Vibration test clamp for spacecraft
By designing a spacecraft vibration test fixture including bottom plate, vertical plate and reinforcement rib, the problem of vibration test in the existing technology is solved, and higher test accuracy and reliability are achieved, and the test efficiency is improved.
Patent Information
- Application Number
- CN202421247066.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-03
- Publication Date
- 2025-01-07
- Estimated Expiration
- 2034-06-03
AI Technical Summary
Existing spacecraft vibration test fixtures are difficult to accurately simulate the vibration environment affected by the spacecraft during launch, resulting in the vibration test being not realistic enough, affecting the accuracy and reliability of the test results.
A vibration test fixture for spacecraft including bottom plate, vertical plate and reinforcement rib was designed. Through the combination of vertical plate and bottom plate and the symmetrical setting of reinforcement ribs, the inherent resonance points are eliminated, and the rigidity and strength of the fixture are improved, so that it can be tested. It is stably connected to the electromagnetic vibration system within the frequency range to simulate the actual vibration environment.
It improves the accuracy and reliability of vibration tests, enhances the reduction degree of tests, reduces clamping time, and improves the test efficiency.
Smart Images
Figure CN222318381U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of simulated vibration test detection, and specifically relates to a vibration test fixture for spacecraft. Background Art
[0002] Vibration test simulates the impact of various vibration environments encountered by products in transportation, installation and use environments, and is used to evaluate the resistance of components, parts and complete machines in the expected transportation and use environments. In order to understand the vibration life of the product and the stability of performance indicators, and to find the weak links that may cause damage or failure, the system is tested under vibration conditions simulating the actual environment.
[0003] During the launch process, the spacecraft will inevitably be affected by huge vibrations. Vibrations will affect the functions of precision equipment. If the structural strength of components does not meet the requirements, it will cause the failure of the spacecraft launch. Therefore, conducting simulated vibration tests on spacecraft is of great significance.
[0004] The test is usually carried out in the laboratory by applying vibration excitation to the test piece using a vibration table to simulate the actual vibration environment. The vibration test fixture is a key component that connects the test piece to the vibration table and transmits the vibration load. The vibration test fixture of spacecraft products is related to the success or failure of the vibration test. Therefore, we propose a vibration test fixture for spacecraft. Utility Model Content
[0005] The utility model aims to provide a vibration test fixture for spacecraft to solve the problems raised in the above background technology.
[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a vibration test fixture for spacecraft, comprising a base plate, a first circular hole is opened on the upper surface of the base plate, a vertical plate is fixedly connected at the center of the upper surface of the base plate, a connecting hole is opened on the surface of the vertical plate, reinforcing ribs are fixedly connected to the four corners of the side wall of the vertical plate, the number of the reinforcing ribs is four, the reinforcing ribs on one side are symmetrically arranged, and the other side is the same, and the lower surface of the reinforcing ribs is fixedly connected to the upper surface of the base plate.
[0007] Preferably, it also includes two side panels, which are symmetrically assembled on the side walls of the bottom plate, a second circular hole is opened on the surface of the side panel, a support plate is fixedly connected to the center of the upper surface of the side panel, and the side wall of the support plate is fixedly connected to the side wall of the vertical plate.
[0008] Preferably, the number of the first circular holes is six, and they are vertically symmetrically arranged in sequence.
[0009] Preferably, the number of the connecting holes is five.
[0010] Preferably, the number of the second circular holes is four and they are arranged at four corners.
[0011] Compared with the prior art, the beneficial effects of the utility model are as follows: by using the vertical plate and the bottom plate, the actual vibration environment is simulated, and the rigid fixation requirements of the test fixture are measured and analyzed according to the weight of its components and the simulated vibration level in the work of the spacecraft. Through measurement and structural design, the inherent resonance point of the fixture is eliminated within the test frequency range. At the same time, the reinforcing ribs are symmetrically arranged on both sides of the vertical plate, and the bottom is connected to the bottom plate. The strength of the reinforcing ribs is designed to meet the vibration level requirements, so that the fixed components can be rigidly connected to the electromagnetic vibration system table, thereby improving the accuracy of the test, and can more realistically simulate the working state of the components and systems in actual application, thereby improving the restoration degree of the simulation test, thereby improving the accuracy of the test, and the test fixture designed for test level measurement and analysis of products in the spacecraft optimizes the overall resonance point and strength, thereby improving the reliability of the test. The clamping methods of the products in the spacecraft are all reflected in the fixture, and can be completed by a set of fixtures, thereby reducing the clamping time and improving the test efficiency. BRIEF DESCRIPTION OF THE DRAWINGS
[0012] Figure 1 It is a schematic diagram of the structure of the utility model;
[0013] Figure 2 for Figure 1 Structural details of the middle vertical plate;
[0014] Figure 3 for Figure 1 Structural details of the midsole plate;
[0015] Figure 4 for Figure 1 Structural details of the middle side panels;
[0016] In the figure: 1, bottom plate; 2, first circular hole; 3, vertical plate; 4, connecting hole; 5, reinforcing rib; 6, side plate; 7, support plate; 8, second circular hole. DETAILED DESCRIPTION
[0017] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0018] See also Figure 1-4The utility model provides a vibration test fixture for a spacecraft, comprising a base plate 1, a first circular hole 2 is opened on the upper surface of the base plate 1, a vertical plate 3 is fixedly connected to the center of the upper surface of the base plate 1, a connecting hole 4 is opened on the surface of the vertical plate 3, and reinforcing ribs 5 are fixedly connected to the four corners of the side wall of the vertical plate 3. The number of the reinforcing ribs 5 is four, the reinforcing ribs 5 on one side are symmetrically arranged, and the other side is the same, and the lower surface of the reinforcing ribs 5 is fixedly connected to the upper surface of the base plate 1.
