CN108146660B - A kind of spacecraft thermal control management system - Google Patents
A kind of spacecraft thermal control management system Download PDFInfo
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- CN108146660B CN108146660B CN201711250499.1A CN201711250499A CN108146660B CN 108146660 B CN108146660 B CN 108146660B CN 201711250499 A CN201711250499 A CN 201711250499A CN 108146660 B CN108146660 B CN 108146660B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
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Abstract
The present invention relates to a kind of spacecraft thermal control management systems, the spacecraft thermal control management system includes: multiple control single machines, according to the thermal control demand of spacecraft by the multiple control stand-alone configuration in each region of the spacecraft, for realizing the thermal control of each region of the spacecraft；Data management computer is connect via bus with the multiple control single machine, and the data management computer is for realizing the control to the multiple control single machine and the information exchange between the multiple control single machine.The present invention carries out global consideration to spacecraft thermal control design, unified to configure thermal control resource, improves thermal control efficiency.
Description
Technical field
The present invention relates to spacecraft thermal control management domain more particularly to a kind of spacecraft thermal control management systems.
Background technique
For the operating temperature and thermal environment for guaranteeing equipment in the in-orbit flight course of spacecraft, heat need to be carried out to entire spacecraft
Control management, provides normal operating temperature range for spacecraft, guarantees the thermal balance of spacecraft.Spacecraft thermal control management one
As by thermal control single machine carry out temperature acquisition, collection result is handled according to thermal control strategy, is judged, and to different heating device
Logic control is carried out, by temperature control in the range of setting, realizes and the autonomous thermistor(-ter) of spacecraft is managed.Manned spacecraft
In, the control also by fluid circuit, pump, blower etc. being acquired and being controlled realization thermal environment.
Manned spacecraft equipment is numerous, and function is complicated, and thermal control management generally comprises propulsion and adds subsystem, docking machine
Four part of structure subsystem, ring thermal control subsystem and loading subsystem, each section are respectively configured thermal control single machine and carry out thermal control
Management mainly carries out thermal control, docking mechanism subsystem pair to pipeline, valve and engine etc. wherein promoting and adding subsystem
Mechanical component carries out thermal control, and ring thermal control subsystem carries out heat management, load to thermal environment in each equipment of spacecraft and sealed compartment
System carries out thermal control management to each loading device.But the technological means of current manned spacecraft thermal control management is lacked there are following
It falls into:
(1) subsystems thermal control strategy designs thermal control scheme just for respective functional requirement, and between each other not
Thermal control information exchange is carried out, the unified consideration of top layer is lacked to the thermal control design of entire spacecraft, is easy to appear thermal environment injustice
The inefficient problem of weighing apparatus, thermal control.
(2) each subsystem is respectively provided for the electronics single machine of thermal control, and function repeats, and increases thermal control cost, together
When temperature point, the configuration of heating sheet and layout lack global the case where considering, there are overlapping or omitting, accordingly result in
The increase of thermal control power consumption and the complexity of cable system.
(3) subsequent manned spacecraft needs to meet the new demand of maintainable technology on-orbit, and current design is unable to satisfy thermal control single machine
The heat management to spacecraft still may be implemented in maintenance replacement process.
Summary of the invention
It is an object of the invention to solve above-mentioned technical problem, a kind of spacecraft thermal control management system is provided, to spacecraft
Thermal control design carries out global consideration, unified to configure thermal control resource, improves thermal control efficiency.
For achieving the above object, the present invention provides a kind of spacecraft thermal control management system, the spacecraft thermistor(-ter)
Reason system includes: multiple control single machines, according to the thermal control demand of spacecraft by the multiple control stand-alone configuration in the space flight
Each region of device, for realizing the thermal control of each region of the spacecraft；Data management computer, via bus and institute
State the connection of multiple control single machines, the data management computer is for realizing control to the multiple control single machine and described
Information exchange between multiple control single machines.
Preferably, the multiple control single machine also has the function of instruction is sent, telemetry intelligence (TELINT) acquires etc..
Preferably, two control single machines adjacent in the multiple control single machine are configured as main and standby relation each other, when it
In control single machine when breaking down, repair or replacing, the thermal control management of the control single machine is taken over by another control single machine
Operation.
Preferably, the multiple control single machine includes corresponding temperature point, heater, pump and blower.
Preferably, temperature point, heater, pump and the blower of two control single machines adjacent in the multiple control single machine
It is configured as main and standby relation each other, when temperature point, heater, pump and/or the blower that one of control single machine summarizes occur
When failure, maintenance or replacement, which is taken over by temperature point, heater, pump and/or the blower in another control single machine
The operation of measuring point, heater, pump and/or blower.
Preferably, the management computer is the central management unit of the spacecraft.
Preferably, the data management computer acquires the working condition of the multiple control single machine simultaneously by the bus
The health status for judging the multiple control single machine, when the working condition of one of control single machine occurs abnormal, the number
The control single machine adjacent with exception control single machine is controlled according to management computer to realize thermal control function.
Preferably, in the case where the multiple control single machine does not need collaboration and data exchange, by each control single machine
Realize independent thermal control operation.
It is single by setting data management computer and multiple controls in the spacecraft thermal control management system according to invention
Machine, and multiple control single machines are configured according to the difference of spacecraft different zones thermal control demand, so to the heat of spacecraft
Control design has carried out global consideration, unified to configure thermal control resource, is conducive to the thermal control efficiency of management.
In addition, different zones, which are configured with, in spacecraft thermal control management system according to the present invention, on spacecraft has heat
The control single machine of control ability realizes thermal control management function and thermal control compared with the prior art for the middle thermal control single machine configured
The one-to-one correspondence of demand avoids the problem of function between thermal control single machine is repeated or omitted.Meanwhile it being needed according to variant region thermal control
Difference is sought to configure control single machine, the complexity of cable system design can be effectively reduced.
In addition, in spacecraft thermal control management system according to the present invention, two adjacent controls in multiple control single machines
Stand-alone configuration be the temperature point of adjacent two control single machines in main and standby relation and multiple control single machines, heater, pump and
Blower is configured to main and standby relation, can be by other one when so that a control single machine breaking down, needs repairing or replaces wherein
A control single machine takes over it and carries out thermal control management operation, increases the fault-tolerance of spacecraft thermal control management system, advantageously ensures that
The stability of spacecraft thermal control management.
Detailed description of the invention
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 is the composition figure for schematically showing spacecraft thermal control management system according to the present invention；
Fig. 2 is the concrete composition figure for schematically showing spacecraft thermal control management system according to the present invention.
Specific embodiment
The description of this specification embodiment should be combined with corresponding attached drawing, and attached drawing should be used as the one of complete specification
Part.In the accompanying drawings, the shape of embodiment or thickness can expand, and to simplify or facilitate mark.Furthermore it is respectively tied in attached drawing
The part of structure will be to describe to be illustrated respectively, it is notable that the member for being not shown in the figure or not being illustrated by text
Part is the form known to a person of ordinary skill in the art in technical field.
The description of embodiments herein, any reference in relation to direction and orientation, is merely for convenience of describing, and cannot manage
Solution is to may be all in any restrictions of the busy scope of the present invention.It can be related to spy below for the explanation of preferred embodiment
The combination of sign, these features may be individually present or combine presence, and the present invention is not defined in preferred embodiment party particularly
Formula.The scope of the present invention is defined by the claims.
Fig. 1 is the composition figure for schematically showing spacecraft thermal control management system according to the present invention.As shown in Figure 1, according to
Spacecraft thermal control management system of the invention includes that data management computer 10 and multiple control single machines (illustrate only control in figure
Single machine 20, control single machine 30 and control single machine 40).Plurality of control single machine is configured according to the thermal control demand of spacecraft in space flight
Each region of device controls the quantity of single machine according to thermal control resource requirement for realizing the thermal control of each region of spacecraft
It is configured, and each control single machine carries out generalization and standardized designs, resource distribution are as consistent as possible.Data management
Computer 10 is connect via bus with multiple control single machines, for realizing the control and the multiple controls of control to multiple control single machines
Information exchange between single machine processed.
In spacecraft heat management system according to the present invention, multiple control single machines are all made of standardization, generalization
Design, so that all control single machines can satisfy the thermal control demand of institute's spacecraft whole, including temperature acquisition, heating circuit
The thermal controls functions such as logic control, the power supply control of pump and blower, the calculating of thermal control algorithm.It specifically, can be according to spacecraft difference
The difference of region thermal control demand, to configure the control single machine with corresponding thermal control function, and reasonable disposition temperature point, heating
Device, pump and blower etc..The thermal control demand of so certifiable spacecraft different zones can be met, while also avoid space flight
Thermal control function repeats the problem of causing the thermal control wasting of resources between controlling single machine on device.
Fig. 2 is the concrete composition figure for schematically showing spacecraft thermal control management system according to the present invention, as shown in Fig. 2,
Multiple control single machines according to the present invention include corresponding temperature point, heater, pump and blower.Spacecraft thermal control management
Multiple control single machines in system are each equipped with thermal control software patrolling for temperature acquisition, heater logic control, pump and blower
Control is collected, realizes that the autonomous thermistor(-ter) of each control single machine is managed according to temperature control strategy and temperature control algorithm with this.In addition, according to the present invention
Multiple control single machines other than having thermal control management function, also there is instruction transmission, other general utility functions such as telemetry-acquisition.Its
Middle instruction sends mainly output program control command signal, realizes the control to spaceborne device, such as plus power-off control, it is distant
The analog quantity status information that acquisition mainly acquires spaceborne device is surveyed, realizes the monitoring to spacecraft state, such as acquire
Equipment operating voltage state signal.Each control single machine arranges according to the layout scenarios of heater and temperature point, as far as possible
Reduce the length of cable system.
Data management computer 10 manages computer as context, realizes control and control to each control single machine
Information exchange between single machine processed, to adapt to different temperature control demands.
In addition, in spacecraft thermal control management system according to the present invention, two adjacent controls in multiple control single machines
Single machine can be configured as main and standby relation each other, when one of control single machine breaks down, needs repairing or replaces, by another
An outer control single machine takes over the thermal control management operation of the control single machine.For example, as shown in Fig. 2, control single machine 20 and control are single
Machine 30 is configurable to main and standby relation each other, i.e., the spare single machine that control single machine 20 and control single machine 30 can be used as other side carries out
It uses, when control single machine 20 breaks down, needs repairing or replaces, enables control single machine 30 to take over the heat of control single machine 20
Keyholed back plate reason operation when similarly control single machine 30 breaks down, can also start control single machine 20 to take over it and carry out thermal control management behaviour
Make.
In addition, in spacecraft thermal control management system according to the present invention, two adjacent controls in multiple control single machines
Temperature point, heater, pump and the blower of single machine are also configurable to main and standby relation each other.For example, as shown in Fig. 2, control is single
Temperature point, heater, pump and the blower of machine 20 and control single machine 30 are configured to main and standby relation each other, when one of control is single
One or more of temperature point, heater, pump and blower in machine (such as control single machine 20) break down, need repairing
It, can be by corresponding temperature point, heater, pump and blower in another control single machine (such as control single machine 30) or when replacement
It takes over it and carries out thermal control operation.
In spacecraft thermal control management system according to the present invention, data management computer 10 can be by the center of spacecraft
Administrative unit is realized, to further decrease design cost.Data management computer 10 is configured with thermal control software, can pass through
Bus acquires the working condition of multiple control single machines and judges the health status of multiple control single machines, when one of control single machine
When (such as control single machine 20) working condition occurs abnormal, data management computer 10 controls the control adjacent with exception control single machine
Single machine (such as control single machine 30) processed realizes thermal control function to take over it.When multiple control single machines do not need collaboration and data exchange
In the case where, each single machine that controls is operated by the thermal control software realization thermal control management itself controlled.
It is single by setting data management computer 10 and multiple controls in the spacecraft thermal control management system according to invention
Machine, and multiple control single machines are configured according to the difference of spacecraft different zones thermal control demand, so to the heat of spacecraft
Control design has carried out global consideration, unified to configure thermal control resource, is conducive to the thermal control efficiency of management.
In addition, different zones, which are configured with, in spacecraft thermal control management system according to the present invention, on spacecraft has heat
The control single machine of control ability realizes thermal control management function and thermal control compared with the prior art for the middle thermal control single machine configured
The one-to-one correspondence of demand avoids the problem of function between thermal control single machine is repeated or omitted.Meanwhile it being needed according to variant region thermal control
Difference is sought to configure control single machine, the complexity of cable system design can be effectively reduced.
In addition, in spacecraft thermal control management system according to the present invention, two adjacent controls in multiple control single machines
Stand-alone configuration be the temperature point of adjacent two control single machines in main and standby relation and multiple control single machines, heater, pump and
Blower is configured to main and standby relation, can be by other one when so that a control single machine breaking down, needs repairing or replaces wherein
A control single machine takes over it and carries out thermal control management operation, increases the fault-tolerance of spacecraft thermal control management system, advantageously ensures that
The stability of spacecraft thermal control management.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (4)
1. a kind of spacecraft thermal control management system, which is characterized in that the spacecraft thermal control management system includes:
Multiple control single machines, according to the thermal control demand of spacecraft by the multiple control stand-alone configuration in each of the spacecraft
Region, for realizing the thermal control of each region of the spacecraft；
Data management computer is connect via bus with the multiple control single machine, the data management computer for realizing
The information exchange between control and the multiple control single machine to the multiple control single machine;
Two adjacent control single machines are configured as main and standby relation each other in the multiple control single machine, when one of control is single
When machine breaks down, repairs or replaces, operated by the thermal control management that another control single machine takes over the control single machine;
The multiple control single machine includes corresponding temperature point, heater, pump and blower, in the multiple control single machine
Temperature point, heater, pump and the blower of two adjacent control single machines are configured as main and standby relation each other, when one of control
When temperature point, heater, pump and/or blower in single machine processed break down, repair or replace, by another control single machine
Temperature point, heater, pump and/or blower take over the operation of the temperature point, heater, pump and/or blower;
The data management computer acquires the working condition of the multiple control single machine by the bus and judges described more
The health status of a control single machine, when the working condition of one of control single machine occurs abnormal, the data management is calculated
Machine controls the control single machine adjacent with exception control single machine to realize thermal control function.
2. spacecraft thermal control management system according to claim 1, which is characterized in that the multiple control single machine also has
The function of instruction transmission, telemetry-acquisition.
3. spacecraft thermal control management system according to claim 1, which is characterized in that the data management computer is institute
State the central management unit of spacecraft.
4. spacecraft thermal control management system according to claim 1, which is characterized in that be not required in the multiple control single machine
In the case where cooperateing with data exchange, realize that independent thermal control operates by each control single machine.
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| CN201711250499.1A CN108146660B (en) | 2017-12-01 | 2017-12-01 | A kind of spacecraft thermal control management system |
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| CN108873969B (en) * | 2018-08-15 | 2021-02-12 | 北京空间飞行器总体设计部 | Distributed temperature control system |
| CN110703826A (en) * | 2019-11-06 | 2020-01-17 | 北京空间技术研制试验中心 | Spacecraft autonomous reconstruction thermal control management system and method |
| CN111086655B (en) * | 2019-12-16 | 2021-08-24 | 上海卫星工程研究所 | Thermal control compensation power saving method and system in non-measurement and control arc segment shadow period |
| CN111813161A (en) * | 2020-06-30 | 2020-10-23 | 武汉理工大学 | Bionic temperature control neural network system based on weak grating and working method thereof |
| CN111930163B (en) * | 2020-08-17 | 2021-06-08 | 中国科学院微小卫星创新研究院 | Satellite-borne single machine differential temperature control system and method |
| CN112231837B (en) * | 2020-10-22 | 2022-11-29 | 上海卫星工程研究所 | Distributed thermal control design system based on spacecraft large-area thermal control scheme |
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| US7270302B1 (en) * | 2003-04-22 | 2007-09-18 | Lockheed Martin Corporation | Scalable thermal control system for spacecraft mounted instrumentation |
| CN102393746B (en) * | 2011-09-20 | 2016-08-31 | 北京国科环宇空间技术有限公司 | A kind of electronic control system towards satellite and method |
| CN104816839B (en) * | 2015-04-22 | 2018-01-12 | 上海微小卫星工程中心 | A kind of satellite platform modularization thermal controls apparatus |
| CN107300864B (en) * | 2016-04-15 | 2019-07-12 | 北京空间技术研制试验中心 | The spacecraft information system and its operating method of autonomous management |
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