CN113125182A - Spacecraft thermal test reference point thermal response test system - Google Patents
Spacecraft thermal test reference point thermal response test system Download PDFInfo
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- CN113125182A CN113125182A CN202110388574.0A CN202110388574A CN113125182A CN 113125182 A CN113125182 A CN 113125182A CN 202110388574 A CN202110388574 A CN 202110388574A CN 113125182 A CN113125182 A CN 113125182A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/002—Thermal testing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
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- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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Abstract
The application discloses a spacecraft thermal test reference point thermal response test system. The method comprises the following steps: the system comprises a control unit, a first information exchange unit, a data acquisition unit and a branching unit; the control unit is used as a main control unit, the selection, heating and temperature acquisition of a reference point are controlled in a communication connection mode, and the first information exchange unit is used as an information exchange medium between the control unit and the data acquisition unit; the connection between a field acquisition device and each reference point in the vacuum container is established through the branching unit, the branching unit receives a selection electric signal of the reference point to be detected, selects one reference point to be detected, performs heating operation, receives a temperature data acquisition electric signal through the data acquisition module, acquires temperature data, and transmits the acquired temperature data to the control unit for storage after being converted by the first information exchange unit; the method achieves the purposes of effectively verifying the correctness of the matching relation between the reference point platinum resistor and the thermocouple compensation end and guaranteeing the smooth performance of the spacecraft vacuum thermal test.
Description
Technical Field
The disclosure generally relates to the technical field of spacecraft and aircraft ground tests, in particular to a thermal test reference point thermal response test system for a spacecraft.
Background
The thermocouple temperature measuring system is widely applied to temperature measurement of spacecraft vacuum thermal test, wherein a single wire system is generally adopted to lead out thermocouple wires from a vacuum container, namely, each group of temperature measuring points are connected together by adopting a common lead method, and the cathodes of each group of thermocouples are led to a common reference point and then led to a measuring instrument.
At present, a method of setting a common reference point in a vacuum container is adopted in a vacuum thermal test, a built-in temperature reference point device is generally a copper cylinder, a hole is formed in the middle of the cylinder, and a thermocouple at the reference point end and a platinum resistor for temperature measurement are placed in the hole; the built-in temperature reference point device is an extremely important tool in a vacuum thermal test, and has great influence on the accuracy of temperature test data and the safety of products. At present, before starting up in a test, a reference point device is in a normal temperature environment, and the temperature of the reference point device is changed without means, so that the following steps cannot be verified: and (4) the correctness of the matching relation between the platinum resistor and the thermocouple compensation end is referenced. The correctness of the welding relationship of the thermocouple compensation end, such as the reverse welding of the platinum resistor at the reference point or the reverse welding of the thermocouple compensation end, may cause errors in a large number of thermocouple temperature measurement data. Therefore, a thermal response test system of a thermal test reference point of a spacecraft is provided to solve the problem that the accuracy of the matching relationship between the platinum resistor of the reference point and the thermocouple compensation end cannot be verified due to the fact that the temperature of the reference point is not adjustable.
Disclosure of Invention
In view of the above defects or shortcomings in the prior art, it is desirable to provide a thermal response test system for a reference point of a thermal test of a spacecraft, which effectively verifies the correctness of the matching relationship between a platinum resistor of the reference point and a thermocouple compensation end, ensures that the vacuum thermal test of the spacecraft is smoothly performed, has a good interpersonal interaction interface, is good in universality, is simple to operate, and is easy to implement.
