Analog loading device for aircraft and aircraft test system

Abstract

The utility model provides an analog loading device for an aircraft and an aircraft test system. The analog loading device comprises: a base; the control surface false piece is pivotally arranged on the base; the driving assembly is arranged on the base, and the driving end of the driving assembly is in driving connection with the control surface false part; and the loading assembly is arranged on the base, the loading assembly comprises a loading structure which can abut against the control surface false piece, and the loading structure is located on the pivoting path of the control surface false piece, so that the abutting force between the control surface false piece and the loading structure is changed after the rotation angle is adjusted. One end of the driving assembly is in driving connection with the control surface fake piece and drives the control surface fake piece to be adjusted to the preset angle, so that the abutting state between the control surface fake piece and the loading structure is changed, the loading load of the loading structure on the control surface fake piece is adjusted to the preset load, and therefore the situation of control surface loading is simulated. Therefore, the problems of poor universality and high cost of the simulation device in the prior art are solved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a simulation loading device for aircraft and an aircraft testing system. Background Art

[0002] There are many types of aircraft. Take the commonly used means of transportation, airplane, for example. Because it plays an important role in carrying people and cargo, its safety must be guaranteed.

[0003] In modern society, airplanes are one of the important means of transportation for people. They are both safe and fast, and more and more people choose to travel by airplane. In order to ensure flight safety, the aircraft will undergo a number of important simulation tests before its first flight. Only after multiple tests and verifications can the safety of the aircraft be guaranteed.

[0004] Among many tests, the aircraft control surface loading system test can verify whether the functions of the moving parts of the control surface, control mechanism, and servo are reliable and stable under the pneumatic hinge torque.

[0005] However, current tests mostly use 1:1 simulation samples or conduct tests on real aircraft rudder surfaces, and simulate loads by loading motors or setting weights on real aircraft rudder surfaces to simulate loads. However, this method will cause damage to the wing skin and rudder surface, and is inconvenient to operate. Therefore, the cost of the test remains high and the versatility is poor.

[0006] It can be seen from the above that the simulation devices in the prior art have the problems of poor versatility and high cost. Utility Model Content

[0007] In view of this, an object of the present invention is to provide a simulation loading device for an aircraft and an aircraft testing system.

[0008] In order to achieve the above purpose, the technical solution provided by an embodiment of the present utility model is as follows:

[0009] A simulated loading device for an aircraft comprises: a base; a dummy rudder surface, which is pivotally arranged on the base; a driving assembly, which is arranged on the base and has a driving end connected to the dummy rudder surface; a loading assembly, which is arranged on the base and comprises a loading structure capable of abutting against the dummy rudder surface, and the loading structure is located on the pivot path of the dummy rudder surface, so that the abutment force between the dummy rudder surface and the loading structure changes after the rotation angle is adjusted.

[0010] By setting a driving component on the base, one end of the driving component is connected to the rudder surface dummy and can drive the rudder surface dummy to adjust to a preset angle, so that the abutment state between the rudder surface dummy and the loading structure is changed, and the loading load of the rudder surface dummy by the loading structure is adjusted to a preset load, thereby simulating the situation of loading the rudder surface, so as to facilitate the implementation of the aircraft rudder surface loading system test.

[0011] Furthermore, the loading assembly also includes a supporting structure, which is detachably connected to the base, and the loading structure is arranged on the supporting structure. By arranging the supporting structure, a strong support can be provided to the loading structure, thereby ensuring that the loading structure can stably provide the load when the loading structure applies the load to the dummy rudder surface, and ensuring that the loading structure and the dummy rudder surface are stably in contact. The detachable connection between the supporting structure and the base can effectively provide the convenience of disassembling and assembling the loading structure, so as to improve the versatility of the simulation loading device.

