An experimental table for testing performance of a space instrument thermal control material

Abstract

This utility model relates to the field of aerospace thermal control material testing technology, and more particularly to an experimental platform for testing the performance of thermal control materials for aerospace instruments. This utility model provides an experimental platform for automatically testing the adhesion strength of coatings on thermal control materials for aerospace instruments, saving manpower and improving testing efficiency and accuracy. The experimental platform includes an experimental platform and a first support frame, with two first support frames connected to the upper front side of the experimental platform. This utility model achieves the effect of automatically testing the adhesion strength of coatings on thermal control materials for aerospace instruments by clamping and fixing the thermal control material on the platform, using a moving component to control a scribing tool to slide out a grid pattern on the coating of the thermal control material, then moving the thermal control material under an adhesive tape, automatically adhering to the tape and then tearing it off.

Description

Technical Field

[0001] This utility model relates to the field of aerospace thermal control material testing technology, and in particular to an experimental platform for testing the performance of thermal control materials for aerospace instruments. Background Technology

[0002] In the aerospace field, the thermal control system of spacecraft plays a crucial role in ensuring the normal operation of various instruments and equipment. As a key component of the thermal control system, thermal control material coating can effectively control the operating temperature of instruments and equipment by adjusting the thermal radiation characteristics of the spacecraft surface, ensuring their stable operation in the complex and ever-changing space environment. The bonding strength of the coating is a key indicator for measuring its performance. If the bonding strength is insufficient, the coating may fall off due to severe vibration and impact during the spacecraft launch process.

[0003] The cross-cut test is a relatively simple and effective method for testing the adhesion strength of coatings. It assesses the adhesion strength by making a grid on the coating surface, then sticking and peeling off the tape, and observing the peeling of the coating. It can intuitively reflect the bonding force between the coating and the substrate. The operation is relatively simple and the testing efficiency is relatively high. However, the existing cross-cut test methods are still mainly carried out manually. The testing process is time-consuming and labor-intensive, with low efficiency, and cannot guarantee the accuracy of the tested structure, making it quite inconvenient.

[0004] Therefore, a test bench for testing the performance of thermal control materials for aerospace instruments has been developed that can automatically test the bonding strength of coatings on thermal control materials for aerospace instruments, saving manpower and improving testing efficiency and accuracy. Utility Model Content

[0005] To overcome the shortcomings of existing cross-hatching testing methods, which are still mainly manual, time-consuming, labor-intensive, inefficient, and cannot guarantee the accuracy of the tested structure, this utility model provides an experimental platform for testing the performance of thermal control materials for aerospace instruments. This platform can automatically test the coating adhesion strength of thermal control materials for aerospace instruments, saving manpower and improving testing efficiency and accuracy.

[0006] The technical solution is as follows: An experimental platform for testing the performance of thermal control materials for aerospace instruments includes an experimental platform, a first support frame, a rodless cylinder, a moving component, a scribing tool, a placement platform, a first bidirectional lead screw, a first clamping frame, a second bidirectional lead screw, a second clamping frame, an adhesive application component, and a pressing component. Two first support frames are connected to the upper front part of the experimental platform. A rodless cylinder is connected to the side of each support frame that is close to the other. A moving component is located on the upper right side of the experimental platform, and a scribing tool is mounted on the moving component. A placement platform is connected between the sliders of the rodless cylinders. A first bidirectional lead screw is rotatably connected to the placement platform. The first clamping frame is threaded to both the front and rear ends of the first bidirectional lead screw. A second bidirectional lead screw is also rotatably connected to the placement platform, positioned above the first bidirectional lead screw. Second clamping frames are threaded to both the left and right ends of the second bidirectional lead screw. Both the second clamping frame and the first clamping frame are slidably connected to the placement platform. An adhesive application component for applying adhesive tape is mounted on the first support frame, and a pressing component for pressing the adhesive tape onto the thermal control material is mounted on the experimental platform.