In a first aspect, the present application provides a spacecraft thermal test reference point thermal response test system, including: the system comprises a control unit, a first information exchange unit, a data acquisition unit and a branching unit;
the control unit is used for sending a reference point selection instruction to be detected, controlling the selected reference point to perform heating operation at the same time, and sending a temperature data acquisition instruction;
the first information exchange unit is used for converting the reference point selection instruction to be detected into a reference point selection electric signal to be detected and converting the temperature data acquisition instruction into a temperature data acquisition electric signal;
the data acquisition unit is used for receiving the temperature data acquisition electric signal and acquiring the temperature data of the selected reference point;
the branching unit is respectively connected with the heating loop and the measuring loop of each reference point to be measured, and is used for receiving the selection electric signal of the reference point to be measured and selecting one reference point to be measured;
the first information exchange unit is also used for receiving the acquired temperature data, converting the acquired temperature data into a temperature data electric signal and sending the temperature data electric signal to the control unit;
the control unit is also used for receiving and storing the temperature data electric signal.
According to the technical scheme provided by the embodiment of the application, the control unit comprises: the device comprises a main control module, a processing module, a heating unit and a measuring unit;
the main control module is used for sending a reference point selection instruction to be detected, heating the selected reference point and sending a temperature data acquisition instruction;
the processing module is used for dividing the reference point selection instruction to be detected, the heating operation instruction and the temperature data acquisition instruction into a selection heating instruction and a temperature acquisition instruction;
the heating unit is used for executing a heating instruction, selecting a reference point and then performing heating operation;
the measuring unit is used for receiving a temperature acquisition instruction and acquiring temperature data;
the processing module is also used for receiving temperature data and transmitting the temperature data to the main control module;
the main control module is also used for receiving and storing the temperature data.
According to the technical scheme provided by the embodiment of the application, the heating unit comprises: the switch switching module and the power supply module;
the switch switching module is connected with the heating loop and used for receiving a heating selection instruction and selecting a reference point;
and the power supply module is used for supplying power to the processing module and providing heating energy for the selected reference point.
According to the technical scheme provided by the embodiment of the application, the power module is connected with a commercial power interface module and is used for inputting power frequency alternating current to the power module.
According to the technical scheme provided by the embodiment of the application, the measuring unit comprises: the protocol conversion module and the temperature inspection module;
the protocol conversion module is used for converting the temperature acquisition instruction into an acquisition instruction with the same communication protocol as the temperature patrol inspection module;
the temperature inspection module is used for receiving an acquisition instruction and acquiring temperature data of the selected reference point;
the protocol conversion module is also used for converting the temperature data into the temperature data with the same communication protocol as the processing module.
According to the technical scheme provided by the embodiment of the application, the control unit is further provided with a display module for displaying the temperature data of each reference point in real time.
According to the technical scheme provided by the embodiment of the application, the method further comprises the following steps: the remote control unit is in communication connection with the first information exchange unit;
and the remote control unit is used for remotely controlling the selection and heating of the reference point to be measured and the corresponding temperature data acquisition.
According to the technical scheme provided by the embodiment of the application, the remote control unit comprises: the second information exchange unit, the acquisition control module and the monitoring control module;
the acquisition control module is used for sending a heating selection instruction and a temperature acquisition instruction;
the second information exchange unit is used for transmitting a temperature acquisition instruction to the first information exchange unit and receiving temperature data transmitted by the first information exchange unit;
and the monitoring control module is used for receiving and storing the temperature data.
In conclusion, the technical scheme specifically discloses a specific process of a thermal test reference point thermal response test system of a spacecraft. The method specifically uses a control unit as a main control unit, controls selection, heating and temperature acquisition of a reference point in a communication connection mode, and uses a first information exchange unit as an information exchange medium between the control unit and a data acquisition unit; the connection between a field acquisition device and each reference point in the vacuum container is established through a branching unit, the field acquisition device is respectively connected with a heating loop and a measuring loop of each reference point to be detected, the field acquisition device receives an electric signal selected by the reference point to be detected, one reference point to be detected is selected for heating operation, a data acquisition module is used for receiving a temperature data acquisition electric signal and acquiring temperature data, and the acquired temperature data is converted by a first information exchange unit and then transmitted to a control unit for storage; the method achieves the purposes of effectively verifying the correctness of the matching relation between the reference point platinum resistor and the thermocouple compensation end and guaranteeing the smooth performance of the spacecraft vacuum thermal test.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
FIG. 1 is a schematic flow chart of a thermal response field work of a spacecraft thermal test reference point.
