CN113900460A - Temperature control method, system and medium for satellite platform - Google Patents
Temperature control method, system and medium for satellite platform Download PDFInfo
- Publication number
- CN113900460A CN113900460A CN202111243372.3A CN202111243372A CN113900460A CN 113900460 A CN113900460 A CN 113900460A CN 202111243372 A CN202111243372 A CN 202111243372A CN 113900460 A CN113900460 A CN 113900460A
- Authority
- CN
- China
- Prior art keywords
- temperature
- control module
- thermal control
- single machine
- temperature control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 238000000034 method Methods 0.000 title claims abstract description 25
- 238000010438 heat treatment Methods 0.000 claims abstract description 48
- 230000003993 interaction Effects 0.000 claims abstract description 3
- 239000000126 substance Substances 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 4
- 238000009529 body temperature measurement Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
Images
Classifications
-
- 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
- G05D23/24—Control of temperature characterised by the use of electric means with sensing elements having variation of electric or magnetic properties with change of temperature the sensing element having a resistance varying with temperature, e.g. a thermistor
Abstract
The embodiment of the invention discloses a temperature control method, a system and a medium for a satellite platform; the system comprises: the temperature control system comprises a temperature main controller, a communication bus and a power supply bus which are extended from the temperature main controller, and thermal control modules which are correspondingly installed with a single machine needing temperature control, wherein each thermal control module realizes communication interaction with the temperature main controller through the communication bus and the power supply bus, and can be selectively coupled to at least one thermistor and/or at least one heating belt which are installed on the corresponding single machine; the temperature main controller is configured to issue the temperature control range of the corresponding single machine to each thermal control module through the communication bus; a thermal control module configured to receive a temperature control range of a corresponding stand-alone machine based on a communication bus; acquiring a temperature value corresponding to the single machine through a thermistor; and controlling the on-off state of the heating belt when the temperature value is not in the temperature control range.
Description
Technical Field
The embodiment of the invention relates to the technical field of space electronics, in particular to a temperature control method, a temperature control system and a temperature control medium for a satellite platform.
Background
In a satellite platform, the positions where temperature control is required are as high as hundreds, and the positions are distributed over each system single machine in the satellite, currently, a conventional temperature control scheme is to measure the temperature of each single machine device in the satellite by using a thermistor, and adaptively adopt a heat dissipation window to match with a heating band according to the requirement so as to control the single machine in the satellite and the whole temperature in the satellite to be in a proper range, and for the thermistor and the heating band, the thermistor and the heating band are usually connected to an independent thermal controller or a power supply controller integrated with the thermal controller. In embodying the above-described conventional scheme, each of the M thermistors and the N heating bands is connected to a thermal controller by a pair of connection lines, as an example, see fig. 1.
For an actual satellite platform, setting is only to meet basic temperature control requirements and does not need to fully understand the on-orbit temperature situation of each single machine, for example, only measuring the temperature of 1 to 2 temperature measuring points for each single machine, tens of thermistors and tens of heating belts need to be arranged, even if, based on the example shown in fig. 1, the number of connecting lines of the thermistors and the heating belts in the satellite platform usually reaches to hundreds. Moreover, the above setting example is only set for meeting the basic temperature control requirement, and according to statistics, in a certain type of satellite in orbit, 1/4 of the total number of the whole satellite power supply and low-frequency communication cables is used for the thermistor and the heating belt, so that the current temperature control scheme needs a larger number of connecting wire cables and is inconvenient to assemble.
In addition, the heating belt is usually designed according to the structural size of each single machine, and the model size of each single machine heating belt is different; and the thermistor usually needs to be mounted during the whole satellite assembly, and the corresponding relation between the thermistor, the circuit sequence of the heating belt and each single machine needs to be confirmed one by one during the assembly, so that great labor cost is brought, and meanwhile, the risk of manual operation errors is brought.
Disclosure of Invention
In view of the above, embodiments of the present invention are directed to a method, system, and medium for controlling temperature of a satellite platform; the temperature state in the satellite platform can be comprehensively controlled by measuring the temperature in the satellite and controlling the temperature through temperature control points as many as possible by using a small number of cables.
