Measurement, operation and control docking test method, system, electronic equipment and medium

Abstract

The present application provides a test method for measurement, operation and control docking, characterized in that the method includes: establishing a communication link between a control station, a space environment device and a satellite under test therein; configuring environmental parameters and test parameters; simulating the environment of the satellite under test according to the environmental parameters and performing a measurement, operation and control docking test according to the test parameters to obtain a test result. The present application also provides a measurement, operation and control docking test system, electronic equipment and medium.

Description

Technical Field

[0001] The present application relates to the field of satellite measurement, operation and control technology, and specifically to a measurement, operation and control docking test method, system, electronic equipment and medium. Background Art

[0002] With the development of science and technology, countries around the world have begun to explore space and scramble for space resources. Since the end of the last century, my country has made many great achievements in space technology and aerospace, and my country's aerospace experiments have entered the fast lane of development.

[0003] With the rapid development of communication technology and central processing units, satellite products have begun to transform from the original high-orbit, large satellites to small satellite constellations, such as the Iridium constellation, OneWeb constellation, and Starlink constellation. The number of satellites has increased from the traditional number to hundreds, thousands, and even tens of thousands. For example, Space-X's Starlink project has a total of more than 40,000 satellites, and currently produces 120 satellites per month. This has challenged the traditional satellite development model and capabilities.

[0004] The development of satellites is divided into three stages: AIT (assembly, integration, testing and experimentation). Among them, the most important test and experimentation stage is particularly important in terms of key share and time share in satellite development. In the development of traditional satellites, the test system is targeted at one satellite and one test, and how to use limited resources for batch testing has become an urgent problem to be solved. The development cycle of traditional satellites is 5 to 10 years, and even the development of small satellites takes 2 to 3 years, which cannot meet the development needs of current and future constellation plans. Therefore, a new development model must be adopted to ensure the increase in the number of satellites developed and a significant shortening of the development cycle.

[0005] Among them, after the satellite is in orbit, the ground station, as the only communication device with the satellite, plays an irreplaceable role. Therefore, it is necessary to conduct measurement and control, operation and control docking tests with the ground station before the satellite is launched, and then verify the communication function of the ground station to ensure that the ground station can maintain smooth communication and control capabilities with the satellite after the satellite is in orbit. The traditional measurement, operation and control docking test method places the satellite far away from the ground station, which puts high requirements on the site and the surrounding electromagnetic environment. At the same time, because the satellite is at normal temperature and pressure, it is impossible to simulate the space environment state when the satellite is in orbit. Summary of the invention

[0006] In order to solve the problems of repeated testing and space environment simulation of small satellite measurement, operation and control docking, the present invention adopts the layout of secondary wireless forwarding of antennas, the method of wireless power supply of satellites for space environment simulation equipment, and innovative new testing processes and methods under space environment simulation conditions, which solves the problems of site, environment, repeated testing and other problems of traditional measurement, operation and control docking in terms of device, layout and test mode.

[0007] The present application provides a method for testing the docking of a micro-satellite under a simulated space environment, the method comprising:

[0008] Establishing communication links between the ground station, the space environment device and the satellite under test within it;

[0009] Configure environmental parameters and test parameters;

[0010] The environment of the satellite under test is simulated according to the environmental parameters and the measurement, operation and control docking test is carried out according to the test parameters to obtain the test results.

[0011] Optionally, the establishing of a communication link between the ground station and the space environment simulation device and the satellite under test therein includes at least one or more of the following:

[0012] The ground station is connected to the space environment simulation device via a network cable;

[0013] The ground station is connected to the tower via a wireless signal;

[0014] The tower is connected to the measured satellite via a wireless signal.

[0015] Optionally, simulating the environment of the satellite under test according to the environmental parameters and performing the measurement, operation and control docking test according to the test parameters to obtain the test results includes:

[0016] Execute the total time loop;

[0017] Trigger the execution of the warm section test task;

[0018] Send and receive uplink and downlink data;

[0019] Generate test results;

[0020] Enter the next temperature section task to be triggered;

[0021] Close the timing loop.

[0022] Optionally, the uplink and downlink data sending and receiving includes:

[0023] Send the illumination system start-up command to measure whether the charging current of the satellite under test is normal when illuminated;

[0024] If yes, send a space environment simulation device startup command to measure whether the vacuum degree in the space environment meets the standard;

[0025] If yes, measure whether the temperature control point data meets the standard;

[0026] If yes, start the docking test to determine whether the antenna tracking reception is locked;

[0027] If yes, then determine whether the remote control uplink data transmission and reception is successful;

[0028] If so, determine whether the telemetry downlink data transmission and reception is successful;

[0029] If yes, a test result is generated.