Fig. 2 is a schematic flow chart of the control unit.
Fig. 3 is a schematic diagram of a connection relationship between the branching unit and the reference point to be measured.
Fig. 4 is a layout diagram of a display module.
Fig. 5 is a layout diagram of each interface of the control unit.
Reference numbers in the figures: 1. a control unit; 2. a first information exchange unit; 3. a data acquisition unit; 4. a branching unit; 5. a main control module; 6. a processing module; 7. a switch switching module; 8. a power supply module; 9. a mains supply interface module; 10. a protocol conversion module; 11. a temperature polling module; 12. a display module; 13. a remote control unit; 14. a second information exchange unit; 15. an acquisition control module; 16. and monitoring the control module.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Example one
Please refer to fig. 1, which illustrates a schematic flow chart of a spacecraft thermal test reference point thermal response test system provided in the present application, including: the system comprises a control unit 1, a first information exchange unit 2, a data acquisition unit 3 and a branching unit 4;
the control unit 1 is used for sending a reference point selection instruction to be detected, controlling the selected reference point to perform heating operation at the same time, and sending a temperature data acquisition instruction;
the first information exchange unit 2 is used for converting the reference point selection instruction to be detected into a reference point selection electric signal to be detected and converting the temperature data acquisition instruction into a temperature data acquisition electric signal;
the data acquisition unit 3 is used for receiving the temperature data acquisition electric signal and acquiring the temperature data of the selected reference point;
the branching unit 4 is connected with the heating loop and the measuring loop of each reference point to be measured respectively, and is used for receiving the selection electric signal of the reference point to be measured and selecting one reference point to be measured;
the first information exchange unit 2 is further configured to receive the acquired temperature data, convert the acquired temperature data into a temperature data electric signal, and send the temperature data electric signal to the control unit 1;
the control unit 1 is further configured to receive and store the temperature data electrical signal.
In this embodiment, as shown in fig. 1, the control unit 1, as a main control unit, can control selection, heating, temperature acquisition, and the like of the reference point through a communication connection manner, and store corresponding acquired data, specifically, send a reference point selection instruction to be measured, and at the same time, control the selected reference point to perform a heating operation, and send a temperature data acquisition instruction; the device is also used for receiving the collected temperature data electric signals, storing the temperature data and filing the temperature data as a preparation file of the vacuum thermal test and control system; a control unit 1, for example, a control box integrating a plurality of modules;
the first information exchange unit 2 is used for completing information exchange between the control unit 1 and the data acquisition unit 3, specifically, converting a reference point selection instruction to be detected into a reference point selection electric signal to be detected, converting a temperature data acquisition instruction into a temperature data acquisition electric signal, and transmitting each signal to the data acquisition unit 3; the temperature sensor is also used for receiving the acquired temperature data, converting the temperature data into a temperature data electric signal and transmitting the temperature data electric signal to the control unit 1; here, the type of the first information exchange unit 2 is, for example, a switch, and its model is, for example, H3C S5130S-28P-EI;
the data acquisition unit 3 is used for receiving the temperature data acquisition electric signal and acquiring the temperature data of the selected reference point; here, the type of the data acquisition unit 3 is, for example, a UX100-001 temperature collector;
the branching unit 4 can establish the connection between the field acquisition device and each reference point in the vacuum container, is respectively connected with the heating loop and the measuring loop of each reference point to be measured, and is used for receiving the selection electric signal of the reference point to be measured and selecting one reference point to be measured; the data acquisition unit 3 is also used for acquiring temperature;
as shown in fig. 3, a heating sheet is adhered to the outer surface of the main structure of the reference point device, a platinum resistor is arranged in the heating sheet, and a power module applies a certain current to the heating sheet to raise the temperature in the reference point cavity, so as to achieve the purpose of heating.
In any preferred embodiment, the control unit 1 comprises: the device comprises a main control module 5, a processing module 6, a heating unit and a measuring unit;
the main control module 5 is used for sending a reference point selection instruction to be detected, heating the selected reference point and sending a temperature data acquisition instruction;
the processing module 6 is used for dividing the reference point selection instruction to be detected, the heating operation instruction and the temperature data acquisition instruction into a selection heating instruction and a temperature acquisition instruction;
the heating unit is used for executing a heating instruction, selecting a reference point and then performing heating operation;
the measuring unit is used for receiving a temperature acquisition instruction and acquiring temperature data;
the processing module 6 is further configured to receive temperature data and transmit the temperature data to the main control module 5;
and the main control module 5 is also used for receiving and storing the temperature data.
In this embodiment, as shown in fig. 2, the main control module 5 is configured to send a reference point selection instruction to be measured, perform heating operation on the selected reference point, and send a temperature data acquisition instruction; the temperature data is also used for receiving and storing; the type of the main control module 5 is, for example, an upper computer, and the model thereof is, for example, XJ-2016-;
the processing module 6 is used for dividing the reference point selection instruction to be detected, the heating operation instruction and the temperature data acquisition instruction into a selection heating instruction and a temperature acquisition instruction; the temperature acquisition module is also used for acquiring and receiving temperature data and transmitting the temperature data to the main control module 5; here, the type of the processing module 6 is, for example, a PLC controller, the model of which is, for example, KEYENCE MV-L40;
the heating unit is used for executing a selective heating instruction, selecting a reference point and then heating the selected reference point;
and the measuring unit is used for receiving the temperature acquisition instruction and acquiring temperature data.
In any preferred embodiment, the heating unit comprises: a switch switching module 7 and a power supply module 8;
the switch switching module 7 is connected with the heating loop and used for receiving a heating selection instruction and selecting a reference point;
and the power supply module 8 is used for supplying power to the processing module 6 and supplying heating energy to the selected reference point.
In this embodiment, the switch switching module 7 is connected to the heating loop, and configured to receive a selective heating instruction and select a reference point; here, the switch switching module 7 is of the type, for example, a relay;
and the power supply module 8 is used for supplying electric energy to the processing module 6 and supplying heating energy to the selected reference point, so that the temperature of the reference point is changed.
In any preferred embodiment, the power module 8 is connected to a commercial power interface module 9, and is configured to input power-frequency alternating current to the power module 8.
In this embodiment, the utility power interface module 9 is connected to the power module 8, and is configured to input power frequency ac power to the power module 8; and, it still patrols and examines module 11 with the temperature, patrols and examines module 11 for the temperature and provides the electric energy.
In any preferred embodiment, the measurement unit comprises: the protocol conversion module 10 and the temperature patrol module 11;
the protocol conversion module 10 is configured to convert the temperature acquisition instruction into an acquisition instruction having the same communication protocol as the temperature inspection module 11;
the temperature inspection module 11 is used for receiving an acquisition instruction and acquiring temperature data of the selected reference point;
the protocol conversion module 10 is further configured to convert the temperature data into temperature data having the same communication protocol as the processing module 6.
In this embodiment, the protocol conversion module 10 is configured to convert a received signal instruction into a signal instruction having a communication protocol the same as that of a next received module, and specifically, convert a temperature acquisition instruction into an acquisition instruction having a communication protocol the same as that of the temperature inspection module 11; the temperature data is also used for converting the temperature data into temperature data with the same communication protocol as the processing module 6; the type of the protocol conversion module 10 is, for example, GW-7472;
the temperature polling module 11 is used for receiving an acquisition instruction and acquiring temperature data of the selected reference point; here, the model of the temperature inspection module 11 is, for example, H23607.
