Fatigue testing device for carbon fiber composite fairing

Abstract

The invention discloses a fatigue testing device for a carbon fiber composite fairing, and relates to the technical field of fatigue testing, and the fatigue testing device comprises a clamping mechanism and a vibration loading mechanism; the clamping mechanism comprises a clamp base and clamping devices, the clamp base is used for placing a fairing, the multiple clamping devices are evenly arranged on the clamp base in the circumferential direction, the clamping devices are arranged around the fairing, the vibration loading mechanism comprises a sliding rail top plate, a sliding groove vertical plate and a vibration loading assembly, and a sliding rail is fixedly arranged at the bottom of the sliding rail top plate; the two ends of the sliding rail are each connected with a sliding groove vertical plate in a sliding mode, the bottom of the sliding rail top plate and the sliding groove vertical plates are each fixedly provided with a mounting plate, and each mounting plate is provided with a vibration loading assembly. The vibration loading assembly comprises a servo motor, a step-up gear box, a rotating disc, an eccentric connecting rod and a vibration sliding rod. According to the invention, broadband multi-direction composite excitation test requirements can be met, and stable lossless clamping of the fairing is realized.

Description

Technical Field

[0001] This invention relates to the field of fatigue testing technology, and in particular to a fatigue testing device for a carbon fiber composite fairing. Background Technology

[0002] As a key component of aerospace launch vehicles, composite material fairings are subjected to long-term broadband and multi-directional aerodynamic vibration loads, leading to fatigue damage and directly affecting flight safety. Accurately simulating the complex vibration conditions in its service environment is the core challenge of fatigue performance evaluation: (1) Load complexity: Low-frequency periodic vibration, high-frequency random vibration, and multi-directional composite excitation exist simultaneously in the actual working environment of the fairing; (2) Clamping difficulties: The fairing is large in size and its curved structure is easily damaged, requiring both stable clamping and non-destructive fixation; (3) Testing limitations: Existing general-purpose fatigue testing devices are difficult to simultaneously achieve broadband multi-directional vibration and lack flexible clamping schemes suitable for large irregular parts. In view of this, we propose a fatigue testing device for composite material fairings to meet the testing requirements of broadband multi-directional composite excitation and achieve stable and non-destructive clamping of the fairing. Summary of the Invention

[0003] The purpose of this invention is to provide a fatigue testing device for carbon fiber composite fairings to solve the problems existing in the prior art, meet the requirements of wide-band multi-directional composite excitation testing, and achieve stable and non-destructive clamping of the fairing.

[0004] To achieve the above objectives, the present invention provides the following solution: This invention provides a fatigue testing device for carbon fiber composite fairings, including a clamping mechanism and a vibration loading mechanism; The clamping mechanism includes a clamp base and clamps. The clamp base is used to place the fairing. Multiple clamps are evenly distributed along the circumference of the clamp base, and each clamp is arranged around the fairing. Each clamp includes a fixed base, a sliding member, a clamping fine-tuning member, an adapter connector, a handle connector, and a handle. The fixed base is fixedly installed on the clamp base. The sliding member is slidably disposed on the fixed base. One end of the sliding member has a threaded hole. One end of the clamping fine-tuning member is threaded into the threaded hole. The other end of the clamping fine-tuning member is used to press against the fairing. The other end of the sliding member is rotatably connected to one end of the adapter connector. The other end of the adapter connector is rotatably connected to the handle connector. One end of the handle connector is rotatably connected to the fixed base, and the other end is fixedly connected to the handle. By turning the handle, the sliding member can be moved, and the clamping fine-tuning member can be moved closer to or away from the fairing. The vibration loading mechanism includes a slide rail top plate, a slide groove vertical plate, and a vibration loading assembly. A slide rail is fixedly mounted on the bottom of the slide rail top plate, and a slide groove vertical plate is slidably connected to each end of the slide rail. A mounting plate is fixedly mounted on the bottom of the slide rail top plate and on each slide groove vertical plate, and a vibration loading assembly is mounted on each mounting plate. The vibration loading assembly includes a servo motor, a speed-increasing gearbox, a turntable, an eccentric connecting rod, and a vibration slide bar. The servo motor is fixed to the mounting plate, and the output shaft of the servo motor is connected to the input shaft of the speed-increasing gearbox. The turntable is fixed to the output shaft of the speed-increasing gearbox. An eccentric shaft is fixed on the turntable. One end of the eccentric connecting rod is rotatably connected to the eccentric shaft, and the other end is rotatably connected to the vibration slide rod. The vibration slide rod is slidably connected to the mounting plate. The vibration slide rod in the vibration loading assembly on the mounting plate located at the bottom of the slide rail top plate is vertically oriented towards the fairing on the fixture base. The vibration slide rod in the vibration loading assembly on the mounting plate connected to the slide rail vertical plate is horizontally oriented towards the fairing on the fixture base.

