A satellite test and experiment system

Abstract

The application discloses a satellite test experiment system, relates to the technical field of satellite testing, and is used for satellite quality testing. In order to solve the problem of low efficiency in satellite test experiments, the application provides a satellite test experiment system, which comprises an EMC darkroom and a satellite conveying device. A glass steel walkway with a first distance higher than the ground is arranged in the EMC darkroom, so that the satellite conveying device can convey the satellite to a designated position for test experiments, and the inner walls on each side of the EMC darkroom are provided with wave-absorbing materials which do not need to be disassembled. Therefore, the wave-absorbing materials do not need to be arranged again every time the satellite is tested, and the satellite conveying device can replace the traditional manual satellite conveying. The satellite is conveyed to the designated position for experiments through the arranged glass steel walkway, so that the labor is saved, the test efficiency is improved, and the effect is more remarkable in large-scale satellite testing.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite testing, in particular to a satellite testing system. BACKGROUND

[0002] Due to the influence of satellite on-orbit life and non-maintainability, satellite constellation must complete batch manufacturing and testing of satellites in a short time, and launch into orbit to form business operation capability. There are many testing and experiment projects required for satellites before leaving the factory, and specific projects need to be determined according to actual needs, but electromagnetic compatibility (EMC) as a necessary condition for normal operation of satellites in orbit is a project that must be tested during the manufacturing process of each satellite.

[0003] When performing satellite testing and experiments such as electromagnetic compatibility, there are strict requirements for the test environment, which needs to build an EMC darkroom through wave-absorbing materials, which requires the wave-absorbing materials to be laid all over the EMC darkroom, for example, if the EMC darkroom is a cubic structure, the wave-absorbing materials need to be laid on the six walls. However, since the wave-absorbing materials are soft in texture and need to be avoided from collision and scratching, and there are strict requirements for the position of the satellite during EMC testing and experiments, the existing EMC testing and experiments need to first disassemble the wave-absorbing materials laid on the floor, then transport the satellite to the designated position, and finally lay the wave-absorbing materials again to meet the environmental requirements of EMC testing and experiments. This method is undoubtedly cumbersome and inefficient, and since the laying of wave-absorbing materials currently still relies on manual operation, the entire EMC testing and experiment process inevitably occupies a large amount of manpower, which is not conducive to improving the efficiency of the experiment.

[0004] Therefore, the technical personnel in the field urgently need a satellite testing system to solve the problem of low efficiency in the current satellite testing. SUMMARY

[0005] The purpose of the present application is to provide a satellite testing system to solve the problem of low efficiency in the current satellite testing.

[0006] To solve the above technical problems, the present application provides a satellite testing system, which comprises: an EMC darkroom and a satellite transportation device.

[0007] The EMC darkroom is provided with a glass steel walkway at a first distance above the ground, and the inner surface of the EMC darkroom is laid with wave-absorbing materials.

[0008] The glass steel walkway is provided with a ground antenna connected with a ground test equipment and an EMC receiving antenna connected with an EMC receiver, and the ground test equipment and the EMC receiver are arranged outside the EMC darkroom.

[0009] The satellite transportation device runs on the glass fiber walkway to transport the satellite to a designated position on the glass fiber walkway; wherein the designated position is at a second preset distance from the EMC receiving antenna and at a distance greater than the first distance from the wave-absorbing material.

[0010] Preferably, the satellite transportation device comprises a satellite transportation vehicle and a support parking table.

[0011] The support parking table is used for parking the satellite.

[0012] The satellite transportation vehicle and the support parking table are detachably connected.

[0013] The satellite transportation vehicle is used for horizontal movement in any direction, and the support parking table is unloaded to the designated position when the satellite transportation vehicle runs near the designated position.

[0014] Preferably, the satellite transportation vehicle comprises a vehicle body part and a lifting column, and the support parking table comprises a table top and a table leg.

[0015] The lifting column is arranged on the top of the vehicle body part, and the lower bottom surface of the table top is provided with a first fixing groove which is adapted to the shape of the lifting column and used for embedding the lifting column.

[0016] The maximum extension height of the lifting column is greater than the height of the table leg, and the minimum extension height of the lifting column is less than the height of the table leg.

