CN110188400A - A kind of solid engines internal ballistics attributes indication software systems - Google Patents
A kind of solid engines internal ballistics attributes indication software systems Download PDFInfo
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- CN110188400A CN110188400A CN201910376056.XA CN201910376056A CN110188400A CN 110188400 A CN110188400 A CN 110188400A CN 201910376056 A CN201910376056 A CN 201910376056A CN 110188400 A CN110188400 A CN 110188400A
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- 239000007787 solid Substances 0.000 title claims abstract description 26
- 239000003380 propellant Substances 0.000 claims abstract description 52
- 235000013372 meat Nutrition 0.000 claims abstract description 19
- 239000002360 explosive Substances 0.000 claims abstract description 10
- 239000000843 powder Substances 0.000 claims description 27
- 239000007789 gas Substances 0.000 claims description 9
- 239000000567 combustion gas Substances 0.000 claims description 8
- 238000002485 combustion reaction Methods 0.000 claims description 8
- 210000000867 larynx Anatomy 0.000 claims description 8
- 241000208340 Araliaceae Species 0.000 claims description 7
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 claims description 7
- 235000003140 Panax quinquefolius Nutrition 0.000 claims description 7
- 235000008434 ginseng Nutrition 0.000 claims description 7
- 230000008676 import Effects 0.000 claims description 6
- 230000008859 change Effects 0.000 claims description 4
- 239000002737 fuel gas Substances 0.000 claims description 4
- 230000029058 respiratory gaseous exchange Effects 0.000 claims description 3
- 230000035945 sensitivity Effects 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 claims description 2
- 239000007921 spray Substances 0.000 claims description 2
- 238000004364 calculation method Methods 0.000 abstract description 10
- 239000000463 material Substances 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 6
- 230000006870 function Effects 0.000 description 4
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012356 Product development Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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Abstract
The invention discloses solid engines internal ballistics attributes to indicate software systems, including input display module, computing module and output display module；Input display module is used to show the input interface of engine parameter, for input interface for inputting engine parameter, engine parameter includes that data of explosive filled, working environment initial parameter, jet pipe conventional parameter, jet pipe type, propellant burning rate parameter, Burning area of grain meat thickness retire the design parameter of data and nozzle with scarfed exit plane；Jet pipe type includes conventional jet pipe and nozzle with scarfed exit plane, and design parameter includes jet pipe number, jet pipe oblique angle, nozzle expansion half-angle, jet pipe angle of chamfer, jet pipe phase layout angle, cover axis intersection point distance, the symmetrical segment length of jet pipe and jet pipe chamfered portion material calculation；Computing module calculates engine performance parameter according to preset algorithm, obtains internal ballistics attributes calculated result；Output display module exports and shows internal ballistics attributes calculated result.The present invention can calculate tilting nozzle with scarfed exit plane engine internal ballistics attributes.
Description
Technical field
The present invention relates to solid engines technical fields, and in particular to a kind of solid engines internal ballistics attributes indication software
System.
Background technique
Conventional solid engine internal ballistics attributes indication software is typically only capable to calculate the internal ballistics attributes of symmetrical straight tube, right
In this kind of engine for having tilting nozzle with scarfed exit plane of escape engine, traditional performance indication software is no longer applicable in, need artificially
Influence of the tilting nozzle with scarfed exit plane to internal ballistics attributes is modified, for there is the throwing cover of multiple tilting nozzle with scarfed exit plane of asymmetry to start
Machine, it is also necessary to further calculate multi nozzle generation resultant force, calculate it is more cumbersome, be unfavorable for engine performance it is quick indication with
Precisely indication, seriously constrains the design efficiency and design level of this kind of engine.
Summary of the invention
In view of the deficiencies in the prior art, the purpose of the present invention is to provide a kind of solid engines internal ballistics attributes
Indicate software systems, tilting nozzle with scarfed exit plane engine internal ballistics attributes can be calculated.
To achieve the above objectives, the technical solution adopted by the present invention is that: a kind of indication of solid engines internal ballistics attributes is soft
Part system comprising:
Display module is inputted, is used to show that the input interface of input engine parameter, the input interface to be used for user
Engine parameter is inputted, the engine parameter includes data of explosive filled, the working environment initial parameter of engine, the routine of jet pipe
Parameter, jet pipe type, the burn rate parameter of propellant, Burning area of grain meat thickness retire the design parameter of data and nozzle with scarfed exit plane；It is described
Jet pipe type includes conventional jet pipe and nozzle with scarfed exit plane, and the design parameter includes jet pipe number, jet pipe oblique angle, nozzle expansion half
Angle, jet pipe angle of chamfer, jet pipe phase layout angle, cover axis intersection point distance, the symmetrical segment length of jet pipe and jet pipe chamfered portion calculate step
It is long；
Computing module is used to calculate engine performance parameter according to preset algorithm, and obtains internal ballistics attributes
Calculated result；
Display module is exported, is used to export and show the internal ballistics attributes calculated result.
Further, the input display module includes:
Charge data module is used to input data of explosive filled；
Primary data module is used to input the working environment initial parameter of engine；
Jet pipe data module is used to input the conventional parameter and selection jet pipe type of jet pipe；
Propellant burning rate module is used to input the burn rate parameter of propellant；
Face data import modul is fired, is used to import Burning area of grain meat thickness and retires data；
Nozzle with scarfed exit plane parameter module is used to input the design parameter of nozzle with scarfed exit plane.
Further, the data of explosive filled includes powder charge meat thickness, Propellants With Lower Pressure Exponent, propellant density, propellant combustion
Gas specific heat ratio, propellant fuel gas temperature, propellant combustion gas gas constant, propellant characteristic velocity and propellant temperature sensitivity system
Number.
Further, the working environment initial parameter includes engine ignition pressure, the effective operating pressure of engine, hair
Motivation work terminal pressure, the nozzle thrust coefficient factor, engine initial free volume, engine operation initial temperature, engine are flat
Equal working depth and engine operating environments atmospheric pressure.
Further, the conventional parameter includes the initial larynx diameter of jet pipe, nozzle exit internal diameter and larynx serif ablating rate.
Further, the burn rate parameter includes the reference pressure of propellant, the reference temperature of propellant and propellant
Standard burn rate.
Further, the Burning area of grain meat thickness retires the combustion face face that data include thick, the remaining powder charge of powder charge meat of burning-off
The breathing area of product, the volume of remaining powder charge, the weight of remaining powder charge and remaining powder charge.
Further, the internal ballistics attributes calculated result includes engine pressure, the engine to change with time
Thrust, engine flow, nozzle thrust coefficient, gas deflector angle, engine axial thrust, engine lateral thrust, thrust are made
With point.
Further, the internal ballistics attributes calculated result includes pressure-time graph, axial thrust-time graph, side
To pushing away force-time curve, flow-deviation angle-time graph and mass flowrate-time graph.
Compared with the prior art, the advantages of the present invention are as follows:
(1) solid engines internal ballistics attributes provided by the invention indicate software systems, can choose jet pipe type and
The parameter of nozzle with scarfed exit plane is set, the performances such as canted nozzle, nozzle with scarfed exit plane, multi nozzle are calculated and incorporate engine internal ballistics attributes
In, it can accurately indicate the internal ballistics attributes of tilting nozzle with scarfed exit plane engine, while can also indicate bullet in conventional solid engine
Road performance.The system internal ballistics attributes predicted precision is high, and indication parameter is complete, and computing function is strong, and setting for engine greatly improved
It counts efficiency and design level, practicability is extremely strong.
(2) software systems of the invention can also calculate each to component, lateral forces point, flow-deviation angle.
Detailed description of the invention
Fig. 1 is that solid engines internal ballistics attributes provided in an embodiment of the present invention indicate software systems block diagram；
Fig. 2 is engine parameter input interface schematic diagram provided in an embodiment of the present invention；
Fig. 3 is design parameter input interface schematic diagram provided in an embodiment of the present invention；
Fig. 4 is internal ballistics attributes calculated result interface schematic diagram provided in an embodiment of the present invention；
Fig. 5 is calculated result statistical parameter interface schematic diagram provided in an embodiment of the present invention；
Fig. 6 is calculated result curve interface schematic diagram provided in an embodiment of the present invention.
Specific embodiment
Invention is further described in detail with reference to the accompanying drawings and embodiments.
Shown in Figure 1, the embodiment of the invention provides a kind of solid engines internal ballistics attributes to indicate software systems,
Including input display module, computing module and output display module；Wherein, input display module is for showing input engine ginseng
Several input interfaces, input interface input engine parameter for user, and engine parameter includes the work of data of explosive filled, engine
Make environment initial parameter, the conventional parameter of jet pipe, jet pipe type, the burn rate parameter of propellant, Burning area of grain meat thickness and retires data
With the design parameter of nozzle with scarfed exit plane；Jet pipe type includes conventional jet pipe and nozzle with scarfed exit plane, design parameter include jet pipe number, jet pipe
Oblique angle, nozzle expansion half-angle, jet pipe angle of chamfer, jet pipe phase layout angle, cover axis intersection point distance, the symmetrical segment length of jet pipe and spray
Pipe chamfered portion material calculation；
Computing module is used to calculate engine performance parameter, and obtain internal ballistics attributes meter according to preset algorithm
Calculate result；The preset algorithm includes common engine interior ballistic calculation formula and performance calculating formula.