[0005] In one embodiment, a guide sleeve is fixedly provided on the fixed base, and the sliding member is slidably disposed in the guide sleeve.

[0006] In one embodiment, the clamp base is provided with mounting slots corresponding to each of the clamps, and the fixing seat is provided with multiple bolt through holes. The fixing seat is fixedly connected to the clamp base by bolts passing through the bolt through holes and mounting slots.

[0007] In one embodiment, the mounting slot is an elongated slot.

[0008] In one embodiment, the slide rail is an inverted T-shaped slide rail, and the upper end of the slide groove plate is provided with a slide groove that slides in cooperation with the inverted T-shaped slide rail.

[0009] In one embodiment, the slide rail is provided with a locking bolt hole, the locking bolt hole leads to the slide rail, and a locking bolt is threaded into the locking bolt hole.

[0010] In one embodiment, six grippers are provided.

[0011] In one embodiment, a plurality of support columns are uniformly fixed at the bottom of the fixture base along the circumferential direction.

[0012] In one embodiment, six support columns are provided.

[0013] The present invention achieves the following technical effects compared to the prior art: This invention provides a fatigue testing device for carbon fiber composite fairings. Multiple grippers evenly distributed circumferentially clamp the fairing, and fine-tuning of the clamping points can be achieved using clamping fine-tuning components to ensure consistent clamping force across all grippers, achieving uniform pressure clamping and preventing damage to the fairing due to uneven force distribution. This results in stable and non-destructive clamping of the fairing. Vibration loading components can apply multi-directional vibration excitation to the fairing, and the vibration frequency can be controlled by a servo motor, thus meeting the requirements for wide-band, multi-directional composite excitation testing. Attached Figure Description

[0014] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 This is a schematic diagram of the structure of the carbon fiber composite fairing fatigue testing device in an embodiment of the present invention; Figure 2 This is a schematic diagram of the clamping mechanism in an embodiment of the present invention; Figure 3 This is a schematic diagram of the vibration loading mechanism in an embodiment of the present invention; Figure 4 This is a schematic diagram of the gripper in an embodiment of the present invention; Figure 5 This is a front view of the vibration loading component in an embodiment of the present invention.

[0016] In the diagram: 1-Clamping mechanism, 2-Vibration loading mechanism, 3-Clamping base, 4-Clamper, 5-Fairing, 6-Fixed seat, 7-Sliding component, 8-Clamping fine-tuning component, 9-Adapter connector, 10-Handle connector, 11-Handle, 12-Slide rail top plate, 13-Slide groove upright plate, 14-Vibration loading assembly, 15-Slide rail, 16-Mounting plate, 17-Servo motor, 18-Turntable, 19-Eccentric connecting rod, 20-Vibration slide rod, 21-Eccentric shaft, 22-Guide sleeve, 23-Mounting slot, 24-Bolt, 25-Locking bolt, 26-Support column. Detailed Implementation

[0017] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0018] The purpose of this invention is to provide a fatigue testing device for carbon fiber composite fairings to solve the problems existing in the prior art, meet the requirements of wide-band multi-directional composite excitation testing, and achieve stable and non-destructive clamping of the fairing.