[0007] Optionally, the experimental platform is equipped with four casters.

[0008] Optionally, both the first and second bidirectional lead screws are equipped with knobs.

[0009] Optionally, the adhesive application assembly includes a second support frame, a first motor, a mounting frame, a mounting rod, a first winding drum, a limiting frame, a telescopic spring, a second motor, and a second winding drum. The second support frame is connected to the left side of the rear first support frame, and the first motor is connected to the rear right side of the second support frame. The mounting frame is connected to the output shaft of the first motor. The second motor is connected to the rear left side of the mounting frame, and the mounting rod is connected to the output shaft of the second motor. The mounting rod is also rotatably connected to the front right side of the mounting frame. The first winding drum is sleeved on the left mounting rod, and the second winding drum is sleeved on the right mounting frame. The limiting frame is slidably and rotatably connected to each mounting rod. The limiting frame is connected to the adjacent mounting rod by a telescopic spring. The left limiting frame is engaged with the first winding drum, and the right limiting frame is engaged with the second winding drum.

[0010] Optionally, each mounting rod has a limit groove, and the limiting frame is located in the limit groove to facilitate the locking and limiting of the first winding drum and the second winding drum.

[0011] Optionally, the pressing assembly includes an electric actuator and a pressure plate. The electric actuator is connected to the upper left part of the experimental platform, and the pressure plate is connected to the telescopic end of the electric actuator.

[0012] The beneficial effects are: after the thermal control material is clamped and fixed on the placement platform, the moving component controls the scribing blade to slide out a grid pattern on the coating of the thermal control material, and then the thermal control material is moved under the tape, automatically adhering to the tape and then tearing it off. This achieves the effect of automatically testing the coating adhesion strength of thermal control materials for aerospace instruments, saving manpower and improving testing efficiency and accuracy. Attached Figure Description

[0013] Figure 1 This is a three-dimensional structural diagram of the present invention.

[0014] Figure 2 This is a three-dimensional structural diagram of the experimental platform and moving component of this utility model.

[0015] Figure 3 This is a three-dimensional structural diagram of the placement platform and clamping frame of this utility model.

[0016] Figure 4 This is a three-dimensional structural diagram of the motor and mounting bracket of this utility model.

[0017] Figure 5 This is a three-dimensional structural diagram of the mounting rod and limiting frame of this utility model.

[0018] Explanation of reference numerals in the attached drawings: 1_Experimental table, 2_First support frame, 3_Rodless cylinder, 4_Moving component, 5_Scribber, 6_Placement platform, 7_First bidirectional lead screw, 8_First clamping frame, 9_Second bidirectional lead screw, 10_Second clamping frame, 11_Second support frame, 12_First motor, 13_Mounting frame, 14_Mounting rod, 15_First winding drum, 16_Restriction frame, 17_Telescopic spring, 18_Second motor, 19_Second winding drum, 20_Electric actuator, 21_Pressure plate. Detailed Implementation

[0019] The following description is only a preferred embodiment of the present invention and does not limit the scope of protection of the present invention.

[0020] An experimental platform for testing the performance of thermal control materials for aerospace instruments, such as Figures 1-5As shown, the apparatus includes an experimental table 1, a first support frame 2, a rodless cylinder 3, a moving assembly 4, a scribing blade 5, a placement table 6, a first bidirectional lead screw 7, a first clamping frame 8, a second bidirectional lead screw 9, a second clamping frame 10, an adhesive application assembly, and a pressing assembly. The experimental table 1 has two first support frames 2 connected to its front upper side. The experimental table 1 is equipped with four casters for easy movement. Rodless cylinders 3 are connected to the adjacent sides of the first support frames 2. A moving assembly 4 is located on the upper right side of the experimental table 1, and a scribing blade 5 is mounted on the moving assembly 4. A placement table 6 connects the sliders of the rodless cylinders 3. A first bidirectional lead screw 7 is rotatably connected to the placement platform 6. The first bidirectional lead screw 7 is threadedly connected to the first clamping frame 8 at both the front and rear ends. A second bidirectional lead screw 9 is also rotatably connected to the placement platform 6. The second bidirectional lead screw 9 is located above the first bidirectional lead screw 7. The second bidirectional lead screw 9 is threadedly connected to the second clamping frame 10 at both the left and right ends. The second clamping frame 10 and the first clamping frame 8 are slidably connected to the placement platform 6. Both the first bidirectional lead screw 7 and the second bidirectional lead screw 9 are equipped with knobs for easy rotation. The first support frame 2 is equipped with an adhesive application component, and the experimental table 1 is equipped with a pressing component.

