CN115001612B - Satellite rapid self-test system and method based on intra-satellite self-test device - Google Patents
Satellite rapid self-test system and method based on intra-satellite self-test device Download PDFInfo
- Publication number
- CN115001612B CN115001612B CN202210406673.1A CN202210406673A CN115001612B CN 115001612 B CN115001612 B CN 115001612B CN 202210406673 A CN202210406673 A CN 202210406673A CN 115001612 B CN115001612 B CN 115001612B
- Authority
- CN
- China
- Prior art keywords
- satellite
- test
- self
- bit
- alone
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 213
- 238000000034 method Methods 0.000 title claims description 20
- 238000005259 measurement Methods 0.000 claims abstract description 37
- 230000036541 health Effects 0.000 claims abstract description 22
- 238000007689 inspection Methods 0.000 claims abstract description 13
- 238000010998 test method Methods 0.000 claims abstract description 12
- 230000002159 abnormal effect Effects 0.000 claims description 9
- FGUUSXIOTUKUDN-IBGZPJMESA-N C1(=CC=CC=C1)N1C2=C(NC([C@H](C1)NC=1OC(=NN=1)C1=CC=CC=C1)=O)C=CC=C2 Chemical compound C1(=CC=CC=C1)N1C2=C(NC([C@H](C1)NC=1OC(=NN=1)C1=CC=CC=C1)=O)C=CC=C2 FGUUSXIOTUKUDN-IBGZPJMESA-N 0.000 claims description 3
- 238000004458 analytical method Methods 0.000 claims description 3
- 238000011835 investigation Methods 0.000 claims description 3
- 230000009191 jumping Effects 0.000 claims description 3
- 238000011084 recovery Methods 0.000 claims description 3
- 238000003860 storage Methods 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 238000012545 processing Methods 0.000 claims description 2
- 238000012552 review Methods 0.000 claims description 2
- 238000001514 detection method Methods 0.000 abstract description 4
- 230000003862 health status Effects 0.000 abstract description 3
- 230000008569 process Effects 0.000 description 5
- 238000009826 distribution Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000006855 networking Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000005856 abnormality Effects 0.000 description 1
- 238000010923 batch production Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B17/00—Monitoring; Testing
- H04B17/40—Monitoring; Testing of relay systems
Landscapes
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Monitoring And Testing Of Transmission In General (AREA)
- Radio Relay Systems (AREA)
Abstract
The invention provides a satellite rapid self-test system and a satellite rapid self-test method based on an intra-satellite self-test device, wherein the system comprises a BIT (Built-in-test) terminal, a BIT test upper computer, a master control server, remote measurement and control ground equipment and a ground power supply; the BIT terminal is arranged in a satellite body and is connected with the BIT test upper computer through a Local Area Network (LAN), after receiving a satellite self-checking flow starting instruction sent by the BIT test upper computer, the BIT test upper computer carries out health status inspection on the satellite system single machine and a lower computer thereof according to a pre-injected test case of the BIT test upper computer, and the inspection result is uploaded to the BIT test upper computer through the LAN. Compared with the traditional external test equipment, the invention has the advantages of greatly reduced volume, simple and convenient operation, faster execution speed and capability of realizing the self-detection of the satellite health state.
Description
Technical Field
The invention relates to a satellite rapid self-test system and method based on an intra-satellite self-test device, and belongs to the field of spacecraft ground test.
Background
Satellite ground testing refers to the complete inspection of the various components of the satellite, including software and hardware systems, by test equipment on the ground to ensure that the satellite is operating in orbit normally and stably after being launched. The current 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 with expected results, all test procedures being completed on ground test equipment external to the satellite.
At present, a large number of ground equipment is needed in ground test of a large satellite, wherein 6-10 computers are needed, and special test equipment comprises power supply and distribution, remote sensing and control system test equipment. The equipment is large in size, inconvenient to move, different in operation method and inconvenient to maintain. Especially, as the satellite functions become more and more complex, the number of test cables connected between the satellite and the ground in the ground test process is large, the test cables are distributed around the satellite, and the test cables need to be plugged and unplugged when the satellite is switched from one stage to another stage, so that the process is time-consuming and labor-consuming, and the test cable state setting needs more time. In addition, the current ground test sets up the satellite through the measurement and control channel and gathers the telemetering measurement and control channel, receive the restriction of measurement and control channel transmission rate, influence on the test efficiency greatly.
The satellite industry is developed towards the directions of higher and higher technical state complexity and larger satellite networking scale, and ground test efficiency becomes a bottleneck of the satellite industry, especially large-scale networking satellite ground manufacturing. The traditional mode of satellite testing by satellite star external testing equipment is increasingly in conflict with the ever-increasing task demands.
Disclosure of Invention
The invention solves the technical problems that: the satellite rapid self-testing system and method based on the intra-satellite self-checking BIT terminal device are provided to overcome the defects of the prior art, replace the traditional EGSE to finish the health state checking of a single satellite and a lower computer thereof, reduce the number, the volume and the satellite-ground connection of testing equipment, improve the testing speed, greatly reduce the cost and the personnel requirement of the testing equipment and adapt to the development mode of the future batch production satellite.
The solution of the invention is as follows:
a satellite rapid self-test system based on an intra-satellite self-test device comprises a BIT terminal, a BIT test upper computer, a master control server, remote-measuring and remote-controlling 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; bus types supported by the BIT terminal comprise 1553B, CAN and RS422 satellite buses; the BIT terminal is fixed inside the satellite through mechanical connection and moves along with the satellite during the satellite ground test site transition stage;
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.
A self-test method of a satellite rapid self-test system based on an intra-satellite self-test device comprises the following specific steps:
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; the BIT test upper computer sends a test instruction to the satellite through the BIT terminal, and if the remote measurement information of the satellite can be received and analyzed, the working conditions of the self-test system and a remote control remote measurement channel of the satellite are considered to be normal, and the BIT test upper computer sends a satellite self-checking 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 and the telemetry data to a BIT test upper computer through a 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.
Further, suppose that M units are installed on the main bus of the satellite system, wherein the i-th unit has N lower computers, the initial value of i is 1, and the working flow for checking the health state of the satellite system unit 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 cannot acquire the telemetry packet information of the ith single machine from the standby bus, indicating that the standby bus of the ith single machine has faults, recording error information by the BIT terminal, sending a closing instruction through the bus, closing the ith single machine, adding 1 to the value of i, returning to the step a) if i is less than or equal to M, and carrying out the inspection flow of the next single machine, 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.
Further, assuming that the initial value of j is 1, the workflow for checking all N lower computers of the ith stand-alone machine is as follows:
a) The BIT terminal sends a power-on instruction of a j-th lower computer of an i-th single machine through a bus, waits for the power-on of the lower computer of the single machine and starts operation;
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.
Compared with the prior art, the invention has the beneficial effects that:
(1) The BIT terminal is connected with the satellite through a bus and is connected with a ground BIT test upper computer through a LAN, and compared with the traditional external test equipment, the test cable connection and the volume of the test equipment in the satellite ground test process can be greatly reduced;
(2) The BIT terminal can be placed in a satellite body, only one network cable and one power line are connected to the outside, after one testing stage is finished, only the network cable and the power line are required to be disconnected, the connection between the BIT terminal and the satellite can be reserved, the BIT terminal moves along with the satellite during the satellite ground testing site transfer stage, and repeated plugging and unplugging of cables and transfer and debugging of ground testing equipment can be reduced;
(3) The BIT terminal and the satellite pass through the data interaction mode of the bus, which is faster than the traditional test mode by more than one order of magnitude through the measurement and control channel, and the test flow execution is obviously improved;
(4) And injecting a satellite system single machine and a self-checking test case of a lower computer into the BIT terminal through the BIT test upper computer, so as to realize customized satellite autonomous detection.
Drawings
FIG. 1 is a flow chart of a method for rapid self-testing of satellites based on an intra-satellite self-testing device;
fig. 2 is a schematic diagram of a satellite rapid self-test system based on an intra-satellite BIT terminal.
Detailed Description
The invention is described in further detail below with reference to the attached drawings and to specific embodiments:
As shown in FIG. 2, the satellite rapid self-test system based on the intra-satellite self-test device comprises a BIT terminal, a BIT test upper computer, a master control server, remote-measuring and remote-controlling ground equipment and a ground power supply; the BIT terminal is placed in a satellite body, is connected with the BIT test upper computer through the LAN, is connected with the satellite through the bus, receives a satellite self-checking flow starting instruction sent by the BIT test upper computer, and then carries out health state inspection on a satellite system single machine and a lower computer thereof according to a test case pre-injected by the BIT test upper computer, and uploads a satellite health state inspection result to the BIT test upper computer through the LAN; bus types supported by the BIT terminal comprise 1553B, CAN, RS422 and other common satellite buses, and are suitable for different satellite test requirements; the BIT terminal is designed in a miniaturized manner, is fixed inside the satellite through mechanical connection, moves along with the satellite during the satellite ground test site transition stage, and can move without disconnecting the satellite from an externally connected cable as in the conventional ground test equipment.
The BIT test upper computer is connected with the BIT terminal, the master control server, the remote-measuring and remote-controlling ground equipment and the ground power supply through the LAN, operates BIT test master control software, issues test cases and satellite self-checking flow starting instructions to the BIT terminal, and acquires satellite health state checking results 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; sending 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 is used for the network control of the self-test system equipment except the BIT terminal; the remote measurement and control ground equipment is connected with a satellite system through a special cable and measurement and control on the satellite, and the satellite and satellite system is powered on and set in state according to satellite measurement and control and satellite system powering on and state setting instructions sent by the BIT test upper computer, so that a remote measurement and control channel of the satellite and the ground is established; and after receiving a self-test system power-on instruction and a satellite power-on remote control instruction sent by the BIT test upper computer, the ground power supply supplies power to the self-test system and the satellite respectively.
The satellite products comprise a measurement and control and satellite system, a power supply controller, an attitude and orbit control computer, an executing mechanism, a sensor, a load service unit, a platform service unit, a load and platform device. The satellite measurement and control and satellite service system completes remote measurement and control of the ground equipment of the self-test system and management and maintenance of on-board data. The satellite power supply controller is used for satellite electric energy generation, storage and distribution. An attitude orbit control computer is used for attitude and orbit measurement and control of satellites during orbit. The load service unit is used for managing satellite load equipment and comprises instruction sending and telemetering acquisition, and an interface between the load equipment and the measurement and control and satellite service system is established. The platform service unit is used for managing satellite load equipment, and comprises instruction sending and telemetry acquisition, and an interface between the platform equipment and the digital management computer is established.
As shown in fig. 1, the detailed steps of a satellite rapid self-test method based on an intra-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, wherein a BIT test upper computer, a master control server and a ground power supply in the self-test system are connected by adopting a LAN, the ground power supply is connected with the satellite by a special ground test cable, and remote-control ground equipment is connected with the satellite system by a special cable and satellite measurement and control; the BIT terminal is connected with the ground BIT test upper computer through a power supply cable and a LAN; products on the satellite are connected through an on-board cable network, and the BIT terminal is accessed to a satellite bus through a bus detection port reserved by the satellite.
2. Ground test equipment status setting
The ground power supply main switch, the main control server, the power supply of the BIT test upper computer and the power supply of the BIT terminal are turned on, corresponding setting is carried out on software operated by the BIT test upper computer, and the normal operation of self-test system equipment is ensured; according to the requirements of test tasks, a BIT test upper computer is utilized to inject test cases into a BIT terminal through a LAN, and the test cases are formulated on the ground according to the states of products on satellites, connection relations, test contents and the like, and comprise the test sequence of single units on satellites, instructions sent by test, the interpretation range of expected telemetry results and the like.
3. Satellite initial state setting
The BIT test upper computer sends a power-on instruction of the self-test system to the ground power supply to complete the power supply of the self-test system; a satellite power-on remote control instruction is sent to a ground power supply, and satellite power supply is completed by controlling a satellite power supply controller; transmitting satellite measurement and control and satellite service system power-up and state setting instructions to the telemetry and remote control ground equipment, setting states, and establishing a remote control telemetry channel of satellites and the ground; sending a test instruction to the satellite through the BIT terminal, and if the telemetry information of the satellite can be received and analyzed, enabling the self-test system and a remote control telemetry channel of the satellite to work normally; and the BIT test upper computer sends a satellite self-checking flow starting instruction to the BIT terminal.
4. Starting the self-checking flow
After receiving a self-checking starting instruction sent by a BIT test upper computer, the BIT terminal carries out satellite health state self-checking according to a pre-injected test case, and single machine health state checking comprises an on-off state, key characteristic parameters and a bus communication function of the single machine, and single machine lower computer health state checking comprises important parameter information of the power-on state of the lower computer and single machine work;
The satellite health status self-test is carried out according to preset steps, and each step has corresponding instruction sending and corresponding telemetry interpretation, and all measurable single machines and lower computers on the satellite need to be covered. Assuming that M units are arranged on a main bus of the satellite system, wherein the ith unit is provided with N lower computers, the initial value of i is 1, and the working flow for checking the health state of the satellite system unit 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 cannot acquire the telemetry packet information of the ith single machine from the standby bus, indicating that the standby bus of the ith single machine has faults, recording error information by the BIT terminal, sending a closing instruction through the bus, closing the ith single machine, adding 1 to the value of i, returning to the step a) if i is less than or equal to M, and carrying out the inspection flow of the next single machine, 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.
