CN108062123A - Temperature-controlling system is distributed for the bus type of spacecraft thermal test - Google Patents
Temperature-controlling system is distributed for the bus type of spacecraft thermal test Download PDFInfo
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- CN108062123A CN108062123A CN201711389999.3A CN201711389999A CN108062123A CN 108062123 A CN108062123 A CN 108062123A CN 201711389999 A CN201711389999 A CN 201711389999A CN 108062123 A CN108062123 A CN 108062123A
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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
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- Automation & Control Theory (AREA)
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Abstract
The present invention proposes a kind of for spacecraft bus formula distribution temperature-controlling system, Switching Power Supply including being located at space environment simulation external container, serial server, computer and several control temperature units composition inside container, include bus inside container inside control temperature unit, 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 connected 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 cycle that should be exported by pid algorithm calculating, control two groups of connecting and disconnecting of the circuit respectively by electronic switch, heating tube to be driven 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 spacecraft, ground experiment of aircraft technical fields, and in particular to a kind of in test to experiment
It tests pipeline and carries out bus type segmentation high-precision control system.
Background technology
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 along program-controlled temperature various pipelines, exemplified by testing microwave catheter, it is mainly used for spacecraft-testing microwave signal
Export, import, the generally 200mm aluminum metal tubes of rectangular cross-section are composed, and need to protect its temperature control in test
Its temperature is demonstrate,proved at 0 DEG C or more to ensure 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 is, it is necessary to herein
When reopen temperature control, prevent that, 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 ensure that its every section temperature meets test program requirement in spacecraft thermal test.
At present, in spacecraft thermal test, generally comprised for the implementation steps of this kind of temperature control pipeline：
1. in experimental design, thermal design personnel are different according to pipeline present position, calculate each section of pipeline and outside respectively
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 plate power, temperature measuring point position；
2. in experiment prepares, electrical fitting technology personnel are respectively to every pipeline sticking heating plates, thermocouple, and pass through cable
It draws respectively outside container；
3. in experiment is implemented, observing and controlling temperature operating personnel test the response of heating plate, thermocouple, set temperature control journey
Sequence carries out in test temperature control as needed.
In this implementation, that on the one hand tests every time has substantial amounts of repeated work, and on the other hand it is for money
The consumption in source is also larger, it is necessary to the temperature controlling point of 40 or so and 4-5 temperature control for the microwave channel formed with 30 sections of waveguides
Circuit when microwave channel is more, will largely occupy measurement, control device resource.As telecommunication satellite testing requirement amount is more next
Bigger, how the consumption by designing reduction personnel, resource and time must be solved the problems, such as in Future Spacecraft heat test
One of.
Therefore, design and invent a kind of quick, easy implementation for being used for temperature control pipeline, simple bus type distribution temperature-controlling system
With positive realistic meaning.
The content 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 the design of experiment thermal control circuit, Denso every time implement, the personnel in the configuration of temperature control program, the time and
Resource consumption, and with 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 present 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 is provided in bus
Power supply, computer read temperature data from bus by serial server, set temperature control parameter；In container inside control temperature unit
Primary clustering includes bus, electric connector, direct current transformation circuit, control unit, temperature sensor, electronic switch, thin-film electro and adds
Hot device, heating tube, communication chip, wherein control unit are connected 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 cycle 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 heating tube to be driven to carry out thermostatic control to own temperature, while drive film electric heater to treat temperature control
Equipment carries out temperature control, and it along Cheng Wendu is predetermined value that can maintain in test full pipeline, and communication chip passes through communication in bus electricity
Cable is connected 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 of Current Temperatures sensor are read, current output power is controlled.
Wherein, temperature sensor measures the temperature of target, and type can be that digital temperature sensor (contains
DS18B20 etc.) or thermocouple, platinum resistance be connected (as use) with dedicated measurement module.
Wherein, electric heater type includes the types such as film electric heater, heating tube, heater strip, ceramic heating plate, can lead to
It crosses heating tube to control the temperature of module itself, and passes through film electric heater and temperature control pipeline isothermal degree is controlled；
Wherein, electronic switch driving circuit quick on-off is included but not with the temperature of control targe, the type of electronic switch
It is limited to field-effect tube, solid-state relay.
Wherein, all capacitances are tantalum capacitance, have resistance to low pressure ability, may operate under vacuum environment.
The bus type for spacecraft thermal test of the present 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 need of Future Satellite can be met
It asks.
Description of the drawings
Fig. 1 is a kind of system schematic of 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 plate of pipeline surface mount, and 203 be electric connector, 301,
302nd, 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：100 inside of control temperature unit includes：101 units in order to control, 102 direct current transformation circuits, with power bus
114 are connected, and are converted to voltage needed for control unit 101, and pass through the transmission of 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
It is communication chip for toggle switch, 108, is connected by 107 communication interfaces with 101 control units, and passes through cable 112 with communicating
Bus 115 connects, and 109 be spi bus, is connected to debugging screen and button 110,116-1 and 116-2 is respectively the temperature control list
The electric connector 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 mode 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 a kind of air velocity transducer calibration system suitable under the extremely low air pressures such as Mars of the present 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 the system schematic that a kind of bus type for spacecraft thermal test of the present invention is distributed temperature-controlling system, in figure
100 be control temperature unit, and 201 be a section temperature control pipeline, and 202 be the heating plate of pipeline surface mount, and 203 be electric connector, 301,
302nd, 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 plates
Kapton electric heater is chosen, model 150*10mm, 30 Ω are connected to control temperature unit by electric connector 203,
301st, 302,303 be one group of electric connector through walls, and model is respectively Y27-2237TKLW, Y27-2237ZJB4H, Y27-
2237TK1L wherein 302 is fixed on vessel flange 305,37 effective passages can be provided on the basis of ensureing to seal, are allowed
9 groups of buses are through walls, i.e., the control temperature measurement and control of 9 waveguides (every usually has 10-40 sections of microwave catheters).401 open
Powered-down source is 100V, and the Switching Power Supply of maximum more than 10A can power for 60 sections or so of control temperature unit, meet experiment 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 connected by 403 LANs with 402 serial servers, and the temperature of all microwave catheters can be carried out
Display, storage, and (PID temperature control parameters, target temperature parameter etc.) is adjusted to temperature control parameter.
Wherein 100 inside of control temperature unit includes：101 units in order to control, 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, bus voltage can be converted to voltage needed for control unit 101,
And passing through the transmission of 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
101 control units connect, and pass through cable 112 and be connected with communication bus 115, and 109 be spi bus, is connected to debugging screen
And button 110,116-1 and 116-2 are respectively the electric connector 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 protocols, and 101 control units choose ATmega2560 types MCU, and 102 choose
Bus voltage can be reduced to 5V by 100V and be transmitted to 101 controls via supply lines 111 by RA11005MD-15W type DCDC circuits
Unit.Temperature sensor 113-1,113-2 select DS18B20 digital temperature sensor, by connecting line 113 (VCC DATA
GND 101 control units (wherein including 4.7k Ω pull-up resistors inside connecting line)) are connected to.Electronic switch 104-1,104-2 are selected
IRF540 type field-effect tube is taken, break-make control can be carried out to the bus voltage of 100V by the break-make of 101 control unit pins,
105 are installed on inside temperature control unit, the temperature of inside modules can be controlled by radiation, transmission of heat by contact mode.106
6 toggle switch are selected, for setting the mailing address of each temperature control module, 110 be debugging screen and button, provides base
Plinth parameter display capabilities, and module self-test, control two basic functions of temperature modification can be carried out by button, only make in troubleshooting
With needing to remove before experiment.108 be communication chip, and the operating voltage of 101 control units is converted to the work electricity of RS-485
Pressure selects MAX485 chips.116-1,116-2 are electric connector, have vacuum-resistant, the working performance of low temperature, select Y2-4TK
With Y2-4ZJ type electric connectors, core 1,2 is respectively 100V and GND, and 3,4 be RS-485 buses.
In a typical embodiment, there is a computer, several Switching Power Supplies and serial server outside container,
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 sections, 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 join end to end shape successively
It into bus, is connected 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 experiment, 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, in each experiment thermal design personnel has been not required to divide respectively every section of thermal environment
Analysis, need not repartition temperature control segment；In experiment prepares, since temperature control module has had been provided with temperature element and plug, work
Artist person need not Denso temperature sensor again, it is only necessary to and sticking heating plates are simultaneously connected to module, and successively by all temperature controls
Module joins end to end；In experiment is implemented, since the temperature of every section of temperature control pipeline is by each control temperature unit independent control, no
It needs to configure and adjust into line program 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 is are installed on the control temperature unit on microwave catheter, and 116-1,116-2 are this control
The electric connector of warm unit is attached respectively with correspondence unit.In section microwave catheter being grown such as Fig. 3 one for the system
Connection mode, 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 experiment prepares, general flow is as follows：
1. respectively to every section of microwave catheter sticking heating plates, and weld contact pin (non-new operation microwave catheter can skip)；
It 2. installing temperature control module on microwave catheter, is fixed with bolt, and passes through jack and connect heating plate；
3. connect the bolt between each section of microwave catheter；
4. the electric connector between each microwave catheter temperature control module of connection, 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:
1. unit is after the power is turned on, system is carried out first from responding, by the break-make temperature sensor to field-effect tube and
The correspondence of heating element.Acquiescence is set controlled at 20 DEG C, collection period 1S, a deuterzooid is sent to bus every 6s
The temperature of module, computer terminal can be displayed and saved；
2. can instruction change target temperature and pid parameter and switch control threshold be sent to 485 buses by computer；
3. temperature is when target temperature ± switch control threshold scope (20 ± 4 DEG C of acquiescence) is outside, system power-on switch control
System, when in the range of, calculated respectively according to algorithm P I D parameters, carry out PID control.When being less than target temperature-threshold value, from
It is dynamic to be powered up with maximum power, it during higher than target temperature+threshold value, automatically powers off, in the range of when is calculated automatically with pid algorithm
PWM duty cycle, the temperature in can working waveguide fly up, decline and quickly compensated.
Although giving detailed description and explanation to the specific embodiment of the present invention above, it should be noted that
We according to the invention can conceive to carry out the above embodiment various equivalent changes and modification, and generated function is made
It, should all be within protection scope of the present invention during with the spirit still covered without departing from specification and attached drawing.
Claims (6)
1. temperature-controlling system is distributed 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 composition inside container, wherein, Switching Power Supply provides the confession in bus
Electricity, computer read temperature data from bus by serial server, set temperature control parameter；It is main inside control temperature unit in container
Component is wanted to include bus, electric connector, direct current transformation circuit, control unit, temperature sensor, electronic switch, film electrical heating
Device, heating tube, communication chip, wherein control unit are connected by electric connector with bus, and bus is four-wire system, provide two
Bus voltage is converted to control unit operating voltage, control unit by power cable and two communications cables, direct current transformation circuit
According to the Current Temperatures of temperature sensor measurement, the duty cycle of output is calculated by pid algorithm, two are controlled respectively by electronic switch
Group connecting and disconnecting of the circuit, heating tube to be driven to carry out thermostatic control to own temperature, while drives film electric heater to treat temperature control and sets
Standby to carry out temperature control, it along Cheng Wendu is predetermined value that can maintain in test full pipeline, and communication chip passes through the communication cable in bus
It is connected with the serial server outside container.
2. the controller the method for claim 1, wherein minimized can control part temperatures, type is
MCU, FPGA by reading the data of Current Temperatures sensor, control current output power.
3. the method for claim 1, wherein temperature sensor measures the temperature of target, type is number temperature
Degree sensor or thermocouple, platinum resistance are connected with measurement module.
4. the method for claim 1, wherein electric heater type include film electric heater, heating tube, heater strip,
Ceramic heating plate controls the temperature of module itself by heating tube, and passes through film electric heater to temperature control pipeline
Temperature is controlled.
5. the method for claim 1, wherein electronic switch driving circuit quick on-off is with the temperature of control targe, electricity
The type of sub switch includes but not limited to field-effect tube and solid-state relay.
6. the method for claim 1, wherein all capacitances are tantalum capacitance, work 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 CN108062123B (en) | 2019-07-26 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN106184831A (en) * | 2016-06-29 | 2016-12-07 | 上海微小卫星工程中心 | Vacuum thermal test device for high heat flux satellite |
| CN106467174A (en) * | 2015-08-10 | 2017-03-01 | 北京卫星环境工程研究所 | Large Spacecraft mechanism normal pressure thermograde pilot system |
| CN106608377A (en) * | 2015-10-22 | 2017-05-03 | 北京卫星环境工程研究所 | Data collection system for vacuum low-temperature environment |
| CN106647873A (en) * | 2016-07-20 | 2017-05-10 | 北京卫星环境工程研究所 | Temperature control method of wave-absorbing external heat flow simulation system for large-scale spacecraft antenna performance test |
-
2017
- 2017-12-21 CN CN201711389999.3A patent/CN108062123B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN106467174A (en) * | 2015-08-10 | 2017-03-01 | 北京卫星环境工程研究所 | Large Spacecraft mechanism normal pressure thermograde pilot system |
| CN106608377A (en) * | 2015-10-22 | 2017-05-03 | 北京卫星环境工程研究所 | Data collection system for vacuum low-temperature environment |
| CN106184831A (en) * | 2016-06-29 | 2016-12-07 | 上海微小卫星工程中心 | Vacuum thermal test device for high heat flux satellite |
| CN106647873A (en) * | 2016-07-20 | 2017-05-10 | 北京卫星环境工程研究所 | Temperature control method of wave-absorbing external heat flow simulation system for large-scale spacecraft antenna performance test |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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| CN108062123B (en) | 2019-07-26 |
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