[0021] like Figure 1 , Figure 4 and Figure 5 As shown, the adhesive application assembly includes a second support frame 11, a first motor 12, a mounting frame 13, a mounting rod 14, a first winding drum 15, a limiting frame 16, a telescopic spring 17, a second motor 18, and a second winding drum 19. The second support frame 11 is connected to the left side of the rear first support frame 2. The first motor 12 is connected to the rear right side of the second support frame 11. The mounting frame 13 is connected to the output shaft of the first motor 12. The second motor 18 is connected to the rear left side of the mounting frame 13. The mounting rod 14 is connected to the output shaft of the second motor 18. The mounting rod 14 is also connected to the front right side of the mounting frame 13. The mounting rod 14 is connected to the first winding drum 15 on the left side of the mounting rod 14 and the second winding drum 19 on the right side of the mounting bracket 13. Each mounting rod 14 is slidably and rotatably connected to a limiting bracket 16. Each limiting bracket 16 is connected to an adjacent mounting rod 14 by a telescopic spring 17. The left limiting bracket 16 is engaged with the first winding drum 15, and the right limiting bracket 16 is engaged with the second winding drum 19. Each mounting rod 14 has a limiting groove, and the limiting bracket 16 is located in the limiting groove, which facilitates the locking and limiting of the first winding drum 15 and the second winding drum 19.

[0022] like Figure 1 As shown, the pressing assembly includes an electric push rod 20 and a pressure plate 21. The electric push rod 20 is connected to the upper left part of the experimental table 1, and the pressure plate 21 is connected to the telescopic end of the electric push rod 20.

[0023] When using this invention, firstly, the experimental platform 1 is moved to the area for testing the coating adhesion strength of thermal control materials for aerospace instruments. The tape to be tested is wound between the first winding drum 15 and the second winding drum 19. Then, the first bidirectional lead screw 7 is rotated, causing the first clamping frame 8 to slide open. Next, the second bidirectional lead screw 9 is rotated, causing the second clamping frame 10 to also slide open. The thermal control material to be tested is then placed on the placement platform 6. Then, the first bidirectional lead screw 7 and the second bidirectional lead screw 9 are rotated in the opposite direction, causing the first clamping frame 8 and the second clamping frame 10 to slide inward to clamp and fix the thermal control material on the placement platform 6. After the thermal control material is clamped and fixed, the scriber 5 is moved by the moving component 4, causing the scriber 5 to scribe the required grid pattern on the coating surface of the thermal control material. After scribing, the placement platform 6 is moved to the left of the first support frame 2 by the rodless cylinder 3, causing the thermal control material on the placement platform 6 to move below the tape. The second motor 18 can then be started. The mounting rod 14 on the left rotates, causing the first winding drum 15 to rotate. This pulls the new tape on the second winding drum 19 to move above the thermal control material. Then, the electric actuator 20 is activated, causing its telescopic end to extend and the pressure plate 21 to move downward, pressing the tape onto the coating of the thermal control material. After 30 seconds, the first motor 12 is activated, causing the mounting bracket 13 to rotate and tear the tape from the surface of the thermal control material. By observing whether the coating near the cut of the scribe 5 has peeled off, the adhesion strength of the coating can be determined. This allows for automatic testing of the adhesion strength of the coating of the thermal control material of aerospace instruments, saving manpower and improving testing efficiency and accuracy. When the tape needs to be removed and replaced, the limiting bracket 16 can be pulled outward and rotated so that it aligns with the limiting grooves of the first winding drum 15 and the second winding drum 19. Then, the first winding drum 15 and the second winding drum 19 can be removed and the tape replaced.

