Full-configuration real-time simulation test method based on double-satellite hardware in loop

A technology of real-time simulation and testing method, which is applied in the field of spacecraft engineering, and can solve problems such as the inability to complete real-time simulation testing of double stars

Active Publication Date: 2020-02-07
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

At present, the full-configuration real-time simulation test system of satellite hardware in the loop mainly uses a single sa

Method used

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  • Full-configuration real-time simulation test method based on double-satellite hardware in loop
  • Full-configuration real-time simulation test method based on double-satellite hardware in loop
  • Full-configuration real-time simulation test method based on double-satellite hardware in loop

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Embodiment

[0022] Such as figure 1 As shown, the method of the present invention is realized by a full-configuration real-time simulation test system, and the whole system is composed of two sets of completely identical satellite full-configuration real-time simulation test systems to form a dual real-time hardware-in-the-loop simulation test system, wherein each satellite real-time simulation system has It is composed of satellite orbit dynamics simulation model, satellite attitude dynamics model, satellite measurement stand-alone model, satellite execution stand-alone model, satellite control stand-alone model, signal processing box, simulated star service subsystem and real-time system cabinet with fully configured hardware equipment and power supply Composed of boxes and switches. Each dSPACE hardware system is equipped with IO boards, DA boards, AD boards, serial port cards, and bus cards. Among them, dSPACE is responsible for the calculation of satellite orbit and attitude dynamic...

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Abstract

The invention discloses a full-configuration real-time simulation test method based on double-satellite hardware in a loop. The method comprises the following steps: step 1, two sets of satellites respectively carry real-time simulation test systems; step 2, data communication mechanisms of the two sets of test systems perform communication interaction by using a fixed-period mutual transmission mode, one set of test system is used as a time sequence main control end, the other set of test system is used as a controlled end, and the controlled end receives a rising edge or a falling edge of amain control end signal to complete time correction work in a triggering mode; and step 3, a software time supplementing mode is used to ensure the time consistency of the track data, so that the timebetween the two sets of test systems is synchronized. According to the invention, the communication protocol interaction can be carried out through two modes of RS422 serial port communication or UDPnetwork port communication under an engineering constraint condition, and the formation test task of the double-satellite formation is completed through a time synchronization method.

Description

technical field [0001] The invention relates to the technical field of spacecraft engineering, in particular to a full-configuration real-time simulation test method based on dual-satellite hardware-in-the-loop, and more specifically, to a debugging method for a joint test platform of a hardware-in-the-loop real-time simulation system for two sets of satellite attitude and orbit control. Background technique [0002] Satellite attitude and orbit control system, as one of the most complex subsystems among many satellite subsystems, plays a very critical role in satellite control. At present, the simulation test work in the research and development stage of the satellite attitude and orbit control system is completed through the real-time satellite hardware-in-the-loop fully configured real-time simulation system to verify the integrity of the satellite attitude and orbit control performance and the reliability and safety of the flight mission. . Hardware-in-the-loop is an im...

Claims

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Application Information

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IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 王嘉轶王文妍杨盛庆崔佳完备何煜斌陈筠力刘美师朱郁斐
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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