Decoupling analysis method for structural response caused by micro-vibration of multi-disturbance vibration source

Abstract

The invention provides a decoupling analysis method for structural response caused by micro-vibration of multiple disturbance vibration sources, which comprises the following steps: acquiring disturbance vibration force data of satellite moving parts, and converting the disturbance vibration force data to the local mass center of each moving part to obtain disturbance vibration force converted to the mass center of each substructure; each movable part is regarded as a substructure, a connection interface exists in the middle of each substructure, and an interface comprehensive kinetic equation of any two substructures is constructed by combining the disturbance vibration force converted to the mass center of each substructure; according to the interface comprehensive kinetic equation, the acceleration response at the substructure interface is obtained; according to the acceleration response at the interface of the substructure, obtaining the acceleration response in the substructure; according to the acceleration response at the interface of the substructure and the acceleration response in the substructure, obtaining the acceleration response of the substructure; obtaining a substructure displacement response according to the substructure acceleration response; and superposing all displacement responses generated when the single substructure is connected with other substructures to obtain the displacement response of the single substructure.

Description

Technical Field

[0001] The invention relates to a decoupling analysis method for structural response caused by micro-vibration of multiple disturbance sources, which can be used for decoupling analysis and processing of structural response caused by local disturbance force inside a spatial structure. Background Art

[0002] There are multiple moving parts (momentum wheels, control moment gyroscopes, refrigerators, etc.) inside high-resolution optical remote sensing satellites, and the structure is complex. The equipment will generate micro-vibrations during operation, affecting the on-orbit imaging quality of space optical payloads. The satellite micro-vibration suppression capability is one of the important indicators to measure the performance of the satellite platform, and it is also the basic condition to ensure that the satellite platform can adapt to high-resolution optical payloads. During the satellite design phase, in order to enable the satellite to have micro-vibration suppression capabilities, it is necessary to obtain the micro-vibration disturbance characteristics of the moving parts, as well as the transmission characteristics and dynamic response characteristics of the micro-vibration inside the satellite, so as to serve as the basis for the satellite to carry out micro-vibration suppression design.

[0003] Remote sensing satellites are multi-disturbance source structures due to their working principles and mechanical design status, and they have complex spatial geometric connections inside, which causes the internal disturbance forces to interact with each other, making the local responses of each structure coupled with each other. At present, it is difficult to analyze the local responses of multi-disturbance source mechanisms such as the satellite's internal momentum wheel, control moment gyro, and refrigerator, which makes it difficult to guide the optimal design of satellite micro-vibration suppression, and the local response analysis of multi-disturbance source mechanisms is not comprehensive enough. Therefore, it is of great significance to decouple the structural response caused by multi-disturbance source micro-vibration and use it as a basis for judging subsequent vibration suppression. Summary of the invention

[0004] In order to overcome the deficiencies in the prior art, the inventors have conducted intensive research and provided a method for decoupling analysis of structural responses caused by micro-vibrations from multiple disturbance sources. Based on the dynamic substructure method, response decoupling analysis is performed on the responses of each substructure, thereby realizing analysis of the response characteristics of each substructure when the overall structure of the remote sensing satellite is affected by its own multiple main disturbance sources.

[0005] The technical solution provided by the present invention is as follows:

[0006] In a first aspect, a method for decoupling analysis of structural response caused by micro-vibration of multiple disturbance sources is provided, comprising:

[0007] Obtaining disturbance force data of satellite moving parts, converting the disturbance force data to the local center of mass of each moving part, and obtaining the disturbance force converted to the center of mass of each substructure;

[0008] Each active part is regarded as a substructure with a connecting interface in between. Combined with the perturbation force converted to the center of mass of each substructure, the comprehensive interface dynamic equation of any two substructures is constructed.

[0009] According to the comprehensive interface dynamics equation, the acceleration response at the substructure interface is obtained;

[0010] According to the acceleration response at the interface of the substructure, the acceleration response inside the substructure is obtained;

[0011] The acceleration response of the substructure is obtained according to the acceleration response at the substructure interface and the acceleration response inside the substructure;

[0012] According to the acceleration response of the substructure, the displacement response of the substructure is obtained;

[0013] All displacement responses generated when a single substructure is connected to other substructures are superimposed to obtain the displacement response of the single substructure.

[0014] In a second aspect, a decoupling analysis device for structural response caused by micro-vibration of multiple disturbance sources comprises:

[0015] one or more processors;

[0016] a storage device for storing one or more programs,

[0017] When the one or more programs are executed by the one or more processors, the one or more processors implement the structural response decoupling analysis method caused by micro-vibrations of multiple disturbance sources as claimed in any one of claims 1 to 6.

