A method of testing a missile-borne computer

Abstract

The present application relates to the technical field of launch vehicle testing, and discloses a test method for a launch vehicle computer, comprising: obtaining a test configuration instruction; generating an automatic test sequence according to a preset test logic based on the test configuration instruction; performing power distribution performance testing and / or actuator interface testing on the launch vehicle computer based on the automatic test sequence; when performing the power distribution performance testing, collecting electrical response data output by the launch vehicle computer after applying an excitation to a power distribution interface; and when performing the actuator interface testing, configuring an equivalent load for a specified drive interface to simulate a corresponding actuator, and collecting interface response data output by the interface when the launch vehicle computer drives the equivalent load after sending a drive control instruction to the specified drive interface. The present application adopts customized and automated data collection and processing, has power distribution power testing capability and real load characteristic simulation capability, and is high in testing efficiency and accuracy.

Description

Technical Field

[0001] This invention relates to the field of launch vehicle testing technology, and more specifically to a testing method for an onboard computer. Background Technology

[0002] The onboard computer is the core unit of the launch vehicle's flight control system, undertaking critical functions such as navigation calculation, guidance command generation, timing mission scheduling, system status monitoring, and fault diagnosis and handling. Its reliability and stability directly determine the success or failure of the rocket's flight and even affect the safety of the entire space mission. Therefore, before the onboard computer is officially installed on the rocket, it must undergo systematic, comprehensive, and rigorous testing to fully verify the accuracy and compatibility of its various functions, performance indicators, and external interfaces.

[0003] However, current testing methods for rocket-borne computers still have several shortcomings. First, there are significant gaps in the coverage of test content, particularly the lack of effective testing capabilities for the output bus power distribution, making it impossible to comprehensively evaluate the power supply performance of the rocket-borne computer under real load conditions. This constitutes a major weakness in the testing and verification system. Second, existing testing methods heavily rely on general-purpose instruments and equipment such as oscilloscopes, signal generators, and multimeters. The testing process often requires manual connection of each device, setting of parameters, recording of data, and separate measurements of timing signals, resistance characteristics, and switching status. This testing mode is not only cumbersome and time-consuming, but also heavily dependent on the experience and proficiency of the operators, easily introducing human error and interpretation bias, making it difficult to guarantee the consistency and repeatability of test results, and also hindering further improvements in testing efficiency. Summary of the Invention

[0004] In view of this, the present invention provides a testing method for rocket-borne computers to solve the problem of low testing efficiency of rocket-borne computers in the prior art.

[0005] This invention provides a testing method for an onboard computer, which includes a power supply and distribution interface and multiple drive interfaces connected to different actuators. The method includes: acquiring test configuration instructions; generating an automated test sequence based on the test configuration instructions and a preset test logic; performing power distribution performance testing and / or actuator interface testing on the onboard computer based on the automated test sequence; when performing power distribution performance testing, applying excitation to the power supply and distribution interface and collecting electrical response data output by the onboard computer; when performing actuator interface testing, configuring an equivalent load for a specified drive interface to simulate the corresponding actuator, sending a drive control instruction to the specified drive interface, and collecting interface response data output by the interface when the onboard computer drives the equivalent load; and generating a test report based on the electrical response data and interface response data, combined with preset pass / fail criteria.

[0006] The testing method for rocket-borne computers provided by this invention achieves integrated and automated testing of the rocket-borne computer's power distribution system and interfaces with various types of actuators by receiving flexibly configurable test commands and automatically generating test sequences based on preset logic. In power distribution performance testing, programmable excitation conditions are applied to the power supply and distribution interfaces of the rocket-borne computer according to the test sequence, and the output electrical response data is collected synchronously, thereby completing a comprehensive verification of the rocket-borne computer's power distribution performance. In actuator interface testing, this method can dynamically configure simulated loads equivalent to the electrical characteristics of their corresponding actuators for various drive interfaces. By sending corresponding drive control commands to designated interfaces and collecting interface response data during the actual driving of the equivalent load by the rocket-borne computer, equivalent verification and performance evaluation of the functions of key interfaces such as pyrotechnic interfaces, solenoid valve interfaces, and motor interfaces are completed in a non-real rocket environment. Finally, the testing system automatically analyzes and adjudicates the collected electrical and interface data according to preset criteria and generates a structured test report. This method integrates previously scattered, manual, and instrument-dependent individual tests into a customizable, fully automated, and environmentally simulated system-level testing process, significantly improving testing efficiency, coverage, and result consistency, and effectively ensuring the functionality and reliability of the rocket-borne computer before it is installed on the rocket.

[0007] In one optional implementation, the process of generating an automated test sequence based on test configuration instructions and according to preset test logic includes: parsing the test configuration instructions and identifying the specified test items; retrieving the corresponding standard test procedures from a preset test step library according to each test item; sorting the retrieved standard test procedures according to preset test logic, and loading the test parameters and judgment criteria associated with each procedure to generate an automated test sequence.

