Airship assembly mechanical test system

Abstract

The invention discloses an airship assembly mechanical test system used for testing an airship flange assembly, the airship flange assembly comprises a skin and a flange which are connected, and the airship assembly mechanical test system relates to the technical field of airships. The airship assembly mechanical test system comprises a temperature control box and a loading mechanism, wherein the temperature control box comprises a cavity and a temperature control assembly; the temperature control assembly is used for adjusting the temperature in the cavity; the cavity is used for containing an airship flange assembly. The loading mechanism comprises a first loading assembly and a connecting assembly, the connecting assembly is used for being connected with the skin, and the first loading assembly drives the connecting assembly to move relative to the temperature control box so as to apply loads to the airship flange assembly. By applying the airship assembly mechanical test system disclosed by the invention, the reliability and sufficiency of airship assembly performance evaluation can be improved.

Description

Technical Field

[0001] The present application relates to, but is not limited to, the field of airship technology, and in particular to an airship component mechanical testing system. Background Art

[0002] The airship flange assembly is the installation interface of important equipment such as the pod, propulsion bracket and ballast tank. Its mechanical properties play a key role in the overall structural stress stability and airtightness of the airship. As the service time increases, if tiny gaps are generated around the airship flange assembly, the airtightness of the airship will be reduced, shortening the flight time of the airship.

[0003] At present, there is no systematic research on the mechanical testing system of airship flange components, and the test method is generally used to verify its load-bearing capacity. The relevant technology lacks the test of the impact of actual flight environment factors on the airship skin and flange components, which makes the test results insufficient and affects the performance evaluation and safety judgment. Summary of the invention

[0004] The airship component mechanical testing system provided in the present application can improve the reliability and adequacy of airship component performance evaluation.

[0005] The present application provides an airship component mechanical testing system for testing an airship flange component, wherein the airship flange component comprises a connected skin and a flange. The airship component mechanical testing system comprises a temperature control box and a loading mechanism, wherein the temperature control box comprises a chamber and a temperature control component; the temperature control component is used to adjust the temperature in the chamber; the chamber is used to accommodate the airship flange component; the loading mechanism comprises a first loading component and a connecting component, wherein the connecting component is used to connect the skin, and the first loading component drives the connecting component to move relative to the temperature control box to apply a load to the airship flange component.

[0006] The mechanical testing system of the airship assembly provided by the present application has a temperature control assembly in the chamber, and the temperature control assembly can adjust the temperature in the chamber. Since the airship flange assembly is contained in the chamber, it can be understood that the temperature in the chamber is the ambient temperature of the airship flange assembly, and the change in the temperature in the chamber can simulate the change in the ambient temperature of the airship flange assembly; the connecting assembly is connected to the skin of the airship flange assembly, and when the first loading assembly drives the connecting assembly to move relative to the temperature control box, the connecting assembly can provide tension to the skin, simulating the load on the skin when the pressure of the hull changes. Such a structure can simultaneously adjust the temperature in the temperature control box and the tension of the loading system, simulate the mechanical working conditions and temperature working conditions of the assembly in actual flight, obtain accurate long-term service test data of the flange assembly, and improve the reliability and adequacy of the performance evaluation.

[0007] In a possible implementation of the present application, the connection assembly includes a connection sleeve, and the outer peripheral side of the connection sleeve is used to be wrapped with the skin; the central axis of the connection sleeve is perpendicular to the loading direction of the first loading assembly.

[0008] In a possible implementation of the present application, the connection assembly further includes a fixing sleeve, which is parallel to the connection sleeve and relatively fixedly arranged, and the fixing sleeve is used to press together the two layers of skin wound around the connection assembly.

[0009] In a possible implementation of the present application, the loading mechanism also includes a base and a guide member, the fixed sleeve and the connecting sleeve are fixedly connected to the base, the base is respectively connected to the first loading assembly and the guide member, and the guide member guides the base to move along the loading direction of the first loading mechanism.

[0010] In a possible implementation of the present application, the first loading assembly includes a motor, a gearbox, a screw and a loading joint. The gearbox is transmission-connected to the motor. There are at least two screws, and at least two screws are connected in parallel to the output side of the gearbox. The loading joint is threadedly connected to the at least two screws to drive the loading joint to move toward or away from the gearbox, and the loading joint is connected to the connecting assembly.

[0011] In a possible implementation of the present application, the first loading assembly further includes a flexible cable, and connecting structures are respectively provided at both ends of the connecting assembly, and the flexible cable is respectively connected to the loading joint and the connecting structure.

[0012] In a possible implementation of the present application, at least one group of connection components is included, each group of connection components includes two connection components arranged opposite to each other, and the two connection components arranged opposite to each other are used to apply opposite loads to the skin.

[0013] In a possible implementation of the present application, the loading mechanism also includes a bracket and a second loading assembly, one end of the second loading assembly is installed on the bracket, and the other end is connected to the flange for applying a load to the flange; wherein the loading direction of the second loading assembly is perpendicular to the loading direction of the first loading assembly.

[0014] In a possible implementation of the present application, the loading mechanism is located outside the temperature control box; the temperature control box is provided with at least one through hole, and the through hole is used for allowing the skin or flange to extend out of the chamber to connect with the loading mechanism.

