Aerospace material multi-temperature-zone synchronous fatigue testing machine with active anti-interference structure

Abstract

The invention discloses a spaceflight material multi-temperature-zone synchronous fatigue testing machine with an active anti-interference structure, and relates to the technical field of spaceflight material fatigue testing. The invention aims to solve the problem that a fatigue test generates a load error due to vibration interference and thermal coupling interference between an application action of a mechanical load in a single temperature zone and temperature change of the temperature zone. Comprising at least three independent temperature boxes arranged on a bearing seat; by constructing an integrated active anti-interference system of'rigid foundation + active vibration isolation + multilayer mechanical isolation + negative pressure heat insulation ', vibration interference in the loading process and thermal coupling interference in a temperature zone are effectively counteracted, and the temperature zone isolation effect and the temperature field stability are improved; meanwhile, through collaborative synchronous control design, precise collaboration of multi-temperature-zone temperature dynamic change and load periodic application is achieved, the multi-temperature-zone complex working conditions of actual service of the material can be truly simulated, the fatigue failure process of the material is accurately reduced, and the authenticity and accuracy of test data are remarkably improved.

Description

Technical Field

[0001] This invention relates to the field of fatigue testing technology, and more specifically to a multi-temperature zone synchronous fatigue testing machine for aerospace materials with an active anti-interference structure. Background Technology

[0002] During actual service, aerospace materials are often in complex environments with alternating or synchronous effects of multiple temperature zones, and are subjected to cyclic loads. Their fatigue performance is directly related to the operational safety of the spacecraft. Therefore, conducting synchronous fatigue testing in multiple temperature zones is a key step in evaluating the reliability of aerospace materials.

[0003] Referring to the patent content disclosed in patent application number 201610411976.7, a temperature-controlled fatigue testing instrument, it can perform rapid and repeated temperature cycling tests under different mechanical loads, and has the characteristics of simple structure, low energy consumption, rapid heating and cooling, and the ability to perform high-cycle or ultra-high-cycle cycling tests. However, it does not have a multi-temperature zone setting, and only performs temperature cycling tests in a single temperature zone. Furthermore, the vibration interference and thermal coupling interference that occur between the application of mechanical load and the temperature change in the temperature zone will directly lead to load errors in fatigue testing, thus failing to accurately reflect the fatigue performance of the material. Therefore, this application proposes a solution. Summary of the Invention

[0004] The purpose of this invention is to provide a multi-temperature zone synchronous fatigue testing machine for aerospace materials with an active anti-interference structure, which can solve the problem that vibration interference and thermal coupling interference between the application of mechanical load and temperature changes in a single temperature zone can cause load errors in fatigue testing.

[0005] The objective of this invention can be achieved through the following technical solution: a multi-temperature zone synchronous fatigue testing machine for aerospace materials with an active anti-interference structure, comprising at least three independent temperature chambers mounted on a support base, wherein each independent temperature chamber is equipped with a temperature control element plate, and infrared heating tubes for precise temperature control within the independent temperature chamber are distributed on the temperature control element plate; a specimen support plate is mounted on the temperature control element plate, and the specimen support plate has spaced positioning grooves, each positioning groove being symmetrically equipped with a locking clamp; a chamber cover is mounted on the upper end of each independent temperature chamber; a load application assembly is provided on the chamber cover, the load application assembly including a reciprocating disk rotatably mounted in the middle of the chamber cover, and a stress rod extending to the specimen support plate is mounted on the bottom of the reciprocating disk.

[0006] The configuration is further defined as follows: a drive mechanism for driving the reciprocating wheel to rotate is installed on the outer side of the box cover. The drive mechanism includes a drive assembly, a transmission assembly, and a connecting rod assembly. The output end of the connecting rod assembly is connected to a crank turntable. The drive assembly drives the transmission assembly to move reciprocally in a linear motion. The transmission assembly drives the crank turntable to rotate reciprocally through the connecting rod assembly.

[0007] A further configuration is provided: a rotating rod is connected to the inner side of the crank turntable, and the rotating rod is rotatably disposed in the middle of the cover and axially connected to the reciprocating wheel.

[0008] The reciprocating disc is further configured such that a mounting rod is horizontally arranged at the bottom, and stress rods are spaced apart at the bottom of the mounting rod, with the stress rods and positioning grooves intersecting each other.

[0009] The specimen support plate is further configured such that its cross-section is arc-shaped, and the reciprocating oscillation trajectory of the stress rod runs along the upper side of the specimen support plate.