[0008] In one alternative implementation, the power distribution performance test items specified in the test configuration instruction include at least one of: power distribution anti-backflow test and power distribution load test.

[0009] In one optional implementation, the power supply and distribution interface includes an onboard power supply interface and a ground power supply interface. When performing a power distribution anti-backflow test, the process of applying an excitation to the power supply and distribution interface and collecting the electrical response data output by the onboard computer includes: applying a first DC voltage to the onboard power supply interface and applying a second DC voltage to the ground power supply interface; controlling the onboard computer to perform at least one power supply switching operation between the onboard power supply interface and the ground power supply interface; and continuously collecting the voltage data of the power supply bus of the onboard computer.

[0010] In one optional implementation, when performing a power distribution load test, the process of applying excitation to the power supply and distribution interface and collecting electrical response data output by the onboard computer includes: applying a nominal operating voltage to the power supply and distribution interface of the onboard computer; applying varying loads to each output bus of the onboard computer according to a preset loading sequence; continuously collecting voltage and current data of each output bus, and then calculating the actual output power and load regulation rate of each output bus.

[0011] In one optional implementation, the actuator interface test items specified in the test configuration instructions include at least one of the following: pyrotechnic channel test, solenoid valve channel test, and motor channel test.

[0012] In one optional implementation, when performing actuator interface testing, the process of configuring an equivalent load for a specified drive interface to simulate the corresponding actuator, and after sending a drive control command to the specified drive interface, collecting the interface response data output by the interface when the onboard computer drives the equivalent load includes: when performing pyrotechnic channel testing, configuring a simulated pyrotechnic load with a resistance equivalent to a real pyrotechnic, sending an ignition command to the pyrotechnic drive interface of the onboard computer, and collecting the voltage and current waveforms output by the pyrotechnic drive interface; when performing solenoid valve channel testing, configuring a simulated solenoid valve load with a resistance equivalent to a real solenoid valve, sending a solenoid valve control command to the solenoid valve drive interface of the onboard computer, and collecting the voltage and current waveforms output by the solenoid valve drive interface; when performing motor channel testing, configuring a simulated motor load with a resistance equivalent to a real motor, sending a motor drive command to the motor drive interface of the onboard computer, and collecting the voltage and current waveforms output by the motor drive interface.

[0013] In one optional implementation, when performing pyrotechnic channel testing, the process of generating a test report based on electrical response data and interface response data, combined with preset pass / fail criteria, includes: analyzing the waveform characteristics of the pyrotechnic drive interface based on the voltage and current waveforms output by the pyrotechnic drive interface, wherein the waveform characteristics of the pyrotechnic drive interface include waveform amplitude, pulse width, and rise time; extracting the waveform threshold of the pyrotechnic drive interface based on preset pyrotechnic ignition pass / fail conditions, and comparing it with the waveform characteristics of the pyrotechnic drive interface to generate a pyrotechnic channel test report.

[0014] In one optional implementation, when performing solenoid valve channel testing, the process of generating a test report based on electrical response data and interface response data, combined with preset pass / fail criteria, includes: analyzing the waveform characteristics of the solenoid valve drive interface based on the voltage and current waveforms output by the solenoid valve drive interface, the waveform characteristics of the solenoid valve drive interface including the establishment time, steady-state value, and reverse peak voltage at turn-off of the current waveform; extracting the waveform threshold of the solenoid valve drive interface based on preset solenoid valve drive performance pass / fail conditions, and comparing it with the waveform characteristics of the solenoid valve drive interface to generate a solenoid valve channel test report.

[0015] In one optional implementation, when performing motor channel testing, the process of generating a test report based on electrical response data and interface response data, combined with preset pass / fail criteria, includes: analyzing the waveform characteristics of the motor drive interface based on the voltage and current waveforms output by the motor drive interface, the waveform characteristics of the motor drive interface including multiphase drive voltage, simulated back EMF signal of equivalent load, harmonic content, and dynamic response characteristics; extracting the waveform threshold of the motor drive interface based on preset motor drive performance pass / fail conditions, and comparing it with the waveform characteristics of the motor drive interface to generate a motor channel test report. Attached Figure Description

[0016] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0017] Figure 1 This is a composition diagram of a test system for a rocket-borne computer according to an embodiment of the present invention; Figure 2 This is a flowchart illustrating a testing method for an onboard computer according to an embodiment of the present invention; Figure 3 This is a diagram showing the composition of the power distribution output interface test circuit of the rocket-borne computer according to an embodiment of the present invention; Figure 4 This is a diagram showing the composition of the test circuit for the timing output channel of the pyrotechnic components of the rocket-borne computer according to an embodiment of the present invention. Figure 5 This is a diagram showing the composition of the test circuit for the timing output channels of the electromagnetic valves and motors of the rocket-borne computer according to an embodiment of the present invention. Figure 6 This is a diagram showing the composition of the digital input channel test circuit of the rocket-borne computer according to an embodiment of the present invention; Figure 7This is a diagram showing the composition of the digital output channel test circuit of the rocket-borne computer according to an embodiment of the present invention; Figure 8 This is an organizational structure diagram of the testing software according to an embodiment of the present invention; Figure 9 This is a flowchart of a one-click test according to an embodiment of the present invention; Figure 10 This is a structural block diagram of a test apparatus for an onboard computer according to an embodiment of the present invention; Figure 11 This is a schematic diagram of the hardware structure of an electronic device according to an embodiment of the present invention. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] It is understood that before using the technical solutions disclosed in the various embodiments of the present invention, users should be informed of the types, scope of use, and usage scenarios of the personal information involved in the present invention and their authorization should be obtained in accordance with relevant laws and regulations through appropriate means.

