CN115001612B - A satellite rapid self-test system and method based on an in-satellite self-test device - Google Patents

Abstract

The present invention proposes a satellite rapid self-test system and method based on an in-satellite self-test device, the system comprising a BIT (Built-in-test) terminal, a BIT test host computer, a master control server, a telemetry and remote control ground device, and a ground power supply; the BIT terminal is placed inside the satellite body, and is connected to the BIT test host computer through a local area network (LAN). After receiving a satellite self-test process start instruction sent by the BIT test host computer, a health status check is performed on a satellite system unit and its subordinate machines according to a test case pre-injected by the BIT test host computer, and the check result is uploaded to the BIT test host computer through the LAN. The present invention replaces the traditional method of mainly relying on external ground test equipment. Compared with traditional external test equipment, the volume is greatly reduced, the operation is simple and convenient, the execution speed is faster, and the satellite health status self-check can be realized.

Description

A satellite rapid self-test system and method based on an in-satellite self-test device

Technical Field

The invention relates to a satellite rapid self-test system and method based on an in-satellite self-test device, belonging to the field of spacecraft ground testing.

Background technique

Satellite ground testing refers to the comprehensive inspection of all components of the satellite, including the software system and hardware system, through testing equipment on the ground to ensure that it can operate normally and stably in orbit after launch. Currently, satellite testing mainly relies on external ground test equipment (EGSE, Electric Ground Support Equipment) to apply excitation signals to the satellite, collect satellite output signals, and compare them with the expected results. All test processes are completed on the ground inspection equipment outside the satellite.

At present, the ground testing of large satellites requires a large number of ground equipment, including 6 to 10 computers, and special test equipment including power supply and distribution, telemetry and remote control, and control system test equipment. The above equipment is large in size, inconvenient to move, and has different operation methods and inconvenient maintenance. Especially as the functions of satellites become more and more complex, the number of test cables connecting the satellite and the ground during ground testing is large and distributed throughout the satellite. When switching from one stage to another, the test cables need to be plugged in and out. This process is time-consuming and labor-intensive, and the test cable status setting takes a long time. In addition, the current ground test uses the measurement and control channel to set up the satellite and collect telemetry. Due to the limitation of the transmission rate of the measurement and control channel, it has a great impact on the test efficiency.

The current satellite industry is developing towards a direction of increasingly complex technical status and larger satellite networking scale. Ground testing efficiency has become a bottleneck for the satellite industry, especially for ground manufacturing of large-scale networked satellites. The traditional model of satellite testing through satellite body external test equipment is increasingly in conflict with the growing mission requirements.

Summary of the invention

The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to propose a satellite rapid self-test system and method based on an in-satellite self-test BIT terminal device, to replace the traditional EGSE to complete the health status check of a single satellite and its subordinate machines, to reduce the number and volume of test equipment and the satellite-to-ground connection, to increase the test speed, to significantly reduce the cost of test equipment and the demand for personnel, and to adapt to the development model of future mass-produced satellites.

The solution of the present invention is:

A satellite rapid self-test system based on an in-satellite self-test device comprises a BIT terminal, a BIT test host computer, a master control server, a telemetry and remote control ground device and a ground power supply; the BIT terminal is placed inside the satellite body; wherein:

BIT terminal: connected to the BIT test host computer via LAN, and connected to the satellite via bus. After receiving the satellite self-test process start command sent by the BIT test host computer, it performs health status checks on the satellite system unit and its subordinate computers according to the test cases pre-injected by the BIT test host computer, and uploads the satellite health status check results to the BIT test host computer via LAN; the bus types supported by the BIT terminal include 1553B, CAN and RS422 satellite buses; the BIT terminal is fixed inside the satellite through mechanical connection and moves with the satellite during the transition period of the satellite ground test site;

