CN109900154A - A kind of rocket launching gas flow field quasi-steady state predicting method and device - Google Patents
A kind of rocket launching gas flow field quasi-steady state predicting method and device Download PDFInfo
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Abstract
A kind of rocket launching gas flow field quasi-steady state predicting method, include the following steps: Step 1: according to the jet size of rocket, rocket take off vertically height, emission system structure, determine rocket it is multiple take off vertically height under the conditions of gas flow field indication feature operating condition；Step 2: establishing gas flow field according to feature operating condition and calculating grid model, gas flow field is calculated using a certain method for numerical simulation；Step 3: determining grid resolution, method for numerical simulation is determined；Step 4: indication operating condition according to the gas flow field limit under rocket launching maximum conditions, the grid resolution that determines in step 3, the gas flow field for establishing limit indication operating condition calculates grid model, using the method for numerical simulation determined in step 3, the gas flow field under rocket launching maximum conditions is calculated.
Description
Technical field
The present invention relates to a kind of rocket launching gas flow field quasi-steady state predicting method and devices, belong to rocket launching technology neck
Domain.
Background technique
In take-off process, the high temperature and high speed combustion gas stream that jet pipe sprays can generate bottom launch system acute for rocket or guided missile
Strong impact and ablation effect, it is therefore desirable to which power, thermal environment locating for design phase clear take-off process emission system are used for
Instruct the structural strength and heat protection design of emission system.Gas flow field emulation is generallyd use in engineering to obtain combustion gas stream to hair
Penetrate power, the heat affecting of system.
Pulsatile flow field emulation and transient flow field emulation can be divided into the emulation of transmitting gas flow field.The emulation of stable state gas flow field
Available rocket is in the gas flow field of the stable state of a certain position, since stable state calculating solution amount is smaller, so needing
Computing resource it is less, required time is also shorter, but stable state gas flow field emulation spatio-temporal restriction it is obvious.Transient state combustion gas stream is imitative
Very can be more accurate obtain rocket, each moment in Missile Launching Process, position gas flow field distribution situation, and then obtain
Obtain influence situation of the gas flow field to each equipment.However to obtain more accurate calculated result, transient state gas flow field is calculated
Time step usually all can very little, grid amount is also all very big, and it is very more that this results in entirely emulating occupied computing resource,
And the period emulated is also very very long, many situations are unacceptable in engineering for this.
Summary of the invention
The technical problem to be solved by the present invention is having overcome the deficiencies of the prior art and provide a kind of rocket launching combustion gas stream
Quasi-steady state predicting method and device are calculated using the stable state of different height operating condition and are taken off dynamic process come simulated rocket.Using
The key of gas flow field quasi-steady state predicting method is to realize multiple spot stable state calculated result to the envelope of transient calculation results, so must
The trajectory that must be taken off according to rocket make rational planning for gas flow field calculate feature operating condition.For rocket takes off vertically trajectory, combustion gas
The coverage of stream is extended out with height in concentric circles substantially, has stronger regularity, so can choose height in calculating
Equidistant feature operating condition is spent to be calculated.And for the trajectory that takes off there are the limit of relatively larger transverse displacement, combustion gas stream pair
The influence of emission system wants more complicated, the variation of existing height change bring flow range and intensity, and has laterally partially
The movement of combustion gas stream center of impact caused by shifting, needs to comprehensively consider a variety of limiting conditions, determines characterization device by combustion gas stream shadow
The worst ballistic conditions that take off are rung, initial stage, to influence amplitude of variation to emitter bigger since limit trajectory takes off, so one
As shorter is wanted to the indication feature operating condition interval of limit trajectory, and should be arranged in the initial take-off stage and answer more dense feature work
Condition.