[0020] like Figure 1 As shown, the onboard computer is the device under test (DUT). The test system hardware includes a power supply, load box, power switching switch, electronic loads, an industrial computer, and a switch. The power supply uses a programmable linear DC power supply to power the onboard computer. The industrial computer can remotely set the voltage and current of the power supply via Ethernet. Programmable DC electronic loads are selected. The industrial computer can remotely set the power of the electronic loads via Ethernet. The onboard computer is connected to the electronic loads via the power switching switch to test the power distribution of the various pyrotechnic components, solenoid valves, and motor output buses of the onboard computer. The load box contains simulated loads for pyrotechnic components, solenoid valves, and motors, used to test the timing output interfaces of the onboard computer. The industrial computer contains a 1553B communication board, a serial communication board, a CAN communication board, and a digital input / output board. The communication boards are used to test various communication interfaces of the onboard computer, the digital input / output boards are used to test the digital input / output interfaces of the onboard computer, and control the load box switching relays. The analog input boards collect the voltage of each simulated load in the load box.

[0021] The specific physical interfaces are as follows: the bus input interface of the rocket computer is connected to the DC power supply; the bus output interface is connected to the electronic load; the pyrotechnic output interface, solenoid valve output interface, and motor output interface are connected to the analog load in the load box; the digital input / output interface is connected to the digital output board and analog input board of the industrial control computer; the communication interface is connected to the 1553B communication board, serial communication board, CAN communication board, and switch of the industrial control computer; and a 1553B coupler is added to the 1553B communication connection cable.

[0022] This embodiment provides a testing method for rocket-borne computers, applied to... Figure 1 The rocket-borne computer test system shown includes a power supply interface and multiple drive interfaces for connecting to different actuators, such as... Figure 2 As shown, the method includes: Step S1: Obtain the test configuration command.

[0023] For example, testers select specific items to be tested and set relevant parameters through a human-machine interface, and the system receives these instructions as input for the test. For instance, operators can select items such as "power distribution anti-backflow test," "power distribution load test," and "pyrotechnics channel test," and adjust parameters such as test voltage and load size as needed.

[0024] Step S2: Based on the test configuration instructions, generate an automated test sequence according to the preset test logic.

[0025] Specifically, based on the selected test items, the system retrieves the corresponding standard test procedure modules from the preset test logic library and automatically arranges the execution order, parameter passing relationships, and result judgment criteria according to logical relationships to form a structured test instruction sequence. For example, when both "Power Distribution Backflow Prevention Test" and "Pyrotechnic Channel Test" are selected, the system will first generate the power initialization steps, then the pyrotechnic load configuration steps, then the power switching test steps, and finally the pyrotechnic ignition test steps, ensuring that the test procedure meets both electrical safety requirements and test logic needs.

[0026] Specifically, the process of generating automated test sequences based on test configuration instructions and according to preset test logic includes: Step S21: Parse the test configuration instructions and identify the specified items to be tested.

[0027] Specifically, the system receives and parses the test configuration instructions input by the testers, identifying the items to be tested contained therein. If the instruction contains "test the power distribution load capacity" and "verify the pyrotechnic channel function", the system will parse these two items as independent test tasks, and at the same time identify the parameter settings that may be related, such as the load current value and ignition pulse width.

[0028] Step S22: Retrieve the corresponding standard test procedure from the preset test procedure library according to each item to be tested.

[0029] Specifically, the system extracts corresponding template processes from its built-in standardized test process library based on the identified test items. These templates predefine the standard operating procedures for various types of tests.

[0030] Step S23: Sort the retrieved standard test processes according to the preset test logic, load the test parameters and judgment criteria associated with each process, and generate an automated test sequence.

[0031] Specifically, the system sequentially arranges and integrates parameters from multiple extracted template processes according to preset scheduling rules. During arrangement, the system considers the test logic relationships and the timing of hardware resource scheduling, ensuring, for example, that pyrotechnic tests must be performed only after power supply is stable. Simultaneously, the system fills in specific parameter settings (such as voltage level and load value) into the corresponding steps, ultimately generating an automated test sequence that can directly drive the test equipment and contains complete instructions and judgment criteria.

[0032] Step S3: Perform power distribution performance testing and / or actuator interface testing on the rocket-borne computer based on an automated test sequence.

