Airplane flap actuator disengagement fault test simulation device

Abstract

The invention provides an airplane flap actuator disengagement fault test simulation device, and belongs to the field of airplane structure test, and the device comprises a support structure which is fixed on a test bench or a wing rear beam simulation part and is used for supporting a flap actuator and a porous clamping drive shaft; the porous clamping driving shaft is mounted in the supporting structure and is used for supporting and restraining the flap actuator; the controllable disengaging mechanism assembly is installed on the supporting structure and controllably connected to the porous clamping driving shaft, and the porous clamping driving shaft can be peripherally limited or peripherally limited can be relieved by controlling the controllable disengaging mechanism assembly; and the end cover assembly is fixedly mounted on the supporting structure and is matched with one end of a non-flap actuator of the multi-hole clamping driving shaft so as to support and limit the multi-hole clamping driving shaft. The device provided by the invention has no rapid heating problem in the disengagement process, is more convenient in clamping position change and installation, and can realize a multi-clamping-position disengagement fault test.

Description

Technical Field

[0001] The present application belongs to the field of aircraft testing, and in particular relates to a device for simulating a test of an aircraft flap actuator disengagement failure. Background Art

[0002] During aircraft flap development, flap actuator disengagement tests are often required. By controlling a disengagement simulator, the flap actuator is "disengaged" with the flaps fixed in position, releasing the rotational constraints imposed by the original structure. During this disengagement simulation, the timing of the disengagement must be controllable, the disengagement process must be safe and reliable, without causing secondary effects, and easy to install and implement. Accurate and controllable simulation of flap actuator disengagement is crucial to the success of this test, and flap actuator disengagement simulators are of great value to aircraft design, analysis, and airworthiness certification.

[0003] During existing flap actuator disengagement failure simulation tests, the flap actuator's rotating shaft is secured by an end cap and explosive bolts. When the explosive bolts break, the rear end cap becomes unsecured, releasing the rotational restraint on the flap actuator's rotating shaft and allowing the actuator to disengage. However, this technical solution has the following disadvantages:

[0004] 1) One set of devices can only simulate the disconnection fault under a single locking position;

[0005] 2) The accurate and synchronous separation of multiple explosive bolts is difficult to control;

[0006] 3) Explosive bolts are controlled items and must be declared before use, making them difficult to obtain;

[0007] 4) During the detonation and fracture process of explosive bolts, the separated bolt components have high impact energy, threatening the safety of test personnel and equipment;

[0008] 5) Explosive bolts generate high temperatures during the explosive separation process, which can easily cause structural deformation and jamming, making it very difficult to change the test state;

[0009] 6) The detonation of explosive bolts requires special equipment and safety protection implementation, and explosive bolts are expensive, which greatly increases the cost of testing. Summary of the Invention

[0010] The purpose of the present application is to provide an aircraft flap actuator disengagement fault test simulation device to solve or alleviate at least one problem in the background technology.

[0011] The technical solution of the present application is: a device for simulating a test of an aircraft flap actuator disengagement failure, comprising:

[0012] Support structure, fixed on the test bench or wing rear spar simulation, used to support the flap actuator and multi-hole locking drive shaft;

[0013] a multi-hole retaining drive shaft mounted in the support structure for supporting and restraining the flap actuator;

[0014] A controllable disengagement mechanism assembly is mounted on the support structure and controllably connected to the multi-hole blocking drive shaft, and the multi-hole blocking drive shaft can be circumferentially limited or released by controlling the controllable disengagement mechanism assembly;

[0015] The end cover assembly is fixedly mounted on the supporting structure and cooperates with the non-flap actuator end of the multi-hole blocking drive shaft to support and limit the multi-hole blocking drive shaft.

[0016] Preferably, the supporting structure includes a back plate and a flange, the back plate is provided with bolt holes, the back plate is mounted on a test bench or a wing rear beam simulation component by fasteners, there are two flanges fixed in parallel on the back plate, a hollow structure with a cylindrical interior is provided between the flanges, the hollow structure is used to install a multi-porous positioning drive shaft, the hollow structure is provided with a mounting boss for fixing a controllable disengagement mechanism component, the middle part of the mounting boss and the hollow structure are provided with through holes, the through holes are connected to the interior of the hollow structure.