[0010] The stress bar is further configured such that its lower end is an arc-shaped structure and does not contact the upper surface of the specimen support plate.

[0011] Further configuration: the outer surface of the independent temperature chamber is covered with heat dissipation fins, and a buffer seat is installed at the bottom of the support base.

[0012] The design further includes: a pressure sensor is embedded in the inner side of the locking clip corresponding to the specimen, and temperature sensors are evenly distributed in the independent temperature chamber.

[0013] A method for synchronous fatigue testing of aerospace materials with active anti-interference structures in multiple temperature zones includes the following steps:

[0014] The lids of each independent temperature chamber are opened by hoisting, and tubular or plate-shaped specimens are placed on the specimen support plate before the lids are closed. The drive assembly is activated to rotate the reciprocating wheel, causing the stress rod to swing back and forth and impact the specimen surface on the specimen support plate, thus completing the load application process. At the same time, the infrared heating tubes in the temperature control element board in each independent temperature chamber are energized and the temperature is set in stages, thereby applying different temperature zones to the specimens in different independent temperature chambers. In each independent temperature chamber, the specimens in different temperature zones receive the same stress loading, and fatigue test data are acquired in real time through temperature and pressure sensors.

[0015] The present invention has the following beneficial effects:

[0016] 1. This invention addresses the problem of load errors in fatigue testing caused by vibration interference and thermal coupling interference between the application of mechanical loads and temperature changes within a single temperature zone. By constructing an integrated active anti-interference system of "rigid foundation + active vibration isolation + multi-layer mechanical isolation + negative pressure thermal insulation," it effectively counteracts vibration interference and thermal coupling interference between temperature zones during the loading process, improving the temperature zone isolation effect and temperature field stability. Simultaneously, through collaborative synchronous control design, it achieves precise coordination between dynamic temperature changes in multiple temperature zones and periodic load application, realistically simulating the complex multi-temperature zone working conditions of materials in actual service, accurately reproducing the fatigue failure process of raw materials, and significantly improving the authenticity and accuracy of test data.

[0017] 2. Through the design of adjustable clamping, elastic buffering and precise guiding structure, it can flexibly adapt to aerospace material specimens of different specifications, reduce clamping stress concentration and improve the versatility of the equipment; and the high-strength rigid bearing seat reduces its own deformation, while the active vibration isolator and the buffer seat work together to offset the vibration generated during loading and the interference of external environmental vibration; the heat insulation material of the independent temperature chamber and the heat dissipation fins form a multi-layer mechanical isolation and negative pressure heat insulation structure, blocking heat conduction between temperature zones and avoiding thermal coupling interference. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art 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.

[0019] Figure 1 This is a schematic diagram of the structure of the present invention;

[0020] Figure 2 This is a schematic diagram of the internal structure of the independent temperature zone of the present invention;

[0021] Figure 3 This is a side sectional view of the present invention;

[0022] Figure 4 This is a cross-sectional view of the present invention with the middle of the independent temperature zone as the cross-section;

[0023] Figure 5 This is a schematic diagram of the load application mechanism of the present invention;

[0024] Figure 6 This is a schematic diagram of the installation of the force-applying end of the load-applying mechanism of the present invention;

[0025] Figure 7 This is a schematic diagram of the lifting of the lid of each independent temperature chamber in this invention.

[0026] In the diagram: 1. Independent temperature chamber; 2. Support base; 3. Chamber cover; 4. Buffer seat; 5. Temperature control element plate; 6. Specimen tray; 7. Positioning groove; 8. Mounting rod; 9. Stress rod; 10. Locking clamp; 11. Reciprocating wheel; 12. Rotating rod; 13. Heat dissipation fins; 14. Crank turntable; 15. Connecting rod assembly; 16. Transmission assembly; 17. Drive assembly. Detailed Implementation

[0027] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. 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.

