The invention discloses a method for automatically testing aerospace measurement and control equipment data. The method comprises the following basic steps: 1, establishing a set of identifiers, excitation data, output data, a verification method, excitation starting time, intervals and time sequence rules of aerospace measurement and control equipment functional modules; 2, establishing a database of spaceflight measurement and control equipment parameters; 3, generating a test excitation database according to the parameters of the aerospace measurement and control equipment; 4, reading the excitation data and the time sequence rule of the to-be-tested functional module, automatically sending the excitation data to the aerospace measurement and control equipment according to the time sequence rule, and monitoring output data (monitoring data) of the aerospace measurement and control equipment; 5, reading the output data (read data) of the to-be-tested functional module, and comparingthe read data with the monitoring data through a verification method and the time sequence rule of the functional module; and 6, periodically repeating the steps 4 and 5 according to a selected to-be-tested function list and to-be-tested function items to complete the test of the selected module.

Method for automatically testing aerospace measurement and control equipment data

This paper proposes a simulation system design together with an effectiveness evaluation method for large flexible spacecraft. To handle the vibration problem of the flexible accessory of the spacecraft simulation system, a sliding mode controller is used to suppress the flexible vibration. To realize the on-orbit identification of the moment of inertia of the flexible spacecraft and improve the identification accuracy, a parallel recursive method is proposed by combining generalized Kalman filtering with recursive least squares. The simulation results verify that the proposed sliding mode control algorithm has strong stability and can effectively suppress the vibration of flexible accessories, and its adjustment time is about 1/10 of PID control. Meanwhile, the proposed identification method has improved accuracy compared with traditional methods, and the identification error can be reduced to 4%. Furthermore, the analytic hierarchy process (AHP) is used to evaluate the effectiveness of the spacecraft simulation device proposed in this paper. The reliability of the simulation system is calculated to be 96.7%, which can be used as a verification platform for related algorithm research. 

Large Flexible Spacecraft Simulation System: Control, Identification and Effectiveness Evaluation

This paper proposes a simulation system design together with an effectiveness evaluation method for large flexible spacecraft. To handle the vibration problem of the flexible accessory of the spacecraft simulation system, a sliding mode controller is used to suppress the flexible vibration. To realize the on-orbit identification of the moment of inertia of the flexible spacecraft and improve the identification accuracy, a parallel recursive method is proposed by combining generalized Kalman filtering with recursive least squares. The simulation results verify that the proposed sliding mode control algorithm has strong stability and can effectively suppress the vibration of flexible accessories, and its adjustment time is about 1/10 of PID control. Meanwhile, the proposed identification method has improved accuracy compared with traditional methods, and the identification error can be reduced to 4%. Furthermore, the analytic hierarchy process (AHP) is used to evaluate the effectiveness of the spacecraft simulation device proposed in this paper. The reliability of the simulation system is calculated to be 96.7%, which can be used as a verification platform for related algorithm research.

Abstract With the development of civil aviation, ground simulation test has gradually become a key link in the transformation of basic theory to engineering application. By forming a closed-loop link between the variable stability aircraft (VSA) dynamics model and the aircraft rudder surface, sensors, etc., the variable-stability ground closed-loop test system can simulate the aircraft flight state and response characteristics in the ground environment. However, the current ground test system suffers from a wide range of signals, complex signal simulation methods, and low system integration. In this study, an improved modular ground closed-loop test system for VSA is designed from three aspects: signal acquisition and simulation of airborne equipment, parameter monitoring and data processing, and fault simulation subsystem, which improves its compatibility and integrates with the software hardware of the variable-stability flight control computer and other air-borne equipment. After the system interconnection test, the generalized ground closed-loop test system designed in this study can replace the original system more efficiently, and its signal connection has inheritability, and provides a design method reference for other related researches of the variable-stability flight control computer. 