[0024] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. An experimental platform for testing the performance of thermal control materials for aerospace instruments, characterized in that, The experimental table (1), first support frame (2), rodless cylinder (3), moving component (4), scriber (5), placement table (6), first bidirectional lead screw (7), first clamping frame (8), second bidirectional lead screw (9), second clamping frame (10), adhesive application component and pressing component are provided. The front upper part of the experimental table (1) is connected to two front and rear first support frames (2). The rodless cylinder (3) is connected to the side of the first support frame (2) that is close to each other. The moving component (4) is provided on the right upper part of the experimental table (1). The scriber (5) is provided on the moving component (4). The placement table (6) is connected between the sliders of the rodless cylinder (3). The first bidirectional lead screw (7) is rotatably connected to the placement platform (6). The first bidirectional lead screw (7) is threadedly connected to the first clamping frame (8) at both the front and rear ends. The second bidirectional lead screw (9) is also rotatably connected to the placement platform (6). The second bidirectional lead screw (9) is located above the first bidirectional lead screw (7). The second bidirectional lead screw (9) is threadedly connected to the second clamping frame (10) at both the left and right ends. The second clamping frame (10) and the first clamping frame (8) are slidably connected to the placement platform (6). The first support frame (2) is equipped with an adhesive tape applicator. The experimental platform (1) is equipped with a pressing component that can press the tape onto the thermal control material.

2. The experimental platform for testing the performance of thermal control materials for aerospace instruments according to claim 1, characterized in that, The experimental table (1) is equipped with four casters.

3. The experimental platform for testing the performance of thermal control materials for aerospace instruments according to claim 1, characterized in that, Both the first bidirectional lead screw (7) and the second bidirectional lead screw (9) are equipped with knobs.

4. The experimental platform for testing the performance of thermal control materials for aerospace instruments according to claim 1, characterized in that, The adhesive application assembly includes a second support frame (11), a first motor (12), a mounting frame (13), a mounting rod (14), a first winding drum (15), a limiting frame (16), a telescopic spring (17), a second motor (18), and a second winding drum (19). The second support frame (11) is connected to the left side of the rear first support frame (2), and the first motor (12) is connected to the rear right side of the second support frame (11). The mounting frame (13) is connected to the output shaft of the first motor (12), and the second motor (18) is connected to the rear left side of the mounting frame (13). The second motor (18) outputs... A mounting rod (14) is connected to the output shaft. A mounting rod (14) is also rotatably connected to the front right side of the mounting frame (13). A first winding drum (15) is sleeved on the mounting rod (14) on the left side. A second winding drum (19) is sleeved on the mounting frame (13) on the right side. A limiting frame (16) is slidably and rotatably connected to each mounting rod (14). A telescopic spring (17) is connected between each limiting frame (16) and the adjacent mounting rod (14). The limiting frame (16) on the left side is engaged with the first winding drum (15), and the limiting frame (16) on the right side is engaged with the second winding drum (19).

5. The experimental platform for testing the performance of thermal control materials for aerospace instruments according to claim 4, characterized in that, Each mounting rod (14) has a limit groove, and each limiting frame (16) is located within the limit groove.

6. The experimental platform for testing the performance of thermal control materials for aerospace instruments according to claim 1, characterized in that, The pressing assembly includes an electric push rod (20) and a pressure plate (21). The electric push rod (20) is connected to the upper left part of the experimental table (1), and the pressure plate (21) is connected to the telescopic end of the electric push rod (20).

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