[0012] Furthermore, both ends of the support structure are detachably connected to the base; and / or the support structure is extended along the pivot path of the dummy rudder surface; and / or the loading structure is sleeved on the support structure; and / or the loading structure is an elastic member; and / or scale marks are provided on the support structure along its extension direction. This not only makes it easy to disassemble and assemble the loading structure, but also can further improve the versatility of the simulation loading device by replacing the support structure. The dummy rudder surface needs to adjust the deflection angle during the simulation process, so the support structure is extended along the pivot path of the dummy rudder surface to ensure that the loading structure is fully in contact with the dummy rudder surface and stably abuts against it, and the force is also easy to be more evenly loaded on the dummy rudder surface.

[0013] Furthermore, a clearance notch is provided at the free end of the dummy rudder surface, the support structure passes through the clearance notch, and a gap is formed between the clearance notch and the support structure. The clearance notch can prevent the support structure from interfering with the rotation of the dummy rudder surface.

[0014] Further, the support structure includes: an arc-shaped rod; a locking portion, the locking portion being arranged at the end of the arc-shaped rod so as to lock or unlock the arc-shaped rod with the base. The locking portion is arranged at the end of the arc-shaped rod so as to lock or unlock the arc-shaped rod with the base. By arranging the locking portion, the end of the arc-shaped rod can be effectively locked with the base, thereby providing effective support for the loading structure.

[0015] Furthermore, there are multiple loading structures, and the multiple loading structures can be interchangeably arranged on the supporting structure; and / or the loading structure is a spring or rubber. When the loading structure is a spring, there are multiple springs, and at least one of the wire diameter, stiffness, and length of the multiple springs is different. By selecting loading structures with different parameters, the demand for applying different loads to the rudder surface dummy can be met, rather than simply adjusting the load by changing the deflection angle of the rudder surface dummy, thereby effectively improving the versatility of the simulation loading device. By selecting different springs and combining them according to the differences in wire diameter, stiffness, and length, the rudder surface dummy is subjected to different loads to adapt to different test conditions.

[0016] Furthermore, the loading structure at least includes a first loading section and a second loading section located on opposite sides of the dummy rudder surface, and both the first loading section and the second loading section can abut against the dummy rudder surface. The first loading section and the second loading section are respectively located on the upper and lower sides of the dummy rudder surface along the arc rod, and by rotating the dummy rudder surface, the first loading section and the second loading section can load different loads on the two surfaces of the dummy rudder surface.

[0017] Furthermore, the loading components are multiple groups, and the multiple groups of loading components are spaced apart along the length direction of the dummy rudder surface. Of course, the loading components can also be one group, which requires selecting appropriate positions on the dummy rudder surface to set the number of loading components according to the actual loading conditions.

[0018] Furthermore, the simulated loading device for an aircraft further comprises an angle measurement sensor and a load measurement sensor, which are arranged on the base and / or the dummy control surface. By arranging the load measurement sensor and the angle measurement sensor, the state of the dummy control surface under the action of the load can be displayed.

[0019] Furthermore, the base includes: a base body, on which at least a part of the driving assembly is arranged; and a mounting plate, on which the mounting plate is arranged, on which the dummy control surface and the loading assembly are arranged. In this way, the positions of the above components can be arranged reasonably, thereby simulating the actual installation position relationship of each component on a real aircraft.

[0020] Furthermore, the mounting plate is connected to the side of the base body; and / or the mounting plate is arranged perpendicularly to the base body; and / or there are multiple mounting plates and loading assemblies, and multiple mounting plates are arranged one-to-one with multiple loading assemblies, and multiple mounting plates are arranged on the base body at intervals. The mounting plate is perpendicular to the base body, which is conducive to determining the horizontal state of the dummy rudder surface, that is, simulating the non-working state of the loading device. Of course, the loading assembly can also be a group, which requires selecting a suitable position on the dummy rudder surface to set the number of loading assemblies according to the actual load conditions.

