CN111651837A - Satellite thermal control management system and method - Google Patents
Satellite thermal control management system and method Download PDFInfo
- Publication number
- CN111651837A CN111651837A CN202010493540.3A CN202010493540A CN111651837A CN 111651837 A CN111651837 A CN 111651837A CN 202010493540 A CN202010493540 A CN 202010493540A CN 111651837 A CN111651837 A CN 111651837A
- Authority
- CN
- China
- Prior art keywords
- module
- satellite
- test
- thermal
- assembly
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 57
- 238000012360 testing method Methods 0.000 claims abstract description 210
- 238000013461 design Methods 0.000 claims abstract description 48
- 230000008569 process Effects 0.000 claims abstract description 48
- 238000010923 batch production Methods 0.000 claims abstract description 44
- 238000012795 verification Methods 0.000 claims abstract description 33
- 238000005457 optimization Methods 0.000 claims abstract description 21
- 238000004886 process control Methods 0.000 claims abstract description 19
- 238000004519 manufacturing process Methods 0.000 claims abstract description 12
- 238000007726 management method Methods 0.000 claims description 133
- 230000005540 biological transmission Effects 0.000 claims description 25
- 230000004044 response Effects 0.000 claims description 24
- 238000004088 simulation Methods 0.000 claims description 21
- 238000010438 heat treatment Methods 0.000 claims description 18
- 238000002360 preparation method Methods 0.000 claims description 12
- 238000004458 analytical method Methods 0.000 claims description 9
- 238000011217 control strategy Methods 0.000 claims description 9
- 238000005286 illumination Methods 0.000 claims description 8
- 230000010354 integration Effects 0.000 claims description 7
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 6
- 229920002379 silicone rubber Polymers 0.000 claims description 5
- 206010057040 Temperature intolerance Diseases 0.000 claims description 4
- 239000011248 coating agent Substances 0.000 claims description 4
- 238000000576 coating method Methods 0.000 claims description 4
- 230000008543 heat sensitivity Effects 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 4
- 238000011112 process operation Methods 0.000 claims description 2
- 238000005070 sampling Methods 0.000 claims 1
- 238000011161 development Methods 0.000 abstract description 40
- 210000001503 joint Anatomy 0.000 description 4
- 230000006855 networking Effects 0.000 description 4
- 238000012937 correction Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000003860 storage Methods 0.000 description 3
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000002955 isolation Methods 0.000 description 2
- 238000009958 sewing Methods 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- -1 acryl Chemical group 0.000 description 1
- NIXOWILDQLNWCW-UHFFFAOYSA-N acrylic acid group Chemical group C(C=C)(=O)O NIXOWILDQLNWCW-UHFFFAOYSA-N 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000004945 silicone rubber Substances 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06Q—INFORMATION AND COMMUNICATION TECHNOLOGY [ICT] SPECIALLY ADAPTED FOR ADMINISTRATIVE, COMMERCIAL, FINANCIAL, MANAGERIAL OR SUPERVISORY PURPOSES; SYSTEMS OR METHODS SPECIALLY ADAPTED FOR ADMINISTRATIVE, COMMERCIAL, FINANCIAL, MANAGERIAL OR SUPERVISORY PURPOSES, NOT OTHERWISE PROVIDED FOR
- G06Q10/00—Administration; Management
- G06Q10/06—Resources, workflows, human or project management; Enterprise or organisation planning; Enterprise or organisation modelling
- G06Q10/063—Operations research, analysis or management
- G06Q10/0639—Performance analysis of employees; Performance analysis of enterprise or organisation operations
- G06Q10/06395—Quality analysis or management
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/08—Thermal analysis or thermal optimisation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Business, Economics & Management (AREA)
- Theoretical Computer Science (AREA)
- Human Resources & Organizations (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Strategic Management (AREA)
- Development Economics (AREA)
- Entrepreneurship & Innovation (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Economics (AREA)
- Educational Administration (AREA)
- Mathematical Analysis (AREA)
- Marketing (AREA)
- Computational Mathematics (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Game Theory and Decision Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Operations Research (AREA)
- Quality & Reliability (AREA)
- Tourism & Hospitality (AREA)
- General Business, Economics & Management (AREA)
- Control Of Temperature (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention provides a satellite thermal control management system and a method, comprising the following steps: in each stage of satellite design, manufacture and launch, the task allocation module is configured to map a plurality of product management modules into the batch process control and test module according to their redundant control functions to respectively complete a plurality of parallel tasks simultaneously; the plurality of product management modules are distributed into a product-level assembly module, a board-level assembly module and a final assembly module in the satellite assembly stage; the plurality of product management modules are distributed into a model thermal balance test module and a normal thermal balance test module in the satellite test stage. By means of scheme design optimization, flow optimization, process control templating, documentation and data packetization, the problem of high cost and long development period is solved. An efficient assembly scheme is designed in the assembly process, and meanwhile, the effectiveness and the correctness of the assembly of the thermal control product are guaranteed through a test scheme and a test verification scheme, the progress of the whole satellite development is guaranteed, and the good in-orbit flight state is also guaranteed.
Description
Technical Field
The invention relates to the technical field of satellite thermal control, in particular to a satellite thermal control management system and a satellite thermal control management method.