[0019] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0020] like Figures 1-5 As shown, this embodiment provides a fatigue testing device for carbon fiber composite fairings, including a clamping mechanism 1 and a vibration loading mechanism 2; The clamping mechanism 1 includes a clamping base 3 and a clamping device 4. The clamping base 3 is used to place the fairing 5. Multiple clamping devices 4 are evenly distributed along the circumference of the clamping base 3. Each clamping device 4 is arranged around the fairing 5. Each clamping device 4 includes a fixed base 6, a sliding member 7, a clamping fine-tuning member 8, an adapter connector 9, a handle connector 10, and a handle 11. The fixed base 6 is fixedly installed on the clamping base 3. The sliding member 7 is slidably disposed on the fixed base 6. One end of the sliding member 7 is provided with a threaded hole. One end of the clamping fine-tuning member 8 is threadedly connected to the threaded hole. The other end of the clamping fine-tuning member 8 is used to press against the fairing 5. The other end of the sliding member 7 is rotatably connected to one end of the adapter connector 9. The other end of the adapter connector 9 is rotatably connected to the handle connector 10. One end of the handle connector 10 is rotatably connected to the fixed base 6. The other end is fixedly connected to the handle 11. By moving the handle 11, the sliding member 7 can be moved and the clamping fine-tuning member 8 can be moved closer to or away from the fairing 5. The vibration loading mechanism 2 includes a slide rail top plate 12, a slide groove vertical plate 13, and a vibration loading assembly 14. A slide rail 15 is fixedly mounted on the bottom of the slide rail top plate 12, and a slide groove vertical plate 13 is slidably connected to each end of the slide rail 15. A mounting plate 16 is fixedly mounted on the bottom of the slide rail top plate 12 and on each slide groove vertical plate 13, and a vibration loading assembly 14 is mounted on each mounting plate 16. The vibration loading assembly 14 includes a servo motor 17, a speed-increasing gearbox, a turntable 18, an eccentric connecting rod 19, and a vibration slide bar 20. The servo motor 17 is fixed to the mounting plate 16, and the output shaft of the servo motor 17... The turntable 18 is fixed to the output shaft of the speed-increasing gearbox and connected to the input shaft of the speed-increasing gearbox. An eccentric shaft 21 is fixed on the turntable 18. One end of the eccentric connecting rod 19 is rotatably connected to the eccentric shaft 21, and the other end is rotatably connected to the vibration slide rod 20. The vibration slide rod 20 is slidably connected to the mounting plate 16. The vibration slide rod 20 in the vibration loading assembly 14 on the mounting plate 16 located at the bottom of the slide rail top plate 12 is vertically oriented towards the fairing 5 on the fixture base 3. The vibration slide rod 20 in the vibration loading assembly 14 on the mounting plate 16 connected to the slide rail vertical plate 13 is horizontally oriented towards the fairing 5 on the fixture base 3.

[0021] In use, the fairing 5 is placed on the fixture base 3, and the fairing 5 is clamped by the clamps 4. During clamping, the handle 11 is turned to bring the clamping fine-tuning piece 8 closer to the fairing 5. The operation is convenient. The clamping point can be finely adjusted by rotating the clamping fine-tuning piece 8 to ensure that the clamping force of each clamp 4 is consistent, so as to achieve uniform pressure clamping and avoid damage to the fairing 5 caused by local pressure >5 MPa. This achieves stable and non-destructive clamping of the fairing 5. The vibration loading components 14 can perform multi-directional vibration excitation on the fairing 5, and the vibration frequency can be controlled by the servo motor 17, thereby meeting the requirements of wide-frequency multi-directional composite excitation testing. The sliding connection between the slide rail plate 13 and the slide rail top plate 12 facilitates the adjustment of the position of the vibration loading components 14 and is suitable for vibration testing of fairings 5 ​​of different sizes.

[0022] In this embodiment, a guide sleeve 22 is fixedly provided on the fixed base 6, and the sliding member 7 is slidably disposed in the guide sleeve 22 to ensure the sliding stability of the sliding member 7.

[0023] In this embodiment, the fixture base 3 is provided with mounting slots 23 corresponding to each clamp 4, and the fixing base 6 is provided with multiple bolt through holes. Bolts 24 pass through the bolt through holes and mounting slots 23 to fix the fixing base 6 to the fixture base 3. The mounting slots 23 are elongated slots. The radial position of each clamp 4 can be adjusted through the mounting slots 23, making it suitable for clamping fairings 5 ​​of different sizes. It supports testing fairings with diameters of 4000-6000 mm, with a contact pressure deviation of <±10%.

[0024] In this embodiment, the slide rail 15 is an inverted T-shaped slide rail, and the upper end of the slide groove plate 13 is provided with a slide groove that slides in cooperation with the inverted T-shaped slide rail, which can ensure the sliding stability of the slide groove plate 13.

[0025] In this embodiment, the slide rail 13 is provided with locking bolt holes, which lead to the slide rail 15, and locking bolts 25 are threaded into the locking bolt holes. The slide rail 13 can be locked onto the slide rail 15 by tightening the locking bolts 25, thus preventing the vibration loading component 14 from shifting position during vibration testing.

[0026] In this embodiment, six grippers 4 are provided, but other numbers of grippers 4 can be provided depending on the diameter of the fairing 5. Multiple support columns 26 are evenly fixed to the bottom of the clamp base 3 along the circumferential direction. The six support columns 26 enhance the anti-overturning property and evenly distribute the vibration load.