[0017] Preferably, the upper surface of the table top is provided with a second fixing groove which is used for embedding and fixing the satellite.

[0018] Preferably, the satellite transportation vehicle further comprises an image acquisition device.

[0019] Preferably, the upper surface of the glass fiber walkway is provided with a two-dimensional code which is used for providing position information when scanned by the image acquisition device.

[0020] Preferably, the height of the table leg satisfies that the center of mass of the satellite is within the first range from the upper surface of the glass fiber walkway when the satellite is parked at the designated position.

[0021] Preferably, the upper surface of the glass fiber walkway is flush with the ground outside the EMC darkroom.

[0022] Preferably, the filter is further arranged between the EMC receiving antenna and the EMC receiver.

[0023] Preferably, the EMC receiving antenna is arranged to avoid the main lobe direction of the satellite transmitting antenna when the satellite is parked at the designated position.

[0024] The satellite test experiment system provided by the application comprises an EMC darkroom and a satellite transportation device, the EMC darkroom is provided with a glass steel walkway with a first distance higher than the ground, so that the satellite transportation device can transport the satellite to a designated position for test experiment, and the inner walls on each side of the EMC darkroom can be provided with wave-absorbing materials without dismounting, thereby avoiding the trouble of arranging the wave-absorbing materials again each time the satellite is tested, and the satellite transportation device can replace the traditional manual satellite transportation, so that the satellite is transported to the designated position for test through the arranged glass steel walkway, thereby saving labor and helping to improve the test efficiency, and the effect is more remarkable in large-scale satellite test. BRIEF DESCRIPTION OF DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the application, the drawings used in the embodiments will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative labor.

[0026] Figure 1 A structural diagram of the EMC darkroom provided by the application is shown in the figure.

[0027] Figure 2 A structural diagram of the satellite transportation device provided by the application is shown in the figure.

[0028] Figure 3 A flowchart of the satellite test experiment provided by the application is shown in the figure.

[0029] Figure 4 A scene schematic diagram of the satellite self-compatibility test provided by the application is shown in the figure.

[0030] Figure 5 A scene schematic diagram of the satellite RE102 test provided by the application is shown in the figure.

[0031] In the figure, 100 is the EMC darkroom, 101 is the glass steel walkway, 102 is the wave-absorbing material, 103 is the ground antenna, 104 is the EMC receiving antenna, 105 is the designated position, 106 is the gate, 107 is the filter, 108 is the two-dimensional code, 200 is the satellite transportation device, 210 is the satellite transportation vehicle, 211 is the vehicle body part, 212 is the lifting column, 220 is the support parking table, 221 is the table top, 222 is the table leg, 223 is the second fixing groove, 224 is the satellite support column, 301 is the ground test equipment, 302 is the EMC receiver, and 303 is the satellite. DETAILED DESCRIPTION

[0032] With reference to the drawings, the technical solutions in the embodiments of the present application will be clearly and completely described in order to make the technical solutions in the embodiments of the present application apparent to those skilled in the art. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.

[0033] The core of the present application is to provide a satellite test system.

[0034] In order to make the technical personnel in the art better understand the present application, the present application will be further described in detail below with reference to the drawings and specific embodiments.

[0035] In the current satellite quality test process, based on different satellite use needs, different performance index tests can be selected for the required test experiment, but electromagnetic compatibility (EMC) is a necessary condition for the normal operation of the satellite in orbit, and is a project that must be tested in the manufacturing process of each satellite, so the test efficiency of the EMC test greatly affects the efficiency of the satellite test experiment.

[0036] Since the EMC test has relatively strict requirements on the test environment, it is usually necessary to be carried out in a specially arranged EMC darkroom, and the EMC darkroom is arranged with wave-absorbing materials on each side wall to meet the requirements of the EMC test in the EMC darkroom, for example, the environmental electromagnetic level should be at least 6dB lower than the limit value specified in the GJB151B-2013 safety standard, and in this environment, the test is completed through the ground test equipment, ground antenna, EMC receiving equipment and EMC receiving antenna.

