CN108062123B - Bus type for spacecraft thermal test is distributed temperature-controlling system - Google Patents
Bus type for spacecraft thermal test is distributed temperature-controlling system Download PDFInfo
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- CN108062123B CN108062123B CN201711389999.3A CN201711389999A CN108062123B CN 108062123 B CN108062123 B CN 108062123B CN 201711389999 A CN201711389999 A CN 201711389999A CN 108062123 B CN108062123 B CN 108062123B
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D23/00—Control of temperature
- G05D23/19—Control of temperature characterised by the use of electric means
- G05D23/20—Control of temperature characterised by the use of electric means with sensing elements having variation of electric or magnetic properties with change of temperature
Abstract
The invention proposes one kind to be distributed temperature-controlling system for spacecraft bus formula, Switching Power Supply including being located at space environment simulation external container, serial server, computer and several control temperature units composition inside container, it include bus inside control temperature unit inside container, electric connector, direct current transformation circuit, control unit, temperature sensor, electronic switch, film electric heater, heating tube, communication chip, the components such as toggle switch, wherein control unit is connect by electric connector with bus, bus voltage is converted to control unit operating voltage by direct current transformation circuit, control unit is according to the Current Temperatures of temperature sensor measurement, the duty ratio that should be exported is calculated by pid algorithm, control two groups of connecting and disconnecting of the circuit respectively by electronic switch, to drive heating tube to carry out thermostatic control to own temperature.Compared with prior art, system of the invention is more simple, and scalability is strong, and waveguide thermal control design can be greatly reduced in spacecraft thermal test, install, remove the workload on receiving, effective lifting test efficiency.
Description
Technical field
The invention belongs to spacecrafts, ground experiment of aircraft technical field, and in particular to arrive a kind of in test to test
It tests pipeline and carries out bus type segmentation high-precision control system.
Background technique
In spacecraft ground thermal vacuum test, heat balance test, generally require to test the performance of spacecraft, it is past
It is past to need to carry out various pipelines for testing microwave catheter, to be mainly used for spacecraft-testing microwave signal along program-controlled temperature
Export, import, generally section be rectangle 200mm aluminum metal tube be composed, need in test to its temperature control protect
Its temperature is demonstrate,proved at 0 DEG C or more to guarantee its signal transmission performance, but when satellite test starts, high-power signal can make its temperature
60 DEG C or more are risen very rapidly up to, needs to stop to its temperature control at this time again, after test stops, rapid drop in temperature needs herein
When reopen temperature control, prevent at a temperature below 0 DEG C, temperature control aluminium slot, test are also to have similar demand with water lines, are both needed to
To guarantee that its every section temperature meets test program requirement in spacecraft thermal test.
Currently, being generally comprised in spacecraft thermal test for the implementation steps of this kind of temperature control pipeline:
1. thermal design personnel calculate separately each section of pipeline and outside according to pipeline present position difference in experimental design
Heat exchange, be grouped as several section temperature sections, by taking microwave catheter as an example, general 3-6 sections of microwave catheter is a temperature control circuit,
And design corresponding heating sheet power, temperature measuring point position；
2. electrical fitting technology personnel pass through cable respectively to every root canal road sticking heating plates, thermocouple in test prepares
It draws outside container respectively；
3. observing and controlling temperature operator tests the response of heating sheet, thermocouple in test is implemented, temperature control journey is set
Sequence carries out in test temperature control as needed.
In this implementation method, that on the one hand tests every time has a large amount of repeated work, and on the other hand it is for money
The consumption in source is also larger, for the microwave channel formed with 30 sections of waveguides, needs 40 or so temperature controlling points and 4-5 temperature control
Circuit will largely occupy measurement, control device resource when microwave channel is more.As telecommunication satellite testing requirement amount is more next
It is bigger, it how by design reduction personnel, resource and the consumption of time must be solved the problems, such as in Future Spacecraft heat test
One of.
