Asteroid analog spinning process dynamic testing device and testing method

Abstract

The present application relates to the technical fields of asteroid analog test, and discloses a kind of asteroid analog self-rotating process dynamic test device and test method, including fixed platform, rotating platform, drive assembly, five telescopic components and measuring plate, rotating platform is rotationally arranged on the surface of fixed platform, drive assembly is arranged in the interior of fixed platform, the surface of rotating platform is also provided with five telescopic rods, the telescopic end of telescopic component is provided with measuring plate, the interior of measuring plate is provided with measurement sensor towards asteroid analog;Through five telescopic components and measuring plate on the surface of rotating platform, and the corresponding measurement plate and asteroid analog, cooperate with the measurement sensor in measuring plate, the synchronous collection of three-dimensional axial dynamic deformation data can be realized, cover the multidimensional measurement of the periphery and top of asteroid analog, to obtain the three-axis length and time relationship curve of analog at different rotation rates, oblateness and elongated ellipsoid eccentricity change curve with time accurately.

Description

Technical Field

[0001] This invention relates to the field of asteroid simulation testing technology, specifically to a dynamic testing device and method for the spin process of an asteroid simulation. Background Technology

[0002] Studies show that as spin velocity increases, asteroids undergo varying degrees of deformation along the X, Y, and Z axes. Material from mid-latitude regions gradually migrates towards the equatorial region, causing the asteroid's geometry to evolve from an ideal spherically symmetric structure into an equatorially bulging, polarly flattened ellipsoid. When the spin angular velocity exceeds a critical threshold, the structural stress generated by elastic deformation within the asteroid cannot counteract the centrifugal stress caused by high-speed rotation, leading to a further transformation into an elongated ellipsoid extending along the equatorial plane. At this stage, the centrifugal force on the material at the equatorial end exceeds the combined force of its own gravity and intergranular cohesion, triggering unsteady ejection of localized material and resulting in the stripping away of a small number of particle units.

[0003] In the field of asteroid research, a deep understanding of the spin evolution process and internal structural characteristics of asteroids is crucial for revealing their formation mechanisms, predicting orbital changes, and identifying potential threats. Currently, existing technologies have made some progress in simulating asteroid-related characteristics. For example, through theoretical models and numerical simulations, it is possible to predict the morphological changes of asteroids at different spin velocities. For instance, the process by which asteroids transform from a spherically symmetric structure to an oblate spheroid or even an elongated spheroid extending along the equatorial plane as spin velocity increases has been theoretically elucidated.

[0004] In the study of asteroid simulations, existing technologies generally use cameras to photograph the asteroid simulations in rotating experimental devices to observe the morphological changes of the asteroid simulations. However, the above devices lack effective means to monitor the dynamic length changes in the positive directions of the X-axis, Y-axis and Z-axis during the spin of the asteroid simulations, making it difficult to obtain quantitative data on the changes of the three-axis length, flattening, eccentricity and other parameters with time and rotation rate in real time and accurately.

[0005] Therefore, existing technologies still need to be improved and developed. Summary of the Invention

[0006] In view of the shortcomings of the prior art, the purpose of this invention is to provide a dynamic testing device and method for the spin process of asteroid simulants, aiming to solve the problem that it is difficult to accurately obtain the dynamically changing parameters during the spin process of asteroid simulants in the prior art.

[0007] The technical solution adopted by this invention to solve the technical problem is as follows:

[0008] A dynamic testing device for the spin process of an asteroid simulator includes:

[0009] Fixed platform;

[0010] A rotating platform, rotatably mounted on the surface of the fixed platform, is used to place asteroid simulators;

[0011] A drive assembly is disposed inside the fixed platform; the drive assembly is connected to the rotary platform to drive the rotary platform to rotate;

[0012] Five telescopic components are disposed on the surface of the rotating platform, located around the asteroid simulator and on top of it, respectively;

[0013] A measuring plate, disposed at the telescopic end of the telescopic assembly, is used to measure the initial and final lengths of the asteroid simulator;

[0014] A measuring sensor, located inside the measuring plate and facing the asteroid simulator, is used to measure the length of the asteroid simulator as it rotates in real time.