[0037] However, since the EMC test not only has requirements on the environmental electromagnetic level, but also has strict requirements on the placement position of the satellite, for example, the satellite should be at least 3m away from the sharp wedge of each wave-absorbing material, and the EMC receiving antenna should be 100cm away from the satellite body, that is, the satellite needs to be tested in a specified position, which requires the satellite to be transported from the EMC darkroom to the specified position in the EMC darkroom. Since the wave-absorbing material is soft and should be avoided from being collided and scratched, and in order to ensure the requirement of the environmental electromagnetic level, the wave-absorbing material also needs to be laid on the ground of the EMC darkroom, so when the satellite is transported, the wave-absorbing material needs to be removed first, and after the satellite is transported to the specified position, the wave-absorbing material needs to be laid again, so as to perform the EMC test. The whole arrangement process is undoubtedly complicated and time-consuming, which affects the satellite test efficiency, especially in the application scenario of commercialized satellite mass testing, the existing EMC test method has been unable to meet the actual satellite test needs.

[0038] To solve the above problems, the application provides a satellite test system, which comprises an EMC darkroom 100 and a satellite transport device 200.

[0039] The EMC darkroom 100 is provided with a glass steel walkway 101 at a first distance above the ground, and the inner surface of the EMC darkroom 100 is paved with wave absorbing material 102. Figure 1

[0040] The glass steel walkway 101 is provided with a ground antenna 103 connected with a ground test device 301 and an EMC receiving antenna 104 connected with an EMC receiver 302, and the ground test device 301 and the EMC receiver 302 are arranged outside the EMC darkroom 100.

[0041] The satellite transport device 200 runs on the glass steel walkway 101 and is used to transport the satellite to a designated position 105 on the glass steel walkway 101.

[0042] The designated position 105 is at a second preset distance from the EMC receiving antenna 104 and at a distance greater than the first distance from the wave absorbing material 102. As described above, in actual application, the first preset distance is usually 100 cm, and the second preset distance is usually 3 m, but the above values are only one possible implementation scheme and do not limit the first preset distance and the second preset distance.

[0043] It should be noted that, in addition to the above structure, shape and arrangement, the EMC darkroom 100 should also have a door 106 for the operator and the satellite to enter and exit the EMC darkroom 100, and a cable port for connecting the ground antenna 103 and the ground test device 301 arranged inside and outside the EMC darkroom 100 respectively, the EMC receiving antenna 104 and the EMC receiver 302. The cable port is also used for the ground low-frequency cable to supply power to the equipment in the EMC darkroom 100. The above settings are all routine settings of the EMC darkroom 100, so this embodiment will not be described here.

[0044] It should also be noted that the ground antenna 103 and the EMC receiving antenna 104 can also be arranged on the glass steel walkway 101 to avoid unnecessary interference with the wave absorbing material 102 paved on the ground. Further, a filter 107 can be arranged between the EMC receiving antenna 104 and the EMC receiver 302 to filter out the satellite transmission signal, ensuring the accuracy of the test.

[0045] For the same purpose, the EMC receiving antenna 104 should avoid the main lobe direction of the satellite transmitting antenna when placed, that is, there is no EMC receiving antenna 104 placed in the range of the main lobe direction of the satellite transmitting antenna. In some specific application scenarios, an attenuation protection can also be added at the front end of the EMC receiver 302.​

[0046] In addition, the shape and size of the glass fiber reinforced plastic walkway 101 should be adapted to the equipment for EMC test and the size of the satellite, and the material strength should be adapted to the weight of the object to be carried. In practical application, the glass fiber reinforced plastic walkway 101 can also be replaced by a walkway made of other non-metallic materials, and the glass fiber reinforced plastic is only one preferred solution considering the material strength, implementation difficulty and other factors.

[0047] Similarly, for the satellite transportation device 200 used for transporting the satellite on the glass fiber reinforced plastic walkway 101 to the designated position 105 of the glass fiber reinforced plastic walkway 101, the embodiment also provides a preferred implementation scheme as shown in Figure 2 The satellite transportation device 200 includes a satellite transportation vehicle 210 and a support parking table 220.

[0048] The support parking table 220 is used for parking the satellite 303.

[0049] The satellite transportation vehicle 210 and the support parking table 220 are detachably connected.

