CN-122016366-A - Automatic testing system for thermal response of spacecraft

CN122016366ACN 122016366 ACN122016366 ACN 122016366ACN-122016366-A

Abstract

The invention relates to the technical field of spacecraft assembly, in particular to an automatic testing system for thermal response of a spacecraft, which comprises a parameterized man-machine interaction module, an intelligent scheduling module, an acquisition module, an interpretation module and a judging module, wherein the parameterized man-machine interaction module is used for constructing a testing task model, the testing task model comprises the steps of pairing heating loops with corresponding temperature sensors in the spacecraft to determine thermal coupling relations of different heating loops, the intelligent scheduling module is used for distributing the heating loops without thermal coupling to the same testing group, controlling an electrothermal dual-control module to heat the heating loops in the current testing group, the acquisition module is used for acquiring the temperatures of all the temperature sensors in the spacecraft, the interpretation module is used for acquiring the net temperature rise of the current testing temperature sensors, and the interpretation module is used for calculating the temperature rise rate of the current testing temperature sensors and judging whether the current testing temperature sensors are communicated with the corresponding heating loops according to the temperature rise rate. The invention automatically identifies the misconnection and crosstalk between the heating loop and the temperature sensor by constructing a full-channel concurrency monitoring matrix and a thermal decoupling concurrency scheduling strategy.

Inventors

YU SHANMENG
CHEN HE
JIANG FAN
CUI YONGPENG
Leng Yuelun
LI XUECHAO
XU YANJUN
GUAN HONGYU
WANG HANG
DU CHUNPING

Assignees

中国科学院长春光学精密机械与物理研究所

Dates

Publication Date: 20260512
Application Date: 20260414

Claims (9)

1. The automatic testing system for the thermal response of the spacecraft is characterized by comprising a parameterized man-machine interaction module, an intelligent scheduling module, an electric heating double-control module, an acquisition module and an interpretation module; The parameterized man-machine interaction module is used for constructing a test task model, wherein the test task model comprises the steps of pairing a heating loop and corresponding temperature sensors in a spacecraft, and determining the thermal coupling relation of different heating loops; The intelligent dispatching module is used for distributing the heating loops without thermal coupling to the same test group, controlling the electric heating double-control module to heat the heating loops in the current test group, monitoring the cooling state of the heating loops in the current test group, and dispatching and testing the next test group if the current test group enters a natural cooling state; The acquisition module is used for acquiring the acquisition temperatures of all the temperature sensors in the spacecraft; The judging and reading module is used for correcting the interference of the environmental temperature fluctuation on the acquisition temperature of the temperature sensor to obtain the net temperature rise of the current test temperature sensor, calculating the temperature rise rate of the current test temperature sensor and judging whether the current test temperature sensor is communicated with the corresponding heating loop or not according to the temperature rise rate.
2. The spacecraft thermal response automatic test system according to claim 1, wherein hardware of the system comprises an upper computer and an automatic test equipment integrated cabinet, the parameterized man-machine interaction module, the intelligent scheduling module and the interpretation module are deployed on the upper computer, the electric heating double-control module and the acquisition module are deployed on the automatic test equipment integrated cabinet, and the automatic test equipment integrated cabinet comprises a program-controlled direct-current power supply, a multichannel relay and a full-channel acquisition instrument.
3. The automatic test system for thermal response of spacecraft according to claim 1, wherein all heating circuits are tested sequentially by the intelligent scheduling module or all heating circuits in the same test group are tested in parallel.
4. The automatic test system of thermal response of a spacecraft according to claim 1, wherein the interpretation module is further configured to scan the remaining temperature sensors except for the current temperature sensor in the spacecraft, and if a temperature sensor with a net temperature rise is found, determine whether there is a misconnection or cable crosstalk between the temperature sensor with the net temperature rise and the current temperature sensor.
5. The automatic test system of thermal response of a spacecraft of claim 2, wherein said programmable dc power supply is configured to power a heating circuit.
6. The automatic test system of thermal response of a spacecraft of claim 5, wherein the programmable direct current power supply is further used for reading current, the multichannel relay is used for controlling a switch of a heating loop in a test set, when the current of the heating loop is 0 or exceeds a preset threshold value, the multichannel relay cuts off a circuit, and when the programmable direct current power supply judges that the current of the heating loop is normal, the multichannel relay maintains power supply of the heating loop.
7. The automatic test system of thermal response of spacecraft according to claim 2, wherein the interpretation module processes the collected temperature of the temperature sensor by adopting a moving average filtering algorithm, the interpretation module sets a sliding time window with a length of 5, and at each sampling moment i, the collected temperatures of the moment i and the front and rear 2 sampling points are taken, and an average value of the 5 sampling points is calculated and is taken as the output temperature after the moment i is smoothed.
8. The automatic test system of spacecraft thermal response of claim 7, wherein said moving average filtering algorithm is expressed as: ; Wherein: the output temperature of the temperature sensor is filtered and smoothed for the ith sampling moment, The acquisition temperature of the temperature sensor at the kth sampling time is calculated and indexed.
9. The automatic test system of thermal response of a spacecraft of claim 8, wherein the rate of temperature rise is expressed as: ; wherein R i is the temperature rise rate of the ith sensor, dt is the sampling time interval, To provide a net temperature rise of the temperature sensor during the sampling interval, The temperature at the end of the sampling, T smooth(tend) -T smooth(tstart) ,T smooth(tend) , is the output temperature of the temperature sensor at the beginning of the sampling, T smooth(tstart) .

