CN109508504A - Rocket sledge tackle system tests aerodynamic characteristic modification method - Google Patents
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Abstract
The invention discloses a kind of calculation methods of aerodynamic characteristic in rocket sledge sled test system, the calculation method, on the one hand by carrying out quantitative analysis to rocket sledge tackle system test data and rocket sledge tackle system Field Flow Numerical Simulation result, the influence that non-stationary motion characteristic calculates testee or system (such as drag parachute system) aeroperformance in rocket sledge sled test is determined；On the other hand, influence of the rocket sledge coaster wake flow to testee or system (such as drag parachute system) aeroperformance calculated result is calculated.Disclose the difference mechanism of aerodynamic characteristic experiment value and design value in rocket sledge sled test, the especially difference mechanism of drag parachute drag characteristic, it establishes the aeroperformance calculation method suitable for rocket sledge sled test condition, solve engineering problem, have important practical significance.
Description
Technical field
The present invention relates to rocket sledge tackle system experimental data processing fields, and it is pneumatic to be related to the test of rocket sledge tackle system
Characteristic revision calculation method, and in particular to drag parachute and parachute and its data processing field in rocket sledge sled test relate to
And to a kind of analysis of rocket sledge coaster-drag parachute system test data and drag parachute be pneumatic and drag characteristics calculation method.
Background technique
Rocket sledge tackle system refers to pushes rocket sledge to move along sliding rail by booster rocket, so that pulling test part is (as hindered
Power umbrella etc.), the experimental rig to testing experiment part working performance.The main composition part of rocket sledge tackle system is rocket sledge
Coaster and testpieces, wherein testpieces is usually a kind of aerodynamic decelerator device, and such as drag parachute, it assists high-speed aircraft to land,
It is mainly used in the aircraft such as aircraft, airship.
The research method of drag parachute working performance mainly includes theoretical method, test method and numerical method.Wherein, it tries
Proved recipe method includes wind tunnel test, rocket sledge sled test, aircraft testing and airdrop test etc. again.Due to constituting the material of drag parachute
With nonlinear mechanical characteristic, the motion process of drag parachute also has the characteristics that nonlinear under normal circumstances.Therefore, deep
Theory analysis is still extremely difficult at present, makes slow progress.
Wind tunnel test is always the important means of drag parachute structure and pneumatic performance evaluation, realizes that process is relatively easy,
Data acquisition is convenient, but the size of test speed, wind tunnel wall interference and test section is restricted to the performance test of drag parachute.Fly
Machine test can provide the experimental condition for more meeting practical application for drag parachute, since drag parachute is mainly applied to aircraft.Cause
This, aircraft testing data can more intuitively reflect the resistance performance of drag parachute.But aircraft testing is to Test Data Collecting technology
It is required that higher, test period length, risk are big, costly.
Rocket sledge was risen in the twentieth century middle and later periods, is promoted using pencil rocket and is used as power, run in dedicated track,
Traction is by test specimen, to simulate by test specimen state of flight.Simultaneously by means of testing such as optics, electronics and remote sensing, it is tested
Part runs a series of performance parameters in overall process.The outstanding advantages of Rocket sled test are to test speed and by the size of test specimen
Limitation is few.In drag parachute working performance research, test ability most worthy only full-scale, close to live flying state.Fire
Arrow sledge sled test can preferably meet drag parachute working performance test request.It can be tested point by rocket sledge sled test
Analyse drag parachute near-earth movement overall process (being straightened, inflate, be filled and throw umbrella) working performance, including resistance performance and structure it is strong
Degree etc..Therefore, Rocket sled test becomes the important means of drag parachute working performance test.