[0021] Furthermore, the driving assembly includes a steering gear, a swing rod, a connecting rod and a connecting seat connected in sequence, the steering gear drives the swing rod to swing, the swing rod and the connecting rod, the connecting rod and the connecting seat are all rotatably connected, and the connecting seat is fixedly connected to the dummy rudder surface. The steering gear drives the swing rod to swing, drives the connecting rod to move, and then drives the dummy rudder surface connected to the connecting seat to rotate relative to the mounting plate. The steering gear is the same model of steering gear installed on the real machine, serving as the power source for the movement of the dummy rudder surface of the device, and is also one of the test objects of the device.

[0022] The utility model also provides an aircraft test system, including the above-mentioned simulation loading device for aircraft. The aircraft test system of the utility model also includes a control system, and the control system is electrically connected to the driving component of the simulation loading device. Optionally, the simulation loading device is multiple and arranged in parallel, and the multiple simulation loading devices are all electrically connected to the control system, so as to verify the stability of the rudder motion mechanism and the control system, realize multiple tests synchronously, improve the versatility of the simulation loading device, and speed up the test efficiency.

[0023] The utility model has the following beneficial effects:

[0024] By setting a driving component on the base, one end of the driving component is connected to the rudder surface dummy and can drive the rudder surface dummy to adjust to a preset angle, so that the abutment state between the rudder surface dummy and the loading structure is changed, and the loading load of the rudder surface dummy by the loading structure is adjusted to a preset load, thereby simulating the situation of loading the rudder surface, so as to facilitate the implementation of the aircraft rudder surface loading system test.

[0025] It should be noted that before the formal test, it is necessary to select the specifications of the loading component and match the rotation angle of the dummy rudder surface through calculation, so that the preset load can be applied to the dummy rudder surface at the preset angle. After the test starts, the drive component drives the dummy rudder surface to rotate, thereby changing the contact force of the dummy rudder surface with the loading structure, that is, simulating the load condition of the rudder surface of the aircraft. Using dummy rudder surfaces to replace real rudder surfaces ensures the accuracy of the test results while reducing the cost loss caused by using real rudder surfaces, thereby solving the problem of poor versatility and high cost of simulation devices in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0027] Figure 1A schematic structural diagram showing a shutdown state of a simulated loading device for an aircraft in a specific embodiment of the utility model; and

[0028] Figure 2 Shows Figure 1 A partial enlarged view of the middle A;

[0029] Figure 3 A schematic structural diagram of the upward swing simulation loading of a dummy control surface of a simulation loading device for an aircraft in a specific embodiment of the utility model is shown;

[0030] Figure 4 A schematic structural diagram of the simulated loading of the dummy control surface swinging of a simulated loading device for an aircraft in a specific embodiment of the utility model is shown.

[0031] The above drawings include the following reference numerals:

[0032] 10. Base; 11. Base body; 12. Mounting plate; 20. Control surface dummy; 21. Clearance gap; 30. Drive assembly; 31. Servo; 32. Swing rod; 33. Connecting rod; 34. Connecting seat; 40. Loading assembly; 41. Loading structure; 411. First loading section; 412. Second loading section; 42. Support structure; 421. Arc rod; 422. Locking part; 50. Connecting piece. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical scheme and advantages of the embodiments of the utility model clearer, the technical scheme in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Generally, the components of the embodiments of the utility model described and shown in the drawings here can be arranged and designed in various different configurations.

[0034] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the present invention to be protected, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0036] In the description of the embodiments of the present invention, it should be understood that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, or are the orientations or positional relationships in which the product of the application is conventionally placed when in use, or are the orientations or positional relationships conventionally understood by those skilled in the art. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0037] In the description of the embodiments of the present utility model, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0038] In the description of the embodiments of the present invention, it is also necessary to explain that the "first", "second", etc. used in this article do not specifically refer to the order or sequence, nor are they used to limit the present case. They are only used to distinguish components or operations described with the same technical terms.

[0039] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

[0040] The technical solution of the present utility model will be described below in conjunction with the accompanying drawings.

[0041] In order to solve the problems of poor versatility and high cost of simulation devices in the prior art, the utility model provides a simulation loading device for aircraft and an aircraft testing system. The aircraft testing system includes the simulation loading device for aircraft.