The object of the invention is achieved by the following technical programs:
A kind of rocket launching gas flow field quasi-steady state predicting method, includes the following steps:
Step 1: according to the jet size of rocket, rocket take off vertically height, emission system structure, determine that rocket exists
The feature operating condition that gas flow field indicates under the conditions of multiple height that take off vertically；
Step 2: the feature work indicated according to gas flow field under the conditions of multiple height that take off vertically described in step 1
Condition, establishes gas flow field and calculates grid model, calculates gas flow field using a certain method for numerical simulation；
Step 3: the grid resolution of grid model described in set-up procedure two, recalculate after gas flow field with step
Gas flow field comparison in two determines grid resolution when comparing result is less than or equal to the first preset value；Based on step 2
Described in grid model, using other method for numerical simulation recalculate after gas flow field with the gas flow field pair in step 2
Than determining method for numerical simulation when comparing result is less than or equal to the second preset value；
Step 4: indication operating condition according to the gas flow field limit under rocket launching maximum conditions, the grid that determines in step 3
Resolution ratio, establish the limit indication operating condition gas flow field calculate grid model, using in step 3 determine method for numerical simulation,
Calculate the gas flow field under rocket launching maximum conditions.
Above-mentioned rocket launching gas flow field quasi-steady state predicting method, in the step 1 according to rocket take off vertically height and
The ratio of the jet size of rocket is divided into multiple rockets and takes off vertically feature height range；According to the structure of emission system, more
A rocket, which takes off vertically, chooses multiple and different ratio within the scope of feature height, determines rocket in multiple height conditions that take off vertically
The feature operating condition of lower gas flow field indication.
Above-mentioned rocket launching gas flow field quasi-steady state predicting method chooses combustion when carrying out gas flow field comparison in step 3
The value range of pressure in airflow field parameter as a comparison, first preset value and the second preset value is 15~25%.
Above-mentioned rocket launching gas flow field quasi-steady state predicting method, rocket launching maximum conditions described in step 4 is according to fire
The arrow limit take off ballistic conditions, rocket engine working limit condition, extreme environment wind friction velocity, emitter place limit appearance
State condition determines.
Above-mentioned rocket launching gas flow field quasi-steady state predicting method, when rocket takes off height less than or equal to preset height,
Extreme environment wind friction velocity can be ignored；The value range of the preset height is 10~15 times of rocket nozzles diameters.
A kind of rocket launching gas flow field quasi-steady state forecasting device, including feature operating condition determining module, gas flow field calculate
Module, grid and proof of algorithm module, gas flow field indicate module；
The feature operating condition determining module according to the jet size of rocket, rocket take off vertically height, emission system knot
Structure, for determine rocket it is multiple take off vertically height under the conditions of gas flow field indication feature operating condition；
The feature operating condition that the gas flow field computing module is exported according to feature operating condition determining module, establishes gas flow field meter
Grid model is calculated, gas flow field is calculated using a certain method for numerical simulation；
The grid that the grid and proof of algorithm module are used to adjust the grid model in gas flow field computing module is differentiated
Rate recalculates the gas flow field after gas flow field with the output of gas flow field computing module and compares, until comparing result is less than etc.
When the first preset value, grid resolution is determined；Based on the grid model in gas flow field computing module, using other Numerical-Modes
Quasi- method is recalculated and is compared after gas flow field with the gas flow field in gas flow field computing module, until comparing result is less than etc.
When the second preset value, method for numerical simulation is determined；
Gas flow field indication module according to gas flow field limit indication operating condition under rocket launching maximum conditions, grid and
The grid resolution determined in proof of algorithm module, the gas flow field for establishing limit indication operating condition calculate grid model, utilize net
The method for numerical simulation determined in lattice and proof of algorithm module calculates the gas flow field under rocket launching maximum conditions.
Above-mentioned rocket launching gas flow field quasi-steady state forecasting device, the feature operating condition determining module vertically rise according to rocket
The ratio for flying the jet size of height and rocket is divided into multiple rockets and takes off vertically feature height range；According to emission system
Structure takes off vertically in multiple rockets and chooses multiple and different ratio within the scope of feature height, determines that rocket vertical rises multiple
The feature operating condition that gas flow field indicates under the conditions of winged height.
Above-mentioned rocket launching gas flow field quasi-steady state forecasting device, the grid and proof of algorithm module carry out gas flow field
When comparison, the pressure parameter as a comparison in gas flow field, the value range of first preset value and the second preset value are chosen
It is 15~25%.
Above-mentioned rocket launching gas flow field quasi-steady state forecasting device, the rocket launching maximum conditions rise according to the rocket limit
It is true to fly ballistic conditions, rocket engine working limit condition, extreme environment wind friction velocity, emitter placement extreme attitude condition
It is fixed.
Above-mentioned rocket launching gas flow field quasi-steady state forecasting device, it is described when rocket takes off height less than or equal to preset height
When, extreme environment wind friction velocity can be ignored；The value range of the preset height is 10~15 times of rocket nozzles diameters.
The present invention has the following beneficial effects: compared with the prior art
(1) for compared to the indication of gas flow field stable state, the present invention uses rocket launching gas flow field quasi-steady state predicting method
The changing rule that rocket take-off process gas flow field can be obtained obtains rocket body, the combustion gas stream shock loading that emission system is born
The changing rule (to take off highly) at any time with ablation, has more directive significance to structural strength and heat protection design；
(2) compared to gas flow field transient state indication for, the method for the present invention need computing resource it is less, required time also compared with
It is short, calculated result can envelope dynamic take-off process, more meet the needs of engineer application；
(3) for compared to the indication of gas flow field transient state, for the method for the present invention without generating dynamic mesh, grid generation is simpler,
It calculates more rapidly, the verification of calculated result is also more convenient, and can be found the problem earlier, be avoided vast resources and waste of time；
(4) the present invention provides a kind of sides that by multiple spot stable state calculated result transient calculation results are carried out with envelope indication
Method, this method have certain versatility, can apply in other numerical simulation fields.
Detailed description of the invention
Fig. 1 is the step flow chart of the method for the present invention；
Fig. 2 is the step flow chart of the embodiment of the present invention；
Fig. 3 is the feature operating condition schematic diagram of the trajectory that takes off vertically of the embodiment of the present invention；
Fig. 4 is the feature operating condition schematic diagram of the limit takeoff condition of the embodiment of the present invention.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with attached drawing to implementation of the invention
Mode is described in further detail.
A kind of rocket launching gas flow field quasi-steady state predicting method, as shown in Figure 1, including the following steps:
Step 101, take off vertically height, the structure of emission system according to the jet size of rocket, rocket, determines that rocket exists
The feature operating condition that gas flow field indicates under the conditions of multiple height that take off vertically.
Determined described in step 101 rocket it is multiple take off vertically height under the conditions of gas flow field indication feature operating condition
Method is as follows: being to divide fire with reference to scale with the ratio range of the opposite nozzle diameter of the practical height of taking off of rocket with nozzle diameter
Arrow takes off feature height range, generally divides 5 feature height ranges, be respectively as follows: 0~0.5,1.5~2.5,3.0~7.5,
14.5~35.0,40.0~65.0, then the transmitting that may be scanned according to rocket and emission system structure and engine gas stream
System component range, takes 3~5 certain heights to correspond to operating condition exploitation forecasting models, carries out specific indication according to forecasting models.
This 3~5 certain heights correspond to operating condition take off vertically condition gas flow field indication feature operating condition.
Step 102, the gas flow field indication feature operating condition for the condition that takes off vertically according to step 101, establish combustion
The computation of the gas flow field grid model calculates gas flow field；
The grid resolution of gas flow field computation model, recalculates gas flow field, tests in step 103, set-up procedure 102
Demonstrate,prove the independence for indicating result and grid resolution in step 102；Grid mould is calculated using the gas flow field described in step 102
Type calculates the accuracy that gas flow field calculates in gas flow field verification step 102 using other numerical algorithms；When in step 102
Grid model or gas flow field results abnormity when, then be transferred to step after adjusting grid model and gas flow field method for numerical simulation
102, until the grid model and gas flow field calculated result verified in step 103 are accurate；
Grid independence described in step 103 and the verification standard of algorithm consistency are as follows: adjustment grid resolution or calculation
After method, indicates that result space monitoring position combustion gas parameter differs each other twice and think that grid reaches unrelated no more than tolerance value
Property, algorithm achieve the effect that consistency, such as space monitoring position fuel gas temperature differs be no more than 15~25% each other.
Step 104 plans that the gas flow field limit indicates operating condition according to rocket launching maximum conditions.The limit indicates that operating condition is main
According to the rocket limit take off ballistic conditions, rocket engine working limit condition, extreme environment wind friction velocity, emitter place
Extreme attitude condition determines.