In the world, the great attention that rocket sledge sled test is made the country prosperous by aerospace science and technologies such as US and Russias.USN from
1945 to nineteen fifty-nine, building together had the Rocket Sled Test Track of ten different lengths, United States Air Force from nineteen fifty to nineteen sixty-eight,
Building together has the Rocket Sled Test Track of six different lengths, and US Army is built together from nineteen fifty-three to nineteen fifty-seven four different lengths
Rocket Sled Test Track.High-precision Rocket sled test track (the Holloman High Speed in the U.S., graceful air base, Huolou
Test Track, HHSTT) it is the most representative Rocket sled test place in the U.S., it is up to 15480m, test Mach Number Never To Be Exceeded is
8.5.The country in Rocket Sled Test Track construction evening, causes Rocket sled test application time slow, nineteen nineties just build up
First rocket sledge sliding rail is studied more than 40 years late than domestic drag parachute.But development speed is quickly, has successively built up three cunnings
Rail.
Rocket sled test in terms of China's drag parachute belongs to newer research method.Due to rocket sledge sled test in the world
Exchange of technology is restricted, and in order to meet the needs of China's aviation development and national defense construction, China is to rocket sledge coaster-drag parachute
The investment of system test continues to increase.Meanwhile experimental technique and analysis means are also continuously improved.Wherein, the analysis of test data
Processing and the calculating of drag parachute resistance performance are the key that rocket sledge-drag parachute system researches.
Existing drag parachute research theory and analysis method, because not accounting for rocket sledge tackle system movement in experiment
The factors such as unsteady characteristic, can not in accurate objective assessment Rocket sled test testpieces aeroperformance, provide accurately
Test data analyzer there are many sport technique segment as a result, still need to further investigate.On the other hand, it is tested in rocket sledge tackle system
In, rocket sledge coaster has differences in terms of pneumatic structure, quality, deceleration characteristic and wake flow with aircraft operating condition.Such as
Fruit simply directly handles Rocket sled test data, the aeroperformance data and aircraft testing data or design of obtained testpieces
Value has differences, and cannot correctly assess design performance.
Therefore, the data analysis theories and method of existing rocket sledge sled test have been unable to the examination of accurate evaluation rocket sledge
Test the aeroperformance (the especially resistance performance of drag parachute) of middle testpieces.
Summary of the invention
In order to solve the technical issues of above-mentioned background technique proposes, it is an object of the invention to solve rocket sledge tackle system
Test data analyzer problem, disclose the mechanism of testpieces aeroperformance difference, a kind of new calculation of aerodynamic characteristics method be provided,
It is capable of the true aeroperformance of accurate evaluation testpieces.
In order to achieve the above technical purposes, the technical solution of the present invention is as follows:
First with true coaster and rocket sledge platform, the test of rocket sledge tackle system is carried out, and to correlation test physics
Parameter measures；On this basis, for operating condition of test, Numerical-Mode is carried out to the rocket sledge tackle system in Steady
It is quasi-, and analysis is compared with the influence of the unsteady regime of actual experimental.By using unsteady correction factor ε to actual experimental
Difference caused by unsteady characteristic is modified, and provides unsteady correction formula.Meanwhile for operating condition of test, to corresponding operating condition
Under independent rocket sledge carry out numerical simulation, and rocket sledge tail flow field is analyzed, using dynamic pressure head correction coefficient ξ to test
Kinetic pressure losses difference is modified, and provides kinetic pressure losses correction formula.Meanwhile for have environment influence (such as ambient side wind effect
Cause rocket sledge wake flow difference) operating condition of test, in corresponding situation rocket sledge tackle system carry out numerical simulation, to test
Difference caused by process environment influences compares and analyzes, and influencing correction factor η using environment influences difference to the environment of test
It is modified, providing environment influences correction formula.Finally, according to the analysis influenced on unsteady influence, kinetic pressure losses, environment,
Comprehensive modification is carried out to rocket sledge tackle system experiment aerodynamic characteristic, provides comprehensive modification formula.
Processing analysis is carried out to new experimental data by the feature calculation correction formula established.Overall flow block diagram ginseng
See Fig. 1.
After adopting the above scheme, the present invention has the advantage that compared with prior art
In embodiments of the present invention, this method is applied in rocket sled coaster-drag parachute test, but this method is not only
It is limited to rocket sled coaster-drag parachute test, other all aerodynamic force carried out using rocket sledge tackle system can also be applied to
Or the test of resistance.