[0027] The carbon fiber composite fairing fatigue testing device provided in this embodiment has a clamping mechanism 1 and a vibration loading mechanism 2 working together to provide a high-precision platform for testing the fatigue performance of composite fairings, effectively improving testing efficiency.

[0028] In this embodiment, a wide frequency vibration of 0.1–100 Hz can be achieved by directly connecting the servo motor 17 to the speed-increasing gearbox. The servo motor 17 drives the turntable 18 to rotate, and the turntable 18 drives the vibration slide bar 20 to vibrate through the eccentric connecting rod 19. This can ensure a constant amplitude and avoid amplitude drift caused by pressure fluctuations in the pneumatic system.

[0029] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A fatigue testing device for carbon fiber composite fairings, characterized in that: Includes a clamping mechanism and a vibration loading mechanism; The clamping mechanism includes a clamp base and clamps. The clamp base is used to place the fairing. Multiple clamps are evenly distributed along the circumference of the clamp base, and each clamp is arranged around the fairing. Each clamp includes a fixed base, a sliding member, a clamping fine-tuning member, an adapter connector, a handle connector, and a handle. The fixed base is fixedly installed on the clamp base. The sliding member is slidably disposed on the fixed base. One end of the sliding member has a threaded hole. One end of the clamping fine-tuning member is threaded into the threaded hole. The other end of the clamping fine-tuning member is used to press against the fairing. The other end of the sliding member is rotatably connected to one end of the adapter connector. The other end of the adapter connector is rotatably connected to the handle connector. One end of the handle connector is rotatably connected to the fixed base, and the other end is fixedly connected to the handle. By turning the handle, the sliding member can be moved, and the clamping fine-tuning member can be moved closer to or away from the fairing. The vibration loading mechanism includes a slide rail top plate, a slide groove vertical plate, and a vibration loading assembly. A slide rail is fixedly mounted on the bottom of the slide rail top plate, and a slide groove vertical plate is slidably connected to each end of the slide rail. A mounting plate is fixedly mounted on the bottom of the slide rail top plate and on each slide groove vertical plate, and a vibration loading assembly is mounted on each mounting plate. The vibration loading assembly includes a servo motor, a speed-increasing gearbox, a turntable, an eccentric connecting rod, and a vibration slide bar. The servo motor is fixed to the mounting plate, and the output shaft of the servo motor is connected to the input shaft of the speed-increasing gearbox. The turntable is fixed to the output shaft of the speed-increasing gearbox. An eccentric shaft is fixed on the turntable. One end of the eccentric connecting rod is rotatably connected to the eccentric shaft, and the other end is rotatably connected to the vibration slide rod. The vibration slide rod is slidably connected to the mounting plate. The vibration slide rod in the vibration loading assembly on the mounting plate located at the bottom of the slide rail top plate is vertically oriented towards the fairing on the fixture base. The vibration slide rod in the vibration loading assembly on the mounting plate connected to the slide rail vertical plate is horizontally oriented towards the fairing on the fixture base.

2. The carbon fiber composite fairing fatigue testing device according to claim 1, characterized in that: A guide sleeve is fixedly provided on the fixed base, and the sliding member is slidably disposed in the guide sleeve.

3. The carbon fiber composite fairing fatigue testing device according to claim 1, characterized in that: The fixture base is provided with mounting slots corresponding to each of the clamps, and the fixing seat is provided with multiple bolt through holes. The fixing seat is fixedly connected to the fixture base by bolts passing through the bolt through holes and mounting slots.

4. The carbon fiber composite fairing fatigue testing device according to claim 3, characterized in that: The mounting slot is a long, narrow slot.

5. The carbon fiber composite fairing fatigue testing device according to claim 1, characterized in that: The slide rail is an inverted T-shaped slide rail, and the upper end of the slide groove plate is provided with a slide groove that slides in cooperation with the inverted T-shaped slide rail.

6. The carbon fiber composite fairing fatigue testing device according to claim 1, characterized in that: The slide rail is provided with locking bolt holes, which lead to the slide rail, and locking bolts are threaded into the locking bolt holes.

7. The fatigue testing device for carbon fiber composite fairings according to claim 1, characterized in that: The clamps are provided in six parts.

8. The carbon fiber composite fairing fatigue testing device according to claim 1, characterized in that: The bottom of the clamp base is uniformly fixed with multiple support columns along the circumferential direction.

9. The carbon fiber composite fairing fatigue testing device according to claim 8, characterized in that: There are six support columns.

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