[0017] Preferably, one end of the porous locking drive shaft is provided with a gear meshing with the flap actuator, and the other end of the porous locking drive shaft 2 is provided with a step shaft, and the step shaft cooperates with the end cover assembly to achieve support and axial limitation of the porous locking drive shaft, and a plurality of circumferentially distributed strip holes are provided between the gear and the step shaft of the porous locking drive shaft, which are used to fix the flap in different positions to carry out disengagement fault tests under different flap positions.

[0018] Preferably, the back plate, flange, hollow structure and the porous positioning drive shaft in the supporting structure are designed based on the shape and size of the actual structure.

[0019] Preferably, the strip-shaped holes are arranged along the axial direction of the porous positioning drive shaft.

[0020] Preferably, the number of the strip-shaped holes is determined according to the angular interval required for positioning in the test.

[0021] Preferably, the controllable disengagement mechanism assembly includes a fastening positioning pin, a mounting seat, a driving motor and a transition shaft, the mounting seat is mounted on the mounting boss of the supporting structure, the driving motor is mounted on the mounting seat, the fastening positioning pin is arranged in the through hole of the supporting structure, the transition shaft is arranged inside the mounting seat, and the two ends of the transition shaft are respectively connected to the driving motor and the fastening positioning pin, and the fastening positioning pin is driven by the driving motor to move along the axial direction of the through hole, so that the fastening positioning pin is inserted into the gear of the porous positioning driving shaft or pulled out from the gear of the porous positioning driving shaft, thereby realizing the circumferential limitation or release of the circumferential limitation of the porous positioning driving shaft by the controllable disengagement mechanism assembly.

[0022] Preferably, the driving motor is a forward and reverse rotary motor, the transition shaft is a threaded shaft or a shaft with a keyway, the fastening positioning pin is connected to the transition shaft by matching threads or keys, and the mounting seat is internally provided with threads or keyways adapted to the transition shaft. The driving motor is driven to rotate in the forward or reverse direction to drive the transition shaft to move along the axial direction in the mounting seat, thereby realizing the fastening positioning pin to move along the axial direction in the through hole.

[0023] Preferably, the width of the strip-shaped hole is 0.2 mm to 0.5 mm greater than the diameter of the fastening positioning pin.

[0024] The flap actuator multi-position disengagement fault simulation device of the present application does not have the problem of rapid heating during the disengagement process. It has a simple structure, low cost, and is easy to use. The position change and installation are more convenient, and it can realize multi-position disengagement fault testing. Disengagement is achieved through a mechanical device, there is no high-speed impact problem, and the safety is relatively high. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this application.

[0026] Figure 1 This is a schematic diagram of the aircraft flap actuator disengagement failure test simulation device of the present application.

[0027] Figure 2 This is a schematic diagram of the supporting structure in this application.

[0028] Figure 3 This is a schematic diagram of the multi-hole positioning drive shaft in this application.

[0029] Figure 4 This is a schematic diagram of the controllable disengagement mechanism components in this application.

[0030] Figure 5 Schematic diagram of the end cap assembly in this application.

[0031] Reference numerals:

[0032] 1- Support structure

[0033] 11-Back panel

[0034] 12-Flange

[0035] 13-Hollow structure

[0036] 14-Installation boss

[0037] 15-Through hole

[0038] 2-Multi-hole positioning drive shaft

[0039] 21-Gear

[0040] 22-strip hole

[0041] 3-Controllable release mechanism components

[0042] 31-Fixed positioning pin

[0043] 32-Mounting seat

[0044] 33-Drive motor

[0045] 34-Transition shaft

[0046] 4-End cover assembly

[0047] 41-round hole DETAILED DESCRIPTION

[0048] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0049] The present application provides a simpler aircraft flap actuator disengagement fault test simulation device, which on the one hand solves the multi-position simulation problem of the flap actuator disengagement fault test; on the other hand, reduces the difficulty of test design and implementation, improves the safety of the test, and reduces the test cost.