Output display module is for exporting and showing internal ballistics attributes calculated result.
Solid engines internal ballistics attributes provided by the invention indicate software systems, can choose jet pipe type and setting
The performances such as canted nozzle, nozzle with scarfed exit plane, multi nozzle are calculated and are incorporated in engine internal ballistics attributes by the parameter of nozzle with scarfed exit plane, energy
Enough internal ballistics attributes for accurately indicating tilting nozzle with scarfed exit plane engine, at the same can also calculate its respectively to component, lateral forces point,
Flow-deviation angle.Software systems of the invention can also indicate conventional solid engine internal ballistics attributes.The system internal ballistics attributes
Predicted precision is high, and indication parameter is complete, and computing function is strong, and the design efficiency and design level of engine, practicability greatly improved
It is extremely strong.
Shown in Figure 1, in the present embodiment, input display module includes charge data module, primary data module, jet pipe
Data module, propellant burning rate module, combustion face data import modul and nozzle with scarfed exit plane parameter module,
Wherein, charge data module is for inputting data of explosive filled, and data of explosive filled includes that powder charge meat is thick, propellant pressure refers to
Number, propellant density, propellant combustion gas specific heat ratio, propellant fuel gas temperature, propellant combustion gas gas constant, propellant feature speed
Degree and propellant temperature sensitivity coefficient；
Primary data module is used to input the working environment initial parameter of engine, and working environment initial parameter includes starting
The effective operating pressure of machine ignition Pressure, engine, engine operation terminal pressure, the nozzle thrust coefficient factor, engine are initial
Free volume, engine operation initial temperature, engine average operation height and engine operating environments atmospheric pressure；
Jet pipe data module is used to input the conventional parameter and selection jet pipe type of jet pipe, and conventional parameter includes that jet pipe is initial
Larynx diameter, nozzle exit internal diameter and larynx serif ablating rate；
Propellant burning rate module is used to input the burn rate parameter of propellant, burn rate parameter include propellant reference pressure,
The reference temperature of propellant and the standard burn rate of propellant；
Combustion face data import modul retires data for importing Burning area of grain meat thickness, and Burning area of grain meat thickness retires data and includes
The logical of face area, the volume of remaining powder charge, the weight of remaining powder charge and remaining powder charge is fired in thick, the remaining powder charge of the powder charge meat of burning-off
Gas area；
Nozzle with scarfed exit plane parameter module is used to input the design parameter of nozzle with scarfed exit plane.
Internal ballistics attributes calculated result includes the engine pressure, motor power, engine stream to change with time
Amount, nozzle thrust coefficient, gas deflector angle, engine axial thrust, engine lateral thrust, thrust point.
Internal ballistics attributes calculated result includes pressure-time graph, axial thrust-time graph, lateral thrust-time song
Line, flow-deviation angle-time graph and mass flowrate-time graph.
The present invention, which solves traditional interior ballistic calculation method, cannot calculate tilting nozzle with scarfed exit plane engine performance, calculating parameter
Not congruent weakness promotes this kind of tilting nozzle with scarfed exit plane solid engines and designs computational efficiency, shortens product development cycle.
It is illustrated below by a specific embodiment.
A kind of solid engines internal ballistics attributes indication software systems, initial interface is as shown in Fig. 2, in the interface upper left corner
Equipped with menu bar, which includes charge data, calculation result data and calculated result curve, and the interface lower right corner is 4 function
Energy key, the calculation document saved can be opened by opening key；Calculation key is that input parameter starts to calculate after the completion；Saving key is to protect
It deposits when secondary calculated result；ESC Escape is to log off.The charge data of menu bar is clicked, interface display charge data is (i.e.
Input data of explosive filled), selection data (i.e. working environment initial parameter), jet pipe data (i.e. jet pipe type), propellant physical property ginseng
Data/coherency (i.e. the burn rate parameter of propellant) and combustion face and related data (i.e. Burning area of grain meat thickness retires data)；
Wherein, shown in Figure 2, charge data provides powder charge meat thickness, Propellants With Lower Pressure Exponent, propellant density, pushes away
It is quick into agent combustion gas specific heat ratio, propellant fuel gas temperature, propellant combustion gas gas constant, propellant characteristic velocity and propellant temperature
Feel the input frame of coefficient；
It is shown in Figure 2, select data to provide the effective operating pressure of engine ignition pressure, engine, engine work
Make terminal pressure, the nozzle thrust coefficient factor, engine initial free volume, engine operation initial temperature, engine average operation
The input frame of height and engine operating environments atmospheric pressure
Shown in Figure 2, jet pipe data can choose normal jet pipe and oblique jet pipe, select normal jet pipe, then with traditional inner trajectory
Program can equally calculate the inner trajectory of traditional conventional engine；Select oblique jet pipe that can calculate tilting nozzle with scarfed exit plane engine
Inner trajectory.When selecting normal jet pipe, conventional parameter includes the initial larynx diameter of jet pipe, nozzle exit internal diameter and larynx serif ablating rate；Ginseng
As shown in Figure 3, when selecting oblique jet pipe, " adding oblique nozzle structure parameter " can brighten, and click can carry out tilting nozzle with scarfed exit plane and set
Parameter input is counted, design parameter includes jet pipe number, jet pipe oblique angle, nozzle expansion half-angle, jet pipe angle of chamfer, jet pipe phase cloth
Office angle, cover axis intersection point distance, the symmetrical segment length of jet pipe and jet pipe chamfered portion material calculation, the exit inside diameter of oblique jet pipe refer to non-
The exit inside diameter of chamfered section jet pipe, jet pipe oblique angle refer to the angle of nozzle axis and powder charge burning chamber axis；Nozzle expansion half-angle
Refer to the angle of jet pipe diffuser bus and nozzle axis；Jet pipe angle of chamfer refers to the folder of jet pipe diffuser beveling plane and nozzle axis
Angle, jet pipe phase layout angle refer to the phase layout angle of multi nozzle, 1 jet pipe input 0.
Shown in Figure 2, propellant physical parameter correlation provides the reference temperature of the reference pressure of propellant, propellant
The input frame of the standard burn rate of degree and propellant；
Shown in Figure 2, combustion face and related data provide the combustion face area, surplus of thick, the remaining powder charge of powder charge meat of burning-off
The input frame of the breathing area of the volume of remaining powder charge, the weight of remaining powder charge and remaining powder charge；
It is shown in Figure 2, the calculation result data in the initial interface upper left corner is clicked, the internal ballistics attributes for obtaining Fig. 4 calculate
As a result, this as the result is shown be instantaneous value, that is, include the engine pressure, motor power, the engine that change with time
Flow, nozzle thrust coefficient, gas deflector angle, engine axial thrust, engine lateral thrust, thrust point.
Fig. 5 is calculated result statistical parameter, and statistics is engine inner ballistic functional parameter, and clicking " calculating " can obtain
?.
Calculated result curve, including pressure-time graph, axial thrust-time graph, lateral thrust-is shown in Fig. 6
Time graph, flow-deviation angle-time graph and mass flowrate-time graph.
When it is implemented, selecting jet pipe type, input are corresponding to calculate data in the interface of Fig. 2, computing function is clicked,
The indication of solid engines internal ballistics attributes is finally obtained as a result, clicking upper left corner calculation result data and calculated result curve, i.e.,
It can check.
The present invention is not limited to the above-described embodiments, for those skilled in the art, is not departing from
Under the premise of the principle of the invention, several improvements and modifications can also be made, these improvements and modifications are also considered as protection of the invention
Within the scope of.The content being not described in detail in this specification belongs to the prior art well known to professional and technical personnel in the field.
Claims (9)
1. a kind of solid engines internal ballistics attributes indicate software systems, characterized in that it comprises:
Display module is inputted, is used to show that the input interface of input engine parameter, the input interface to be inputted for user
Engine parameter, the engine parameter include the conventional ginseng of data of explosive filled, the working environment initial parameter of engine, jet pipe
Number, jet pipe type, the burn rate parameter of propellant, Burning area of grain meat thickness retire the design parameter of data and nozzle with scarfed exit plane；The spray
Tubing type includes conventional jet pipe and nozzle with scarfed exit plane, and the design parameter includes jet pipe number, jet pipe oblique angle, nozzle expansion half
Angle, jet pipe angle of chamfer, jet pipe phase layout angle, cover axis intersection point distance, the symmetrical segment length of jet pipe and jet pipe chamfered portion calculate step
It is long；
Computing module is used to calculate engine performance parameter according to preset algorithm, and obtains internal ballistics attributes calculating
As a result；
Display module is exported, is used to export and show the internal ballistics attributes calculated result.