[0015] In a possible implementation of the present application, the temperature control component includes a heating element, which is used to increase the temperature in the chamber; and / or the temperature control component includes a cooling element, which is used to reduce the temperature in the chamber.

[0016] In a possible implementation of the present application, the airship component mechanical testing system also includes a detection component and a test host, the detection component is used to obtain the operating parameters of the loading mechanism, the temperature control box, and / or the test parameters of the airship flange assembly; the test host is electrically connected to the loading mechanism, the temperature control box and the detection component, respectively, and the test host is configured to control the working state of the loading mechanism and the temperature control box, and to obtain the operating parameters and test parameters through the detection component; wherein the detection component includes at least one of the following sensors: a temperature sensor, arranged in the chamber, for collecting temperature data in the chamber; a distance sensor, arranged in the loading mechanism, for collecting displacement data of the connecting component; a shooting device, for obtaining image information of the airship flange assembly; a force sensor is arranged on the loading mechanism, for obtaining force data of the loading mechanism. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 One of the structural schematic diagrams of the airship component mechanical testing system provided in the embodiment of the present application;

[0018] Figure 2 A partial structural diagram of an airship component mechanical testing system provided in an embodiment of the present application;

[0019] Figure 3 A schematic diagram of the installation structure of the flange and skin of the airship component mechanical testing system provided in an embodiment of the present application;

[0020] Figure 4 A schematic diagram of the structure of the connection structure and base of the airship component mechanical testing system provided in an embodiment of the present application;

[0021] Figure 5 A schematic diagram of the partial structure of a loading mechanism of an airship component mechanical testing system provided in an embodiment of the present application;

[0022] Figure 6 A schematic diagram of the structure of a loading mechanism of an airship component mechanical testing system provided in an embodiment of the present application;

[0023] Figure 7 A schematic diagram of the structure of a gearbox of an airship component mechanical testing system provided in an embodiment of the present application;

[0024] Figure 8 A schematic diagram of the installation structure of a "cross"-shaped skin, flange and temperature control box of the airship component mechanical testing system provided in an embodiment of the present application;

[0025] Fig. 9 A schematic diagram of the installation structure of the bracket, the second loading assembly and the temperature control box of the airship assembly mechanical testing system provided in an embodiment of the present application;

[0026] Fig.10A schematic diagram of the internal structure of a temperature control box of an airship component mechanical testing system provided in an embodiment of the present application;

[0027] Fig.11 This is a test flow chart of the airship component mechanical testing system provided in an embodiment of the present application.

[0028] Reference numerals:

[0029] 1-skin; 11-heat-sealing area; 2-flange; 3-temperature control box; 31-chamber; 32-temperature control assembly; 321-heating element; 322-refrigeration element; 33-through hole; 331-first through hole; 332-second through hole; 4-loading mechanism; 41-first loading assembly; 411-motor; 412-gear box; 4121-transmission shaft; 4122-input gear; 4123-transmission gear; 4124-output gear; 4125-output stud; 413-screw; 414-loading joint; 415-flexible cable; 42-connection assembly; 4 21-connecting sleeve; 422-fixing sleeve; 423-connecting structure; 43-base; 44-guide; 45-bracket; 451-column; 452-top beam; 453-normal loading beam; 454-normal gear transmission chassis; 455-middle beam; 46-second loading assembly; 5-detection assembly; 51-temperature sensor; 52-distance sensor; 53-shooting equipment; 54-force sensor; 55-three-dimensional full-field strain measurement system; 6-test host; X-first loading direction; Y-second loading direction; Z-third loading direction. DETAILED DESCRIPTION

[0030] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the specific technical solution of the present application will be further described in detail below in conjunction with the drawings in the embodiments of the present application. The following embodiments are used to illustrate the present application, but are not used to limit the scope of the present application.

[0031] In the embodiments of the present application, the terms "first" and "second" are used for descriptive purposes only and are not to be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the embodiments of the present application, unless otherwise specified, "multiple" means two or more.

[0032] In addition, in the embodiments of the present application, directional terms such as "up", "down", "left" and "right" are defined relative to the orientation of the components in the drawings. It should be understood that these directional terms are relative concepts. They are used for relative description and clarification, and they may change accordingly according to the changes in the orientation of the components in the drawings.

[0033] In the embodiments of the present application, unless otherwise clearly specified and limited, the term "connection" should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection or an indirect connection through an intermediate medium.

[0034] In the embodiments of the present application, the terms "include", "comprises" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprises a ..." does not exclude the presence of other identical elements in the process, method, article or device including the element.

[0035] In the embodiments of the present application, words such as "exemplary" or "for example" are used to indicate examples, illustrations or descriptions. Any embodiment or design described as "exemplary" or "for example" in the embodiments of the present application should not be interpreted as being more preferred or more advantageous than other embodiments or designs. Specifically, the use of words such as "exemplary" or "for example" is intended to present related concepts in a specific way.

[0036] Near-space airships have the advantages of being able to fly at a fixed point, staying in the air for a long time, and having a wide detection range. At present, my country has set the research and development of stratospheric airships as a national strategic need. The airship flange assembly is the installation interface on the airship for important equipment such as the pod, propulsion bracket and ballast. Its mechanical properties play a key role in the overall structural stress stability and the airtightness of the airship. The airship flange assembly must not only withstand the periodic changes in skin tension caused by changes in pressure, but also withstand the out-of-plane loads generated by equipment such as the pod, propulsion bracket and ballast, as well as the internal stress caused by day and night temperature changes. The service conditions are very harsh.