Therefore, design and invent it is a kind of for temperature control pipeline it is quick, easy implementation, simple bus type distribution temperature-controlling system
With positive realistic meaning.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of for quick, simple, easy to operate in spacecraft thermal test
Pipeline temperature-controlling system, reduce every time test thermal control circuit design, Denso implement, temperature control program configuration on personnel, the time and
Resource consumption, and there is good vacuum, low temperature adaptability, there is stronger scalability and reliability, be the survey of spacecraft
Examination provides stable temperature environment demand.
To solve the above problems, The technical solution adopted by the invention is as follows:
For spacecraft bus formula be distributed temperature-controlling system, including be located at space environment simulation external container Switching Power Supply,
Serial server, computer and several control temperature units composition inside container, wherein Switching Power Supply provides in bus
Power supply, computer read temperature data, setting temperature control parameter by serial server from bus；In container inside control temperature unit
Primary clustering includes that bus, electric connector, direct current transformation circuit, control unit, temperature sensor, electronic switch, thin-film electro add
Hot device, heating tube, communication chip, wherein control unit is connect by electric connector with bus, and bus is four-wire system, provides two
Bus voltage is converted to control unit operating voltage by root power cable and two communications cables, direct current transformation circuit, and control is single
Member is calculated the duty ratio of output by pid algorithm, is controlled respectively by electronic switch according to the Current Temperatures of temperature sensor measurement
Two groups of connecting and disconnecting of the circuit to drive heating tube to carry out thermostatic control to own temperature, while driving film electric heater to treat temperature control
Equipment carries out temperature control, and can maintain in test full pipeline along Cheng Wendu is predetermined value, and communication chip passes through the communication electricity in bus
Cable is connect with the serial server outside container.
Wherein, the controller of miniaturization can control part temperatures, and type can be the types such as MCU, FPGA, pass through
The data for reading Current Temperatures sensor, control current output power.
Wherein, temperature sensor measures the temperature of target, and type can be digital temperature sensor and (contain
DS18B20 etc.), it is also possible to thermocouple, platinum resistance is connected (as used) with dedicated measurement module.
Wherein, electric heater type includes the types such as film electric heater, heating tube, heater strip, ceramic heating plate, can be led to
It crosses heating tube to control the temperature of module itself, and temperature control pipeline isothermal degree is controlled by film electric heater；
Wherein, electronic switch driving circuit quick on-off to be to control the temperature of target, and the type of electronic switch includes but not
It is limited to field-effect tube, solid-state relay.
Wherein, all capacitors are tantalum capacitor, have resistance to low pressure ability, may operate under vacuum environment.
Bus type for spacecraft thermal test of the invention is distributed temperature-controlling system, can be greatly reduced in existing heat test
Process is designed and implemented for temperature control pipeline, there is stronger reliability and scalability, the test for being able to satisfy Future Satellite needs
It asks.
Detailed description of the invention
Fig. 1 is a kind of system schematic of the bus type distribution temperature-controlling system for spacecraft thermal test of the present invention；Wherein:
100 be control temperature unit, and 201 be a section temperature control pipeline, and 202 be the heating sheet of pipeline surface mount, and 203 be electric connector, 301,
302,303 be one group of electric connector through walls, and 304 be space environment simulation vessel flange, and 401 be Switching Power Supply, and 402 take for serial ports
Business device, 403 Ethernets, 404 be Measurement &control computer；
Wherein: it include: 101 inside control temperature unit 100 for control unit, 102 direct current transformation circuits, with power bus
114 are connected, voltage needed for being converted to control unit 101, and are transmitted by 111 supply lines, and 103-1,103-2 are temperature sensing
Device is connected to control unit by connecting line 113 and measures, and 104-1,104-2 are electronic switch, and 105 be heating tube, and 106
Be communication chip for toggle switch, 108, connect by 107 communication interfaces with 101 control units, and by cable 112 with communicate
Bus 115 connects, and 109 be spi bus, is connected to debugging screen and key 110,116-1 and 116-2 are respectively the temperature control list
The electric connector for being included in member 100, respectively electric connector 116-1 ' and 116-2 ' connection corresponding with front-and-back unit.
If Fig. 2 is scheme of installation of the system on one section of microwave catheter；
Wherein: 201 be microwave catheter, and 202 be the film electric heating sheets of microwave catheter surface mount, and 100 is micro- to be installed on
Control temperature unit on waveguide, 116-1,116-2 are the electric connector of this control temperature unit, are connected respectively with correspondence unit
It connects.
If Fig. 3 is connection type of the system in a microwave catheter, wherein all microwave catheters join end to end, own
The electric connector 116-1 of control temperature unit is docked with 116-2, forms bus structures.
Specific embodiment
Referring to the drawings to the air velocity transducer calibration system under a kind of extremely low air pressure suitable for Mars etc. of the invention
Be described in detail, but this describe it is merely illustrative, it is no intended to protection scope of the present invention carry out any restrictions.
Figure .1 is a kind of system schematic of the bus type distribution temperature-controlling system for spacecraft thermal test of the present invention, in figure
100 be control temperature unit, and 201 be a section temperature control pipeline, and 202 be the heating sheet of pipeline surface mount, and 203 be electric connector, 301,
302,303 be one group of electric connector through walls, and 304 be space environment simulation vessel flange, and 401 be Switching Power Supply, and 402 take for serial ports
Business device, 403 Ethernets, 404 be Measurement &control computer.In a kind of typical embodiment, 100 control temperature units are made of metal box
Assembling structure is installed on above 201 pipelines, and 201 temperature control pipelines are by taking one section of microwave catheter as an example, long 200mm or so, 202 heating sheets
Kapton electric heater is chosen, model 150*10mm, 30 Ω are connected to control temperature unit by electric connector 203,
301,302,303 be one group of electric connector through walls, and model is respectively Y27-2237TKLW, Y27-2237ZJB4H, Y27-
2237TK1L can provide 37 effective channels on the basis of guaranteeing sealing, allow wherein 302 are fixed on vessel flange 305
9 groups of buses are through walls, i.e., the control temperature measurement and control of 9 waveguides (every usually with 10-40 sections of microwave catheters).401 open
Powered-down source is 100V, and the Switching Power Supply of maximum 10A or more can power for 60 sections or so of control temperature unit, meet test with whole
The temperature control requirement of waveguide.402 serial servers have 4 RS-485 interfaces, and single serial server can meet the survey of 4 buses
Temperature, control.404 computers are connect by 403 local area networks with 402 serial servers, can be carried out to the temperature of all microwave catheters
Display, storage, and (PID temperature control parameter, target temperature parameter etc.) is adjusted to temperature control parameter.
Wherein include: 101 inside control temperature unit 100 for control unit, can be the circuit of the types such as MCU, FPGA, 102
For direct current transformation (DCDC) circuit, it is connected with power bus 114, voltage needed for bus voltage being converted to control unit 101,
And transmitted by 111 supply lines, 103-1,103-2 are temperature sensor, can be the classes such as thermocouple, digital temperature sensor
Type is connected to control unit by connecting line 113 and measures, and 104-1,104-2 are electronic switch, can choose field-effect
The hardware such as pipe, solid-state relay, 105 be heating tube, and 106 be toggle switch, and 108 be communication chip, by 107 communication interfaces with
The connection of 101 control units, and connect by cable 112 with communication bus 115,109 be spi bus, is connected to debugging screen
And key 110,116-1 and 116-2 are respectively the electric connector for being included on the control temperature unit 100, respectively with front-and-back unit
Corresponding electric connector 116-1 ' and 116-2 ' connection.In a kind of typical embodiment, power bus 114 chooses 100V electricity
Pressure, data/address bus 115 choose RS485 communication protocol, and 101 control units choose ATmega2560 type MCU, and 102 choose
Bus voltage can be reduced to 5V to be transmitted to 101 controls via supply lines 111 by RA11005MD-15W type DCDC circuit by 100V
Unit.Temperature sensor 113-1,113-2 select DS18B20 digital temperature sensor, by connecting line 113 (VCC DATA
GND) it is connected to 101 control units (wherein including 4.7k Ω pull-up resistor inside connecting line).Electronic switch 104-1,104-2 choosing
IRF540 type field-effect tube is taken, on-off control can be carried out to the bus voltage of 100V by the on-off of 101 control unit pins,
105 are installed on inside temperature control unit, can be controlled by radiation, transmission of heat by contact mode the temperature of inside modules.106
6 toggle switch are selected, for the mailing address of each temperature control module to be arranged, 110 be debugging screen and key, provides base
Plinth parameter display capabilities, and module self-test, control two basic functions of temperature modification can be carried out by key, only make in troubleshooting
With needing to remove before test.108 be communication chip, and the operating voltage of 101 control units is converted to the work electricity of RS-485
Pressure selects MAX485 chip.116-1,116-2 are electric connector, and the working performance with vacuum-resistant, low temperature selects Y2-4TK
With Y2-4ZJ type electric connector, core 1,2 is respectively 100V and GND, and 3,4 be RS-485 bus.
In a typical embodiment, there is a computer, several Switching Power Supplies and serial server outside container,
It include several control temperature units for being installed on more temperature-controlled tube roads in container, wherein every temperature control pipeline can be divided into several segments, often
Duan Guanlu installs at least one control temperature unit and carries out temperature control, and all control temperature units of a temperature-controlled tube road successively join end to end shape
It at bus, is connect by one group of Switching Power Supply outside the electric connector and container on flange with serial server, all serial ports clothes
Business device is connected by Ethernet with computer, and computer can be read out the temperature of all control temperature units, and sets temperature control ginseng
Number.
In each test, since every section of pipeline carries out temperature control by temperature control circuit respectively, the design of control temperature unit has been examined
Consider suitable for most extreme hot-cool environment, has not needed thermal design personnel in each test and every section of thermal environment is divided respectively
Analysis, does not need to repartition temperature control segment；In test prepares, since temperature control module has had been provided with temperature element and plug, work
Artist person does not need Denso temperature sensor again, it is only necessary to which sticking heating plates are simultaneously connected to module, and successively by all temperature controls
Module joins end to end；In test is implemented, since the temperature of every section of temperature control pipeline is by each control temperature unit independent control, no
It needs to carry out program configuration and adjustment in external container.
If Fig. 2 is scheme of installation of the system on a microwave catheter, wherein 201 be microwave catheter, 202 be microwave
The film electric heating sheets that catheter surface is pasted, 100 be the control temperature unit being installed on microwave catheter, and 116-1,116-2 are this control
The electric connector of warm unit is attached with correspondence unit respectively.If Fig. 3 is the system in a long section microwave catheter
Connection type, all microwave catheters join end to end, and the electric connector 116-1 of all control temperature units is docked with 116-2, form bus
Structure.
By taking microwave catheter as an example, in test prepares, general flow is as follows:
1. respectively to every section of microwave catheter sticking heating plates, and welding contact pin (non-new operation microwave catheter can skip)；
2. installing temperature control module on microwave catheter, fixed with bolt, and heating sheet is connected by jack；
3. connecting the bolt between each section of microwave catheter；
4. connecting the electric connector between each microwave catheter temperature control module, each temperature control list is set gradually by toggle switch
The address of member (generally flange section is 1, and successively+1)；
5. flange section microwave catheter electric connector is connected to flange, Switching Power Supply, serial server and meter are installed outside container
Calculation machine, and tested.
In test run, the work-based logic of control temperature unit is as follows:
After 1. unit powers on, system is carried out first from responding, by on-off temperature sensor to field-effect tube and
The corresponding relationship of heating element.Setting default sends a deuterzooid to bus controlled at 20 DEG C, collection period 1S, every 6s
The temperature of module, computer terminal can be displayed and saved；
2. instruction change target temperature and pid parameter and switch control threshold value can be sent to 485 buses by computer；
3. temperature is when target temperature ± switch control threshold range (20 ± 4 DEG C of default) is outside, system power-on switch control
System, when in range, according to algorithm calculate separately P I D parameter, carry out PID control.When being lower than target temperature-threshold value, from
It is dynamic to be powered on maximum power, when being higher than target temperature+threshold value, automatically powers off, calculated automatically when in range with pid algorithm
PWM duty cycle, can work waveguide in temperature fly up, decline and quickly compensated.
Although the detailed description and description of the specific embodiments of the present invention are given above, it should be noted that
We can carry out various equivalent changes and modification to above embodiment according to the concept of the present invention, and generated function is made
It, should all be within protection scope of the present invention when with the spirit still covered without departing from specification and attached drawing.
Claims (5)
1. being distributed temperature-controlling system for spacecraft bus formula, Switching Power Supply, string including being located at space environment simulation external container
Mouth server, computer and several control temperature units inside container, wherein Switching Power Supply provides the power supply in bus,
Computer reads temperature data, setting temperature control parameter by serial server from bus；It is main inside control temperature unit in container
Component include bus, electric connector, direct current transformation circuit, control unit, temperature sensor, electronic switch, film electric heater,
Heating tube, communication chip, wherein control unit is connect by electric connector with bus, and bus is four-wire system, provides two confessions
Bus voltage is converted to control unit operating voltage, control unit root by electric wire cable and two communications cables, direct current transformation circuit
According to the Current Temperatures of temperature sensor measurement, the duty ratio of output is calculated by pid algorithm, controls two groups respectively by electronic switch
Connecting and disconnecting of the circuit to drive heating tube to carry out thermostatic control to own temperature, while driving film electric heater to treat temperature controlling instruments
Carry out temperature control, can maintain in test full pipeline along Cheng Wendu is predetermined value, communication chip by communication cable in bus with
Serial server connection outside container.
2. being distributed temperature-controlling system for spacecraft bus formula as described in claim 1, wherein the control unit of miniaturization is to portion
Part temperature is controlled, type MCU, FPGA, by read Current Temperatures sensor data, to current output power into
Row control.
3. being distributed temperature-controlling system for spacecraft bus formula as described in claim 1, wherein temperature of the temperature sensor to target
Degree measures, and type includes digital temperature sensor, thermoelectricity occasionally platinum resistance.
4. being distributed temperature-controlling system for spacecraft bus formula as described in claim 1, wherein electronic switch driving circuit is quick
For on-off to control the temperature of target, the type of electronic switch includes field-effect tube and solid-state relay.
5. being distributed temperature-controlling system for spacecraft bus formula as claimed in claim 4, wherein all capacitors are tantalum capacitor,
It works under vacuum environment.
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| CN201711389999.3A CN108062123B (en) | 2017-12-21 | 2017-12-21 | Bus type for spacecraft thermal test is distributed temperature-controlling system |
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| CN201711389999.3A CN108062123B (en) | 2017-12-21 | 2017-12-21 | Bus type for spacecraft thermal test is distributed temperature-controlling system |
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| CN108062123B true CN108062123B (en) | 2019-07-26 |
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| CN109878764A (en) * | 2019-02-28 | 2019-06-14 | 上海微小卫星工程中心 | A kind of mechanical, electrical and heating integrated satellite structure plate |
| CN111176349A (en) * | 2019-12-16 | 2020-05-19 | 北京空间机电研究所 | Space remote sensor temperature control system easy to expand |
| CN113900460A (en) * | 2021-10-25 | 2022-01-07 | 哈尔滨工大卫星技术有限公司 | Temperature control method, system and medium for satellite platform |
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| EP2832340A1 (en) * | 2013-08-02 | 2015-02-04 | Astrium GmbH | Insulating container device |
| RU2585613C2 (en) * | 2014-10-01 | 2016-05-27 | Акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" | Method for correction of intrinsic temperature dependence of silicon photoelectric converters |
| CN106467174B (en) * | 2015-08-10 | 2019-03-22 | 北京卫星环境工程研究所 | Large Spacecraft mechanism normal pressure temperature gradient pilot system |
| CN106608377B (en) * | 2015-10-22 | 2019-05-03 | 北京卫星环境工程研究所 | Data collection system for vacuum low-temperature environment |
| CN106184831B (en) * | 2016-06-29 | 2018-04-13 | 上海微小卫星工程中心 | Vacuum thermal test device for high heat flux density satellite |
| CN106647873B (en) * | 2016-07-20 | 2019-06-14 | 北京卫星环境工程研究所 | The suction wave Orbital heat flux simulation system temperature control method of Large Spacecraft antenna performance test |
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