The gas flow field limit described in step 104 indicates that operating condition planing method is as follows: four kinds of maximum conditions are made jointly
Used time, arbitrary height rocket rocket body posture are located in a conical envelopes spatial dimension, and corresponding combustion gas stream is scanned space and also formed
One conical envelopes space is still chosen during practical indication and states 5 feature height ranges, and entry evaluation analyzes combustion gas stream
In conical envelopes space emission system apparatus structure, rocket body be hit, ablation coverage and influence degree, in conjunction with rocket, hair
System concern demand is penetrated, specified rocket height corresponding specified limit posture of taking off is selected and correspond to operating condition and develops forecasting models, according to
Carry out specific indication according to forecasting models.These indication operating conditions the selected i.e. gas flow field limit indicates operating condition.
When above-mentioned four kinds of maximum conditions collective effects, respective heights rocket rocket body is also at spatial margins attitude angle state,
Correspondingly rocket tube is also at spatial margins attitude angle state, combines combustion gas stream ablation range to can determine combustion gas accordingly
The flow field limit indicates operating condition.Rocket tube is under the conditions of spatial margins attitude angle, nozzle axis extended line and transmitting
When system structure surface is intersected, combustion gas stream impacts emission system body structure surface, ablation is in most strong operating condition；Large-sized structural parts table
Area is larger, and nozzle axis extended line intersects with large-sized structural parts surface, while when combustion gas stream coverage area reaches maximum again, combustion
Air-flow reaches maximum duty to the impact of emission system structure, ablation range.Combustion gas stream impact, the most strong operating condition of ablation and punching
Hit, ablation range maximum duty be the gas flow field limit indication operating condition planning concrete foundation.
Step 105 indicates operating condition based on the limit that step 104 is planned, the gas flow field for establishing limit indication operating condition calculates
Grid model carries out the indication of gas flow field limiting condition, provides the distribution of gas flow field envelope and result of variations.
A kind of rocket launching gas flow field quasi-steady state forecasting device, including feature operating condition determining module, gas flow field calculate
Module, grid and proof of algorithm module, gas flow field indicate module；
The feature operating condition determining module according to the jet size of rocket, rocket take off vertically height, emission system knot
Structure, for determine rocket it is multiple take off vertically height under the conditions of gas flow field indication feature operating condition；
The feature operating condition that the gas flow field computing module is exported according to feature operating condition determining module, establishes gas flow field meter
Grid model is calculated, gas flow field is calculated using a certain method for numerical simulation；
The grid that the grid and proof of algorithm module are used to adjust the grid model in gas flow field computing module is differentiated
Rate recalculates the gas flow field after gas flow field with the output of gas flow field computing module and compares, until comparing result is less than etc.
When the first preset value, grid resolution is determined；Based on the grid model in gas flow field computing module, using other Numerical-Modes
Quasi- method is recalculated and is compared after gas flow field with the gas flow field in gas flow field computing module, until comparing result is less than etc.
When the second preset value, method for numerical simulation is determined；
Gas flow field indication module according to gas flow field limit indication operating condition under rocket launching maximum conditions, grid and
The grid resolution determined in proof of algorithm module, the gas flow field for establishing limit indication operating condition calculate grid model, utilize net
The method for numerical simulation determined in lattice and proof of algorithm module calculates the gas flow field under rocket launching maximum conditions.
Embodiment:
Rocket launching gas flow field quasi-steady state predicting method specific steps are as shown in Fig. 2, specific carry out according to the following steps:
Step 1: taking off vertically trajectory planning characteristic point of trajectory according to rocket
For rocket takes off vertically trajectory, the coverage of combustion gas stream substantially with take off height in concentric circles to
Outer expansion has stronger regularity, can calculate that gas flow field is joined between two kinds of feature operating conditions by the method for linear fit
Number change procedure, so can choose height in calculating, feature operating condition is calculated at equal intervals, and feature operating condition can take larger
Vertical separation.Characteristic point schematic diagram based on the trajectory that takes off vertically is as shown in Figure 3.
Step 2: carrying out the indication of rocket launching gas flow field for characteristic point of trajectory
Gas flow field indication is carried out for each characteristic point of trajectory.Rocket body position is adjusted to ballistic characteristic point first
It sets, establishes gas flow field and calculate grid model, using second order accuracy, two-component steady state values analogy method indication gas flow field point
Cloth rule.When indicating different height operating condition, it should be noted that correct engine pressure to present level pressure, to ensure
Calculated result is accurate as far as possible.After completing flow field indication, grid independence to calculated result and algorithm consistency verify,
It keeps other design conditions constant, changes grid resolution to verify grid independence；It keeps other design conditions constant, changes
Numerical algorithm carrys out checking algorithm consistency.
Step 3: planning gas flow field limiting condition according to rocket launching maximum conditions
Rocket is analyzed first, in Missile Launching Process, various possible takeoff conditions, including rocket take-off limitation trajectory item
Part, extreme environment wind friction velocity, flat pad place posture maximum conditions and engine operation maximum conditions.Rocket take-off limitation
Trajectory is calculated by Launch Dynamics and is determined, is changed with time pass for rocket height, lateral maximum offset and maximum attitude angle
System；Extreme environment wind friction velocity, that is, vertical rocket take off direction reach transmitting allow maximum wind velocity state；Emitter is placed
Posture maximum conditions, that is, posture of the rocket on platform is in maximum deflection angle, and the shape deflected to emitter key structure
State；Engine operation maximum conditions are maximum temperature condition, the i.e. highest state of engine performance.
The combination of limiting condition is to aggravate influence of the combustion gas stream to emitter as principle, by various possible take-off limitations
Condition superposition, determines that emitter is influenced worst takeoff condition by combustion gas stream.By taking the motor-driven heat emission of highway as an example, when taking off
When height is lower than certain altitude (10~15 times of nozzle exit diameters), air speed influence is negligible, only considers other maximum conditions, enables
Take-off limitation trajectory offset direction is consistent with rocket placement posture deflection direction, and car launcher is on rocket offset direction；So
After take engine to be in maximum temperature condition, when take off height be higher than certain altitude (10~15 times of nozzle exit diameters) when, examine
Considering Limit of Wind Speed influences, and takes wind speed direction consistent with trajectory lateral shift direction of taking off.So combined by a variety of maximum conditions
Optimization, available emitter are influenced worst limit takeoff condition by combustion gas stream.
After determining limit takeoff condition, the planning of feature operating condition is completed, since limit trajectory takes off initial stage to transmitting dress
It is bigger to set influence amplitude of variation, so generally wanting shorter to the indication feature operating condition interval of limit trajectory, and in initial take-off
Stage, which should be arranged, answers more dense feature operating condition.Feature operating condition schematic diagram based on limit takeoff condition is as shown in Figure 4.
Step 4: the gas flow field limiting condition based on planning carries out envelope indication
Carry out envelope indication based on planning limiting condition in previous step.It is consistent in the method and step 2 specifically indicated.
Limiting condition is able to reflect the most harsh conditions that emission system is faced substantially, and the envelope to all situations of taking off may be implemented.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (10)
1. a kind of rocket launching gas flow field quasi-steady state predicting method, characterized by the following steps:
Step 1: according to the jet size of rocket, rocket take off vertically height, emission system structure, determine rocket multiple
The feature operating condition that gas flow field indicates under the conditions of the height that takes off vertically；
Step 2: being built according to the feature operating condition that gas flow field under the conditions of multiple height that take off vertically described in step 1 indicates
Vertical gas flow field calculates grid model, calculates gas flow field using a certain method for numerical simulation；
Step 3: the grid resolution of grid model described in set-up procedure two, recalculate after gas flow field and in step 2
Gas flow field comparison, until comparing result be less than or equal to the first preset value when, determine grid resolution；Based on institute in step 2
The grid model stated is recalculated using other method for numerical simulation and is compared after gas flow field with the gas flow field in step 2,
When comparing result is less than or equal to the second preset value, method for numerical simulation is determined；
Step 4: being differentiated according to gas flow field limit indication operating condition, the grid determined in step 3 under rocket launching maximum conditions
Rate, the gas flow field for establishing limit indication operating condition calculate grid model, using the method for numerical simulation determined in step 3, calculate
Gas flow field under rocket launching maximum conditions.
2. a kind of rocket launching gas flow field quasi-steady state predicting method according to claim 1, it is characterised in that: the step
It is taken off vertically the ratio of the jet size of height and rocket in rapid one according to rocket, is divided into multiple rockets and takes off vertically feature height
Range；According to the structure of emission system, takes off vertically in multiple rockets and choose multiple and different ratio within the scope of feature height, really
Determine rocket it is multiple take off vertically height under the conditions of gas flow field indication feature operating condition.
3. a kind of rocket launching gas flow field quasi-steady state predicting method according to claim 1, it is characterised in that: step 3
When middle progress gas flow field comparison, the pressure parameter as a comparison in gas flow field is chosen, first preset value and second pre-
If the value range of value is 15~25%.
4. a kind of rocket launching gas flow field quasi-steady state predicting method according to claim 1, it is characterised in that: step 4
Described in rocket launching maximum conditions take off ballistic conditions, rocket engine working limit condition, limit cycle according to the rocket limit
Border wind friction velocity, emitter are placed extreme attitude condition and are determined.
5. a kind of rocket launching gas flow field quasi-steady state predicting method according to claim 4, it is characterised in that: work as rocket
When height of taking off is less than or equal to preset height, extreme environment wind friction velocity can be ignored；The value range of the preset height is
10~15 times of rocket nozzles diameters.
6. a kind of rocket launching gas flow field quasi-steady state forecasting device, it is characterised in that: including feature operating condition determining module, combustion gas
Flow Field Calculation module, grid and proof of algorithm module, gas flow field indicate module；
The feature operating condition determining module according to the jet size of rocket, rocket take off vertically height, emission system structure, use
In determine rocket it is multiple take off vertically height under the conditions of gas flow field indication feature operating condition；
The feature operating condition that the gas flow field computing module is exported according to feature operating condition determining module establishes gas flow field and calculates net
Lattice model calculates gas flow field using a certain method for numerical simulation；
The grid and proof of algorithm module are used to adjust the grid resolution of the grid model in gas flow field computing module, weight
It is new to calculate the gas flow field comparison exported after gas flow field with gas flow field computing module, until comparing result is less than or equal to first
When preset value, grid resolution is determined；Based on the grid model in gas flow field computing module, using other method for numerical simulation
It is compared after recalculating gas flow field with the gas flow field in gas flow field computing module, until comparing result is less than or equal to second
When preset value, method for numerical simulation is determined；
The gas flow field indication module is according to gas flow field limit indication operating condition, grid and algorithm under rocket launching maximum conditions
The grid resolution determined in authentication module, the gas flow field for establishing limit indication operating condition calculate grid model, using grid and
The method for numerical simulation determined in proof of algorithm module calculates the gas flow field under rocket launching maximum conditions.
7. a kind of rocket launching gas flow field quasi-steady state forecasting device according to claim 6, it is characterised in that: the spy
The ratio that sign operating condition determining module takes off vertically according to rocket highly with the jet size of rocket, is divided into multiple rockets and takes off vertically
Feature height range；According to the structure of emission system, multiple rockets take off vertically choose within the scope of feature height it is multiple and different
Ratio, determine rocket it is multiple take off vertically height under the conditions of gas flow field indication feature operating condition.
8. a kind of rocket launching gas flow field quasi-steady state forecasting device according to claim 6, it is characterised in that: the net
When lattice and proof of algorithm module carry out gas flow field comparison, pressure in gas flow field parameter as a comparison is chosen, described first
The value range of preset value and the second preset value is 15~25%.
9. a kind of rocket launching gas flow field quasi-steady state forecasting device according to claim 6, it is characterised in that: the fire
Arrow transmitting maximum conditions are taken off ballistic conditions, rocket engine working limit condition, extreme environment wind speed item according to the rocket limit
Part, emitter are placed extreme attitude condition and are determined.
10. a kind of rocket launching gas flow field quasi-steady state forecasting device according to claim 9, it is characterised in that: described
When rocket takes off height less than or equal to preset height, extreme environment wind friction velocity can be ignored；The value of the preset height
Range is 10~15 times of rocket nozzles diameters.
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| CN113886943A (en) * | 2021-09-06 | 2022-01-04 | 蓝箭航天空间科技股份有限公司 | Carrier rocket takeoff interference detection method and detection device |
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