Design of Improved Ground Closed-loop Test System Based on Variable-stability Flight Control Computer

In this paper, damage pre-cursors based residual life computation approach for various package elements to prognosticate electronic systems prior to appearance of any macro-indicators of damage has been presented. In order to implement the system-health monitoring system, precursor variables or leading indicators-of-failure have been identified for various package elements and failure mechanisms. Model-algorithms have been developed to correlate precursors with impending failure for computation of residual life. Package elements investigated include, first-level interconnects, dielectrics, chip interconnects, underfills and semiconductors. Examples of damage proxies include, phase growth rate of solder interconnects, intermetallics, normal stress at chip interface, and interfacial shear stress

Prognostics and Health Management of Electronics

In this paper, the design of the test case, the demand for the traction, the existing ground dynamics in the star dynamics, astronomical kinematics, gyro sensors, solar sensors, infrared globe sensors and star sensors to simplify the model, developed based on VxWorks satellite ground dynamics simulation software, the application of the simulation software and the AOCC simulator on the formation of closed-loop simulation system, and gives the ground dynamic model simulation results, the results show that the software design is reasonable, real-time, the results are correct, And the model can be configured, easy to expand, and the development of test technology play a positive role in promoting.

Design of Ground Dynamics Simulation Platform for Satellite Control Test

In this paper, the fault prediction method of spacecraft electrical equipment is studied with telemetry data. After analyzing the pattern of object fault and the law of telemetry data change, the fault prediction method of spacecraft electrical equipment based on telemetry data is proposed, and the application of the prediction method is analyzed. The results show that for short-term fault prediction, the short-term fault prediction with echo state network time series is better, and the average relative error of the prediction results is small. It can predict the changing trend of satellite telemetry parameters, and provide an effective tool for the management and decision of spacecraft in orbit.

Spacecraft Short-Term Fault Prediction Method Based on Echo State Network Time Series

The invention discloses a digital verification system and method for an electrical performance test case of a spacecraft. The system is composed of a test management platform, an interface adapter, asimulation verification platform, and a data subscription server. The test management platform is used for controlling execution of an electrical performance test case, generating an excitation signal, subscribing a telemetry parameter form the data subscription server, and outputting a testing result. The interface adapter is used for simulating ground test equipment, mapping the excitation signal to the simulation verification platform, and outputting an execution instruction that can be identified by the simulation verification platform. The simulation verification platform is used for simulating satellite equipment, decoding the execution instruction and performing the decoded instruction, and outputting the telemetry parameter. And the data subscription server is used for storing andbroadcasting the received telemetry parameter. Therefore, on the condition that no ground test equipment and satellite simulator are provided, digital simulation closed-loop verification of the electric performance test case is realized; the correctness and rationality of the electric performance test case design are verified; the design defect of the electrical performance test case can be foundout in advance and then can be improved; and thus the efficiency and safety of comprehensive spacecraft testing are improved.

Digital verification system and method for electrical performance test case of spacecraft

In order to obtain stable and high-precision motion tracking in mixed reality (MR) simulation of the complex system, an optical-inertial hybrid tracking method is proposed, which combines the accuracy of optical motion capture equipment and the robustness of inertial motion capture equipment, and can reduce the occlusion problem of entity scene on the premise of ensuring the localization accuracy. The method has been applied to the ergonomic evaluation of large civil aircraft development processes, and the effectiveness and usability of the method have been verified.

A human hybrid tracking and localization method for mixed reality simulation of complex system

In order to analyze the proposed method, this paper takes the cockpit as the complex system, since the traditional cockpit design evaluation method can set up an actual engineering prototype. Although this method can realize the accurate evaluation of the internal structure layout, control devices, and interface display of the cockpit, it is difficult to make modifications once the production is completed, which is not suitable for multi-scheme comparison and rapid iteration in the early stage of civil aircraft design. In this regard, this paper establishes the civil aircraft cockpit physical environment and the corresponding virtual cockpit environment based on the virtual-real matching technology, then proposes a mixed reality simulation evaluation method so as to realize the real-time ergonomic evaluation of the digital human body followed by a real person. Experimental results show that this mixed reality simulation evaluation method can effectively improve the evaluation accuracy of cockpit design, ensure the efficiency of multi-scheme comparison and optimization iteration in the early stage of cockpit design.

A mixed reality simulation evaluation method for complex system

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