Testpieces calculation of aerodynamic characteristics method in rocket sledge sled test of the invention passes through unsteady modifying factor, amount
Influence of the testpieces non-stationary motion to calculation of aerodynamic characteristics value is changed.On the other hand, this calculation method has quantified rocket sledge
Influence of the breech stream kinetic pressure losses to calculation of aerodynamic characteristics value；Modifying factor can also be influenced by environment, quantify environment
Influence the influence to calculation of aerodynamic characteristics value.It is pneumatically special that this modification method can greatly improve testpieces in rocket sledge sled test
Property analysis accuracy, provides accurate refer to for the test and design of correlation test part (such as drag parachute).
Detailed description of the invention
Fig. 1 is the Aerodynamic characteristics process of testpieces in rocket sledge sled test；
Fig. 2 is variation of the unsteady influence correction factor with system acceleration；
Fig. 3 is variation of the different tests kinetic pressure losses correction factor with speed；
Fig. 4 is that varying environment crosswind influences correction factor with the variation of environment crosswind wind speed.
Specific embodiment
Further explanation is done to the present invention with specific example with reference to the accompanying drawing:
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description.Based on the embodiments of the present invention, those of ordinary skill in the art institute without making creative work
The every other embodiment obtained, shall fall within the protection scope of the present invention.
The present invention provides a kind of calculation method of aerodynamic characteristic in rocket sledge coaster test platform system test, the calculating
On the one hand method passes through steady flow field numerical simulation under comparison rocket sledge coaster test platform system test data and respective conditions
As a result, and carry out quantitative analysis, determine in rocket sledge coaster test platform system test non-stationary motion characteristic to test number
According to the influence of aeroperformance difference；On the other hand, rocket sledge coaster test platform wake flow and environmental factor (such as ambient side are calculated
Wind) to the differentia influence of test data aeroperformance.
Above-mentioned calculation method specifically includes the following steps:
Step 1 carries out the test of rocket sledge tackle system using true coaster and rocket sledge platform, and to correlation test object
Reason parameter measures, and obtains test data, analyzes aerodynamic characteristic；
Step 2 carries out numerical simulation to the rocket sledge tackle system in Steady, calculates analysis for operating condition of test
Its aerodynamic characteristic；
Step 3 carries out the test measurement data under the unsteady regime of steady numerical simulation result and actual experimental pair
Than, the unsteady influence of test is analyzed, it is poor caused by actual experimental unsteady characteristic using unsteady correction factor
It is different to be modified, provide unsteady correction formula；
Step 4 carries out numerical simulation to the independent rocket sledge coaster flow field under corresponding operating condition for operating condition of test；
Step 5 analyzes rocket sledge coaster tail flow field, using dynamic pressure head correction coefficient in test because rocket sledge is sliding
Kinetic pressure losses difference caused by vehicle is modified, and provides kinetic pressure losses correction formula；
Step 6, the operating condition of test of needle effect on environment (such as ambient side wind effect causes rocket sledge wake flow difference), to phase
Rocket sledge system in the case of answering carries out numerical simulation；
Step 7, difference caused by influencing on test process environment are compared and analyzed (such as environment crosswind difference), are used
Environment influences correction factor and is modified on the influence of the environment of test, and providing environment influences correction formula；
Step 8, according to the analysis for influencing difference on unsteady influence, kinetic pressure losses, environment, to rocket sledge tackle system
It tests aerodynamic characteristic and carries out comprehensive modification, provide comprehensive modification formula.
Step 9 carries out processing analysis to new experimental data by the calculation of aerodynamic characteristics correction formula established.
Example: the present embodiment is by going deep into rocket sledge coaster-drag parachute system mechanical characteristic and flow field characteristic
Analysis and exploration disclose the mechanism of testpieces aeroperformance difference, establish the testpieces gas suitable for Rocket sled test condition
Dynamic Calculation Methods for Performance solves engineering problem, has important practical significance.But this method is not limited only to rocket sled
Coaster-drag parachute test can also be applied to the examination of other all aerodynamic force or resistance carried out using rocket sledge tackle system
It tests.