[0030] The present application also provides a micro-satellite measurement, operation, control and docking test system under space environment simulation, the system comprising: a ground station, a tower, a space environment simulation device and at least one satellite under test; wherein,

[0031] The satellite under test is arranged inside the space environment simulation device;

[0032] The ground station establishes a signal link with the satellite under test through the tower, at least for performing uplink and downlink data transmission testing;

[0033] The space environment simulation device comprises an illumination system and a vacuum system. The illumination system and the vacuum system are linked to the ground station and controlled to simulate the real space environment where the satellite under test is located.

[0034] Optionally, the ground station includes:

[0035] A baseband control processor connected to a space environment simulation device;

[0036] A channel simulator connected to the baseband control processor;

[0037] A measurement, operation and control antenna is connected to the channel simulator; the measurement, operation and control antenna communicates with the tower.

[0038] Optionally, the target tower includes:

[0039] a first test antenna in communication with the ground station;

[0040] A first repeater antenna is connected to the first test antenna; the first repeater antenna communicates with the space environment simulation device.

[0041] Optionally, the space environment simulation device includes:

[0042] a second repeater antenna in communication with the tower;

[0043] a second test antenna, connected to the second forwarding antenna and used to establish a link with the satellite under test;

[0044] an illumination system connected to the ground station and used to provide the measured satellite with illumination required for satellite charging; and

[0045] A vacuum system includes the second test antenna, the illumination system and at least one of the satellites under test and constructs a vacuum simulation environment.

[0046] The present application provides an electronic device, including:

[0047] one or more processors;

[0048] A storage device for storing one or more programs;

[0049] When the one or more programs are executed by the one or more processors, the one or more processors implement the described method.

[0050] The present application provides a computer-readable medium having a computer program stored thereon, wherein the method described is implemented when the program is executed by a processor.

[0051] The present application provides a measurement, operation and control docking test system and method under space environment simulation. Compared with traditional test methods, the space simulation and measurement, operation and control docking are co-designed to simplify the test process; at the same time, the real space environment is simulated, which greatly improves the test accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0052] Figure 1 The schematic diagram shows the structure of the measurement, operation and control docking test system of the present application under space environment simulation.

[0053] Figure 2 A schematic diagram of the measurement, operation and control docking test method of the present application under space environment simulation is shown.

[0054] Figure 3 A specific flow chart of step S100 is shown.

[0055] Figure 4 A specific flow chart of step S200 is shown.

[0056] Figure 5 A specific flow chart of step S300 is shown.

[0057] Figure 6 A specific flow chart of the measurement, operation and control docking test method under space environment simulation in an embodiment is shown. DETAILED DESCRIPTION

[0058] The following is an explanation of the implementation of the present application by means of specific embodiments. People familiar with the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification.

[0059] In the following description, reference is made to the accompanying drawings, which describe several embodiments of the present application. It should be understood that other embodiments may be used and that mechanical, structural, electrical, and operational changes may be made without departing from the spirit and scope of the present application. The following detailed description should not be considered limiting, and the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit the present application.

[0060] Although the terms first, second, etc. are used herein to describe various elements in some instances, these elements should not be limited by these terms. These terms are only used to distinguish one element from another element.

[0061] Furthermore, as used in this article, the singular forms "one", "an" and "the" are intended to include plural forms as well, unless there is an indication to the contrary in the context. It should be further understood that the terms "comprise", "include" indicate the presence of features, steps, operations, elements, components, projects, kinds, and / or groups, but do not exclude the presence, occurrence or addition of one or more other features, steps, operations, elements, components, projects, kinds, and / or groups. The terms "or" and "and / or" used herein are interpreted as inclusive, or mean any one or any combination. Therefore, "A, B or C" or "A, B and / or C" means "any of the following: A; B; C; A and B; A and C; B and C; A, B and C". Only when the combination of elements, functions, steps or operations is inherently mutually exclusive in some way, will there be an exception to this definition.

[0062] like Figure 1 As shown, the entire test method and system are divided into three parts: ground station, tower and space environment simulation equipment.