[0018] In a third aspect, a readable storage medium stores a computer program, which, when executed by a processor, implements the method for decoupling analysis of structural responses caused by micro-vibrations of multiple disturbance sources as described in the first aspect.

[0019] In a fourth aspect, a computer program product is provided, comprising: a computer program, which, when executed, executes the method for decoupling analysis of structural response caused by micro-vibrations of multiple disturbance sources as described in the first aspect.

[0020] The structural response decoupling analysis method caused by micro-vibration of multiple disturbance sources provided by the present invention has the following beneficial effects:

[0021] (1) The present invention provides a method for decoupling and analyzing structural responses caused by micro-vibrations of multiple disturbance sources. The method performs coordinate transformation on the disturbance forces obtained by each force platform, and then divides the substructures and performs analysis based on the dynamic substructure method. Compared with the structural responses obtained by separate tests that are currently widely used, the method comprehensively considers the mutual coupling factors between the responses of different disturbance sources. The method has obvious advantages in decoupling and analyzing the individual responses of each substructure under the action of multi-source disturbance forces, making the micro-vibration analysis of each substructure under the influence of such mutual coupling more complete, and can provide a reference for the subsequent satellite micro-vibration suppression design.

[0022] (2) The present invention provides a method for decoupling analysis of structural responses caused by micro-vibrations of multiple disturbance sources, which can superimpose the overall structural response according to the responses of each substructure, thereby forming a complete process from local structural analysis to overall structural analysis. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a flow chart of the decoupling analysis method for structural response caused by micro-vibrations from multiple disturbance sources;

[0024] Figure 2 Schematic diagram of the structure division of the refrigerator Dewar end and compressor terminal. DETAILED DESCRIPTION

[0025] The following detailed description of the present invention will make the features and advantages of the present invention more clear and explicit.

[0026] The word “exemplary” is used exclusively herein to mean “serving as an example, example, or illustration.” Any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments.

[0027] The present invention provides a method for decoupling analysis of structural response caused by micro-vibration of multiple disturbance sources, such as Figure 1 As shown, the following steps are included:

[0028] Step 1: Convert the disturbance force data measured by the force platform during the disturbance force test of the satellite moving parts to the local center of mass of each moving part:

[0029]

[0030] Where: f i (i=1,2,…,n) are the disturbance force vectors measured by the force platforms at each end; R is the disturbance force vector converted from the disturbance force measured by the force platform to the local center of mass of each substructure; i (i=1,2,…,N) is the transformation matrix between the local coordinates of the end force platform and the local coordinates at the center of mass of each substructure.

[0031] Step 2: Use the dynamic substructure method to treat each active component as a substructure with a connection interface between them. Figure 2 As shown, the refrigerator consists of two parts: the dewar and the compressor. The dewar is divided into substructure A; the compressor is divided into substructure B; substructure A and substructure B are connected by copper pipes. Here we consider the case of two substructures, and the displacement analytical expressions of each substructure are:

[0032]

[0033] Where: X A and X B represents the displacement response of the two substructures; X S A and X BS represents the displacement response of the degree of freedom inside the corresponding substructure; and represents the displacement response of the degree of freedom corresponding to the connection interface between the two substructures; q b A and q Bb represents the modal coordinates of the corresponding substructure; and The eigenvalue vector representing the corresponding substructure; and Represents the statically restrained modes corresponding to the two substructures.

[0034] The modal synthesis method is used to obtain the eigenvalues ​​and eigenvectors of the system, and then the modal superposition method is used to superimpose the responses, which requires complicated and lengthy calculations. The present invention uses the interface comprehensive dynamics equation for calculation:

[0035] (M A (ω)+M B (ω))A m =M AB (ω)A m =F AB =F A +F B (3)

[0036] in:

[0037]

[0038]

[0039] Where: M A is the mass of the active component at the connection interface, M B is the mass of the second moving part at the connection interface, A m is the interface acceleration between the two moving parts, M AB is the mass of the structure at the interface between the two moving parts, F AB is the shrinkage force vector at the interface between the two moving parts, F A is the shrinkage force vector at the interface between the moving parts, F B is the shrinkage force vector at the interface between the moving parts. A and m B are the total modal masses of the two active components, and are the apparent masses of the two moving parts, ω is the natural frequency of the structure, I is the unit matrix, and are the modal participation factors of the two active components, and are diagonal matrices composed of the modal eigenvalues ​​of the two active components under fixed boundaries, and are the modal internal components under the fixed boundaries of the two active parts, and are the connection interface load coefficients of the two moving parts, and are the reaction force vectors of the connection interface on the two moving parts respectively.

