System for testing wired measurement and control interface of deep space exploration surrounding device to lander

Abstract

The invention provides a system for testing a wired measurement and control interface of a deep space exploration surrounding device to a lander. The system comprises a main control module, an OC gate instruction receiving module, a voltage remote measurement simulation module, a thermistor simulation module, an RS422 communication simulation module, a heater simulation module and a power supply module. The OC gate instruction receiving module, the voltage remote measurement simulation module, the thermistor simulation module, the RS422 communication simulation module and the heater simulation module are all connected to the main control module; and the OC gate instruction receiving module, the voltage remote measurement simulation module, the thermistor simulation module, the RS422 communication simulation module and the heater simulation module are all connected to the power supply module. According to the invention, the function of the surround device to the lander wired measurement and control interface can be tested before the surround device is in butt joint with the lander electrical interface, the correctness of the interface and the coordination of information interaction are fully verified, and abnormal communication or potential safety hazards between the two devices caused by mismatching of the interfaces after the two devices are in butt joint are avoided.

Description

technical field [0001] The invention relates to the technical field of spacecraft testing, in particular to a test system for a wired measurement and control interface between a deep space exploration orbiter and a lander. Background technique [0002] In recent years, my country's aerospace industry has developed vigorously. In addition to near-Earth satellites, aerospace engineering has gradually expanded to the field of deep space probes. A typical composition of deep space probes includes orbiters and landers. After the launch of deep space probes, The two devices fly from the earth to the deep space planet in the form of a combination. After reaching the planet, the two devices are separated, and the orbiter orbits the planet, while the lander lands on the surface of the star. Before the separation of the two devices, there is a gap between the two devices. Tight electrical interface, the orbiter provides wired measurement and control interface, power supply and distribut...

AI Technical Summary

Problems solved by technology

Compared with near-Earth satellites, deep-space probes are quite different. Conventional near-Earth satellite test devices cannot effectively meet the test requirements for the interface between deep-space orbiters and landers.

[0004] The patent document with the publication number CN202189106U discloses a satellite low-frequency signal interface automatic test system, which is composed of a contact switching device, an oscilloscope, a digital multimeter, a monitoring computer, and an adapter cable. The monitoring computer, the contact switching device and the oscilloscope use Ethernet communication. , the monitoring computer and the multimeter adopt the USB-to-Ethernet communication method. After the contact switching device is connected to the on-board equipment correctly through the adapter cable, the monitoring computer sends instructions to the contact switching device, oscilloscope and multimeter respectively, and the contact switching device returns relay status information. The oscilloscope and multimeter return the test data of the on-board equipment, but this patent document does not have the test function of the wired measurement and control interface

The patent document with the publication number CN202085171U discloses a general-purpose satellite-ground wired interface test system, including main test equipment, an interface adapter, a disconnected electrical connector interface cable, a CAN bus interface cable, and a connecting cable between devices; the disconnected electrical connector interface The cable and CAN bus interface cable are connected to the satellite satellite-ground wired interface, and the satellite wired test signal is transmitted to the interface adapter; the interface adapter performs signal interface conversion, and converts the satellite wired test signal into analog signal, RS-422 signal, and CAN bus The signal is output and transmitted to the main test equipment through the cable between the equipment; the main test equipment completes the acquisition, processing, analysis, storage and display of analog signals, RS-422 signals, and CAN bus signals, but this patent document does not have the scope of this patent. Heater simulation function, thermistor simulation function and OC gate command detection function

The patent document with the publication number CN103913672A discloses a satellite low-frequency interface automated test system, including a satellite low-frequency interface automated test platform and an interface automatic tester, and the satellite low-frequency interface automated test platform establishes a test process and a test form for the satellite low-frequency interface to be tested According to the test process, send control instructions to the interface automatic tester connected to the satellite low-frequency interface to be tested, and receive the test data returned by the interface automatic tester; the satellite low-frequency interface automatic test platform sends control instructions to the satellite master control system according to the test process Send remote control commands and receive telemetry data returned by the satellite master control system; after the satellite low-frequency interface automation test platform completes the test process, fill in the test results into the corresponding test form file, but this patent document does not have the wired measurement and control interface test function

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