BIT test host computer: connected to BIT terminal, master control server, telemetry and remote control ground equipment, and ground power supply through LAN; injects test cases into BIT terminal, sends satellite self-test process start command, obtains satellite health status check results uploaded by BIT terminal; sends self-test system power-on command and satellite power-on remote control command to ground power supply; sends satellite measurement and control and satellite service system power-on and status setting command to telemetry and remote control ground equipment;

Master control server: used for network control of all devices in the self-test system except BIT terminal;

Telemetry and remote control ground equipment: connected to the satellite's measurement and control and satellite service system through a dedicated cable, and powered on and set the status of the satellite's measurement and control and satellite service system according to the satellite measurement and control and satellite service system power-on and status setting instructions sent by the BIT test host computer;

Ground power supply: after receiving the self-test system power-on command and satellite power-on remote control command sent by the BIT test host computer, it supplies power to the self-test system and the satellite respectively.

A self-test method for a satellite rapid self-test system based on an in-satellite self-test device, the specific steps comprising:

Step 1: Complete the connection between the self-test system and the satellite system;

Step 2: Power the self-test system and check whether the self-test system works normally. If it works normally, proceed to step 3.

Step 3: The BIT test host computer injects test cases into the BIT terminal inside the satellite;

Step 4: The BIT test host computer controls the ground power supply to supply power to the self-test system and the satellite; controls the telemetry and remote control ground equipment to power on and set the status of the satellite measurement and control and satellite service systems; the BIT test host computer sends a test command to the satellite through the BIT terminal. If the satellite's telemetry information can be received and analyzed, it is considered that the self-test system and the satellite's remote control and telemetry channels are working normally, and the BIT test host computer sends a satellite self-test process start command to the BIT terminal;

Step 5: The BIT terminal sends test instructions to the satellite system unit and its subordinate computers through the bus in turn according to the injected test cases, and receives and interprets the telemetry data fed back by the satellite system unit and its subordinate computers;

Step 6: The BIT terminal uploads the interpretation result and telemetry data to the BIT test host computer via LAN for manual review and subsequent processing; the interpretation result is the satellite health status check result;

Step seven: Power off the satellite system and restore the ground equipment status.

Furthermore, assuming that there are M stand-alone machines mounted on the main bus of the satellite system, where the i-th stand-alone machine has N subordinate machines, and the initial value of i is 1, the workflow for checking the health status of the satellite system stand-alone machine is as follows:

a) The BIT terminal sends a power-on command to the i-th single machine;

b) The BIT terminal waits for the stand-alone machine to be powered on and start running. When the stand-alone machine is powered on, it works on the main bus by default;

c) The BIT terminal obtains the telemetry packet of the i-th single machine through the main bus and analyzes its power supply voltage and related telemetry information;

d) The BIT terminal reads the telemetry information of the i-th single machine according to the pre-written reading range of the telemetry information of the i-th single machine. If the telemetry information of the i-th single machine is not within the reading range, it is determined that the working state of the i-th single machine is abnormal, and the error information is recorded. The BIT terminal sends a shutdown command through the bus to shut down the i-th single machine, and the value of i is increased by 1. If i≤M, return to step a) and perform the inspection process of the next single machine. If i＞M, end; if the telemetry information of the i-th single machine is within the reading range, enter step e);

e) The BIT terminal sends a command through the bus to switch the i-th single machine from the main bus to the standby bus; the BIT terminal obtains the telemetry package information of the i-th single machine through the standby bus. If the telemetry package information of the single machine can be obtained through the standby bus, it indicates that the standby bus of the i-th single machine is working normally. The BIT terminal sends a command to switch the i-th single machine to the main bus and enters step f); if the BIT terminal cannot obtain the telemetry package information of the i-th single machine from the standby bus, it indicates that the standby bus of the i-th single machine has a fault. The BIT terminal records the error information. The BIT terminal sends a shutdown command through the bus to shut down the i-th single machine. The value of i is increased by 1. If i≤M, return to step a) and perform the inspection process of the next single machine. If i＞M, end;

f) Check all N lower machines of the ith single machine in turn and record the inspection results. When all N lower machines are checked, the BIT terminal sends a shutdown command through the bus to shut down the ith single machine. The value of i is increased by 1. If i≤M, return to step a) and proceed to the inspection process of the next single machine. If i＞M, end.

Furthermore, assuming that the initial value of j is 1, the workflow for checking all N subordinate machines of the i-th single machine is as follows:

a) The BIT terminal sends a power-on command to the jth slave computer of the i-th stand-alone machine through the bus, waiting for the slave computer of the stand-alone machine to be powered on and start running;

b) The telemetry information of the jth lower computer of the ith single machine is collected by the ith single machine and transmitted to the BIT terminal through the main bus;

c) The BIT terminal obtains the telemetry package of the jth slave computer of the i-th single machine from the telemetry information, parses the power-on status of the jth slave computer of the i-th single machine, and the working status information after power-on, and compares it with the preset judgment range. If it is within the judgment range, it goes to step d); if it is not within the judgment range, it is determined that the working status of the jth slave computer is abnormal, records the error information, and goes to step d);

d) Add 1 to the value of j. If j≤N, jump to step a) and check the next lower computer. If j>N, end.

The beneficial effects of the present invention compared with the prior art are:

(1) The BIT terminal establishes a connection with the satellite through a bus and is connected to the ground BIT test host computer through a LAN. Compared with traditional external test equipment, it can greatly reduce the test cable connection and the volume of test equipment during the satellite ground test process;

(2) The BIT terminal can be placed inside the satellite body, and is connected to the outside world by only one network cable and one power cable. After a test phase, only the network cable and the power cable need to be disconnected, and the connection between the BIT terminal and the satellite can be retained. During the transition period of the satellite ground test site, the BIT terminal moves with the satellite, which can reduce the repeated plugging and unplugging of cables and the transfer and debugging of ground test equipment.

(3) The data exchange between the BIT terminal and the satellite through the bus is more than an order of magnitude faster than the traditional test method through the measurement and control channel, which significantly improves the test process execution;

(4) Through the BIT test host computer, the BIT terminal is injected with the satellite system single machine and its lower machine self-test trial cases to achieve customized satellite autonomous detection.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG1 is a flow chart of a satellite rapid self-test method based on an in-satellite self-test device;

FIG2 is a schematic diagram of a satellite rapid self-test system based on an in-satellite BIT terminal.

Detailed ways

The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments:

As shown in FIG2 , a satellite rapid self-test system based on an in-satellite self-test device includes a BIT terminal, a BIT test host computer, a master control server, telemetry and remote control ground equipment, and a ground power supply; the BIT terminal is placed inside the satellite body, connected to the BIT test host computer via LAN, and connected to the satellite via a bus. After receiving the satellite self-test process start instruction sent by the BIT test host computer, the health status check of the satellite system unit and its subordinate computers is carried out according to the test cases pre-injected by the BIT test host computer, and the satellite health status check results are uploaded to the BIT test host computer via LAN; the bus types supported by the BIT terminal include common satellite buses such as 1553B, CAN, and RS422, which can meet the testing requirements of different satellites; the BIT terminal adopts a miniaturized design, is fixed inside the satellite by mechanical connection, and moves with the satellite during the transition period of the satellite ground test site. Unlike traditional ground test equipment, it is not necessary to disconnect the satellite and the external connection cable to move the satellite.

The BIT test host computer is connected to the BIT terminal, the master control server, the telemetry and remote control ground equipment, and the ground power supply through LAN, runs the BIT test main control software, sends test cases and satellite self-test process start instructions to the BIT terminal, and obtains the satellite health status check results uploaded by the BIT terminal; sends the self-test system power-on instruction and the satellite power-on remote control instruction to the ground power supply; sends the satellite measurement and control and satellite service system power-on and status setting instructions to the telemetry and remote control ground equipment; the master control server is used for network control of the self-test system equipment except the BIT terminal; the telemetry and remote control ground equipment is connected to the measurement and control and satellite service system on the satellite through a dedicated cable, and according to the satellite measurement and control and satellite service system power-on and status setting instructions sent by the BIT test host computer, the measurement and control and satellite service system on the satellite is powered on and the status is set, and a remote control and telemetry channel between the satellite and the ground is established; after receiving the self-test system power-on instruction and the satellite power-on remote control instruction sent by the BIT test host computer, the ground power supply supplies power to the self-test system and the satellite respectively.

Products on the satellite include measurement, control and satellite service systems, power controllers, attitude and orbit control computers, actuators, sensors, payload business units, platform business units, payloads and platform equipment. The satellite measurement, control and satellite service system completes the telemetry and remote control of the ground equipment of the self-test system, as well as on-board data management and maintenance. The satellite power controller is used for satellite power generation, storage and distribution. The attitude and orbit control computer is used for attitude and orbit measurement and control of the satellite while in orbit. The payload business unit is used for the management of satellite payload equipment, including command sending and telemetry collection, and establishes an interface between the payload equipment and the measurement, control and satellite service system. The platform business unit is used for the management of satellite payload equipment, including command sending and telemetry collection, and establishes an interface between the platform equipment and the digital control computer.

As shown in FIG1 , the detailed steps of a satellite rapid self-test method based on an in-satellite self-test device are described as follows:

1. Connection of self-test system

Before the test, the connection between the self-test system and the satellite system is completed. The BIT test host computer, the master control server, and the ground power supply in the self-test system are connected by LAN. The ground power supply and the satellite are connected by a dedicated ground test cable. The telemetry and remote control ground equipment are connected to the satellite control and satellite service system through a dedicated cable; the BIT terminal and the ground BIT test host computer are connected to the LAN through the power supply cable; the products on the satellite are connected through the onboard cable network, and the BIT terminal is connected to the satellite bus through the bus detection port reserved on the satellite.

2. Ground test equipment status setting

Turn on the main power switch on the ground, the power of the master control server and the BIT test host computer, as well as the power of the BIT terminal, and make corresponding settings for the software running on the BIT test host computer to ensure the normal operation of the self-test system equipment; according to the test task requirements, use the BIT test host computer to inject test cases into the BIT terminal through LAN. The above test cases are formulated on the ground based on the product status, connection relationship, and test content on the satellite, including the test sequence of the single machine on the satellite, the instructions sent by the test, and the expected interpretation range of the telemetry results.

3. Satellite initial status setting

The BIT test host computer sends a self-test system power-on command to the ground power supply to complete the power supply of the self-test system; sends a satellite power-on remote control command to the ground power supply to complete the satellite power supply by controlling the satellite power controller; sends satellite measurement and control and satellite service system power-on and status setting commands to the telemetry and remote control ground equipment, and performs status setting to establish a remote control and telemetry channel between the satellite and the ground; sends a test command to the satellite through the BIT terminal. If the satellite's telemetry information can be received and analyzed, the self-test system and the satellite's remote control and telemetry channel are working normally; the BIT test host computer sends a satellite self-test process start command to the BIT terminal.

4. Start the self-check process

After receiving the self-test start command sent by the BIT test host computer, the BIT terminal performs a satellite health status self-test according to the pre-injected test cases. The health status check of a single machine includes the power-on and power-off status, key characteristic parameters and bus communication function of the single machine. The health status check of the lower machine of the single machine includes the power-on status of the lower machine and important parameter information of the single machine's work;

The satellite health status self-test is performed according to the preset steps. Each step has a corresponding command to send and a corresponding telemetry interpretation, which needs to cover all testable units and slave computers on the satellite. Assuming that there are M units mounted on the satellite system main bus, the i-th unit has N slave computers, and the initial value of i is 1, the health status check workflow for the satellite system unit is as follows:

a) The BIT terminal sends a power-on command to the i-th single machine;

b) The BIT terminal waits for the stand-alone machine to be powered on and start running. When the stand-alone machine is powered on, it works on the main bus by default;

c) The BIT terminal obtains the telemetry packet of the i-th single machine through the main bus and analyzes its power supply voltage and related telemetry information;

d) The BIT terminal reads the telemetry information of the i-th single machine according to the pre-written reading range of the telemetry information of the i-th single machine. If the telemetry information of the i-th single machine is not within the reading range, it is determined that the working state of the i-th single machine is abnormal, and the error information is recorded. The BIT terminal sends a shutdown command through the bus to shut down the i-th single machine, and the value of i is increased by 1. If i≤M, return to step a) and perform the inspection process of the next single machine. If i＞M, end; if the telemetry information of the i-th single machine is within the reading range, enter step e);

e) The BIT terminal sends a command through the bus to switch the i-th single machine from the main bus to the standby bus; the BIT terminal obtains the telemetry package information of the i-th single machine through the standby bus. If the telemetry package information of the single machine can be obtained through the standby bus, it indicates that the standby bus of the i-th single machine is working normally. The BIT terminal sends a command to switch the i-th single machine to the main bus and enters step f); if the BIT terminal cannot obtain the telemetry package information of the i-th single machine from the standby bus, it indicates that the standby bus of the i-th single machine has a fault. The BIT terminal records the error information. The BIT terminal sends a shutdown command through the bus to shut down the i-th single machine. The value of i is increased by 1. If i≤M, return to step a) and perform the inspection process of the next single machine. If i＞M, end;

f) Check all N lower machines of the ith single machine in turn and record the inspection results. When all N lower machines are checked, the BIT terminal sends a shutdown command through the bus to shut down the ith single machine. The value of i is increased by 1. If i≤M, return to step a) and proceed to the inspection process of the next single machine. If i＞M, end.

Assuming that the initial value of j is 1, the workflow for checking all N lower machines of the i-th single machine is as follows:

a) The BIT terminal sends a power-on command to the jth slave computer of the i-th stand-alone machine through the bus, waiting for the slave computer of the stand-alone machine to be powered on and start running;

b) The telemetry information of the jth lower computer of the ith single machine is collected by the ith single machine and transmitted to the BIT terminal through the main bus;

c) The BIT terminal obtains the telemetry package of the jth slave computer of the i-th single machine from the telemetry information, parses the power-on status of the jth slave computer of the i-th single machine, and the working status information after power-on, and compares it with the preset judgment range. If it is within the judgment range, it goes to step d); if it is not within the judgment range, it is determined that the working status of the jth slave computer is abnormal, records the error information, and goes to step d);

d) Add 1 to the value of j. If j≤N, jump to step a) and check the next lower computer. If j>N, end.

5. Test results summary

The BIT terminal sends the health check status of all satellite units to the BIT test host computer on the ground through the LAN using a predetermined protocol. The BIT test host computer generates a report based on the health check results of the units, pops up a prompt box for users to browse, and stores the results in the database. The result reporting and report generation are all automated.

When performing a quick self-test, the BIT terminal also uploads the original data of the satellite bus to the BIT test host computer, which performs database storage operations on the original bus records, which can be used as a basis for fault analysis and troubleshooting, and for detailed troubleshooting and analysis afterwards.

6. Satellite and ground equipment status recovery

On the BIT test host computer, power-off commands are sent to the measurement and control system, satellite service system and power controller in turn to restore the satellite's status; after the satellite is powered off, the ground test equipment is powered off.

The following is further described in conjunction with specific embodiments:

Example:

1. The self-test system is connected to the satellite, the self-test system is powered on, and the state of the BIT terminal is set to be in standby state;

2. Write test cases, covering the 5 stand-alone machines on the satellite bus. The main and backup buses of each stand-alone bus are A bus and B bus respectively; download the test cases from the BIT test host computer to the BIT terminal via LAN;

3. The ground power supply voltage is 100V, the power supply current is 10A, and the self-status setting is completed; the satellite is powered on through remote control commands, the power controller, measurement and control, and satellite service systems are powered on, and it is confirmed that the satellite's telemetry information can be obtained through telemetry remote control of the ground equipment;

4. The BIT terminal sends command 00120 to turn on the power of the attitude and track control computer. After waiting for 3 seconds, the attitude and track control computer is powered on and the software is running. At this time, the attitude and track control defaults to working as A bus;

5. The BIT terminal obtains all telemetry packets on the satellite through the main bus, and obtains the attitude and orbit control computer's own working status information package PK61 from it, obtains the +5V power supply voltage information ZK2100 from PK61, and decodes the physical quantity of ZK2100 as 4.89V. The BIT terminal compares 4.89V with the pre-downloaded ZK2100 power-on judgment range of 4.5V to 5.5V to confirm that the attitude and orbit control computer is powered on normally;

6. The BIT terminal sends bus instruction 56012 to switch the bus of the attitude and orbit control computer to the B bus, obtain telemetry from the B bus, filter out the PK61 package, obtain the bus working status information ZK3010 from the PK61 package, and confirm that the bus duty status is the B bus; after the above information is correct, the BIT terminal sends a command to switch the bus to the A bus;

7. The attitude and orbit control lower computer contains sensors and actuators, among which the sensors include gyroscopes and star sensors. The BIT terminal sends instructions to the gyroscope circuit box through the attitude and orbit control computer, turning on the four gyroscopes in turn. The power-on status of the four gyroscopes obtained through the bus is all 1, indicating that the power is normal. The steady-state working current of the four gyroscopes obtained through the bus is 0.14A, 0.13A, 0.02A and 0.12A.

8. The BIT terminal compares the above currents with the pre-downloaded test cases. The currents of gyroscopes 1, 2, and 4 are all within the normal range of 0.1A to 0.15A. The current of gyroscope 3 exceeds the judgment range, and it is determined that gyroscope 3 is working abnormally. The BIT terminal records the abnormal working information locally and continues to check other lower computers of attitude and orbit control.

9. Repeat the above process to complete the health status check of the load business unit, platform business unit and other single machines and lower machines, and record the abnormal items in the check;

10. The BIT terminal completes all the self-test processes of the single machine and the lower machine, and feeds back the test results to the BIT test host computer through LAN. The BIT test host computer pops up the test abnormality information "Gyro 3 steady-state current exceeds the standard" and transfers it to manual processing;

11. After the results are manually confirmed, the BIT test host computer automatically implements the satellite and ground power-off process to complete the entire satellite rapid self-test process.

The present invention proposes a satellite rapid self-test system and method based on an in-satellite self-test device, the system comprising a BIT terminal, a BIT test host computer, a master control server, telemetry and remote control ground equipment, and a ground power supply; the BIT terminal is placed inside the satellite body, and is connected to the BIT test host computer via a LAN. After receiving a satellite self-test process start instruction sent by the BIT test host computer, the health status of the satellite system unit and its subordinate computers are checked according to the test cases pre-injected by the BIT test host computer, and the inspection results are uploaded to the BIT test host computer via a LAN. The present invention replaces the traditional method of mainly relying on external ground test equipment. Compared with traditional external test equipment, the volume is greatly reduced, the operation is simple and convenient, the execution speed is faster, and the satellite health status self-check can be realized.

The contents not described in detail in the specification of the present invention belong to the well-known technologies of professionals in the field.