[0037] Therefore, as the service time increases, if tiny gaps appear around the airship flange assembly, the airtightness of the capsule will be reduced, shortening the flight time of the airship. However, the harsh service conditions put forward higher requirements on the mechanical properties of the airship flange assembly. The temperature changes during the day and night will cause the airship pressure. The airship flange assembly is also subjected to internal stress caused by temperature changes. If tiny gaps appear at the joints of the airship flange assembly after long-term service, the airtightness of the capsule will be reduced, shortening the flight time in the air.

[0038] Biaxial tensile testing machine is a common mechanical properties testing system, which can test and study the mechanical behaviors of polymer composite fabric materials such as nonlinearity, anisotropy and bidirectionality. However, in actual engineering applications, we not only focus on the mechanical properties of the film material itself, but also pay more attention to the long-term service performance of the rigid-flexible coupling structure represented by the flange assembly under the influence of mechanical-temperature load. Therefore, the mechanical loading system, temperature control system and three-dimensional strain measurement system are combined to develop a mechanical properties testing system for airship flange assemblies with mechanical-temperature synchronous control and full-field strain real-time monitoring functions, which has broad application prospects.

[0039] At present, there is no systematic research on the mechanical testing system of airship flange components at home and abroad, and the test method is generally used to verify its bearing capacity. The airship flange component is a rigid-flexible coupling structure with complex nonlinear mechanical behavior characteristics. The mechanical properties under different service conditions have significant differences, and the triaxial tensile test is an effective method to reveal the mechanical behavior of the airship flange component.

[0040] The "Multifunctional Thin Film Triaxial Tensile Tester and Test Method" published by Shanghai Jiao Tong University is based on the biaxial film material tensile tester, and adds a Z-axis tensile test device to realize the triaxial tensile test of the thin film connector. However, the invention has the following shortcomings: First, the tester mainly focuses on the mechanical properties of the thin film material itself, and does not design the fixture and loading device separately according to the use requirements of the airship flange assembly. The test area is small and the loading capacity is insufficient, which cannot meet the tensile test requirements of the airship flange assembly; second, there is a lack of three-dimensional strain monitoring means, and it is impossible to monitor the full-field strain during the loading process in real time; third, there is a lack of mechanical-temperature load synchronous loading capability, and it is impossible to actually test the flange assembly according to the actual flight environment of the airship.

[0041] Reference Figure 1 and Figure 2 and Fig.10 The embodiment of the present application provides an airship component mechanical testing system for testing an airship flange component, wherein the airship flange component includes a skin 1 and a flange 2 connected to each other. The airship component mechanical testing system includes a temperature control box 3 and a loading mechanism 4, wherein the temperature control box 3 includes a chamber 31 and a temperature control component 32; the temperature control component 32 is used to adjust the temperature in the chamber 31; the chamber 31 is used to accommodate the airship flange component; the loading mechanism 4 includes a first loading component 41 and a connecting component 42, wherein the connecting component 42 is used to connect the skin 1, and the first loading component 41 drives the connecting component 42 to move relative to the temperature control box 3 to apply a load to the airship flange component.

[0042] Reference Figure 3In the embodiment of the present application, the flange 2 is installed in the center of the skin 1. The flange 2 is divided into two parts, the inner part and the outer part. The inner part and the outer part clamp the skin 1 in the middle and are installed on the skin 1 by screws, which can form an airship flange assembly for testing. The airship flange assembly belongs to a typical rigid-flexible coupling structure. The temperature control box 3 includes a chamber 31, and the space in the chamber 31 can at least accommodate the airship flange assembly and the temperature control assembly 32. In addition, the connection assembly 42 and the first loading assembly 41 can also be arranged in the temperature control box 3; or, the connection assembly 42 is arranged in the temperature control box 3, and the first loading assembly 41 is arranged outside the temperature control box 3; or, the connection assembly 42 and the first loading assembly 41 are both arranged outside the temperature control box 3.

[0043] In the embodiment of the present application, the first loading assembly 41 is used to provide a driving force to drive the connecting assembly 42 to move relative to the temperature control box 3. The connecting mechanism is connected to the skin 1, and the movement of the connecting mechanism relative to the temperature control box 3 can drive the skin 1 to be tightened or relaxed to change the stress on the surface of the skin 1, simulating the stress on the skin 1 when the pressure inside the airship changes.

[0044] In the embodiment of the present application, the temperature control box 3 can be of any shape, for example, the circumferential profile of the temperature control box 3 can be circular, rectangular, rhombus, etc. When the circumferential profile of the temperature control box 3 is circular, the moving direction of the connecting mechanism can be perpendicular to the tangent of the circle, and when the circumferential profile of the temperature control box 3 is rectangular, the moving direction of the connecting mechanism can be perpendicular to the extension direction of the side of the rectangle.