Background
Aiming at the thermal control development of the networking constellation satellite for batch production in a short period, the development of a thermal control subsystem in the prior art has great difficulty, and particularly the development difficulty caused by the complex requirement of multi-dimensional interweaving is difficult to overcome. Fig. 1 shows the matching relationship between the demand characteristics and difficulties in the thermal control development process according to the characteristics of the satellite. The method mainly comprises the following steps: a) due to the problem of orbit difference generated by constellation layout, a high-tolerance scheme is required to adapt to high-low temperature severe working conditions in the same orbit plane during thermal design, and the problem of influence of heat flow difference in different orbit planes on a temperature field is solved; b) due to the weight reduction requirement brought by the lightweight target, the selection and assembly of products are strictly controlled during thermal design, and the use of thermal control products is reduced as much as possible on the premise of ensuring that the whole satellite temperature field reaches the design index and the temperature homogenization control; c) because the instantaneous power consumption of the load cabin is large, the controllable temperature field of the load single machine is ensured by an effective thermal control strategy; d) because the load compartment is a rotating system, strict requirements are provided for the anti-hook design and implementation of the thermal control product; e) due to the characteristic of short development period, the development stage of the satellite is in an overlapped state, when the whole satellite enters the normal development stage, the actual requirement of the thermal control subsystem reaches the next stage, namely the batch production stage in advance, and therefore the feasibility and the effectiveness of the thermal control scheme have high requirements; meanwhile, due to the limitation of time, the corresponding requirement of the system verification time of the thermal control subsystem is shortened; f) due to the characteristics of satellite batch production, high requirements are provided for the assembly efficiency and the state consistency of the thermal control products.
Disclosure of Invention
The invention aims to provide a satellite thermal control management system and a satellite thermal control management method, which aim to solve the problem that the development of a thermal control subsystem for batch production of the conventional networking constellation satellite in a short period has complex multi-dimensional difficulty.
In order to solve the technical problems, the invention provides a satellite thermal control management system, which comprises a simulation design and optimization module, a product quality management module and a batch process control and test module, wherein:
the simulation design and optimization module is configured to simulate the space thermal environments under different orbital planes according to the launching scheme of the satellite and the working mode of each satellite to obtain the in-orbit layout result of the satellite;
the product quality management module comprises a task allocation module and a plurality of product management modules, and the task allocation module is configured to map the product quality management modules into the batch process control and test module according to the redundant control functions of the product management modules in each stage of satellite design, manufacture and transmission so as to respectively complete a plurality of parallel tasks simultaneously;
the batch production process control and test module is configured to perform simulation analysis and verification on the conditions that the satellite is in multiple orbits, is in multiple working modes and is fully covered by the solar illumination angle according to the on-orbit layout result of the satellite;
the batch production process control and test module comprises a product-level assembly module, a board-level assembly module and a final assembly module, wherein in the satellite assembly stage, the product-level assembly module controls the positioning, wiring and checking interference of the thermal control product, the board-level assembly module optimizes the multilayer assembly of the thermal control product, and the final assembly module detects whether the multilayer assembly meets the thermal control requirement;
the plurality of product management modules are assigned to the product-level assembly module, board-level assembly module, and final assembly module at a satellite assembly stage;
the batch production process control and test module further comprises a model heat balance test module and a sample heat balance test module, the model heat balance test module performs a heat balance test of a model satellite in satellite test verification, and the sample heat balance test module simultaneously performs a bottoming test and a three-star jointly performed whole-star-level thermal vacuum test on the sample satellite;
the plurality of product management modules are distributed into the model thermal balance test module and the positive thermal balance test module in a satellite test stage.
Optionally, in the satellite thermal control management system, the number of the product management modules is 6, where:
in the scheme design stage, the product management modules comprise a heater module, a thermistor module, a multilayer component module, a thermal control coating module, a thermal control auxiliary material module and a thermal control electric test module, and the product management modules are configured to design various thermal control products to be installed on the satellite and control the quality of the thermal control products.
Optionally, in the satellite thermal control management system, in a prototype stage, the task allocation module allocates the plurality of product management modules to be a prototype module and an identification module according to the redundancy control function of the product management modules, the prototype module completes pre-assembly of a thermal control product of a prototype star, total assembly of a whole star, comprehensive testing and a thermal balance test, and the identification module completes refitting of the thermal control product of the identification star, total assembly of the whole star and the thermal balance test;
the identification module comprises the model thermal equilibrium test module.
Optionally, in the satellite thermal control management system, in a sample stage, the task allocation module allocates the product management modules to a factory preparation module and a batch module according to the redundant control functions of the product management modules, where:
the factory preparation module is configured to perform a samsung general assembly integration test and a factory state preparation;
the batch module is configured to perform preassembly and test of thermal control products simultaneously, and comprises a three-star common assembly, a three-star common test, a three-star common thermal vacuum test and a three-star common assembly integration test;
the batch production module comprises the product-level assembly module, the board-level assembly module, the final assembly module and the sample thermal balance test module.
Optionally, in the satellite thermal control management system, in a satellite transmission stage, the task allocation module allocates the multiple product management modules to a transmission field process operation module, a transmission field test module, a transmission task execution module, and an on-satellite flight control task module according to the redundant control functions of the multiple product management modules, where:
the transmit field flow operation module is configured to perform a preparation flow prior to satellite transmission;
the transmission field test module is configured to execute a test task before satellite transmission;
the launching task execution module is configured to execute a satellite launching task;
the on-board flight control task module is configured to control on-board in-orbit and on-orbit-keeping thermal control tests.
Optionally, in the satellite thermal control management system, the batch process control and test module further includes a heating infrared test module, a thermal control satellite-mounted ground response module, and a comprehensive test process response module, where:
the heating infrared testing module is configured to perform heater testing on an active heater loop with power larger than 10W through an infrared imager so as to check whether silicon rubber used for adhering a heater is uniform;
the thermal control satellite-mounting ground response module is configured to detect the pasting position of the thermistor and the welding channel of the electric connector;
the comprehensive test process response module is configured to test the response relation between the heating loop and the heater through electrification, detect the response relation of the corresponding temperature control heat sensitivity through a heater switch of the closed loop in the process, and confirm the effectiveness of the heating loop.
