Satellite load antenna hinge coaxiality adjustment test system and test method thereof

Abstract

The invention discloses a satellite load antenna hinge coaxiality adjustment test system and a test method thereof. The system is characterized by comprising a light source system which is fixed on an upper pin shaft of an antenna hinge in a manner of realizing 360-degree reciprocating rotation motion on the upper pin shaft; the imaging system is fixed on the lower pin shaft of the antenna hinge in a manner that the imaging system can realize reciprocating rotation motion greater than 180 degrees on the lower pin shaft; and the display control system is used for man-machine interaction, displaying the dynamic condition of the cross image on the target surface of the camera of the imaging system, searching the center of the cross through an image processing algorithm, fitting a circle curve and displaying and measuring the coaxiality of the antenna hinge, and has the functions of recording and inquiring measured data. The method solves the problems of indirect measurement, inaccurate measurement result and the like, can be used for satellite load antenna assembly production, and is high in precision, capable of realizing direct measurement, traceable in data and high in assembly and adjustment efficiency.

Description

Technical Field

[0001] The invention relates to satellite ground testing technology, in particular to a satellite payload antenna hinge coaxiality assembly and adjustment testing system. Background Art

[0002] Satellite payload antennas are an important type of effective payload in the satellite field. The satellite payload antenna deployment mechanism needs to complete the release function, deployment function, and locking function in orbit, and support the normal operation of the satellite payload antenna. The coaxiality adjustment of the antenna hinge directly affects the reliability of the deployment and locking of the satellite payload antenna deployment mechanism, and also directly affects whether the payload antenna can work normally in orbit. At present, when installing antenna hinges in China, the coaxiality of the upper and lower hinge rotation axes uses an indirect measurement method of mechanical dimension calculation, which cannot intuitively and accurately reflect the coaxiality error of the antenna hinge. Since this method includes factors such as the satellite attitude error and the shape and position error of the hinge rotation axis itself, the coaxiality measurement accuracy is poor, which also directly affects the reliability of the hinge deployment and locking, bringing important impacts to the model development.

[0003] At present, the measurement of antenna hinge coaxiality in China is to reflect the hinge coaxiality by measuring the deviation value between a single hinge mounting surface and the fitting surface of the upper and lower hinge mounting surfaces. The measurement method mainly has the following problems:

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

[0005] Second, the measurement is indirect. This method only measures the machining error of the mounting surface, but 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 the present invention is to solve the problems of inaccurate measurement results, indirect measurement and the like existing in the prior art.

[0007] In order to achieve the above-mentioned purpose, the present invention provides a satellite payload antenna hinge coaxiality adjustment test system, which is characterized by comprising:

[0008] The light source system is fixed on the upper pin shaft of the antenna hinge in a manner that it can realize 360° reciprocating rotation on the upper pin shaft, and is used to provide a light source with a fixed angle cross spot to facilitate the imaging system to take pictures;

[0009] An imaging system is fixed on the lower pin of the antenna hinge in a manner that it can realize a reciprocating rotational motion greater than 180° on the lower pin, and is used to take photos to form a cross image and provide data to the display and control system for processing;

[0010] The display and control system is used for human-computer interaction, displays the dynamic situation of the cross image on the target surface of the imaging system camera, finds the center of the cross through image processing algorithm, fits the circular curve, displays the coaxiality of the measured antenna hinge, and has the function of measuring data recording and query.

[0011] Furthermore, the light source system includes sequentially arranged components such as a pin shaft, a pin shaft mounting seat, a light source pressure plate, a condenser pressure plate, a cross-reticle pressure plate, a lens barrel, and a glued lens pressure plate, and sequentially inserted into these components are a light source, a condenser, a ground glass, a cross-reticle plate, and a glued lens.

[0012] The pin is used to connect with the hinge rotation axis of the load antenna, the pin mounting seat is used to set the pin, the light source pressure plate is used to fix the light source to the bottom side of the pin mounting seat, the condenser pressure plate is used to fix the condenser to the bottom side of the light source pressure plate and fix the frosted glass to the top side of the cross-graticule plate pressure plate, the cross-graticule plate pressure plate is used to fix the cross-graticule plate to the top side of the lens barrel, and the glued lens pressure plate fixes the glued lens to the bottom of the lens barrel.

[0013] Furthermore, the imaging system includes a filter holder, a filter, a prism holder, a pin, a right-angle prism, a camera holder, and a camera. The filter holder is arranged on the prism holder to fix the filter. The prism holder is arranged on the right-angle prism to fix the right-angle prism. The pin is used to connect to the second rotating axis of the load antenna hinge. The camera holder is arranged on the side of the prism holder to fix the camera.