The technical scheme of the embodiment of the invention is realized as follows:
in a first aspect, an embodiment of the present invention provides a temperature control system for a satellite platform, where the temperature control system includes: the temperature control system comprises a temperature main controller, a communication bus and a power supply bus which are extended from the temperature main controller, and thermal control modules which are correspondingly installed with a single machine needing temperature control, wherein each thermal control module is communicated and interacted with the temperature main controller through the communication bus and the power supply bus, and can be selectively coupled to at least one thermistor and/or at least one heating belt which are installed on the corresponding single machine; wherein the content of the first and second substances,
the temperature main controller is configured to issue a temperature control range of a corresponding single machine to each thermal control module through the communication bus;
the thermal control module is configured to receive a temperature control range of a corresponding single machine based on the communication bus; acquiring a temperature value corresponding to the single machine through the thermistor; and when the temperature value is not in the temperature control range, controlling the on-off state of the heating belt.
In a second aspect, an embodiment of the present invention provides a temperature control method for a satellite platform, where the method is applied to the temperature control system for a satellite platform in the first aspect, and the method includes:
the temperature master controller sends the temperature control range of the corresponding single machine to each thermal control module through the communication bus; each thermal control module is correspondingly installed on a single machine needing temperature control, communication interaction between each thermal control module and the temperature main controller is realized through a communication bus and a power supply bus, and each thermal control module can be selectively coupled to at least one thermistor and/or at least one heating belt installed on the corresponding single machine;
the thermal control module receives the temperature control range of the corresponding single machine based on the communication bus;
the thermal control module acquires the temperature value of the corresponding single machine through the thermistor;
and when the temperature value is not in the temperature control range, the thermal control module controls the on-off state of the heating belt.
In a third aspect, an embodiment of the present invention provides a computer storage medium storing a temperature control program for a satellite platform, where the temperature control program for a satellite platform implements the steps of the temperature control method for a satellite platform according to the second aspect when executed by at least one processor.
The embodiment of the invention provides a temperature control method, a system and a medium for a satellite platform; the number of cables connected to the satellite-borne computer is reduced through a bus-based topological form, so that the temperature state in a satellite platform can be comprehensively controlled by utilizing a small number of cables through temperature measurement and temperature control points in the satellite as many as possible, and the workload and the error probability of the whole satellite assembly are reduced.
Drawings
FIG. 1 is a schematic topology diagram of a temperature control scheme for a satellite according to the conventional art;
fig. 2 is a schematic diagram illustrating a temperature control system for a satellite platform according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of another temperature control system for a satellite platform according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of another temperature control system for a satellite platform according to an embodiment of the present invention;
fig. 5 is a schematic flow chart of a temperature control method for a satellite platform according to an embodiment of the present invention.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.
For a complete satellite system, multiple subsystems are required to implement different tasks, and in some examples, the multiple subsystems may include a measurement and control subsystem, an integrated electronics subsystem, an attitude and flight trajectory control (hereinafter referred to as attitude and orbit control) subsystem, a power supply and distribution subsystem, and the like. Each subsystem may include one or more single devices, and in order to ensure the temperature environment for the on-orbit normal operation of the spacecraft, the temperature of the single devices in the on-orbit operation state needs to be controlled. In the conventional scheme, a plurality of thermistors and heating belts are arranged on each single-machine device according to the temperature control requirement, and are connected to an on-board computer serving as a temperature control main control end through connecting wires. According to the conventional scheme, the number of the thermistors and the heating belts is increased for the comprehensive sampling, so that the connecting wires connected to the satellite-borne computer are increased correspondingly, and the total number of cables of the satellite system is 1/4. Therefore, in order to reduce the number of cables used for realizing temperature control, the embodiments of the present invention desirably reduce the number of cables connected to the on-board computer through a bus-based topology, so that the temperature state in the satellite platform can be comprehensively controlled by using as many intra-satellite temperature measurements and temperature control points as possible with a smaller number of cables, and the workload and the error probability of the whole satellite assembly can be reduced.
Based on this, referring to fig. 2, a temperature control system 2 for a satellite platform according to an embodiment of the present invention is shown, where the temperature control system 2 includes: the temperature control system comprises a temperature main controller 21, a communication bus 22 extended from the temperature main controller 21 and a power supply bus 23, thermal control modules 24 installed corresponding to a single machine needing temperature control, wherein each thermal control module 24 is communicated and interacted with the temperature main controller 21 through the communication bus 22 and the power supply bus 23, and each thermal control module 24 can be selectively coupled to at least one thermistor 25 and/or at least one heating belt 26 installed on the corresponding single machine.