[0063] The ground station mainly includes the measurement, operation and control antenna, channel simulator and baseband control processor. The ground station mainly completes the transmission of uplink remote control data from software to antenna, including information modulation and coding, channel link attenuation, Doppler and delay adjustment, and wireless signal azimuth angle adjustment.

[0064] The benchmark tower mainly includes test antennas, forwarding antennas and corresponding high-frequency cable components. The benchmark tower part is mainly used to complete the wireless transfer of measurement and control and operation control signals between multiple scenarios.

[0065] The space environment simulation device includes the device body, which contains the lighting system, test antenna, and wall cable assembly inside, and the repeater antenna outside. At least one satellite under test is placed in the space environment simulation device. The space environment simulation device provides a vacuum environment, high and low temperature environment, and background radiation. The test antenna is placed inside to provide wireless measurement and control signals, and the lighting system is placed to charge the satellite solar panels.

[0066] More specifically, the main functions that the micro-satellite measurement, operation, control and docking test system needs to achieve under space environment simulation include:

[0067] Ground station remote control uplink sending function:

[0068] It includes: sending a satellite uplink command from a ground station and forwarding it through multiple stages so that the satellite in the space environment simulation device receives it;

[0069] Satellite downlink telemetry data shows:

[0070] It includes: the telemetry sent from the satellite is forwarded through multiple stages so that it can be received and displayed by a ground station far away outside the space environment simulation equipment.

[0071] Satellite channel simulation:

[0072] Includes: link calculation and measurement through multi-stage forwarding, and the use of channel simulation equipment to correct the communication signal to a real on-orbit signal.

[0073] Satellite wireless power supply and control:

[0074] It includes: controlling the lighting device in the space environment simulation equipment through the ground station system and providing wireless power to the satellite.

[0075] The entire system is divided into three areas according to spatial distribution. The areas are connected wirelessly through satellite measurement and control antennas and wired through network TCP / IP. The areas are connected internally through RF cables, intermediate frequency cables, network TCP / IP wired connections and antenna wireless connections. The connection sequence is as follows:

[0076] The baseband control processor and the lighting system are connected via TCP / IP network cable;

[0077] The baseband control processor is connected to the channel simulator via an intermediate frequency cable;

[0078] The channel simulator is connected to the measurement, operation and control antenna via a radio frequency cable;

[0079] The measurement, operation and control antenna is connected to the first test antenna through wireless alignment;

[0080] The first test antenna is connected to the first forwarding antenna via a radio frequency cable;

[0081] The first forwarding antenna is connected to the second forwarding antenna via wireless alignment;

[0082] The second forwarding antenna is connected to the second test antenna via a radio frequency cable;

[0083] The second test antenna is connected to the satellite under test via wireless;

[0084] The illumination system is connected to the satellite under test through optical radiation.

[0085] In this embodiment, the space environment simulation device includes:

[0086] a second repeater antenna in communication with the tower;

[0087] a second test antenna, connected to the second forwarding antenna and used to establish a link with the satellite under test;

[0088] an illumination system connected to the ground station and used to provide the measured satellite with illumination required for satellite charging; and

[0089] A vacuum system includes the second test antenna, the illumination system and at least one of the satellites under test and constructs a vacuum simulation environment.

[0090] like Figure 2-6 As shown, the present application provides a method for testing the docking of a micro-satellite under a space environment simulation, characterized in that the method comprises:

[0091] S100, establishing a communication link between the ground station, the space environment device and the satellite under test therein;

[0092] S200, configure environmental parameters and test parameters;

[0093] S300, simulating the environment of the satellite under test according to the environmental parameters and performing a measurement, operation and control docking test according to the test parameters to obtain a test result.

[0094] Figure 6 The specific flow chart of the test method in this embodiment is shown. Figure 3-5 for Figure 2 and Figure 6 further elaborate on the content.

[0095] Step S100 establishes a communication link between the ground station, the space environment device and the satellite under test; mainly includes:

[0096] The ground station is connected to the space environment simulation device via a network cable;

[0097] The ground station is connected to the tower via a wireless signal;

[0098] The tower is connected to the measured satellite via a wireless signal.

