Equivalent static load determination method, system, medium and equipment for satellite transportation shock response

Abstract

This invention provides a method, system, medium, and equipment for determining the equivalent static load of satellite transportation impact response, including: Step S1: Establishing a satellite transportation finite element model and obtaining the model establishment result information; Step S2: Based on the satellite transportation finite element model establishment result information and the impact signal, performing constant amplitude static load analysis and obtaining constant amplitude static load analysis result information; Step S3: Based on the constant amplitude static load analysis result information, performing result verification and judgment, and obtaining the equivalent static load determination result information of satellite transportation impact response. This invention uses the constant amplitude static load method to analyze the impact response, ignoring the influence of system dynamic effects and only focusing on the maximum value of the response, reducing the time cost and computational load of transportation impact response analysis, and is a fast and efficient equivalent determination method.

Description

Technical Field

[0001] This invention relates to the field of spacecraft mechanics simulation technology, specifically to a method, system, medium, and equipment for determining the equivalent static load of satellite transportation impact response. Background Technology

[0002] Transportation is a crucial part of the satellite development process. Satellites are typically packaged in transport containers using transport support fixtures. Impact is a common form of load during satellite transportation. Uneven roads, turns and braking during rail transport, and landing during air transport all generate impact excitations for the satellite. Whether the satellite will collide with the packaging container under transport impact, and whether excessive stress will lead to structural failure, are issues that must be considered in engineering.

[0003] Simulation analysis of impact processes mainly employs transient response analysis and impact response spectrum analysis. The transient response method uses the time-domain curve of the impact signal as input and solves the system's dynamic equations using direct or modal methods to obtain the transient response. Impact response spectrum analysis, on the other hand, transforms the time-domain impact signal into a frequency-domain impact response spectrum and obtains the maximum response of the impact process through a linear transformation of the system's modal analysis results. During satellite transportation, the time-domain impact curve changes drastically and is complex to describe. Transient response analysis requires small time steps to ensure solution accuracy, resulting in complex calculations and a large amount of data. Impact response spectrum analysis reduces computation by processing the time-domain impact signal, but the solution process remains complex. In engineering, the impact response during satellite transportation generally focuses only on the maximum value in the time domain, serving as the basis for determining whether a collision or failure will occur in the satellite structure.

[0004] In recent years, research has been conducted on impact response analysis and the design of satellite transportation structures, for example:

[0005] (1) Satellite Transportation Vibration Response Analysis (CN11-5333 / V). This article mainly analyzes the transportation vibration response test data of several typical satellites from the perspective of measured data, and compares and evaluates the impact of transportation modes such as highways, railways, and aviation on satellites. This patent mainly focuses on the impact excitation during transportation and adopts a simulation prediction method.

[0006] (2) Universal transport packaging box for remote sensing satellites (CN102774576A). This invention discloses a universal transport packaging box for remote sensing satellites, which is equipped with a shock-absorbing device on the inner side of the bottom of the box. It is a typical type of packaging box for satellite transportation and does not involve mechanical response analysis of the satellite transportation process.

[0007] (3) Impact Response Analysis of Vibration Isolation System with Limitation (CN31-1316 / TU) This article simulates the impact on shipborne equipment, analyzes the influence of limiting parameters on the impact response, and verifies the simulation results through impact tests. The research object of this invention is the transportation process of satellites. The dynamic characteristics of satellites and the excitation characteristics of transportation impacts are fundamentally different from those of shipboard equipment, and this invention focuses on an efficient equivalent analysis and judgment method.

[0008] In summary, existing related technologies mainly focus on the structural design of transport packaging boxes and the measurement of transport impact response. This patent, from the perspective of simulation prediction, proposes an equivalent static load determination method for impact response to adapt to future high-density satellite development missions. It can quickly provide conclusions and evaluations on structural collisions and failures of concern during satellite transportation, providing a basis for structural design and transportation scheme design. Summary of the Invention

[0009] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method, system, medium, and device for determining the equivalent static load of satellite transportation impact response.

[0010] The equivalent static load determination method for satellite transportation impact response provided by the present invention includes:

[0011] Step S1: Establish a finite element model of satellite transportation and obtain the results of establishing the finite element model of satellite transportation;

[0012] Step S2: Based on the results information and impact signal of the satellite transportation finite element model, perform constant amplitude static load analysis and obtain the constant amplitude static load analysis results information;

[0013] Step S3: Based on the results of the constant amplitude static load analysis, verify and judge the results to obtain the equivalent static load judgment results of the satellite transportation impact response.

[0014] Preferably, step S3 includes:

[0015] Step S3.1: Determine whether collision stress failure information has occurred and obtain the determination result information.

[0016] Preferably, step S3.1 includes:

[0017] Step S3.1.1: If so, perform structural optimization and transportation scheme optimization, and obtain structural optimization result information and transportation scheme optimization result information.

[0018] Preferably, step S3 includes:

[0019] Step S3.1: If not, obtain the completion judgment result information.

[0020] The present invention provides a method for determining the equivalent static load of satellite transportation impact response, comprising:

[0021] Module M1: Establish a finite element model of satellite transportation and obtain the results of establishing the finite element model of satellite transportation;

[0022] Module M2: Based on the results information and impact signals of the satellite transportation finite element model, perform constant amplitude static load analysis and obtain constant amplitude static load analysis results information;

[0023] Module M3: Based on the results of the constant amplitude static load analysis, it performs result verification and judgment to obtain the equivalent static load judgment result information of the satellite transportation impact response.

[0024] Preferably, the module M3 includes:

[0025] Module M3.1: Determines whether collision stress failure information has occurred and obtains the determination result information.

[0026] Preferably, module M3.1 includes:

[0027] Module M3.1.1: If so, perform structural optimization and transportation scheme optimization, and obtain structural optimization result information and transportation scheme optimization result information.

[0028] Preferably, the module M3 includes:

[0029] Module M3.1: If not, obtain the completion judgment result information.

[0030] According to the present invention, a computer-readable storage medium storing a computer program is provided, wherein when the computer program is executed by a processor, the steps of an equivalent static load determination method for satellite transportation impact response are implemented.

[0031] An equivalent static load determination device for satellite transportation impact response provided by the present invention includes: a controller;

[0032] The controller includes a computer-readable storage medium storing a computer program, which, when executed by a processor, implements the steps of an equivalent static load determination method for satellite transport impact response; or, the controller includes an equivalent static load determination system for satellite transport impact response.

[0033] Compared with the prior art, the present invention has the following beneficial effects: Attached Figure Description

[0034] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0035] Figure 1This is a schematic diagram of the equivalent static load determination method in this invention.

[0036] Figure 2 This is a schematic diagram of the satellite transportation scheme in this invention.

[0037] Figure 3(a) is a schematic diagram of the time-domain curve of the impact signal in this invention.

[0038] Figure 3(b) is a schematic diagram of the impact signal response spectrum in this invention.

[0039] In the diagram: 1-Transportation support fixture, 2-Connecting ring, 3-Satellite body, 4-Strut, 5-Vibration damping spring. Detailed Implementation

[0040] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0041] like Figure 1 -3. The equivalent determination method for satellite transportation impact response mainly includes the processes of finite element model establishment, impact signal extraction, constant amplitude static load analysis, result verification and judgment, and iterative optimization analysis. The finite element model generally includes finite element models of the satellite and transportation support fixtures, which are established based on the actual state of satellite transportation, accurately define the connection method and boundary conditions, and can fully reflect the mechanical characteristics of the structure.

[0042] The impact signal is generally derived from measured data of similar transportation processes. To ensure sufficient safety margin, the maximum envelope of the data is typically used. When relevant measured data is lacking, standards and specifications such as "Environmental Conditions for Military Material Transportation" can be referenced for determination.

[0043] The constant amplitude static load analysis uses the maximum value of the impact signal in the time domain as the static overload condition, ignores the dynamic effects of the system, and only cares about the maximum value of the response. The analysis results include the displacement and stress of the satellite structure.

[0044] The results verification is generally performed by using transient response analysis or impact response spectrum analysis to verify the constant amplitude static load analysis. Generally, if the difference in analysis results is within 10%, the constant amplitude static load analysis method can be considered effective and applicable to the transportation impact process of this type of satellite. When the displacement and stress analysis results indicate that structural collision or failure will occur during transportation, iterative optimization analysis is required.

[0045] The iterative optimization analysis described is a cyclical process of satellite structure optimization, transportation scheme optimization, and constant amplitude static load analysis. Based on the state-corrected finite element model of structure optimization and transportation scheme optimization, constant amplitude static load analysis is carried out until the analysis results show that no structural collision or failure will occur during transportation, at which point the cycle ends and the judgment process is completed.

[0046] The impact response equivalent static load determination method for satellite highway transportation, the determination process is as follows: Figure 1 As shown, the main steps include finite element model establishment, impact signal extraction, constant amplitude static load analysis, result verification and judgment, and iterative optimization analysis.

[0047] The finite element model is established based on the actual state of satellite transportation. The satellite transportation state is based on... Figure 2 For example, satellite 3 is connected to transport support fixture 1 via connecting ring 2 and receives auxiliary support from strut 4. Transport support fixture 1 is connected to transport packaging box via vibration damping spring 5. In finite element modeling, the connection method and boundary conditions between the satellite and support fixture are consistent with the actual state.

[0048] The impact signal is obtained from the actual transport data of the same type of transport vehicle, and the maximum envelope is taken. It includes two forms: impact time domain curve and impact response spectrum, as shown in Figure 3.

[0049] Using the peak value of the impact time-domain curve in Figure 3(a) as the static overload condition, static load analysis was carried out based on commercial finite element software to obtain the displacement and stress response on the celestial structure.

[0050] Furthermore, using the impact response spectrum curve in Figure 3(b) as input, impact response spectrum analysis was conducted using commercial finite element software to obtain the displacement and stress responses on the satellite structure. The results were compared with those of the static load analysis. When the difference was within 10%, the constant amplitude static load analysis method was considered effective and applicable to the transportation analysis of this type of satellite. It should be noted that the response of the satellite structure under transportation impact is generally slightly less than that under constant amplitude static load, and the results of the static load analysis are more conservative.

[0051] Furthermore, after verifying the effectiveness of the constant amplitude static load analysis method, the displacement analysis results are decomposed to determine whether the satellite will collide with the packaging box; the structural stress analysis results are then used for strength verification to determine whether the structure will fail.

[0052] Furthermore, when the analysis results indicate that structural collision or failure may occur, the transportation connection method, transportation support tooling, and celestial structure are locally strengthened or optimized, the finite element model is modified, and constant amplitude static load analysis is carried out again until the design scheme can meet the requirements.

[0053] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application 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. Therefore, they should not be construed as limitations on this application.

[0054] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for determining the equivalent static load of satellite transportation impact response, characterized in that, include: Step S1: Establish a finite element model of satellite transportation and obtain the results of establishing the finite element model of satellite transportation; Step S2: Based on the results information and impact signal of the satellite transportation finite element model, perform constant amplitude static load analysis and obtain the constant amplitude static load analysis results information; Step S3: Based on the results of the constant amplitude static load analysis, verify and judge the results to obtain the equivalent static load judgment results of the satellite transportation impact response; The finite element model includes finite element models of the satellite and transportation support fixtures, which are established based on the actual state of satellite transportation, defining the connection method and boundary conditions. When the analysis results of displacement and stress indicate that structural collision or failure will occur during transportation, iterative optimization analysis needs to be carried out. The iterative optimization analysis is a cyclical process of satellite structure optimization, transportation scheme optimization, and constant amplitude static load analysis. Based on the state-corrected finite element model of structural optimization and transportation scheme optimization, and conducting constant amplitude static load analysis, the loop ends and the judgment process is completed until the analysis results show that no structural collision or failure will occur during the transportation process. The constant amplitude static load analysis uses the maximum value of the impact signal in the time domain as the static overload condition, ignores the dynamic effects of the system, and only cares about the maximum value of the response. The analysis results include the displacement and stress of the satellite structure.

2. The method for determining the equivalent static load of satellite transportation impact response according to claim 1, characterized in that, Step S3 includes: Step S3.1: Determine whether collision stress failure information has occurred and obtain the determination result information; Step S3.1.1: If so, perform structural optimization and transportation scheme optimization, and obtain structural optimization result information and transportation scheme optimization result information.

3. An equivalent static load determination system for satellite transportation impact response, characterized in that, include: Module M1: Establish a finite element model of satellite transportation and obtain the results of establishing the finite element model of satellite transportation; Module M2: Based on the results information and impact signals of the satellite transportation finite element model, perform constant amplitude static load analysis and obtain constant amplitude static load analysis results information; Module M3: Based on the results of the constant amplitude static load analysis, the module verifies and judges the results to obtain the equivalent static load determination results of the satellite transportation impact response. The finite element model includes finite element models of the satellite and transportation support fixtures, which are established based on the actual state of satellite transportation, defining the connection method and boundary conditions. When the analysis results of displacement and stress indicate that structural collision or failure will occur during transportation, iterative optimization analysis needs to be carried out. The iterative optimization analysis is a cyclical process of satellite structure optimization, transportation scheme optimization, and constant amplitude static load analysis. Based on the state-corrected finite element model of structural optimization and transportation scheme optimization, and conducting constant amplitude static load analysis, the loop ends and the judgment process is completed until the analysis results show that no structural collision or failure will occur during the transportation process. The constant amplitude static load analysis uses the maximum value of the impact signal in the time domain as the static overload condition, ignores the dynamic effects of the system, and only cares about the maximum value of the response. The analysis results include the displacement and stress of the satellite structure.

4. The equivalent static load determination system for satellite transportation impact response according to claim 3, characterized in that, The module M3 includes: Module M3.1: Determines whether collision stress failure information has occurred and obtains the determination result information; Module M3.1.1: If so, perform structural optimization and transportation scheme optimization, and obtain structural optimization result information and transportation scheme optimization result information.

5. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it implements the steps of the equivalent static load determination method for satellite transportation impact response as described in any one of claims 1 to 2.

6. An equivalent static load determination device for satellite transportation impact response, characterized in that, include: Controller; The controller includes a computer-readable storage medium storing a computer program as described in claim 5, wherein the computer program, when executed by a processor, implements the steps of the equivalent static load determination method for satellite transportation impact response as described in any one of claims 1 to 2; or, the controller includes an equivalent static load determination system for satellite transportation impact response as described in any one of claims 3 to 4.

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