CN103942349A - DSM-based satellite coupling design flow structured analysis and retrieval method - Google Patents
DSM-based satellite coupling design flow structured analysis and retrieval method Download PDFInfo
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Abstract
The invention relates to a DSM-based satellite coupling design flow structured analysis and retrieval method and belongs to the field of design of spacecrafts. The method includes the first step of sorting and summarizing the general flow of designing remote sensing satellites or other types of spacecrafts on the basis of a traditional process expression mode, the second step of conducting mapping to generate a DSM matrix, conducting statistics on DSM items and conducting structured quantitative analysis item by item to obtain a perfect parameter correlation list, and the third step of utilizing the spreadsheet-based middleware technology to achieve storage of a spreadsheet in a database, and retrieving the coupling design process of the satellites according to the storage information about DSM correlation subitems in the database. According to the DSM-based satellite coupling design flow structured analysis and retrieval method, on the basis of the existing design process of the spacecrafts, the design process is mapped to generate a DSM, the DSM is stored into the database for maintenance, the Excel spreadsheet is used as a front-end interface, and consequently a foundation is laid for follow-up optimization.
Description
Technical field
The present invention relates to a kind of flowage structure fractional analysis of satellite Coupling Design and inversion method based on DSM, belong to spacecraft design field.
Background technology
Project organization matrix (Design Structure Matrix, DSM) technology is applicable to the modeling of the coupled relation of a complication system, in American-European space industry, has obtained application extensively and profoundly.DSM develops from digraph, the design factor of a certain type of formal description by math matrix, and as design parameter, design activity etc., the complex relationships such as dependence each other, restriction.In the design evolutionary process of spacecraft product, parameter configuration is constantly updated, and is tending towards ripe and stable, and finally reaches predetermined design object with the pattern of spiral iteration.By project organization matrix, can comparatively intactly reflect the potential problems in product design and process thereof, be the process restructuring in product design, the basis that organization optimization provides planning, analyzes and implement.The concept of project organization matrix is proposed in 1981 by U.S. doctor Steward the earliest, and the Roger J. at NASA langley center in 1989 is applied to first space industry and has developed the DeMAID software based on DSM.The application demonstration of NASA makes DSM theory cause extensive concern in academia and engineering circles, in a plurality of fields such as automobile, buildings, obtains more research and application.At a plurality of industrial circles such as China's space flight, by the mode of operation of serial or parallel, complication system or complex process are described traditionally, for the coupling iterative relation extensively existing in objective reality, be difficult to describe, and brought great difficulty to follow-up systematic analysis and process optimization.DSM project organization matrix is applicable to solving this difficult problem with the advantage of its iconicity, operability very much.
Institute of divine boat of the Chinese Academy of Space Technology, in carrying out the process of employee and customer training, promotes the ability of student's spacecraft design by Project, formed the spacecraft virtual design teaching platform of a set of uniqueness.Development through nearly 5 years, aspect construction of software and hardware, begin to take shape, substantially can contain majority specialty and the subject of a plurality of series such as communication, remote sensing, manned space flight, for the hundreds space flight talent has cultivated in Chinese and other countries, but also there is the unintelligible standard of flow process, integrated systematized not problem aspect integrated and design collaboration interdisciplinary, particularly lack the system platform that a spacecraft design parameter information is transmitted and linked up, parameter exchange still relies on document and meeting, and efficiency needs to be further improved.
In order to meet teaching task, student need to put spacecraft in order, particularly the general technology flow process of design of satellites, determines tentative programme design phase various information data structure and dependence, develops the software information system of a set of support design of satellites theory teaching and practice.Complicacy due to spacecraft self, relate to numerous subjects, specialty, personnel and task, and exist each other the relation of coupling, nested, iteration, maximum difficulty is how to describe exactly the information relationship between every design activity in spacecraft design process, and project organization matrix (DSM) has scientifically reflected this relation.Herein in the performance history of spacecraft virtual design teaching platform, use DSM technology to set up the universal process model of spacecraft schematic design phase, and independent development a set ofly for coupling complication system, carry out the Software tool that the DSM of modeling analysis analyzes, and apply it in the research and development of the spacecraft integrated design system based on parameter.
Summary of the invention
Coupling and a complicacy difficult problem for the R&D process analysis of large scale industry product, particularly spacecraft, a kind of method that provides process analysis for complex product or service, coupling analysis, association analysis, flow process to reproduce have been provided technology of the present invention.The method can realize the bar of complicated research object and analyze in detail, simplifies, and it is clear changing chaos, is conducive to optimization, the raising work efficiency of flow process.
The technique effect that the present invention will reach is: based on existing design of satellites flow process, shone upon and generated DSM, carried out structuring quantitative test, deposit database in and safeguard, take excel spreadsheet lattice as front-end interface, reproduce the multidisciplinary Coupling Design flow process of satellite.
The present invention has following salient feature:
1. based on existing procedure and traditional flow process form of presentation;
2. flow process mapping is generated to DSM;
3. automatically add up DSM item,
4. carry out item by item structuring quantitative test;
5. use relational database technology to carry out associated storage;
6. with Excel, as front-end interface, carry out flow process reproduction.
Technical solution of the present invention is: from people's traditional thinking mode, the flow process mapping of serial parallel pattern is generated to project organization matrix (DSM), then count all associated subitems, then it is carried out to structuring quantitative test item by item, thereby thoroughly put relation of interdependence in order; Deposited in SQL relational database, use excel spreadsheet lattice to reproduce, now original serial parallel flow process has upgraded to netted process flow diagram; By friendly man-machine interface, user is intuitively shown to incidence relation, and realize the automatic flow of data based on examination and approval workflow.
The flowage structure fractional analysis of satellite Coupling Design and the inversion method based on DSM that the present invention relates to comprise the following steps:
The first step: the flow process form of presentation based on traditional, arranges and summarize the general flow that designs satellite; The design of described satellite is divided into overall S0 and several subsystems, described several subsystems comprise load subsystem S1, rail control subsystem S2, propulsion subsystem S3, data handling subsystem S4, tracking-telemetry and command subsystem S5, thermal control subsystem S6, power subsystem S7, structure subsystem S8, and the activity of each subsystem can further be decomposed into respectively multinomial subactivity:
Overall S0 comprises: 1) development general requirements is assigned, 2) the preliminary interface of large system is coordinated, 3) each subsystem FMEA (failure mode and consequences analysis), 4) each subsystem reliability prediction, 5) dynamic imaging quality analysis, 6) image position accuracy simulation analysis, 7) image radiation quality simulation is analyzed, 8) reliability index is distributed, 9) whole star reliability prediction, 10) whole star FMEA, 11) safety Design, 12) useful load Allocation Analysis, 13) platform selecting analysis, 14) track tentative programme design, 15) population parameter budget, 16) space environment condition analysis, 17) Track desigh, 18) image geometry quality requirement is analyzed, 19) image radiation quality requirement is analyzed, 20) on star, admittedly deposit capacity requirement analysis, 21) useful load design of operating modes, 22) satellite configuration, 23) each device layout, 24) general assembly design correlation analysis,
Load subsystem S1 comprises: 1) initiating task analysis, 2) imaging mode is selected, 3) spectrum obtain manner is selected, 4) optical system type selecting, 5) sensitive detection parts type selecting, 6) on star, calibration mode is selected, 7) refrigeration modes is selected, 8) preliminary overall plan, 9) reliability, safety Design, 10) electronics conceptual design and analysis, 11) optical system conceptual design, 12) optical system MTF analyzes, 13) Scheme design, 14) structural model analysis, 15) thermal control conceptual design and thermal design, 16) calibration conceptual design, 17) scanning mechanism design, 18) two-dimensional pointing mechanism design, 19) comprehensively analyze and Performance Prediction, 20) crucial parts is debug detection scheme design, 21) optical sensor general assembly conceptual design, 22) optical sensor system test conceptual design, 23) optical sensor preliminary design review file,
Rail control subsystem S2 comprises: 1) user's request, 2) the tentative programme demonstration of system unit configuration and installation, 3) tentative programme of working pattern analysis demonstration, 4) the tentative programme demonstration that burnup is calculated, 5) tentative programme Demonstration Report, 6) project study, 7) simulating, verifying, 8) Summary on technology, 9) tackling problems in key technologies report, 10) mode of operation, 11) the first sample conceptual design of system unit configuration and installation, 12) the first sample conceptual design of Dynamic Modeling, 13) the first sample conceptual design that disturbing influence is analyzed, 14) attitude is determined the first sample conceptual design of scheme, 15) the first sample conceptual design of Scheme of Attitude Control, 16) ponent design strategy, 17) system reconfiguration strategy, 18) stability analysis of control system, 19) Digital Simulation, 20) the first sample conceptual design that burnup is calculated, 21) mission requirements analysis, 22) first sample conceptual design report PDR, 23) demand analysis of Dynamic Modeling, 24) disturbing influence is analyzed demand analysis, 25) Attitude Control Strategies, 26) attitude is determined strategy, 27) system unit configuration and installation requirements analysis, 28) demand analysis of working pattern analysis, 29) requirement analysis report, 30) tentative programme of Dynamic Modeling demonstration, 31) the tentative programme demonstration that disturbing influence is analyzed, 32) tentative programme of Scheme of Attitude Control demonstration, 33) attitude is determined the tentative programme demonstration of scheme,
Propulsion subsystem S3 comprises: 1) totally input, 2) Satellite Engine mode of operation input, 3) propulsion system task analysis, 4) propulsion system security verification, 5) propulsion system reliability demonstration, 6) propulsion system file edit, 7) propulsion system file evaluation, 8) propulsion system interface is coordinated, 9) propulsion system Scheme Choice, 10) propulsion system conceptual design, 11) propulsion system safety Design, 12) propulsion system reliability design, 13) propulsion system scheme entry evaluation, 14) set up system mathematic model, 15) propulsion system mathematical simulation, 16) tentative programme evaluation, 17) propulsion system thermal design, 18) propulsion system Seal Design, 19) propulsion system structure Intensity Design, 20) propulsion system Interface design,
Data handling subsystem S4 comprises: 1) subsystem user's request, 2) subsystem user requirements analysis, 3) bus design, 4 on star) telecommand design, 5) telemetry design, 6) thermometric, temperature control Interface design, 7) time system design, 8) Software for Design, 9) hardware design, 10) anti-irradiation, anti-SEU design, 11) reliability prediction, 12) FMEA analyzes, 13) conceptual design report writes, 14) evaluation of subsystem user requirements analysis;
Tracking-telemetry and command subsystem S5 comprises: 1) tracking-telemetry and command subsystem demand analysis, 2) subsystem tentative programme design review file edit, 3) the clear and definite development stage, workflow, 4) star ground observing and controlling demand, 5) tracking-telemetry and command subsystem external interface is coordinated, 6) reliability, the preliminary requirement of security, 7) the preliminary requirement of tracking-telemetry and command subsystem, 8) subsystem program analysis, 9) radio-frequency channel parameter designing, 10) answering machine ranging and range rate index and system design, 11) answering machine frequency acquisition following range design, 12) remote measurement system design, 13) remote control system design, 14) satellite-ground link budget, 15) with Star Service subsystem Interface design, 16) with power subsystem Interface design, 17) with overall circuit Interface design, 18) with thermal control subsystem Interface design, 19) with antenna subsystem Interface design, 20) with the design of satellite overall interface, 21) reliability, security is estimated, 22) reliability compliance test, 23) subsystem test plan,
Thermal control subsystem S6 comprises: 1) thermal control subsystem task analysis, 2) service module modeling, 3) load cabin modeling, 4) the hot physical property of material and radiation parameter are chosen, 5) instrument and equipment hear rate and well heater setting, 6) track setting, 7) outer hot-fluid calculates, 8) extreme operating condition temperature field analysis, 9) optimize thermal design parameter and meet index request, 10) determine thermal design state, 11) thermal control subsystem reliability, 12) safety analysis and design, 13) thermal control subsystem test plan, 14) the preliminary demand analysis of thermal control subsystem, 15) thermal control subsystem preliminary design review file edit, 16) satellite orbit environmental analysis, 17) plate heat-sinking capability in cabin is analyzed, 18) the average hear rate statistics of each cabin section of satellite, 19) thermal control subsystem external interface is coordinated, 20) thermal control subsystem preliminary project, 21) the preliminary thermal control design proposal in load cabin, 22) the preliminary thermal control design proposal of service module, 23) each cludy radiating surface of load cabin calculates, 24) each cludy radiating surface sketch of load cabin, 25) the special unit temperature control in load cabin demand analysis, 26) the special unit temperature control in load cabin loop primary design, 27) load cabin heat pipe type selecting, 28) load cabin heat pipe layout, 29) service module heat pipe type selecting, 30) service module heat pipe layout, 31) each cludy radiating surface of service module calculates, 32) each cludy radiating surface sketch of service module, 33) the special unit temperature control of service module demand analysis, 34) the special unit temperature control of service module loop primary design, 35) propulsion system thermal control design, 36) the outer thermal control design of satellite capsule plate, 37) satellite equipment Design of State, 38) thermal control design in satellite capsule plate, 39) thermal control subsystem primary design result,
Power subsystem S7 comprises: 1) power-supply system initiating task is analyzed, 2) determine power supply-distribution system topological structure and basic configuration, 3) the preliminary demand of solar battery array and battery pack, 4) power division requirement validation, 5) the preliminary technical requirement of power subsystem, 6) solar battery array primary design, 7) battery pack primary design, 8) power control (PCU) primary design, 9) power supply slave computer primary design, 10) distributor design, 11) distributor slave computer primary design, 12) cable system design, 13) reliability, safety analysis and design, 14) power subsystem Energy Balance Analysis, 15) power-supply system test plan, 16) power subsystem preliminary design review file edit,
Structure subsystem S8 comprises: 1) structure subsystem Development Techniques requirement, 2) overall, general assembly, thermal control interface, 3) antenna, sun wing finite element model, 4) task is clear and definite and coordinate, 5) preliminary technical requirement evaluation (PTRR), 6) structure subsystem overall design, 7) sun wing Interface design, 8) antennal interface design, 9) satellite and the rocket Interface design, 10) tank Interface design, 11) main force support structure design, 12) design of the connection between structure, 13) Heave Here design, 14) structure subsystem critical component conceptual design, 15) structure subsystem critical component mechanical analysis checking, 16) structure subsystem critical component mechanics demonstration test design, 17) set up the preliminary three-dimensional model of satellite main structure, 18) set up the preliminary finite element model of satellite main structure, 19) the preliminary static analysis of whole star, 20) the preliminary model analysis of whole star, 21) the preliminary mechanical analysis report of satellite main structure, 22) structure subsystem primary design assessment, 23) whole star mechanical test proof scheme, 24) whole star mechanical test design, 25) set up the detailed three-dimensional model of satellite main structure, 26) structure subsystem portion installing meter, 27) structure subsystem pattern design, 28) the detailed modeling of whole star finite element, 29) whole star static analysis, 30) whole star model analysis, 31) whole star Frequency Response Analysis, 32) the detailed mechanical analysis report of satellite main structure, 33) structure subsystem preliminary project evaluation (PDR),
Overall (S0) and subsystem (S1-S8) above, every subactivity of each module all forms a hybrid flow process of serial parallel jointly, as shown in Figure 1.
Second step: mapping generates DSM; Every subactivity of the described overall S0 of described design satellite and subsystem S1-S8 is arranged or cluster, as several independently element along diagonal of a matrix, arrange, form the square formation of a N * N, be referred to as N dimension DSM matrix; Then in this matrix, in the cell above or below diagonal line, mark, the principle of mark is: establish cell (i, j) represent that i is capable, j column unit lattice, when i the element that starts number on and if only if diagonal line from the upper left corner have information transmission to j unit, be designated as 1, can be denoted as D (i, j)=1; Otherwise D (j, i)=1 represents that on diagonal line, j element have information transmission to i unit; If there is no information dependence between two elements, be designated as 0 or give over to blank; As D (m, n)=0, representing does not have information from m element flow to n element;
The 3rd step: statistics DSM item; For described N dimension DSM matrix, since the 1st row or the 1st row, travel through line by line or by column, the associated subitem of non-zero in cell on all off-diagonals/non-NULL is out exhaustive, and be numbered in order, supplement item by item again the details of upper two associated element, form a form, described details comprise title, the bullets of element;
The 4th step: carry out item by item structuring quantitative test; By every association in above table, carry out deep anatomy, according to predefined structured analysis masterplate side information, further exhaustively go out all associated subitems, thereby realize information Accurate Model and the transmission between satellite subsystem design subactivity;
The 5th step: use electrical form middleware Technology and the SQL relational database technologies such as ExcelSever, store the managing detailed catalogue of above-mentioned associated subitem;
The 6th step: according to the storage information for the associated subitem of DSM in database, be finally inversed by the Coupling Design flow process of satellite, the concrete steps of described Coupling Design flow process comprise:
1) according to the code name of current each subsystem of satellite, inquire about and obtain all subactivity collection A, by it, according to activity, serial number and the bullets in subsystem inside carries out ascending order arrangement;
2) according to data correlation, inquire about the external activity item collection B of subsystem relevant to all subactivitys of current subsystem, that come from other, equally it is arranged according to affiliated subsystem ascending order;
3) the subsystem collection C under each outside design activity in statistics set B;
4) according to order from left to right, from top to bottom, generate successively each subactivity picture frame that A collection, C are concentrated;
5), for the association of subsystem inside, starting point and terminal are mobile element in A collection, can tieline, from the right side anchor point of starting point activity picture frame, be connected to the left side anchor point of the movable picture frame of terminal; Travel through all associated subitems of well-behaved internal system, until the association line between active set A inner element is all generated;
6) for the association across subsystem, one is outside subsystem, another is the specific design activity of current subsystem, and the starting point of line is still for the right side anchor point of the design activity picture frame of information output is provided, and terminal is the left side anchor point of design activity of input of receiving information.
Preferably, operating in Microsoft Office Excel of described second step defines according to structurized masterplate.
Preferably, in the influential position, the upper left corner of described masterplate, mark the object of current DSM matrix analysis and the relevant agreement of making a report on, then on diagonal line, will except current subsystem, other subsystems arrange in order, and then place in order every subactivity of current subsystem.On diagonal line, element is all used the eye-catching sign of black underframe white text, the place of diagonal line above and below mark " 1 " represents that this place exists the transitive relation of information, the flow direction of information along clockwise direction, information always the diagonal entry from be expert at " 1 " flow to the diagonal entry in column.Upper left matrix area is the association across subsystem, and bottom right matrix area is the data correlation of subsystem inside.
Preferably, in described the 4th step, described form is carried out to sub-argument according to the difference of the corresponding starting point of described associations, terminal, here unification has adopted standard masterplate to analyze associated data, comprises the fields such as variable name, data type, dimension, variable range, default value, variable description.
Preferably, design process for more complicated satellite, can first be about to that it is decomposed into submodule, the single submodule of then take after decomposing carries out structuring quantitative test as research object, by above-mentioned structuring quantitative analysis results according to module carry out DSM matrix along cornerwise splicing, can obtain more massive comprehensive DSM; Association between modules can also be carried out to interface refinement, thereby realize information Accurate Model and transmission between ultra-large satellite subsystem design subactivity.
Preferably, in described the 5th step, be decomposed in advance 2-10 submodule, the scale of each submodule DSM analysis matrix is controlled at 10～40 subactivitys.
Preferably, in described the 6th step, information association and FB(flow block) are drawn line according to the flow direction of data correlation, not only have incidence relation from front to back, also have from rear associated to front feedback, thereby obtain a coupling flow process that reflects the true process of design of satellites iteration.
Preferably, in described the 6th step, in order to realize the traversal of all design activities, the method that employing sequentially travels through or recurrence travels through, guarantees that all activities and associations are all plotted on guide graphical interfaces according to pre-defined rule.
Preferably, in described the 6th step, in order simplifying across the association of subsystem, to show, and to make interface parameters distincter, to coming from picture frame that the design activity of current subsystem outside only retains subsystem under it with associated, Transfer Parameters item is merged.
The present invention, by above step, has provided the method that complication system or product carry out association analysis, has provided some the most frequently used analysis masterplates simultaneously.
Major advantage of the present invention is: with a kind of structured analysis method of easy operating, complete and explain scrupulously the complex process of large scale industry product or service, there is the unlimited statement degree of depth, and make it to become and can supply client's analytical approach easy to use.
Accompanying drawing explanation
The string that Fig. 1 satellite system is overall hybrid design cycle (part)
The DSM structured analysis tools interfaces of Fig. 2 satellite power supply subsystem based on electrical form
Fig. 3 adds up the analysis tool interface of DSM associations automatically
Fig. 4 is the parameter information assay surface of node one by one
The form that embodies of Fig. 5 information association item content
Fig. 6 satellite modules design cycle and reproduction thereof (part)
Embodiment
With regard to the load subsystem S1 of remote sensing satellite, be only embodiment herein, by reference to the accompanying drawings structured process analytical approach of the present invention described in detail.Remote sensing satellite other each subsystem and analytic process and the following description all fours of each subsystem of other spacecrafts designs such as telstar, landsat, those skilled in the art have the ability to draw inferences about other cases from one instance, and at this, do not repeat.
The first step: the flow process form of presentation based on traditional, arranges and summarize the general flow that designs remote sensing satellite load-antenna subsystem, load subsystem S1 comprises: 1) initiating task analysis, 2) imaging mode is selected, 3) spectrum obtain manner is selected, 4) optical system type selecting, 5) sensitive detection parts type selecting, 6) on star, calibration mode is selected, 7) refrigeration modes is selected, 8) preliminary overall plan, 9) reliability, safety Design, 10) electronics conceptual design and analysis, 11) optical system conceptual design, 12) optical system MTF analyzes (MTF, be Modulation Transfer Function, optical transfer function, to characterize the transmission performance of optical system to the objective function of different space frequency, it introduces applied optics field by this mathematical tool of Fourier transform, thereby making image quality evaluation have Mathematics Proof, is one of the leading indicator of the image quality evaluation of current optical system), 13) Scheme design, 14) structural model analysis, 15) thermal control conceptual design and thermal design, 16) calibration conceptual design, 17) scanning mechanism design, 18) two-dimensional pointing mechanism design, 19) comprehensively analyze and Performance Prediction, 20) crucial parts is debug detection scheme design, 21) optical sensor general assembly conceptual design, 22) optical sensor system test conceptual design, 23) optical sensor preliminary design review file, an above hybrid flow process of serial parallel of the common formation of every subactivity, as shown in Figure 1.
Second step: mapping generates DSM.Links in above-mentioned general flow is arranged a little (indivisible or be closely related carried out cluster), as several independently element along diagonal of a matrix, arrange, form the square formation (DSM-Product Design Matrix) of a N * N, be referred to as N dimension DSM matrix; Then in this matrix, in the cell above or below diagonal line, mark.The principle of mark is, establishes cell (i, j) and represents that i is capable, j column unit lattice, when i the element that starts number on and if only if diagonal line from the upper left corner have information transmission to j unit, is designated as 1, can be denoted as D (i, j)=1; Otherwise D (j, i)=1 represents that on diagonal line, j element have information transmission to i unit.If there is no information dependence between two elements, be designated as 0 or give over to blank.As D (m, n)=0, representing does not have information from m element flow to n element.
Aforesaid operations defines according to structurized masterplate in Microsoft Office Excel again.As shown in Figure 2, in the influential position, the upper left corner of this form masterplate, mark the object of current DSM matrix analysis and the relevant agreement of making a report on.Then on diagonal line, will except current subsystem, other subsystems arrange in order, and then place in order each activity of current subsystem.On diagonal line, element is all used the eye-catching sign of black underframe white text, the place of diagonal line above and below mark " 1 " represents that this place exists the transitive relation of information, the flow direction of information along clockwise direction, information always the diagonal entry from be expert at " 1 " flow to the diagonal entry in column.Upside and left side matrix area are associated across subsystem, and lower right area is the data correlation of subsystem inside.
The 3rd step: automatically add up DSM item.For N dimension DSM matrix, since the 1st row or the 1st row, travel through line by line or by column, the associations of non-zero in cell on all off-diagonals/non-NULL is out exhaustive, and be numbered in order, the details (comprising the title, bullets of element etc.) of supplementing item by item upper two associated element, form a list.
After DSM analysis matrix travels through, can obtain form as shown in Figure 3, list and had associated all items.Association is expressed with the form of D (a, b), and wherein " D " means " Dependency " (association), and a is the serial number of starting point activity, and b is the serial number of terminal activity; In addition the information such as bullets, activity name that also have, terminal.With current associations of ASCII character character visual representation such as pentagram (★), dicyclos (◎), be forward transmission or information feedback; With colouring information, indicate whether associations is the association across subsystem.
The 4th step: carry out item by item structuring quantitative test.By every association in above-mentioned list, carry out deep anatomy, according to predefined structured analysis masterplate side information, further exhaustively go out all associated subitems, thereby realize information Accurate Model and the transmission between remote sensing satellite Subsystem Design subactivity.。
This step can first be carried out the parameter information analysis of node one by one, obtains form as shown in Figure 4; Then above table is carried out to sub-argument according to the difference of the corresponding starting point of associations, terminal, obtain form as shown in Figure 5.Here unification has adopted standard masterplate to analyze associated data, comprises the fields such as variable name, data type, dimension, variable range, default value, variable description.
The 5th step: use ExcelSever electrical form middleware Technology and SQL relational database technology, store the managing detailed catalogue of above-mentioned associated subitem; It is representative that ExcelSever electrical form middleware Technology described in the application be take the ExcelServer software of Beijing Qin Zhe company, and described SQL refers to Structured Query Language (SQL).
The 6th step: according to the storage information for the associated subitem of DSM in database, be finally inversed by the Coupling Design flow process of satellite, as shown in Figure 6, the concrete steps of described Coupling Design flow process comprise:
1) according to the code name of current each subsystem of satellite, inquire about and obtain all subactivity collection A, by it, according to activity, serial number and the bullets in subsystem inside carries out ascending order arrangement;
2) according to data correlation, inquire about the external activity item collection B of subsystem relevant to all subactivitys of current subsystem, that come from other, equally it is arranged according to affiliated subsystem ascending order;
3) the subsystem collection C under each outside design activity in statistics set B;
4) according to order from left to right, from top to bottom, generate successively each subactivity picture frame that A collection, C are concentrated;
5), for the association of subsystem inside, starting point and terminal are mobile element in A collection, can tieline, from the right side anchor point of starting point activity picture frame, be connected to the left side anchor point of the movable picture frame of terminal; Travel through all associated subitems of well-behaved internal system, until the association line between active set A inner element is all generated;
6) for the association across subsystem, one is outside subsystem, another is the specific design activity of current subsystem, and the starting point of line is still for the right side anchor point of the design activity picture frame of information output is provided, and terminal is the left side anchor point of design activity of input of receiving information.
For complicated especially product and system, can first be about to that it is decomposed into several subsystems or submodule, then take single subsystem after decomposing or module carries out above-mentioned analysis as research object.Can accomplish in theory a unlimited level of nesting, here author recommends to carry out the decomposition of 2-10 submodule, the scale of each submodule DSM analysis matrix is controlled at 10～40 movable blocks, by above-mentioned analysis result according to bulk carry out DSM matrix along cornerwise splicing, can obtain more massive comprehensive DSM; Association between modules can also be carried out to interface refinement, thereby realize information Accurate Model and transmission between ultra-large design activity.
Operating in Microsoft Office Excel of described second step defines according to structurized masterplate.
In the influential position, the upper left corner of described masterplate, mark the object of current DSM matrix analysis and the relevant agreement of making a report on, then on diagonal line, will except current subsystem, other subsystems arrange in order, and then place in order every subactivity of current subsystem.On diagonal line, element is all used the eye-catching sign of black underframe white text, the place of diagonal line above and below mark " 1 " represents that this place exists the transitive relation of information, the flow direction of information along clockwise direction, information always the diagonal entry from be expert at " 1 " flow to the diagonal entry in column.Upper left matrix area is the association across subsystem, and bottom right matrix area is the data correlation of subsystem inside.
In described the 4th step, described form is carried out to sub-argument according to the difference of the corresponding starting point of described associations, terminal, here unification has adopted standard masterplate to analyze associated data, comprises the fields such as variable name, data type, dimension, variable range, default value, variable description.
Design process for more complicated satellite, can first be about to that it is decomposed into submodule, the single submodule of then take after decomposing carries out structuring quantitative test as research object, by above-mentioned structuring quantitative analysis results according to module carry out DSM matrix along cornerwise splicing, can obtain more massive comprehensive DSM; Association between modules can also be carried out to interface refinement, thereby realize information Accurate Model and transmission between ultra-large satellite subsystem design subactivity.
In described the 5th step, be decomposed in advance 2-10 submodule, the scale of each submodule DSM analysis matrix is controlled at 10～40 subactivitys, so carries out from top to bottom the decomposition of 2～5 levels.
In described the 6th step, information association and FB(flow block) are drawn line according to the flow direction of data correlation, not only have incidence relation from front to back, also have from rear associated to front feedback, thereby obtain a coupling flow process that reflects the true process of design of satellites iteration.
In described the 6th step, in order to realize the traversal of all design activities, the method that employing sequentially travels through or recurrence travels through, guarantees that all activities and associations are all plotted on guide graphical interfaces according to pre-defined rule.
In described the 6th step, in order simplifying across the association of subsystem, to show, and to make interface parameters distincter, to coming from picture frame that the design activity of current subsystem outside only retains subsystem under it with associated, Transfer Parameters item is merged.
In described the 6th step, information association and FB(flow block) are drawn line according to the flow direction of data correlation, not only have incidence relation from front to back, also have from rear associated to front feedback, thereby obtain a coupling flow process that reflects the true process of design of satellites iteration.In order to realize the traversal of all design activities, the method that employing sequentially travels through or recurrence travels through, guarantees that all activities and associations are all plotted on guide graphical interfaces according to pre-defined rule.In described the 6th step, in order simplifying across the association of subsystem, to show, and to make interface parameters distincter, to coming from picture frame that the design activity of current subsystem outside only retains subsystem under it with associated, Transfer Parameters item is merged.
Claims (10)
1. the flowage structure fractional analysis of satellite Coupling Design and the inversion method based on DSM, is characterized in that, described analytical approach comprises the following steps:
The first step: the flow process form of presentation based on traditional, arranges and summarize the general flow that designs satellite; The design of described satellite is divided into overall S0 and several subsystems, described several subsystems comprise load subsystem S1, rail control subsystem S2, propulsion subsystem S3, data handling subsystem S4, tracking-telemetry and command subsystem S5, thermal control subsystem S6, power subsystem S7, structure subsystem S8, and the activity of each subsystem can further be decomposed into respectively multinomial subactivity:
Overall S0 comprises: 1) development general requirements is assigned, 2) the preliminary interface of large system is coordinated, 3) each subsystem FMEA, 4) each subsystem reliability prediction, 5) dynamic imaging quality analysis, 6) image position accuracy simulation analysis, 7) image radiation quality simulation is analyzed, 8) reliability index is distributed, 9) whole star reliability prediction, 10) whole star FMEA, 11) safety Design, 12) useful load Allocation Analysis, 13) platform selecting analysis, 14) track tentative programme design, 15) population parameter budget, 16) space environment condition analysis, 17) Track desigh, 18) image geometry quality requirement is analyzed, 19) image radiation quality requirement is analyzed, 20) on star, admittedly deposit capacity requirement analysis, 21) useful load design of operating modes, 22) satellite configuration, 23) each device layout, 24) general assembly design correlation analysis,
Load subsystem S1 comprises: 1) initiating task analysis, 2) imaging mode is selected, 3) spectrum obtain manner is selected, 4) optical system type selecting, 5) sensitive detection parts type selecting, 6) on star, calibration mode is selected, 7) refrigeration modes is selected, 8) preliminary overall plan, 9) reliability, safety Design, 10) electronics conceptual design and analysis, 11) optical system conceptual design, 12) optical system MTF analyzes, 13) Scheme design, 14) structural model analysis, 15) thermal control conceptual design and thermal design, 16) calibration conceptual design, 17) scanning mechanism design, 18) two-dimensional pointing mechanism design, 19) comprehensively analyze and Performance Prediction, 20) crucial parts is debug detection scheme design, 21) optical sensor general assembly conceptual design, 22) optical sensor system test conceptual design, 23) optical sensor preliminary design review file,
Rail control subsystem S2 comprises: 1) user's request, 2) the tentative programme demonstration of system unit configuration and installation, 3) tentative programme of working pattern analysis demonstration, 4) the tentative programme demonstration that burnup is calculated, 5) tentative programme Demonstration Report, 6) project study, 7) simulating, verifying, 8) Summary on technology, 9) tackling problems in key technologies report, 10) mode of operation, 11) the first sample conceptual design of system unit configuration and installation, 12) the first sample conceptual design of Dynamic Modeling, 13) the first sample conceptual design that disturbing influence is analyzed, 14) attitude is determined the first sample conceptual design of scheme, 15) the first sample conceptual design of Scheme of Attitude Control, 16) ponent design strategy, 17) system reconfiguration strategy, 18) stability analysis of control system, 19) Digital Simulation, 20) the first sample conceptual design that burnup is calculated, 21) mission requirements analysis, 22) first sample conceptual design report PDR, 23) demand analysis of Dynamic Modeling, 24) disturbing influence is analyzed demand analysis, 25) Attitude Control Strategies, 26) attitude is determined strategy, 27) system unit configuration and installation requirements analysis, 28) demand analysis of working pattern analysis, 29) requirement analysis report, 30) tentative programme of Dynamic Modeling demonstration, 31) the tentative programme demonstration that disturbing influence is analyzed, 32) tentative programme of Scheme of Attitude Control demonstration, 33) attitude is determined the tentative programme demonstration of scheme,
Propulsion subsystem S3 comprises: 1) totally input, 2) Satellite Engine mode of operation input, 3) propulsion system task analysis, 4) propulsion system security verification, 5) propulsion system reliability demonstration, 6) propulsion system file edit, 7) propulsion system file evaluation, 8) propulsion system interface is coordinated, 9) propulsion system Scheme Choice, 10) propulsion system conceptual design, 11) propulsion system safety Design, 12) propulsion system reliability design, 13) propulsion system scheme entry evaluation, 14) set up system mathematic model, 15) propulsion system mathematical simulation, 16) tentative programme evaluation, 17) propulsion system thermal design, 18) propulsion system Seal Design, 19) propulsion system structure Intensity Design, 20) propulsion system Interface design,
Data handling subsystem S4 comprises: 1) subsystem user's request, 2) subsystem user requirements analysis, 3) bus design, 4 on star) telecommand design, 5) telemetry design, 6) thermometric, temperature control Interface design, 7) time system design, 8) Software for Design, 9) hardware design, 10) anti-irradiation, anti-SEU design, 11) reliability prediction, 12) FMEA analyzes, 13) conceptual design report writes, 14) evaluation of subsystem user requirements analysis;
Tracking-telemetry and command subsystem S5 comprises: 1) tracking-telemetry and command subsystem demand analysis, 2) subsystem tentative programme design review file edit, 3) the clear and definite development stage, workflow, 4) star ground observing and controlling demand, 5) tracking-telemetry and command subsystem external interface is coordinated, 6) reliability, the preliminary requirement of security, 7) the preliminary requirement of tracking-telemetry and command subsystem, 8) subsystem program analysis, 9) radio-frequency channel parameter designing, 10) answering machine ranging and range rate index and system design, 11) answering machine frequency acquisition following range design, 12) remote measurement system design, 13) remote control system design, 14) satellite-ground link budget, 15) with Star Service subsystem Interface design, 16) with power subsystem Interface design, 17) with overall circuit Interface design, 18) with thermal control subsystem Interface design, 19) with antenna subsystem Interface design, 20) with the design of satellite overall interface, 21) reliability, security is estimated, 22) reliability compliance test, 23) subsystem test plan,
Thermal control subsystem S6 comprises: 1) thermal control subsystem task analysis, 2) service module modeling, 3) load cabin modeling, 4) the hot physical property of material and radiation parameter are chosen, 5) instrument and equipment hear rate and well heater setting, 6) track setting, 7) outer hot-fluid calculates, 8) extreme operating condition temperature field analysis, 9) optimize thermal design parameter and meet index request, 10) determine thermal design state, 11) thermal control subsystem reliability, 12) safety analysis and design, 13) thermal control subsystem test plan, 14) the preliminary demand analysis of thermal control subsystem, 15) thermal control subsystem preliminary design review file edit, 16) satellite orbit environmental analysis, 17) plate heat-sinking capability in cabin is analyzed, 18) the average hear rate statistics of each cabin section of satellite, 19) thermal control subsystem external interface is coordinated, 20) thermal control subsystem preliminary project, 21) the preliminary thermal control design proposal in load cabin, 22) the preliminary thermal control design proposal of service module, 23) each cludy radiating surface of load cabin calculates, 24) each cludy radiating surface sketch of load cabin, 25) the special unit temperature control in load cabin demand analysis, 26) the special unit temperature control in load cabin loop primary design, 27) load cabin heat pipe type selecting, 28) load cabin heat pipe layout, 29) service module heat pipe type selecting, 30) service module heat pipe layout, 31) each cludy radiating surface of service module calculates, 32) each cludy radiating surface sketch of service module, 33) the special unit temperature control of service module demand analysis, 34) the special unit temperature control of service module loop primary design, 35) propulsion system thermal control design, 36) the outer thermal control design of satellite capsule plate, 37) satellite equipment Design of State, 38) thermal control design in satellite capsule plate, 39) thermal control subsystem primary design result,
Power subsystem S7 comprises: 1) power-supply system initiating task is analyzed, 2) determine power supply-distribution system topological structure and basic configuration, 3) the preliminary demand of solar battery array and battery pack, 4) power division requirement validation, 5) the preliminary technical requirement of power subsystem, 6) solar battery array primary design, 7) battery pack primary design, 8) power control (PCU) primary design, 9) power supply slave computer primary design, 10) distributor design, 11) distributor slave computer primary design, 12) cable system design, 13) reliability, safety analysis and design, 14) power subsystem Energy Balance Analysis, 15) power-supply system test plan, 16) power subsystem preliminary design review file edit,
Structure subsystem S8 comprises: 1) structure subsystem Development Techniques requirement, 2) overall, general assembly, thermal control interface, 3) antenna, sun wing finite element model, 4) task is clear and definite and coordinate, 5) preliminary technical requirement evaluation (PTRR), 6) structure subsystem overall design, 7) sun wing Interface design, 8) antennal interface design, 9) satellite and the rocket Interface design, 10) tank Interface design, 11) main force support structure design, 12) design of the connection between structure, 13) Heave Here design, 14) structure subsystem critical component conceptual design, 15) structure subsystem critical component mechanical analysis checking, 16) structure subsystem critical component mechanics demonstration test design, 17) set up the preliminary three-dimensional model of satellite main structure, 18) set up the preliminary finite element model of satellite main structure, 19) the preliminary static analysis of whole star, 20) the preliminary model analysis of whole star, 21) the preliminary mechanical analysis report of satellite main structure, 22) structure subsystem primary design assessment, 23) whole star mechanical test proof scheme, 24) whole star mechanical test design, 25) set up the detailed three-dimensional model of satellite main structure, 26) structure subsystem portion installing meter, 27) structure subsystem pattern design, 28) the detailed modeling of whole star finite element, 29) whole star static analysis, 30) whole star model analysis, 31) whole star Frequency Response Analysis, 32) the detailed mechanical analysis report of satellite main structure, 33) structure subsystem preliminary project evaluation (PDR),
The hybrid flow process of serial parallel of the common formation of every subactivity of above overall S0 and subsystem S1-S8 and corresponding subsystem.