[0050] The satellite transportation vehicle 210 is used for horizontal movement in any direction, and the support parking table 220 is unloaded to the designated position 105 when it is driven to the vicinity of the designated position 105.

[0051] Considering the ease of implementation and stability, the support parking table 220 can be a common four-legged table, and in order to avoid interference with the EMC test, the support parking table 220 should be made of non-metallic materials such as wood, high-strength plastic, etc. For the satellite transportation vehicle 210, a common transportation vehicle for transporting materials can be used, and the form of transporting materials can be achieved by a liftable fork arranged at the front end of the satellite transportation vehicle 210 or by a lifting column 212 arranged at the top end of the satellite transportation vehicle 210. The embodiment does not limit this, and the satellite transportation vehicle 210 can transport the satellite along the glass fiber reinforced plastic walkway 101 to the designated position 105. In addition, the material of the satellite transportation vehicle 210 is not strictly limited in the embodiment, because at the beginning of the EMC test, the satellite transportation vehicle 210 is different from the support parking table 220 and should have exited the EMC dark room 100, so the material of the satellite transportation vehicle 210 will not interfere with the EMC test, and therefore the material of the satellite transportation vehicle 210 is not limited too much.

[0052] Further, in order to ensure that the satellite will not fall off when being transported on the satellite transportation vehicle 210, and can be smoothly unloaded to the designated position 105 when the satellite transportation vehicle 210 reaches the designated position 105, the embodiment provides a further preferred scheme of the structure of the satellite transportation vehicle 210 and the support parking table 220:

[0053] The satellite transport vehicle 210 comprises a vehicle body part 211 and a lifting column 212, and the support parking table 220 comprises a table top 221 and a table leg 222;

[0054] The lifting column 212 is arranged on the top of the vehicle body part 211, and the lower bottom surface of the table top 221 is provided with a first fixing groove which is adapted to the shape of the lifting column 212 and used for embedding the lifting column 212.

[0055] The highest extension height of the lifting column 212 is greater than the height of the table leg 222, and the lowest extension height of the lifting column 212 is less than the height of the table leg 222.

[0056] The above structure makes it possible to place the satellite on the support parking table 220, and then place the support parking table 220 on the lifting column 212, so as to achieve the detachable fixing effect by embedding the lifting column 212 in the first fixing groove. Meanwhile, when the lifting column 212 is lifted to a height greater than the height of the table leg 222, the table leg 222 of the support parking table 220 does not contact the ground, and can be kept stable by the embedding of the first fixing groove under the action of gravity during the transportation. When the satellite transport vehicle 210 reaches the designated position 105, the lifting column is retracted to a height lower than the height of the table leg 222, the table leg 222 of the support parking table 220 contacts the ground, and the lifting table is separated from the first fixing groove, so as to complete the unloading and separation of the support parking table 220 from the satellite transport vehicle 210.

[0057] It should be noted that, for the above structure, the thickness of the table top 221 and the depth of the first fixing groove can be determined according to actual needs, as long as the first fixing groove can ensure the stability during transportation and can unload the support parking table 220 from the satellite transport vehicle 210.

[0058] Therefore, for the same reason as above, since the support parking table 220 is a device for supporting the satellite, the embodiment also provides a preferred embodiment for the stability of the satellite placed on the support parking table 220:

[0059] The upper surface of the table top 221 is provided with a second fixing groove 223 for embedding and fixing the satellite.

[0060] For the same reason as the first fixing groove, the depth of the second fixing groove 223 is determined according to the actual satellite size and stability needs, and the shape and size of the second fixing groove 223 are also determined according to the shape and size of the satellite to be measured.

[0061] Alternatively, in another application scenario, the satellite does not directly contact the support parking table 220, but is achieved through a plurality of satellite support columns 224, and the second fixing groove 223 can be a plurality of fixing grooves respectively adapted to different satellite support columns 224.

[0062] In addition, the height of the table leg 222 is further preferably such that, when the satellite is parked at the designated position 105, the distance between the center of mass of the satellite placed on the support parking table 220 and the upper surface of the glass steel walkway 101 is within a first range, and in actual applications, the first range can be 60cm-100cm.

