CN107182259B - The test method of overload is combined in a kind of ground simulation in the air - Google Patents
The test method of overload is combined in a kind of ground simulation in the airInfo
- Publication number
- CN107182259B CN107182259B CN201010052032.8A CN201010052032A CN107182259B CN 107182259 B CN107182259 B CN 107182259B CN 201010052032 A CN201010052032 A CN 201010052032A CN 107182259 B CN107182259 B CN 107182259B
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- CN
- China
- Prior art keywords
- overload
- test
- engine
- test engine
- motion
- Prior art date
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Links
- 238000004088 simulation Methods 0.000 title claims abstract description 17
- 238000010998 test method Methods 0.000 title claims abstract description 13
- 238000000034 method Methods 0.000 claims abstract description 7
- 230000001133 acceleration Effects 0.000 abstract description 11
- 238000009413 insulation Methods 0.000 abstract description 9
- 230000001141 propulsive Effects 0.000 abstract description 6
- 238000000354 decomposition reaction Methods 0.000 abstract description 3
- 238000005259 measurement Methods 0.000 abstract description 2
- 239000002245 particle Substances 0.000 description 9
- 238000002679 ablation Methods 0.000 description 6
- 230000003628 erosive Effects 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000009421 internal insulation Methods 0.000 description 2
- 238000003786 synthesis reaction Methods 0.000 description 2
- 230000002194 synthesizing Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000875 corresponding Effects 0.000 description 1
- 230000000593 degrading Effects 0.000 description 1
- 238000009114 investigational therapy Methods 0.000 description 1
- 230000035800 maturation Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000005514 two-phase flow Effects 0.000 description 1
Abstract
The present invention is the test method that overload is combined in a kind of ground simulation in the air, this test method is to utilize acceleration decomposition principle, the combination overload undergone in the air in ground simulation engine, test engine is fixed on a mounting bracket, mounting bracket is fixed in rocket sledge, rocket sledge is promoted along guide rail high-speed motion by boost motor, α is kept at an angle between the axial direction of test engine and the direction of motion of rocket sledge, in motion process, test engine is lighted a fire, so as to simulate the combination overload that test engine is subject to, the axial load factor n ' vertically that test engine is subject in measurement motion processxWith the normal g-load n ' perpendicular to axial directiony；Compared with prior art, the inventive method can more be coincide the aerial experimental condition truly overloaded, and the heat insulation layer thickness needed for missile propulsive plant under aerial overload condition is reasonably determined.
Description
Technical field
The present invention is the test method that overload is combined in a kind of ground simulation in the air, category
In field of measuring technique.
Background technology
Lock on requires that air-to-air missile has good mobility.Guided missile
Mobility is better, it is desirable to which the ability that guided missile bears motor-driven overload is stronger, but higher
Normal g-load can have a strong impact on the condensed-phase Particles Moving rule in missile propulsive plant,
Particle is caused to be assembled in high local concentrations.Due to high consistency two phase flow erosion and
Heat and mass is acted on, and larger shadow can be produced to missile propulsive plant burning and interior flowing
Ring, be especially degrading the working environment of heat insulation layer, while investigation on thermal protection for nozzle layer also can
Motor body or jet pipe is caused to burn by serious erosion, when serious, so that
Guided missile Development Schedule is influenceed, therefore to be born in the checking missile propulsive plant course of work
The ability of overload, rationally determines heat insulation layer thickness, except the corresponding theory analysis of progress
Calculate outer, should also overload simulated test facility by ground is examined, to ensure
Security reliability during flight.
Fig. 1 is the motor-driven overload lower stress sketch of guided missile, it can be seen that guided missile
Engine receives the influence of axial load factor and normal g-load simultaneously when motor-driven.
Domestic existing engine overload experiment is enterprising in rotation test bay
OK, as shown in Fig. 2 utilizing centrifugal motion principle, the work of main analog engine
During normal g-load, study it to propellant combustion and the influence of thermal protection.
