Calibration data correction method for test cable in thermal vacuum test

A technology for thermal vacuum test and test cable, applied in the field of measurement, can solve the problems of test data deviation, test cable calibration can not reflect the real insertion loss and delay value, etc., to achieve the effect of wide application, improved test accuracy and simple principle

Inactive Publication Date: 2013-01-16
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

In this way, the calibration of the test cable under normal pressure cannot reflect the real insertion loss and delay values ​​under thermal vacuum, and these changes will cause deviations in the test data

Method used

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  • Calibration data correction method for test cable in thermal vacuum test
  • Calibration data correction method for test cable in thermal vacuum test

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Embodiment Construction

[0013] Such as figure 1 As shown, the correction method of the present invention includes a step of calibrating the test cable and the calibration cable, a step of installing the calibration cable, a step of dynamically measuring the insertion loss and output delay of the calibration cable, and a step of correcting the calibration data of the test cable.

[0014] (1) First select two cables with the same specifications, parameters and length as the test cable as the calibration cable, calibrate the test cable and the calibration cable at normal temperature and pressure, and obtain the insertion of the test cable and the calibration cable at the corresponding operating frequency loss and transmission delay;

[0015] Before the test cables are connected to the satellite, the insertion loss and signal transmission delay parameters of each test cable should be measured according to the operating frequency of each test cable. At this time, two calibration cables are added on the b...

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Abstract

The invention discloses a calibration data correction method for a test cable in a thermal vacuum test. Aiming at the fact that a calibration result of insertion loss and time delay of the test cable in a satellite thermal test under relatively normal pressure changes under a low temperature environment of a thermal vacuum tank, a cable of the same specification, parameter and length as those of the test cable is selected as a calibration cable, the insertion loss change and the time delay change of the calibration cable under a thermal vacuum environment are measured, thereby correcting the calibration data of the test cable under normal pressure; and the actual values of the insertion loss and the time delay of the satellite under different working environments in the thermal vacuum test are obtained by measuring so as to reflect actual data to the greatest extent. The method has a simple implementation principle; and the testing accuracy for power of each inlet of the satellite and time delay of a channel is improved. The method can be applied to input and output cables of other subsystems and other types of satellite repeaters or electronic equipment for correcting the calibration data, and is wide in application.

Description

technical field [0001] The invention relates to a method for correcting calibration data of a thermal vacuum test cable, in particular to a method for correcting calibration data of a navigation satellite payload thermal vacuum test cable, and belongs to the field of measurement technology. Background technique [0002] The navigation satellite payload includes antennas, multi-channel transponders, time-frequency subsystems, RNSS and other subsystems. For the multi-channel transponder applied to Beidou-1 and the RNSS load of Beidou-2, the electrical performance test needs to provide uplink signals to satellites and receive downlink broadcast signals from satellites. The receiving power and transmitting power level of the satellite payload, and the channel delay of the satellite receiving and transmitting signals are very important indicators and parameters of the navigation satellite. In order to ensure the safety of the satellite and accurately measure the performance of t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01R35/00
Inventor 刘庆军崔小准董海青王璐
Owner BEIJING INST OF SPACECRAFT SYST ENG
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