[0042] like Figures 1 to 4 As shown, the simulated loading device for an aircraft comprises a base 10, a dummy control surface 20, a driving assembly 30 and a loading assembly 40. The dummy control surface 20 is pivotably arranged on the base 10. The driving assembly 30 is arranged on the base 10, and the driving end of the driving assembly 30 is drivingly connected to the dummy control surface 20. The loading assembly 40 is arranged on the base 10, and the loading assembly 40 comprises a loading structure 41 capable of abutting against the dummy control surface 20, and the loading assembly 40 is located on the pivot path of the dummy control surface 20, so that the abutting force between the dummy control surface 20 and the loading structure 41 changes after adjusting the rotation angle.

[0043] By setting a driving component 30 on the base 10, one end of the driving component 30 is connected to the rudder surface dummy 20 and can drive the rudder surface dummy 20 to adjust to a preset angle, so that the abutment state between the rudder surface dummy 20 and the loading structure 41 is changed, and the loading load of the rudder surface dummy 20 by the loading structure 41 is adjusted to a preset load, thereby simulating the situation of loading the rudder surface, so as to facilitate the implementation of the aircraft rudder surface loading system test.

[0044] It should be noted that before the formal test, it is necessary to select the specifications of the loading component and match the rotation angle of the dummy rudder surface 20 through calculation, so that the preset load can be applied to the dummy rudder surface 20 at the preset angle. After the test starts, the driving component 30 drives the dummy rudder surface 20 to rotate, thereby changing the contact force of the dummy rudder surface 20 with the loading structure 41, that is, simulating the load on the rudder surface of the aircraft. Using the dummy rudder surface 20 to replace the real rudder surface ensures the accuracy of the test results while reducing the cost loss caused by using the real rudder surface, thereby solving the problem of poor versatility and high cost of the simulation device in the prior art.

[0045] like Figure 1 As shown, the loading assembly 40 also includes a support structure 42, which is detachably connected to the base 10, and the loading structure 41 is arranged on the support structure 42. By arranging the support structure 42, a strong support can be provided to the loading structure 41, so as to ensure that the loading structure 41 can stably provide the load during the process of the loading structure 41 applying the load to the rudder surface dummy 20, and ensure that the loading structure 41 and the rudder surface dummy 20 are stably abutted. The support structure 42 is detachably connected to the base 10, which can effectively provide the convenience of disassembling and assembling the loading structure 41, so as to improve the versatility of the simulated loading device. The loading structure 41 is mainly used to simulate the pneumatic hinge torque borne by the rudder surface when it moves.

[0046] Specifically, the support structure 42 is disposed on the side of the base 10 , so as to facilitate the disassembly and assembly of the support structure 42 . Correspondingly, the loading structure 41 is also disposed on the side of the base 10 .

[0047] In this embodiment, both ends of the support structure 42 are detachably connected to the base 10. This not only facilitates the disassembly and assembly of the loading structure 41, but also enables the versatility of the simulation loading device to be further improved by replacing the support structure 42.

[0048] In this embodiment, the support structure 42 is extended along the pivot path of the dummy rudder surface 20. In this way, the loading structure 41 placed on the support structure 42 can also be extended along the pivot path of the dummy rudder surface 20. In addition, in this embodiment, the dummy rudder surface 20 needs to adjust the deflection angle during the simulation process, so the support structure 42 is extended along the pivot path of the dummy rudder surface 20 to ensure that the loading structure 41 is fully in contact with the dummy rudder surface 20 and abuts stably, and the force is also easy to be more evenly loaded on the dummy rudder surface 20.

[0049] like Figures 2 to 4 As shown, the support structure 42 includes an arc-shaped rod 421 and a locking portion 422. The locking portion 422 is provided at the end of the arc-shaped rod 421 to lock or unlock the arc-shaped rod 421 with the base 10. By providing the locking portion 422, the end of the arc-shaped rod 421 can be effectively locked with the base 10, thereby providing effective support for the loading structure 41. In addition, by releasing the locking state between the end of the arc-shaped rod 421 and the base 10 through the locking portion 422, the support structure 42 and / or the loading structure 41 can also be effectively disassembled. Specifically, the arc-shaped rod can be a round tube or square steel.

[0050] Specifically, both ends of the arc rod 421 are provided with locking parts 422. The locking parts 422 are threadedly connected or clamped with the base 10. In this way, the ends of the arc rod 421 can be effectively locked with the base 10, and it can also be easy to disassemble and assemble. Optionally, both ends of the arc rod 421 are buckles or slots, and the base 10 is provided with corresponding slots or buckles. The shape of the arc rod 421 is adapted to the rotation trajectory of the rudder surface dummy 20, and the arc rod 421 can be stretched or rolled by metal. In this embodiment, the locking part 422 is a self-locking nut.

[0051] In the present invention, the loading structure 41 is sleeved on the supporting structure 42. By means of sleeve installation, the supporting area of ​​the loading structure 41 and the supporting structure 42 can be effectively increased, so that the supporting structure 42 can stably support the loading structure 41; and the loading structure 41 can be effectively prevented from accidentally detaching from the supporting structure 42 during the process of applying load to the rudder dummy 20, thereby causing the loading failure.

[0052] Specifically, the loading structure 41 is an elastic member. The elastic member has a certain deformation capability and can also provide a corresponding load by compression, so that the process of simulating loading has the advantage of being easy to operate.

[0053] Optionally, the loading structure 41 is a spring or rubber. Both have a certain ability to be compressed or stretched, and can adjust the load applied to the dummy control surface 20 according to the compressed or stretched state, so as to simulate the load condition of the control surface of the aircraft. Specifically, the loading structure 41 can be a rubber rope.

[0054] In order to meet different test requirements, there can be multiple loading structures 41, and the multiple loading structures 41 can be interchangeably arranged on the support structure 42. By selecting loading structures 41 with different parameters, the requirements of applying different loads to the dummy rudder surface 20 can be met, rather than simply adjusting the load by changing the deflection angle of the dummy rudder surface 20, thereby effectively improving the versatility of the simulation loading device.

[0055] Specifically, when the loading structure 41 is a spring, there are multiple springs, and at least one of the wire diameter, stiffness, and length of the multiple springs is different. By selecting different springs and combining them according to the differences in wire diameter, stiffness, and length, the rudder dummy 20 is subjected to different loads to adapt to different test conditions. In addition, the support structure 42 can prevent the compressed spring from bending and deforming when subjected to force, and can also verify the correctness of the motion trajectory of the rudder dummy 20 when it moves. Specifically, the loading structure 41 can be a tension spring or a gas spring.

[0056] In addition, scale marks may be provided on the support structure 42 along its extension direction, so that the specific value of the deflection of the dummy rudder surface 20 can be directly determined by setting the scale, and the rotation angle of the dummy rudder surface 20 can be adjusted conveniently, which has the characteristic of good visualization effect.

[0057] In this embodiment, a clearance notch 21 is provided at the free end of the dummy control surface 20, and the support structure 42 passes through the clearance notch 21, and a gap is formed between the clearance notch 21 and the support structure 42. Therefore, the shape of the arc rod 421 is adapted to the bottom track of the clearance notch 21 and the gap is maintained, so as to prevent the arc rod 421 from interfering with the rotation of the dummy control surface 20.

[0058] exist Figure 1 In the illustrated embodiment, since there are two groups of loading assemblies 40 corresponding to the two ends of the length of the dummy rudder surface 20, two clearance notches 21 are provided at the two ends of the length of the dummy rudder surface 20 corresponding to the two arc-shaped rods 421. The opening size of the clearance notch 21 is larger than the diameter of the support structure 42. The clearance notch 21 is U-shaped as a whole.

[0059] When the dummy rudder surface 20 rotates relative to the base 10, the support structure 42 never contacts the clearance notch 21, thereby preventing the dummy rudder surface 20 from contacting the support structure 42, causing errors in the load of the dummy rudder surface 20 and affecting the test results. In this embodiment, the support structure 42 is made of stainless steel.

[0060] In this embodiment, the loading structure 41 at least includes a first loading section 411 and a second loading section 412 located on opposite sides of the dummy rudder surface 20, and both the first loading section 411 and the second loading section 412 can abut against the dummy rudder surface 20. Figure 2 It can be seen that the first loading segment 411 and the second loading segment 412 correspond to the upper and lower sides of the rudder surface dummy 20 along the arc rod 421 respectively. By rotating the rudder surface dummy 20, the first loading segment 411 and the second loading segment 412 can load different loads on the two surfaces of the rudder surface dummy 20.

[0061] In this embodiment, the loading structure 41 is a spring, and the loading structure 41 maintains a naturally extended state when the dummy rudder surface 20 maintains a horizontal state. The length direction of the spring is not fixedly connected and is in a free state, so as to prevent the dummy rudder surface 20 from exerting force in the opposite direction when the dummy rudder surface 20 moves. Figure 1 In the state shown, the rudder surface dummy 20 is in a horizontal position, that is, the rudder surface is in a zero position, and the spring is in a natural state (no compression).

[0062] When the rudder surface dummy 20 is cut upward (such as Figure 3 As shown in FIG. 1 , the first loading section 411 is compressed, and the second loading section 412 keeps the same length; when the rudder surface dummy 20 is cut downward (as shown in FIG. 1 ), the first loading section 411 is compressed, and the second loading section 412 keeps the same length; Figure 4 As shown), the second loading section 412 is compressed while the first loading section 411 maintains an unchanged length, thereby achieving different simulation test states.

[0063] In another undisclosed embodiment of the present application, the first loading section 411 and the second loading section 412 are both made of rubber material.

[0064] As Figures 1 to 4 As shown in the figure, the loading components 40 are multiple groups, and the multiple groups of loading components 40 are arranged at intervals along the length direction of the dummy rudder surface 20. Of course, the loading components 40 can also be one group, which requires selecting appropriate positions on the dummy rudder surface 20 to set the number of loading components 40 according to the actual load conditions.

[0065] In this embodiment, the simulated loading device for an aircraft further comprises an angle measuring sensor and a load measuring sensor, which are arranged on the base 10 and / or the dummy control surface 20. By arranging the load measuring sensor and the angle measuring sensor, the state of the dummy control surface 20 under the action of the load can be displayed.

[0066] Furthermore, the angle measurement sensor and the load measurement sensor are arranged corresponding to the loading assembly 40. Specifically, a through-axis pressure sensor is selected as the load measurement sensor, and the through-axis pressure sensor sleeve is arranged on the arc rod 421. One end of the through-axis pressure sensor abuts against the rudder dummy 20, and the other end abuts against the loading structure 41, and the detection data is obtained when the rudder dummy 20 receives the abutting force. The angle measurement sensor can be an angle encoder.

[0067] like Figures 1 to 4As shown, the base 10 includes a base body 11 and a mounting plate 12. At least a portion of the drive assembly 30 is disposed on the base body 11. The mounting plate 12 is disposed on the base body 11, and the control surface dummy 20 and the loading assembly 40 are both disposed on the mounting plate 12.

[0068] Specifically, the mounting plate 12 is connected to the side of the base 11; the mounting plate 12 is vertically arranged with the base 11, and the mounting plate 12 and the base 11 are connected by bolts. The rudder surface dummy 20 is connected to the mounting plate 12 by a connecting member 50. Further, the connecting member 50 is a hinge, and of course other pivot connection structures that can realize the rotation of the rudder surface dummy 20 can also be selected.

[0069] In this embodiment, there are multiple mounting plates 12 and multiple loading assemblies 40, and multiple mounting plates 12 are arranged one by one with multiple loading assemblies 40. Multiple mounting plates 12 are arranged on the base body 11 at intervals. The number of connectors 50 needs to be determined according to the number of mounting plates 12. Figure 1 In the illustrated embodiment, there are two mounting plates 12 , and thus a connecting member 50 is disposed on each mounting plate 12 .

[0070] exist Figure 1 In the illustrated embodiment, any rudder surface dummy component 20 is connected to two mounting plates 12 via two connectors 50. Each loading assembly 40 is provided with a corresponding mounting plate 12. The mounting plate 12 is perpendicular to the base body 11, which is helpful for determining the horizontal state of the rudder surface dummy component 20, i.e., simulating the non-working state of the loading device.

[0071] like Figures 1 to 4 As shown, the driving assembly 30 is arranged on the top surface of the seat body 11, driving the dummy control surface 20 to rotate relative to the mounting plate 12. The driving assembly 30 includes a steering engine 31, a swing rod 32, a connecting rod 33 and a connecting seat 34 connected in sequence. The steering engine 31 drives the swing rod 32 to swing. The swing rod 32 and the connecting rod 33, and the connecting rod 33 and the connecting seat 34 are all rotatably connected. The connecting seat 34 is connected and fixed to the dummy control surface 20. The steering engine 31 is a steering engine of the same model installed on the real machine, serving as the power source for the movement of the dummy control surface 20 of the device, and is also one of the test objects of the device.

[0072] Specifically, the steering engine 31 is arranged on the top of the seat body 11, and the connecting seat 34 is fixed to the dummy rudder surface 20 by fasteners. The steering engine 31 drives the swing rod 32 to swing and drives the connecting rod 33 to move, thereby driving the dummy rudder surface 20 connected to the connecting seat 34 to rotate relative to the mounting plate 12. Optionally, the steering engine 31, the swing rod 32, the connecting rod 33 and the connecting seat 34 are all connected by a pin shaft, so that the driving assembly 30 can adjust the angle of the dummy rudder surface 20.

[0073] In this embodiment, the dummy rudder surface 20 is made of an aluminum alloy metal flat plate. The base 10 is composed of an aluminum profile and an aluminum plate, and is used as a bearing mechanism of the simulated loading device for installing the steering gear 31, the dummy rudder surface 20, and the mounting plate 12. The mounting plate 12 is also machined from an aluminum alloy and is used for fixing and installing the connecting piece 50, the arc rod 421, and the dummy rudder surface 20.

[0074] The aircraft test system of the utility model also includes a control system, which is electrically connected to the driving assembly 30 of the simulation loading device. Optionally, the simulation loading devices are multiple and arranged in parallel, and the multiple simulation loading devices are all electrically connected to the control system, so as to verify the stability of the control surface motion mechanism and the control system, realize multiple tests synchronously, improve the versatility of the simulation loading device, and speed up the test efficiency.

[0075] From the above description, it can be seen that the above embodiments of the utility model achieve the following technical effects:

[0076] By setting a driving component 30 on the base 10, one end of the driving component 30 is connected to the rudder surface dummy 20 and can drive the rudder surface dummy 20 to adjust to a preset angle, so that the abutment state between the rudder surface dummy 20 and the loading structure 41 is changed, and the loading load of the rudder surface dummy 20 by the loading structure 41 is adjusted to a preset load, thereby simulating the situation of loading the rudder surface, so as to facilitate the implementation of the aircraft rudder surface loading system test.

[0077] The simulation loading device proposed in the utility model is a device that does not require a 1:1 real rudder surface, and applies abutment force to the rudder surface dummy 20 by compressing the spring on the simulation loading device to simulate the pneumatic hinge torque borne by the rudder surface during movement, thereby verifying the reliability of the operating system and the performance of the steering gear.

[0078] The installation points of the servo 31, the connector 50, and the connector seat 34 in the simulated loading device must completely simulate the relative spatial positions of the real aircraft. At the same time, when designing the loading structure 41 and the dummy rudder 20, the hinge torque during the movement of the rudder and the weight of the rudder of the real aircraft must be matched to ensure the accuracy of the simulated loading test.

[0079] It is obvious to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, the embodiments should be regarded as exemplary and non-restrictive from any point of view, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims be included in the present invention. Any reference numeral in a claim should not be regarded as limiting the claim to which it relates.

[0080] In addition, it should be understood that although the present specification is described according to embodiments, not every embodiment contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A simulation loading device for an aircraft, characterized in that: include: Pedestal; A dummy rudder surface, wherein the dummy rudder surface is pivotally arranged on the base; A driving assembly, wherein the driving assembly is arranged on the base, and a driving end of the driving assembly is drivingly connected to the rudder surface dummy; A loading component is arranged on the base, and the loading component includes a loading structure capable of abutting against the rudder surface dummy, and the loading structure is located on the pivot path of the rudder surface dummy, so that the abutment force between the rudder surface dummy and the loading structure changes after adjusting the rotation angle.

2. The simulation loading device for an aircraft according to claim 1, characterized in that: The loading assembly further comprises a supporting structure, wherein the supporting structure is detachably connected to the base, and the loading structure is arranged on the supporting structure.

3. The simulation loading device for an aircraft according to claim 2, characterized in that: Both ends of the support structure are detachably connected to the base; and / or The support structure is arranged to extend along the pivot path of the rudder surface dummy; and / or The loading structure is sleeved on the supporting structure; and / or The loading structure is an elastic member; and / or The support structure is provided with scale marks along its extension direction.

4. The simulation loading device for an aircraft according to claim 2, characterized in that: A clearance gap is arranged at the free end of the rudder surface dummy, the support structure passes through the clearance gap, and a gap is formed between the clearance gap and the support structure.

5. The simulation loading device for aircraft according to claim 2, characterized in that: The support structure comprises: curved rod; A locking portion is provided at the end of the arc-shaped rod to lock or unlock the arc-shaped rod and the base.

6. The simulation loading device for an aircraft according to claim 2, characterized in that: There are multiple loading structures, and the multiple loading structures can be replaced on the supporting structure; and / or The loading structure is a spring or rubber. When the loading structure is the spring, there are multiple springs, and at least one of the wire diameters, stiffnesses, and lengths of the multiple springs is different.

7. The simulation loading device for an aircraft according to claim 1, characterized in that: The loading structure at least includes a first loading section and a second loading section located on two opposite side surfaces of the rudder surface dummy, and both the first loading section and the second loading section can abut against the rudder surface dummy.

8. The simulation loading device for an aircraft according to claim 1, characterized in that: The loading components are multiple groups, and the multiple groups of loading components are arranged at intervals along the length direction of the rudder surface dummy.

9. The simulation loading device for an aircraft according to claim 1, characterized in that: The simulated loading device for an aircraft further comprises an angle measurement sensor and a load measurement sensor, and the angle measurement sensor and the load measurement sensor are arranged on the base and / or the control surface dummy.

10. The simulation loading device for an aircraft according to any one of claims 1 to 9, characterized in that: The base comprises: a seat body, on which at least a portion of the drive assembly is disposed; A mounting plate is provided on the seat body, and the rudder surface dummy and the loading assembly are both provided on the mounting plate.

11. The simulation loading device for an aircraft according to claim 10, characterized in that: The mounting plate is connected to the side of the seat body; and / or The mounting plate is arranged vertically to the base body; and / or There are multiple mounting plates and multiple loading assemblies, and the multiple mounting plates are arranged in one-to-one correspondence with the multiple loading assemblies. The multiple mounting plates are arranged on the base body at intervals.

12. The simulation loading device for an aircraft according to any one of claims 1 to 9, characterized in that: The driving assembly includes a steering gear, a swing rod, a connecting rod and a connecting seat connected in sequence, the steering gear drives the swing rod to swing, the swing rod and the connecting rod, the connecting rod and the connecting seat are all rotatably connected, and the connecting seat is fixedly connected to the rudder surface dummy.

13. An aircraft test system, characterized in that: A simulation loading device for an aircraft comprising any one of claims 1 to 12.

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