Optionally, in the satellite thermal control management system, the platform cabin and the load cabin of the satellite are independent cabin bodies, and the load cabin has an independent rotating baseline;
the platform cabin is independently controlled by a satellite computer, and a temperature control strategy with a passive mode as a main mode and an active mode as an auxiliary mode is adopted;
the load cabin carries out independent temperature control through the load management unit, and the load cabin adopts an active and passive simultaneous temperature control strategy.
The invention also provides a satellite thermal control management method, which comprises the following steps:
the simulation design and optimization module simulates the space thermal environment under different orbital planes according to the launching scheme of the satellite and the working mode of each satellite to obtain the in-orbit layout result of the satellite;
in each stage of satellite design, manufacture and emission, the task allocation module maps the product management modules into a batch process control and test module according to the redundancy control function of the product management modules so as to respectively complete a plurality of parallel tasks simultaneously;
the batch production process control and test module carries out simulation analysis and verification on the conditions that the satellite is in multiple orbits, is in multiple working modes and is fully covered by the solar illumination angle according to the satellite on-orbit layout result;
in the satellite assembly stage, a product-level assembly module controls the positioning, wiring and interference checking of the thermal control product, a board-level assembly module optimizes the multilayer assembly of the thermal control product, and a final assembly module detects whether the multilayer assembly meets the thermal control requirement;
the plurality of product management modules are assigned to the product-level assembly module, board-level assembly module, and final assembly module at a satellite assembly stage;
in satellite test verification, the model thermal balance test module performs thermal balance test on the model satellite, and the positive sample thermal balance test module simultaneously performs a bottoming test on the positive sample satellite and a whole-satellite-level thermal vacuum test performed by three stars together;
the plurality of product management modules are distributed into the model thermal balance test module and the positive thermal balance test module in a satellite test stage.
In the satellite thermal control management system and the satellite thermal control management method, in each stage of satellite design, manufacture and launch, the task allocation module maps the product management modules into the batch process control and test module according to the redundancy control functions of the product management modules to respectively complete a plurality of parallel tasks simultaneously, the product management modules are allocated into a product-level assembly module, a board-level assembly module and a final assembly module in the satellite assembly stage, and the product management modules are allocated into a model thermal balance test module and a normal thermal balance test module in the satellite test stage, so that the management and the control of the whole development process of a thermal control subsystem are realized, the scheme design optimization, the process optimization, the templating, the documentation and the data packetization of the process control are carried out, and the problems that the cost is low, the development period is short and the simultaneous solution cannot be realized are solved. An efficient assembly scheme is designed in the assembly process, and meanwhile, by developing a series of test schemes and test verification schemes, the effectiveness and the correctness of the assembly of the thermal control product are guaranteed, the progress of the whole satellite development is guaranteed, and the good on-orbit flight state is also guaranteed.
Drawings
FIG. 1 is a schematic diagram illustrating the matching relationship between the requirement characteristics and difficulties in the thermal control development process according to the characteristics of the existing satellite;
fig. 2 is a schematic diagram of a satellite thermal management system according to an embodiment of the invention.
Detailed Description
The satellite thermal control management system and method provided by the invention are further described in detail with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
The core idea of the invention is to provide a satellite thermal control management system and a method thereof, so as to solve the problem that the development of the thermal control subsystem for batch production of the existing networking constellation satellite in a short period has complex multi-dimensional difficulty.
In order to realize the idea, the invention provides a satellite thermal control management system and a method, wherein the satellite thermal control management system comprises a simulation design and optimization module, a product quality management module and a batch process control and test module, wherein: the simulation design and optimization module is configured to simulate the space thermal environments under different orbital planes according to the launching scheme of the satellite and the working mode of each satellite to obtain the in-orbit layout result of the satellite; the product quality management module comprises a task allocation module and a plurality of product management modules, and the task allocation module is configured to map the product quality management modules into the batch process control and test module according to the redundant control functions of the product management modules in each stage of satellite design, manufacture and transmission so as to respectively complete a plurality of parallel tasks simultaneously; the batch production process control and test module is configured to perform simulation analysis and verification on the conditions that the satellite is in multiple orbits, is in multiple working modes and is fully covered by the solar illumination angle according to the on-orbit layout result of the satellite; the batch production process control and test module comprises a product-level assembly module, a board-level assembly module and a final assembly module, wherein in the satellite assembly stage, the product-level assembly module controls the positioning, wiring and checking interference of the thermal control product, the board-level assembly module optimizes the multilayer assembly of the thermal control product, and the final assembly module detects whether the multilayer assembly meets the thermal control requirement; the plurality of product management modules are assigned to the product-level assembly module, board-level assembly module, and final assembly module at a satellite assembly stage; the batch production process control and test module further comprises a model heat balance test module and a sample heat balance test module, the model heat balance test module performs a heat balance test of a model satellite in satellite test verification, and the sample heat balance test module simultaneously performs a bottoming test and a three-star jointly performed whole-star-level thermal vacuum test on the sample satellite; the plurality of product management modules are distributed into the model thermal balance test module and the positive thermal balance test module in a satellite test stage.
< example one >
This embodiment provides a satellite thermal control management system, as shown in fig. 2, the satellite thermal control management system includes a simulation design and optimization module, a product quality management module, and a batch process control and test module, wherein: the simulation design and optimization module is configured to simulate the space thermal environments under different orbital planes according to the launching scheme of the satellite and the working mode of each satellite to obtain the in-orbit layout result of the satellite; the product quality management module comprises a task allocation module and a plurality of product management modules, and the task allocation module is configured to map the product quality management modules into the batch process control and test module according to the redundant control functions of the product management modules in each stage of satellite design, manufacture and transmission so as to respectively complete a plurality of parallel tasks simultaneously; the batch production process control and test module is configured to perform simulation analysis and verification on the conditions that the satellite is in multiple orbits, is in multiple working modes and is fully covered by the solar illumination angle according to the on-orbit layout result of the satellite; the batch production process control and test module comprises a product-level assembly module, a board-level assembly module and a final assembly module, wherein in the satellite assembly stage, the product-level assembly module controls the positioning, wiring and checking interference of the thermal control product, the board-level assembly module optimizes the multilayer assembly of the thermal control product, and the final assembly module detects whether the multilayer assembly meets the thermal control requirement; the plurality of product management modules are assigned to the product-level assembly module, board-level assembly module, and final assembly module at a satellite assembly stage; the batch production process control and test module further comprises a model heat balance test module and a sample heat balance test module, the model heat balance test module performs a heat balance test of a model satellite in satellite test verification, and the sample heat balance test module simultaneously performs a bottoming test and a three-star jointly performed whole-star-level thermal vacuum test on the sample satellite; the plurality of product management modules are distributed into the model thermal balance test module and the positive thermal balance test module in a satellite test stage.
Specifically, in the satellite thermal control management system, the number of the product management modules is 6 (as shown in fig. 2, a to F), where: in the scheme design stage, the product management modules A to F respectively correspond to a heater module for performing heater product management, a thermistor module for performing thermistor product management, a multilayer assembly module for multilayer assembly product management, a thermal control coating module for thermal control coating product management, a thermal control auxiliary material module for thermal control auxiliary material product management and a thermal control electrical test module for thermal control comprehensive electrical test, and the product management modules A to F are configured to design various thermal control products to be installed on a satellite and control the quality of the thermal control products.
Further, in the satellite thermal control management system, in a prototype stage, the task allocation module allocates a to C as prototype modules according to the redundancy control functions of the plurality of product management modules, allocates D to F as identification modules, the prototype modules a to C complete the thermal control product pre-assembly, whole satellite final assembly, comprehensive test and thermal balance test of a prototype satellite, and the identification modules D to F complete the thermal control product modification, whole satellite final assembly and thermal balance test of an identification satellite; the identification modules D-F comprise the model heat balance test module.
Further, in the satellite thermal control management system, in a sample stage, the task allocation module allocates a to C as factory preparation modules and allocates D to F as batch modules according to the redundant control functions of the plurality of product management modules, wherein: the factory preparation modules A-C are configured to carry out Samsung assembly integration test and factory state preparation; the batch modules D-F are configured to simultaneously perform preassembly and test of thermal control products, and comprise a three-star common assembly, a three-star common test, a three-star common thermal vacuum test and a three-star common assembly integration test; the batch production modules D-F comprise the product-level assembly module, the board-level assembly module, the final assembly module and the sample thermal balance test module.
In addition, in the satellite thermal control management system, in a satellite transmission stage, the task allocation module allocates a to F to a transmission field flow operation module, a transmission field test module, a transmission task execution module and an on-satellite flight control task module according to the redundant control functions of the plurality of product management modules, wherein: the transmit field flow operation module is configured to perform a preparation flow prior to satellite transmission; the transmission field test module is configured to execute a test task before satellite transmission; the launching task execution module is configured to execute a satellite launching task; the on-board flight control task module is configured to control on-board in-orbit and on-orbit-keeping thermal control tests.
In addition, in the satellite thermal control management system, the batch process control and test module further comprises a heating infrared test module, a thermal control satellite-mounted ground response module and a comprehensive test process response module, wherein: the heating infrared testing module is configured to perform heater testing on an active heater loop with power larger than 10W through an infrared imager so as to check whether silicon rubber used for adhering a heater is uniform; the thermal control satellite-mounting ground response module is configured to detect the pasting position of the thermistor and the welding channel of the electric connector; the comprehensive test process response module is configured to test the response relation between the heating loop and the heater through electrification, detect the response relation of the corresponding temperature control heat sensitivity through a heater switch of the closed loop in the process, and confirm the effectiveness of the heating loop.
Specifically, in the satellite thermal control management system, a platform cabin and a load cabin of the satellite are independent cabin bodies, and the load cabin is provided with an independent rotating base line; the platform cabin is independently controlled by a satellite computer, and a temperature control strategy with a passive mode as a main mode and an active mode as an auxiliary mode is adopted; the load cabin carries out independent temperature control through the load management unit, and the load cabin adopts an active and passive simultaneous temperature control strategy.
In summary, the above embodiments have described the different configurations of the satellite thermal management system in detail, and it is needless to say that the present invention includes, but is not limited to, the configurations listed in the above embodiments, and any modifications made on the configurations provided in the above embodiments are within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
< example two >
The present embodiment provides a satellite thermal control management method, as shown in fig. 2, the satellite thermal control management method includes: the simulation design and optimization module simulates the space thermal environment under different orbital planes according to the launching scheme of the satellite and the working mode of each satellite to obtain the in-orbit layout result of the satellite; in each stage of satellite design, manufacture and emission, the task allocation module maps the product management modules into a batch process control and test module according to the redundancy control function of the product management modules so as to respectively complete a plurality of parallel tasks simultaneously; the batch production process control and test module carries out simulation analysis and verification on the conditions that the satellite is in multiple orbits, is in multiple working modes and is fully covered by the solar illumination angle according to the satellite on-orbit layout result; in the satellite assembly stage, a product-level assembly module controls the positioning, wiring and interference checking of the thermal control product, a board-level assembly module optimizes the multilayer assembly of the thermal control product, and a final assembly module detects whether the multilayer assembly meets the thermal control requirement; the plurality of product management modules are assigned to the product-level assembly module, board-level assembly module, and final assembly module at a satellite assembly stage; in satellite test verification, the model thermal balance test module performs thermal balance test on the model satellite, and the positive sample thermal balance test module simultaneously performs a bottoming test on the positive sample satellite and a whole-satellite-level thermal vacuum test performed by three stars together; the plurality of product management modules are distributed into the model thermal balance test module and the positive thermal balance test module in a satellite test stage.
In the satellite thermal control management system and the satellite thermal control management method, in each stage of satellite design, manufacture and launch, the task allocation module maps the product management modules into the batch process control and test module according to the redundancy control functions of the product management modules to respectively complete a plurality of parallel tasks simultaneously, the product management modules are allocated into a product-level assembly module, a board-level assembly module and a final assembly module in the satellite assembly stage, and the product management modules are allocated into a model thermal balance test module and a normal thermal balance test module in the satellite test stage, so that the management and the control of the whole development process of a thermal control subsystem are realized, the scheme design optimization, the process optimization, the templating, the documentation and the data packetization of the process control are carried out, and the problems that the cost is low, the development period is short and the simultaneous solution cannot be realized are solved. An efficient assembly scheme is designed in the assembly process, and meanwhile, by developing a series of test schemes and test verification schemes, the effectiveness and the correctness of the assembly of the thermal control product are guaranteed, the progress of the whole satellite development is guaranteed, and the good on-orbit flight state is also guaranteed.
Aiming at the characteristic of short development period of thermal control of the batch satellites, the thermal control is combined with the condition of structural layout of the thermal control of the satellites, and the thermal control carries out batch design, batch assembly and batch verification on the basis of ensuring the validity of scheme design.
Firstly, the optimization of the scheme design is characterized by a one-arrow-three-star launching scheme, short development period and low development cost, and when the thermal control scheme is designed, the scheme is ensured to be effective, the integrated design and the weight reduction design of the thermal control product are carried out, and the requirement of isothermal process is reduced. For example, the in-satellite single machine layout is optimized through coordination with each subsystem, simulation analysis demonstration is carried out on the use of the heat pipe, so that the quality of the whole satellite is reduced, and the production period of the structural honeycomb plate is shortened. The concept of the integrated design of the thermal control product is implemented, and the assembly time of the final assembly is greatly shortened.
Secondly, a scheme for constellation orbital planes is demonstrated, space thermal environments under different orbital planes are analyzed in a simulation mode, layout suggestions are given by combining different working modes of the satellite, on one hand, the supply requirements of on-satellite energy sources are greatly saved, and on the other hand, high adaptability in the whole orbital plane is achieved.
And moreover, under the condition of instantaneous high power generated in the load working and non-working periods, the thermal control subsystem is subjected to scheme design combining a passive scheme and an active scheme, on one hand, the thermal control subsystem is subjected to active thermal control at a low temperature through the design of a heat dissipation scheme at the low temperature, and on the other hand, the thermal control subsystem is combined with a thermal control energy management strategy on the satellite to effectively control the temperature level of the load cabin within an index range.
Finally, the satellite is characterized by double-cabin isolation and load cabin rotation, namely, the platform cabin and the load cabin are independent cabin bodies, and the load cabin has an independent rotation base line. Aiming at the characteristics, the thermal control subsystem is designed for double-cabin thermal isolation, the platform cabin is independently controlled in temperature by a satellite computer, the load is independently controlled in temperature by a load management unit, and the temperature control level and the control strategy of the two cabins are different. The platform cabin adopts a temperature control strategy of taking the passive as the main part and taking the active as the auxiliary part, and the load cabin adopts a strategy of controlling the temperature by adopting the active and passive schemes simultaneously. Table 1 summarizes the solution optimization developed by the present invention.
TABLE 1 scheme design optimization
By the scheme, the problems of high-power heat dissipation and rapid assembly of the satellite in different working modes in complex space environments with different orbital planes are successfully solved, and feasibility and high efficiency of a thermal design scheme of the satellite are ensured.
In order to ensure the reliability of the thermal control products, the thermal control subsystem carries out detailed verification on the selection and purchase period of the thermal control products and the ground storage period. In the aspect of product selection, products with high maturity level, high inheritance and good product performance are adopted, and meanwhile, the thermal control product assembly process adopts a mature process to ensure the reliability of the products. The ground storage conditions of the product are set as on-satellite product condition control conditions and are used within the validity period. And a rich management mode is adopted for the silicone rubber with a short effective period, so that the effectiveness of the product in star loading is ensured.
The batch production satellite is a satellite integrated with a science and packaging system, a scientific research satellite and an equipment satellite are developed in parallel, batch production development work is carried out simultaneously, and the thermal control subsystem is combined with the full-period development characteristic to implement a dynamic management mode on a plurality of product management modules for thermal control of the satellite.
In the initial stage of satellite development, a thermal control subsystem classifies products, a product-level management mode is adopted, and the design and assembly of each product are independently controlled through a product management module respectively so as to ensure the progress of the product; with the progress of satellite development, a plurality of product management modules carry out a grouping mode to respectively control the test state of a single satellite, and complete comprehensive electrical test, satellite final assembly and test product assembly. When a first group of satellites (3) enters an Assembly Integration Test (AIT) stage, networking satellites are redistributed at the same time, state control, preassembly, assembly and AIT of a group of satellites are completed, and redistribution is performed on subsequent batch production and execution of a launching task. FIG. 2 is a schematic diagram of the dynamic adjustment of the thermal control subsystem. The thermal control subsystem ensures the development progress of the whole satellite through effective dynamic management and fully completes the launching task.
In the conventional satellite development process, a scheme stage, a prototype stage, a normal stage and a launch stage are generally adopted, and due to the short development cycle of the project, the overlap of the prototype stage, the normal stage and the batch stage is carried out in the development process. In order to ensure the consistency and correctness of the technical state of the scheme and the satellite, the full-coverage simulation analysis verification of multiple orbits, multiple working modes and solar illumination angles is carried out firstly in the development process, and meanwhile, the templated control of batch assembly is designed to strengthen the key point control in the thermal control subsystem. For test verification, in order to effectively shorten the development period, on one hand, a model thermal balance test is carried out, on the other hand, the thermal balance test verification in the sample correction stage is moved forward, a positive satellite is assembled, a background test is carried out in the sample correction state, only the whole-satellite-level thermal vacuum test is carried out in the sample correction stage to check and verify the on-satellite products, and meanwhile, the thermal control subsystem designs a scheme of a three-satellite simultaneous thermal vacuum test. As shown in Table 2, the comparison table of the time cost saved in the development process of the project by the thermal control subsystem is compared with the conventional thermal control development process.
TABLE 2 development flow management optimization (each star)
In the development process, in order to ensure the controllable technological process, on one hand, the data packet control in the thermal control assembly stage is carried out, on the other hand, thermal control drawings and templates in different states are designed, the accuracy and traceability of product assembly are effectively controlled, and the efficiency of thermal control product assembly is improved. The control process and the experimental verification, which are important to the development process, are explained in detail below.
Because the satellites are produced in batches, a series of batch assembly control requirements are formulated for ensuring the state consistency in the production process, and the process is subjected to standardized control. Aiming at the stage of thermal control assembly, the thermal control subsystem carries out staged control, and the product assembly process is designed into three processes of product-level assembly, board-level assembly and final assembly of the whole satellite, wherein the product-level assembly and the board-level assembly are collectively called as the product preassembly stage of thermal control, and the final assembly of the whole satellite is the final assembly stage. The product-level assembly is developed aiming at key components of the satellite, is also a key control process of the thermal control subsystem, and mainly comprises a storage battery, a propulsion subsystem, a rotary table locking device and high-frequency cable thermal control assembly. The product-level thermal control assembly writes standard control files and identifies key control points. The board level assembly can also be called integrated assembly, namely after the thermal control product is assembled, the data acquisition channel and the heating channel are integrated in the electric connector, and the board level assembly is in butt joint with a low-frequency cable network of the whole satellite during the assembly of the whole satellite assembly. The process basically implements and completes the thermal control product, and the time requirement of the final assembly process can be greatly reduced. The whole satellite assembly is a butt joint process of the thermal control product and the whole satellite, the process comprises butt joint of the electric connector and butt joint of a few scattered wires, and compared with the conventional thermal design and thermal assembly process, the process greatly reduces the assembly time.
In the process of assembling the thermal control product, the template control is adopted, so that the assembling time is reduced on one hand, and the consistency of batch development is ensured on the other hand. In the development process, 3 sets of templates are generated in total, the 1 st set of templates is a pre-assembled template drawing of a heater and a thermistor, the pre-assembled template drawing is converted into a transparent acrylic template through an entity, and the template is used for positioning, wiring and checking interference of a thermal control product in a pre-assembling stage; the 2 nd set of template is a drawing template of multilayer drawings, the template includes the concrete size and pattern of multilayer, is used for the preliminary multilayer to produce the sewing work of the appearance, the template is mainly used for assembling the on-board state and verifying before at the same time, is used for finishing the multilayer assembly producing the appearance, mainly include the trepanning, the surplus and grounded location; the 3 rd set of template is a multilayer acryl template containing hasp sewing, and the drawing is a splicing complete drawing and is used for positioning the complete star integrity hasp and checking the acceptance work of a multilayer assembly finished product. Through the process control of 3 sets of templates, the accuracy and consistency of the assembly of the thermal control product are ensured, and the efficiency of the thermal control assembly is effectively improved.
In the process of batch production development, a thermal control subsystem designs a series of process verifications for ensuring the validity of product assembly, and the process verifications mainly comprise heating infrared test verification, ground response verification of thermal control star loading, response test of a comprehensive test process, thermal vacuum three-star simultaneous tank feeding thermal test verification and the like. The heating infrared test verification is mainly to carry out heater test on an active heater loop with power larger than 10W through an infrared imager so as to check whether silicon rubber used for adhering a heater is uniform or not and guarantee the adhering effect of a heater product. The ground response test of the thermal control star mainly comprises the step of checking the correctness of the pasting position of the thermistor and the correctness of a welding channel of the electric connector in a hand touch mode. By adding the test and verification process, the phenomenon of product assembly error after star loading is effectively controlled. The response test in the comprehensive test process mainly tests the response relationship between the heating circuit and the heater by electrification, and observes the response relationship of the corresponding temperature control heat sensitivity by switching the heater of the closed loop in the process to confirm the effectiveness of the heating circuit. Through the test verification, the correctness of the matching of all the heating loops on the satellite is effectively ensured.
