Satellite testing device

Abstract

The embodiment of the utility model provides a satellite test device, which comprises a multi-core plug male head, a multi-core plug female head, a test board and a sensor assembly, and is characterized in that the multi-core plug male head is electrically connected with a BNC wire male head, the BNC wire male head is electrically connected with a control acquisition instrument, the control acquisition instrument is electrically connected with the test board, the test board is used for placing a satellite to be tested, the multi-core plug female head is electrically connected with a BNC wire female head, and the sensor assembly is electrically connected with the BNC wire male head. The BNC wire female head is electrically connected with the sensor assembly, and the sensor assembly is arranged on a satellite to be tested or a test board. The multi-core plug male head and the multi-core plug female head are arranged, the multi-core plug male head is electrically connected with the control acquisition instrument through the BNC wire male head, the multi-core plug female head is electrically connected with the sensor assembly through the BNC wire female head, and the sensor assembly can be electrically connected to the control acquisition instrument through the multi-core plug male head and the multi-core plug female head. The multi-core plug male head and the multi-core plug female head are separated, so that disconnection of the sensor assembly and the control acquisition instrument can be realized.

Description

Technical Field

[0001] This specification relates to the field of spacecraft testing technology, and specifically to a satellite testing device. Background Art

[0002] Pre-launch mechanical environment assessments for satellites, including sinusoidal, random, and noise tests, often require multiple satellite transports and frequent plugging and unplugging of sensors and controllers. When there are numerous sensor channels, plugging and unplugging is time-consuming and error-prone, impacting test efficiency. Summary of the Invention

[0003] In view of this, an embodiment of the present specification provides a satellite testing device, which provides a multi-core plug male head and a multi-core plug female head. The multi-core plug male head is electrically connected to the control acquisition instrument through the BNC line male head, and the multi-core plug female head is electrically connected to the sensor assembly through the BNC line female head. By matching the multi-core plug male head and the multi-core plug female head, the sensor assembly can be electrically connected to the control acquisition instrument, thereby realizing the collection of various parameters during satellite testing. After the test is completed, the multi-core plug male head and the multi-core plug female head are separated to achieve the disconnection of the sensor assembly and the control acquisition instrument.

[0004] The embodiments of this specification provide the following technical solutions: a satellite testing device, comprising a multi-core male plug, a multi-core female plug, a test bench, and a sensor assembly, wherein the multi-core male plug and the multi-core female plug cooperate with each other, the multi-core male plug is electrically connected to a BNC cable male head, the BNC cable male head is electrically connected to a control acquisition instrument, the control acquisition instrument is electrically connected to the test bench, the test bench is used to place a satellite to be tested, the multi-core female plug is electrically connected to a BNC cable female head, the BNC cable female head is electrically connected to the sensor assembly, and the sensor assembly is disposed on the satellite to be tested and / or the test bench;

[0005] Wherein, when the satellite to be measured is transferred, the sensor component and the control acquisition instrument are disconnected by separating the multi-core plug male head and the multi-core plug female head.

[0006] Preferably, the multi-core male plug is a 65-core aviation male plug;

[0007] And / or, the multi-core female plug is a 65-core aviation female plug.

[0008] Preferably, the sensor assembly includes a vibration sensor, and the vibration sensor monitors the vibration frequency of the satellite to be measured.

[0009] Preferably, the vibration sensor is mounted on the satellite to be tested or the test bench by pasting.

[0010] Preferably, the sensor assembly further includes an acceleration sensor, which monitors the acceleration of the satellite to be measured.

[0011] Preferably, the acceleration sensor is mounted on the satellite to be tested or the test bench by pasting.

[0012] Preferably, the test bench comprises a vibration table.

[0013] Preferably, the control collector includes a vibration collector and an acceleration collector.

[0014] Compared with the prior art, the at least one technical solution adopted in the embodiments of this specification can achieve the following beneficial effects:

[0015] By setting a multi-core plug male head and a multi-core plug female head, the multi-core plug male head is electrically connected to the control acquisition instrument through the BNC line male head, and the multi-core plug female head is electrically connected to the sensor assembly through the BNC line female head. By matching the multi-core plug male head and the multi-core plug female head, the sensor assembly can be electrically connected to the control acquisition instrument, thereby realizing the collection of various parameters during satellite testing. After the test is completed, the multi-core plug male head and the multi-core plug female head are separated to realize the disconnection of the sensor assembly and the control acquisition instrument, and prepare for the next stage of testing or transportation, which greatly simplifies the operation process. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0017] Figure 1 It is a structural schematic diagram of the satellite testing device provided in this application.

[0018] In the figure, 1. Multi-core plug male connector; 2. Multi-core plug female connector; 3. BNC cable male connector; 4. BNC cable female connector; 5. Control acquisition instrument; 6. Sensor assembly; 7. Satellite to be tested; 8. Test bench. DETAILED DESCRIPTION

[0019] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0020] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the features in the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this application.

[0021] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on this application, it should be understood by those skilled in the art that an aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number and aspect described herein can be used to implement an apparatus and / or practice a method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this apparatus and / or practice this method.

[0022] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present application. The illustrations only show components related to the present application and are not drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component can be changed at will, and the component layout type may also be more complicated.

[0023] Additionally, in the following description, specific details are provided to provide a thorough understanding of the examples. However, one skilled in the art will appreciate that the aspects described can be practiced without these specific details.

[0024] Pre-launch mechanical environment assessments for satellites, including sinusoidal, random, and noise tests, often require multiple satellite transports and frequent plugging and unplugging of sensors and controllers. When there are numerous sensor channels, plugging and unplugging is time-consuming and error-prone, impacting test efficiency.

[0025] The following describes the technical solutions provided by various embodiments of the present application in conjunction with the accompanying drawings.

[0026] like Figure 1As shown, a satellite testing device includes a multi-core plug male connector 1, a multi-core plug female connector 2, a test bench 8 and a sensor assembly 6, wherein the multi-core plug male connector 1 and the multi-core plug female connector 2 cooperate with each other, the multi-core plug male connector 1 is electrically connected to a BNC cable male connector 3, the BNC cable male connector 3 is electrically connected to a control acquisition instrument 5, the control acquisition instrument 5 is electrically connected to the test bench 8, the test bench 8 is used to place a satellite 7 to be tested, the multi-core plug female connector 2 is electrically connected to a BNC cable female connector 4, the BNC cable female connector 4 is electrically connected to the sensor assembly 6, and the sensor assembly 6 is arranged on the satellite 7 to be tested and / or the test bench 8;

[0027] When the satellite to be measured 7 is transferred, the sensor assembly 6 and the control acquisition instrument 5 are disconnected by separating the multi-core plug male head 1 and the multi-core plug female head 2.

[0028] By setting a multi-core plug male head 1 and a multi-core plug female head 2, and the multi-core plug male head 1 and the multi-core plug female head 2 can be plugged in and matched with each other, the multi-core plug male head 1 is electrically connected to the control acquisition instrument 5 through the BNC line male head 3, and the multi-core plug female head 2 is electrically connected to the sensor assembly 6 through the BNC line female head 4. By plugging in and matching the multi-core plug male head 1 and the multi-core plug female head 2, when the multi-core plug male head 1 and the multi-core plug female head 2 are plugged in, a connecting path is formed between the multi-core plug male head 1 and the multi-core plug female head 2, and the sensor assembly 6 can be electrically connected to the control acquisition instrument 5, thereby realizing the collection of various parameters during satellite testing. After the test is completed, the multi-core plug male head 1 and the multi-core plug female head 2 are separated, and the sensor assembly 6 and the control acquisition instrument 5 can be disconnected, preparing for the next stage of testing or transportation, which greatly simplifies the operation process.

[0029] It should be noted that when the sensor component 6 is set on the satellite to be tested 7, the monitoring purpose can be achieved by directly monitoring the status of the satellite. When the sensor component 6 is set on the test bench 8, the test bench 8 drives the satellite to be tested 7 and the sensor component 6 to move synchronously, thereby realizing the monitoring of the satellite by the sensor component 6.

[0030] In some embodiments, the multi-core plug male head 1 is a 65-core aviation plug male head, and the multi-core plug female head 2 is a 65-core aviation plug female head. By adopting a 65-core aviation plug male head and a 65-core aviation plug female head, it is a connector with more contact points, which can provide up to 65 independent electrical connection channels. At the same time, it can adapt to the interface standards of different devices, ensure good compatibility of the equipment, and ensure that multiple sensors can be connected. It is durable and reliable and can work stably for a long time in harsh aviation environments.

[0031] In some embodiments, the sensor assembly 6 includes a vibration sensor, which monitors the vibration frequency of the satellite to be measured 7. By setting up the vibration sensor, the vibration sensor can monitor the vibration frequency of the satellite to be measured 7 and control the collector 5 to collect, analyze and display the monitoring results.

[0032] In some embodiments, the vibration sensor is installed on the satellite to be tested 7 or the test platform 8 by pasting. The vibration sensor can be installed by pasting, and the installation operation is relatively convenient.

[0033] It should be noted that, in this embodiment, the vibration sensor is attached to the satellite 7 to be tested. In other embodiments, the vibration sensor can also be attached to the test bench 8. It is only necessary to ensure that the vibration sensor and the satellite 7 to be tested move synchronously.

[0034] In some embodiments, the sensor assembly 6 also includes an acceleration sensor, which monitors the acceleration of the satellite to be measured 7. By setting the acceleration sensor, the acceleration sensor can monitor the acceleration of the satellite to be measured 7 and control the collector 5 to collect, analyze and display the monitoring results.

[0035] In some embodiments, the acceleration sensor is installed on the satellite to be tested 7 or the test platform 8 by pasting. The acceleration sensor can be installed by pasting, and the installation operation is relatively convenient.

[0036] It should be noted that, in this embodiment, the acceleration sensor is attached to the satellite 7 to be tested. In other embodiments, the acceleration sensor may also be attached to the test bench 8 , and it is only necessary to ensure that the acceleration sensor and the satellite 7 to be tested move synchronously.

[0037] In some embodiments, the test bench 8 includes a vibration table. By setting up the vibration table, the vibration table drives the satellite to be tested 7 to vibrate, thereby realizing a vibration test of the satellite.

[0038] In some embodiments, the control acquisition instrument 5 includes a vibration acquisition instrument and an acceleration acquisition instrument. The vibration acquisition instrument collects and displays the satellite vibration parameters monitored by the vibration sensor, and the acceleration acquisition instrument collects and displays the satellite acceleration parameters monitored by the acceleration sensor, thereby realizing the test operation of multiple parameters of the satellite.

[0039] The specific working process of the satellite test device is described below:

[0040] Before conducting the test, the satellite to be tested 7 is installed on the test bench 8. The vibration sensor can be installed on the satellite to be tested 7 by pasting, and the acceleration sensor can also be installed on the satellite to be tested 7 by pasting to complete the installation operation of the sensor assembly 6. When conducting the test, the 65-core aviation plug male head and the 65-core aviation plug female head are plugged in to realize the electrical connection between the sensor assembly 6 and the control acquisition instrument 5. The vibration sensor can monitor the vibration frequency of the satellite to be tested 7, and the control acquisition instrument 5 collects, analyzes and displays the monitoring results. The acceleration sensor can monitor the acceleration of the satellite to be tested 7, and the control acquisition instrument 5 collects, analyzes and displays the monitoring results. After the test is completed, the multi-core plug male head 1 and the multi-core plug female head 2 are separated to realize the disconnection of the sensor assembly 6 and the control acquisition instrument 5, and prepare for the next stage of testing or transportation.

[0041] The same or similar parts between the various embodiments in this specification can be referred to in conjunction with each other, and each embodiment focuses on the differences from other embodiments. In particular, for the method embodiments described later, since they correspond to the system, the description is relatively simple, and the relevant parts can be referred to the partial description of the system embodiment.

[0042] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A satellite testing device, characterized in that: The device comprises a multi-core plug male head, a multi-core plug female head, a test bench and a sensor assembly, wherein the multi-core plug male head and the multi-core plug female head cooperate with each other, the multi-core plug male head is electrically connected to the BNC line male head, the BNC line male head is electrically connected to the control acquisition instrument, the control acquisition instrument is electrically connected to the test bench, the test bench is used to place the satellite to be tested, the multi-core plug female head is electrically connected to the BNC line female head, the BNC line female head is electrically connected to the sensor assembly, and the sensor assembly is arranged on the satellite to be tested and / or the test bench; Wherein, when the satellite to be measured is transferred, the sensor component and the control acquisition instrument are disconnected by separating the multi-core plug male head and the multi-core plug female head.

2. The satellite testing device according to claim 1, characterized in that: The multi-core male plug is a 65-core aviation male plug; And / or, the multi-core female plug is a 65-core aviation female plug.

3. The satellite testing device according to claim 1, characterized in that: The sensor assembly includes a vibration sensor, which monitors the vibration frequency of the satellite to be measured.

4. The satellite testing device according to claim 3, characterized in that: The vibration sensor is mounted on the satellite to be tested or the test platform in a pasting manner.

5. The satellite testing device according to claim 4, characterized in that: The sensor assembly further includes an acceleration sensor, which monitors the acceleration of the satellite to be measured.

6. The satellite testing device according to claim 5, characterized in that: The acceleration sensor is mounted on the satellite to be tested or the test platform in a pasting manner.

7. The satellite testing device according to any one of claims 1 to 6, characterized in that: The test bench includes a vibration table.

8. The satellite testing device according to claim 7, characterized in that: The control acquisition instrument includes a vibration acquisition instrument and an acceleration acquisition instrument.

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