[0063] Furthermore, for the satellite transport vehicle 210, other devices for ensuring that the satellite transport vehicle 210 normally implements functions should also be included, for example, to achieve that the satellite transport vehicle 210 can transport the satellite from outside the EMC darkroom 100 to the designated position 105 in the EMC darkroom 100, the satellite transport vehicle 210 can further include: an image acquisition device.

[0064] The image acquisition device is used to identify a path, and the satellite is transported to the designated position 105 through a preset path. Correspondingly, the glass steel walkway 101 can be provided with a path mark for the image acquisition device to identify, for example, a common tracking scheme, a tape or other mark that is obviously different from the color of the upper surface of the glass steel can be pasted on the glass steel walkway 101, so as to track the satellite transport vehicle 210. Similarly, the satellite transport vehicle 210 with the image acquisition device can also be used for obstacle avoidance. If an object, a person or other obstacles are scanned in the path of the glass steel walkway 101, the satellite transport vehicle 210 should avoid or wait for the technical personnel to remove the obstacles.

[0065] It should be further pointed out that the above functions can not only be achieved by the image acquisition device, but also by devices such as infrared scanning devices. For the image acquisition device, it can be achieved by a camera and a matching controller and software, and there are mature technical solutions at present, which will not be described here in this embodiment.

[0066] Alternatively, the embodiment also provides a possible implementation scheme:

[0067] The upper surface of the glass steel walkway 101 is provided with a two-dimensional code 108, which is used to provide position information when scanned by the image acquisition device.

[0068] It should be noted that one or more QR codes 108 can be set. If only one QR code 108 is set, it should be set at the designated location 105 mentioned above, so that the satellite transport vehicle 210 can determine the designated location 105. Similarly, if multiple QR codes 108 are set, they can guide the satellite transport vehicle 210's travel path. QR codes 108 storing different location information are set at regular intervals on the fiberglass walkway 101. The satellite transport vehicle 210 scans the current QR code 108 to determine its current location, and scans the QR code 108 ahead to determine the next travel direction, thereby completing the transport path guidance.

[0069] To minimize human intervention and improve EMC testing efficiency, the satellite transport device 200 should handle all transportation tasks from outside the EMC anechoic chamber 100 to the designated location 105 inside the EMC anechoic chamber 100. Therefore, this embodiment provides another preferred implementation scheme:

[0070] The upper surface of the fiberglass walkway 101 is flush with the ground outside the EMC anechoic chamber 100.

[0071] Correspondingly, the EMC anechoic chamber door 106 should not have a threshold, so that the satellite transport device 200 can travel directly from outside the EMC anechoic chamber 100 into the EMC anechoic chamber 100, and ensure the stability of the transported satellite to avoid losses and dangers caused by the satellite falling off.

[0072] This application provides a satellite testing system, including an EMC anechoic chamber 100 and a satellite transport device 200. The satellite transport device 200 travels on a fiberglass walkway 101 installed inside the EMC anechoic chamber 100 to transport the satellite to a designated location 105 for EMC testing, without manual intervention. Furthermore, since the fiberglass walkway 101 is located at a certain distance above the floor of the EMC anechoic chamber 100, even after the floor of the EMC anechoic chamber 100 is covered with absorbing material 102, it does not affect the transport of the satellite 303. There is no need to repeatedly remove the absorbing material 102 to transport the satellite to the designated location 105, simplifying the EMC testing preparation process and greatly improving testing efficiency.

[0073] Furthermore, the lower surface of the tabletop 221 of the supporting parking table 220 is provided with a first fixing groove, allowing the lifting column 212 of the satellite transport vehicle 210 to engage, thereby ensuring the stability of transportation and preventing the satellite from falling off. Similarly, the upper surface of the tabletop 221 of the supporting parking table 220 is provided with a second fixing groove 223 for fixing the satellite 303, further ensuring the safety and reliability of the satellite 303 during transportation. In addition, the satellite transport vehicle 210 also includes an image acquisition device to realize tracking and obstacle avoidance functions, and the fiberglass walkway 101 can be equipped with a QR code 108 for easy positioning of the satellite transport vehicle 210. At the same time, in order to reduce human intervention and improve stability during the transportation of the satellite 303 to the designated location, the upper surface of the fiberglass walkway 101 is flush with the ground outside the EMC anechoic chamber 100, reducing the bumps when the satellite transport vehicle 200 enters the EMC anechoic chamber 100 and avoiding the risks and losses caused by the satellite falling off. Finally, in order to improve the accuracy of EMC testing, a filter 107 is also set between the EMC receiver 302 and the EMC receiving antenna 104 to filter out the transmitted signal of the satellite 303, meet the relevant requirements in radiated emission testing, and ensure that the EMC receiving antenna 104 is placed away from the main lobe direction of the satellite transmitting antenna. When necessary, attenuation protection is added to the front end of the EMC receiver 302.

[0074] Finally, to clearly illustrate the implementation scheme of the above-mentioned satellite testing system in practical applications, the following example describes a possible embodiment of satellite testing using the above-mentioned satellite testing system. The overall process is as follows: Figure 3 As shown:

[0075] S10: Preparation for satellite status modification.

[0076] Specifically, the modifications to the satellite's technical status include:

[0077] S11: Each subsystem of the satellite completes its installation on the satellite;

[0078] S12: Solar panels without stars;

[0079] S13: The high and low frequency cables of all satellite antennas and individual units have been connected and routed, bundled and fixed as required;

[0080] S14: All structural panels of the satellite have been sealed and opening is not permitted.

[0081] S15: Gaps in the various structural panels and wiring holes of the satellite shall be covered with shielding cloth as required.

[0082] After the satellite status modification is completed, the following will be available:

[0083] S20: Set up an EMC darkroom.

[0084] S21: Lay fiberglass walkways in the EMC darkroom.

[0085] like Figure 1 As shown, the upper surface of the fiberglass walkway 101 is flush with the ground outside the EMC anechoic chamber 100; a QR code 108 is affixed to the upper surface of the fiberglass walkway 101 for positioning and guidance; the designated position 105 is at least 3m away from the wedges of each absorbing material 102 laid in the EMC anechoic chamber 100.

[0086] S22: Install the receiving antenna in the EMC anechoic chamber.

[0087] The EMC receiving antenna 104 is positioned 100cm away from the satellite body placed at the designated location 105. The receiving antenna is connected to the EMC receiver 302, which is located outside the EMC anechoic chamber 100, via a filter 107.

[0088] S23: EMC background environment measurement in a darkroom.

[0089] This means testing whether the environment inside the EMC anechoic chamber 100 meets the conditions for EMC testing. The test frequency band should cover 10kHz to 18GHz (up to 40GHz if equipment allows). Specifically, only vertical polarization testing is performed in the 10kHz to 30MHz band, while both vertical and horizontal dual polarization testing is required in the remaining 30MHz to 18GHz band. The measured ambient electromagnetic level should be at least 6dB lower than the limit specified in the GJB151B-2013 safety regulations to ensure that the anechoic chamber environment meets the EMC testing requirements.

[0090] After the background inspection in step S23 passes, the EMC test can be prepared to begin. It should be noted that steps S21 and S22 in step S20 only need to be performed once at the very beginning. After that, they do not need to be performed before each EMC test. However, considering the standard specifications, the background inspection in step S23 needs to be repeated periodically.

[0091] S30: The satellite is transported to a designated location within the EMC anechoic chamber via a satellite transport device.

[0092] Specifically, the satellite transport device 200 comprises two parts: a satellite transport vehicle 210 and a support and parking table 220, such as... Figure 2 As shown.

[0093] The satellite transport vehicle 210 is responsible for powered transportation and can move in any horizontal direction. It can also be lifted and lowered vertically via the lifting column 212. The satellite transport vehicle 210 is equipped with an image acquisition device to support visual guidance. It can be positioned and guided by scanning the QR code 108 affixed to the upper surface of the fiberglass walkway 101.

[0094] The support table 220 is responsible for the load-bearing and parking of satellite 303. It is made of non-metallic materials, commonly solid wood. The upper surface of the support table 220 has a second fixing groove 223 for engaging with the satellite support column 224 to secure the satellite. The lower surface has a first fixing groove, which serves as the lifting position for the satellite transport vehicle 210's lifting column 212 for engagement and fixation. The height of the support table 220 should ensure that the center of gravity of satellite 303 is 60cm to 100cm from the upper surface of the fiberglass structure when the satellite is parked.

[0095] In the specific implementation of satellite transportation, satellite 303 is first suspended on the support and parking table 220. The satellite support column 224 is placed in the second fixing groove 223 of the support and parking table 220, and the satellite's upward-facing side and ground-facing side are both arranged in a direction perpendicular to the ground to avoid being obstructed by the EMC testing equipment. Then, the satellite transport vehicle 210 lifts the combination of the support and parking table 220 and satellite 303 using the lifting column 212, and guides it to the designated position 105 inside the EMC anechoic chamber 100 by scanning the QR code 108 on the transportation route using the image acquisition device. The lifting column 212 of the satellite transport vehicle 210 lowers, so that the table legs 222 of the support and parking table 220 accurately land on the satellite tooling parking point inside the anechoic chamber (i.e., the designated position 105 mentioned above). The satellite transport vehicle 210 then exits the EMC anechoic chamber 100.

[0096] S40: Detect the background environment of the EMC anechoic chamber without powering on the satellite.

[0097] Specifically, the measurement is conducted under two working conditions:

[0098] Operating Condition 1: Satellite and equipment are not powered on; anechoic chamber background environment.

[0099] Operating Condition 2: Satellite not powered on, equipment powered on, anechoic chamber background environment;

[0100] Background environment measurement mainly aims to eliminate potential interference sources from the external environment, either generated by the ground equipment itself or introduced into the anechoic chamber by the equipment. The test frequency band and electromagnetic level limits are the same as in step S23. After the test in step S40 is also passed, the preparation work before satellite testing is completed, and testing can begin.

[0101] S50: Satellite self-compatibility test.

[0102] Specifically, the satellite is powered by an external power source during self-compatibility testing, specifically via a low-frequency terrestrial cable. Satellite 303 establishes a satellite-to-ground link with ground test equipment 301 through ground antenna 103. The satellite's technical status is as follows: Figure 4 As shown.

[0103] The satellite operating modes should include the following:

[0104] A. Initial orbital mode;

[0105] B. On-orbit satellite platform operating mode;

[0106] C. On-orbit payload operating mode;

[0107] D. Track control mode;

[0108] E, Safe Mode, etc.

[0109] During testing, all individual satellite components should function normally, with particular attention paid to receiver channel sensitivity, uplink bit error rate, and downlink spectrum, with the downlink spectrum used only for monitoring reference. If the satellite's functional performance indicators obtained from testing do not meet the design requirements, the satellite needs to be redesigned, reassembled, and tested again until the requirements are met.

[0110] S60: RE102 Vertical and Horizontal Polarization Tests.

[0111] Specifically, the test configuration is as follows: Figure 5 As shown, the following conditions should be met during testing:

[0112] When placing the EMC receiving antenna 104, it should avoid the direction of the main lobe of the satellite transmitting antenna, and attenuation protection should be added to the front end of the EMC receiver 302 if necessary.

[0113] Radiated emission testing should meet the emission testing requirements and related test method requirements in GJB151B-2013 standard. For measurements in the concave tightened frequency band, the intermediate frequency bandwidth should be reduced accordingly. If necessary, a combination of "low-noise amplifier + filter" should be used for measurement.

[0114] The radiated emission test covers the frequency band from 10 kHz to 18 GHz (up to 40 GHz if equipment allows), of which only vertical polarization testing is performed in the 10 kHz to 30 MHz band, and both vertical and horizontal dual polarization testing is required in the 30 MHz to 18 GHz band.

[0115] During radiated emission testing, the satellite receiving frequency band is tightened and recessed. The specific recess requirements should be determined based on the actual environment and needs.

[0116] S70: The satellite transport device enters the EMC anechoic chamber, rotates the satellite horizontally 180°, places it, and then exits the EMC anechoic chamber.

[0117] Specifically, that is:

[0118] S71: The EMC anechoic chamber door opens, and the satellite transport device enters the EMC anechoic chamber via QR code navigation, accurately positioning itself under the support and parking table;

[0119] S72: The satellite transport device uses a lifting column to lift and support the combination of the parking table and the satellite;

[0120] S73: After the satellite transport device rotates 180° in place (if the lifting column supports rotation, it can also be achieved by rotating the lifting column half a turn), the lifting column descends and places the support parking table at the satellite tooling parking point.

[0121] S74: The satellite transport equipment is withdrawn to the EMC darkroom.

[0122] S80: RE102 Vertical and Horizontal Polarization Tests.

[0123] This is equivalent to repeating step S60.

[0124] S90: Test data processing and interpretation.

[0125] Specifically, analyze the test data of satellite RE102 under different states of S60 and S80. The test results should meet the limit requirements of GJB151B-2013 and the tightened concave requirements of step S60 in the above embodiments.

[0126] If the results do not meet the requirements, the satellite needs to be redesigned and modified until the requirements are met, thus completing the EMC test of a satellite.

[0127] The satellite testing system provided in this application has been described in detail above. The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to in the method section. It should be noted that those skilled in the art can make several improvements and modifications to this application without departing from the principles of this application, and these improvements and modifications also fall within the protection scope of the claims of this application.

[0128] It should also be noted that, in this specification, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

Claims

1. A satellite test bed system, characterized by, The application relates to an EMC darkroom (100) and a satellite transportation device (200). The EMC darkroom (100) is provided with a glass steel walkway (101) at a first distance above the ground, and the inner surface of the EMC darkroom (100) is paved with wave-absorbing material (102); The glass steel walkway (101) is provided with a ground antenna (103) connected with a ground test device (301) and an EMC receiving antenna (104) connected with an EMC receiver (302), and the ground test device (301) and the EMC receiver (302) are arranged outside the EMC darkroom (100); the upper surface of the glass steel walkway (101) is flush with the ground outside the EMC darkroom (100); The satellite transportation device (200) travels on the glass steel walkway (101) and is used for transporting a satellite (303) to a designated position (105) of the glass steel walkway (101); wherein the designated position (105) is at a second preset distance from the EMC receiving antenna (104) and is spaced apart from the wave-absorbing material (102) by a distance greater than the first distance; The satellite transportation device (200) comprises a satellite transportation vehicle (210), a supporting parking table (220) and an image acquisition device; The supporting parking table (220) is used for parking the satellite (303); The satellite transportation vehicle (210) and the supporting parking table (220) are detachably connected; The satellite transportation vehicle (210) is used for moving in a horizontal and arbitrary direction, and the supporting parking table (220) is unloaded to the designated position (105) when the satellite transportation vehicle (210) travels to the vicinity of the designated position (105); before EMC testing starts, the satellite transportation vehicle (210) exits the EMC darkroom (100); The upper surface of the glass steel walkway (101) is provided with a two-dimensional code (108) for providing position information when scanned by the image acquisition device; wherein the two-dimensional code (108) is multiple and is arranged at intervals on the glass steel walkway (101), different two-dimensional codes (108) store different position information, and the satellite transportation vehicle (210) scans the current two-dimensional code (108) to determine the current position and scans the two-dimensional code (108) in front to determine the next traveling direction, so that the transportation path guidance is completed; The satellite transportation vehicle (210) comprises a vehicle body part (211) and a lifting column (212), and the supporting parking table (220) comprises a table top (221) and a table leg (222); The lifting column (212) is arranged at the top of the vehicle body part (211), the lower bottom surface of the table top (221) is provided with a first fixing groove, and the shape of the first fixing groove is matched with the lifting column (212) and is used for embedding the lifting column (212). ​ The highest extension height of the lifting column (212) is greater than the height of the table leg (222), and the lowest extension height is less than the height of the table leg (222); the height of the table leg (222) satisfies that the center of mass of the satellite (303) is within the first range from the upper surface of the glass steel walkway (101) when the satellite (303) is parked at the specified position (105).

2. The satellite test experiment system of claim 1, wherein The upper surface of the table top (221) is provided with a second fixing groove (223) for fitting and fixing the satellite (303).

3. The satellite test experiment system of claim 1, wherein A filter (107) is further arranged between the EMC receiving antenna (104) and the EMC receiver (302).

4. The satellite test bed system of any of claims 1 to 3, wherein, The arrangement position of the EMC receiving antenna (104) avoids the main lobe direction of the satellite transmitting antenna when the satellite (303) is parked at the specified position (105).

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