[0015] Furthermore, the telescopic component includes:

[0016] A support sleeve is disposed on the surface of the rotary table; the opening of the support sleeve faces the asteroid simulator;

[0017] A telescopic component is provided inside the support sleeve;

[0018] A connecting rod is slidably disposed within the support sleeve; one side of the connecting rod is connected to the telescopic member, and the other end is connected to the measuring plate;

[0019] A measuring component, mounted on the support sleeve, is used to measure the sliding distance of the connecting rod.

[0020] Furthermore, the telescopic component can be an electric telescopic rod, a hydraulic telescopic rod, or a pneumatic telescopic rod.

[0021] Furthermore, the measurement component includes:

[0022] The scale is set on the connecting rod;

[0023] A camera is mounted on the support sleeve; the camera corresponds to the scale on the connecting rod.

[0024] Furthermore, a U-shaped support rod is provided on the rotating platform, and the telescopic component located on top of the asteroid simulator is mounted on the U-shaped support rod.

[0025] Furthermore, it also includes:

[0026] A platform is provided on the fixed platform; a placement tray is provided on the platform.

[0027] A pressure-bearing head is disposed on the fixed platform; a pressure-bearing plate is disposed at the bottom of the pressure-bearing head, and the pressure-bearing plate is aligned with the platform.

[0028] An axial displacement extensometer is mounted on the fixed platform; the axial displacement extensometer is matched with the axis of the asteroid simulator and is used to measure the change in the axis of the asteroid simulator.

[0029] A radial displacement extensometer is mounted on the fixed platform; the radial displacement extensometer is matched with the radial direction of the asteroid simulator to measure the radial change of the asteroid simulator.

[0030] Furthermore, the pressure-bearing head is mounted on the fixed platform via a rigid support.

[0031] Furthermore, a fixing member is provided at the center of the rotating platform, and the fixing member is connected to the asteroid simulation object.

[0032] Furthermore, the driving component includes:

[0033] The motor is installed inside the fixed platform; the output shaft of the motor is connected to the rotary table.

[0034] A method for dynamically testing the spin process of an asteroid simulator, based on the aforementioned device for dynamically testing the spin process of an asteroid simulator, includes:

[0035] The asteroid simulator is placed on the rotating platform, and the telescopic assembly is activated to measure the initial length of the asteroid simulator in conjunction with the measuring plate.

[0036] The drive assembly and the measuring sensor are activated to rotate the asteroid simulator and measure the length of the asteroid simulator that changes during rotation.

[0037] After a preset time, the drive component is shut down, and the termination length of the asteroid simulator is measured by the telescopic component in conjunction with the measuring plate. All measurement data is then transmitted to the control terminal to complete the test experiment.

[0038] Compared with the prior art, the beneficial effects of the present invention are:

[0039] In this invention, by using five telescopic components and a measuring plate on the surface of the rotating stage, and aligning the measuring plate with the asteroid simulator, and with the measuring sensors inside the measuring plate, synchronous acquisition of three-dimensional axial dynamic deformation data can be achieved. This covers multi-dimensional measurements around and on top of the asteroid simulator, thereby accurately obtaining the curves of the three-axis length versus time, flattening, and elongated ellipsoid eccentricity of the simulator at different rotation rates, so as to study the spin evolution rules of different asteroid simulators at different rotation rates. Attached Figure Description

[0040] Figure 1 This is a schematic diagram of the overall structure of the present invention.

[0041] Figure 2 This is a schematic diagram of the measuring plate and measuring sensor structure of the present invention.

[0042] Figure 3 This is a flowchart of the dynamic testing method for the spin process of an asteroid simulator according to the present invention.