When aerial normal g-load is simulated with centripetal acceleration, sent out during fixed-axis rotation
Gas particle is necessarily influenceed by Corioli's acceleration in motivation, Corioli's acceleration
Occur be derived from kinematics effect generation, but in rotating overload test it to examination
The influence for issuing after examination and approval motivation is very real.Because stream is strong three-dimensional flow in engine
It is dynamic, especially show particularly evident in rotation test, and also particle is in engine
The direction of motion and speed differ, and suffered Corioli's acceleration is also different, and Ge Shi adds
Speed make it that particle distribution is with differing larger in rotation test under state of flight, it is impossible to
The true distribution situation for reflecting particle in engine under flight overload, causes examination
Test rear engine insulation erosion degree and ablation position with live flying state
Also there is larger difference, and be difficult with unified method to eliminate or correct brother
Family name's acceleration moves the extra error brought, therefore the test method to rotating particle
Obtained result can not be provided for the design of engine thermal guard system and accurately set
Count foundation.
The country has research institution to devise a kind of high concentrations of particles stream of can producing
Convergence-broken pipe experimental rig, is mainly used in research high concentrations of particles stream to heat insulation layer
Ablation rule, be suitable for study mechanism, it is unable to simulated missile engine in mistake
Synthesis flow field in the case of load, therefore cannot also reflect that overload is sent out live flying
The ablation influence degree of motivation heat insulation layer.
The content of the invention
The present invention is exactly designed and provided for the deficiencies in the prior art
The test method of overload is combined in a kind of ground simulation in the air, and the purpose is to pass through ground
The combination overload that the simulated engine course of work undergoes in the air, research combination overload
To the combined influence of engine insulation erosion, rationally determine under aerial overload condition
Heat insulation layer thickness needed for missile propulsive plant.
The purpose of the present invention is achieved through the following technical solutions：
The test method of overload is combined in this kind of ground simulation in the air, and its feature exists
In：This test method is to utilize acceleration decomposition principle, in ground simulation engine
The combination overload undergone in the air, a mounting bracket is fixed on by test engine
On, mounting bracket is fixed in rocket sledge, and rocket sledge promotes high along guide rail by boost motor
Speed motion, one is kept between the axial direction of test engine and the direction of motion of rocket sledge
Fixed angle [alpha], in motion process, test engine is lighted a fire, so that mould
Intend testing in the combination overload that test engine is subject to, measurement motion process and started
The axial load factor n ' vertically that machine is subject toxWith the normal g-load perpendicular to axial direction
n′y；
Test engine (4) when mounted with direction of motion angulation α according to
Below equation is determined：
In formula：
α is angle of the test engine (4) axially with rocket sledge (2) direction of motion；
N is the motion overload of rocket sledge, and span is 50~100；
nxTo need simulation, the axial mistake vertically that test engine (4) is subject to
Carry；
nyTo need the method perpendicular to axial direction simulate, that test engine (4) is subject to
To overload.
According to the resistance of rocket sledge, the thrust and test engine of test engine
Vertically and horizontally overload, can be with by different operating time and the booster assembly of thrust
Calculate the boost motor parameter index needed for determination.According to test engine vertically and horizontally mistake
Numerical value is carried, setting angle of the engine in rocket sledge is determined, if necessary in examination
Middle progress overload change is tested, carry equipment by sledge rotates to provide auxiliary by spreadsheet engine
Equipment, the change at missile attitude angle is carried out by rotating machinery, wherein vertically and horizontally mistake
The synthesis of load is the overload of rocket skid body.
Rocket sledge simulation overload values can reach 50~100, air-to-air missile engine
The general work time is less than 10s, and overload is less than 70.Overloading larger situation
Under, test engine different operating time phase can be divided, progress about 2~
3 hair experiment, by with fast cookof rear engine internal insulation ablation pair
Than, you can the ablation situation of internal insulation under overload condition is obtained completely.
This combination overload test method is realized using the translational motion of rocket sledge,
There is no rotary motion, thus the transfer problem without coordinate system, just fundamentally yet
The influence of Corioli's acceleration is avoided, so as to more accurate simulation overload to thermal insulation
The affecting laws of layer ablation, the design for missile propulsive plant thermal protection shield is provided accurately
Foundation.
The advantage of the test method be can once test in and meanwhile simulate axially and
Normal direction combination overload, and completely avoid shadow of the Corioli's acceleration to overload simulation
Ring, simulation effect is consistent with time of day.
Brief description of the drawings
Fig. 1 is the motor-driven overload lower stress sketch of guided missile
Fig. 2 is existing rotating overload test schematic diagram
Fig. 3 is the combination overload test schematic diagram of the inventive method
Embodiment
Technical solution of the present invention is made further below with reference to drawings and examples
It is described in detail：
Referring to shown in accompanying drawing 3, the experiment side of overload is combined in this kind of ground simulation in the air
Method, it is characterised in that：This method is that test engine 4 is fixed on into an installation
On frame 3, mounting bracket 3 is fixed in rocket sledge 2, and rocket sledge 2 is pushed away by boost motor
Move along the high-speed motion of guide rail 1, the axial direction of test engine 4 and the fortune of rocket sledge 2
α is kept at an angle between dynamic direction, in motion process, test is sent out
Motivation 4 is lighted a fire, and measures the axial load factor vertically that test engine 4 is subject to
n′xWith the normal g-load n ' perpendicular to axial directiony；
Test engine 4 is when mounted with direction of motion angulation α according to following
Formula is determined：
In formula：
α is angle of the test engine 4 axially with the direction of motion of rocket sledge 2；
N is the motion overload of rocket sledge, and span is 50~100；
nxTo need simulation, the axial mistake vertically that test engine 4 is subject to
Carry；
nyTo need the method perpendicular to axial direction simulate, that test engine 4 is subject to
To overload.
By actual tests, the test method make use of maturation rocket sledge technology and
Acceleration decomposition principle, by with the angled installation engine of the direction of motion,
The combination that simulated engine undergoes in the air after the acceleration of rocket sledge is decomposed
Carry, it is technically feasible.
Compared with prior art, although experiment is required to consume a certain amount of fire every time
Arrow sledge booster, compared with rotating overload test, Rocket sled test expense
Slightly show costliness, but the aerial experimental condition truly overloaded that can more be coincide,
For aerial program control bullet experiment, comprehensive economy is preferable.
Claims (1)
1. the test method of overload is combined in a kind of ground simulation in the air, its feature exists
In：This method is that test engine (4) is fixed on a mounting bracket (3), peace
Shelve (3) to be fixed in rocket sledge (2), rocket sledge (2) promotes edge to lead by boost motor
Rail (1) high-speed motion, the axial direction of test engine (4) and the motion of rocket sledge (2)
α is kept at an angle between direction, in motion process, test is started
Machine (4) is lighted a fire, and measures the axial load factor vertically that test engine (4) is subject to
n′xWith the normal g-load n ' perpendicular to axial directiony；
Test engine (4) when mounted with direction of motion angulation α according to
Below equation is determined：
<mrow>
<mi>n</mi>
<mo>=</mo>
<msqrt>
<mrow>
<msubsup>
<mi>n</mi>
<mi>x</mi>
<mn>2</mn>
</msubsup>
<mo>+</mo>
<msubsup>
<mi>n</mi>
<mi>y</mi>
<mn>2</mn>
</msubsup>
</mrow>
</msqrt>
</mrow>
In formula：
α is folder of the test engine (4) axially with rocket sledge (2) direction of motion
Angle；
N is the motion overload of rocket sledge, and span is 50~100；
nxTo need simulation, the axial direction vertically that test engine (4) is subject to
Overload；
nyTo need, simulating, test engine (4) is subject to perpendicular to axial direction
Normal g-load.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107182259B true CN107182259B (en) | 2013-12-18 |
Family
ID=
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109252982A (en) * | 2018-11-19 | 2019-01-22 | 北京理工大学 | The test method that solid propellant rocket nonlinear instability burns under overload condition |
| CN109108857B (en) * | 2018-09-29 | 2023-09-05 | 中国空空导弹研究院 | Wireless transmission device environment test fixture |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109108857B (en) * | 2018-09-29 | 2023-09-05 | 中国空空导弹研究院 | Wireless transmission device environment test fixture |
| CN109252982A (en) * | 2018-11-19 | 2019-01-22 | 北京理工大学 | The test method that solid propellant rocket nonlinear instability burns under overload condition |
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| GR03 | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted |