Patent RU-2764837-C1 (RU)
Inventor: Nedorezov Dmitrii Aleksandrovich
IPC: G06N7/00
Filed: 2021-01-25
Granted: 2022-01-21
Abstract: FIELD: computer technology; space technology. 
     SUBSTANCE: invention relates to a method for testing computing devices (hereinafter – CD) of spacecraft (hereinafter – SC) control systems. In a method, auxiliary on-board equipment (hereinafter – AOE) is imitated semi-naturally on programmable logic integrated circuits (hereinafter – PLIC), which, during normal operation, interacts with the tested CD; in PLIC projects of semi-natural AOE models, implemented in languages of the equipment description, malfunctions are intentionally introduced, simulating abnormal situations; then, tests are carried out in order to assess the probability of detection by the tested CD of malfunctions introduced into AOE models; during tests, a project of a serviceable semi-natural model (hereinafter – PSSM) of AOE is created in languages of the equipment description, simulating the behavior of its input-output channels; the resulting PSSM is recorded in PLIC of a fault simulation device (hereinafter – FSD) containing interface input-output channels; tests are conducted on PSSM; in languages of the equipment description, a project of a faulty semi-natural model (PFSM) of AOE is created, wherein the possibility of enabling/disabling malfunctions without recompiling the PLIS project is provided during testing, using high-level control software; the resulting PFSM is recorded in PLIS of FSD; using a test process control device (hereinafter – TPCD), an array of control actions, alternately including malfunctions implemented in the PFSM and specified in the array, is formed; the same tests are conducted on the PFSM, as in the previous case with the PSSM; using TPCD, test results from PSSM and PFSM are compared for each malfunction from the given array, if no malfunctions are detected during testing on PSSM, and when testing on PFSM, the entire array of introduced malfunctions is detected, then the tested CD is considered to have passed the test; if, during testing on PSSM, malfunctions are detected, then the coefficient of the first stage   is determined, where o is the number of detected malfunctions; if not all malfunctions are detected during testing on the PFSM, then the coefficient of the second stage   is determined, where ov is the number of malfunctions introduced into the model, oo is the number of detected malfunctions, while during the above-mentioned tests, by issuing a series of commands from AOE simulation models, the tested CD is put into orientation and stabilization mode (hereinafter – OS); then, the CD initiates iteration of OS of the SC according to the following algorithm; the CD requests the current state of directivity and angular velocities of the SC from simulation models of devices (hereinafter – SMD) of the OS; SMD of the OS receive a request from the tested CD and analyze it for the address of the device on the information main line in order to determine the addressee of this command; according to the received request, the corresponding SMD of the OS, which is defined as the addressee of this request, based on a mathematical model of SC movement in space, calculates the current state of directivity and angular velocities of SC movement and issues them to the CD; next, the CD analyzes data received from the SMD of the OS and, based on results of the analysis, forms a control command to turn on/off engines necessary for the OS, which completes the iteration of the OS of the SC; such iterations of the OS are repeated many times, until the SC orients itself to a given landmark. 
     EFFECT: increase in the reliability of testing CD of SC control systems. 
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