In any preferred embodiment, the control unit 1 is further provided with a display module 12 for displaying the temperature data of each reference point in real time.
In this embodiment, as shown in fig. 4, a display module 12 is disposed on the control unit 1 and configured to display temperature data of each reference point in real time; the display module 12 is positioned on the front panel of the control box and can also display the state of the temperature inspection module 11, 3 instrument switches are arranged on the display module, the left side of the digital display surface board respectively displays a current value and a temperature value, and the right side of the digital display surface board is provided with a channel indicator lamp;
as shown in FIG. 5, the rear panel of the control box is provided with 1Y 27A-2455ZJBW plug, 1 LAN port, 1 AC220V input, 1 fan port and 1 safety guard
In any preferred embodiment, further comprising: a remote control unit 13 in communication connection with the first information exchange unit 2;
and the remote control unit 13 is used for remotely controlling the selection and heating of the reference point to be measured and the corresponding temperature data acquisition.
In this embodiment, as shown in fig. 1, the remote control unit 13 is in communication connection with the first information exchange unit 2, and is configured to remotely control selection and heating of the reference point to be tested and corresponding temperature data acquisition, so that the reference point thermal response test can be performed not only in the field, but also in a remote control manner.
In any preferred embodiment, the remote control unit 13 comprises: a second information exchange unit 14, an acquisition control module 15 and a monitoring control module 16;
the acquisition control module 15 is used for sending a selective heating instruction and a temperature acquisition instruction;
the second information exchange unit 14 is configured to transmit a temperature acquisition instruction to the first information exchange unit 2, and receive temperature data transmitted by the first information exchange unit 2;
and the monitoring control module 16 is used for receiving and storing the temperature data.
In this embodiment, as shown in fig. 1, the acquisition control module 15 is configured to send a selective heating instruction and a temperature acquisition instruction; here, the type of the acquisition control module 15 is, for example, an acquisition computer;
the second information exchange unit 14 is configured to transmit a temperature acquisition instruction to the first information exchange unit 2, and receive temperature data transmitted by the first information exchange unit 2; here, the type of the second information exchange unit 14 is, for example, a switch, and its model is, for example, H3C S5130S-28P-EI;
the monitoring control module 16 is used for receiving and storing the temperature data; here, the monitoring control module 16 is of the type, for example, a monitoring computer.
The specific working process of the system is as follows:
before the system is started, the test equipment interface cable is connected, as shown in fig. 1, the reference point device in the vacuum container is connected to the external branching unit of the vacuum container through the cable, and the PLC communicates with the upper computer of the control box through the Ethernet. Before testing, a local/remote selection knob on a control box is turned to be remote, an upper computer selects a certain reference point as a current test point, and a heating loop of the upper computer is heated by a power supply module; the PLC is used for controlling the relay, switching each heating loop and supplying power to the three heating loops respectively; the reference point device is powered up through a cable, the temperature value acquired by the temperature polling instrument is read, and the temperature polling instrument transmits temperature data to the PLC through the protocol conversion module and then transmits the temperature data to the upper computer through the Ethernet; the system automatically generates a test result report, stores and prints the test result, and the report is used as a preparation file of the vacuum thermal test control system for filing.
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by a person skilled in the art that the scope of the invention as referred to in the present application is not limited to the embodiments with a specific combination of the above-mentioned features, but also covers other embodiments with any combination of the above-mentioned features or their equivalents without departing from the inventive concept. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.