[0040] Formula (3) is the interface comprehensive dynamic equation at the interface of two active parts, or the generalized Newton equation. So far, the degrees of freedom of active part one a+m and the degrees of freedom of active part two b+m are reduced to the interface comprehensive equation of m degrees of freedom on the connection interface. Among them, a and b are the low-order main mode retention numbers of the two active parts.

[0041] The external load vector of the satellite substructure is known to be:

[0042]

[0043] According to equations (3), (5) and (6), the shrinkage force vector F of the active part one substructure and the active part two substructure can be obtained: A With F B , and thus the shrinkage force vector F at the connection interface is calculated AB , then the acceleration response at the interface is:

[0044] A m =H AB (ω)F AB (7)

[0045] Where: H AB (ω)=(M AB (ω) -1 is the frequency response function at the interface.

[0046] The displacement response X of active component 1 can be derived A for:

[0047]

[0048] Its moving parts - acceleration response A A =-ω 2 X A for:

[0049]

[0050] Where: A A is the acceleration response of the moving part-substructure; is the static constraint mode of the active component 1; The active component is in the mode under the fixed boundary.

[0051] The internal acceleration response of the moving part is A S A for:

[0052]

[0053] Where: is the acceleration response inside the substructure; is the load proportionality factor; is the participation factor of each mode under the moving part-fixed boundary; is the modal internal component of the active component under the fixed boundary; Λ s is a diagonal matrix composed of the modal eigenvalues ​​of active component one.

[0054] According to the dynamic equation (3), the acceleration response equation (7) at the connection interface is obtained. The acceleration response equation (7) is used to obtain the equation (10), and then the acceleration response A of the active component 1 in equation (9) is calculated by equation (10): A .

[0055] The displacement response of active component 1 is X A =-A A / ω 2 , according to formula (8), the displacement response of active component 1 is obtained.

[0056] By analogy with the solution formula of active component one, the displacement response X of active component two can be obtained. B . So far, the response characteristics of each substructure are obtained.

[0057] The number of movable parts may be more than two, and the corresponding number of substructures is more than two. The displacement response of each substructure when two substructures are connected is considered separately, and all displacement responses generated when a single substructure is connected to other substructures are superimposed to obtain the displacement response of the single substructure.

[0058] The present invention also provides a decoupling analysis device for structural response caused by micro-vibration of multiple disturbance sources, comprising:

[0059] one or more processors;

[0060] a storage device for storing one or more programs,

[0061] When the one or more programs are executed by the one or more processors, the one or more processors implement the structural response decoupling analysis method caused by micro-vibrations of multiple disturbance sources described in the first aspect.

[0062] The present invention also provides a readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the structural response decoupling analysis method caused by micro-vibrations of multiple disturbance sources described in the first aspect.

[0063] The readable storage medium includes, but is not limited to, various media that can store program codes, such as a USB flash drive, a mobile hard disk, a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk.

[0064] The present invention also provides a computer program product, which includes: a computer program (also referred to as code, or instruction), which, when executed, executes the structural response decoupling analysis method caused by micro-vibration of multiple disturbance sources described in the first aspect.

[0065] In the above embodiments, it can be implemented in whole or in part by software, hardware, firmware or any combination thereof. When implemented using software, it can be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer instructions. When the computer instructions are loaded and executed on a computer, the process or function described in the embodiment of the present application is generated in whole or in part. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer instructions can be stored in a computer-readable storage medium, or transmitted from one computer-readable storage medium to another computer-readable storage medium, for example, the computer instructions can be transmitted from a website site, computer, server or data center by wired (e.g., coaxial cable, optical fiber, digital subscriber line (digital subscriber line, DSL)) or wireless (e.g., infrared, microwave, etc.) mode to another website site, computer, server or data center.

[0066] Those of ordinary skill in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application.

[0067] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working processes of the above-described equipment, devices and modules can refer to the corresponding processes in the aforementioned method embodiments and will not be repeated here.

[0068] In order to analyze the dynamic response of local structures caused by the main disturbance sources on the satellite separately, the dynamic substructure method is adopted. The interface comprehensive equation between substructures is used to solve its interface response, and the response of the corresponding substructure is obtained according to the analytical expression of the substructure response. This solves the problem that each structure cannot be analyzed separately due to the micro-vibration of each disturbance source.

[0069] The present invention has been described in detail above in conjunction with specific implementations and exemplary examples, but these descriptions cannot be understood as limiting the present invention. Those skilled in the art understand that, without departing from the spirit and scope of the present invention, a variety of equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its implementation methods, all of which fall within the scope of the present invention. The scope of protection of the present invention shall be subject to the attached claims.