[0033] Specifically, the test execution process is driven by an automated test sequence, which contains multiple test instructions arranged according to predetermined logic. When the sequence includes power distribution performance test tasks, the system automatically executes the corresponding power supply excitation and parameter acquisition operations; when it includes actuator interface tests, it sequentially executes interface configuration, instruction sending, and response acquisition. The test system supports the independent or combined execution of these two types of tests, enabling flexible system function verification.

[0034] Step S4: When performing power distribution performance testing, after applying excitation to the power supply and distribution interface, collect the electrical response data output by the onboard computer.

[0035] Specifically, the test system applies a specified voltage excitation to the power supply interface of the onboard computer according to a sequence of instructions, simulating onboard or ground power supply conditions. During and after the excitation application, the data acquisition module continuously monitors and records electrical parameters such as voltage and current at the output of the onboard computer, forming an electrical response dataset with timestamps for subsequent analysis and performance evaluation.

[0036] The power supply interfaces include the onboard power supply interface and the ground power supply interface. Figure 3This is a test circuit for the power distribution output interfaces of the rocket-borne computer. The power distribution interfaces include a main power distribution output interface, a main power distribution output interface for pyrotechnic components, a main power distribution output interface for solenoid valves, and a main power distribution output interface for motors. These four power distribution output interfaces are connected to power switching switches. The power switching switches are mechanically interlocked between the various power distribution output interfaces, ensuring that only one interface is connected to the electronic load at a time. The power switching switches adjust their opening and closing states according to a predetermined program, and the electronic load adjusts its own power according to a predetermined program, allowing for the verification of the power distribution power of each output interface of the rocket-borne computer. The power distribution performance test items specified in the test configuration instructions include: power distribution backflow prevention test and power distribution load test.

[0037] For example, when conducting a power distribution backflow prevention test, the process of acquiring electrical response data output by the onboard computer after applying excitation to the power supply interface includes: applying a first DC voltage to the onboard power supply interface and a second DC voltage to the ground power supply interface; controlling the onboard computer to perform at least one power supply switching operation between the onboard power supply interface and the ground power supply interface; and continuously acquiring voltage data of the onboard computer's power supply bus. The specific test steps are as follows: (1) Configure power channel 1 to 30V / 10A and power channel 2 to 33V / 3A, and turn on the power.

[0038] (2) The onboard computer performs a self-test.

[0039] (3) The analog input board continuously collects the ground supply, arrow supply and bus voltage.

[0040] (4) The industrial control computer sends a power transfer command to the onboard computer, and the onboard computer performs the power transfer operation.

[0041] (5) Turn off the output of power channel 2.

[0042] (6) If there are no abnormalities, turn off the power channel 1 output.

[0043] (7) Set power channel 1 to 33V / 70A and power channel 2 to 30V / 3A, and turn on the power.

[0044] (8) The onboard computer performs a self-test.

[0045] (9) The industrial control computer sends a power transfer command to the onboard computer, and the onboard computer performs the power transfer operation.

[0046] (10) Turn off the output of power channel 2.

[0047] (11) The analog input board continuously collects the ground supply, arrow supply and bus voltage.

[0048] (12) Turn off the output of power channel 1.

[0049] For example, when performing a power distribution load test, the process of applying excitation to the power supply and distribution interface and collecting the electrical response data output by the onboard computer includes: applying the nominal operating voltage to the power supply and distribution interface of the onboard computer; applying varying loads to each output bus of the onboard computer according to a preset loading sequence; continuously collecting voltage and current data of each output bus, and then calculating the actual output power and load regulation rate of each output bus. The specific test steps are as follows: (1) Set the electronic load to constant current mode 65A.

[0050] (2) Collect the current current.

[0051] (3) The electronic load starts outputting, and +B2 and +B3 are started in sequence to collect the current.

[0052] (4) Turn off +B2, +B3 and electronic load.

[0053] (5) Turn on +BF1, +BF2 and the electronic load for 0.5 seconds and collect the current.

[0054] (6) Turn off +BF1, +BF2 and electronic load.

[0055] Step S5: When performing actuator interface testing, configure an equivalent load for the specified drive interface to simulate the corresponding actuator, and after sending drive control commands to the specified drive interface, collect the interface response data output by the interface when the onboard computer drives the equivalent load.

[0056] Specifically, the system first connects simulated loads with corresponding electrical characteristics to the corresponding drive interfaces based on the test item type (e.g., pyrotechnics, solenoid valves, motors); then, it sends specific drive control commands to the interface to trigger the onboard computer to execute drive operations; during this process, it simultaneously collects the voltage and current waveforms and load response characteristics output by the interface to obtain interface response data reflecting the drive capability of the onboard computer. The actuator interface test items specified in the test configuration command include: pyrotechnics channel test, solenoid valve channel test, and motor channel test.

[0057] Figure 4 This is a test circuit for the timing output channel of pyrotechnic devices, using resistors to simulate the pyrotechnic devices. The main power distribution output interface for the pyrotechnic devices is designed with interstage separation and rectifier separation mechanisms, requiring it to withstand instantaneous high currents. A relay can be used to select between a standard measurement mode and a power measurement mode. In standard measurement mode, a precision resistor is used to simulate the pyrotechnic device, while in power measurement mode, a power resistor is used. The analog input board acquires and records the voltage across the simulated load to verify the availability and output power of the timing output channel for the pyrotechnic devices.

[0058] For example, the process of conducting pyrotechnic channel testing includes: configuring a simulated load with a resistance value equivalent to a real pyrotechnic device, sending an ignition command to the pyrotechnic drive interface of the onboard computer, and then acquiring the voltage and current waveforms output by the pyrotechnic drive interface. The specific test steps are as follows: (1) Switch the load bank to timing equivalent mode.

[0059] (2) Continuously collect analog quantities from channel 1 of pyrotechnics.

[0060] (3) Open the pyrotechnics channel 1 and read the waveform and sampling parameters.

[0061] (4) Follow steps (2) and (3) to complete all pyrotechnic channel tests.

[0062] Figure 5 This test circuit includes timing output channels for solenoid valves and motors, simulating both using a combination of resistors and inductors. The main power output interface for solenoid valves is designed for attitude control solenoid valves, requiring a short response time. The main power output interface for motors is designed for servo motors, requiring large current fluctuations. A relay switch allows selection between a standard measurement mode and a power measurement mode. In standard measurement mode, a combination of precision resistors and precision winding inductors simulates solenoid valves and motors; in power measurement mode, a combination of power resistors and power winding inductors simulates pyrotechnic devices. The analog input board acquires and records the voltage across the simulated load to verify the availability and output power of the timing output channels for solenoid valves and motors.

[0063] For example, the process of testing a solenoid valve channel includes: configuring a simulated solenoid valve load with a resistance equivalent to a real solenoid valve, sending solenoid valve control commands to the solenoid valve drive interface of the onboard computer, and then acquiring the voltage and current waveforms output by the solenoid valve drive interface. The specific test steps are as follows: (1) Switch the load bank to timing equivalent mode.

[0064] (2) Continuously collect analog signals from solenoid valve channel 1.

[0065] (3) Open solenoid valve channel 1 and read the waveform and sampling parameters.

[0066] (4) Follow steps (2) and (3) to complete the test of all solenoid valve channels.

[0067] For example, the process of performing motor channel testing includes: configuring a simulated motor load with a resistance value equivalent to that of a real motor, sending motor drive commands to the motor drive interface of the onboard computer, and then acquiring the voltage and current waveforms output by the motor drive interface. The specific steps are as follows: (1) Switch the load bank to timing equivalent mode.

[0068] (2) Continuously collect analog signals from motor channel 1.

[0069] (3) Open motor channel 1 and read the waveform and sampling parameters.

[0070] (4) The load cell is switched to transient load.

[0071] (5) Open motor channel 1 and read the waveform and sampling parameters within 0.2 seconds.

[0072] (6) Complete all motor channel tests according to steps (2) to (5).

[0073] For example, the specific steps for the communication test of the rocket-borne computer are as follows: (1) Conduct basic communication tests on each bus and channel.

[0074] (2) Conduct full-function testing of 153B communication.

[0075] (3) Conduct full-function tests of 422 communication on each channel.

[0076] (4) Conduct full-function tests of CAN communication for each channel.

[0077] For example, the specific steps for testing the switching quantity of the onboard computer are as follows: (1) Set the power supply to 5V / 1A, 24V / 1A, and 33.6V / 1A in sequence.

[0078] (2) Turn the power output on and off in sequence.

[0079] (3) Test all switch input channels in sequence.

[0080] (4) Test all digital output channels in sequence.

[0081] For example, the specific steps for voltage surge testing of the rocket-borne computer are as follows: (1) Set the power supply to 18V / 3A and turn on the output.

[0082] (2) The onboard computer self-test is normal, and the ground power supply, rocket power supply and bus voltage are collected.

[0083] (3) Turn off the power output after 60 seconds.

[0084] (4) Set the power supply to 40V / 3A and turn on the output.

[0085] (5) The onboard computer self-test is normal, and the ground power supply, rocket power supply, and bus voltage acquisition are normal.

[0086] (6) Turn off the power output after 60 seconds.

[0087] Specifically, such as Figure 6 As shown, in the measurement circuit of the digital input channel of the rocket-borne computer, a programmable DC power supply serves as the test excitation source, providing a high-precision, high-resolution, and continuously adjustable DC voltage. The positive terminal of the power supply is connected to the digital output channel of the rocket-borne computer via the output point of the digital input / output board, and then returns to the negative terminal of the power supply, forming a closed-loop circuit. Adjusting the power supply voltage can verify the voltage adaptability and availability of the digital input channel.

[0088] like Figure 7 As shown, in the measurement circuit of the digital output channel of the onboard computer, a programmable DC power supply provides voltage, which is then connected to the analog input board via the digital output channel of the onboard computer. The analog input board has an oscilloscope function, and the software can record the voltage waveform curve. Adjusting the power supply voltage can verify the voltage adaptability and availability of the digital output channel.

