Method for optimizing acceleration measuring points in satellite vibration test cabin

Abstract

The invention relates to a method for optimizing acceleration measuring points in a satellite vibration test cabin. The method comprises the following steps: S1, classifying the setting positions of the acceleration measuring points in the cabin; the in-cabin acceleration measuring points comprise a first type measuring point and a second type measuring point, and the structural plate where the first type measuring point is located is provided with a structural surface located outside the cabin; the structural plate where the type 2 measuring point is located is provided with two structural surfaces located in the cabin; s2, optimizing the position of the measuring point of the type 1 to the corresponding position of the structural plate outside the cabin; s3, for the type 2 measurement points, calculating the preorder satellite measurement data consistency r of the type 2 measurement points; and S4, if the calculated consistency r of the preorder satellite measurement data of the type 2 measurement point is greater than an optimization threshold value, that is, the consistency of the preorder satellite measurement data of the type 2 measurement point is good, the type 2 measurement point can be optimized, otherwise, the type 2 measurement point cannot be optimized. According to the invention, the number of acceleration measuring points in the satellite vibration test cabin and the dismounting and mounting times of the test cabin structure plate can be effectively reduced, so that the satellite vibration test flow is effectively simplified.

Description

Technical Field

[0001] The invention relates to the technical field of spacecraft vibration testing, and in particular to a method for optimizing acceleration measuring points in a satellite vibration testing cabin. Background Art

[0002] In traditional satellite vibration tests, a large number of vibration sensors are usually arranged in the satellite vibration test cabin. With the rapid deployment of large-scale constellations, the satellite development cycle is getting shorter and shorter, and the time for mechanical test preparation and implementation is becoming more and more urgent. At present, the traditional satellite vibration test has a large number of vibration sensor measurement points, and most of them are arranged in the satellite vibration test cabin. During the test, there is a lot of time for satellite opening and closing plates due to the disassembly and installation of sensors, which seriously affects the preparation and implementation time of mechanical tests.

[0003] Therefore, how to optimize the existing measurement points in the satellite vibration test chamber is an important issue facing the optimization of the satellite development process. Summary of the invention

[0004] In order to solve the technical problems existing in the above-mentioned prior art, the purpose of the present invention is to provide a method for optimizing acceleration measurement points in a satellite vibration test chamber, which can optimize the measurement points in the existing satellite vibration test chamber.

[0005] To achieve the above-mentioned object of the invention, the present invention provides a method for optimizing acceleration measurement points in a satellite vibration test chamber, comprising the following steps:

[0006] Step S1, classifying the setting positions of the acceleration measuring points in the cabin; the acceleration measuring points in the cabin include type one measuring points and type two measuring points, the structural plate where the type one measuring point is located has a structural surface located outside the cabin; the structural plate where the type two measuring point is located has two structural surfaces located inside the cabin;

[0007] Step S2, optimizing the position of the type one measuring point to the corresponding position of the structural plate where the measuring point is located outside the cabin;

[0008] Step S3, for the type 2 measuring point, calculating the consistency r of the preceding star measurement data;

[0009] Step S4: If the calculated consistency r of the predecessor star measurement data of the type 2 measurement point is greater than the optimization threshold, that is, the consistency of the predecessor star measurement data of the type 2 measurement point is good, then the type 2 measurement point can be optimized, otherwise it cannot be optimized.

[0010] According to a technical solution of the present invention, in step S3, the calculation formula for the consistency of the preceding satellite measurement data of the type 2 measurement point is as follows:

[0011]

[0012] Among them, for the measurement data sets x and y of the two leading stars, there exists x={x1,x2,x3,…x N}, y={y1,y2,y3,…y N}, x i ,y i are the response data of the same measurement point of the two preceding stars at frequency i, are the average values ​​of the response data in the measurement data sets x and y, respectively, and N is the number of response data in the measurement data sets x and y.

[0013] According to a technical solution of the present invention, the optimization threshold of the consistency of the preceding satellite measurement data of the type 2 measurement point is set according to engineering experience.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] The present invention proposes a method for optimizing acceleration measurement points in a satellite vibration test cabin, which classifies the acceleration measurement points in the satellite vibration test cabin according to their setting positions, optimizes the measurement points whose structural plates have structural surfaces outside the cabin to outside the cabin, calculates the consistency of measurement data for the measurement points whose structural plates are located inside the cabin, and optimizes them according to the calculation results. The optimization method proposed in the present invention can effectively reduce the number of acceleration measurement points in the satellite vibration test cabin, thereby reducing the number of times the structural plates of the satellite vibration test cabin are disassembled and assembled, thereby effectively simplifying the process of satellite vibration testing and reducing the preparation and implementation time of mechanical testing. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0017] Figure 1 A flowchart schematically showing a method for optimizing acceleration measurement points in a satellite vibration test chamber provided in one embodiment of the present invention;

[0018] Figure 2 A schematic diagram showing the locations of measurement points in an existing satellite vibration test chamber. DETAILED DESCRIPTION

[0019] The description of the embodiments of this specification should be combined with the corresponding drawings, which should be considered as part of the complete specification. In the drawings, the shape or thickness of the embodiments may be enlarged and indicated for simplification or convenience. Furthermore, the parts of each structure in the drawings will be described separately. It is worth noting that the elements not shown in the drawings or not described in words are in a form known to ordinary technicians in the relevant technical field.