[0070] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A decoupling analysis method for structural response caused by micro-vibration of multiple disturbance sources, characterized in that: include: Obtaining disturbance force data of satellite moving parts, converting the disturbance force data to the local center of mass of each moving part, and obtaining the disturbance force converted to the center of mass of each substructure; Each active part is regarded as a substructure with a connecting interface in between. Combined with the perturbation force converted to the center of mass of each substructure, the comprehensive interface dynamic equation of any two substructures is constructed. According to the comprehensive interface dynamics equation, the acceleration response at the substructure interface is obtained; According to the acceleration response at the interface of the substructure, the acceleration response inside the substructure is obtained; The acceleration response of the substructure is obtained according to the acceleration response at the substructure interface and the acceleration response inside the substructure; According to the acceleration response of the substructure, the displacement response of the substructure is obtained; All displacement responses generated when a single substructure is connected to other substructures are superimposed to obtain the displacement response of the single substructure.

2. The structural response decoupling analysis method caused by micro-vibration of multiple disturbance sources according to claim 1 is characterized in that: The step of considering each active component as a substructure with a connecting interface in between and constructing a comprehensive dynamic equation of the interface comprises: Each active part is regarded as a substructure, and there is a connecting interface between each substructure. The comprehensive dynamic equation for the interface between any two substructures is: (M A (ω)+M B (oh))A m =M AB (ω)A m =F AB =F A +F B Among them: Where: M A is the mass of the active component at the connection interface, M B is the mass of the second moving part at the connection interface, A m is the interface acceleration between the two moving parts, M AB is the mass of the structure at the interface between the two moving parts, F AB is the shrinkage force vector at the interface between the two moving parts, F A is the shrinkage force vector at the interface between the moving parts, F B is the condensation force vector at the interface between the moving parts; m A and m B are the total modal masses of the two active components, and are the apparent masses of the two moving parts, ω is the natural frequency of the structure, I is the unit matrix, and are the modal participation factors of the two active components, and are diagonal matrices composed of the modal eigenvalues ​​of the two active components under fixed boundaries, and are the normalized modal internal components of the two active parts under fixed boundaries, and are the connection interface load coefficients of the two moving parts, and are the reaction force vectors of the connection interface on the two moving parts respectively; and They are the disturbing force vectors after the disturbing forces measured by the force platforms of the two movable parts are converted to the center of mass.

3. The structural response decoupling analysis method caused by micro-vibration of multiple disturbance sources according to claim 2 is characterized in that: The step of obtaining the acceleration response at the substructure interface according to the interface comprehensive dynamic equation includes: determining the condensation force vector F of the active component one substructure and the active component two substructure according to the interface comprehensive dynamic equation. A With F B , according to F A With F B Get the condensation force vector F at the connection interface AB , and then the acceleration response at the interface is obtained as: A m =H AB (ω)F AB Where: H AB (ω)=(M AB (ω) -1 is the frequency response function at the interface.

4. The structural response decoupling analysis method caused by micro-vibration of multiple disturbance sources according to claim 3 is characterized in that: The step of obtaining the acceleration response inside the substructure according to the acceleration response at the interface of the substructure comprises: Where: is the acceleration response inside the active component-substructure; is the load proportionality factor; is the participation factor of each mode under the moving part-fixed boundary; is the modal internal component of the active component under the fixed boundary; Λ s is a diagonal matrix composed of the modal eigenvalues ​​of active component one.

5. The structural response decoupling analysis method caused by micro-vibration of multiple disturbance sources according to claim 4 is characterized in that: The step of obtaining the acceleration response of the substructure according to the acceleration response at the substructure interface and the acceleration response inside the substructure comprises: Where: A A is the acceleration response of the moving part-substructure; is the static constraint mode of the active component 1; The active component is in the mode under the fixed boundary.

6. The structural response decoupling analysis method caused by micro-vibration of multiple disturbance sources according to claim 5 is characterized in that: The step of obtaining the displacement response of the substructure according to the acceleration response of the substructure comprises: A A =-ω 2 X A Where: X A is the displacement response of the active component-substructure.

7. A decoupling analysis device for structural response caused by micro-vibration of multiple disturbance sources, characterized in that: include: one or more processors; a storage device for storing one or more programs, When the one or more programs are executed by the one or more processors, the one or more processors implement the structural response decoupling analysis method caused by micro-vibrations of multiple disturbance sources as claimed in any one of claims 1 to 6.

8. A readable storage medium, characterized in that: A computer program is stored thereon, and when the program is executed by a processor, the method for decoupling analysis of structural response caused by micro-vibration of multiple disturbance sources as claimed in any one of claims 1 to 6 is implemented.

9. A computer program product, characterized in that The computer program product comprises: a computer program, which, when being executed, executes the structural response decoupling analysis method caused by micro-vibrations of multiple disturbance sources as claimed in any one of claims 1 to 6.

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