[0089] Step S6: Generate a test report based on the electrical response data and interface response data, combined with the preset pass / fail criteria.

[0090] Specifically, the system automatically compares and judges the electrical response data collected from power distribution performance tests and the interface response data collected from interface tests of various actuators with the pre-existing pass thresholds, standard waveforms, or logical expectations in the system. Finally, the system integrates the pass / fail conclusions, key data curves, and anomaly records of all test items, and automatically generates a structured test report document that includes a test overview, results summary, problem analysis, and suggestions.

[0091] Specifically, the process of generating a test report based on electrical response data and interface response data, combined with preset pass / fail criteria, includes: (1) When conducting pyrotechnic channel testing, the waveform characteristics of the pyrotechnic drive interface are analyzed based on the voltage and current waveforms output by the pyrotechnic drive interface. The waveform characteristics of the pyrotechnic drive interface include waveform amplitude, pulse width and rise time. Based on the preset pyrotechnic ignition qualification conditions, the waveform threshold of the pyrotechnic drive interface is extracted and compared with the waveform characteristics of the pyrotechnic drive interface to generate a pyrotechnic channel test report.

[0092] (2) When performing solenoid valve channel test, the waveform characteristics of the solenoid valve drive interface are analyzed based on the voltage and current waveforms output by the solenoid valve drive interface. The waveform characteristics of the solenoid valve drive interface include the establishment time, steady-state value and reverse peak voltage of the current waveform when turned off. Based on the preset solenoid valve drive performance qualification conditions, the waveform threshold of the solenoid valve drive interface is extracted and compared with the waveform characteristics of the solenoid valve drive interface to generate a solenoid valve channel test report.

[0093] (3) When performing motor channel testing, the waveform characteristics of the motor drive interface are analyzed based on the voltage and current waveforms output by the motor drive interface. The waveform characteristics of the motor drive interface include multiphase drive voltage, simulated back EMF signal of equivalent load, harmonic content and dynamic response characteristics. Based on the preset motor drive performance qualification conditions, the waveform threshold of the motor drive interface is extracted and compared with the waveform characteristics of the motor drive interface to generate a motor channel test report.

[0094] For example, such as Figure 8 As shown, the test software in this embodiment is written in LabVIEW and adopts a producer-consumer pattern. LabVIEW can work closely with the board to achieve high-speed data acquisition and protocol communication. The program flowchart consists of an instruction receiving loop, an instruction execution loop, a data processing loop, and a data storage loop. The user sends action commands to the instruction receiving loop through the panel input controls. The instruction execution loop defines the test process, receives input data from the board, executes each action step by step, and triggers the output point actions of the board. The data processing loop parses the instruction execution loop data according to the protocol, draws waveform curves, and outputs them to the panel display controls. The data storage loop records the operation time, operation steps, and test data in real time to the permanent storage area of ​​the industrial control computer. The database adopts the TDMS file format, which uses binary format, has a high compression ratio, saves storage space, and supports direct reading of specific data segments without loading the entire file.

[0095] like Figure 9 As shown, to improve testing efficiency, the software is designed with a one-click testing program, allowing users to complete all routine testing tasks with simple operations. After the system powers on, it automatically performs a self-test. Once the self-test passes, users select test items, and the software automatically completes all tests and records the data. If an error occurs during testing, the software automatically records the error information and terminates the test.

[0096] The testing method for the rocket-borne computer provided in this embodiment achieves integrated and automated testing of the rocket-borne computer's power distribution system and interfaces with various types of actuators by receiving flexibly configurable test commands and automatically generating test sequences based on preset logic. In power distribution performance testing, programmable excitation conditions are applied to the power supply and distribution interfaces of the rocket-borne computer according to the test sequence, and its output electrical response data is collected synchronously, thereby completing a comprehensive verification of the rocket-borne computer's power distribution performance. In actuator interface testing, this method can dynamically configure simulated loads equivalent to the electrical characteristics of their corresponding actuators for various drive interfaces. By sending corresponding drive control commands to designated interfaces and collecting interface response data during the actual driving of the equivalent load by the rocket-borne computer, equivalent verification and performance evaluation of the functions of key interfaces such as pyrotechnic interfaces, solenoid valve interfaces, and motor interfaces are completed in a non-real rocket environment. Finally, the testing system automatically analyzes and adjudicates the collected electrical and interface data according to preset criteria and generates a structured test report. This method integrates previously scattered, manual, and instrument-dependent individual tests into a customizable, fully automated, and environmentally simulated system-level testing process, significantly improving testing efficiency, coverage, and result consistency, and effectively ensuring the functionality and reliability of the rocket-borne computer before it is installed on the rocket.

[0097] This embodiment also provides a test apparatus for an onboard computer, which is used to implement the above embodiments and preferred embodiments; details already described will not be repeated. As used below, the term "module" can be a combination of software and / or hardware that implements a predetermined function. Although the apparatus described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0098] This embodiment provides a testing device for an onboard computer, such as... Figure 10 As shown, it includes: Module 1001 is used to obtain test configuration commands.

[0099] The test sequence generation module 1002 is used to generate automated test sequences based on test configuration instructions and according to preset test logic.

[0100] Test module 1003 is used to perform power distribution performance testing and / or actuator interface testing on the rocket-borne computer based on an automated test sequence.

[0101] The power distribution performance test module 1004 is used to collect electrical response data output by the onboard computer after applying excitation to the power supply and distribution interface during power distribution performance testing.

[0102] The actuator interface testing module 1005 is used to configure an equivalent load for a specified drive interface to simulate the corresponding actuator when performing actuator interface testing, and after sending drive control commands to the specified drive interface, collect the interface response data output by the interface when the onboard computer drives the equivalent load.

[0103] The test result generation module 1006 is used to generate a test report based on electrical response data and interface response data, combined with preset pass / fail criteria.

[0104] The test apparatus for the rocket-borne computer provided in this embodiment of the invention can execute the method provided in any embodiment of the invention, and has the corresponding functional modules and beneficial effects for executing the method. Further functional descriptions of the various modules and units described above are the same as those in the corresponding embodiments described above, and will not be repeated here.

[0105] Figure 11 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention.

[0106] The following is a detailed reference. Figure 11 The diagram illustrates a structural schematic suitable for implementing an electronic device according to embodiments of the present invention. The electronic device may include a processor (e.g., a central processing unit, graphics processor, etc.) 001, which can perform various appropriate actions and processes according to a program stored in read-only memory (ROM) 002 or a program loaded from memory 008 into random access memory (RAM) 003. The RAM 003 also stores various programs and data required for the operation of the electronic device. The processor 001, ROM 002, and RAM 003 are interconnected via bus 004. An input / output (I / O) interface 005 is also connected to bus 004.

[0107] Typically, the following devices can be connected to I / O interface 005: input devices 006 including, for example, touchscreens, touchpads, keyboards, mice, cameras, microphones, accelerometers, gyroscopes, etc.; output devices 007 including, for example, liquid crystal displays (LCDs), speakers, vibrators, etc.; memory devices 008 including, for example, magnetic tapes, hard disks, etc.; and communication devices 009. Communication device 009 allows electronic devices to exchange data via wireless or wired communication with other devices. Although Figure 11 Electronic devices with various devices are shown, but it should be understood that it is not required to implement or have all of the devices shown, and more or fewer devices may be implemented or have instead.

[0108] In particular, according to embodiments of the present invention, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of the present invention include a computer program product comprising a computer program carried on a non-transitory computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via communication device 009, or installed from memory 008, or installed from ROM 002. When the computer program is executed by processor 001, it performs the functions defined in the methods of the embodiments of the present invention.

[0109] Figure 11 The electronic device shown is merely an example and should not be construed as limiting the functionality and scope of use of the embodiments of the present invention.

[0110] This invention also provides a computer-readable storage medium. The methods described above according to embodiments of the invention can be implemented in hardware or firmware, or implemented as computer code that can be recorded on a storage medium, or implemented as computer code downloaded via a network and originally stored on a remote storage medium or a non-transitory machine-readable storage medium and then stored on a local storage medium. Thus, the methods described herein can be processed by software stored on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. The storage medium can be a magnetic disk, optical disk, read-only memory, random access memory, flash memory, hard disk, or solid-state drive, etc.; further, the storage medium can also include combinations of the above types of memory. It is understood that computers, processors, microprocessor controllers, or programmable hardware include storage components capable of storing or receiving software or computer code, which, when accessed and executed by the computer, processor, or hardware, implements the methods shown in the above embodiments.

[0111] A portion of this invention can be applied as a computer program product, such as computer program instructions, which, when executed by a computer, can invoke or provide the methods and / or technical solutions according to the invention through the operation of the computer. Those skilled in the art will understand that the forms in which computer program instructions exist in a computer-readable medium include, but are not limited to, source files, executable files, installation package files, etc. Correspondingly, the ways in which computer program instructions are executed by a computer include, but are not limited to: the computer directly executing the instructions, or the computer compiling the instructions and then executing the corresponding compiled program, or the computer reading and executing the instructions, or the computer reading and installing the instructions and then executing the corresponding installed program. Here, the computer-readable medium can be any available computer-readable storage medium or communication medium accessible to a computer.

[0112] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A testing method for an onboard computer, characterized in that, The onboard computer includes a power supply interface and multiple drive interfaces connected to different actuators; the method includes: Get test configuration instructions; Based on the test configuration instructions, an automated test sequence is generated according to the preset test logic; Based on the automated test sequence, the power distribution performance of the rocket-borne computer and / or the actuator interface test are performed. When conducting power distribution performance testing, after applying excitation to the power supply and distribution interface, the electrical response data output by the onboard computer is collected. When performing actuator interface testing, an equivalent load is configured for the specified drive interface to simulate the corresponding actuator. After sending drive control commands to the specified drive interface, the interface response data output by the interface when the onboard computer drives the equivalent load is collected. A test report is generated based on the electrical response data and the interface response data, combined with preset pass / fail criteria.