[0019] When the vibration test is carried out on the vibration table, the test piece is first punched and clamped according to the requirements of the technical documents according to the actual use and installation mode and installation status of the spacecraft and its components, and matching bolts are selected according to its weight, size and other factors. The bottom plate 1 is first placed on the surface of the vibration table. First circular holes 2 are opened on both sides of the bottom plate 1. Then matching bolts are passed through the first circular holes 2 to fix the bottom plate 1 on the surface of the vibration table, and the vertical plate 3 is fixed on the surface of the bottom plate 1. The vertical plate 3 and the bottom plate 1 form a complete vibration test fixture. The surface of the vertical plate 3 is opened with connecting holes 4. The connecting holes 4 are the connecting points of the test piece. Through matching bolts The test piece is connected and fixed, and then vibration excitation is applied to the test piece through a vibration table to simulate the actual vibration environment. The rigid fixation requirements of the test fixture are measured and analyzed according to the weight of its components and the simulated vibration level during the operation of the spacecraft. Through measurement and structural design, the inherent resonance point of the fixture is eliminated within the test frequency range. At the same time, the reinforcing ribs 5 are symmetrically arranged on both sides of the vertical plate 3 and connected to the bottom plate 1. The reinforcing ribs 5 are designed to have a strength that meets the vibration level requirements, so that the fixed components can be rigidly connected to the electromagnetic vibration system table, thereby improving the accuracy of the test and completing the overall vibration test.
[0020] It also includes two side panels 6, which are symmetrically assembled on the side walls of the bottom plate 1. A second circular hole 8 is opened on the surface of the side panel 6. A support plate 7 is fixedly connected to the center of the upper surface of the side panel 6. The side walls of the support plate 7 are fixedly connected to the side walls of the vertical plate 3. The side panels 6 are arranged on both sides of the bottom plate 1 and supported by the support plates 7. The support plates 7 and the reinforcing ribs 5 play the same role. At the same time, a second circular hole 8 is also opened on the surface of the side panel 6, which can assist in fixing the bottom plate 1 and make the fixing effect of the bottom plate 1 more firm.
[0021] The number of the first circular holes 2 is six, and they are arranged in sequence in a vertically symmetrical manner.
[0022] The number of the connection holes 4 is five, and the connection holes 4 are arranged at four corners, and a connection hole 4 is also arranged at the intersection of the center point.
[0023] There are four second circular holes 8 , which are arranged at four corners.
[0024] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A vibration test fixture for spacecraft, characterized in that: The invention comprises a bottom plate (1), wherein a first circular hole (2) is provided on the upper surface of the bottom plate (1), a vertical plate (3) is fixedly connected to the center of the upper surface of the bottom plate (1), a connecting hole (4) is provided on the surface of the vertical plate (3), and reinforcing ribs (5) are fixedly connected to the four corners of the side wall of the vertical plate (3), wherein the number of the reinforcing ribs (5) is four, the reinforcing ribs (5) on one side are symmetrically arranged and the other side is the same, and the lower surface of the reinforcing ribs (5) is fixedly connected to the upper surface of the bottom plate (1).
2. A vibration test fixture for spacecraft according to claim 1, characterized in that: It also includes two side panels (6), the two side panels (6) are symmetrically assembled on the side walls of the bottom plate (1), the surface of the side panels (6) is provided with a second circular hole (8), a support plate (7) is fixedly connected to the center of the upper surface of the side panel (6), and the side wall of the support plate (7) is fixedly connected to the side wall of the vertical plate (3).
3. A vibration test fixture for spacecraft according to claim 1, characterized in that: The number of the first circular holes (2) is six, and they are arranged in sequence in a vertically symmetrical manner.
4. A vibration test fixture for spacecraft according to claim 1, characterized in that: The number of the connecting holes (4) is five.
5. The vibration test fixture for spacecraft according to claim 2, characterized in that: The number of the second circular holes (8) is four and they are arranged at four corners.