[0020] The description of the embodiments herein and any reference to directions and orientations are only for the convenience of description and are not to be construed as any limitation on the scope of protection of the present invention. The following description of the preferred embodiments may involve combinations of features, which may exist independently or in combination, and the present invention is not particularly limited to the preferred embodiments. The scope of the present invention is defined by the claims.

[0021] like Figure 1 As shown, a method for optimizing acceleration measurement points in a satellite vibration test chamber of the present invention comprises the following steps:

[0022] Step S1, classifying the setting positions of the acceleration measuring points in the cabin; the acceleration measuring points in the cabin include type one measuring points and type two measuring points, the structural plate where the type one measuring point is located has a structural surface located outside the cabin; the structural plate where the type two measuring point is located has two structural surfaces located inside the cabin;

[0023] like Figure 2 As shown, measuring point M1 is a type 1 measuring point, which is set on the outer plate of the satellite vibration test cabin, and the outer plate has a structural surface located outside the cabin. Measuring points M2 and M3 are type 2 measuring points, which are set on the inner plate of the satellite vibration test cabin, and the two structural surfaces of the inner plate are both set inside the cabin.

[0024] Step S2, optimizing the position of the type one measuring point to the corresponding position of the structural plate where the measuring point is located outside the cabin;

[0025] For the measuring point M1, it can be optimized to the back of the original installation position, that is, the measuring point M1 can be optimized to the corresponding position on the structural surface outside the cabin on the outer plate where it is located.

[0026] Step S3, for the type 2 measuring point, calculating the consistency r of the preceding star measurement data;

[0027] For measuring points M2 and M3, the consistency of the measurement data of their predecessor stars can be calculated according to the formula.

[0028] The calculation formula for the consistency of the pre-sequence star measurement data of the type II measurement point is as follows:

[0029]

[0030] Among them, for the measurement data x and y of the two leading stars, x={x1,x2,x3,…x N}, y={y1,y2,y3,…y N ), x i ,y i They are the response data of each frequency point of the same measurement point of the two leading stars, are the average values ​​of variables x and y respectively, and N is the number of variables x and y.

[0031] Step S4: If the calculated consistency r of the predecessor star measurement data of the type 2 measurement point is greater than the optimization threshold, that is, the consistency of the predecessor star measurement data of the type 2 measurement point is good, then the type 2 measurement point can be optimized, otherwise it cannot be optimized.

[0032] The optimization threshold of the consistency of the preceding satellite measurement data of the type II measurement point is set according to engineering experience. In this embodiment, the optimization threshold r0 is set to 0.5.

[0033] After calculation, the consistency of the measurement data of the pre-sequence stars of the measuring point M2 is r=0.75>r0, and the consistency of the measurement data of the pre-sequence stars is good. The measuring point can be optimized, that is, the measuring point can be deleted; the consistency of the measurement data of the pre-sequence stars of the measuring point M3 is r=0.36>r0, and the consistency of the measurement data of the pre-sequence stars is not good. The measuring point cannot be optimized, that is, the measuring point cannot be deleted.

[0034] It should be noted that the above is a preferred embodiment of the present invention. It should be pointed out that although the preferred embodiment of the present invention has been described, once the basic creative concept of the present invention is known, a number of improvements and modifications can be made by a person skilled in the art without departing from the principles of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention. Therefore, the attached claims are intended to be interpreted as including the preferred embodiment and all changes and modifications that fall within the scope of the embodiments of the present invention.

Claims

1. A method for optimizing acceleration measurement points in a satellite vibration test chamber, characterized in that: The following steps are involved: Step S1, classifying the setting positions of the acceleration measuring points in the cabin; the acceleration measuring points in the cabin include type one measuring points and type two measuring points, the structural plate where the type one measuring point is located has a structural surface located outside the cabin; the structural plate where the type two measuring point is located has two structural surfaces located inside the cabin; Step S2, optimizing the position of the type one measuring point to the corresponding position of the structural plate where the measuring point is located outside the cabin; Step S3, for the type 2 measuring point, calculating the consistency r of the preceding star measurement data; Step S4: If the calculated consistency r of the predecessor star measurement data of the type 2 measurement point is greater than the optimization threshold, that is, the consistency of the predecessor star measurement data of the type 2 measurement point is good, then the type 2 measurement point can be optimized, otherwise it cannot be optimized.

2. The method for optimizing acceleration measurement points in a satellite vibration test chamber according to claim 1, characterized in that: In step S3, the calculation formula for the consistency of the preceding star measurement data of the type 2 measurement point is as follows: Among them, for the measurement data sets x and y of the two leading stars, there exists x={x1,x2,x3,…x N }, y={y1,y2,y3,…y N }, x i ,y i are the response data of the same measurement point of the two preceding stars at frequency i, are the average values ​​of the response data in the measurement data sets x and y, respectively, and N is the number of response data in the measurement data sets x and y.

3. The method for optimizing acceleration measurement points in a satellite vibration test chamber according to claim 2, characterized in that: The optimization threshold of the consistency of the preceding satellite measurement data of the type II measurement point is set according to engineering experience.

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