Claims (8)
1. A spacecraft thermal test reference point thermal response test system, comprising: the system comprises a control unit (1), a first information exchange unit (2), a data acquisition unit (3) and a branching unit (4);
the control unit (1) is used for sending a reference point selection instruction to be detected, controlling the selected reference point to perform heating operation and sending a temperature data acquisition instruction;
the first information exchange unit (2) is used for converting the reference point selection instruction to be tested into a reference point selection electric signal to be tested and converting the temperature data acquisition instruction into a temperature data acquisition electric signal;
the data acquisition unit (3) is used for receiving the temperature data acquisition electric signal and acquiring the temperature data of the selected reference point;
the branching unit (4) is respectively connected with the heating loop and the measuring loop of each reference point to be measured, and is used for receiving the selection electric signal of the reference point to be measured and selecting one reference point to be measured;
the first information exchange unit (2) is also used for receiving the acquired temperature data, converting the acquired temperature data into a temperature data electric signal and sending the temperature data electric signal to the control unit (1);
the control unit (1) is also used for receiving and storing the temperature data electric signal.
2. A spacecraft thermal test reference point thermal response test system according to claim 1, characterized in that the control unit (1) comprises: the device comprises a main control module (5), a processing module (6), a heating unit and a measuring unit;
the main control module (5) is used for sending a reference point selection instruction to be detected, heating the selected reference point and sending a temperature data acquisition instruction;
the processing module (6) is used for dividing the reference point selection instruction to be detected, the heating operation instruction and the temperature data acquisition instruction into a selection heating instruction and a temperature acquisition instruction;
the heating unit is used for executing a heating instruction, selecting a reference point and then performing heating operation;
the measuring unit is used for receiving a temperature acquisition instruction and acquiring temperature data;
the processing module (6) is also used for receiving temperature data and transmitting the temperature data to the main control module (5);
the main control module (5) is also used for receiving and storing temperature data.
3. A spacecraft thermal test reference point thermal response test system according to claim 2, wherein the heating unit comprises: a switch switching module (7) and a power supply module (8);
the switch switching module (7) is connected with the heating loop and used for receiving a heating selection instruction and selecting a reference point;
the power supply module (8) is used for supplying power to the processing module (6) and providing heating energy for the selected reference point.
4. The spacecraft thermal test reference point thermal response test system according to claim 3, wherein the power module (8) is connected with a mains supply interface module (9) for inputting power frequency alternating current to the power module (8).
5. A spacecraft thermal test reference point thermal response test system according to claim 2, wherein the measurement unit comprises: the protocol conversion module (10) and the temperature patrol module (11);
the protocol conversion module (10) is used for converting the temperature acquisition instruction into an acquisition instruction with the same communication protocol as that of the temperature inspection module (11);
the temperature inspection module (11) is used for receiving an acquisition instruction and acquiring temperature data of the selected reference point;
the protocol conversion module (10) is also used for converting the temperature data into the temperature data with the same communication protocol as the processing module (6).
6. A spacecraft thermal test reference point thermal response test system according to claim 1, characterized in that the control unit (1) is further provided with a display module (12) for displaying temperature data of each reference point in real time.
7. The spacecraft thermal test reference point thermal response test system of claim 1, further comprising: a remote control unit (13) in communication connection with the first information exchange unit (2);
and the remote control unit (13) is used for remotely controlling the selection and heating of the reference point to be measured and the corresponding temperature data acquisition.
8. A spacecraft thermal test reference point thermal response test system according to claim 7, characterized in that the remote control unit (13) comprises: a second information exchange unit (14), an acquisition control module (15) and a monitoring control module (16);
the acquisition control module (15) is used for sending a selective heating instruction and a temperature acquisition instruction;
the second information exchange unit (14) is used for transmitting a temperature acquisition instruction to the first information exchange unit (2) and receiving temperature data transmitted by the first information exchange unit (2);
and the monitoring control module (16) is used for receiving and storing the temperature data.
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| CN202110388574.0A CN113125182A (en) | 2021-04-12 | 2021-04-12 | Spacecraft thermal test reference point thermal response test system |
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| CN202110388574.0A CN113125182A (en) | 2021-04-12 | 2021-04-12 | Spacecraft thermal test reference point thermal response test system |
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