[0045] In the mechanical testing system of the airship assembly of the embodiment of the present application, a temperature control assembly 32 is arranged in the chamber 31, and the temperature control assembly 32 can adjust the temperature in the chamber 31. Since the airship flange assembly is contained in the chamber 31, it can be understood that the temperature in the chamber 31 is the ambient temperature of the airship flange assembly, and the change of the temperature in the chamber 31 can simulate the change of the ambient temperature of the airship flange assembly; the connecting assembly 42 is connected to the skin 1 of the airship flange assembly, and when the first loading assembly 41 drives the connecting assembly 42 to move relative to the temperature control box 3, the connecting assembly 42 can provide tension to the skin 1, simulating the load on the skin 1 when the pressure of the hull changes. Such a structure can simultaneously adjust the temperature in the temperature control box 3 and the tension of the loading system, simulate the mechanical working conditions and temperature working conditions of the assembly in actual flight, obtain accurate long-term service test data of the flange 2 assembly, and improve the reliability and adequacy of the performance evaluation.

[0046] Reference Figure 4 , Figure 5 and Figure 6 The embodiment of the present application provides a mechanical testing system for airship components, wherein the connecting component 42 includes a connecting sleeve 421, and the outer peripheral side of the connecting sleeve 421 is used to be wrapped by the skin 1; the central axis of the connecting sleeve 421 is perpendicular to the loading direction of the first loading component 41.

[0047] In the prior art, the commonly used biaxial tensile testing machine for skin 1 generally adopts the form of clips or single sleeves for loading, which may cause the skin 1 to tear or separate during the loading process and cannot meet the large-scale heavy-load testing requirements of the airship flange assembly. In order to reduce the damage to the skin 1.

[0048] Reference Figure 4 In the embodiment of the present application, the skin 1 is wound around the outer circumference of the connecting sleeve 421, and one end of the skin 1 is connected to the skin 1 by heat sealing after passing through the connecting sleeve 421; it can also be understood that one end of the skin 1 is folded to form a cylindrical structure, and the part of the cylindrical structure is reserved, and the end of the skin 1 and the skin 1 overlapped after the folding are connected by heat sealing, and the cylindrical structure is closed on the circumference, and then the formed cylindrical structure is sleeved on the outer circumference of the connecting sleeve 421. In the present application, the area where the skin 1 is connected by heat sealing is defined as the heat sealing area 11. With such a structure, the connecting sleeve 421 can apply tension to the skin 1 through the cylindrical structure.

[0049] In the embodiment of the present application, the direction in which the first loading assembly 41 drives the connection structure 423 to move is perpendicular to the axial direction of the connection sleeve 421 and is parallel to the extension direction of the skin 1. This can make the tension generated by the connection structure 423 on the skin 1 more uniform in the axial direction of the connection mechanism, increase the force-bearing area of ​​the skin 1, and also improve the uniformity of the force on the skin 1.

[0050] Since the heat-sealed area 11 of the skin 1 has two layers of skin 1, when the skin 1 is subjected to tension, the heat-sealed area 11 of the skin 1 may crack or delaminate, causing damage to the skin 1. In order to reduce the damage to the skin 1. The embodiment of the present application provides an airship component mechanical testing system, wherein the connecting component 42 further includes a fixing sleeve 422, which is parallel to and relatively fixed to the connecting sleeve 421, and the fixing sleeve 422 is used to press the two layers of skin 1 bypassing the connecting component 42.

[0051] Reference Figure 2 and Figure 4 In the embodiment of the present application, when the skin 1 is connected to the connecting sleeve 421, the heat sealing area 11 of the skin 1 is located between the connecting sleeve 421 and the temperature control box 3. Therefore, the position of the fixed sleeve 422 is closer to the temperature control box 3 than the connecting sleeve 421, so as to facilitate the pressing of the heat sealing area 11.

[0052] In the embodiment of the present application, in the direction perpendicular to the extension of the skin 1, there is a position offset between the axes of the fixing sleeve 422 and the connecting sleeve 421, so that the plane where the axes of the fixing sleeve 422 and the connecting sleeve 421 are located has a certain angle with the extension direction of the skin 1, so that the skin 1 is subjected to forces in two different directions applied by the fixing sleeve 422 and the connecting sleeve 421, thereby improving the pressing effect of the fixing sleeve 422 on the heat-sealed area 11 of the skin 1, and reducing the delamination and cracking of the heat-sealed area 11 of the skin 1 when subjected to force.

[0053] In the embodiment of the present application, the connecting sleeve 421 and the fixing sleeve 422 can be directly connected to the first loading assembly 41, or can be indirectly connected to the first loading assembly 41 through other structures. In order to improve the stability of the movement of the connecting assembly 42. Figure 5 and Figure 6 The embodiment of the present application provides a mechanical testing system for airship components. The loading mechanism 4 also includes a base 43 and a guide member 44. The fixing sleeve 422 and the connecting sleeve 421 are fixedly connected to the base 43. The base 43 is respectively connected to the first loading component 41 and the guide member 44. The guide member 44 guides the base 43 to move along the loading direction of the first loading component 41.

[0054] In the embodiment of the present application, the base 43 is used to provide an installation basis for the connecting sleeve 421 and the fixing sleeve 422. The connecting sleeve 421 and the fixing sleeve 422 can be fixedly connected to the base 43, or can be detachably connected to the base 43. For example, a through hole is opened on the base 43, and the connecting sleeve 421 and the fixing sleeve 422 pass through the through hole and are fixed to the base 43 by screws, which is convenient for disassembly and installation, and also convenient for maintenance and replacement.