[0043] The numbers in the diagram represent: 1. Fixed platform; 2. Rotary platform; 21. U-shaped support rod; 3. Rotating assembly; 4. Telescopic assembly; 41. Support sleeve; 42. Connecting rod; 5. Measuring plate; 6. Measuring sensor; 7. Loading stage; 71. Pressure head; 72. Pressure plate; 73. Rigid support; 74. Placement tray; 8. Control terminal. Detailed Implementation

[0044] To make the objectives, technical solutions, and effects of this invention clearer and more explicit, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0045] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined with "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0046] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0047] In existing technologies, morphological monitoring of asteroid simulation spin processes primarily relies on visual observation. Traditional methods use fixed cameras to capture changes in the appearance of the simulation during rotation. However, due to limitations in the shooting angle and the lack of multi-dimensional measurement mechanisms, it is impossible to obtain real-time dynamic length change data along the X, Y, and Z axes. Existing devices struggle to capture the deformation differences between the equatorial and polar regions under high-speed rotation conditions, leading to errors in the quantitative analysis of key parameters such as oblateness and eccentricity.

[0048] In view of the shortcomings of the prior art, this embodiment provides a dynamic testing device and method for the spin process of an asteroid simulator, which can be referred to as follows:

[0049] As attached Figure 1 and attached Figure 2 As shown, a dynamic testing device for the spin process of an asteroid simulator includes a fixed stage 1, a rotating stage 2, a drive assembly, five telescopic components 4, and a measuring plate 5. The rotating stage 2 is rotatably mounted on the surface of the fixed stage 1 for placing and fixing the asteroid simulator. The drive assembly is located inside the fixed stage 1 and is connected to the rotating stage 2 to drive the rotating stage 2 to rotate. The surface of the rotating stage 2 is also provided with five telescopic rods, located around the asteroid simulator and on top. The telescopic ends of the telescopic components 4 are provided with the measuring plate 5, which is used to measure the initial and final lengths of the asteroid simulator. The measuring plate 5 is provided inside the measuring plate 5 and faces the asteroid simulator. The measuring sensor 6 is used to measure the length of the asteroid simulator that changes in real time during its rotation.

[0050] The fixed platform 1 is the foundation platform supporting the entire device, which can be implemented using a steel frame structure or a concrete base, providing stable support for rotational movement. The rotary platform 2 is a circular turntable mounted on the surface of the fixed platform 1, which rotates via a bearing assembly, used to fix the asteroid simulator and transmit driving torque. The drive assembly is the power output device, such as a servo motor with a reducer, used to precisely control the angular velocity of the rotary platform 2. The telescopic assembly 4 is an adjustable-length robotic arm structure, such as an electric actuator or hydraulic cylinder, whose orientation covers the X-axis, Y-axis radial, and Z-axis axial directions, used to establish multi-dimensional measurement benchmarks. The measuring plate 5 is a detection unit installed at the end of the telescopic assembly 4, which obtains absolute displacement values ​​through contact measurement, while simultaneously capturing dynamic relative deformation using a built-in acceleration sensor.

[0051] The measuring plate 5 has an opening slot on the side facing the asteroid simulator, and the measuring sensor 6 is located in the opening slot. A transparent glass is installed at the opening of the slot, and the surface of the transparent glass is flush with the surface of the measuring plate 5.

[0052] Specifically, as the asteroid simulator rotates with the rotary table 2, five telescopic components 4 form an encircling measurement layout from four horizontal directions and a top vertical direction. The drive component simulates different centrifugal force conditions by adjusting the rotation speed, and the telescopic components 4 perform position calibration according to a preset program. The measuring plate 5 records the reference length of each axis in the initial stage. During rotation, it continuously collects surface displacement data through contact sensors, while a built-in non-contact sensor monitors microscopic deformation fluctuations. The simultaneous acquisition of the two types of measurement data enables cross-verification of absolute and relative values. For example, when displacement increases suddenly in the equatorial region, the laser ranging data and the acceleration change curve complement each other, accurately reflecting the geometric evolution caused by material migration. After data fusion, a three-dimensional dynamic model is generated, which can calculate the flattening parameter and the trend of eccentricity change in real time.

[0053] Compared to existing technologies, traditional camera observation methods can only acquire two-dimensional projected images and cannot distinguish between axial and radial deformation differences. This solution establishes a three-dimensional measurement network through a multi-directional telescopic component 4, which can simultaneously capture the deformation characteristics of equatorial bulge and polar compression. The contact measuring plate 5 directly acquires the physical displacement, reducing image distortion errors compared to visual recognition methods. The relative value measurement sensor 6 compensates for the hysteresis of mechanical contact, and can still record instantaneous fluctuation data under high-speed rotation.