[0014] Furthermore, the display and control system includes a laptop computer and antenna hinge coaxiality measurement software loaded on the laptop computer, and the software operation interface of the antenna hinge coaxiality measurement software includes a coaxiality measurement interface, a historical data interface, and a system setting interface.

[0015] Furthermore, the coaxiality measurement interface is mainly composed of four areas, namely the measurement process status area, the image processing and data display area, the measurement result recording area, and the current status operation prompt area. The coaxiality adjustment test is performed according to the measurement process status prompt. The system collects data, performs image processing calculations, and finally calculates and displays the coaxiality measurement results.

[0016] Furthermore, the historical data interface is used to view past measurement data, and the measurement results can be exported as Excel files.

[0017] Furthermore, 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.

[0018] Furthermore, the light source system is powered externally by an adapter connected to a 220V mains supply, and the imaging system is connected to the display and control system via a USB3.1 cable, which simultaneously transmits images and powers the imaging system.

[0019] The present invention also provides a test method for the satellite payload antenna hinge coaxiality adjustment test system, which is characterized by comprising the following steps:

[0020] When the measurement process status area of ​​the coaxiality measurement interface is "collecting the first set of data", the imaging system is at the 0° position, rotate the light source system to the 0° position, and after the cross cursor position and coaxiality test data in the image processing and calculation area are stable, click the "record" button in the measurement result recording area to record the measurement results, then rotate the light source system 11 to the 60° position ~ 300° position in sequence, and record the measurement results;

[0021] Next, when the measurement process state area is "collecting the second set of data", the rotating imaging system 12 is located at the 45° position, and the light source system 11 is rotated to the 0° position to the 300° position in sequence, and the measurement results are recorded;

[0022] Next, the third set of data, the fourth set of data, and the fifth set of data are collected in turn, and the measurement results are recorded.

[0023] Furthermore, after all five sets of data in the measurement process status area are collected, the coaxiality measurement result display interface is entered, and the measurement result recording area displays the current coaxiality measurement result.

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

[0025] Highlight 1: The coaxiality adjustment test system for satellite payload antenna hinges of the present invention realizes direct measurement of antenna hinge coaxiality through the light source system and imaging system of the coaxiality adjustment test system, which changes the indirect measurement mode of antenna hinge coaxiality in the past and improves the test accuracy;

[0026] Highlight 2: The coaxiality adjustment test system of the satellite payload antenna hinge of the present invention can display and store test data in real time through the display and control system of the coaxiality adjustment test system, and the traceability of the data provides favorable support for the assembly process;

[0027] Highlight 3: The coaxiality adjustment test system for the hinge of the satellite payload antenna of the present invention has certain scalability, can solve the measurement problem of parameters such as the coaxiality of the payload antenna deployment mechanism, and has certain economic benefit potential. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1It is a schematic diagram of the overall structure of a satellite payload antenna hinge coaxiality adjustment test system in a preferred embodiment of the present invention.

[0029] Figure 2 It is a structural schematic diagram of a light source system in a preferred embodiment of the present invention.

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

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

[0032] Figure 5 It is a schematic diagram of the software coaxiality measurement results of the imaging system in a preferred embodiment of the present invention. DETAILED DESCRIPTION

[0033] The following will be combined Figure 1 to Figure 4 The coaxiality adjustment test system for the hinge of a satellite payload antenna of the present invention is further described in detail.

[0034] The invention discloses an assembly and adjustment test system for the coaxiality of a satellite payload antenna hinge, which is suitable for the assembly and test process of a satellite payload antenna deployment mechanism, and is particularly designed for the field of assembly and testing whether the coaxiality of an antenna hinge meets design requirements during the assembly process of a satellite payload antenna deployment mechanism.

[0035] Figure 1 It is a schematic diagram of the overall structure of a satellite payload antenna hinge coaxiality adjustment test system in a preferred embodiment of the present invention.

[0036] like Figure 1 As shown, the payload antenna hinge 1 22 and the payload antenna hinge 2 23 of the satellite 21 are installed on the satellite 21. During the assembly process of the satellite payload antenna deployment mechanism, the satellite payload antenna hinge coaxiality adjustment test system of this embodiment is connected to the payload antenna hinge 1 22 and the payload antenna hinge 2 23.

[0037] like Figure 1 As shown, the satellite payload antenna hinge coaxiality adjustment test system of this embodiment includes a light source system 11, an imaging system 12 and a display and control system 13. The light source system 11 is used to provide a light source with a fixed angle cross spot so that the imaging system can take pictures and images, and the imaging system 12 is used to take pictures to form a cross image and provide it to the display and control system for processing data.

[0038] The light source system 11 is fixed on the upper pin shaft of the load antenna hinge 22, and can realize 360° reciprocating rotation on the upper pin shaft of the load antenna hinge 22; the imaging system 12 is fixed on the lower pin shaft of the load antenna hinge 23, and can realize reciprocating rotation on the lower pin shaft of the load antenna hinge 23 greater than 180°. The display and control system 13 is used for human-computer interaction, displays the dynamic situation of the cross image on the target surface of the imaging system camera, and finds the center of the cross through the image processing algorithm, fits the circular curve, displays the coaxiality of the measured antenna hinge, and has the function of measuring data recording and query. The light source system 11 adopts an external power supply method, and is powered by a 220V AC power supply connected to the adapter 14. The imaging system 12 is connected to the display and control system 13 via a USB3.1 cable, and can simultaneously transmit images and power the imaging system 13.

[0039] Figure 2 FIG. 1 is a schematic diagram of the structure of a light source system in a preferred embodiment of the present invention.

[0040] like Figure 2 As shown, the light source system 11 of the present invention includes components such as a pin 111, a pin mounting seat 112, a light source pressure plate 113, a condenser pressure plate 114, a cross-reticle pressure plate 115, a lens barrel 116, a glued lens pressure plate 117, etc. which are arranged in sequence, and parts such as the light source 1111, the condenser 1112, the frosted glass 1113, the cross-reticle plate 1114, the glued lens 1115, etc. which are sequentially inserted into these components.

[0041] The pin shaft 111 is used to be connected to the rotating shaft of the load antenna hinge 22, the pin shaft mounting seat 112 is used to set the pin shaft 111, the light source pressure plate 113 is used to fix the light source 1111 to the bottom side of the pin shaft mounting seat 112, the condenser pressure plate 114 is used to fix the condenser 1112 to the bottom side of the light source pressure plate 113 and fix the frosted glass 1113 to the top side of the cross-grain plate pressure plate 115, the cross-grain plate pressure plate 115 is used to fix the cross-grain plate 1114 to the top side of the lens barrel 116, and the glued lens pressure plate 117 fixes the glued lens 1115 to the bottom of the lens barrel 116.

[0042] Figure 3 FIG. 1 is a schematic diagram of the structure of an imaging system in a preferred embodiment of the present invention.

[0043] like Figure 3As shown, the imaging system 12 includes a filter support 121, a filter 122, a prism support 123, a pin 124, a right angle prism 125, a camera support 126, a camera 127 and other parts. 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 124 is used to connect with the rotation axis of the hinge 23 of the load antenna, and the camera support 126 is arranged on the side of the prism support 123 for fixing the camera 127.

[0044] Figure 4 ] is a schematic diagram of the software operation interface of the imaging system in a preferred embodiment of the present invention.

[0045] The display control system 13 of the present invention includes a laptop computer and antenna hinge coaxiality measurement software loaded on the laptop computer. The laptop computer can be a THINKPAD portable computer, T450 series, i5 CPU, solid state hard disk, and equipped with an external optical drive for easy data import and export. The computer is easy to carry, and the solid state hard disk runs fast and has good shock resistance.

[0046] like Figure 4 As shown, the software operation interface of the antenna hinge coaxiality measurement software of the present invention includes a coaxiality measurement interface 1321, a historical data interface 1322, and a system setting interface 1323. The coaxiality measurement interface 1321 is mainly composed of four areas, namely a measurement process status 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 measurement process status prompt, the coaxiality adjustment test is performed, the system collects data, performs image processing calculations, and finally calculates and displays the coaxiality measurement results.

[0047] The historical data interface 1322 is used to view the past measurement data and export the measurement results as Excel files. The system setting interface 1323 is used to set the parameters of the software system itself, such as the configuration of calculation units, calculation parameters, etc.

[0048] Specific software operation process combined Figure 1 and Figure 4 The following are some examples:

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

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

[0051] Next, the third set of data, the fourth set of data, and the fifth set of data are collected in turn, and the measurement results are recorded.

[0052] Figure 5 , which is a schematic diagram of software coaxiality measurement of an imaging system in a preferred embodiment of the present invention.

[0053] like Figure 5 As shown, after all five sets of data in the measurement process status area 1324 of the coaxiality measurement interface 1321 are 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 present invention solves the problems existing in the existing satellite payload antenna deployment mechanism antenna hinge coaxiality measurement process method, such as indirect measurement and inaccurate measurement results; it can be used for satellite payload antenna assembly production, and has the beneficial effects of high precision, direct measurement, data traceability, high assembly and adjustment efficiency, etc.

[0055] It should be noted that the above is only an illustrative description and explanation of the present invention, and those skilled in the art should understand that any modification and replacement of the present invention belongs to the protection scope of the present invention.

Claims

1. A satellite payload antenna hinge coaxiality adjustment test system, characterized in that: include: The light source system is fixed on the upper pin shaft of the antenna hinge in a manner that it can realize 360° reciprocating rotation on the upper pin shaft, and is used to provide a light source with a fixed angle cross spot to facilitate the imaging system to take pictures; An imaging system is fixed on the lower pin of the antenna hinge in a manner that it can realize a reciprocating rotational motion greater than 180° on the lower pin, and is used to take photos to form a cross image and provide data to the display and control system for processing; The display and control system is used for human-computer interaction, displays the dynamic situation of the cross image on the target surface of the imaging system camera, finds the center of the cross through image processing algorithm, fits the circular curve, displays the coaxiality of the measured antenna hinge, and has the function of measuring data recording and query.

2. The satellite payload antenna hinge coaxiality adjustment test system according to claim 1, characterized in that: The light source system comprises sequentially arranged components such as a pin shaft, a pin shaft mounting seat, a light source pressure plate, a condenser pressure plate, a cross-reticle pressure plate, a lens barrel, and a glued lens pressure plate, and sequentially inserted into these components are a light source, a condenser, a ground glass, a cross-reticle plate, and a glued lens. The pin is used to connect with the hinge rotation axis of the load antenna, the pin mounting seat is used to set the pin, the light source pressure plate is used to fix the light source to the bottom side of the pin mounting seat, the condenser pressure plate is used to fix the condenser to the bottom side of the light source pressure plate and fix the frosted glass to the top side of the cross-graticule plate pressure plate, the cross-graticule plate pressure plate is used to fix the cross-graticule plate to the top side of the lens barrel, and the glued lens pressure plate fixes the glued lens to the bottom of the lens barrel.

3. The satellite payload antenna hinge coaxiality adjustment test system according to claim 1, characterized in that: The imaging system includes a filter holder, a filter, a prism holder, a pin, a right-angle prism, a camera holder, and a camera. The filter holder is arranged on the prism holder to fix the filter. The prism holder is arranged on the right-angle prism to fix the right-angle prism. The pin is used to connect with the second rotating shaft of the load antenna hinge. The camera holder is arranged on the side of the prism holder to fix the camera.

4. The satellite payload antenna hinge coaxiality adjustment test system as claimed in claim 1, characterized in that: The display and control system includes a laptop computer and antenna hinge coaxiality measurement software loaded on the laptop computer. The software operation interface of the antenna hinge coaxiality measurement software includes a coaxiality measurement interface, a historical data interface, and a system setting interface.

5. The satellite payload antenna hinge coaxiality adjustment test system as claimed in claim 4, characterized in that: The coaxiality measurement interface is mainly composed of four areas, namely the measurement process status area, the image processing and data display area, the measurement result recording area, and the current status operation prompt area. The coaxiality adjustment test is performed according to the measurement process status prompt. The system collects data, performs image processing calculations, and finally calculates and displays the coaxiality measurement results.

6. The satellite payload antenna hinge coaxiality adjustment test system as claimed in claim 4, characterized in that: The historical data interface is used to view past measurement data and export measurement results as Excel files.

7. The satellite payload antenna hinge coaxiality adjustment test system as claimed in claim 4, characterized in that: 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 coaxiality adjustment test system according to claim 1, characterized in that: The light source system is powered by an external power supply and is connected to a 220V mains power supply through an adapter. The imaging system is connected to the display and control system through a USB3.1 cable, and image transmission and imaging system power supply are performed simultaneously.

9. The test method of the satellite payload antenna hinge coaxiality adjustment test system according to any one of claims 1 to 8, characterized in that: The steps include: When the measurement process status area of ​​the coaxiality measurement interface is "collecting the first set of data", the imaging system is at the 0° position, and the light source system is rotated to the 0° position. After the cross cursor position and the coaxiality test data in the image processing and calculation area are stable, click the "record" button in the measurement result recording area to record the measurement results. Then, rotate the light source system 11 to the 60° position ~ 300° position in sequence, and record the measurement results; Next, when the measurement process state area is "collecting the second set of data", the rotating imaging system 12 is located at the 45° position, and the light source system 11 is rotated to the 0° position to the 300° position in sequence, and the measurement results are recorded; Next, the third set of data, the fourth set of data, and the fifth set of data are collected in turn, and the measurement results are recorded.

10. The testing method according to claim 9, characterized in that: After all five sets of data in the measurement process status area are collected, the coaxiality measurement result display interface is entered, and the measurement result recording area displays the current coaxiality measurement result.

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