[0028] Example 1

[0029] To address the issue of load errors in fatigue testing caused by vibration interference and thermal coupling interference between the application of mechanical loads and temperature changes within a single temperature zone, the following technical solution is proposed:

[0030] Reference Figure 1 - Figure 7 As shown, the aerospace material multi-temperature zone synchronous fatigue testing machine with an active anti-interference structure in this embodiment includes at least three independent temperature chambers 1 mounted on a support 2. Each independent temperature chamber 1 is equipped with a temperature control element plate 5, on which infrared heating tubes for precise temperature control within the independent temperature chamber 1 are distributed. A buffer seat 4 is installed at the bottom of the support 2. The support 2 is integrally cast from high-strength cast iron, with a cross-shaped reinforcing rib structure added to the bottom, and undergoes double aging treatment to eliminate internal stress. The buffer seat 4 is installed at the bottom of the support 2, and a buffer seat 4 is also installed between the support 2 and the ground. Four sets of electromagnetic active vibration isolators are symmetrically arranged, with a matching guide and limit sleeve mechanical structure. The vibration isolators are rigidly fixed to the bearing seat 2 and the ground through flanges and with the help of buffer rubber pads to form an integrated anti-interference foundation of "rigid foundation + active vibration isolation". The principle is that the high-strength rigid bearing seat 2 reduces its own deformation, and the active vibration isolator and the buffer seat work together to offset the vibration generated during the loading process and the vibration interference from the external environment. The heat insulation material of the independent temperature box 1 and the heat dissipation fins 13 form a multi-layer mechanical isolation and negative pressure heat insulation structure to block heat conduction between temperature zones and avoid thermal coupling interference.

[0031] Reference Figure 2 , Figure 3 and Figure 6As shown, a specimen tray 6 is mounted on the temperature control element plate 5. The specimen tray 6 has spaced positioning grooves 7, and a locking clip 10 is symmetrically installed in each positioning groove 7. A lid 3 is installed on the top of the independent temperature chamber 1. After the independent temperature chamber 1 is covered by the lid 3, it forms a sealed state. A negative pressure suction system (not shown in the figure) is attached to the outside of the chamber to maintain the internal cavity pressure, ensuring that the fatigue test process is free from pressure interference that could lead to inaccurate fatigue testing. Infrared sensors for precise temperature control are distributed on the temperature control element plate 5. The heat pipe is equipped with a semiconductor cooler (not shown in the figure); the temperature control element is detachably mounted on the temperature control element plate 5 via a mechanical bracket. The semiconductor cooler is attached to the heat dissipation fins 13 on the outside of the independent temperature chamber 1 to achieve rapid cooling. The infrared heating tubes are evenly distributed inside the independent temperature chamber 1 to achieve precise temperature control. The principle is that the infrared heating tubes achieve rapid heating, and the semiconductor cooler works with the heat dissipation fins 13 to achieve rapid cooling. The two work together, and through the uniform layout of the temperature control element plate 5, the temperature field inside each independent temperature chamber 1 is kept stable to meet the requirements of different test temperature zones.

[0032] Reference Figure 2 and Figure 6 As shown, a load application assembly is provided on the box cover 3. The load application assembly includes a reciprocating wheel 11 rotatably disposed in the middle of the box cover 3. A stress rod 9 extending to the specimen support plate 6 is installed at the bottom of the reciprocating wheel 11. An installation rod 8 is horizontally disposed at the bottom of the reciprocating wheel 11. The stress rod 9 is spaced at the bottom of the installation rod 8 and is staggered with the positioning groove 7. The cross section of the specimen support plate 6 is arc-shaped. The reciprocating swing trajectory of the stress rod 9 is along the upper side of the specimen support plate 6. The lower end of the stress rod 9 is an arc-shaped structure and does not contact the upper surface of the specimen support plate 6.

[0033] The principle is as follows: the matching design of the arc-shaped specimen support plate 6 and the stress rod 9 makes the reciprocating swing trajectory of the stress rod 9 fit the surface of the specimen, ensuring the accurate application of the load; the staggered distribution and non-contact installation of the stress rod 9 and the positioning groove 7 ensure that the load is applied evenly to the specimen, while avoiding additional friction interference.

[0034] Basic principle: This invention constructs an integrated active anti-interference system consisting of a rigid foundation, active vibration isolation, multi-layer mechanical isolation, and negative pressure thermal insulation. This system effectively counteracts vibration interference during loading and thermal coupling interference within temperature zones, improving temperature zone isolation and temperature field stability. Simultaneously, through collaborative synchronous control design, it achieves precise coordination between dynamic temperature changes in multiple temperature zones and periodic load application. This realistically simulates the complex multi-temperature zone working conditions of materials in actual service, accurately reproduces the fatigue failure process of raw materials, and significantly improves the authenticity and accuracy of test data.

[0035] Example 2

[0036] Reference Figure 1 - Figure 7 As shown, the load applied to each independent temperature chamber 1 is driven by the following method: a drive mechanism for driving the reciprocating wheel 11 to rotate is installed on the outer side of the chamber cover 3. The drive mechanism includes a drive assembly 17, a transmission assembly 16, and a connecting rod assembly 15. The output end of the connecting rod assembly 15 is connected to a crank turntable 14. The drive assembly 17 drives the transmission assembly 16 to move reciprocally in a linear motion. The transmission assembly 16 drives the crank turntable 14 to rotate reciprocally through the connecting rod assembly 15. A rotating rod 12 is connected to the inner side of the crank turntable 14. The rotating rod 12 is rotatably disposed in the middle of the chamber cover 3 and is axially connected to the reciprocating wheel 11.

[0037] The outer surface of the independent temperature chamber 1 is covered with heat dissipation fins 13, and the locking clip 10 is fitted with a pressure sensor on the inner side of the specimen. Temperature sensors are evenly distributed in the independent temperature chamber 1.

[0038] For the load application process in the independent temperature chamber 1, the reciprocating wheel 11 is rotated in conjunction with the crank rocker structure, which in turn drives the stress rod 9 at the output end to swing back and forth and be applied to the specimen. By detecting the stress on the specimen, the dynamic temperature change of multiple temperature zones and the periodic application of load are accurately synchronized, providing real-time and reliable data support for the evaluation of material fatigue performance.

[0039] Example 3

[0040] Reference Figure 1 - Figure 7 As shown, this embodiment combines the technical content of Embodiment 1 and Embodiment 2 to form a method for synchronous fatigue testing of aerospace materials in multiple temperature zones with an active anti-interference structure, including the following steps:

[0041] The lid 3 of each independent temperature chamber 1 is opened by hoisting, and the tubular or plate-shaped specimens are placed on the specimen support plate 6 before the lid 3 is closed. At this time, the independent temperature chamber 1 is sealed, and the air extraction system is started to maintain the pressure inside the independent temperature chamber 1.

[0042] The drive assembly 17 drives the reciprocating wheel 11 to rotate, causing the stress rod 9 to swing back and forth and impact the specimen surface on the specimen support plate 6. Specifically, the transmission assembly 16 and the connecting rod assembly 15 drive the crank turntable 14 to rotate back and forth, which in turn drives the reciprocating wheel 11 to rotate through the rotating rod 12, causing the stress rod 9 to swing back and forth along the upper side of the specimen support plate 6 and impact the specimen surface, thus completing the periodic load application. The vibration interference generated during the loading process is offset in real time by the active vibration isolator, thus completing the load application process.

[0043] At the same time, the infrared heating tube in the temperature control element board 5 in each independent temperature chamber 1 is powered on and the temperature is set in stages, so that different temperature zones are applied to the specimens in different independent temperature chambers 1. After setting the target temperature of different independent temperature chambers 1 according to the test conditions, the temperature field uniformity is monitored in real time by the temperature sensor.

[0044] In each independent temperature chamber 1, specimens in different temperature zones are subjected to the same stress loading. Fatigue test data are acquired in real time through temperature and pressure sensors. Specifically, the system automatically alarms and stops operation when the temperature deviation exceeds ±5℃, the load fluctuation exceeds ±5%, or the specimen breaks. At the same time, the output power of the temperature control element and the drive parameters of the loading mechanism in each temperature zone are adjusted in real time through a collaborative synchronization algorithm to ensure that the temperature change in the temperature zone is synchronized with the load application.

[0045] In summary, combining Embodiments 1, 2, and 3, this invention constructs an integrated active anti-interference system consisting of a rigid foundation, active vibration isolation, multi-layer mechanical isolation, and negative pressure thermal insulation. This effectively counteracts vibration interference during loading and thermal coupling interference within temperature zones, significantly improving temperature zone isolation and temperature field stability. Simultaneously, through a collaborative synchronous control design, it achieves precise coordination between dynamic temperature changes in multiple temperature zones and periodic load application. This realistically simulates the complex multi-temperature zone operating conditions of materials in actual service, accurately reproducing the fatigue failure process of raw materials and significantly improving the authenticity and accuracy of test data.

[0046] The above description is merely an example and illustration of the structure of the present invention. Those skilled in the art can make various modifications or additions to the specific embodiments described, or use similar methods to replace them, as long as they do not deviate from the structure of the invention or exceed the scope defined in the claims, all of which should fall within the protection scope of the present invention.

[0047] In the description of this specification, references to terms such as "an embodiment," "example," and "specific example" indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0048] The preferred embodiments of the present invention disclosed above are merely illustrative of the invention. These preferred embodiments do not exhaustively describe all details, nor do they limit the invention to specific implementations. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention. The invention is limited only by the claims and their full scope and equivalents.

Claims

1. A multi-temperature zone synchronous fatigue testing machine for aerospace materials with an active anti-interference structure, comprising at least three independent temperature chambers (1) mounted on a support (2), characterized in that, The independent temperature chamber (1) is equipped with a temperature control element plate (5), and infrared heating tubes for precise temperature control in the independent temperature chamber (1) are distributed on the temperature control element plate (5); a specimen tray (6) is installed on the temperature control element plate (5), and a positioning groove (7) is provided on the specimen tray (6) at intervals. A locking clip (10) is symmetrically installed in each positioning groove (7). A box cover (3) is installed at the top of the independent temperature chamber (1). The box cover (3) is provided with a load application component, which includes a reciprocating wheel (11) rotatably disposed in the middle of the box cover (3), and a stress rod (9) extending to the specimen support plate (6) is installed at the bottom of the reciprocating wheel (11).

2. The aerospace material multi-temperature zone synchronous fatigue testing machine with an active anti-interference structure according to claim 1, characterized in that, The outer side of the box cover (3) is equipped with a drive mechanism for driving the reciprocating wheel (11) to rotate back and forth. The drive mechanism includes a drive assembly (17), a transmission assembly (16), and a connecting rod assembly (15). The output end of the connecting rod assembly (15) is connected to a crank turntable (14). The drive assembly (17) drives the transmission assembly (16) to move back and forth linearly. The transmission assembly (16) drives the crank turntable (14) to rotate back and forth through the connecting rod assembly (15).

3. The aerospace material multi-temperature zone synchronous fatigue testing machine with an active anti-interference structure according to claim 2, characterized in that, The inner side of the crank turntable (14) is connected to a rotating rod (12), which is rotatably located in the middle of the cover (3) and axially connected to the reciprocating wheel (11).

4. The aerospace material multi-temperature zone synchronous fatigue testing machine with an active anti-interference structure according to claim 1, characterized in that, The bottom of the reciprocating wheel (11) is provided with a horizontal mounting rod (8), and the stress rods (9) are spaced apart at the bottom of the mounting rods (8), and the stress rods (9) are staggered with the positioning grooves (7).

5. The aerospace material multi-temperature zone synchronous fatigue testing machine with an active anti-interference structure according to claim 1, characterized in that, The cross-section of the specimen support plate (6) is arc-shaped, and the reciprocating swing trajectory of the stress rod (9) is along the upper side of the specimen support plate (6).

6. The aerospace material multi-temperature zone synchronous fatigue testing machine with an active anti-interference structure according to claim 5, characterized in that, The lower end of the stress rod (9) is an arc-shaped structure, and the lower end of the stress rod (9) does not contact the upper surface of the specimen support plate (6).

7. The aerospace material multi-temperature zone synchronous fatigue testing machine with an active anti-interference structure according to claim 1, characterized in that, The outer surface of the independent temperature chamber (1) is covered with heat dissipation fins (13), and the bottom of the support seat (2) is equipped with a buffer seat (4).

8. The aerospace material multi-temperature zone synchronous fatigue testing machine with an active anti-interference structure according to claim 1, characterized in that, The locking clip (10) is fitted with a pressure sensor on the inner side of the specimen, and the independent temperature chamber (1) is uniformly distributed with temperature sensors.

9. The aerospace material multi-temperature zone synchronous fatigue testing machine with an active anti-interference structure according to any one of claims 1-8, characterized in that, The method for synchronous fatigue testing of aerospace materials with active anti-interference structure in multiple temperature zones includes the following steps: The lid (3) of each independent temperature chamber (1) is opened by hoisting, and the tubular or plate-shaped specimens are placed on the specimen support plate (6) and then the lid (3) is closed. The reciprocating wheel (11) is rotated by starting the drive assembly (17), so that the stress rod (9) swings back and forth and hits the specimen surface on the specimen support plate (6) to complete the load application process. At the same time, the infrared heating tube in the temperature control element plate (5) in each independent temperature chamber (1) is energized and the temperature is set in stages, so that different temperature zones are applied to the specimens in different independent temperature chambers (1). In each independent temperature chamber (1), the specimens in different temperature zones are subjected to the same stress loading, and fatigue test data are obtained in real time through temperature sensors and pressure sensors.

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