2. solid engines internal ballistics attributes as described in claim 1 indicate software systems, which is characterized in that the input is aobvious
Show that module includes:
Charge data module is used to input data of explosive filled；
Primary data module is used to input the working environment initial parameter of engine；
Jet pipe data module is used to input the conventional parameter and selection jet pipe type of jet pipe；
Propellant burning rate module is used to input the burn rate parameter of propellant；
Face data import modul is fired, is used to import Burning area of grain meat thickness and retires data；
Nozzle with scarfed exit plane parameter module is used to input the design parameter of nozzle with scarfed exit plane.
3. solid engines internal ballistics attributes as described in claim 1 indicate software systems, it is characterised in that: the powder charge ginseng
Number includes powder charge meat thickness, Propellants With Lower Pressure Exponent, propellant density, propellant combustion gas specific heat ratio, propellant fuel gas temperature, promotes
Agent combustion gas gas constant, propellant characteristic velocity and propellant temperature sensitivity coefficient.
4. solid engines internal ballistics attributes as described in claim 1 indicate software systems, it is characterised in that: the building ring
Border initial parameter includes engine ignition pressure, the effective operating pressure of engine, engine operation terminal pressure, nozzle thrust system
The number factor, engine initial free volume, engine operation initial temperature, engine average operation height and engine operating environments are big
Atmospheric pressure.
5. solid engines internal ballistics attributes as described in claim 1 indicate software systems, it is characterised in that: the conventional ginseng
Number includes the initial larynx diameter of jet pipe, nozzle exit internal diameter and larynx serif ablating rate.
6. solid engines internal ballistics attributes as described in claim 1 indicate software systems, it is characterised in that: the burn rate ginseng
Number includes reference pressure, the reference temperature of propellant and the standard burn rate of propellant of propellant.
7. solid engines internal ballistics attributes as described in claim 1 indicate software systems, it is characterised in that: the powder charge combustion
Face meat thickness retires the combustion face area of thick, the remaining powder charge of powder charge meat that data include burning-off, the volume of remaining powder charge, remaining powder charge
The breathing area of weight and remaining powder charge.
8. solid engines internal ballistics attributes as described in claim 1 indicate software systems, it is characterised in that: the inner trajectory
Performance calculated result includes the engine pressure to change with time, motor power, engine flow, nozzle thrust system
Number, gas deflector angle, engine axial thrust, engine lateral thrust, thrust point.
9. solid engines internal ballistics attributes as described in claim 1 indicate software systems, it is characterised in that: the inner trajectory
Performance calculated result includes pressure-time graph, axial thrust-time graph, lateral thrust-time graph, flow-deviation angle-
Time graph and mass flowrate-time graph.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110633522A (en) * | 2019-09-11 | 2019-12-31 | 南京航空航天大学 | A Reverse Design Method of Supersonic Thrust Nozzle Based on Maximum Thrust Theory |
| CN111027222A (en) * | 2019-12-18 | 2020-04-17 | 北京空天技术研究所 | Multi-pulse engine total impact correction method and system for Lambert orbit change of spacecraft |
| CN111814348A (en) * | 2020-07-21 | 2020-10-23 | 北京中科宇航技术有限公司 | A Predictive Method for Internal Ballistic Performance of Solid Rocket Motors |
| CN111881614A (en) * | 2020-09-28 | 2020-11-03 | 中国人民解放军国防科技大学 | Solid rocket engine charging characterization method |
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| CN107832565A (en) * | 2017-12-06 | 2018-03-23 | 内蒙动力机械研究所 | A kind of solid engines One-dimensional interior ballistic modeling and performance indication software systems |
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| CN106777457A (en) * | 2016-11-10 | 2017-05-31 | 内蒙动力机械研究所 | A kind of solid rocket motor grain Structural Reliability Evaluation software systems |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110633522A (en) * | 2019-09-11 | 2019-12-31 | 南京航空航天大学 | A Reverse Design Method of Supersonic Thrust Nozzle Based on Maximum Thrust Theory |
| CN111027222A (en) * | 2019-12-18 | 2020-04-17 | 北京空天技术研究所 | Multi-pulse engine total impact correction method and system for Lambert orbit change of spacecraft |
| CN111814348A (en) * | 2020-07-21 | 2020-10-23 | 北京中科宇航技术有限公司 | A Predictive Method for Internal Ballistic Performance of Solid Rocket Motors |
| CN111814348B (en) * | 2020-07-21 | 2022-02-08 | 中国科学院力学研究所 | Method for predicting internal ballistic performance of solid rocket engine |
| CN111881614A (en) * | 2020-09-28 | 2020-11-03 | 中国人民解放军国防科技大学 | Solid rocket engine charging characterization method |
| CN111881614B (en) * | 2020-09-28 | 2020-12-08 | 中国人民解放军国防科技大学 | A solid rocket motor charge characterization method |
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Application publication date: 20190830 |