In order to reduce the test verification time in the development process, the group of batch-produced satellites adopt a three-star simultaneous test on the premise of meeting on-satellite environment test conditions and whole-star thermal vacuum test conditions, and 3-star simultaneous temperature control is carried out through an infrared cage, so that an instructive operation file is formed, the assessment strength of the thermal vacuum test is ensured on one hand, and the consistency of the 3-star simultaneous test is ensured on the other hand.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (8)
1. The utility model provides a satellite thermal control management system, its characterized in that, satellite thermal control management system includes simulation design and optimization module, product quality management module and batch process control and test module, wherein:
the simulation design and optimization module is configured to simulate the space thermal environments under different orbital planes according to the launching scheme of the satellite and the working mode of each satellite to obtain the in-orbit layout result of the satellite;
the product quality management module comprises a task allocation module and a plurality of product management modules, and the task allocation module is configured to map the product quality management modules into the batch process control and test module according to the redundant control functions of the product management modules in each stage of satellite design, manufacture and transmission so as to respectively complete a plurality of parallel tasks simultaneously;
the batch production process control and test module is configured to perform simulation analysis and verification on the conditions that the satellite is in multiple orbits, is in multiple working modes and is fully covered by the solar illumination angle according to the on-orbit layout result of the satellite;
the batch production process control and test module comprises a product-level assembly module, a board-level assembly module and a final assembly module, wherein in the satellite assembly stage, the product-level assembly module controls the positioning, wiring and checking interference of the thermal control product, the board-level assembly module optimizes the multilayer assembly of the thermal control product, and the final assembly module detects whether the multilayer assembly meets the thermal control requirement;
the plurality of product management modules are assigned to the product-level assembly module, board-level assembly module, and final assembly module at a satellite assembly stage;
the batch production process control and test module further comprises a model heat balance test module and a sample heat balance test module, the model heat balance test module performs a heat balance test of a model satellite in satellite test verification, and the sample heat balance test module simultaneously performs a bottoming test and a three-star jointly performed whole-star-level thermal vacuum test on the sample satellite;
the plurality of product management modules are distributed into the model thermal balance test module and the positive thermal balance test module in a satellite test stage.
2. The satellite thermal management system of claim 1, wherein the number of product management modules is 6, wherein:
in the scheme design stage, the product management modules comprise a heater module, a thermistor module, a multilayer component module, a thermal control coating module, a thermal control auxiliary material module and a thermal control electric test module, and the product management modules are configured to design various thermal control products to be installed on the satellite and control the quality of the thermal control products.
3. The satellite thermal management system according to claim 1, wherein in a prototype stage, the task allocation module allocates the plurality of product management modules into a prototype module and an identification module according to the redundancy control functions of the product management modules, the prototype module completes pre-assembly of thermal control products, whole-satellite assembly, comprehensive testing and thermal balance testing of a prototype satellite, and the identification module completes refitting of thermal control products, whole-satellite assembly and thermal balance testing of an identification satellite;
the identification module comprises the model thermal equilibrium test module.
4. The satellite thermal control management system according to claim 1, wherein in a sampling phase, the task allocation module allocates the plurality of product management modules into a factory preparation module and a batch module according to their redundant control functions, wherein:
the factory preparation module is configured to perform a samsung general assembly integration test and a factory state preparation;
the batch module is configured to perform preassembly and test of thermal control products simultaneously, and comprises a three-star common assembly, a three-star common test, a three-star common thermal vacuum test and a three-star common assembly integration test;
the batch production module comprises the product-level assembly module, the board-level assembly module, the final assembly module and the sample thermal balance test module.
5. The satellite thermal control management system according to claim 1, wherein in a satellite transmission phase, the task allocation module allocates the plurality of product management modules into a transmission field process operation module, a transmission field test module, a transmission task execution module, and an on-satellite flight control task module according to redundant control functions of the plurality of product management modules, wherein:
the transmit field flow operation module is configured to perform a preparation flow prior to satellite transmission;
the transmission field test module is configured to execute a test task before satellite transmission;
the launching task execution module is configured to execute a satellite launching task;
the on-board flight control task module is configured to control on-board in-orbit and on-orbit-keeping thermal control tests.
6. The satellite thermal control management system of claim 1, wherein the batch process control and testing module further comprises a heating infrared test module, a thermal control satellite-mounted ground response module, and a comprehensive test process response module, wherein:
the heating infrared testing module is configured to perform heater testing on an active heater loop with power larger than 10W through an infrared imager so as to check whether silicon rubber used for adhering a heater is uniform;
the thermal control satellite-mounting ground response module is configured to detect the pasting position of the thermistor and the welding channel of the electric connector;
the comprehensive test process response module is configured to test the response relation between the heating loop and the heater through electrification, detect the response relation of the corresponding temperature control heat sensitivity through a heater switch of the closed loop in the process, and confirm the effectiveness of the heating loop.
7. The satellite thermal management system of claim 1, wherein the platform bay and the load bay of the satellite are independent bays, the load bay having an independent rotating baseline;
the platform cabin is independently controlled by a satellite computer, and a temperature control strategy with a passive mode as a main mode and an active mode as an auxiliary mode is adopted;
the load cabin carries out independent temperature control through the load management unit, and the load cabin adopts an active and passive simultaneous temperature control strategy.
8. A satellite thermal control management method is characterized by comprising the following steps:
the simulation design and optimization module simulates the space thermal environment under different orbital planes according to the launching scheme of the satellite and the working mode of each satellite to obtain the in-orbit layout result of the satellite;
in each stage of satellite design, manufacture and emission, the task allocation module maps the product management modules into a batch process control and test module according to the redundancy control function of the product management modules so as to respectively complete a plurality of parallel tasks simultaneously;
the batch production process control and test module carries out simulation analysis and verification on the conditions that the satellite is in multiple orbits, is in multiple working modes and is fully covered by the solar illumination angle according to the satellite on-orbit layout result;
in the satellite assembly stage, a product-level assembly module controls the positioning, wiring and interference checking of the thermal control product, a board-level assembly module optimizes the multilayer assembly of the thermal control product, and a final assembly module detects whether the multilayer assembly meets the thermal control requirement;
the plurality of product management modules are assigned to the product-level assembly module, board-level assembly module, and final assembly module at a satellite assembly stage;
in satellite test verification, the model thermal balance test module performs thermal balance test on the model satellite, and the positive sample thermal balance test module simultaneously performs a bottoming test on the positive sample satellite and a whole-satellite-level thermal vacuum test performed by three stars together;
the plurality of product management modules are distributed into the model thermal balance test module and the positive thermal balance test module in a satellite test stage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010493540.3A CN111651837B (en) | 2020-06-03 | 2020-06-03 | Satellite thermal control management system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010493540.3A CN111651837B (en) | 2020-06-03 | 2020-06-03 | Satellite thermal control management system and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111651837A true CN111651837A (en) | 2020-09-11 |
| CN111651837B CN111651837B (en) | 2023-03-24 |
Family
ID=72347526
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010493540.3A Active CN111651837B (en) | 2020-06-03 | 2020-06-03 | Satellite thermal control management system and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111651837B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112434909A (en) * | 2020-10-30 | 2021-03-02 | 中国空间技术研究院 | Element relationship-based mass production satellite AIT process generation method |
| CN112705920A (en) * | 2020-12-16 | 2021-04-27 | 中国科学院微小卫星创新研究院 | Satellite assembling method |
| CN113125181A (en) * | 2021-04-07 | 2021-07-16 | 深圳航天东方红卫星有限公司 | Satellite thermal control detection method and system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103324787A (en) * | 2013-06-03 | 2013-09-25 | 北京空间飞行器总体设计部 | Verification method for thermal design of volume-produced satellites |
| WO2015180000A1 (en) * | 2014-05-26 | 2015-12-03 | 中国科学院长春光学精密机械与物理研究所 | Comprehensive management system for platform and payload integrated satellite |
| CN105928723A (en) * | 2016-04-20 | 2016-09-07 | 上海微小卫星工程中心 | Flight model satellite test method and system of minisatellite |
| CN110171584A (en) * | 2019-06-19 | 2019-08-27 | 上海微小卫星工程中心 | Vacuum thermal test method for mass production of satellite constellation system |
-
2020
- 2020-06-03 CN CN202010493540.3A patent/CN111651837B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103324787A (en) * | 2013-06-03 | 2013-09-25 | 北京空间飞行器总体设计部 | Verification method for thermal design of volume-produced satellites |
| WO2015180000A1 (en) * | 2014-05-26 | 2015-12-03 | 中国科学院长春光学精密机械与物理研究所 | Comprehensive management system for platform and payload integrated satellite |
| CN105928723A (en) * | 2016-04-20 | 2016-09-07 | 上海微小卫星工程中心 | Flight model satellite test method and system of minisatellite |
| CN110171584A (en) * | 2019-06-19 | 2019-08-27 | 上海微小卫星工程中心 | Vacuum thermal test method for mass production of satellite constellation system |
Non-Patent Citations (2)
| Title |
|---|
| 周宇鹏等: "硬X射线调制望远镜卫星热设计及验证", 《航天器工程》 * |
| 周砚耕: "一种兼顾不同轨道姿态的卫星热控优化设计方法", 《空间科学学报》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112434909A (en) * | 2020-10-30 | 2021-03-02 | 中国空间技术研究院 | Element relationship-based mass production satellite AIT process generation method |
| CN112434909B (en) * | 2020-10-30 | 2023-11-10 | 中国空间技术研究院 | Factor relation-based batch satellite AIT flow generation method |
| CN112705920A (en) * | 2020-12-16 | 2021-04-27 | 中国科学院微小卫星创新研究院 | Satellite assembling method |
| CN113125181A (en) * | 2021-04-07 | 2021-07-16 | 深圳航天东方红卫星有限公司 | Satellite thermal control detection method and system |
| CN113125181B (en) * | 2021-04-07 | 2024-04-09 | 深圳航天东方红卫星有限公司 | Satellite thermal control detection method and system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111651837B (en) | 2023-03-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111651837B (en) | Satellite thermal control management system and method | |
| CN102411313B (en) | Satellite flight control closed loop simulation system based on component simulator | |
| CN110171584A (en) | Vacuum thermal test method for mass production of satellite constellation system | |
| You | Space microsystems and micro/nano satellites | |
| GB2548109A (en) | Apparatus and method for satellite payload development | |
| CN104777757A (en) | Closed-loop simulation testing system and method for ground attitude control of microsatellites | |
| CN109669472A (en) | A kind of generic concept star verification platform | |
| CN106771704B (en) | A kind of agility satellite power system power supply balanced capacity closed loop test method | |
| CN107391795A (en) | Across the CAD platform device collaboration layout method of Complex Spacecraft based on XML | |
| Parkhomenko et al. | Virtual tools and collaborative working environment in embedded system design | |
| Di Domenico et al. | STASIS: an Attitude Testbed for Hardware-in-the-Loop Simulations of Autonomous Guidance, Navigation, and Control Systems | |
| CN105843745A (en) | Method and system for testing redundancy management software | |
| CN107665616B (en) | A kind of nine-degree of freedom motion simulator relative motion equivalent method and system | |
| CN109471424B (en) | Ground simulation test system and method for large-angle momentum rotating part | |
| CN106503317B (en) | Energy supply test system based on V-I curve simulation technology | |
| Li et al. | Lessons Learned from the Development and Flight of the First Miniature Tethered Electrodynamics Experiment (MiTEE-1) | |
| Dorn | NPS-SCAT electrical power system | |
| CN114544212B (en) | Design method and system for heat balance test of complex external heat flow antenna | |
| Dickinson et al. | CYGNSS command and data subsystem and electrical power subsystem phase A and B developments | |
| Koller et al. | Lessons Learned and First Results of the E-Band CubeSat EIVE | |
| CN114757040A (en) | Microsatellite thermal balance test method and system | |
| Xin et al. | A Configuration Approach and Effectiveness Evaluation of Modular Reconfigurable Satellite | |
| Xu et al. | Design and implementation of automatic test system for multi-cabin joint test of space station | |
| CN112061422A (en) | Multifunctional integrated intelligent networking satellite architecture | |
| Shibukawa et al. | Thermal Design Approach for Efficient Development of CubeSats with a Common Bus System |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |