An autonomous program-controlled system level test method

Abstract

The application discloses an autonomous program control system level test method, and proposes a solution method for the correctness, effectiveness, safety and integrity of satellite active stage operation period satellite-rocket separation program control, autonomous flight program control, synchronous orbit stage operation period machine cutting program control, and emergency program control task verification. Based on satellite 1553B bus data simulation function and automatic test, satellite program control execution process is simulated and forwarded, satellite autonomous instruction sequence during program control execution is analyzed or intercepted, satellite program control process safety risk hidden danger is guaranteed, and effective verification of satellite autonomous program control function and comprehensive interpretation of instruction telemetry are realized.

Description

Technical Field

[0001] This invention relates to an autonomous programmable control system-level testing method, belonging to the field of spacecraft ground testing. Background Technology

[0002] Satellite ground testing refers to a comprehensive inspection of all components of a satellite, including both software and hardware systems, using ground-based testing equipment to ensure its normal and stable operation in orbit after launch. During the active phase of operation after launch, the satellite's operational software autonomously performs programmed tasks such as satellite-launcher separation and active phase flight, completing tasks including propulsion system venting, tracking and orbit determination, pyrotechnic device detonation, deployment of deployable accessories, gas and liquid circuit interruption, geostationary acquisition, satellite attitude adjustment at different orbital positions, and orbital maneuvers. System-level testing addresses the above-mentioned autonomous programming requirements of the satellite software and the overall hardware status of the satellite, completing the construction and verification of the ground testing system.

[0003] Currently, due to the complexity and diversity of autonomous programmable functions and the high degree of integration of software and hardware functions with various satellite subsystems, the existing verification methods in the system-level ground testing phase rely on a large number of ground equipment. This results in problems such as numerous ground equipment, software, and cables, complex manual operation, incomplete test coverage, low productization of the test process, and low test efficiency. At the same time, the high coupling between the onboard equipment and software states leads to control risks and hidden dangers in key onboard components. How to realistically reproduce the satellite's on-orbit operating conditions while reducing safety risks and verifying the satellite's autonomous programmable functions more comprehensively and efficiently is an urgent problem to be solved. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose an autonomous programmable control system-level testing method. By setting up a ground test sequence, the satellite programmable control execution process is simulated and forwarded, thereby realizing the effective verification of the satellite's autonomous programmable control function and the comprehensive interpretation of command telemetry.

[0005] The technical solution of this invention is:

[0006] An autonomous programmable control system-level testing method includes:

[0007] Based on the testing phase and the functions of the satellite under test, key command codes, command numbers, and corresponding simulation telemetry configurations are set for key units in the ground testing equipment, and a test sequence containing target RT telemetry parameters and simulation data is compiled.

[0008] The ground test equipment is connected in series between the satellite's 1553B bus and the target RT. After powering on the ground test equipment and the satellite service system, the ground test equipment runs the test sequence while periodically acquiring the data transmitted by the target RT, receiving the target RT's pending instructions on the 1553B bus in real time, and performing inversion. Based on the above data and instructions, telemetry simulation is performed before forwarding or direct transparent forwarding.

[0009] The test results of the test sequence are used to determine the correctness of the programmable logic and execution effect in satellite telemetry, and the inversion results recorded by the ground test equipment are used to determine the correctness of the sequence of satellite programmable instruction strings and the content of instruction codewords.

[0010] Preferably, the step of performing telemetry simulation or transparent forwarding on the target RT based on the above data and instructions includes:

[0011] If no receiving instruction is received from the target RT on the 1553B bus in the current cycle, it is determined whether simulation is required based on the simulation data content of the test sequence. If simulation is required, the simulation result is written into the target RT transmission data in the current cycle, and the data is forwarded to the satellite 1553B bus in the next cycle. If simulation is not required, the target RT transmission data is transparently forwarded to the 1553B bus in the current cycle.

[0012] If a target RT receives a command to be received on the 1553B bus within the current cycle, the command number is inverted to obtain the codeword inversion code. It is then determined whether the codeword inversion code is a critical command codeword. If it is a critical command codeword, it is intercepted, and simulation is performed according to the simulation data content corresponding to the pre-configured critical command. The simulation result is written into the target RT's data transmission data for the current cycle, and the data is then forwarded to the satellite 1553B bus in the next cycle. Otherwise, the received target RT command to be received is transparently forwarded to the target RT.

[0013] Preferably, a simulation is performed, and the simulation results are written into the current period target RT transmission data, including:

[0014] Obtain parameter codes from simulation data content, and query the location and processing method corresponding to the current satellite parameter codes from the satellite basic database;

[0015] If the processing method does not contain multi-level variables, the physical quantities in the test sequence simulation data are solved using the processing method to obtain the simulation source code.

[0016] The simulation source code is written as the simulation result to the location where the target RT transmits data in the current cycle.

[0017] Preferably, the parameter code is obtained based on the simulation data content, and the location and processing method corresponding to the current satellite parameter code are queried from the satellite basic database; if the processing method is a special processing method with multi-level variables, the special processing method is formatted and defined as three valid units: the first unit is the processing formula, the second unit is the coefficient referenced by the processing formula, and the third unit is the relevant variable of the processing formula.

[0018] Substituting the physical quantities from the test sequence simulation data into the above definitions, if the third cell is empty, then substitute the values ​​from the second cell into the formula of the first cell to obtain the specific values ​​of the single-level variables; if the third cell is not empty, then use the solution formula to obtain V. h Value, then V h Substitute these values ​​into the first unit formula to obtain the special values ​​of the multi-level variables;

[0019] The special value obtained above is used as the simulation result and written into the position where the target RT transmits data in the current cycle.

[0020] Preferably, the received target RT command to be received on the 1553B bus is inverted, specifically by performing codeword comparison processing to identify the command content information.

[0021] Preferably, all obtained inversion results are processed by message printing and archiving to determine the correctness of the satellite programmable instruction string sequence and instruction codeword content.

[0022] Preferably, the period for acquiring the target RT transmission data is set to 448ms.

[0023] Preferably, the key instruction is an instruction that cannot be sent from the satellite programmable instruction string.

[0024] Preferably, based on the 1553B bus data format, the RT address in the data transmitted on the bus is determined. If it is the target RT address, the data is received, and this data is the target RT instruction to be received.

[0025] The advantages of this invention compared to the prior art are:

[0026] (1) This invention proposes a satellite 1553B bus data simulation test method, which can verify various software functions in satellite program control functions such as satellite-rocket separation program control, autonomous flight program control, aircraft switching program control, and emergency program control, and has universality among different satellite platforms, models, and software function differences.

[0027] (2) This invention proposes a special value calculation method, which solves the problem of calculation and simulation of special telemetry parameters such as variable thermistors, and realizes telemetry data processing under multi-level variables.

[0028] (3) This invention proposes a method for intercepting critical instructions. By receiving the instruction codeword sent to the target RT, comparing, identifying and intercepting the critical instructions, the risk of critical components that may be caused by the system-level autonomous programmable instruction sequence can be effectively controlled.

[0029] (4) This invention can simultaneously simulate and process data of multiple products on a satellite, and can more realistically simulate on-orbit conditions. It can solve the problem of satellite technical status changes affecting test integrity and untestability in various stages of comprehensive testing. It can still realize the functional verification of target software when the products on the satellite under test are not installed in place. It can move the testing time forward, expose design problems in advance, and improve feasibility and test comprehensiveness. Attached Figure Description

[0030] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0031] Figure 1 This is a flowchart illustrating the satellite autonomous programmable control system-level testing method according to an embodiment of the present invention.

[0032] Figure 2 This is a diagram showing the connection relationship between the satellite and ground systems according to an embodiment of the present invention. Detailed Implementation

[0033] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the disclosure to those skilled in the art. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0034] This invention proposes a test method for autonomous programmable control systems, including:

[0035] Preparations before testing:

[0036] (1) Based on the testing phase and the functions of the satellite under test, confirm whether the relevant key units are installed.

[0037] (2) During different stages of system-level testing, changes in the installation status of satellite products and the functions of the satellite under test increase the critical risk points of on-board products, necessitating the addition of corresponding critical commands and status control measures. Based on the corresponding critical units, commands that cannot be sent in the satellite programmable command string are defined as critical commands, and the critical command codewords, command numbers, and their corresponding simulation telemetry are configured in the test equipment. For example, after the solar panel product is installed, the critical risk point is that the SADA rotation causes damage to the SADA product; therefore, risk control measures for the SADA power-on command must be added at the corresponding stage.