2. The testing method for the rocket-borne computer according to claim 1, characterized in that, The process of generating an automated test sequence based on the test configuration instructions and according to preset test logic includes: Parse the test configuration instructions and identify the specified items to be tested; According to each item to be tested, the corresponding standard test procedure is retrieved from the preset test procedure library; The automated test sequence is generated by sorting the retrieved standard test processes according to the preset test logic, loading the test parameters and judgment criteria associated with each process, and then generating the automated test sequence.

3. The testing method for the rocket-borne computer according to claim 2, characterized in that, The power distribution performance test items specified in the test configuration instruction include at least one of the following: power distribution anti-backflow test and power distribution load test.

4. The testing method for the rocket-borne computer according to claim 3, characterized in that, The power supply and distribution interface includes an onboard power supply interface and a ground power supply interface. During power distribution anti-backflow testing, the process of applying excitation to the power supply and distribution interface and then collecting the electrical response data output by the onboard computer includes: A first DC voltage is applied to the power supply interface on the arrow, and a second DC voltage is applied to the ground power supply interface; The onboard computer is controlled to perform at least one power switching operation between the onboard power supply interface and the ground power supply interface; The voltage data of the power supply bus of the onboard computer is continuously collected.

5. The testing method for the rocket-borne computer according to claim 3, characterized in that, When performing a power distribution load test, the process of acquiring the electrical response data output by the onboard computer after applying excitation to the power supply and distribution interface includes: Apply the nominal operating voltage to the power supply interface of the onboard computer; According to a preset loading sequence, varying loads are applied to each output bus of the rocket-borne computer. After continuously collecting voltage and current data from each output bus, the actual output power and load regulation rate of each output bus are calculated.

6. The testing method for the rocket-borne computer according to claim 2, characterized in that, The actuator interface test items specified in the test configuration instructions include at least one of the following: pyrotechnic channel test, solenoid valve channel test, and motor channel test.

7. The testing method for a rocket-borne computer according to claim 6, characterized in that, The process of configuring an equivalent load for a specified drive interface to simulate the corresponding actuator during actuator interface testing, sending drive control commands to the specified drive interface, and then collecting the interface response data output by the interface when the onboard computer drives the equivalent load includes: When conducting pyrotechnic channel testing, a simulated load with a resistance value equivalent to that of a real pyrotechnic is configured, and after sending an ignition command to the pyrotechnic drive interface of the rocket-borne computer, the voltage and current waveforms output by the pyrotechnic drive interface are collected. When performing solenoid valve channel testing, a solenoid valve with a resistance equivalent to that of a real solenoid valve is configured to simulate a load. After sending solenoid valve control commands to the solenoid valve drive interface of the rocket computer, the voltage and current waveforms output by the solenoid valve drive interface are collected. When performing motor channel testing, a simulated motor load with a resistance equivalent to that of a real motor is configured, and after sending a motor drive command to the motor drive interface of the rocket-borne computer, the voltage and current waveforms output by the motor drive interface are collected.

8. The testing method for the rocket-borne computer according to claim 7, characterized in that, When conducting pyrotechnic channel testing, the process of generating a test report based on the electrical response data and the interface response data, combined with preset pass / fail criteria, includes: Based on the voltage and current waveforms output by the pyrotechnic drive interface, the waveform characteristics of the pyrotechnic drive interface are analyzed. The waveform characteristics of the pyrotechnic drive interface include waveform amplitude, pulse width, and rise time. Based on the preset ignition qualification conditions of pyrotechnics, the waveform threshold of the pyrotechnic driving interface is extracted and compared with the waveform characteristics of the pyrotechnic driving interface to generate a pyrotechnic channel test report.

9. The testing method for a rocket-borne computer according to claim 7, characterized in that, When performing solenoid valve channel testing, the process of generating a test report based on the electrical response data and the interface response data, combined with preset pass / fail criteria, includes: Based on the voltage and current waveforms output by the solenoid valve drive interface, the waveform characteristics of the solenoid valve drive interface are analyzed. The waveform characteristics of the solenoid valve drive interface include the establishment time of the current waveform, the steady-state value, and the reverse peak voltage when turned off. Based on the preset solenoid valve drive performance qualification conditions, the waveform threshold of the solenoid valve drive interface is extracted and compared with the waveform characteristics of the solenoid valve drive interface to generate a solenoid valve channel test report.

10. The testing method for the rocket-borne computer according to claim 7, characterized in that, When performing motor channel testing, the process of generating a test report based on the electrical response data and the interface response data, combined with preset pass / fail criteria, includes: Based on the voltage and current waveforms output by the motor drive interface, the waveform characteristics of the motor drive interface are analyzed. The waveform characteristics of the motor drive interface include multiphase drive voltage, simulated back electromotive force signal of equivalent load, harmonic content, and dynamic response characteristics. Based on preset motor drive performance qualification conditions, the waveform threshold of the motor drive interface is extracted and compared with the waveform characteristics of the motor drive interface to generate a motor channel test report.

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