[0050] The aircraft flap actuator disengagement failure simulation device provided in the present application uses a fastenable positioning pin to automatically pull out, thereby releasing the rotation constraint of the flap actuator's multi-hole locking drive shaft, thereby controllably simulating the actuator disengagement failure / failure.

[0051] like Figure 1 As shown, the aircraft flap actuator disengagement fault test simulation device provided by the present application includes a support structure 1, a multi-hole locking drive shaft 2, a controllable disengagement mechanism assembly 3, and an end cover assembly 4.

[0052] like Figure 2The figure shows a schematic diagram of the support structure in the present application. The support structure 1 includes a back plate 11 and a flange 12. Bolt holes are provided on the edges of the back plate 11. The back plate 11 is mounted on a test bench or a wing rear beam simulation component by fasteners to support the flap actuator 5 and the multi-hole positioning drive shaft. There are two flanges 12, which can be fixed to the back plate 11 in parallel by welding. A hollow structure 13 with a cylindrical interior is provided between the two flanges 12. The hollow structure 13 is used to install the multi-hole positioning drive shaft 2. A mounting boss 14 is provided on the upper or lower part of the hollow structure 13. A plurality of threaded holes are provided on the edge of the mounting boss 14, which can be used to fasten and install the controllable disengagement mechanism component 3. In some embodiments of the present application, the mounting boss 14 can be formed by cutting the outer surface of the hollow structure 13. A smooth through hole 15 is provided in the middle of the mounting boss 14 and at a corresponding position of the hollow structure 1 . The through hole 15 is connected to the interior of the hollow structure 13 and is used to cooperate with the fastenable positioning pin 13 of the controllable disengagement mechanism assembly 3 .

[0053] In a preferred embodiment of the present application, the support structure 1 can be designed based on the shape and dimensions of the original real structure. Furthermore, the back plate 11, flange 12, and hollow structure 13 of the support structure 1 can all be made of metal materials. For example, the above structures can be made of Q235 or 45# carbon steel, which is cost-effective and easy to process.

[0054] like Figure 3 Shown is a schematic diagram of the multi-hole locking drive shaft in the present application. The multi-hole locking drive shaft 2 is used to support and constrain the flap actuator 5. In the preferred embodiment of the present application, the strip holes 22 are arranged along the axial direction of the multi-hole locking drive shaft 2.

[0055] like Figure 4 The figure shows a schematic diagram of a controllable disengagement mechanism assembly in the present application, wherein the controllable disengagement mechanism assembly 3 is used to trigger a disengagement fault. The controllable disengagement mechanism assembly 3 includes a fastening pin 31, a mounting seat 32, a drive motor 33, and a transition shaft 34. The mounting seat 32 is mounted on the mounting boss 14 of the support structure 1 by means of fasteners such as bolts. The drive motor 33 is mounted on the mounting seat 32, and the transition shaft 34 is arranged inside the mounting seat 32. The fastening pin 31 is movably arranged in the through hole 15 of the support structure 1, and the two ends of the transition shaft 34 are respectively connected to the drive motor 33 and the fastening pin 31. The drive motor 33 can drive the fastening pin 31 to move along the axial direction of the through hole 15, thereby inserting into or pulling out from the gear 21 of the porous positioning drive shaft 2.

[0056] In some embodiments of the present application, the driving motor 33 may be a telescopic motor, so that it can directly drive the fastening positioning pin 31 to move along the axial direction through the transition shaft 34 .

[0057] In a preferred embodiment of the present application, the drive motor 33 is a rotary motor, and the transition shaft 34 is a threaded shaft or a shaft with a keyway. The fixing pin 31 is connected to the transition shaft 34 by matching threads or keys. The mounting seat 32 is internally provided with threads or keyways adapted to the threaded shaft. The drive motor 33 can rotate forward and reverse. By rotating the drive motor 33 forward or reverse, the transition shaft 34 is driven to move along the axis within the mounting seat 32, and the fixing pin 31 can finally move along the axis within the through hole 15. By using a rotary motor, the drive motor 33 can fit into a smaller space, thereby improving the applicability of the controllable disengagement mechanism assembly 3.

[0058] In the present application, the width of the strip-shaped hole 22 is slightly larger than the diameter of the fastening pin 31, thereby facilitating the fastening pin 13 to be inserted into the strip-shaped hole 22. For example, in some embodiments, the width of the strip-shaped hole 22 may be 0.2 mm to 0.5 mm larger than the diameter of the fastening pin 31. The plurality of strip-shaped holes 22 are evenly distributed in the circumferential direction, and the number of strip-shaped holes 22 can be determined based on the angular spacing required for positioning in the test. For example, if a 30-degree positioning spacing is required in the test, the number of strip-shaped holes 22 can be set to 12.

[0059] like Figure 5 The figure shows a schematic diagram of the end cap assembly in this application. The end cap assembly 4 supports one end of the porous locking drive shaft 2 and seals the support structure 1. A circular hole 41 is provided in the middle of the end cap assembly 4. The diameter of the circular hole 41 is the same as the diameter of the smaller end of the stepped structure of the porous locking drive shaft 2. The edge of the end cap assembly 4 is a flange hole, which can be fixed to the support structure 1 using fasteners.

[0060] The installation and working process of the aircraft flap actuator disengagement fault test simulator of this application are as follows:

[0061] First, the support structure 1 is fixed to the test bench or the wing rear beam simulation component via the back plate 11. The multi-hole locking drive shaft 2 passes through the flange 12 of the support structure 1. Its gear 21 is connected to the flap actuator 5. The smaller end of the stepped structure of the multi-hole locking drive shaft 2 is inserted into the circular hole 41 of the end cover assembly 4. The end cover assembly 4 is fixedly connected to the flange 12 of the support structure 1 via a connector, thereby axially limiting the multi-hole locking drive shaft 2.

[0062] The fastening pin 31 and the driving motor 33 of the controllable disengagement mechanism assembly 3 are respectively connected to the transition shaft 34, and the driving motor 33 is fixed on the mounting seat 32. The fastening pin 31 is inserted into the through hole 15 of the supporting structure 1;

[0063] In the non-disengaged state of the flap actuator 5, the fastening pin of the controllable disengagement mechanism assembly 3 is inserted into a certain strip hole 22 of the multi-hole positioning drive shaft 2. Different strip holes 22 can be used to fix the flap in different set positions for the disengagement test;

[0064] When the driving motor 33 of the controllable disengagement mechanism assembly 3 is controlled to move the fastening positioning pin 31 out of the strip hole 22 of the multi-hole locking drive shaft 2 to simulate the disengagement of the wing actuator 5, the fixation of the multi-hole locking drive shaft 2 can be released to realize the disengagement fault simulation of the flap actuator 5.

[0065] The flap actuator multi-position disengagement fault simulation device of the present application does not have the problem of rapid heating during the disengagement process. It has a simple structure, low cost, and is easy to use. The position change and installation are more convenient, and it can realize multi-position disengagement fault testing. Disengagement is achieved through a mechanical device, there is no high-speed impact problem, and the safety is relatively high.

[0066] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. An aircraft flap actuator disengagement fault test simulator, characterized in that: include: A support structure (1) is fixed on a test bench or a wing rear beam simulation component, and is used to support a flap actuator (5) and a multi-hole locking drive shaft (2); A multi-hole latch drive shaft (2) is installed in the support structure (1) and is used to support and constrain the flap actuator (5); A controllable disengagement mechanism component (3) is mounted on the support structure (1) and controllably connected to the multi-hole locking drive shaft (2). The multi-hole locking drive shaft (2) can be circumferentially limited or released by controlling the controllable disengagement mechanism component (3); An end cover assembly (4) is fixedly mounted on the support structure (1) and cooperates with one end of the non-flap actuator (5) of the multi-hole locking drive shaft (2) to support and limit the multi-hole locking drive shaft (2).