[0054] Through the above technical solution, this application achieves real-time monitoring of the three-axis length changes during the spin of an asteroid simulator, overcoming the technical bottleneck of traditional methods being unable to quantify dynamic deformation parameters. Multi-dimensional measurement data can be directly used to calculate key indicators such as flattening and eccentricity, providing precise experimental evidence for studying the migration patterns of matter under centrifugal force. The collaborative acquisition mechanism of absolute and relative values ​​effectively improves measurement accuracy under high-speed rotation, supporting the visualization analysis of complex deformation processes.

[0055] As attached Figure 2 As shown, this application further proposes a telescopic assembly 4 including a support sleeve 41, a telescopic member, a connecting rod 42, and a measuring component. The support sleeve 41 is fixed to the surface of the rotary table 2, with its opening aligned with the asteroid simulator. The telescopic member is installed inside the support sleeve 41, and the connecting rod 42 is connected to the telescopic member and slides along the inner wall of the support sleeve 41. The measuring component is integrated into the support sleeve 41 for directly detecting the displacement of the connecting rod 42.

[0056] The support sleeve 41 is a cylindrical structure with a guiding function, which can be made of metal or high-strength composite material. It ensures the linearity of the sliding trajectory by restricting the movement direction of the connecting rod 42. The telescopic component is a drive device that provides linear power, which can be an electric push rod or a hydraulic cylinder, used to precisely control the extension and retraction stroke of the connecting rod 42. The connecting rod 42 is a rigid component that transmits displacement. The measuring component is a displacement detection unit, which can be a laser displacement sensor or an optical encoder, to capture the positional changes of the connecting rod 42 in real time through non-contact detection.

[0057] Specifically, the opening of the support sleeve 41 faces the asteroid simulator, ensuring that the extension and retraction direction of the connecting rod 42 always maintains spatial consistency with the target measurement direction. When the telescopic component is activated, it pushes the connecting rod 42 to move along the axis of the support sleeve 41, ensuring that the measuring plate 5 always contacts the surface of the object being measured in the predetermined direction. The measuring assembly eliminates the error accumulation caused by multi-stage transmission in traditional indirect measurements by directly observing the physical displacement of the connecting rod 42. The rigid connection between the telescopic component and the connecting rod 42 avoids the hysteresis effect caused by flexible transmission, ensuring real-time synchronization of displacement data.

[0058] Compared to existing technologies, which rely solely on external cameras to capture simulated object shapes, the measurement accuracy of these methods is limited by lighting conditions, image distortion, and shooting angle, making it impossible to acquire real-time dynamic data along the axial direction. This solution addresses this by incorporating a guide sleeve 41 along the measurement direction, constraining the sliding freedom of the connecting rod 42 to a single axis, thus eliminating measurement deviations caused by multi-directional motion. The measurement component directly detects the displacement of the connecting rod 42, increasing the data acquisition frequency to the microsecond level compared to indirect measurement methods based on image processing, and is unaffected by changes in ambient light. The mating structure between the support sleeve 41 and the connecting rod 42 forms a physical limit, preventing measurement failure caused by mechanical vibration during high-speed rotation.

[0059] Through the above technical solution, this application achieves synchronous monitoring of the dynamic length changes of an asteroid simulator in three axes. The guiding function of the support sleeve 41 ensures the independence of each measurement direction and avoids mutual interference between different axial displacement data. The direct detection of the sliding distance of the connecting rod 42 by the measuring component reduces the measurement error of axial deformation to the micrometer level.

[0060] This application further proposes that the telescopic component can be an electric telescopic rod, a hydraulic telescopic rod, or a pneumatic telescopic rod.

[0061] Electric telescopic masts are mechanical devices that achieve linear displacement through electrical energy. Specifically, they can be implemented using a stepper motor or servo motor in conjunction with a ball screw structure, with precise displacement adjustment controlled by electrical signals. Hydraulic telescopic masts are telescopic mechanisms that transmit power using liquid pressure. Specifically, they can be implemented using a hydraulic pump station in conjunction with a piston-cylinder structure, with the telescopic stroke controlled by adjusting the hydraulic oil flow and pressure. Pneumatic telescopic masts are linear motion devices driven by compressed gas. Specifically, they can be implemented using a combination of a cylinder and a solenoid valve, achieving rapid telescopic movement through changes in air pressure.

[0062] Specifically, the telescopic rods with different power sources are designed to meet specific testing requirements. When high-precision displacement control is needed, an electric telescopic rod is used, achieving millimeter-level or even micrometer-level displacement adjustment through programmed control. When bearing large-mass simulations or applying high-intensity contact pressure, a hydraulic telescopic rod is used, utilizing the incompressibility of liquids to provide stable support. When rapid adjustment of the telescopic frequency or response to dynamic changes is required, a pneumatic telescopic rod is used, leveraging the compressibility of gas to achieve millisecond-level response speeds. These three power sources are integrated into the same testing device through a modular design, allowing for flexible replacement or combination according to experimental needs.

[0063] Through the above technical solution, this application can select the appropriate type of telescopic component 4 according to parameters such as the mass of the simulated object, the experimental rotation speed, and the data acquisition frequency, thereby ensuring the effective acquisition of dynamic deformation data of the simulated object under different test conditions.

[0064] This application further proposes a measuring component including a scale set on a connecting rod 42 and a camera set on a support sleeve 41, wherein the camera and the scale on the connecting rod 42 form a spatial correspondence.

[0065] Here, the scale refers to the measurement markings on the surface of the connecting rod 42; the camera refers to the image acquisition device fixed on the support sleeve 41, specifically a high-speed industrial camera, whose lens optical axis is perpendicularly aligned with the plane where the scale is located. This feature ensures that images of scale position changes can be continuously acquired during the sliding of the connecting rod 42 by establishing a stable spatial correspondence.

[0066] Specifically, when the connecting rod 42 slides axially under the drive of the telescopic component, its surface scale moves synchronously. The camera on the support sleeve 41 acquires scale images at a fixed frequency, calculates the pixel displacement of a specific scale mark in adjacent images using an image recognition algorithm, and converts the pixel displacement into an actual physical displacement value by combining the calibration parameters.

[0067] Through the above technical solution, this application achieves sub-millimeter precision measurement of the sliding distance of the connecting rod 42, and can accurately obtain displacement data.

[0068] As attached Figure 1 As shown, this application further proposes that a U-shaped support rod 21 is provided on the rotary table 2, and a telescopic component 4 located on the top of the asteroid simulator is provided on the U-shaped support rod 21.

[0069] The U-shaped support rod 21 refers to a frame structure consisting of two vertical support rods and a horizontal beam. It can be implemented using metal profile welding or a one-piece molding process, with its two side support points forming a stable connection to the surface of the rotary table 2. This structure distributes the centrifugal force load during the rotation of the rotary table 2 through the two side support points, while simultaneously providing suspended support for the telescopic assembly 4 using the top beam. The telescopic assembly 4, in the top direction, refers to the measuring unit located directly above the asteroid simulator. It can be implemented using an electric push rod, hydraulic cylinder, or pneumatic actuator, with its telescopic end fixed to the measuring plate 5 via a connecting rod 42.

[0070] Specifically, when the rotary table 2 drives the asteroid simulator to rotate at high speed, the two fulcrums of the U-shaped support rod 21 rotate synchronously with the rotary table 2, preventing radial displacement of the support structure due to centrifugal force. The suspended layout of the top beam keeps the telescopic assembly 4 vertically aligned with the apex of the asteroid simulator, and the measuring plate 5 is adjusted to contact the surface of the asteroid simulator via the telescopic end. During rotation, the telescopic assembly 4 drives the connecting rod 42 to slide through the telescopic component inside the support sleeve 41, while the measuring sensor 6 measures the dynamic length data in the top direction in real time. The double-fulcrum design of the U-shaped support rod 21 further reduces the impact of rotational vibration on the top telescopic assembly 4, ensuring that the measuring sensor 6 continuously acquires vertical deformation data under high-speed rotation conditions.