Claims (10)

1. A satellite rapid self-test system based on an intra-satellite self-test device is characterized in that: the system comprises a BIT terminal, a BIT test upper computer, a master control server, telemetering and remote control ground equipment and a ground power supply; the BIT terminal is placed in the satellite body; wherein:

BIT terminal: the method comprises the steps that the satellite system single machine and a lower computer thereof are subjected to health state inspection according to a test case pre-injected by the BIT upper computer after receiving a satellite self-checking flow starting instruction sent by the BIT upper computer through connection of a LAN and a satellite, and a satellite health state inspection result is uploaded to the BIT upper computer through the LAN;

BIT test upper computer: the system is connected with a ground power supply through a LAN and a BIT terminal, a master control server and remote control ground equipment; injecting test cases into the BIT terminal, sending a satellite self-checking flow starting instruction, and acquiring a satellite health state checking result uploaded by the BIT terminal; a power-on instruction of the self-test system and a satellite power-on remote control instruction are sent to a ground power supply; transmitting satellite measurement and control and satellite service system power-up and state setting instructions to the telemetering and remote control ground equipment;

the master control server: the network control is used for controlling each device except the BIT terminal of the self-test system;

telemetry and remote control of surface equipment: the satellite measurement and control and satellite system power-up and state setting instructions sent by the BIT test upper computer are used for powering up the satellite measurement and control and satellite system and setting states through connection of the special cable and the satellite measurement and control and satellite system;

ground power supply: and after receiving a power-on instruction of the self-test system and a power-on remote control instruction of the satellite, which are sent by the BIT test upper computer, respectively supplying power to the self-test system and the satellite.

2. The satellite rapid self-test system based on the intra-satellite self-test device according to claim 1, wherein: bus types supported by BIT terminals include 1553B, CAN and RS422 satellite buses.

3. The satellite rapid self-test system based on the intra-satellite self-test device according to claim 1, wherein: the BIT terminals are fixed inside the satellite by mechanical connections and move with the satellite during the satellite ground test site transition phase.

4. A self-test method of a satellite rapid self-test system based on an intra-satellite self-test device according to any one of claims 1 to 3, characterized by comprising:

step one, completing connection between a self-test system and a satellite system;

Step two, supplying power to the self-test system, checking whether the working condition of the self-test system is normal, and entering step three after the working condition is normal;

Step three, the BIT test upper computer injects test cases into the BIT terminal in the satellite;

Step four, the BIT test upper computer controls a ground power supply to supply power for the self-test system and the satellite; controlling telemetry and remote control ground equipment to power up and set states of a satellite measurement and control system and a satellite service system; if the working conditions of the self-test system and the remote control telemetry channel of the satellite are normal, the BIT test upper computer sends a satellite self-test flow starting instruction to the BIT terminal;

Step five, the BIT terminal sequentially sends test instructions to the satellite system single machine and the lower computer thereof through the bus according to the injected test cases, and receives and interprets telemetry data fed back by the satellite system single machine and the lower computer thereof;

Step six, uploading the interpretation result to a BIT test upper computer through LAN by the BIT terminal for manual review and subsequent processing; the interpretation result is a satellite health state checking result;

and step seven, carrying out satellite system outage and ground equipment state recovery.

5. The self-test method of the satellite rapid self-test system based on the intra-satellite self-test device according to claim 4, wherein the method comprises the following steps: in the fourth step, the BIT test upper computer sends a test instruction to the satellite through the BIT terminal, and if the telemetry information of the satellite can be received and analyzed, the working conditions of the self-test system and the remote control telemetry channel of the satellite are considered to be normal.

6. The self-test method of the satellite rapid self-test system based on the intra-satellite self-test device according to claim 4, wherein the method comprises the following steps: and in the fifth step, the BIT terminal directly grabs telemetry data from the satellite bus.

7. The self-test method of the satellite rapid self-test system based on the intra-satellite self-test device according to claim 4, wherein the method comprises the following steps: the method is characterized in that the single machine is assumed to be mounted on a main bus of a satellite system, wherein the ith single machine is provided with N lower computers, the initial value of i is 1, and the working flow of the fifth step is as follows:

a) The BIT terminal sends a power-on instruction to the ith stand-alone machine;

b) The BIT terminal waits for the single machine to be powered on and starts to operate, and the single machine works on a main bus by default when powered on;

c) The BIT terminal acquires a telemetry packet of the ith stand-alone machine through a main bus and analyzes the power supply voltage and related telemetry information of the telemetry packet;

d) The BIT terminal judges the acquired telemetry information of the ith stand-alone according to the read range of the pre-written telemetry information of the ith stand-alone, if the telemetry information of the ith stand-alone is not in the read range, the working state of the ith stand-alone is judged to be abnormal, error information is recorded, the BIT terminal sends a closing instruction through a bus to close the ith stand-alone, the i value is added with 1, if i is less than or equal to M, the next stand-alone is returned to the step a), the next stand-alone checking flow is carried out, and if i is more than M, the next stand-alone checking flow is ended; if the telemetry information of the ith stand-alone is in the interpretation range, entering a step e);

e) The BIT terminal sends an instruction through a bus, and the i-th stand-alone is switched from a main bus to a standby bus;

The BIT terminal acquires the telemetry packet information of the ith stand-alone machine through the standby bus, if the telemetry packet information of the ith stand-alone machine can be acquired through the standby bus, the standby bus of the ith stand-alone machine is indicated to work normally, and the BIT terminal sends an instruction to switch the ith stand-alone machine to the main bus to enter the step f); if the BIT terminal can not acquire the telemetry packet information of the ith stand-alone from the standby bus, the BIT terminal indicates that the standby bus of the ith stand-alone has faults, records error information, sends a closing instruction through the bus, closes the ith stand-alone, adds 1 to the i value, returns to the step a if the i is less than or equal to M,

Performing the next single machine checking flow, and ending if i is more than M;

f) And (3) sequentially checking all N lower computers of the ith single machine, recording checking results, sending a closing instruction by the BIT terminal through a bus after all the N lower computers are checked, closing the ith single machine, adding 1 to the i value, returning to the step a if i is less than or equal to M, and performing the checking flow of the next single machine, and ending if i is more than M.

8. The self-test method of the satellite rapid self-test system based on the intra-satellite self-test device according to claim 7, wherein the method comprises the following steps: assuming that the initial value of j is 1, the working flow for checking all N lower computers of the ith single machine is as follows:

a) The BIT terminal sends a power-on instruction of a j-th lower computer of an i-th stand-alone machine through a bus, waits for the lower computer to be powered on and starts running;

b) The remote measurement information of the jth lower computer of the ith stand-alone machine is collected by the ith stand-alone machine and is transmitted to the BIT terminal through a main bus;

c) The BIT terminal acquires a telemetry packet of the j-th lower computer of the i-th single machine from telemetry information, analyzes the power-on state of the j-th lower computer of the i-th single machine and working state information after power-on, compares the working state information with a preset interpretation range, and enters step d if the working state information is within the interpretation range; if the operation state of the j-th lower computer is not in the interpretation range, judging that the operation state of the j-th lower computer is abnormal, recording error information, and entering the step d);

d) And (c) adding 1 to the value of j, if j is less than or equal to N, jumping to the step a), checking the next lower computer, and if j is more than N, ending.

9. The self-test method of the satellite rapid self-test system based on the intra-satellite self-test device according to claim 4, wherein the method comprises the following steps: in the sixth step, the BIT terminal uploads the telemetry data to the BIT test upper computer for storage when performing the self-test, and the telemetry data is used as a basis for fault analysis and investigation.

10. The self-test method of the satellite rapid self-test system based on the intra-satellite self-test device according to claim 4, wherein the method comprises the following steps: in the seventh step, the BIT test upper computer sends a satellite measurement and control and satellite system outage instruction to the telemetry and remote control ground equipment, and sends a satellite power supply controller outage instruction to the ground power supply to complete satellite outage; and after the satellite is powered off, the power off of the self-test system is completed.