The work flow for checking all N lower computers of the ith single machine is as follows, assuming that the initial value of j is 1:
a) The BIT terminal sends a power-on instruction of a j-th lower computer of an i-th single machine through a bus, waits for the power-on of the lower computer of the single machine and starts operation;
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.
5. Summarizing test results
The BIT terminal sends the health check state of all the single machines of the satellite to a BIT test upper computer on the ground through the LAN according to a preset protocol; the BIT test upper computer generates a report aiming at the health check result of the single machine, pops up a prompt box for a user to browse and stores the result into a database, and the report and report generation are both automatically implemented;
And the BIT terminal also uploads the original data of the satellite bus to the BIT test upper computer when performing quick self-test, and the BIT test upper computer performs database storage operation of original bus records, so that the BIT terminal can be used as a basis for fault analysis and investigation and is used for detailed investigation and analysis afterwards.
6. Satellite and ground device state recovery
On a BIT test upper computer, successively sending power-off instructions of a measurement and control system, a satellite service system and a power supply controller, and recovering the state of a satellite; and after the satellite is powered off, the ground test equipment is powered off.
Further description of specific embodiments follows:
examples:
1. The self-test system is connected with the satellite, and is powered on to set the state of the BIT terminal so as to be in a standby state;
2. Writing test cases, namely covering 5 single machines on a satellite bus, wherein the main backup buses of each single machine bus are an A bus and a B bus respectively; downloading the test cases from the BIT test upper computer to the BIT terminal through the LAN;
3. Ground power supply voltage 100V, power supply current 10A, and complete self state setting; powering up the satellite through a remote control instruction, completing the powering up of a power supply controller, measurement and control and a satellite service system, and confirming that the remote measurement information of the satellite can be obtained through remote measurement and control of ground equipment;
4. the BIT terminal sends 00120 instructions, the power supply of the attitude and orbit control computer is turned on, the attitude and orbit control computer is waited for 3s to finish powering up, the software operation is finished, and the attitude and orbit control default work is used as an A bus at the moment;
5. The BIT terminal acquires all telemetry packets on the satellite through a main bus, acquires a working state information packet PK61 of the attitude and orbit control calculation self from the telemetry packets, acquires +5V power supply voltage information ZK2100 from the PK61, and decodes the physical quantity of the ZK2100 to be 4.89V. The BIT terminal compares 4.89V with 4.5V-5.5V of a pre-downloaded ZK2100 power-on interpretation range to confirm that the power-on state of the attitude and orbit control computer is normal;
6. The BIT terminal sends a bus instruction 56012, switches the bus of the attitude and orbit control computer into a B bus, acquires telemetry from the B bus, filters PK61 packets from the B bus, acquires bus working state information ZK3010 from the PK61 packets, and confirms that the bus on duty state is the B bus; after the information is correct, the BIT terminal sends an instruction to switch the bus into an A bus;
7. The attitude and orbit control lower computer comprises a sensor and an actuating mechanism, wherein the sensor comprises a gyroscope, a star sensor and the like; the BIT terminal sends instructions to the gyro circuit box through the attitude and orbit control computer, sequentially opens 4 gyroscopes, and obtains the power-on state of the four gyroscopes to be 1 through a bus, so that the power-on state is normal; obtaining steady-state working currents of 4 gyroscopes to be 0.14A, 0.13A, 0.02A and 0.12A through a bus;
8. The BIT terminal compares the current with the pre-downloaded test case, the current of the gyroscopes 1,2 and 4 is in the normal range of 0.1A-0.15A, the current of the gyroscopes 3 exceeds the interpretation range, and the working abnormality of the gyroscopes 3 is judged; the BIT terminal records the abnormal information of the work locally and continues to check other lower computers controlled by the gesture track;
9. Repeating the above process to complete the health status check of the single machine and the lower computer such as the load service unit, the platform service unit and the like, and recording the check abnormal items;
10. The BIT terminal completes the self-test flow of all single machines and lower computers, feeds test results back to the BIT test upper computer through LAN, pops up test abnormal information 'the steady-state current of the gyroscope 3 exceeds standard', and is manually processed;
11. after the result is confirmed manually, the BIT test upper computer automatically executes the satellite and ground power-off flow to complete the whole satellite rapid self-test process.
The invention provides a satellite rapid self-test system and a satellite rapid self-test method based on an intra-satellite self-test device, wherein 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 arranged in a satellite star and is connected with the BIT test upper computer through the LAN, after receiving a satellite self-checking flow starting instruction sent by the BIT test upper computer, the BIT test upper computer carries out health state inspection on the satellite system single machine and the lower computer thereof according to the pre-injected test cases of the BIT test upper computer, and the inspection result is uploaded to the BIT test upper computer through the LAN. Compared with the traditional external test equipment, the invention has the advantages of greatly reduced volume, simple and convenient operation, faster execution speed and capability of realizing the self-detection of the satellite health state.
What is not described in detail in the present specification is a known technology to those skilled in the art.
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210406673.1A CN115001612B (en) | 2022-04-18 | 2022-04-18 | Satellite rapid self-test system and method based on intra-satellite self-test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210406673.1A CN115001612B (en) | 2022-04-18 | 2022-04-18 | Satellite rapid self-test system and method based on intra-satellite self-test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115001612A CN115001612A (en) | 2022-09-02 |
| CN115001612B true CN115001612B (en) | 2024-05-31 |
Family
ID=83024200
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210406673.1A Active CN115001612B (en) | 2022-04-18 | 2022-04-18 | Satellite rapid self-test system and method based on intra-satellite self-test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115001612B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107612610A (en) * | 2017-08-31 | 2018-01-19 | 航天东方红卫星有限公司 | A kind of spaceborne TT＆C Transponder self-testing system and method based on slave computer |
| CN112564772A (en) * | 2020-12-03 | 2021-03-26 | 中国空间技术研究院 | Satellite data acquisition system |
| CN113885351A (en) * | 2021-03-18 | 2022-01-04 | 长沙天仪空间科技研究院有限公司 | Simulation test equipment and method for satellite simulation test |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9720042B2 (en) * | 2014-05-21 | 2017-08-01 | The Boeing Company | Built-in test for satellite digital payload verification |
-
2022
- 2022-04-18 CN CN202210406673.1A patent/CN115001612B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107612610A (en) * | 2017-08-31 | 2018-01-19 | 航天东方红卫星有限公司 | A kind of spaceborne TT＆C Transponder self-testing system and method based on slave computer |
| CN112564772A (en) * | 2020-12-03 | 2021-03-26 | 中国空间技术研究院 | Satellite data acquisition system |
| CN113885351A (en) * | 2021-03-18 | 2022-01-04 | 长沙天仪空间科技研究院有限公司 | Simulation test equipment and method for satellite simulation test |
Non-Patent Citations (1)
| Title |
|---|
| 一种小卫星在轨自主测试方法;张德全 等;航天器工程(第02期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115001612A (en) | 2022-09-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107769836B (en) | Satellite universal automatic test platform and data interaction method thereof | |
| CN1982863B (en) | Universal micro-satellite comprehensive testing platform based on PXI system | |
| CN101628628A (en) | Self-correcting redundancy switching mechanism for spacecraft system and verification method thereof | |
| CN115333988B (en) | Test method, system and equipment for rocket interstage communication signals | |
| KR100949814B1 (en) | Monitoring system for totally remotely managing multiple uninterrupted power supplys | |
| CN101286053A (en) | Method and apparatus to facilitate logic control and interface communication | |
| CN112925705B (en) | Unmanned-duty-based carrier rocket flight software acceptance method and system | |
| CN110727255B (en) | Whole vehicle controller software upgrading test system and vehicle | |
| CN115001612B (en) | Satellite rapid self-test system and method based on intra-satellite self-test device | |
| CN114415572A (en) | Integrated test, launch and control method and equipment for liquid carrier rocket | |
| CN106612215A (en) | Integrated remote detection device and method based on Ethernet | |
| CN101726691B (en) | Method of inspecting the integrity of an avionics system, and an inspection device for implementing said method | |
| JPH01156896A (en) | Fault information collecting/processing system | |
| CN116263595A (en) | Universal automatic test platform for satellite single machine environment test and control method thereof | |
| CN210400199U (en) | Remote control device for ground launch support system of carrier rocket | |
| CN112165162B (en) | Ground power supply control system of carrier rocket | |
| CN115220945A (en) | Raspberry pie-based vehicle detection device and method, vehicle and storage medium | |
| CN114090432A (en) | Method, system, device, electronic equipment and storage medium for simulation test | |
| CN209930280U (en) | Network automation bus test rack | |
| CN112437265A (en) | Security monitoring network and intelligent fault processing method thereof | |
| CN118010361B (en) | Engine ground test command decision method, system, equipment and medium | |
| CN114802820B (en) | Power management control structure and method for spacecraft payload | |
| CN109462516B (en) | Dual-redundancy universal test system | |
| CN112328290B (en) | Remote updating method and system for agricultural machinery data acquisition terminal program | |
| CN107544474A (en) | A kind of nuclear power plant's relay logic processing rack experimental rig and method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |