CN108170963A - The automation computational methods and device of solid-liquid rocket flight reappearance characteristic - Google Patents
The automation computational methods and device of solid-liquid rocket flight reappearance characteristic Download PDFInfo
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Abstract
The present invention provides the automation computational methods and device of a kind of solid-liquid rocket flight reappearance characteristic, are related to computer realm, with alleviate heavy workload in the prior art, it is inefficient the technical issues of.This method is simple and efficient, can accurately realize that result exports, improve user experience.This method includes：Receive parameter information input by user；Wherein, the parameter information includes solid-liquid engine fuel burning data file and rocket structure parameter；The quality center of mass performance data of the entire flight course of solid-liquid rocket is generated according to the parameter information；The quality center of mass performance data is exported.
Description
Technical field
The present invention relates to technical field of data processing, more particularly, to a kind of automation of solid-liquid rocket flight reappearance characteristic
Computational methods and device.
Background technology
Rocket master-plan is a comprehensive considering various effects, meets the process of multinomial performance index, and rocket is overall
The calculating of mass property analysis especially barycenter and rotary inertia is the important work of one of which.Rocket is designed outside structure
Shape after determining installation equipment and engine parameter, needs to be changed according to mass property during actual conditions and rocket flight,
Carry out the flight aerodynamics simu1ation simulation of rocket, and then matching control system.It is therefore desirable to for designed the rocket of completion into
The mass property calculation of row entirety flight course.Since solid-liquid engine is related to including the tank of liquid oxidizer, gas is included
Gas cylinder of body etc., therefore the flight reappearance characteristic calculating of solid-liquid rocket is more complicated, factor needed to be considered is also more.
In current rocket master-plan, the design of rocket will often iterate repeatedly, and workload is very big.And it lacks now
A kind of weary for solid-liquid rocket mass property effective and efficiently computational methods, also lack efficiently, easily calculating instrument, this
Result in the inefficient of solid-liquid rocket design iteration process.
In view of the above-mentioned problems, solution also not yet in effect at present.
Invention content
In view of this, the purpose of the present invention is to provide a kind of automation computational methods of solid-liquid rocket flight reappearance characteristic
And device, with alleviate heavy workload in the prior art, it is inefficient the technical issues of.
In a first aspect, an embodiment of the present invention provides a kind of automation computational methods of solid-liquid rocket flight reappearance characteristic,
Including：
Receive parameter information input by user；Wherein, the parameter information includes solid-liquid engine fuel burning data text
Part and rocket structure parameter；
The quality center of mass performance data of the entire flight course of solid-liquid rocket is generated according to the parameter information；
The quality center of mass performance data is exported.
With reference to first aspect, an embodiment of the present invention provides the first possible embodiment of first aspect, wherein, institute
It states and exports the quality center of mass performance data, specifically include：
The quality center of mass performance data is written according to preset format in the table automatically generated, generation tables of data text
Part；
The data list file of generation is stored in designated position；
And/or
According to the quality center of mass performance data, change curve is generated；
The change curve is exported to display interface.
With reference to first aspect, an embodiment of the present invention provides second of possible embodiment of first aspect, wherein, institute
The quality center of mass performance data that the entire flight course of solid-liquid rocket is generated according to the parameter information is stated, is specifically included：
Gas cylinder system is obtained using the initial pressure of gas cylinder of the gas cylinder computation model in parameter information and Mass Calculation
First quality center of mass performance data；
The of tank system is calculated using oxidizer flow rate of the oxidant tank computation model in parameter information
Two quality center of mass performance datas；
It is calculated using ground test data of the combustion chamber computation model in parameter information, obtains chamber system
Third quality center of mass performance data；
Above-mentioned first quality center of mass performance data, the second quality characteristics data and third quality characteristics data are counted
It calculates, generates the quality center of mass performance data of the entire flight course of solid-liquid rocket.
Second of possible embodiment with reference to first aspect, an embodiment of the present invention provides the third of first aspect
Possible embodiment, wherein, this method further includes：
Rational Simplification is carried out to oxidant tank, gas cylinder and combustor section respectively, structure obtains the calculating of oxidant tank
Model, gas cylinder computation model and combustion chamber computation model.
The third possible embodiment with reference to first aspect, an embodiment of the present invention provides the 4th kind of first aspect
Possible embodiment, wherein, it is described that Rational Simplification is carried out to oxidant tank, gas cylinder and combustor section respectively, it builds
To oxidant tank computation model, gas cylinder computation model and combustion chamber computation model, specifically include：
Process to simplify the calculation makees following basic assumption：
Gas cylinder calculating section, it is assumed that gas is cylinder in gas cylinder, even variation in outer radial；
Oxidant tank calculating section, it is assumed that tank hydrogen peroxide is cylinder, even variation in outer radial, and is simplified
Tank liquid capsule model is 2mm thickness sleeves；
Combustion chamber calculating section, it is assumed that the powder column of solid-liquid engine is single-hole cylindrical body, and only internal bore burning, powder uniformly moves back
It moves；
Based on above-mentioned basic assumption, corresponding oxidant tank computation model, gas cylinder computation model and burning are established respectively
Room computation model.
Second aspect, an embodiment of the present invention provides a kind of automation computing device of solid-liquid rocket flight reappearance characteristic,
Including：
MIM message input module, for receiving parameter information input by user；Wherein, the parameter information starts including solid-liquid
Machine fuel combustion data file and rocket structure parameter；
Computing module, for generating the quality center of mass characteristic quantity of the entire flight course of solid-liquid rocket according to the parameter information
According to；
Output module, for the quality center of mass performance data to be exported.
With reference to second aspect, an embodiment of the present invention provides the first possible embodiment of second aspect, wherein, institute
It states MIM message input module and includes the first input module and the second input module；
First input module is used to receive rocket structure parameter input by user；Wherein, first input module includes
Architecture quality window, structure barycenter window, rotary inertia Ix windows, rotary inertia Iy windows, oxidant parameter window, gas cylinder pressure
Power window, whole rocket length window；
Second input module is used to receive solid-liquid engine fuel burning data file input by user.
With reference to second aspect, an embodiment of the present invention provides second of possible embodiment of second aspect, wherein, institute
It states output module and includes the first output module and the second output module；
First output module is used for automatically generate the quality center of mass performance data according to preset format write-in
In table, data list file is generated；The data list file of generation is stored in designated position；
Second output module is used to, according to the quality center of mass performance data, generate change curve；By the variation
Curve is exported to display interface.
With reference to second aspect, an embodiment of the present invention provides the third possible embodiment of second aspect, wherein, it should
Device further includes：
Study module, for carrying out Rational Simplification to oxidant tank, gas cylinder and combustor section respectively, structure obtains oxygen
Agent tank computation model, gas cylinder computation model and combustion chamber computation model.With reference to the third possible implementation of second aspect
Mode, an embodiment of the present invention provides the 4th kind of possible embodiment of second aspect, wherein, the computing module is specifically used
In：
Gas cylinder system is obtained using the initial pressure of gas cylinder of the gas cylinder computation model in parameter information and Mass Calculation
First quality center of mass performance data；
The of tank system is calculated using oxidizer flow rate of the oxidant tank computation model in parameter information
Two quality center of mass performance datas；
It is calculated using ground test data of the combustion chamber computation model in parameter information, obtains chamber system
Third quality center of mass performance data；
Above-mentioned first quality center of mass performance data, the second quality characteristics data and third quality characteristics data are counted
It calculates, generates the quality center of mass performance data of the entire flight course of solid-liquid rocket.
The third aspect, the embodiment of the present invention also provide a kind of electronic equipment, including memory, processor, the memory
On be stored with the computer program that can be run on the processor, the processor is realized when performing the computer program
The step of stating the method described in first aspect.
Fourth aspect, the embodiment of the present invention also provide a kind of meter of non-volatile program code that can perform with processor
Calculation machine readable medium, said program code make the processor perform the method described in above-mentioned first aspect.
The embodiment of the present invention brings following advantageous effect：
In the automation computational methods of solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention, first by connecing
Receive parameter information input by user；Wherein, which includes solid-liquid engine fuel burning data file and rocket structure
Parameter；Then the quality center of mass performance data of the entire flight course of solid-liquid rocket is generated according to above-mentioned parameter information；It finally will be upper
Quality center of mass performance data is stated to be exported.Therefore, technical solution provided in an embodiment of the present invention, can be with by input parameter
Quickly and accurately calculating solid-liquid rocket flight course obtains total quality barycenter performance data, can alleviate in the prior art
Existing heavy workload, it is inefficient the problem of.In addition, the solid-liquid rocket flight course obtains total quality barycenter performance data
Necessary data can also be provided for Pneumatic Calculation, Control System Design.This method simply, conveniently, can accurately realize knot
Fruit exports, and improves user experience, meanwhile, the automation computational methods of the solid-liquid rocket flight reappearance characteristic have theoretical base
Plinth, strong applicability, reliability are high.
Other features and advantages of the present invention will illustrate in the following description, also, partly become from specification
It obtains it is clear that being understood by implementing the present invention.The purpose of the present invention and other advantages are in specification, claims
And specifically noted structure is realized and is obtained in attached drawing.
For the above objects, features and advantages of the present invention is enable to be clearer and more comprehensible, preferred embodiment cited below particularly, and coordinate
Appended attached drawing, is described in detail below.
Description of the drawings
It, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical solution of the prior art
Embodiment or attached drawing needed to be used in the description of the prior art are briefly described, it should be apparent that, in being described below
Attached drawing is some embodiments of the present invention, for those of ordinary skill in the art, before not making the creative labor
It puts, can also be obtained according to these attached drawings other attached drawings.
Fig. 1 is a kind of flow of the automation computational methods of solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention
Schematic diagram；
Fig. 2 is the schematic diagram of step S102 in Fig. 1；
Fig. 3 is the stream of the automation computational methods of another solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention
Journey schematic diagram；
Fig. 4 is a kind of signal of the automation computing device of solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention
Figure；
Fig. 5 is a kind of the detailed of the automation computing device of solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention
Schematic diagram；
Fig. 6 is showing for the interface of the automation computing device of solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention
It is intended to；
Fig. 7 is the automation computing device of solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention for solid-liquid fire
The automation calculation flow chart of flight mass property；
Fig. 8 is the structure diagram of electronic equipment provided in an embodiment of the present invention.
Specific embodiment
Purpose, technical scheme and advantage to make the embodiment of the present invention are clearer, below in conjunction with attached drawing to the present invention
Technical solution be clearly and completely described, it is clear that described embodiment be part of the embodiment of the present invention rather than
Whole embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art are not making creative work premise
Lower all other embodiments obtained, shall fall within the protection scope of the present invention.
In current rocket master-plan, the design of rocket will often iterate repeatedly, and workload is very big.And it lacks now
A kind of weary for solid-liquid rocket mass property effective and efficiently computational methods, also lack efficiently, easily calculating instrument, this
Result in the inefficient of solid-liquid rocket design iteration process.Based on this, a kind of solid-liquid rocket provided in an embodiment of the present invention flies
The automation computational methods of row mass property and device electronic equipment can alleviate computationally intensive, effect in the prior art
The problem of rate is not high.
For ease of understanding the present embodiment, first to a kind of solid-liquid rocket flight matter disclosed in the embodiment of the present invention
The automation computational methods of flow characteristic describe in detail.
Embodiment one：
Fig. 1 shows a kind of automation computational methods of solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention
Flow diagram.With reference to Fig. 1, the automation computational methods of the solid-liquid rocket flight reappearance characteristic can be applied to solid-liquid rocket design
Field, this method include following steps：
Step S101：Receive parameter information input by user；Wherein, above-mentioned parameter information is fired including solid-liquid engine fuel
Burn data file and rocket structure parameter.
Here rocket structure parameter includes the information such as structure and the engine parameter of solid-liquid rocket, specifically, rocket knot
Structure parameter includes the pure structural portion of centroid position, solid-liquid rocket of the pure architecture quality of reality of solid-liquid rocket, the pure structure division of rocket
The rotary inertia of the pure structure division vertical axial of rotary inertia, solid-liquid rocket point in an axial direction, oxidation agent parameter, solid-liquid rocket
The initial whole rocket length of practical gas cylinder initial pressure and solid-liquid rocket.Wherein, oxidation agent parameter includes oxidant quality, big stream
Amount, big flow working time and small flow.It should be noted that above-mentioned oxidation agent parameter is defeated with specific reference to design requirement progress
Enter.
Solid-liquid engine fuel burning data file can input in a manner that file is transferred.In one embodiment,
Solid-liquid engine fuel burning data file can be clicked right side navigation button by user and be scanned for, such as consolidating design
Liquid engine combustion test data is imported in the form of Excel tables in program.It should be pointed out that user can be by local meter
The data of any position import in calculation machine, and path and filename are included facilitating subscriber checking in the window in left side.
Step S102：The quality center of mass performance data of the entire flight course of solid-liquid rocket is generated according to above-mentioned parameter information.
Specifically, with reference to Fig. 2, step S102 is mainly realized by following steps：
S1021：Gas cylinder is obtained using the initial pressure of gas cylinder of the gas cylinder computation model in parameter information and Mass Calculation
First quality center of mass performance data of system.
Wherein, it is used to include gaseous mass in gas cylinder, gas cylinder barycenter and the rotation of gas cylinder barycenter for the first quality center of mass performance data
Amount.
S1022：Tank system is calculated using oxidizer flow rate of the oxidant tank computation model in parameter information
Second quality center of mass performance data of system.
Wherein, the second quality center of mass performance data includes gaseous mass, tank total quality, tank barycenter and storage in tank
Case barycenter rotary inertia.
S1023：It is calculated, is burnt using ground test data of the combustion chamber computation model in parameter information
The third quality center of mass performance data of chamber system.
Wherein, third quality center of mass performance data includes combustion chamber total quality (including fuel and oxidant quality), combustion
Burn room barycenter and combustion chamber barycenter rotary inertia.
S1024：To above-mentioned first quality center of mass performance data, the second quality characteristics data and third quality characteristics data into
Row calculates, and generates the quality center of mass performance data of the entire flight course of solid-liquid rocket.
It should be noted that above-mentioned oxidant tank computation model, gas cylinder computation model and combustion chamber computation model are logical
It crosses after Rational Simplification is carried out to oxidant tank, gas cylinder and combustor section respectively and builds what is obtained.
Here S1021, S1022 and S1023 is only to describe easy to use, does not represent its sequencing, such as
S1021, S1022 and S1023 can be carried out at the same time or be performed with the sequence of any permutation and combination.
Therefore, before step S102, this method further includes the step of establishing computation model：
That is, carrying out Rational Simplification to oxidant tank, gas cylinder and combustor section respectively, structure obtains oxidant tank meter
Calculate model, gas cylinder computation model and combustion chamber computation model.
It described the step of establishing computation model, is mainly accomplished by the following way：
Process to simplify the calculation makees following basic assumption：
Gas cylinder calculating section, it is assumed that gas is cylinder in gas cylinder, even variation in outer radial.
Oxidant tank calculating section, it is assumed that tank hydrogen peroxide is cylinder, even variation in outer radial, and is simplified
Tank liquid capsule model is 2mm thickness sleeves.
Combustion chamber calculating section, it is assumed that the powder column of solid-liquid engine is single-hole cylindrical body, and only internal bore burning, powder uniformly moves back
It moves.
Based on above-mentioned basic assumption, corresponding oxidant tank computation model, gas cylinder computation model and burning are established respectively
Room computation model.
Specifically, according to above-mentioned basic assumption and cylinder rotary inertia formula, the fire of the comparative maturities such as inertia translation law
Arrow design formula establishes corresponding oxidant tank computation model, gas cylinder computation model and combustion chamber computation model respectively.
Step S103：Above-mentioned quality center of mass performance data is exported.
In the specific implementation, step S103 can be accomplished by the following way：
Mode A：
Above-mentioned quality center of mass performance data is written according to preset format in the table automatically generated A1, generation tables of data text
Part.
Wherein, preset format is to have pre-defined the unit of each data, the reference format of size and each data
Output sequence, table be with the corresponding multiple lines and multiple rows table of preset format, so as to which data be facilitated to insert table, generate data
List file.The form of the tables of data is succinct, it may be convenient to directly use.The working automation of data will be extracted, improves user
The operating efficiency of (such as computing staff).
During specific implementation, automatically create and the Excel tables of form needed for generating, at the same by the data being calculated according to
In form write-in table, the tables of data of required form is finally directly obtained, the working automation of data will be extracted, improves efficiency.
The data list file of generation is stored in designated position by A2.
The data list file of generation can be stored in designated position according to the path of user setting, specifically, by generation
Data list file is stored under the same file of input file.
And/or；
Mode B：
B1 generates change curve according to above-mentioned quality center of mass performance data.
Wherein, above-mentioned change curve includes the first change curve (qualitative data and time curve), the second variation song
Line (barycenter data and time curve), third change curve (axial rotation inertia data and time curve), the 4th
Change curve (vertical axial rotational inertia data and time curve)；Above-mentioned first change curve, the second change curve,
Three change curves, the 4th change curve reflect qualitative data, barycenter data, the axial rotation inertia number of solid-liquid rocket respectively
It changes with time according to, vertical axial rotational inertia data.
Specifically, according to the quality center of mass performance data, the rotation of rocket flight quality, centroid position, axial direction is drawn
The rotary inertia of inertia and vertical axial with the flight time change curve.
B2 exports above-mentioned change curve to display interface.
Here display interface can be the graphical display of the screen or software that show equipment or projection device
Interface.
Specifically, exporting change curve to display screen, and pass through graphic display interface and shown to user, facilitate user couple
As a result intuitive preliminary test analysis is carried out.
The automation computational methods of solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention are used first by receiving
The parameter information of family input；Wherein, which includes solid-liquid engine fuel burning data file and rocket structure parameter；
Then the quality center of mass performance data of the entire flight course of solid-liquid rocket is generated according to above-mentioned parameter information；Finally by above-mentioned quality
Barycenter performance data is exported.Therefore, technical solution provided in an embodiment of the present invention, by solid-liquid rocket theory analysis
On the basis of, founding mathematical models, and appliance computer software (such as matlab) is programmed, and can show GUI to user
Interface；Above-mentioned gui interface includes parameter input area, output fruiting area and graphing area；It, can quickly again by input parameter
Accurately calculating solid-liquid rocket flight course obtains total quality barycenter performance data, i.e., by receiving ginseng input by user
Number carries out analysis and solution using the mathematical model of structure, automatically generates result and exports the result of generation, alleviates existing skill
Heavy workload present in art, it is inefficient the problem of.In addition, the solid-liquid rocket flight course obtains total quality barycenter characteristic
Data can also provide necessary data for Pneumatic Calculation, Control System Design.This method simply, conveniently, can be accurately real
Now output emulation, improves user experience, meanwhile, the automation computational methods of the solid-liquid rocket flight reappearance characteristic have reason
By basis, strong applicability, reliability is high.
Embodiment two：
As shown in figure 3, on the basis of embodiment one, an embodiment of the present invention provides another solid-liquid rocket flight reappearances
The automation computational methods of characteristic, before step S102, the automation computational methods of the solid-liquid rocket flight reappearance characteristic are also
Including：
Step S201：Judge whether above-mentioned parameter information overflows.
Wherein, it overflows and includes certain of parameter information input by user not in preset parameter area or in parameter information
A little parameters do not meet boundary condition or input format is wrong.
If when, i.e., when above-mentioned parameter information is to overflow, perform step S202：Prompt error message and suggestion side
Case.
Wherein, error message includes the information such as numerical fault, single bit error, file error；Proposed projects can be again
Input or suggestion expand or reduce numerical values recited.
If it is not, i.e. when above-mentioned parameter information is not overflowed, step S102 is performed.
Follow-up invalid calculating can be prevented by judging whether parameter overflows, user time is saved, improves efficiency.
Embodiment three：
As shown in Figure 4 and Figure 5, the automation of solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention calculates dress
It puts, the automation computing device of the solid-liquid rocket flight reappearance characteristic includes：
MIM message input module 100, for receiving parameter information input by user；Wherein, the parameter information includes solid-liquid
Engine fuel burning data file and rocket structure parameter.
Computing module 200, it is special for generating the quality center of mass of the entire flight course of solid-liquid rocket according to the parameter information
Property data.
Output module 300, for the quality center of mass performance data to be exported.
Further, described information input module 100 includes the first input module 101 and the second input module 102.
First input module 101 is also known as rocket structure parameter input module, for receiving rocket structure input by user
Parameter；Wherein, first input module includes architecture quality window, structure barycenter window, rotary inertia Ix windows, rotates and be used to
Measure Iy windows, oxidant parameter window, storage pressure window, whole rocket length window.Each window is from top to bottom arranged in order, and
The remarks for inserting content are equipped on the left of window.
Specifically, the content of rocket parameter input module is：
Architecture quality window, for receiving the pure architecture quality of reality of (inserting) solid-liquid rocket input by user.Wherein, Gu
The pure architecture quality of reality of liquid extract arrow can according to the threedimensional model of solid-liquid rocket, by graphics software (such as Inventor,
Solidworks it) is directly calculated, specifically, graphics software uses Inventor.
Structure barycenter window, for receiving the centroid position of the pure structure division of rocket input by user.Wherein, the rocket is pure
The centroid position of structure division can be according to the threedimensional model of solid-liquid rocket, the face on the basis of rocket bottom face, by graphics software
Directly it is calculated.
Rotary inertia Ix windows, for receiving the rotary inertia of the pure structure division of solid-liquid rocket input by user in an axial direction.
Wherein, here the rotary inertia of the pure structure division of solid-liquid rocket in an axial direction can be according to the threedimensional model of solid-liquid rocket, by making
Figure software is directly calculated.
Rotary inertia Iy windows, the rotation for receiving the pure structure division vertical axial of solid-liquid rocket input by user are used to
Amount.Wherein, herein the rotary inertia of the pure structure division vertical axial of solid-liquid rocket can according to the threedimensional model of solid-liquid rocket,
It is directly calculated by graphics software.
Oxidant parameter window, including four data windows, oxidant quality, big flow, big flow working time, small stream
Amount, is inputted by user by design requirement.
Storage pressure window, for receiving the practical gas cylinder initial pressure of solid-liquid rocket input by user.
Whole rocket length window, for receiving the initial whole rocket length of solid-liquid rocket input by user.
Second input module 102 is also known as solid-liquid engine fuel burning data document input module, for receiving user
The solid-liquid engine fuel burning data file of input.
Specifically, the second input module includes input file window and the navigation button on the right side of input file window
(or referred to as input file select button), user are scanned for by clicking the navigation button on right side, can consolidating design
Liquid engine combustion test data is imported in the form of Excel tables in program.The module can will be arbitrary in local computer
The data of position import, and by path and filename including being examined in the input file window on the left of navigation button
It tests.
Further, output module 300 includes the first output module 301 and the second output module 302.
First output module 301 is also known as operation result file output module, for by the quality center of mass performance data
In the table automatically generated according to preset format write-in, data list file is generated；The data list file of generation is stored in specified
Position.
Specifically, operation result file output module will create needed for form (preset format) Excel tables, simultaneously will
The data being calculated are written according to preset format in table, finally obtain required tables of data, and be stored in input file
With under file.The form of tables of data is succinct, it may be convenient to directly use.The working automation of data will be extracted, improves meter
The operating efficiency of calculation personnel.
Second output module 302 is also known as image display module, for according to the quality center of mass performance data, generation to become
Change curve；The change curve is exported to display screen and is shown.
Specifically, being provided with graphic plotting and display area on the right side of program main interface, image display module therein is being counted
After calculation, solid-liquid rocket flight reappearance (being represented with m, units/kg), centroid position are drawn (with x in program interface right area
Represent, unit mm), the rotary inertia Iy of axial rotary inertia Ix and vertical axial with the flight time curve.It is conveniently operated
Personnel carry out result of calculation preliminary intuitive analysis, to judge the validity of this result of calculation.
Further, the device further includes：Study module 400.
For carrying out Rational Simplification to oxidant tank, gas cylinder and combustor section respectively, structure obtains study module 400
Oxidant tank computation model, gas cylinder computation model and combustion chamber computation model.
Specifically, study module is used for gas cylinder calculating section, it is assumed that gas is cylinder in gas cylinder, is uniformly become in outer radial
Change,
Oxidant tank calculating section, it is assumed that tank hydrogen peroxide is cylinder, even variation in outer radial, and is simplified
Tank liquid capsule model is 2mm thickness sleeves；
Combustion chamber calculating section, it is assumed that the powder column of solid-liquid engine is single-hole cylindrical body, and only internal bore burning, powder uniformly moves back
It moves；
Based on above-mentioned basic assumption, corresponding oxidant tank computation model, gas cylinder computation model and burning are established respectively
Room computation model.
Further, computing module 200 is specifically used for：
Gas cylinder system is obtained using the initial pressure of gas cylinder of the gas cylinder computation model in parameter information and Mass Calculation
First quality center of mass performance data；
The of tank system is calculated using oxidizer flow rate of the oxidant tank computation model in parameter information
Two quality center of mass performance datas；
It is calculated using ground test data of the combustion chamber computation model in parameter information, obtains chamber system
Third quality center of mass performance data；
Above-mentioned first quality center of mass performance data, the second quality characteristics data and third quality characteristics data are counted
It calculates, generates the quality center of mass performance data of the entire flight course of solid-liquid rocket.
Specifically, computing module includes computed push-buttom and the calculation procedure on backstage, for calculating the quality center of mass of whole rocket spy
Property, main body is the mass property calculation of solid-liquid engine system.Therefore, here in terms of the mass property of solid-liquid engine system
Calculate the quality center of mass characteristic to characterize the entire flight course of solid-liquid rocket；After user clicks computed push-buttom, device is according to above-mentioned defeated
Enter data and calculate quality center of mass characteristic of the solid-liquid rocket in flight course, while lattice needed for being exported by output module
The Excel tables of formula, image display module draw mass, barycenter, rotary inertia with the flight time change curve.
Wherein, the mass property calculation method of solid-liquid engine system is：
Gas cylinder calculating section, it is assumed that gas is cylinder in gas cylinder, and even variation in outer radial passes through the initial pressure of gas cylinder
With the input of quality, residual mass is calculated by ratio in flight course, and calculates the change of barycenter and rotary inertia
Change.
Oxidant tank calculating section, it is assumed that tank hydrogen peroxide is cylinder, even variation in outer radial, and is simplified
Tank liquid capsule model is 2mm thickness sleeves, is combined with gas calculating in gas cylinder, synchronous to calculate the gaseous mass entered in tank
Characteristic, with reference to given oxidizer flow rate calculate the quality of tank entirety, barycenter, rotary inertia with the flight time variation.
Combustion chamber calculating section, it is assumed that the powder column of solid-liquid engine is single-hole cylindrical body, and only internal bore burning, powder uniformly moves back
It moves, passes through the ground test data of input, you can calculate total quality, barycenter, rotation of the combustor section with the flight time
Inertia changes.
By by the department patterns Rational Simplification such as tank, gas cylinder, combustion chamber, establishing corresponding computation model, calculating respectively
The data such as quality, barycenter and the rotary inertia of each system, it is final to unifiedly calculate, obtain the flight reappearance barycenter characteristic of whole arrow (i.e.
The quality center of mass performance data of the entire flight course of solid-liquid rocket).Wherein, centroid calculation is exactly by each section center analysis
It calculates, total rotary inertia is calculated then according to the rotary inertia of each section, is calculated with parallel-axis theorem.
Fig. 6 shows the interface of the automation computing device of solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention
Schematic diagram, the automation computing device of the solid-liquid rocket flight reappearance characteristic passes through in rocket design theory and kinematics analysis
On the basis of, founding mathematical models, and appliance computer language is programmed, and to user's present graphical user interface (GUI)；
Above-mentioned GUI includes parameter input area, output file area (including output file window and computed push-buttom) and graphing area.Parameter
Input area includes each input window, and parameter input area is arranged on the left side upper end at interface；Output file area is arranged on interface
Left side lower end；Graphing area is arranged on the right side at interface.
With reference to Fig. 7 to the automation computing device needle of solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention
One brief description is made to the automation calculation flow chart of solid-liquid rocket flight reappearance characteristic：
1) start
Program is run, shows program main interface.
2) input paramete information
Input solid-liquid rocket parameter and solid-liquid engine fuel burning data file.
3) it calculates
Chamber system, tank system and gas cylinder system are calculated first, respectively obtain chamber fuel and oxidation
Agent quality, combustion chamber barycenter and combustion chamber geocentric coordinate system rotary inertia, gaseous mass, tank barycenter and tank barycenter in tank
Coordinate system rotary inertia and, gaseous mass, gas cylinder barycenter and gas cylinder geocentric coordinate system rotary inertia in gas cylinder.
Then gross mass and total rotary inertia is calculated.
4) it exports
The operation result file of above-mentioned gross mass and total rotary inertia is exported, meanwhile, it can be by above-mentioned gross mass and total
Rotary inertia carries out graphical display.
5) terminate
Solid-liquid rocket flight reappearance characteristic automation computing device provided in an embodiment of the present invention has the following advantages：
1st, solid-liquid rocket flight reappearance characteristic automation computing device of the present invention can make the work in any industry
Make personnel after program main interface is entered, the information that each window being apparent that in MIM message input module should be filled in
Content avoids the need for title and the sequence list of control developer's offer to fill in, can not if the title list of papery is lost
It uses, greatly improves practicability and comfort level；A kind of information corresponds to a window, and window is from top to bottom arranged successively
Row make program more orderly and clear.
2nd, solid-liquid engine calculating section passes through Rational simplified model so that the solid-liquids engine such as tank, gas cylinder, combustion chamber
The parameter of component is able to facilitate calculating, and by being combined with ground experiment parameter, the flight reappearance characteristic of high accuracy is calculated.
3rd, it is encapsulated by program, data needed for calculating need to be only inputted as set form, you can correctly calculated, obtained
It is required as a result, whole operation flow is greatly simplified.
4th, the arrangement of data and ablation process are automated, the Excel tables of the data of required form is directly obtained after calculating
Lattice improve operating personnel's efficiency.
The 5th, graphics display area is set, result of calculation is drawn into curve, side in the relevant range of panel after calculating
Just result is intuitively analyzed, judges the validity of result of calculation, further improve computational efficiency.
6th, each functional area distribution is clear, and the interface of entire calculation procedure is clearly succinct, and program is convenient in different computers
Upper installation, it is easy to operate, it is easy to use.
Embodiment three：
Referring to Fig. 8, the embodiment of the present invention also provides a kind of electronic equipment 800, including：Processor 40, memory 41, bus
42 and communication interface 43, the processor 40, communication interface 43 and memory 41 connected by bus 42；Processor 40 is used to hold
The executable module stored in line storage 41, such as computer program.
Wherein, memory 41 may include high-speed random access memory (RAM, RandomAccessMemory), also may be used
Non-labile memory (non-volatile memory), for example, at least a magnetic disk storage can be further included.By at least
One communication interface 43 (can be wired or wireless) realizes the communication between the system network element and at least one other network element
Connection can use internet, wide area network, local network, Metropolitan Area Network (MAN) etc..
Bus 42 can be isa bus, pci bus or eisa bus etc..The bus can be divided into address bus, data
Bus, controlling bus etc..Only represented for ease of representing, in Fig. 8 with a four-headed arrow, it is not intended that an only bus or
A type of bus.
Wherein, for memory 41 for storing program, the processor 40 performs the journey after execute instruction is received
Sequence, the method performed by device that the stream process that aforementioned any embodiment of the embodiment of the present invention discloses defines can be applied to handle
It is realized in device 40 or by processor 40.
Processor 40 may be a kind of IC chip, have the processing capacity of signal.During realization, above-mentioned side
Each step of method can be completed by the integrated logic circuit of the hardware in processor 40 or the instruction of software form.Above-mentioned
Processor 40 can be general processor, including central processing unit (Central Processing Unit, abbreviation CPU), network
Processor (Network Processor, abbreviation NP) etc.；It can also be digital signal processor (Digital Signal
Processing, abbreviation DSP), application-specific integrated circuit (Application Specific Integrated Circuit, referred to as
ASIC), ready-made programmable gate array (Field-Programmable Gate Array, abbreviation FPGA) or other are programmable
Logical device, discrete gate or transistor logic, discrete hardware components.It can realize or perform in the embodiment of the present invention
Disclosed each method, step and logic diagram.General processor can be microprocessor or the processor can also be appointed
What conventional processor etc..The step of method with reference to disclosed in the embodiment of the present invention, can be embodied directly in hardware decoding processing
Device performs completion or performs completion with the hardware in decoding processor and software module combination.Software module can be located at
Machine memory, flash memory, read-only memory, programmable read only memory or electrically erasable programmable memory, register etc. are originally
In the storage medium of field maturation.The storage medium is located at memory 41, and processor 40 reads the information in memory 41, with reference to
Its hardware completes the step of above method.
The automation computing device and electronic equipment of solid-liquid rocket flight reappearance characteristic provided in an embodiment of the present invention, it is and upper
The automation computational methods for stating the solid-liquid rocket flight reappearance characteristic of embodiment offer have identical technical characteristic, so also can
The technical issues of identical is solved, reaches identical technique effect.
The computer of the automation computational methods of progress solid-liquid rocket flight reappearance characteristic that the embodiment of the present invention is provided
Program product, the computer readable storage medium of non-volatile program code that can perform including storing processor, the journey
The instruction that sequence code includes can be used for performing the method described in previous methods embodiment, and specific implementation can be found in method and implement
Example, details are not described herein.
It is apparent to those skilled in the art that for convenience and simplicity of description, the device of foregoing description
And the specific work process of electronic equipment, the corresponding process in preceding method embodiment can be referred to, details are not described herein.
Flow chart and block diagram in attached drawing show multiple embodiment method and computer program products according to the present invention
Architectural framework in the cards, function and operation.In this regard, each box in flow chart or block diagram can represent one
A part for module, program segment or code, a part for the module, program segment or code are used to implement comprising one or more
The executable instruction of defined logic function.It should also be noted that in some implementations as replacements, the work(marked in box
It can also be occurred with being different from the sequence marked in attached drawing.For example, two continuous boxes can essentially be substantially parallel
Ground performs, they can also be performed in the opposite order sometimes, this is depended on the functions involved.It is also noted that block diagram
And/or the combination of each box in flow chart and the box in block diagram and/or flow chart, work(as defined in performing can be used
Can or action dedicated hardware based system come realize or can with the combination of specialized hardware and computer instruction come reality
It is existing.
In the description of the present invention, it should be noted that term " " center ", " on ", " under ", "left", "right", " vertical ",
The orientation or position relationship of the instructions such as " level ", " interior ", " outer " be based on orientation shown in the drawings or position relationship, merely to
Convenient for the description present invention and simplify description rather than instruction or imply signified device or element must have specific orientation,
With specific azimuth configuration and operation, therefore it is not considered as limiting the invention.In addition, term " first ", " second ",
" third " is only used for description purpose, and it is not intended that instruction or hint relative importance.
In several embodiments provided herein, it should be understood that disclosed systems, devices and methods, it can be with
It realizes by another way.The apparatus embodiments described above are merely exemplary, for example, the division of the unit,
Only a kind of division of logic function, can there is other dividing mode in actual implementation, in another example, multiple units or component can
To combine or be desirably integrated into another system or some features can be ignored or does not perform.Another point, it is shown or beg for
The mutual coupling, direct-coupling or communication connection of opinion can be by some communication interfaces, device or unit it is indirect
Coupling or communication connection can be electrical, machinery or other forms.
The unit illustrated as separating component may or may not be physically separate, be shown as unit
The component shown may or may not be physical unit, you can be located at a place or can also be distributed to multiple
In network element.Some or all of unit therein can be selected according to the actual needs to realize the mesh of this embodiment scheme
's.
In addition, each functional unit in each embodiment of the present invention can be integrated in a processing unit, it can also
That each unit is individually physically present, can also two or more units integrate in a unit.
If the function is realized in the form of SFU software functional unit and is independent product sale or in use, can be with
It is stored in the non-volatile computer read/write memory medium that a processor can perform.Based on such understanding, the present invention
The part that substantially contributes in other words to the prior art of technical solution or the part of the technical solution can be with software
The form of product embodies, which is stored in a storage medium, including some instructions use so that
One computer equipment (can be personal computer, server or the network equipment etc.) performs each embodiment institute of the present invention
State all or part of step of method.And aforementioned storage medium includes：USB flash disk, mobile hard disk, read-only memory (ROM, Read-
Only Memory), random access memory (RAM, Random Access Memory), magnetic disc or CD etc. are various can be with
Store the medium of program code.
Finally it should be noted that：Embodiment described above, only specific embodiment of the invention, to illustrate the present invention
Technical solution, rather than its limitations, protection scope of the present invention is not limited thereto, although with reference to the foregoing embodiments to this hair
It is bright to be described in detail, it will be understood by those of ordinary skill in the art that：Any one skilled in the art
In the technical scope disclosed by the present invention, it can still modify to the technical solution recorded in previous embodiment or can be light
It is readily conceivable that variation or equivalent replacement is carried out to which part technical characteristic；And these modifications, variation or replacement, do not make
The essence of corresponding technical solution is detached from the spirit and scope of technical solution of the embodiment of the present invention, should all cover the protection in the present invention
Within the scope of.Therefore, protection scope of the present invention described should be subject to the protection scope in claims.
Claims (10)
1. a kind of automation computational methods of solid-liquid rocket flight reappearance characteristic, which is characterized in that including：
Receive parameter information input by user；Wherein, the parameter information include solid-liquid engine fuel burning data file and
Rocket structure parameter；
The quality center of mass performance data of the entire flight course of solid-liquid rocket is generated according to the parameter information；
The quality center of mass performance data is exported.
2. according to the method described in claim 1, it is characterized in that, described export the quality center of mass performance data,
It specifically includes：
The quality center of mass performance data is written according to preset format in the table automatically generated, generates data list file；
The data list file of generation is stored in designated position；
And/or
According to the quality center of mass performance data, change curve is generated；
The change curve is exported to display interface.
It is 3. according to the method described in claim 1, it is characterized in that, described entire according to parameter information generation solid-liquid rocket
The quality center of mass performance data of flight course, specifically includes：
The first of gas cylinder system is obtained using the initial pressure of gas cylinder of the gas cylinder computation model in parameter information and Mass Calculation
Quality center of mass performance data；
The second matter of tank system is calculated using oxidizer flow rate of the oxidant tank computation model in parameter information
Measure barycenter performance data；
It is calculated using ground test data of the combustion chamber computation model in parameter information, obtains the of chamber system
Three quality center of mass performance datas；
Above-mentioned first quality center of mass performance data, the second quality characteristics data and third quality characteristics data are calculated, it is raw
Into the quality center of mass performance data of the entire flight course of solid-liquid rocket.
4. it according to the method described in claim 3, it is characterized in that, further includes：
Respectively to oxidant tank, gas cylinder and combustor section carry out Rational Simplification, structure obtain oxidant tank computation model,
Gas cylinder computation model and combustion chamber computation model.
It is 5. according to the method described in claim 4, it is characterized in that, described respectively to oxidant tank, gas cylinder and combustor section
Divide and carry out Rational Simplification, structure obtains oxidant tank computation model, gas cylinder computation model and combustion chamber computation model, specific to wrap
It includes：
Process to simplify the calculation makees following basic assumption：
Gas cylinder calculating section, it is assumed that gas is cylinder in gas cylinder, even variation in outer radial；
Oxidant tank calculating section, it is assumed that tank hydrogen peroxide is cylinder, even variation in outer radial, and simplifies tank
Liquid capsule model is 2mm thickness sleeves；
Combustion chamber calculating section, it is assumed that the powder column of solid-liquid engine is single-hole cylindrical body, and only internal bore burning, powder is uniformly retired；
Based on above-mentioned basic assumption, corresponding oxidant tank computation model, gas cylinder computation model and combustion chamber meter are established respectively
Calculate model.
6. a kind of automation computing device of solid-liquid rocket flight reappearance characteristic, which is characterized in that including：
MIM message input module, for receiving parameter information input by user；Wherein, the parameter information is fired including solid-liquid engine
Expect burning data file and rocket structure parameter；
Computing module, for generating the quality center of mass performance data of the entire flight course of solid-liquid rocket according to the parameter information；
Output module, for the quality center of mass performance data to be exported.
7. device according to claim 6, which is characterized in that described information input module includes the first input module and the
Two input modules；
First input module is used to receive rocket structure parameter input by user；Wherein, first input module includes structure
Mass window, structure barycenter window, rotary inertia Ix windows, rotary inertia Iy windows, oxidant parameter window, storage pressure window
Mouth, whole rocket length window；
Second input module is used to receive solid-liquid engine fuel burning data file input by user.
8. device according to claim 6, which is characterized in that the output module is defeated including the first output module and second
Go out module；
First output module is used for the table for automatically generating the quality center of mass performance data according to preset format write-in
In, generate data list file；The data list file of generation is stored in designated position；
Second output module is used to, according to the quality center of mass performance data, generate change curve；By the change curve
It exports to display interface.
9. device according to claim 6, which is characterized in that further include：
Study module, for carrying out Rational Simplification to oxidant tank, gas cylinder and combustor section respectively, structure obtains oxidant
Tank computation model, gas cylinder computation model and combustion chamber computation model.
10. device according to claim 9, which is characterized in that the computing module is specifically used for：
The first of gas cylinder system is obtained using the initial pressure of gas cylinder of the gas cylinder computation model in parameter information and Mass Calculation
Quality center of mass performance data；
The second matter of tank system is calculated using oxidizer flow rate of the oxidant tank computation model in parameter information
Measure barycenter performance data；
It is calculated using ground test data of the combustion chamber computation model in parameter information, obtains the of chamber system
Three quality center of mass performance datas；
Above-mentioned first quality center of mass performance data, the second quality characteristics data and third quality characteristics data are calculated, it is raw
Into the quality center of mass performance data of the entire flight course of solid-liquid rocket.
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