Description

Automatic testing system for thermal response of spacecraft Technical Field The invention belongs to the technical field of spacecraft assembly, and particularly relates to an automatic test system for thermal response of a spacecraft. Background In the assembly and vacuum thermal test stage of spacecraft (such as satellites, airships and deep space probes), the reliability verification of a thermal control subsystem is important. Spacecraft thermal control systems typically comprise a large number of active heating circuits (consisting of heating plates) and corresponding temperature sensors (e.g. thermistors, thermocouples). When running on the track, the temperature control computer controls the on-off of the corresponding heating loop according to the temperature data acquired by the sensor so as to maintain the temperature of the equipment within the index range. Therefore, during the ground test phase, it is necessary to strictly verify whether the physical correspondence between "heating circuit" and "temperature sensor" is correct (i.e. to verify that, when heating circuit A is in operation, sensor a does detect a temperature rise, but not sensor b). With the improvement of the complexity of the spacecraft, the number of single star heating circuits and sensors has been increased to hundreds or even thousands, and the wiring network is extremely complex, so that the problems of misplug of connectors, wrong definition of cables, internal short circuit and the like are very easy to occur. Currently, implementation schemes in industry mainly rely on manual testing or semi-automatic single point testing. And (3) manually testing, wherein a tester manually operates a power supply to start a certain heating loop, stares at data at a monitoring terminal by another person, observes which temperature sensor has a rising value, and manually records the result. The semi-automatic single-point test uses a handheld heating device to heat the sensor externally, and the host computer collects data, so that the method is mainly used for verifying whether the sensor is good or not, but not verifying the loop correspondence of the heater-sensor in the whole satellite. By utilizing a universal data acquisition instrument (such as Agilent 34970A) matched with a PC, although data display is realized, intelligent interpretation logic is lacking, and the point-to-point on-off can only be verified, so that the point-to-multiple misconnection crosstalk problem can not be effectively detected. Disclosure of Invention Therefore, the invention aims to provide a spacecraft thermal response automatic test system, which is used for monitoring all temperature sensors when a single loop is heated by constructing a full-channel concurrency monitoring matrix and a thermal decoupling parallel scheduling strategy, automatically identifying misconnection and crosstalk between the heating loop and the temperature sensors, automatically grouping based on thermal coupling relations of different heating loops, realizing multi-loop parallel test, eliminating interference of environmental temperature drift on the heating loop and realizing accurate interpretation. In order to achieve the above purpose, the technical scheme of the invention is realized as follows: The invention provides an automatic testing system for thermal response of a spacecraft, which comprises a parameterized man-machine interaction module, an intelligent scheduling module, an electric heating double-control module, an acquisition module and an interpretation module, wherein the parameterized man-machine interaction module is used for acquiring the thermal response of the spacecraft; The parameterized man-machine interaction module is used for constructing a test task model, wherein the test task model comprises the steps of pairing a heating loop and corresponding temperature sensors in a spacecraft, and determining the thermal coupling relation of different heating loops; The intelligent dispatching module is used for distributing the heating loops without thermal coupling to the same test group, controlling the electric heating double-control module to heat the heating loops in the current test group, monitoring the cooling state of the heating loops in the current test group, and dispatching and testing the next test group if the current test group enters a natural cooling state; the acquisition module is used for acquiring the acquisition temperatures of all the temperature sensors in the spacecraft; The judging and reading module is used for correcting the interference of the environmental temperature fluctuation on the acquisition temperature of the temperature sensor to obtain the net temperature rise of the current test temperature sensor, calculating the temperature rise rate of the current test temperature sensor and judging whether the current test temperature sensor is communicated with the corresponding heating loop or not according to the temperature rise