2. The aircraft flap actuator disengagement fault test simulator according to claim 1, characterized in that: The support structure (1) includes a back plate (11) and a flange (12), wherein the back plate (11) is provided with bolt holes, and the back plate (11) is mounted on a test bench or a wing rear beam simulation component by fasteners, and the flanges (12) are two and fixed in parallel on the back plate (11), and a hollow structure (13) with a cylindrical interior is provided between the flanges (12), and the hollow structure (13) is used to install a multi-hole locking drive shaft (2), and a mounting boss (14) for fixing a controllable disengagement mechanism component (3) is provided on the hollow structure (13), and a through hole (15) is provided in the middle of the mounting boss (14) and the hollow structure (1), and the through hole (15) is connected to the interior of the hollow structure (13).

3. The aircraft flap actuator disengagement fault test simulator according to claim 2, characterized in that: One end of the multi-hole locking drive shaft (2) is provided with a gear (21) meshing with the flap actuator (5), and the other end of the multi-hole locking drive shaft 2 is provided with a step shaft, and the step shaft cooperates with the end cover assembly (4) to achieve support and axial limitation of the multi-hole locking drive shaft (2), and a plurality of circumferentially distributed strip holes (22) are provided between the gear (21) and the step shaft of the multi-hole locking drive shaft (2) for fixing the flap in different locking positions to carry out a disengagement fault test under different flap locking positions.

4. The aircraft flap actuator disengagement fault test simulator according to claim 3, characterized in that: The back plate (11), flange (12), hollow structure (13) and the porous positioning drive shaft (2) in the support structure (1) are all designed based on the shape and size of the actual structure.

5. The aircraft flap actuator disengagement fault test simulator according to claim 3, characterized in that: The strip-shaped holes (22) are arranged along the axial direction of the porous locking drive shaft (2).

6. The aircraft flap actuator disengagement fault test simulator according to claim 3, characterized in that: The number of the strip-shaped holes (22) is determined according to the angular interval required for positioning in the test.

7. The aircraft flap actuator disengagement fault test simulator according to claim 3, characterized in that: The controllable disengagement mechanism assembly (3) comprises a fastening positioning pin (31), a mounting seat (32), a driving motor (33) and a transition shaft (34), wherein the mounting seat (32) is mounted on a mounting boss (14) of a support structure (1), the driving motor (33) is mounted on the mounting seat (32), the fastening positioning pin (31) is arranged in a through hole (15) of the support structure (1), the transition shaft (34) is arranged inside the mounting seat (32), and the transition shaft The two ends of (34) are respectively connected to the driving motor (33) and the tightly fixed positioning pin (31), and the driving motor (33) drives the tightly fixed positioning pin (31) to move along the axial direction of the through hole (15), so that the tightly fixed positioning pin (31) is inserted into the gear (21) of the multi-hole blocking driving shaft (2) or pulled out from the gear (21) of the multi-hole blocking driving shaft (2), thereby realizing the circumferential limitation or release of the circumferential limitation of the multi-hole blocking driving shaft (2) by the controllable disengagement mechanism component (3).

8. The aircraft flap actuator disengagement fault test simulator according to claim 7, characterized in that: The driving motor (33) is a forward and reverse rotating motor, the transition shaft (34) is a threaded shaft or a shaft with a keyway, the fastening pin (13) is connected to the transition shaft (34) through matching threads or keys, and the interior of the mounting seat (32) is provided with threads or keyways adapted to the transition shaft (34). The driving motor (33) is rotated in the forward or reverse direction to drive the transition shaft (34) to move along the axial direction in the mounting seat (32), thereby enabling the fastening pin (13) to move along the axial direction in the through hole (15).

9. The aircraft flap actuator disengagement fault test simulator according to claim 7, characterized in that: The width of the strip-shaped hole (22) is 0.2 mm to 0.5 mm greater than the diameter of the fastening positioning pin (13).

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