more selected embodiments are described to provide the best possible explanation of the principles and practical applications of the embodiments and to enable those skilled in the art to understand the disclosure of various embodiments, including various modifications suitable for specific intended applications.

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 a second end of the actuating member (210) and a 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; An 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 a first length of the support member (206), a second length of the load member (208), a third length of the actuating member (210), 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 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 said platform (102), said base structure (103) having said device (102) mounted thereon; a load application system (105) comprising a plurality of load systems (116), the frame (202) and the linkage system (204) forming 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. 1. 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 a second end of the actuating member (210) and a 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 having 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 a 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: manipulating 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 transferred from the actuating member to the control surface via the load member.

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

12. or, operating (1106) the actuator (714) comprises remotely controlling the settings of the actuator (714); The method further includes moving (1402) the control surface (106) of the device (102) into a test position prior to 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 (1402) the control surface (106) of the device (102) from a neutral position into a test position.

14. The method of claim 9, further comprising:

15. The linkage system (204) is connected to a frame (202), and manipulating (1106) the actuator (714); applying a resistive tensile load to the control surface (106) of the device (102) as 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) as 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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