[0055] In the embodiment of the present application, the guide member 44 is arranged along the loading direction of the first loading component 41. The guide member 44 can be set as a guide rail, or it can be a groove or other structure. The base 43 is provided with a slider or a wheel that can move on the guide rail. The base 43 can also be provided with a protrusion corresponding to the groove or a wheel that can match the groove, etc., so as to realize the movement of the base 43 along the guide member 44.

[0056] In the prior art, an electro-hydraulic servo system is generally used to load the skin 1. This solution has problems such as complex structure and high cost. During the test, the volume elastic modulus of the liquid will also change with the temperature and the content of the mixed air, resulting in significant changes in the transmission performance. At the same time, the electro-hydraulic servo system also has the risk of oil leakage, which is easy to cause a fire. Therefore, the transmission loading system cannot meet the long-term service test requirements of the flange 2 component.

[0057] Reference Figure 6 and Figure 7The embodiment of the present application provides a mechanical testing system for an airship component. The first loading component 41 includes a motor 411, a gear box 412, a screw 413 and a loading joint 414. The gear box 412 is transmission-connected to the motor 411. There are at least two screws 413, and at least two screws 413 are connected in parallel to the output side of the gear box 412. The loading joint 414 is threadedly connected to the at least two screws 413 to drive the loading joint 414 to move toward or away from the gear box 412. The loading joint 414 is connected to the connecting component 42.

[0058] In the embodiment of the present application, the gear box 412 transmits the force of the motor 411 to the two screws 413, so that the two screws 413 rotate relative to the loading joint 414. Through the threaded connection between the loading joint 414 and the two screws 413, the loading joint 414 moves relative to the two screws 413, thereby driving the connection assembly 42 to move. The bottom of the gear box 412 can be connected to the ground by screws to provide a stable installation platform for the transmission assembly.

[0059] In the embodiment of the present application, the gears in the gearbox 412 at least include a transmission shaft 4121, an input gear 4122, a transmission gear 4123, an output gear 4124 and an output stud 4125. The motor 411 is connected to the input gear 4122. With the motor 411 as the center, the transmission gear 4123 is symmetrically connected to two transmission shafts 4121. The two transmission shafts 4121 are respectively connected to the transmission gears 4123. The two transmission gears 4123 are respectively connected to the input gear 4122, and the two output gears 4124 are respectively connected to the screw 413.

[0060] In the embodiment of the present application, the force sensor 54 and the servo motor 411 are connected to the central control system via cables, and the change of the tension at the loading end is accurately controlled by means of negative feedback regulation.

[0061] The airship component mechanical testing system of the embodiment of the present application can amplify the output torque of the servo motor 411 in two stages through the above structure, and the left-right symmetrical design can increase the structural stability while ensuring the synchronization of the output.

[0062] Reference Figure 2 and Figure 6 The embodiment of the present application provides a mechanical testing system for airship components. The first loading component 41 also includes a flexible cable 415. Both ends of the connecting component 42 are respectively provided with connecting structures 423. The flexible cable 415 is respectively connected to the loading joint 414 and the connecting structure 423.

[0063] In the embodiment of the present application, the two ends of the connecting assembly 42 can be understood as the two ends in the axial direction of the connecting sleeve 421. The connecting structure 423 can be set at the two ends of the connecting sleeve 421, or at the two ends of the fixing sleeve 422, or at the two ends of the base 43. For example, the connecting structure 423 is set at the two ends of the base 43, and one end of the flexible cable 415 is connected to the connecting structure 423 at the two ends of the base 43 through a shackle.

[0064] In the embodiment of the present application, the other end of the flexible cable 415 is connected to the loading joint 414 , and can be connected to both ends of the loading joint 414 in the axial direction of the connecting sleeve 421 , or can be connected to the middle position of the loading joint 414 .

[0065] The airship component mechanical testing system of the embodiment of the present application is provided with connection structures 423 at both ends of the connection component 42, and is connected to the loading joint 414 through a flexible cable 415, so that the two ends of the connection component 42 can be evenly stressed, thereby improving the stability of the movement of the connection component 42.

[0066] An embodiment of the present application provides an airship component mechanical testing system, which includes at least one group of connection components 42, each group of connection components 42 includes two connection components 42 arranged opposite to each other, and the two connection components 42 arranged opposite to each other are used to apply opposite loads to the skin 1.

[0067] In the embodiment of the present application, two relatively arranged connecting components 42 form a group. When the connecting components 42 move in a direction away from the temperature control box 3, the connecting structure 423 can provide a loading force to the skin 1. At this time, two relatively arranged groups of connecting components 42 can provide two loading forces in opposite directions to the skin 1, thereby balancing the force on the skin 1 and reducing the displacement of the skin 1 relative to the temperature control box 3 after the force is applied.

[0068] For example, refer to Figure 2 In order to facilitate experiments, the embodiment of the present application adopts a skin 1 similar to a "cross" shape. The middle area of ​​the "cross"-shaped skin 1 is used to install the flange 2 and is located in the temperature control box 3; the "cross"-shaped skin 1 extends in two directions.

[0069] In the embodiment of the present application, in order to make the loading force on the skin 1 more uniform and reduce the deviation of the center of the skin 1 relative to the temperature control box, the present embodiment provides two groups of connection components 42 for the "cross" shaped skin 1, wherein the direction of the loading force applied to the skin 1 by one group of connection components 42 is the first loading direction X, and the direction of the loading force applied to the skin 1 by the other group of connection components 42 is the second loading direction Y. The first loading direction X and the second loading direction Y are located in the same plane and are perpendicular to each other.

[0070] The first loading direction X and the second loading direction Y are kept parallel to the extension direction of the skin 1, so that the skin 1 can be subjected to balanced force when loaded, thereby reducing the displacement of the skin 1 relative to the temperature control box 3 when loaded, reducing unnecessary deformation of the skin 1, and making the test results of the stress on the skin 1 more accurate.

[0071] In the embodiment of the present application, multiple groups of relatively arranged connection components 42 can be set according to the experimental requirements. When there are two groups of relatively arranged connection components 42, the directions between the two groups of relatively arranged connection components 42 can be perpendicular to each other. Each group of connection components 42 will provide two opposite loading forces to the skin 1. Such a structure can provide two groups of mutually perpendicular and opposite loading forces to the skin 1. It can be understood that the skin 1 is subjected to loading forces in four mutually perpendicular directions. The stress on the skin 1 can be made more balanced, and the stress on the airship in the radial and axial directions can be simulated, providing the skin 1 with a stress environment closer to the actual working conditions.

[0072] In the mechanical testing system of the airship assembly of the embodiment of the present application, the two sets of connecting assemblies 42 maintain synchronous symmetrical movement, the center of the airship flange assembly remains stationary, and the bottom of the loading fixture base 43 is connected to the guide rail, so that synchronous symmetrical loading is achieved under system control, reducing the deviation of the sample center during loading. It is also convenient to combine with DIC in-situ observation.

[0073] In addition to being used for the installation of fans and valves, the airship flange assembly is also the basis for the installation of pod systems such as avionics, measurement and control, and energy. Therefore, during long-term service testing, it is necessary to consider adding out-of-plane loads to the airship flange assembly and applying corresponding loads in the normal direction to ensure that the service conditions of flange 2 are consistent with the actual situation.

[0074] Reference Figure 1 , Figure 2 , Figure 3 and Fig. 9 An embodiment of the present application provides a mechanical testing system for airship components, wherein the loading mechanism 4 further includes a bracket 45 and a second loading component 46, wherein one end of the second loading component 46 is mounted on the bracket 45, and the other end is connected to the flange 2, for applying a load to the flange 2; wherein the loading direction of the second loading component 46 is perpendicular to the loading direction of the first loading component 41.

[0075] In the embodiment of the present application, the bracket 45 is used to provide a stable installation platform and support for the second loading assembly 46. The bracket 45 may include a plurality of columns 451 and beams and other structures, which can be adjusted according to the structure of the device. For example, the bracket 45 includes a column 451, a top beam 452, a normal loading beam 453, a normal gear transmission chassis 454 and a middle beam 455. The top beam 452 adopts an I-shaped cross section, and the column 451, the middle beam 455 and the loading beam cross section all adopt a rectangular cross section, and are connected to each other by screws.

[0076] In the embodiment of the present application, the load applied by the second loading component 46 to the flange 2 is used to simulate the load of other structures installed on the flange 2 when the airship is in actual working conditions. In the present application, the direction in which the second loading component 46 applies the load to the flange 2 is defined as the third loading direction Z. The loading direction of the second loading component 46 is perpendicular to the loading direction of the first loading component 41. Therefore, the third loading direction Z is perpendicular to the plane where the first loading direction X and the second loading direction Y are located. It can also be understood that the third loading direction Z is perpendicular to the extension direction of the skin 1.

[0077] In the airship component mechanical testing system of the embodiment of the present application, the second loading assembly 46 is used to simulate the load of flange 2 installed with other structures when the airship is in actual working conditions, and the bracket 45 can provide a stable installation platform for the second loading assembly 46, so that the second loading assembly 46 applies a stable normal load to the airship flange assembly.

[0078] In order to reduce the influence of temperature on the first loading component 41 and the connecting component 42, and to reduce the size of the temperature control box 3, thereby saving costs, in an embodiment of the present application, the first loading component 41, the connecting component 42 and the second loading component 46 are arranged on the outside of the temperature control box 3.

[0079] Reference Figure 2 and Fig. 9 An embodiment of the present application provides a mechanical testing system for airship components, wherein a loading mechanism 4 is located outside a temperature control box 3 ; the temperature control box 3 is provided with at least one through hole 33 , and the through hole 33 is used for allowing the skin 1 or the flange 2 to extend out of the chamber 31 to connect with the loading mechanism 4 .

[0080] Reference Figure 2 , Figure 8 and Fig. 9 In the embodiment of the present application, the through hole 33 on the temperature control box 3 for the skin 1 to extend out of the cavity 31 is defined as the first through hole 331. The first through hole 331 is opened along the circumference of the temperature control box 3. The size and number of the openings can be adjusted according to the experimental requirements. For example, in order to facilitate the experiment, the embodiment of the present application adopts a skin 1 similar to a "cross" shape. The middle area of ​​the "cross"-shaped skin 1 is used to install the flange 2, and is located in the temperature control box 3; therefore, the temperature control box 3 is set to a rectangular structure, and through holes are respectively opened on the four edges of the side of the temperature control box 3. The through holes connect the cavity 31 with the outside of the temperature control box 3. The areas where the "cross"-shaped skin 1 extends in four directions extend out from the through holes 33 of the temperature control box 3.

[0081] In the embodiment of the present application, the through hole 33 on the temperature control box 3 for the flange 2 to extend out of the chamber 31 is defined as a second through hole 332. The second through hole 332 can be opened according to the setting direction of the flange 2. Since the flange 2 is a structure in which the upper and lower parts clamp the skin 1, the opening direction of the second through hole 332 is perpendicular to the extension direction of the skin 1. For example, the second through hole 332 is opened on the side of the temperature control box 3 away from the ground, and a part of the flange 2 extends out of the chamber 31 through the second through hole 332. The flange 2 extending out of the chamber 31 is connected to the second loading assembly 46 through the loading ear.

[0082] Reference Fig.10 An embodiment of the present application provides an airship component mechanical testing system, wherein the temperature control component 32 includes a heating element 321, and the heating element 321 is used to increase the temperature in the chamber 31; and / or, the temperature control component 32 includes a cooling element 322, and the cooling element 322 is used to reduce the temperature in the chamber 31.

[0083] In an embodiment of the present application, the heating element 321 may be a resistance wire or a heating plate, etc. For example, the heating element 321 may be a heating plate, which is a flat heater. The heating plate is arranged on the bottom wall. The heating plate can provide large-area uniform heating in the chamber 31, and the heating efficiency is high and uniform.

[0084] In the embodiment of the present application, the refrigeration component 322 may include refrigeration devices such as a fan and liquid nitrogen. In the example, an air inlet for introducing liquid nitrogen is provided inside the strong part, and a valve is provided on the air inlet to control the flow rate and flow velocity of the liquid nitrogen.

[0085] In the airship component mechanical testing system of the embodiment of the present application, the temperature control component 32 can lower or raise the temperature in the chamber 31, and can simulate the increase and decrease of the ambient temperature faced by the airship under natural working conditions, thereby improving the authenticity of the experimental data.

[0086] Reference Figure 1 , Figure 6 and Fig.10The embodiment of the present application provides a mechanical testing system for an airship component, which also includes a detection component 5 and a test host 6. The detection component 5 is used to obtain the working parameters of the loading mechanism 4 and the temperature control box 3, and / or the test parameters of the airship flange component; the test host 6 is electrically connected to the loading mechanism 4, the temperature control box 3 and the detection component 5 respectively, and the test host 6 is configured to control the working states of the loading mechanism 4 and the temperature control box 3, and to obtain the working parameters and the test parameters through the detection component 5; wherein the detection component 5 includes at least one of the following sensors: a temperature sensor 51, which is arranged in the chamber 31, and is used to collect temperature data in the chamber 31; a distance sensor 52, which is arranged in the loading mechanism 4, and is used to collect displacement data of the connection component 42; a shooting device 53, which is used to obtain image information of the airship flange component; a force sensor 54 is arranged on the loading mechanism 4, and is used to obtain force data of the loading mechanism 4.

[0087] In the embodiment of the present application, the temperature collector, the liquid nitrogen valve and the heating plate are connected to the test host 6 through a signal cable, so that the central control system in the test host 6 can adjust the temperature in the box according to the negative feedback regulation mechanism. For example, when the temperature in the chamber 31 needs to be adjusted to a preset temperature, the central control system determines the parameters that need to be adjusted through the temperature in the chamber 31 collected by the temperature collector, and the parameters that need to be adjusted include at least performing a heating action or performing a cooling action, and the degree of performing a heating or cooling action. For example, when the temperature in the chamber 31 is higher than the preset temperature, the central control system controls the liquid nitrogen valve to fill the chamber 31 with liquid nitrogen to reduce the temperature in the chamber 31; when the temperature in the chamber 31 is lower than the preset temperature, the central control system controls the heating element 321 to heat up to increase the temperature in the chamber 31.

[0088] Reference Fig.10 In the embodiment of the present application, the three-dimensional full-field strain measurement system 55 realizes non-contact strain measurement by real-time tracking of the speckle image on the "cross"-shaped skin 1, combining digital image correlation method and binocular stereo vision technology. The traditional skin 1 tensile testing machine does not have the ability of non-contact strain measurement and cannot continuously monitor the changes in mechanical properties during long-term service testing; when the maximum real-time strain of the airship flange assembly exceeds the allowable range, the central control system will stop the test and retain all test data.

[0089] Reference Fig.11 The embodiment of the present application provides a mechanical testing system for airship components. The process of using the mechanical testing system for airship components to test flange 2 components is mainly divided into nine steps: inputting overall design parameters, determining temperature and mechanical load spectra, building a test system, preliminary experiments, long-term service tests, and post-processing of test data.

[0090] A mechanical performance test system for the airship flange assembly is built, and the flange 2 specimen is installed on the cross-shaped test skin 1 by screws to form an airship flange assembly. The airship flange assembly is placed as a whole in a temperature control box 3, and holes 33 are left around the temperature control box 3 for the cross-shaped skin 1 to pass through; the cross-shaped skin 1 is connected to the connection assembly 42 on all sides, and the in-plane tension of the skin 1 is controlled by moving the first loading assembly 41 relative to the temperature control box 3; the loading lug at one end of the flange 2 is connected to the second loading assembly 46 by a wire rope; the detector assembly can monitor the full-field strain of the airship flange assembly in real time.