In the test of rocket sledge coaster drag parachute, resistance coefficient is the important indicator for evaluating drag parachute characteristic.Usual resistance
The resistance coefficient of umbrella can indicate are as follows:
In formula: CDFor testpieces resistance coefficient, FSFor the drag parachute pulling force measured in rocket sledge sled test, ρ is to carry out gas
Current density, u are volume airflow speed, and A is drag parachute area of reference (generally desirable drag parachute apparent area).
And in actual tests, since there are the unsteady characteristic in flow field, environment influences and rocket sledge tail flow field dynamic pressure
The influence of loss can not accurately guide product design, therefore so that the resultant error that above-mentioned conventional method formula calculates is larger
Here drag parachute resistance coefficient is corrected, correction formula are as follows:
In formula: ε is the unsteady influence correction factor of testpieces, and η is that environment influences correction factor, and ξ is kinetic pressure losses amendment
Coefficient.Every correction factor and method are carefully stated respectively below.
1. influence of the unsteady influence to aerodynamic characteristic
Influence of the unsteady influence to aerodynamic characteristic (such as resistance coefficient), is measured with ε, is defined as 1+ ε=FD/FS.Pass through
The analysis of experiment and numeric data determines unsteady influence quantization parameter with the variation of acceleration, and usually unsteady influence is to examination
The influence for testing part correction factor can be expressed as the functional form of system acceleration, be with Taylor series expansion correlation here
Example:
ε=b0+b1a+b2a2+…+bnan
In formula, a is system acceleration, b0、b1、b2…bnFor unsteady incidence coefficient.
Under normal circumstances, first two usually be can use for engineering problem, it may be assumed that
ε=b0+b1a
For this example drag parachute umbellate form, by experiment and numerical analysis, unsteady influence quantization parameter is with acceleration
Variation as shown in Fig. 2, by least square method acquire its incidence coefficient be b0=1.15 × 10-1、b1=1.1 × 10-3, so
It is ε=1.15 × 10 for its unsteady correction factor of this example drag parachute umbellate form-1+1.1×10-3a。
2. influence of the kinetic pressure losses to aerodynamic characteristic
Influence of the kinetic pressure losses to aerodynamic characteristic (such as resistance coefficient), is quantified with ξ, is defined as 1+ ξ=FDF/FD, wherein
FDFIndicate the aerodynamic drag of drag parachute under no ambient wind velocity, permanent, drag parachute be symmetrical and far field boundary operating condition；FDIndicate no environment
Under wind and Steady in rocket sledge-drag parachute system Field Flow Numerical Simulation drag parachute aerodynamic drag.Pass through experiment and numerical value
Data analysis, determines kinetic pressure losses correction factor ξ with the variation of system motion speed, equally establishes kinetic pressure losses and hinders drag parachute
The correlation of the influence of force coefficient:
ξ=c0+c1u+c2u2+…+cnun
In formula, u is stream air wind speed, c0、c1、c2…cnFor kinetic pressure losses incidence coefficient.
Under normal circumstances, first two are usually taken for engineering problem, it may be assumed that
ξ=c0+c1u
To this example drag parachute umbellate form, by experiment and numerical analysis, kinetic pressure losses quantization parameter ξ is with movement velocity
Variation relation is as shown in figure 3, determine that its incidence coefficient is c by least square method0=1.02 × 10-2、c1=6.03 × 10-4,
So being ξ=1.02 × 10 for this example drag parachute umbellate form kinetic pressure losses correction factor-2+6.03×10-4u。
3. influence of the environmental factor to aerodynamic characteristic
Influence for environmental factor to aerodynamic characteristic (such as resistance coefficient) is divided by taking environment crosswind factor as an example here
Analysis.Influence of the environment crosswind to resistance coefficient, is measured with η, is defined as 1+ η=FD2/FD.Wherein FD2Indicate no environment crosswind,
The aerodynamic drag of drag parachute, F under SteadyDIndicate the aerodynamic drag of drag parachute under environment crosswind, Steady.Pass through experiment
And numerical analysis, determine that influence coefficient η of the environmental factor to aerodynamic characteristic with the variation of environment crosswind wind speed, establishes environment crosswind
Influence correlation of the situation to drag parachute resistance coefficient:
In formula, ucwFor environment crosswind wind speed, d0、d1、d2…dnFor environment crosswind incidence coefficient.
Under normal circumstances, first two are usually taken for engineering problem, it may be assumed that
η=d0+d1ucw
For this example drag parachute umbellate form, respectively to environment crosswind size be 3.2m/s, 1.4m/s and 0.7m/s the case where
Experiment and numerical simulation analysis are carried out, crosswind influences coefficient with the variation of crosswind wind speed as shown in figure 4, passing through least square
Method, acquiring related incidence coefficient is d0=3.5 × 10-3、d1=5 × 10-3, so, for this example drag parachute umbellate form, environment
It is η=3.5 × 10 that crosswind, which influences correction factor,-3+5×10-3ucw。
4. rocket sledge drag parachute tests aerodynamic characteristic comprehensive correction method
In conclusion comprehensively considering the unsteady characteristic in flow field, environment influence and rocket sledge tail flow field kinetic pressure losses
It influences, testpieces aerodynamic characteristic (such as resistance coefficient) amendment correlation can indicate are as follows:
In formula: CDFor testpieces Aerodynamic Coefficient, FSPulling force for the testpieces measured in rocket sledge sled test, ρ is incoming flow
Current density, u are volume airflow speed, and A is testpieces area of reference (generally can use its apparent area for drag parachute), and ε is
The unsteady influence correction factor of testpieces, η are that environment influences correction factor, and ξ is kinetic pressure losses correction factor, and a is system acceleration
Degree, b0、b1For unsteady incidence coefficient, u is stream air wind speed, c0、c1For kinetic pressure losses incidence coefficient, ucwFor ambient wind velocity,
d0、d1For ambient wind velocity incidence coefficient.
For this example, correction factor takes ε=1.15 × 10 respectively-1+1.1×10-3A, η=3.5 × 10-3+5×10- 3ucw, ξ=1.02 × 10-2+6.03×10-4u。
Thinking and method of the invention, there are many method and the approach for implementing the technical solution, and the above is only the present invention
Preferred embodiment, it is noted that for those skilled in the art, do not departing from the principle of the invention
Under the premise of, several improvements and modifications can also be made, these modifications and embellishments should also be considered as the scope of protection of the present invention.This implementation
The available prior art of each component part being not known in example is realized.
Claims (5)
1. the calculation method of aerodynamic characteristic in a kind of rocket sledge tackle system test, which is characterized in that the calculation method, a side
Face carries out quantization point by steady flow field numerical simulation result under comparison rocket sledge tackle system test data and experimental condition
Analysis determines the influence that non-stationary motion characteristic calculates test data aeroperformance in the test of rocket sledge tackle system；Another party
Face calculates influence of the rocket sledge coaster wake flow to test data aeroperformance calculated result.
2. the calculation method of aerodynamic characteristic, feature exist in a kind of rocket sledge sled test system according to claim 1
In, the calculation method specifically includes the following steps:
Step 1 carries out the test of rocket sledge tackle system using true coaster and rocket sledge platform, and joins to correlation test physics
Number measures, and obtains test data, analyzes aerodynamic characteristic；
Step 2 carries out numerical simulation to the rocket sledge tackle system in Steady, calculates and analyze its gas for operating condition of test
Dynamic characteristic；
Step 3 compares the test measurement data under the unsteady regime of steady numerical simulation result and actual experimental,
The unsteady influence of test is analyzed, using unsteady correction factor ε difference caused by actual experimental unsteady characteristic
It is modified, provides unsteady correction formula；
Step 4 carries out numerical simulation to the independent rocket sledge coaster flow field under corresponding operating condition for operating condition of test；
Step 5 analyzes rocket sledge coaster tail flow field, using dynamic pressure head correction coefficient ξ in test because rocket sledge coaster draws
The kinetic pressure losses difference risen is modified, and provides kinetic pressure losses correction formula；
Step 6, the operating condition of test of needle effect on environment carry out numerical simulation to the rocket sledge system in corresponding situation；
Step 7, difference caused by influencing on test process environment compares and analyzes (such as environment crosswind difference), using environment
It influences correction factor η to be modified the influence of the environment of test, providing environment influences correction formula；
Step 8 tests rocket sledge tackle system according to the analysis for influencing difference on unsteady influence, kinetic pressure losses, environment
Aerodynamic characteristic carries out comprehensive modification, provides comprehensive modification formula.
Step 9 carries out processing analysis to new experimental data by the calculation of aerodynamic characteristics correction formula established.
3. the calculation method of aerodynamic characteristic, feature exist in a kind of rocket sledge sled test system according to claim 2
In:
The unsteady influence correction factor is indicated using ε, is defined as 1+ ε=FD/FS, wherein FDIndicate fire under Steady
The aerodynamic force of testpieces, F in arrow sledge sled testSFor the pulling force of testpieces in unsteady test, unsteady influence correction factor ε
It can be expressed as functional form, such as multinomial: ε=b0+b1a+b2a2+…+bnan, wherein a is system acceleration, b0、b1、
b2…bnFor unsteady incidence coefficient；
The kinetic pressure losses correction factor is quantified with ξ, is defined as 1+ ξ=FDF/FD, wherein FDFIndicate permanent, far field boundary work
The aerodynamic force of testpieces under condition；FDIndicate that the aerodynamic force of testpieces under Steady, kinetic pressure losses correction factor ξ can be expressed as
Functional form, such as multinomial: ξ=c0+c1u+c2u2+…+cnun, wherein u is stream air speed, c0、c1、c2…cnIt is
Crushing loses incidence coefficient；
The environment is influenced correction factor and is measured using η, and 1+ η=F is defined asD2/FD, wherein FD2Indicate permanent, without ambient wind
The aerodynamic force of testpieces, F under the conditions of speedDIndicate the aerodynamic force of testpieces under Steady, environment influences correction factor η can be with table
It is shown as functional form, such as multinomial:Wherein, ucwFor ambient wind velocity, d0、d1、
d2…dnFor ambient wind velocity incidence coefficient.
4. the calculation method of testpieces aerodynamic characteristic in a kind of rocket sledge sled test system according to claim 2,
It is characterized in that,
Aerodynamic characteristic (such as resistance coefficient) calculation formula
Wherein, ε is unsteady influence correction factor, and ξ is kinetic pressure losses correction factor, and η is that environment influences correction factor, and ρ is next
Gas volume density, u are speed of incoming flow, and A is the apparent area of testpieces, FSFor the testpieces that is measured in rocket sledge sled test
Pulling force.
5. the calculation method of aerodynamic characteristic in a kind of rocket sledge sled test system according to any one of claims 1 to 4,
It is characterized in that, the method is applied to rocket sledge coaster-drag parachute pilot system or the other test platforms of rocket sledge coaster
System, the testpieces are drag parachute system or other test examining systems.
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| CN110472935B (en) * | 2019-07-31 | 2022-12-13 | 武汉科技大学 | Method for acquiring LCA environmental impact factors of solid rocket cabin section based on Internet of things |
| CN110702364A (en) * | 2019-10-22 | 2020-01-17 | 西北工业大学 | High-altitude propeller wind tunnel test data correction method aiming at propeller tip Mach number influence |
| CN110702364B (en) * | 2019-10-22 | 2020-06-30 | 西北工业大学 | High-altitude propeller wind tunnel test data correction method aiming at propeller tip Mach number influence |
| CN112199635A (en) * | 2020-10-17 | 2021-01-08 | 中国人民解放军63876部队 | Rocket sled movement trajectory calculation correction method |
| CN112199635B (en) * | 2020-10-17 | 2024-03-29 | 中国人民解放军63876部队 | Rocket sled movement trajectory calculation correction method |
| CN115618501A (en) * | 2022-12-03 | 2023-01-17 | 北京宇航系统工程研究所 | Sub-span aerodynamic characteristic acquisition method, system and device based on data fusion correction |
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