Satellite payload antenna hinge coaxial degree adjustment test system and test method thereof

Abstract

The application discloses a satellite load antenna hinge coaxiality adjustment and testing system and a testing method thereof. The system is characterized in that it comprises: a light source system fixed on the upper pin shaft of the antenna hinge in a manner that can realize 360° reciprocating rotation on the upper pin shaft; an imaging system fixed on the lower pin shaft of the antenna hinge in a manner that can realize more than 180° reciprocating rotation on the lower pin shaft; and a display and control system used for man-machine interaction, displaying the dynamic condition of a cross image on the camera target surface of the imaging system, and finding the cross center through an image processing algorithm, fitting a circle curve, displaying the measurement of the antenna hinge coaxiality, and having a measurement data recording and query function. The application solves the problems of indirect measurement and inaccurate measurement results, and can be used for satellite load antenna assembly production, has high precision, realizes direct measurement, data traceability and high adjustment and assembly efficiency.

Description

Technical Field

[0001] This invention relates to satellite ground testing technology, and more particularly to a satellite payload antenna hinge coaxiality assembly and adjustment testing system. Background Technology

[0002] Satellite payload antennas are a crucial type of payload in the satellite field. The deployment mechanism of a satellite payload antenna must perform release, deployment, and locking functions in orbit, supporting the normal operation of the satellite payload antenna. The coaxiality of the antenna hinges directly affects the reliability of the deployment and locking of the satellite payload antenna deployment mechanism, and also directly impacts the normal operation of the payload antenna in orbit. Currently, during antenna hinge installation in China, the coaxiality of the upper and lower hinge rotation axes is measured indirectly using mechanical dimension calculations. This method cannot directly and accurately reflect the coaxiality error of the antenna hinges. Because this method includes factors such as satellite attitude errors and the form and position errors of the hinge rotation axis itself, the accuracy of coaxiality measurement is poor, directly affecting the reliability of hinge deployment and locking, and significantly impacting the development of satellite models.

[0003] Currently, the coaxiality of antenna hinges in China is measured by measuring the deviation between the mounting surface of a single hinge and the fitted surface of the upper and lower hinge mounting surfaces. This measurement method has the following main problems:

[0004] First, the measurement results are inaccurate. The measurement process of this method includes factors such as the attitude error of the celestial body and the shape and position error of the hinge rotation axis itself, resulting in poor accuracy of coaxiality measurement;

[0005] Secondly, the measurement is indirect. The method only measures the machining error of the mounting surface and does not measure the actual rotation axis of the upper and lower hinges. Moreover, it is impossible to re-measure after the antenna is assembled. Summary of the Invention

[0006] The purpose of this invention is to solve the problems of inaccurate measurement results and indirect measurement in the prior art.

[0007] To achieve the above-mentioned objectives, this invention provides a satellite payload antenna hinge coaxiality assembly and testing system, characterized in that it comprises:

[0008] The light source system is fixed on the upper pin of the antenna hinge in a manner that allows for 360° reciprocating rotation on the upper pin, and is used to provide a light source for a fixed-angle cross-shaped light spot so that the imaging system can take pictures and form images.

[0009] The imaging system is fixed to the lower pin of the antenna hinge in a manner that allows for reciprocating rotational motion of more than 180° on the lower pin. It is used to take pictures to form a cross image and provide data to the display and control system for processing.

[0010] The control system is used for human-computer interaction, displays the dynamic condition of the cross image on the camera target surface of the imaging system, and finds the cross center through the image processing algorithm, fits a circle curve, displays the coaxiality of the antenna hinge, and has the functions of measuring data recording and inquiring.

[0011] Further, the light source system comprises sequentially arranged pin shaft, pin shaft mounting seat, light source pressing plate, condenser pressing plate, cross dividing plate pressing plate, lens barrel, adhesive lens pressing plate and the like components, and light source, condenser, frosted glass, cross dividing plate, adhesive lens inserted in these components in sequence,

[0012] The pin shaft is used for connecting with the rotating shaft of the load antenna hinge, the pin shaft mounting seat is used for arranging the pin shaft, the light source pressing plate is used for fixing the light source on the bottom side of the pin shaft mounting seat, the condenser pressing plate is used for fixing the condenser on the bottom side of the light source pressing plate and fixing the frosted glass on the top side of the cross dividing plate pressing plate, the cross dividing plate pressing plate is used for fixing the cross dividing plate on the top side of the lens barrel, and the adhesive lens pressing plate is used for fixing the adhesive lens on the bottom of the lens barrel.

[0013] Further, the imaging system comprises filter support, filter, prism support, pin shaft, right-angle prism, camera support and camera, the filter support is arranged on the prism support and used for fixing the filter, the prism support is arranged on the right-angle prism and used for fixing the right-angle prism, the pin shaft is used for connecting with the rotating shaft of the load antenna hinge, and the camera support is arranged on the side edge of the prism support and used for fixing the camera.

[0014] Further, the control system comprises notebook computer and antenna hinge coaxiality measuring software loaded on the notebook computer, the software operation interface of the antenna hinge coaxiality measuring software comprises coaxiality measuring interface, historical data interface and system setting interface.

[0015] Further, the coaxiality measuring interface mainly comprises four areas, namely measurement process state area, image processing and data display area, measurement result recording area and current state operation prompt area, coaxiality adjustment test is carried out according to the measurement process state prompt, the system collects data, carries out image processing calculation, and finally calculates and displays the coaxiality measurement result.

[0016] Further, the historical data interface is used for viewing the past measurement data, and the measurement result can be exported as Excel file.

[0017] Further, the system setting interface is used for setting the parameters of the software system itself, and the setting contents comprise calculation unit and calculation parameter.

[0018] Further, the light source system adopts an external power supply mode, is powered through an adapter to access 220V mains, and the imaging system is connected to the display control system through a USB3.1 cable, while image transmission and imaging system power supply are simultaneously performed.

[0019] The application also provides a test method of the satellite payload antenna hinge coaxiality adjustment and test system.

[0020] When the measurement process state area of the coaxiality measurement interface is "collecting the first group of data", the imaging system is located at the 0° position, the light source system is rotated to the 0° position, and after the crosshair position of the image processing and calculation area and the coaxiality test data are stable, the "record" button of the measurement result recording area is clicked to record the measurement result, then the light source system is rotated to the 11° position to the 300° position in sequence, and the measurement result is recorded;

[0021] Next, when the measurement process state area is "collecting the second group of data", the imaging system is rotated to the 45° position, and the light source system is rotated to the 0° position to the 300° position in sequence, and the measurement result is recorded;

[0022] Next, the third group of data, the fourth group of data and the fifth group of data are collected in sequence, and the measurement result is recorded.

[0023] Further, after the five groups of data in the measurement process state area are all collected, the coaxiality measurement result display interface is entered, and the current coaxiality measurement result is displayed in the measurement result recording area.

[0024] Compared with the prior art, the application has the following beneficial effects:

[0025] Highlight 1: The satellite payload antenna hinge coaxiality adjustment and test system of the application directly measures the antenna hinge coaxiality through the light source system and the imaging system of the coaxiality adjustment and test system, changes the past indirect measurement mode of the antenna hinge coaxiality, and improves the test accuracy;

[0026] Highlight 2: The satellite payload antenna hinge coaxiality adjustment and test system of the application realizes that the test data can be displayed in real time and stored through the display control system of the coaxiality adjustment and test system, and the traceability of the data provides favorable support for the assembly process;

[0027] Highlight 3: The satellite payload antenna hinge coaxiality adjustment and test system of the application has certain generalizability, can solve the measurement problem of the coaxiality of the payload antenna deployment mechanism, and has certain economic benefit potential. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1It is the whole structure schematic diagram of satellite payload antenna hinge coaxial degree installation and adjustment test system in the preferred embodiment of the present application.

[0029] Figure 2 It is the structure schematic diagram of light source system in the preferred embodiment of the present application.

[0030] Figure 3 It is the structure schematic diagram of imaging system in the preferred embodiment of the present application.

[0031] Figure 4 It is the software operation interface schematic diagram of imaging system in the preferred embodiment of the present application.

[0032] Figure 5 It is the software coaxial degree measurement result schematic diagram of imaging system in the preferred embodiment of the present application. DETAILED DESCRIPTION

[0033] The following will be combined with Figures 1-4 The satellite payload antenna hinge coaxial degree installation and adjustment test system of the present application is further described in detail.

[0034] The present application discloses a kind of installation and adjustment test system for satellite payload antenna hinge coaxial degree, it is applicable to satellite payload antenna deployment mechanism installation test process, especially design is used for whether the assembly test field of antenna hinge coaxial degree meets design requirement in the process of satellite payload antenna deployment mechanism assembly.

[0035] Figure 1 It is the whole structure schematic diagram of satellite payload antenna hinge coaxial degree installation and adjustment test system in the preferred embodiment of the present application.

[0036] As Figure 1 Satellite 21 payload antenna hinge one 22 and payload antenna hinge two 23 are installed on satellite 21, in the process of satellite payload antenna deployment mechanism assembly, the satellite payload antenna hinge coaxial degree installation and adjustment test system of the embodiment is connected with payload antenna hinge one 22 and payload antenna hinge two 23.

[0037] As Figure 1 The satellite payload antenna hinge coaxial degree installation and adjustment test system of the embodiment includes light source system 11, imaging system 12 and display control system 13.Light source system 11 is used to provide fixed angle cross light spot light source, to facilitate imaging system to take photograph, imaging system 12 is used to take photo to form cross image, and provide for display control system to process data.

[0038] The light source system 11 is fixed on the upper pin shaft of the load antenna hinge one 22 and can realize 360° reciprocating rotation on the upper pin shaft of the load antenna hinge one 22; the imaging system 12 is fixed on the lower pin shaft of the load antenna hinge two 23 and can realize more than 180° reciprocating rotation on the lower pin shaft of the load antenna hinge two 23. The display and control system 13 is used for human-computer interaction, displays the dynamic situation of the cross image on the camera target surface of the imaging system, and finds the cross center through the image processing algorithm, fits a circle curve, displays the coaxiality of the measurement antenna hinge, and has the functions of measurement data recording and query. The light source system 11 adopts an external power supply mode and is powered through the adapter 14 connected to 220V mains.

[0039] Figure 2 Fig. 2 is a structural schematic diagram of the light source system in the preferred embodiment of the present application.

[0040] As shown in Fig. 2, the light source system 11 of the present application includes sequentially arranged components such as a pin shaft 111, a pin shaft mounting seat 112, a light source pressing plate 113, a condenser lens pressing plate 114, a cross division plate pressing plate 115, a lens barrel 116, a cemented lens pressing plate 117, and parts such as a light source 1111, a condenser lens 1112, a ground glass 1113, a cross division plate 1114, and a cemented lens 1115 inserted in these components in sequence. Figure 2

[0041] The pin shaft 111 is used for connecting with the rotating shaft of the load antenna hinge 22, the pin shaft mounting seat 112 is used for arranging the pin shaft 111, the light source pressing plate 113 is used for fixing the light source 1111 to the bottom side of the pin shaft mounting seat 112, the condenser lens pressing plate 114 is used for fixing the condenser lens 1112 to the bottom side of the light source pressing plate 113 and fixing the ground glass 1113 to the top side of the cross division plate pressing plate 115, the cross division plate pressing plate 115 is used for fixing the cross division plate 1114 to the top side of the lens barrel 116, and the cemented lens pressing plate 117 fixes the cemented lens 1115 to the bottom of the lens barrel 116.

[0042] Figure 3 Fig. 3 is a structural schematic diagram of the imaging system in the preferred embodiment of the present application.

[0043] As shown in Fig. 3, the imaging system 12 of the present application includes sequentially arranged components such as a load antenna hinge two 23, a load antenna hinge one 22, a pin shaft 121, a pin shaft mounting seat 122, a lens barrel 126, a cemented lens pressing plate 127, a cross division plate pressing plate 125, a condenser lens pressing plate 124, a light source pressing plate 123, a pin shaft mounting seat 122, a pin shaft 121, a load antenna hinge one 22, and a load antenna hinge two 23, and parts such as a light source 1211, a condenser lens 1212, a ground glass 1213, a cross division plate 1214, and a cemented lens 1215 inserted in these components in sequence. Figure 3 ​As shown, the imaging system 12 includes a filter support 121, a filter 122, a prism support 123, a pin shaft 124, a right-angle prism 125, a camera support 126, a camera 127, and the like. The filter support 121 is arranged on the prism support 123 for fixing the filter 122, the prism support 123 is arranged on the right-angle prism 125 for fixing the right-angle prism 125, the pin shaft 124 is used for connecting with the rotation shaft of the load antenna hinge 23, and the camera support 126 is arranged on the side of the prism support 123 for fixing the camera 127.

[0044] Figure 4 As shown in the middle, it is a schematic diagram of the software operation interface of the imaging system in the preferred embodiment of the application.

[0045] The display control system 13 of the application includes a notebook computer and antenna hinge coaxiality measurement software loaded on the notebook computer. The notebook computer can adopt a THINKPAD portable computer, a T450 series, an i5 CPU, a solid state disk, and is equipped with an external optical drive for facilitating data import and export. The computer is convenient to carry, has a fast running speed of the solid state disk, and is good in shock resistance.

[0046] As shown in the middle, it is a schematic diagram of the software operation interface of the imaging system in the preferred embodiment of the application. Figure 4 As shown, the software operation interface of the antenna hinge coaxiality measurement software of the application includes functional interfaces of a coaxiality measurement interface 1321, a historical data interface 1322, and a system setting interface 1323. The coaxiality measurement interface 1321 mainly consists of four areas, namely, a measurement process state area 1324, an image processing and data display area 1325, a measurement result recording area 1326, and a current state operation prompt area 1327. According to the coaxiality adjustment test of the measurement process state prompt, the system collects data, performs image processing and calculation, and finally calculates and displays the coaxiality measurement result.

[0047] The historical data interface 1322 is used for viewing the past measurement data, and the measurement result can be exported as an Excel file. The system setting interface 1323 is used for setting the parameters of the software system itself, such as the configuration of the calculation unit, the calculation parameter, and the like.

[0048] The specific software operation process is illustrated as follows: Figure 1 and Figure 4 For example:

[0049] When the measurement process state area 1324 of the coaxiality measurement interface 1321 is "collecting the first group of data", the imaging system 12 is located at the 0° position, the light source system 11 is rotated to the 0° position, and after the crosshair position and the coaxiality test data of the image processing and calculation area 1325 are stable, the "record" button of the measurement result recording area 1326 is clicked to record the measurement result. Then, the light source system 11 is rotated to the 60° position ~ 300° position in sequence, and the measurement result is recorded.

[0050] Next, when the measurement process state area 1324 is "collecting the second group of data", the imaging system 12 is rotated to the 45° position, and the light source system 11 is rotated to the 0° position ~ 300° position in sequence, and the measurement result is recorded.

[0051] Next, the third group of data, the fourth group of data, and the fifth group of data are collected in sequence, and the measurement result is recorded.

[0052] Figure 5 The software coaxiality measurement schematic diagram of the imaging system in the preferred embodiment of the application is shown in the figure.

[0053] As Figure 5 shown, after the five groups of data of the measurement process state area 1324 of the coaxiality measurement interface 1321 are all collected, the software enters the coaxiality measurement result display interface, and the measurement result recording area 1326 displays the current coaxiality measurement result.

[0054] The application solves the problems of indirect measurement and inaccurate measurement result of the existing satellite payload antenna deployment mechanism antenna hinge coaxiality measurement process method, and can be used for satellite payload antenna assembly production, has the beneficial effects of high precision, direct measurement, traceable data, high assembly and adjustment efficiency, etc.

[0055] It should be noted that the above is only a schematic description and elaboration of the application, and those skilled in the art should understand that any modification and replacement of the application belongs to the protection scope of the application.

Claims

1. A satellite payload antenna hinge coaxiality alignment test system, characterized in that, It comprises: a light source system fixed on the upper pin shaft of the antenna hinge in a way that it can realize 360° reciprocating rotation on the upper pin shaft, for providing a fixed angle cross light spot for the imaging system to take pictures; an imaging system fixed on the lower pin shaft of the antenna hinge in a way that it can realize more than 180° reciprocating rotation on the lower pin shaft, for taking pictures to form a cross image, which is provided to the display and control system for data processing; a display and control system for human-computer interaction, displaying the dynamic situation of the cross image on the camera target surface of the imaging system, and finding the cross center through image processing algorithm, fitting a circle curve, displaying the coaxiality of the antenna hinge, and having the functions of measuring data recording and querying, The test method comprises the following steps: When the measurement process state area of the coaxiality measurement interface is "collecting the first group of data", the imaging system is located at 0° position, the light source system is rotated to 0° position, the cross cursor position and coaxiality test data in the image processing and calculation area are stable, and then the measurement result is recorded by clicking the "record" button in the measurement result recording area, and then the light source system is rotated to 11-60° position-300° position in sequence and the measurement result is recorded; Next, when the measurement process state area is "collecting the second group of data", the imaging system is rotated to 45° position, and then the light source system is rotated to 11-60° position-300° position in sequence and the measurement result is recorded; Next, the third group of data, the fourth group of data and the fifth group of data are collected in sequence and the measurement result is recorded.

2. The satellite payload antenna hinge coaxality alignment test system of claim 1, wherein, The light source system comprises sequentially arranged pin shaft, pin shaft mounting seat, light source pressing plate, condenser lens pressing plate, cross division plate pressing plate, lens barrel, adhesive lens pressing plate and the like, and light source, condenser lens, frosted glass, cross division plate and adhesive lens inserted in these components in sequence. The pin shaft is used for connecting with the rotating shaft of the load antenna hinge, the pin shaft mounting seat is used for arranging the pin shaft, the light source pressing plate is used for fixing the light source on the bottom side of the pin shaft mounting seat, the condenser lens pressing plate is used for fixing the condenser lens on the bottom side of the light source pressing plate, and the frosted glass is fixed on the top side of the cross division plate pressing plate, the cross division plate pressing plate is used for fixing the cross division plate on the top side of the lens barrel, and the adhesive lens pressing plate is used for fixing the adhesive lens on the bottom of the lens barrel.

3. The satellite payload antenna hinge coaxality alignment test system of claim 1, wherein, The imaging system comprises filter support, filter, prism support, pin shaft, right-angle prism, camera support and camera, the filter support is arranged on the prism support and used for fixing the filter, the prism support is arranged on the right-angle prism and used for fixing the right-angle prism, the pin shaft is used for connecting with the second rotating shaft of the load antenna hinge, and the camera support is arranged on the side of the prism support and used for fixing the camera.

4. The satellite payload antenna hinge coaxality alignment test system of claim 1, wherein, The display and control system comprises a notebook computer and antenna hinge coaxiality measurement software loaded on the notebook computer, and the software operation interface of the antenna hinge coaxiality measurement software comprises the functional interfaces of the coaxiality measurement interface, the historical data interface and the system setting interface.

5. The satellite payload antenna hinge coaxality alignment test system of claim 4, wherein, The coaxiality measurement interface mainly consists of four areas, namely, a measurement process state area, an image processing and data display area, a measurement result recording area, and a current state operation prompt area, coaxiality adjustment and testing are performed according to the measurement process state prompt, the system collects data, performs image processing and calculation, and finally calculates and displays the coaxiality measurement result.

6. The satellite payload antenna hinge coaxality alignment test system of claim 4, wherein, The historical data interface is used to view past measurement data, and the measurement result can be exported as an Excel file.

7. The satellite payload antenna hinge coaxality alignment test system of claim 4, wherein, The system setting interface is used to set the parameters of the software system itself, and the setting content includes calculation units and calculation parameters.

8. The satellite payload antenna hinge coaxality alignment test system of claim 1, wherein, The light source system adopts an external power supply mode, is connected to 220V mains power through an adapter for power supply, and the imaging system is connected to the display control system through a USB3.1 cable, while image transmission and imaging system power supply are performed.

9. The satellite payload antenna hinge coaxality alignment test system of claim 1, wherein, After the five groups of data in the measurement process state area are all collected, the coaxiality measurement result display interface is entered, and the current coaxiality measurement result is displayed in the measurement result recording area.

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