[0091] The airship component mechanical testing system provided in the embodiment of the present application has the advantages of mechanical-temperature synchronous control, real-time monitoring of full-field strain, high degree of automation of the loading system and easy operation. It can complete long-term service testing of airship components on the ground and provide data support for the actual flight of the airship.

[0092] The serial numbers of the embodiments of the present application are only for description and do not represent the advantages and disadvantages of the embodiments. The above are only preferred embodiments of the present application, and do not limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made by using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. An airship component mechanical testing system, used for testing an airship flange component, wherein the airship flange component comprises a skin (1) and a flange (2) connected to each other, characterized in that: include: A temperature control box (3) comprises a chamber (31) and a temperature control component (32); the temperature control component (32) is used to adjust the temperature in the chamber (31); the chamber (31) is used to accommodate the airship flange component; The loading mechanism (4) comprises a first loading component (41) and a connecting component (42), wherein the connecting component (42) is used to connect the skin (1), and the first loading component (41) drives the connecting component (42) to move relative to the temperature control box (3) to apply a load to the airship flange component.

2. The airship component mechanical testing system according to claim 1, characterized in that: The connecting assembly (42) comprises a connecting sleeve (421), the outer peripheral side of which is used to be wrapped by the skin (1); the central axis of the connecting sleeve (421) is perpendicular to the loading direction of the first loading assembly (41).

3. The airship component mechanical testing system according to claim 2, characterized in that: The connecting assembly (42) further comprises a fixing sleeve (422), wherein the fixing sleeve (422) is arranged parallel to and relatively fixed to the connecting sleeve (421), and the fixing sleeve (422) is used to press together the two layers of the skin (1) wound around the connecting assembly (42).

4. The airship component mechanical testing system according to claim 3, characterized in that: The loading mechanism (4) further comprises a base (43) and a guide member (44); the fixed sleeve (422) and the connecting sleeve (421) are fixedly connected to the base (43); the base (43) is respectively connected to the first loading component (41) and the guide member (44); and the guide member (44) guides the base (43) to move along the loading direction of the first loading component (41).

5. The airship component mechanical testing system according to any one of claims 1 to 4, characterized in that: The first loading component (41) comprises a motor (411), a gear box (412), a screw (413) and a loading joint (414); the gear box (412) is drivingly connected to the motor (411); there are at least two screws (413), and at least two screws (413) are connected in parallel to the output side of the gear box (412); the loading joint (414) is threadedly connected to the at least two screws (413) to drive the loading joint (414) to move toward or away from the gear box (412); and the loading joint (414) is connected to the connecting component (42).

6. The airship component mechanical testing system according to claim 5, characterized in that: The first loading component (41) further comprises a flexible cable (415), and connecting structures (423) are respectively provided at both ends of the connecting component (42), and the flexible cable (415) respectively connects the loading joint (414) and the connecting structure (423).

7. The airship component mechanical testing system according to any one of claims 1 to 4, characterized in that: At least one group of the connection components (42) is included, and each group of the connection components (42) includes two connection components (42) arranged opposite to each other, and the two connection components (42) arranged opposite to each other are used to apply opposite loads to the skin (1).

8. The airship component mechanical testing system according to any one of claims 1 to 4, characterized in that: The loading mechanism (4) further comprises a bracket (45) and a second loading component (46), wherein one end of the second loading component (46) is mounted on the bracket (45) and the other end is connected to the flange (2) for applying a load to the flange (2); Wherein, the loading direction of the second loading component (46) is perpendicular to the loading direction of the first loading component (41).

9. The airship component mechanical testing system according to any one of claims 1 to 4, characterized in that: The loading mechanism (4) is located outside the temperature control box (3); The temperature control box (3) is provided with at least one through hole (33), and the through hole (33) is used to allow the skin (1) or the flange (2) to extend out of the chamber (31) so as to be connected to the loading mechanism (4).

10. The airship component mechanical testing system according to any one of claims 1 to 4, characterized in that: The temperature control component (32) comprises a heating element (321), and the heating element (321) is used to increase the temperature in the chamber (31); And / or, the temperature control component (32) includes a refrigeration component (322), and the refrigeration component (322) is used to reduce the temperature in the chamber (31).

11. The airship component mechanical testing system according to any one of claims 1 to 4, characterized in that: Also includes: A detection component (5) for obtaining operating parameters of the loading mechanism (4), the temperature control box (3), and / or test parameters of the airship flange component; A test host (6) is electrically connected to the loading mechanism (4), the temperature control box (3) and the detection component (5), respectively, and the test host (6) is configured to control the working states of the loading mechanism (4) and the temperature control box (3), and to obtain the working condition parameters and the test parameters through the detection component (5); Wherein, the detection component (5) comprises at least one of the following sensors: A temperature sensor (51) is disposed in the chamber (31) and is used to collect temperature data in the chamber (31); A distance sensor (52) is arranged on the loading mechanism (4) and is used to collect displacement data of the connecting component (42); A photographing device (53) for acquiring image information of the airship flange assembly; A force sensor (54) is arranged on the loading mechanism (4) and is used to obtain force data of the loading mechanism (4).

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