[0038] (3) Determine the telemetry parameters and simulation data content of the satellite product to be simulated based on the functions of the satellite under test, and form a test sequence.

[0039] (4) According to Figure 2 Connect the ground test equipment in series between the satellite's 1553B bus and the target RT, confirm that the satellite-to-ground cable connection is correct, and then power on the ground test equipment.

[0040] Test steps:

[0041] (5) Power on the satellite service system and perform satellite initialization settings;

[0042] (6) Run the test sequence through the test software. The simulation data content in the test sequence is used to perform telemetry simulation or transparent forwarding on the target RT. At the same time, the test software receives and processes the instruction data sent to the RT by the 1553B bus in real time.

[0043] More specifically, Figure 1 This is a data flow diagram for 1553B bus data simulation and processing. The specific implementation steps are as follows:

[0044] (6.1) The ground test equipment acquires data in a format that conforms to the 1553B bus packet telemetry protocol, which includes RT address, sub-address, data length, and data source code;

[0045] (6.2) Extract and judge the data in step (6.1), extract the data of the target RT address, and judge whether the data is (6.3) data sent by the target RT or (6.10) data received by the RT on the 1553B bus according to the sub-address;

[0046] (6.3) Obtain the data sent by the target RT. The data update cycle of one source code is 448ms. In this step, the data source code sent by the target RT is received in real time and archived.

[0047] (6.4) Determine whether simulation is required. If simulation data content sent by the test sequence is received within the current data update cycle, proceed to step (6.5); otherwise, proceed to step (6.9).

[0048] (6.5) Processing method analysis: The test software obtains satellite parameter codes, location information, and processing method information from the satellite basic database. Based on the parameter codes of the data content to be simulated in step (6.4), it searches for the corresponding telemetry location and processing method in the acquired target RT transmission data.

[0049] (6.6) Special value judgment: Based on the processing method, determine whether the current simulation parameters use a special processing method with multiple levels of variables, such as variable thermistor temperature telemetry, etc. If the judgment result is yes, proceed to step (6.7); otherwise, proceed to step (6.8).

[0050] (6.7) Calculation of special values ​​for multi-level variables: The test software defines the processing method of the current telemetry parameters in the basic database in a formatted manner. The definition is divided into three valid units: the first unit is the processing formula, the second unit is the coefficients referenced by the processing formula, and the third unit is the related variables of the processing formula. During processing, if the third unit is empty, the value in the second unit is substituted into the formula in the first unit to obtain the special value of the single-level variable; if the third unit is not empty, the solution formula is used to obtain V. h Value, then V h Substitute these values ​​into the first unit formula to obtain the special values ​​of the multi-level variables;

[0051] The solution formula is:

[0052]

[0053] In the formula, T0 is a special value of a single-level variable of the physical quantity to be simulated; variables i and j are the relevant variables of the third unit; R0 is the coefficient of the processing formula in the second unit; and A is the calibration voltage constant.

[0054] (6.8) Modify RT data. The physical quantities in the test sequence simulation data are processed by source code calculation according to the processing method. After calculation, the simulation source code is obtained. The simulation source code is written into the target RT data of the current period. The simulation data of special values ​​is directly written into the target RT data of the current period, overwriting the actual received target RT data. This step can complete the modification of single, multiple or all target RT data according to the test needs. The processing time is less than 20ms. The modification process is archived.

[0055] (6.9) Forward RT data and send all RT data to the satellite 1553B bus in the next data cycle.

[0056] (6.10) Obtain the data received by the RT on the 1553B bus. The target RT receives the instruction codewords sent by the 1553B bus from time to time. This step is in real-time reception state.

[0057] (6.11) Instruction codeword comparison: Perform codeword comparison processing on the instruction source code information, identify instruction content information, and perform instruction number inversion, message printing and archiving processing on all received instructions for subsequent test result interpretation.

[0058] (6.12) Determine whether it is a critical instruction based on the comparison result of step (6.11). If the codeword inversion codeword is a critical instruction codeword, then execute step (6.13); otherwise, execute step (6.15).

[0059] (6.13) Intercept command codewords, intercept the key commands pre-configured by the test software in step (2), and terminate the forwarding of the current codeword, thereby ensuring the safety of the satellite's key components;

[0060] (6.14) Simulate the effect of the command. Simulate the telemetry corresponding to the key command pre-configured in the test software in step (2) and proceed to step (6.5).

[0061] (6.15) Forward the RT receive command and send the RT received data to the target RT.

[0062] Data interpretation:

[0063] (7) Sufficient, effective and correct interpretation: judge the correctness of the program control logic and execution effect in satellite telemetry through the test sequence, and judge the correctness of the sequence of satellite program control command string and the content of command codeword through the inversion results recorded by the ground test software, so as to ensure that the test is sufficient, effective and correct.

[0064] This invention is applicable to satellite ground testing scenarios for 1553B bus packet telemetry, improving versatility, security, and testing comprehensiveness. Currently, this method has been preliminarily applied to the programmable function testing in the integrated testing of 1553B bus packet telemetry satellites in the communication series, meeting the requirements for satellite programmable function verification.

[0065] The following is a further explanation with reference to specific embodiments:

[0066] During the test preparation phase, confirm that the test equipment and satellite are correctly connected, confirm that the key single unit solar array of the satellite in the current stage has been installed, and that the target RT is the actuator. In the test software, define the SADA rotation command as the key command, and configure the command and its corresponding solar array deployment position indication, etc., for simulation telemetry.

[0067] Edit the test sequence. The function under test is the star-rocket separation programmable test. Before the solar array rotates, the solar array damping temperature must meet the condition. Enter the data content in the test sequence, which is that the solar array damping temperature is set to 50℃.

[0068] The ground testing equipment is powered on and working normally.

[0069] The satellite service system is powered on and initialized normally.

[0070] The test sequence was started, which included pre-launch status settings for satellite energy, attitude and orbit control, integrated electronics, and thermal control systems; orbital phase settings; activation of pyrotechnic detonation pathways and monitoring of detonation current; and collection of autonomous programmable telemetry parameters.

[0071] The test sequence calls simulation data to simulate the telemetry of solar array damping temperature T = 50℃. The test equipment starts the simulation and queries the satellite basic database to find the parameter code TN18 for the telemetry of solar array damping temperature. The position on the bus is obtained as the 64th byte of the PK13 source packet in RT5. The processing method is MF501, with a total of 6 coefficients: 7.5, 6.01, 4622.53, -86421.72, 1.25, and 3.24. A special processing method format is defined for this parameter. The three effective units are the processing formula MF501, the reference coefficients R0 = 7.5, a = -6.01, b = 4622.53, and c = -86421.72, and the multi-level variables i = 1.25 and j = 3.24. At the same time, the calibration voltage nominal value constant A = 5V and the voltage level value 0.02 are obtained from the satellite basic database.

[0072] First, substitute the above coefficients into the general thermistor formula MF501 for calculation:

[0073]

[0074] We obtain T0 = 13.477, and then substitute it into the special value formula to solve:

[0075]

[0076] Get V h =0.6, divided by the stratification value of 0.02, we get V h The source code is 1EH. The simulation source code is written into the 64th byte of the PK13 source packet in the current cycle RT5, forwarded, and the simulation is completed.

[0077] The onboard software autonomously executes the programmable instruction string, while simultaneously testing the sequence to determine the telemetry status, checking whether the programmable logic and execution are correct, and testing the software to determine whether the instruction order in the programmable instruction string is correct and whether the instruction codeword inversion result is correct.

[0078] The test software retrieves the key SADA rotation command code, and the test equipment automatically intercepts the command code. The command is prohibited from being forwarded to the actuator, and the ground parameter key command reception count is set to 1, indicating that a SADA related command code has been received. At the same time, the simulated solar array deployment position telemetry shows that it has been deployed, in order to meet the conditions required for subsequent satellite-rocket separation program control.

[0079] Perform data analysis until the test is completed;

[0080] Clear the simulation data in the test software, restore the satellite status, and power off the satellite.

[0081] The embodiments described above are merely preferred embodiments of the present invention. Ordinary variations and substitutions made by those skilled in the art within the scope of the technical solution of the present invention should be included within the protection scope of the present invention.

Claims

1. An autonomous programmatic system-level test method, characterized by, include: Based on the testing phase and the functions of the satellite under test, key command codes, command numbers, and corresponding simulation telemetry configurations are set for key units in the ground testing equipment, and a test sequence containing target RT telemetry parameters and simulation data is compiled. The ground test equipment is connected in series between the satellite's 1553B bus and the target RT. After powering on the ground test equipment and the satellite service system, the ground test equipment runs the test sequence while periodically acquiring the data transmitted by the target RT, receiving the target RT's pending instructions on the 1553B bus in real time, and performing inversion. Based on the above data and instructions, telemetry simulation is performed before forwarding or direct transparent forwarding. The test results of the test sequence are used to determine the correctness of the programmable logic and execution effect in satellite telemetry, and the inversion results recorded by the ground test equipment are used to determine the correctness of the sequence of satellite programmable instruction strings and the content of instruction codewords. The process of performing telemetry simulation or transparent forwarding on the target RT based on the aforementioned data and instructions includes: If no receiving instruction is received from the target RT on the 1553B bus in the current cycle, it is determined whether simulation is required based on the simulation data content of the test sequence. If simulation is required, the simulation result is written into the target RT transmission data in the current cycle, and the data is forwarded to the satellite 1553B bus in the next cycle. If simulation is not required, the target RT transmission data is transparently forwarded to the 1553B bus in the current cycle. If a target RT receives a command to be received on the 1553B bus within the current cycle, the command number is inverted to obtain the codeword inversion code. It is then determined whether the codeword inversion code is a critical command codeword. If it is a critical command codeword, it is intercepted, and simulation is performed according to the simulation data content corresponding to the pre-configured critical command. The simulation result is written into the target RT's data transmission data for the current cycle, and the data is then forwarded to the satellite 1553B bus in the next cycle. Otherwise, the received target RT command to be received is transparently forwarded to the target RT.

2. The autonomous system level test method of claim 1, wherein, Perform simulation and write the simulation results into the current period target RT transmission data, including: Obtain parameter codes from simulation data content, and query the location and processing method corresponding to the current satellite parameter codes from the satellite basic database; If the processing method does not contain multi-level variables, the physical quantities in the test sequence simulation data are solved using the processing method to obtain the simulation source code. The simulation source code is written as the simulation result to the location where the target RT transmits data in the current cycle.

3. The autonomous system level test method of claim 1, wherein, Obtain parameter codes from simulation data content, and query the location and processing method corresponding to the current satellite parameter codes from the satellite basic database; If the processing method is a special processing method with multi-level variables, then the special processing method is formatted as three valid units: the first unit is the processing formula, the second unit is the coefficients referenced by the processing formula, and the third unit is the related variables of the processing formula. Substitute the physical quantities in the test sequence simulation data into the above definition. If the third unit is empty, substitute the values ​​in the second unit into the formula of the first unit to obtain the special values ​​of the single-level variables. If the third unit is not empty, then use the solving formula to get value, and then put it into the first unit formula to get the special value of the multi-level variable. If the third unit is not empty, then use the solving formula to get wherein: is a single-level variable special value of the physical quantity to be simulated; variable and are related variables of the third unit; is a processing formula coefficient in the second unit; A is a calibration voltage constant; The special value obtained above is used as the simulation result and written into the position where the target RT transmits data in the current cycle.

4. The autonomous system level test method of claim 1, wherein, The received command to be received from the target RT on the 1553B bus is inverted, specifically by performing codeword comparison processing to identify the command content information.

5. The autonomous system level test method of claim 4, wherein, All inversion results are processed by message printing and archiving to determine the correctness of the satellite programmable command string sequence and command codeword content.

6. The autonomous system level test method of claim 1, wherein, The period for acquiring data transmitted by the target RT is set to 448ms.

7. The autonomous system level test method of claim 1, wherein, The key instructions are those that cannot be sent from the satellite programmable instruction string.

8. The autonomous system level test method of claim 1, wherein, Based on the 1553B bus data format, determine the RT address in the data transmitted on the bus. If it is the target RT address, then receive the data, which is the target RT instruction to be received.

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