[0071] Compared to existing technologies, current devices typically mount the top telescopic component 4 directly on the edge of the rotary table 2 or on a lateral support, resulting in an angle between the measurement direction and the rotation axis, making it impossible to vertically align with the apex of the asteroid simulator. Furthermore, the single-support-point mounting structure is prone to radial displacement due to centrifugal force during high-speed rotation, causing unstable contact between the measuring plate 5 and the simulator surface. This solution uses a U-shaped support rod 21 to form double-sided fixed supports, effectively suppressing structural displacement caused by centrifugal force. The suspended layout of its top crossbeam ensures the vertical orientation of the telescopic component 4, eliminating measurement angle errors.

[0072] Through the above technical solution, this application solves the problem of data deviation of the measuring sensor 6 caused by the unstable installation structure of the top telescopic component 4, ensures the dynamic monitoring accuracy of the length change in the top direction during high-speed rotation, and provides a structural basis for synchronously acquiring X, Y, and Z axis deformation data.

[0073] As attached Figure 1 As shown, this application further proposes a dynamic testing device for the spin process of an asteroid simulator, which also includes a stage 7, a pressure head 71, an axial displacement extensometer, and a radial displacement extensometer. The stage 7 is mounted on a fixed platform 1, and a placement disk 74 is mounted on the stage 7. A pressure plate is mounted on the bottom of the pressure head 71 and is positioned corresponding to the placement disk 74. The axial displacement extensometer is axially engaged with the simulator, and the radial displacement extensometer is radially engaged with the simulator.

[0074] The stage 7 refers to the rigid support platform on the fixed stage 1 used to support the test object. A placement tray 74 is provided on the stage 7 for placing the asteroid simulator. The pressure head 71 refers to a force-applying mechanism with power output function. Both the axial displacement extensometer and the radial displacement extensometer employ existing technology to capture lateral expansion or contraction displacement, and their function is to simultaneously record the equatorial bulge phenomenon caused by centrifugal force.

[0075] Specifically, after the simulant has been spun, a thin layer of lubricant (Vaseline) is applied to both the top and bottom surfaces and then placed in the center of the placement tray 74. A rigid pad is placed between the top of the simulant and the pressure plate. Then, axial and radial displacement extensometers are installed, and their positions are adjusted to obtain initial readings. The pressure head 71 is adjusted to ensure uniform contact between the rigid pad and the pressure plate, so that the sample is subjected to uniform force. The load is applied at a rate of 0.1-0.5 MPa per second until the sample fails. The experimental failure load and the phenomena that occur during the experiment are recorded, and the sample after failure is described. Finally, the stress-strain curve of the simulant is obtained.

[0076] Through the above technical solution, this application achieves simultaneous monitoring of axial and radial deformation under rotation. By constructing a three-dimensional deformation model through correlation analysis of orthogonal displacement data, it can accurately identify the deformation characteristics of equatorial bulge and polar flattening, providing data support for establishing material failure criteria under centrifugal force. During the static loading stage, the dual extensometers work together to fully record the anisotropic deformation behavior during compression, and the influence of the spin process on the mechanical properties of the material is revealed through stress-strain curves.

[0077] As attached Figure 1 As shown, this application further proposes that the pressure-bearing head 71 is mounted on the fixed platform 1 via a rigid support 73.

[0078] Among them, rigid support 73 refers to a support structure made of high-rigidity material, which can be steel, alloy or engineering plastic.

[0079] This application further proposes to set a fixing member at the center of the rotating stage 2, and the fixing member is connected to the asteroid simulation object.

[0080] The fixing component refers to the mechanical constraint part located at the geometric center of the rotary table 2. It can be implemented using a clamp or bolt structure with positioning grooves, applying constraint force to the asteroid simulator through physical contact. The connection method refers to the contact form between the fixing component and the asteroid simulator, which can be implemented using mechanical snap-fit, magnetic adsorption, or adhesive fixation, restricting the radial displacement of the asteroid simulator during rotation through rigid contact.

[0081] Specifically, the fixing component is positioned at the central axis of the rotary table 2, and the asteroid simulator is forcibly positioned within the constraint range of this component during installation. After the rotary table 2 is started, the fixing component transmits the rotational driving force through the contact surface, while simultaneously limiting the radial sliding that the asteroid simulator may experience under centrifugal force. Through the axial symmetry constraint of the fixing component, it is ensured that the center of mass of the asteroid simulator always coincides with the axis of the rotary table 2, thereby eliminating measurement errors caused by installation eccentricity.

[0082] Through the above technical solution, this application solves the problem of axis offset caused by unstable fixation when the asteroid simulation object rotates at high speed, ensures the stability of the measurement benchmark for morphological changes during dynamic testing, and improves the acquisition accuracy of length change data and experimental repeatability.

[0083] This application further proposes a drive assembly including a motor, which is fixedly installed inside the fixed platform 1, and the output shaft of the motor is directly connected to the rotary table 2.

[0084] The motor refers to a power device that converts electrical energy into mechanical energy. Specifically, it can be a servo motor or a stepper motor, used to provide controllable rotational driving force for the rotary table 2. The output shaft refers to the mechanical structure that transmits power from the motor. Specifically, it can be rigidly connected to the rotary table 2 using a flange connection or a coupling, used to directly drive the rotary table 2 to rotate.

[0085] In some embodiments, the motor can be a servo motor with a high-precision encoder, and the output shaft is bolted to the rotary table 2 via a flange. In another embodiment, the output shaft is connected to the rotary table 2 via a flexible coupling to compensate for minor assembly errors.

[0086] As attached Figure 3 As shown, this application also proposes a dynamic testing method for the spin process of an asteroid simulator, based on the aforementioned dynamic testing device for the spin process of an asteroid simulator, comprising the following steps:

[0087] Step S100: Place the asteroid simulator on the rotating platform and activate the telescopic assembly to measure the initial length of the asteroid simulator in conjunction with the measuring plate.

[0088] In this embodiment, after the asteroid simulator is fixed on the rotating platform 2, five telescopic components 4 measure its initial length along its perimeter and top, respectively, and establish a reference coordinate system. Before the drive component rotates the simulator at a set speed, the initial length of the asteroid simulator is measured by the telescopic components 4 in conjunction with the measuring plate 5. After the measurement is completed, the telescopic components 4 and the measuring plate 5 are reset to avoid affecting the rotation of the asteroid simulator.

[0089] Step S200: Activate the drive assembly and the measurement sensor to rotate the asteroid simulator and measure the length of the asteroid simulator that changes during rotation.

[0090] In this embodiment, the drive assembly and the measuring sensor 6 are activated. During the rotation process, the measuring sensor 6 records the deformation in the three-axis directions in real time.

[0091] Step S300: After a preset time, the drive component is turned off, and the termination length of the asteroid simulator is measured by the telescopic component in conjunction with the measuring plate. All measurement data is then transmitted to the control terminal to complete the test experiment.

[0092] Once the preset time is reached, the drive component stops operating, and the telescopic component 4, in conjunction with the measuring plate 5, measures the termination length again. Finally, the initial length data, termination length data, and dynamic change data measured by the measuring sensor 6 are transmitted to the control terminal 8. The control terminal 8 calculates parameters such as flatness and eccentricity based on the difference. During this process, the continuous sampling of the measuring sensor 6 and the measurement of the telescopic component 4 complement each other, fully covering the deformation and material migration data throughout the entire rotation cycle.

[0093] The control terminal 8 monitors the spin angular velocity over time in real time to verify whether the conservation of angular momentum is satisfied, where the moment of inertia I changes with the shape. The data processing unit processes the real-time data to obtain the three-axis length versus time curves of the simulated object at different rotation rates. Furthermore, the lengths of the principal axes (major axes a and b on the equatorial plane) and the polar axis (minor axis c) are measured in real time, and the flattening and elongated ellipsoid eccentricity are calculated, where c0 is the initial polar radius. Processing this data yields the flattening and elongated ellipsoid eccentricity curves over time.

[0094] Through the above technical solution, this application solves the problem in the prior art that it is impossible to monitor the dynamic deformation of asteroid simulators in three axes during spin in real time. It can accurately obtain the correlation data between rotation rate and morphological parameters, providing experimental support for establishing asteroid evolution models. At the same time, by comparing absolute and relative values, it effectively distinguishes the stage characteristics of deformation and material migration, providing a data basis for analyzing structural instability phenomena under critical angular velocities.

[0095] Other embodiments of the invention will readily occur to those skilled in the art upon consideration of the specification and practice of the solutions disclosed herein. This invention is intended to cover any variations, uses, or adaptations of the invention that follow the general principles of the invention and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only, and the true scope and spirit of the invention are indicated by the claims.

Claims

1. An apparatus for dynamic testing of asteroid analog spin processes, characterized in that, The device comprises: a fixed table; a rotating table arranged on the surface of the fixed table and used for placing an asteroid simulation object; a driving assembly arranged in the fixed table; the driving assembly is connected with the rotating table to drive the rotating table to rotate; five telescopic assemblies arranged on the surface of the rotating table and respectively located around and on the top of the asteroid simulation object; a measuring plate arranged at the telescopic end of the telescopic assembly and used for measuring the initial length and the final length of the asteroid simulation object; a measuring sensor arranged in the measuring plate and facing the asteroid simulation object and used for measuring the length of the asteroid simulation object changing in real time during rotation.

2. The device for dynamic testing of asteroid analog spinning processes according to claim 1, characterized in that The telescopic assembly comprises: a support sleeve arranged on the surface of the rotating table and having an opening facing the asteroid simulation object; a telescopic part arranged in the support sleeve; a connecting rod slidingly arranged in the support sleeve and having one side connected with the telescopic part and the other end connected with the measuring plate; a measuring assembly arranged on the support sleeve and used for measuring the sliding distance of the connecting rod.

3. A device for dynamic testing of the spin process of an asteroid analog according to claim 2, characterized in that The telescopic part can be an electric telescopic rod, a hydraulic telescopic rod or a pneumatic telescopic rod.

4. The device of claim 2, wherein, The measuring assembly comprises: a scale arranged on the connecting rod; a camera arranged on the support sleeve and corresponding to the scale on the connecting rod.

5. The device of claim 1, wherein, A U-shaped support rod is arranged on the rotating table, and the telescopic assembly arranged on the top of the asteroid simulation object is arranged on the U-shaped support rod.

6. The device of claim 1, wherein, The device further comprises: a carrier table arranged on the fixed table and having a placing disc arranged thereon; a pressure head arranged on the fixed table and having a pressure plate arranged at the bottom thereof and corresponding to the carrier table; an axial displacement extensometer arranged on the fixed table and matched with the axial direction of the asteroid simulation object and used for measuring the change amount of the axial direction of the asteroid simulation object; a radial displacement extensometer arranged on the fixed table and matched with the radial direction of the asteroid simulation object and used for measuring the change amount of the radial direction of the asteroid simulation object.

7. A device for dynamic testing of the spin process of an asteroid analog according to claim 6, characterized in that The pressure head is arranged on the fixed table through a rigid support.

8. The device of claim 1, wherein, A fixing part is arranged at the center of the rotating table and connected with the asteroid simulation object.

9. The device of claim 1, wherein, The driving assembly comprises: a motor arranged in the fixed table and having an output shaft connected with the rotating table.

10. A method of dynamic testing of asteroid analog spinning process, based on the dynamic testing device of asteroid analog spinning process according to any one of claims 1-9, characterized in that, The device comprises: placing the asteroid simulation object on the rotating table and starting the telescopic assembly to cooperate with the measuring plate to measure the initial length of the asteroid simulation object; starting the driving assembly and the measuring sensor to drive the asteroid simulation object to rotate and measure the length of the asteroid simulation object changing during rotation; after a preset time, stopping the driving assembly, measuring the final length of the asteroid simulation object through the telescopic assembly cooperating with the measuring plate, transmitting all the measurement data to a control terminal and completing the test experiment.

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