Second step: mapping generates DSM; Every subactivity of the described overall S0 of described design satellite and subsystem S1-S8 is arranged or cluster, as several independently element along diagonal of a matrix, arrange, form the square formation of a N * N, be referred to as N dimension DSM matrix; Then in this matrix, in the cell above or below diagonal line, mark, the principle of mark is: establish cell (i, j) represent that i is capable, j column unit lattice, when i the element that starts number on and if only if diagonal line from the upper left corner have information transmission to j unit, be designated as 1, can be denoted as D (i, j)=1; Otherwise D (j, i)=1 represents that on diagonal line, j element have information transmission to i unit; If there is no information dependence between two elements, be designated as 0 or give over to blank; As D (m, n)=0, representing does not have information from m element flow to n element;
The 3rd step: automatically add up DSM item; For described N dimension DSM matrix, since the 1st row or the 1st row, travel through line by line or by column, the associated subitem of non-zero in cell on all off-diagonals/non-NULL is out exhaustive, and be numbered in order, supplement item by item again the details of upper two associated element, form a form, described details comprise title, the bullets of element;
The 4th step: carry out item by item structuring quantitative test; By every association in above table, carry out deep anatomy, according to predefined structured analysis masterplate side information, further exhaustively go out all associated subitems, thereby realize information Accurate Model and the transmission between satellite subsystem design subactivity;
The 5th step: use ExcelSever electrical form middleware Technology and SQL relational database technology, store the managing detailed catalogue of above-mentioned associated subitem;
The 6th step: according to the storage information for the associated subitem of DSM in database, be finally inversed by the Coupling Design flow process of satellite, the concrete steps of described Coupling Design flow process comprise:
1) according to the code name of current each subsystem of satellite, inquire about and obtain all subactivity collection A, by it, according to activity, serial number and the bullets in subsystem inside carries out ascending order arrangement;
2) according to data correlation, inquire about the external activity item collection B of subsystem relevant to all subactivitys of current subsystem, that come from other, equally it is arranged according to affiliated subsystem ascending order;
3) the subsystem collection C under each outside design activity in statistics set B;
4) according to order from left to right, from top to bottom, generate successively each subactivity picture frame that A collection, C are concentrated;
5), for the association of subsystem inside, starting point and terminal are mobile element in A collection, can tieline, from the right side anchor point of starting point activity picture frame, be connected to the left side anchor point of the movable picture frame of terminal; Travel through all associated subitems of well-behaved internal system, until the association line between active set A inner element is all generated;
6) for the association across subsystem, one is outside subsystem, another is the specific design activity of current subsystem, and the starting point of line is still for the right side anchor point of the design activity picture frame of information output is provided, and terminal is the left side anchor point of design activity of input of receiving information.
2. a kind of flowage structure fractional analysis of satellite Coupling Design and inversion method based on DSM according to claim 1, is characterized in that, operating in Microsoft Office Excel of described second step defines according to structurized masterplate.
3. a kind of flowage structure fractional analysis of satellite Coupling Design and inversion method based on DSM according to claim 2, it is characterized in that, in the influential position, the upper left corner of described masterplate, mark the object of current DSM matrix analysis and the relevant agreement of making a report on, then on diagonal line, will except current subsystem, other subsystems arrange in order, and then place in order every subactivity of current subsystem.On diagonal line, element is all used the eye-catching sign of black underframe white text, the place of diagonal line above and below mark " 1 " represents that this place exists the transitive relation of information, the flow direction of information along clockwise direction, information always the diagonal entry from be expert at " 1 " flow to the diagonal entry in column.Upper left matrix area is the association across subsystem, and bottom right matrix area is the data correlation of subsystem inside.
4. a kind of flowage structure fractional analysis of satellite Coupling Design and inversion method based on DSM according to claim 1, it is characterized in that, in described the 4th step, described form is carried out to sub-argument according to the difference of the corresponding starting point of described associated subitem, terminal, here unification has adopted standard masterplate to analyze associated data, comprises at least one in variable name, data type, dimension, variable range, default value, variable description.
5. a kind of flowage structure fractional analysis of satellite Coupling Design and inversion method based on DSM according to claim 1, it is characterized in that, design process for more complicated satellite, can first be about to that it is decomposed into several submodules, the single submodule of then take after decomposing carries out structuring quantitative test as research object, by above-mentioned structuring quantitative analysis results according to module carry out DSM matrix along cornerwise splicing, can obtain more massive comprehensive DSM; Association between modules can also be carried out to interface refinement, thereby realize information Accurate Model and transmission between ultra-large satellite subsystem design subactivity.
6. a kind of flowage structure fractional analysis of satellite Coupling Design and inversion method based on DSM according to claim 1, it is characterized in that, be decomposed in advance 2～10 submodules, the scale of each submodule DSM analysis matrix is controlled at 10～40 subactivitys, so carries out from top to bottom the decomposition of 2～5 levels.
7. a kind of flowage structure fractional analysis of satellite Coupling Design and inversion method based on DSM according to claim 1, it is characterized in that, in described the 6th step, information association and FB(flow block) are drawn line according to the flow direction of data correlation, not only there is incidence relation from front to back, also have from rear associated to front feedback, thereby obtain a coupling flow process that reflects the true process of design of satellites iteration.
8. a kind of flowage structure fractional analysis of satellite Coupling Design and inversion method based on DSM according to claim 1, it is characterized in that, in described the 6th step, in order to realize the traversal of all design activities, the method that employing sequentially travels through or recurrence travels through, guarantees that all activities and associations are all plotted on guide graphical interfaces according to pre-defined rule.
9. a kind of flowage structure fractional analysis of satellite Coupling Design and inversion method based on DSM according to claim 1, it is characterized in that, in described the 6th step, for the association of simplifying across subsystem shows, and make interface parameters distincter, to coming from picture frame that the design activity of current subsystem outside only retains subsystem under it with associated, Transfer Parameters item is merged by affiliated subsystem.
10. a kind of flowage structure fractional analysis of satellite Coupling Design and inversion method based on DSM according to claim 1, it is characterized in that, in described the 6th step, the associated definition of DSM masterplate carries out after newly-built, the modification, deletion action of relevant parameter item, can automatically refresh the displaying of DSM matrix, and automatically refresh the design cycle guide of corresponding described each subsystem of satellite.
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