In some examples, the temperature master controller 21 may be embodied by an on-board computer on the satellite platform, and the communication bus 22 and the power supply bus 23 extend from the on-board computer. The thermal control modules 24 are installed corresponding to the stand-alone devices that need to be temperature-controlled, so that each thermal control module 24 corresponds to one stand-alone device on the satellite platform, and further, since the requirements of each stand-alone device for temperature control are different, only one thermistor 25 and one heating tape 26 may be installed for each stand-alone device; or only one thermistor 25, or only one heating tape 26, or a plurality of thermistors 25 and one heating tape 26, or one thermistor 25 and a plurality of heating tapes 26, or a plurality of thermistors 25 and a plurality of heating tapes 26 are mounted. It is to be understood that the number of the thermistors 25 and the heating tapes 26 is determined according to the temperature control requirement of the single-machine device, and the embodiment of the present invention is not limited thereto. After determining the number of thermistors 25 and heater strips 26 to be installed for each stand-alone device, each thermal control module 24 may be coupled to the thermistor 25 and/or heater strip 26 installed in the corresponding stand-alone device. For the components in fig. 1, specifically, the temperature master controller 21 is configured to issue a temperature control range of a corresponding single machine to each of the thermal control modules 24 through the communication bus 22;
the thermal control module 24 is configured to receive a temperature control range of the corresponding single machine based on the communication bus 22; acquiring the temperature value of the corresponding single machine through the thermistor 25; and controlling the on-off state of the heating belt 26 when the temperature value is not in the temperature control range.
For the above Specific example, the thermal control module 24 may have a control Processor inside for acquiring the temperature value represented by the thermistor 25 and controlling the on/off state of the heating tape 26, and the control Processor may be a general purpose Processor, a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field Programmable Gate Array (FPGA) or other Programmable logic device, a discrete Gate or transistor logic device, or a discrete hardware component. If a general purpose processor is used, it may be a microprocessor, or the processor may be any conventional processor or the like. In addition, in the implementation process, each thermal control module 24 has a communication address corresponding to the thermal control module, so that the temperature master controller 21 can access and communicate with the corresponding thermal control module 24 according to the communication address. In some examples, the communication address corresponding to each thermal control module 24 can be used by the temperature master controller 21 to issue a temperature control range of a corresponding stand-alone machine.
For the system shown in fig. 2, in some possible implementations, referring to fig. 3, the communication bus 22 includes a pair of communication signal lines, as indicated by a dashed box, and the power supply bus 23 includes a pair of power supply lines, as indicated by a dashed box; each of the thermal control modules 24 is connected to the communication signal line and the power line, respectively.
For the implementation shown in fig. 3, in a specific implementation process, the communication signal line may be a communication signal line meeting the RS485 standard. Based on the illustration in fig. 3, the number of cables extending from the temperature master controller 21, i.e. the satellite computer, is only 4, and each thermal control module is connected to the communication bus 22 and the power supply bus 23 through 4 connecting wires within the maximum number of access nodes allowed by the communication bus, so that the number of cables required for realizing the whole temperature control is no longer related to the number of thermistors and heating tapes, but is only related to the number of single devices required for temperature control, and the number of cables required for realizing the whole temperature control system is reduced; in addition, the thermal control module is connected through the bus, and the number of cables connected to the on-satellite computer is greatly reduced.
For the system shown in fig. 2, in some possible implementations, referring to fig. 4, the communication bus 22 still includes a pair of communication signal lines, as shown by the dashed box, and the power supply bus 23 still includes a pair of power supply lines, as shown by the dashed box; all the thermal control modules 24 are connected in series by the communication bus 22 and the power supply bus 23, and then coupled to the temperature master controller 21 through the primary thermal control module 24.
For the implementation shown in fig. 4, specifically, each thermal control module 24 connected in series may be provided with two end interfaces, a first end interface is connected to the upper-stage thermal control module 24, and a second end interface is connected to the lower-stage thermal control module 24. For the thermal control module 24 of the first stage, the first end interface thereof is connected to the onboard computer as the temperature main controller 21; as shown in fig. 4, the on-board computer as the temperature master controller 21 and the first-stage thermal control module are connected to each other through a pair of communication signal lines and a pair of power lines between the thermal control modules 24.
With respect to the foregoing solution, in some possible implementations, the thermistor 25 may be integrated inside the thermal control module 24, or connected to the thermal control module 24 through a short wire; the heating belt 26 is connected to the thermal control module 24 by short wires.
Based on the above implementation manner, the thermal control module, the thermistor and the heating tape can be integrated, and the thermal control module, the thermistor and the heating tape are assembled to the corresponding stand-alone equipment after the stand-alone equipment is delivered and before the whole satellite general assembly starts, so that when the whole satellite general assembly is performed, only the thermal control module needs to be connected to the communication bus and the power supply bus, and the communication address of the thermal control module 24 and the corresponding stand-alone equipment are recorded, in detail, automatic reading can be realized by using bar codes, two-dimensional codes and the like, and thus the communication address of the thermal control module 24 and the corresponding relation between the communication address and the stand-alone equipment are recorded in the onboard computer. The mounting of the thermistor and the heating belt is not required on site, the corresponding relation between the thermistor and the heating belt and the single machine equipment is not required to be confirmed, and the workload and the error probability of the whole satellite assembly stage are reduced
With regard to the foregoing technical solution, in some possible implementations, the temperature main controller 21 is further configured to: and reading the temperature value of each thermal control module 24 acquired by the corresponding single machine based on the set reading period, and telemetering and downloading the read temperature value to the ground station as the equipment temperature value on the satellite platform.
Compared with the conventional scheme, the temperature control system 2 set forth by the technical scheme greatly reduces the number of cables for temperature acquisition and control in the satellite. Taking the basic requirement for realizing the current situation as an example, for a satellite of 50 to 100kg grade, the number of thermistors is about 40, the number of heating belts is about 20, and considering the cable backup requirement, each heating belt needs 4 cables, so that the total number of the required cables is about 160. By adopting the temperature control system 2 explained in the technical scheme, under the same basic requirement condition, only 8 cables (namely 2 cables for each communication and power supply bus) are needed in consideration of cable backup requirements, and the number of the required cables is greatly reduced; and each communication bus can be connected with 256 thermal control module nodes at most, and each thermal control module node can be connected with 4-8 thermistors and 2-4 heating bands under the condition of controllable volume, so that the capability of acquiring the integral temperature state of the satellite is greatly improved. In addition, in the whole satellite assembling process of the satellite, required operations are greatly reduced, the corresponding relation of the thermistor, the heating belt and the single machine does not need to be manually confirmed on an assembling site, and the workload and the error probability during assembling are greatly reduced.
Based on the same inventive concept in the foregoing technical solution, referring to fig. 5, a temperature control method for a satellite platform is shown, which is provided in an embodiment of the present invention and is applied to the temperature control system for a satellite platform in the foregoing technical solution, where the method includes:
s501: the temperature master controller sends the temperature control range of the corresponding single machine to each thermal control module through the communication bus;
s502: the thermal control module receives the temperature control range of the corresponding single machine based on the communication bus;
s503: the thermal control module acquires the temperature value of the corresponding single machine through the thermistor;
s504: and when the temperature value is not in the temperature control range, the thermal control module controls the on-off state of the heating belt.
For the technical solution shown in fig. 5, the system shown in fig. 3 is taken as an example to be described in detail, for example, a pair of RS485 buses are adopted as the communication bus, and a pair of power lines are adopted as the power supply bus. All the thermal control modules are connected to the same bus, a control processor is arranged in each thermal control module, each thermal control module has a unique communication address, and a satellite computer serving as a temperature master controller can determine the corresponding thermal control module through the communication address and communicate with the thermal control module. A thermistor is integrated in the thermal control module, and the heating belt is arranged outside the thermal control module and is connected to the thermal control module through a short lead and a small-size connector. Each single-machine device needing temperature control is correspondingly provided with one thermal control module, and specifically, each thermal control module can be connected with more than one thermistor and/or heating belt according to the temperature control requirements of different single-machine devices.
Before the whole satellite final assembly stage, the thermal control module, the corresponding thermistor and the corresponding heating band can be installed on corresponding single-machine equipment in advance, and in the whole satellite final assembly process, the on-satellite computer which is used as the temperature master controller only needs to record the communication address of the thermal control module and the corresponding single machine.
When the system shown in fig. 3 is used to execute the solution shown in fig. 5, specifically, the on-board computer as the master temperature controller sends an instruction to the control processor of each thermal control module through the communication bus based on the communication address, where the instruction is used to set the temperature control range of the individual device corresponding to each thermal control module. The control processor of the thermal control module reads the resistance value of the thermistor and converts the resistance value into a temperature value according to the temperature control range set in the received instruction; and then judging whether the temperature value is in the temperature control range: if the temperature value exceeds the set temperature control range, closing the heating belt; and if the temperature value is lower than the set temperature range, starting the heating belt. Furthermore, in some possible implementations, the method further includes:
the temperature main controller can read the temperature value of the corresponding single machine acquired by each thermal control module based on a set reading period, and telemeter and download the read temperature value to the ground station as the equipment temperature value on the satellite platform.
It is understood that the technical solution shown in fig. 5 may be implemented in the form of software functional modules. If the solution is implemented in the form of a software functional module and is not sold or used as a standalone product, the solution may be stored in a computer readable storage medium, and based on the understanding, a part of the technical solution shown in fig. 5 or all or part of the technical solution may be embodied in the form of a software product stored in a storage medium, and the computer software product includes several instructions to make a computer device (which may be a personal computer, a server, or a network device) or a processor (processor) execute all or part of the steps of the method according to this embodiment. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
Therefore, the present embodiment provides a computer storage medium, where a temperature control program for a satellite platform is stored, and when the temperature control program for the satellite platform is executed by at least one processor, the steps of the temperature control method for the satellite platform in the above technical solution are implemented.
It should be noted that: the technical schemes described in the embodiments of the present invention can be combined arbitrarily without conflict.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (9)
1. A temperature control system for a satellite platform, the temperature control system comprising: the temperature control system comprises a temperature main controller, a communication bus and a power supply bus which are extended from the temperature main controller, and thermal control modules which are correspondingly installed with a single machine needing temperature control, wherein each thermal control module is communicated and interacted with the temperature main controller through the communication bus and the power supply bus, and can be selectively coupled to at least one thermistor and/or at least one heating belt which are installed on the corresponding single machine; wherein the content of the first and second substances,
the temperature main controller is configured to issue a temperature control range of a corresponding single machine to each thermal control module through the communication bus;
the thermal control module is configured to receive a temperature control range of a corresponding single machine based on the communication bus; acquiring a temperature value corresponding to the single machine through the thermistor; and when the temperature value is not in the temperature control range, controlling the on-off state of the heating belt.
2. The system of claim 1, wherein the communication bus comprises a pair of communication signal lines, and the power bus comprises a pair of power lines; and each thermal control module is respectively connected with the communication signal line and the power line.
3. The system of claim 1, wherein all of the thermal control modules are coupled to the thermal master controller via a primary thermal control module after being connected in series via the communication bus and the power supply bus.
4. The system of claim 1, wherein the thermistor is integrated into the thermal control module or connected to the thermal control module by a short wire; the heating belt is connected to the thermal control module through a short lead.
5. The system of claim 1, wherein each of the thermal control modules corresponds to a communication address for the temperature master controller to issue a temperature control range of the corresponding stand-alone machine.
6. The system of claim 1, wherein the temperature master controller is further configured to: and reading the temperature value of the corresponding single machine acquired by each thermal control module based on a set reading period, and telemetering and downloading the read temperature value to a ground station as an equipment temperature value on the satellite platform.
7. A temperature control method for a satellite platform, wherein the method is applied to the temperature control system for a satellite platform according to any one of claims 1 to 6, and the method comprises:
the temperature master controller sends the temperature control range of the corresponding single machine to each thermal control module through the communication bus; each thermal control module is correspondingly installed on a single machine needing temperature control, communication interaction between each thermal control module and the temperature main controller is realized through a communication bus and a power supply bus, and each thermal control module can be selectively coupled to at least one thermistor and/or at least one heating belt installed on the corresponding single machine;
the thermal control module receives the temperature control range of the corresponding single machine based on the communication bus;
the thermal control module acquires the temperature value of the corresponding single machine through the thermistor;
and when the temperature value is not in the temperature control range, the thermal control module controls the on-off state of the heating belt.
8. The method of claim 7, further comprising:
and the temperature main controller reads the temperature value of the corresponding single machine acquired by each thermal control module based on a set reading period, and telemeters and downloads the read temperature value to the ground station as the equipment temperature value on the satellite platform.
9. A computer storage medium, characterized in that the computer storage medium stores a temperature control program for a satellite platform, which when executed by at least one processor implements the steps of the temperature control method for a satellite platform of claim 7 or 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111243372.3A CN113900460A (en) | 2021-10-25 | 2021-10-25 | Temperature control method, system and medium for satellite platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111243372.3A CN113900460A (en) | 2021-10-25 | 2021-10-25 | Temperature control method, system and medium for satellite platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113900460A true CN113900460A (en) | 2022-01-07 |
Family
ID=79026596
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111243372.3A Withdrawn CN113900460A (en) | 2021-10-25 | 2021-10-25 | Temperature control method, system and medium for satellite platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113900460A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115826646A (en) * | 2023-02-20 | 2023-03-21 | 银河航天(北京)网络技术有限公司 | Temperature control method of temperature measuring point, thermal management system and storage medium |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020008101A1 (en) * | 2000-04-20 | 2002-01-24 | Hauschulz Dana S. | Heater control system with combination modular and daisy chained connectivity and optimum allocation of functions between base unit and local controller modules |
| CN102577303A (en) * | 2009-04-20 | 2012-07-11 | 思杰系统有限公司 | Systems and methods for generating a dns query to improve resistance against a dns attack |
| CN105159158A (en) * | 2015-07-31 | 2015-12-16 | 上海卫星工程研究所 | Electrical bus applicable to micro satellites |
| CN108062123A (en) * | 2017-12-21 | 2018-05-22 | 北京卫星环境工程研究所 | Temperature-controlling system is distributed for the bus type of spacecraft thermal test |
| CN108873969A (en) * | 2018-08-15 | 2018-11-23 | 北京空间飞行器总体设计部 | A kind of distribution temperature-controlling system |
| CN112231837A (en) * | 2020-10-22 | 2021-01-15 | 上海卫星工程研究所 | Distributed thermal control design system based on spacecraft large-area thermal control scheme |
-
2021
- 2021-10-25 CN CN202111243372.3A patent/CN113900460A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020008101A1 (en) * | 2000-04-20 | 2002-01-24 | Hauschulz Dana S. | Heater control system with combination modular and daisy chained connectivity and optimum allocation of functions between base unit and local controller modules |
| CN102577303A (en) * | 2009-04-20 | 2012-07-11 | 思杰系统有限公司 | Systems and methods for generating a dns query to improve resistance against a dns attack |
| CN105159158A (en) * | 2015-07-31 | 2015-12-16 | 上海卫星工程研究所 | Electrical bus applicable to micro satellites |
| CN108062123A (en) * | 2017-12-21 | 2018-05-22 | 北京卫星环境工程研究所 | Temperature-controlling system is distributed for the bus type of spacecraft thermal test |
| CN108873969A (en) * | 2018-08-15 | 2018-11-23 | 北京空间飞行器总体设计部 | A kind of distribution temperature-controlling system |
| CN112231837A (en) * | 2020-10-22 | 2021-01-15 | 上海卫星工程研究所 | Distributed thermal control design system based on spacecraft large-area thermal control scheme |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115826646A (en) * | 2023-02-20 | 2023-03-21 | 银河航天(北京)网络技术有限公司 | Temperature control method of temperature measuring point, thermal management system and storage medium |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4626996A (en) | Aircraft data instrumentation and acquisition system | |
| AU658842B2 (en) | Process controller with modular input/output units | |
| CN113900460A (en) | Temperature control method, system and medium for satellite platform | |
| US11208916B2 (en) | Self-healing remote dynamic data recording | |
| RU2735582C1 (en) | Programmable connector | |
| GB2518631A (en) | Power converter for a computer device and method for operating a power converter | |
| EP2407923A2 (en) | Carbon emission tracker and tracking system | |
| CN110785713B (en) | Automated field device | |
| CN112285586A (en) | BMS test method, device and system, simulation test equipment and storage medium | |
| CN103314554B (en) | DynamicHost configuration file for option mod | |
| EP3345071A1 (en) | Smart downloading of sensing data in remote sensing systems | |
| CN104067544B (en) | Update the data of the controller of the primary device of transformer station | |
| RU106768U1 (en) | HEATER CONTROL UNIT | |
| CN114448837A (en) | Method and device for measuring time delay of heaven-earth loop | |
| CN210351208U (en) | Vehicle-mounted electric control work full-signal recording system | |
| Wilhelm et al. | An instrumentation system for environmental measurements in broiler and swine housing | |
| US20040004130A1 (en) | Identification module for mobile platform | |
| CN111212753B (en) | Vehicle monitoring system | |
| CN111817820A (en) | Equipment coding method and device and coding system based on two buses | |
| Kovacs et al. | Design and implementation of a GPRS remote data logger for weather forecasting | |
| CN110290162A (en) | Document transmission method and its system, computer system | |
| CN108234197B (en) | Method for extending the functionality of a field device | |
| CN112383341B (en) | Load data downloading planning method and device | |
| Breuer et al. | Wireless diagnostic tool for electric vehicles with synchronized data acquisition: Development of a multi-purpose wireless sensor system | |
| EP4084445A1 (en) | Gas turbine engine communication data management function communicating via aircraft wireless gateway |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20220107 |