[0099] Specifically, Figure 3 The specific flow chart of step S100 is shown, that is, the following connections are completed in sequence:

[0100] The baseband control processor and the lighting system are connected via TCP / IP network cable;

[0101] The baseband control processor is connected to the channel simulator via an intermediate frequency cable;

[0102] The channel simulator is connected to the measurement, operation and control antenna via a radio frequency cable;

[0103] The measurement, operation and control antenna is connected to the first test antenna through wireless alignment;

[0104] The first test antenna is connected to the first forwarding antenna via a radio frequency cable;

[0105] The first forwarding antenna is connected to the second forwarding antenna via wireless alignment;

[0106] The second forwarding antenna is connected to the second test antenna via a radio frequency cable;

[0107] The second test antenna is connected to the satellite under test via wireless;

[0108] The illumination system is connected to the satellite under test through optical radiation.

[0109] Specific reference Figure 4 , Figure 4 The specific flow chart of step S200 is shown. The step 200 configures the environmental parameters and test parameters including at least one or more of the following:

[0110] Configure signal source, configure modulation and demodulation mode, configure polynomial parameter configuration, configure telemetry data parsing formula parameters, configure channel simulator loop, configure RF link attenuation value, configure antenna pointing parameters, configure tracking closed-loop PID parameters, configure lighting system illumination, configure power-on time configuration, configure vacuum degree of space environment simulation equipment, configure high and low temperature limits of space environment simulation equipment, and configure number of cycles.

[0111] Specifically, the configuration environment parameters and test parameters are as follows:

[0112] 1. The baseband control processor sets the signal source, modulation and demodulation to spread spectrum incoherent mode, polynomial parameter configuration, and telemetry data analysis formula parameter configuration.

[0113] 2. Channel simulator loop configuration, RF link attenuation value configuration (typical value 60dB, 1~110dB adjustable).

[0114] 3. Antenna pointing parameter configuration and tracking closed-loop PID parameter configuration.

[0115] 4. Configuration of illumination system illumination and power-on time.

[0116] 5. Configuration of vacuum degree, high and low temperature limits, and number of cycles of space environment simulation equipment.

[0117] Figure 5 The specific implementation steps of step S300 are shown. Optionally, the uplink and downlink data transmission and reception include:

[0118] Send the illumination system start-up command to measure whether the charging current of the satellite under test is normal when illuminated;

[0119] If yes, send a space environment simulation device startup command to measure whether the vacuum degree in the space environment meets the standard;

[0120] If yes, measure the temperature control point data and the temperature measurement point data to see if they meet the standards;

[0121] Preferably, corresponding to Figure 6 The measured temperature control point data and temperature measurement points shown in the figure include the rapid temperature change cooling section test, low temperature section test, rapid temperature change heating section test, and high temperature section test. In the simulated space environment, the temperature change range of the satellite under test and the entire simulated environment is about ±70°C, but the temperature change is not steady. The rapid temperature change cooling section test, low temperature section test, rapid temperature change heating section test, and high temperature section test are used to simulate the different temperature changes of the satellite under test under different light intensities, as well as the performance of the satellite under test under these conditions.

[0122] The rapid temperature change cooling stage test refers to the temperature change situation in which the temperature of the satellite under test starts to drop from the high temperature stage and the temperature changes greatly within a unit time. For example, in the process of cooling from +70℃ to -70℃, the cooling speed in the interval from +10℃ to -20℃ is obvious, and this interval is the rapid temperature change cooling stage. For the illumination system, it refers to the simulated state in which the illumination intensity decreases rapidly.

[0123] Low temperature test refers to the steady-state low temperature stage close to -70℃ in the low temperature space simulation environment. For the lighting system, it refers to the simulated state of low light intensity or turning off the lighting system.

[0124] The rapid temperature change heating section test refers to the heating process with a large temperature change within a unit time. For example, in the heating process from -70℃ to +70℃, the cooling speed in the interval from -20℃ to +10℃ is obvious, and this interval is the rapid temperature change heating section. For the lighting system, it refers to the simulation state where the light intensity continues to increase rapidly.

[0125] The high temperature stage test refers to the steady low temperature stage close to +70℃ in a high temperature space simulation environment. Corresponding to the lighting system, it refers to the simulated state of maintaining high light intensity.

[0126] The above-mentioned temperature change amplitudes, low temperature and high temperature judgment thresholds are well-known in the art, including ±70°C, -20°C and +10°C, which are examples used for illustration in the embodiment, and belong to the temperature changes that the satellite under test will experience under normal circumstances in the measurement, operation and control docking test. They are used to elaborate on the specific implementation of step S300 in this application, and have no limiting effect on the scheme and protection scope of this application. Therefore, the specific judgment thresholds for the above-mentioned situations are not repeated in this embodiment.

[0127] If yes, start the docking test to determine whether the antenna tracking reception is locked;

[0128] If yes, then determine whether the remote control uplink data transmission and reception is successful;

[0129] If so, determine whether the telemetry downlink data transmission and reception is successful;

[0130] If yes, a test result is generated.

[0131] The above embodiments are merely illustrative of the principles and effects of the present application and are not intended to limit the present application. Anyone familiar with the technology may modify or change the above embodiments without violating the spirit and scope of the present application. Therefore, all equivalent modifications or changes made by a person of ordinary skill in the art without departing from the spirit and technical ideas disclosed in the present application shall still be covered by the claims of the present application.

Claims

1. A micro-satellite measurement, operation and control docking test method under space environment simulation, characterized in that: The method comprises: Establishing communication links between ground stations, space environment simulation equipment and the satellite under test within them; At least one of the satellites under test is arranged in the space environment simulation device; The space environment simulation device includes a lighting system and a vacuum system, and the lighting system and the vacuum system are linked to the ground station and controlled to simulate the real space environment where the satellite under test is located; Configure environmental parameters and test parameters; Simulate the environment of the satellite under test according to the environmental parameters and perform the measurement, operation and control docking test according to the test parameters to obtain the test results; The test results obtained by simulating the environment of the satellite under test according to the environmental parameters and performing the measurement, operation and control docking test according to the test parameters include: Execute the total time loop; Trigger the execution of the warm section test task; Send and receive uplink and downlink data; Generate test results; Enter the next temperature section task to be triggered; Close the timing loop; The uplink and downlink data transmission and reception comprises: Send the illumination system start-up command to measure whether the charging current of the satellite under test is normal when illuminated; If yes, send a space environment simulation device startup command to measure whether the vacuum degree in the space environment meets the standard; If yes, measure whether the temperature control point data meets the standard; If yes, start the docking test to determine whether the antenna tracking reception is locked; If yes, then determine whether the remote control uplink data transmission and reception is successful; If so, determine whether the telemetry downlink data transmission and reception is successful; If yes, a test result is generated.

2. The micro-satellite measurement, operation and control docking test method under space environment simulation according to claim 1 is characterized in that: The establishment of a communication link between the ground station and the space environment simulation device and the satellite under test therein includes at least one or more of the following: The ground station is connected to the space environment simulation device via a network cable; The ground station is connected to the tower via a wireless signal; The tower is connected to the measured satellite via a wireless signal.

3. A micro-satellite measurement, operation, control and docking test system in a space environment simulation for implementing the method of claim 1, characterized in that: The system comprises: a ground station, a beacon tower, a space environment simulation device and at least one satellite to be tested; wherein, The satellite under test is arranged inside the space environment simulation device; The ground station establishes a signal link with the satellite under test through the tower, at least for performing uplink and downlink data transmission testing; The space environment simulation device includes a lighting system and a vacuum system, and the lighting system and the vacuum system are linked to the ground station and controlled to simulate the real space environment where the satellite under test is located; The space environment simulation device comprises: a second repeater antenna in communication with the tower; a second test antenna, connected to the second forwarding antenna and used to establish a link with the satellite under test; an illumination system connected to the ground station and used to provide the measured satellite with illumination required for satellite charging; and A vacuum system includes the second test antenna, the illumination system and at least one of the satellites under test and constructs a vacuum simulation environment.

4. The micro-satellite measurement, operation, control and docking test system under space environment simulation according to claim 3 is characterized in that: The ground station comprises: A baseband control processor connected to a space environment simulation device; A channel simulator connected to the baseband control processor; A measurement, operation and control antenna is connected to the channel simulator; the measurement, operation and control antenna communicates with the tower.

5. The micro-satellite measurement, operation, control and docking test system under space environment simulation according to claim 3 is characterized in that: The tower comprises: a first test antenna in communication with the ground station; A first repeater antenna is connected to the first test antenna; the first repeater antenna communicates with the space environment simulation device.

6. An electronic device, characterized in that: include: one or more processors; A storage device for storing one or more programs; When the one or more programs are executed by the one or more processors, the one or more processors implement the method as claimed in claim 1 or 2.

7. A computer readable medium having a computer program stored thereon, characterized in that: When the program is executed by a processor, the method according to claim 1 or 2 is implemented.

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