CN109252982A - The test method that solid propellant rocket nonlinear instability burns under overload condition - Google Patents
The test method that solid propellant rocket nonlinear instability burns under overload condition Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
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Abstract
The test method that solid propellant rocket nonlinear instability burns under overload condition disclosed by the invention, belongs to solid propellant rocket rough burning field.The present invention increases overload condition on the basis of the static instability combustion test of solid propellant rocket ground；Solid propellant rocket is installed in the high overload test device of ground, the overload angle, θ and rotational speed omega of high overload test device are adjusted, makes solid propellant rocket that there is the acceleration of different directions, size, so that work is under different overload conditions；After ignition operation, it is mounted on the pulse trigger at end socket and generates pulse, the combustion instability phenomenon of solid propellant rocket is triggered, while the combustion state of solid propellant rocket is observed and recorded by standard inner trajectory pressure sensor, high frequency response pressure sensor；By changing test variable, the coupling between other test variables is overloaded in analysis, realizes the nonlinear instability combustion test to solid propellant rocket in an overload condition.
Description
Technical field
The present invention relates to the test methods that solid propellant rocket nonlinear instability under overload condition burns, and belong to solid
Rocket engine rough burning field.
Background technique
With the continuous development of missile armament and missile propellant technology, the demands such as high thrust, Far Range are constantly proposed, more
Carry out more high-energy propellants applied in solid propellant rocket (SRM).Since high energy composite propellant easily causes to burn
Instability problem, gently then causes inner trajectory curve abnormality, heavy then solid propellant rocket is caused to explode, therefore composite propellant is not
The theory for stablizing burning has been a hot spot of research.Wherein the specific mechanism of nonlinear instability burning even lacks authoritative mould
Type, theoretical research is still at an early stage, and solve nonlinear instability burning has extremely urgent demand in engineering.
At the same time, with the development in low latitude and air-to-air missile, the mobility of guided missile has higher requirement, this but also
SRM will work in bigger transverse direction and axial load factor operating condition.Acceleration field under overload condition combustion process can be generated compared with
It is big to influence, therefore high overload operating condition can be such that the combustion position of propellant becomes more complicated, while solid-rocket can be caused to start
The rough burning of machine causes solid propellant rocket operation irregularity, or even scraps.Since the burning of SRM under overload condition relates to
And the physics and chemical process of numerous complicated, and can with the factor coupling of other influences rough burning, therefore cross carrier strip
Part is the emphasis and difficult point of current solid propellant rocket research to the influence problem that solid propellant rocket burns.
At the end of the 20th century, linear and nonlinear instability combustion problem, USN's Air Warfare Center (Naval Air
Warfare Center) professor Blomshield the solid propellant rocket to work under the static conditions of ground has been carried out largely
Test, detailed test influence of each factor to rough burning.People have carried out a large number of experiments for rough burning, obtain
The affecting laws of each factor are arrived, but the test of most of rough burning only carries out under the static conditions of ground at present,
The influence of high overload condition suffered by solid propellant rocket under actual state is not considered.Since overload condition is to solid-rocket
The course of work and rough burning phenomenon of engine have large effect effect, therefore existing conclusion (of pressure testing) can not be complete
It is suitable for solid propellant rocket of the work under real working condition entirely.Influence for overload to combustion process, foreign study person
There is relatively deep understanding for the combustion law of solid propellant under overload condition, if Glick is in Thiokol
Carry out a large number of experiments under the subsidy of Chemical Corporation, summarizes overload to propulsion with Experimental Comparison by theoretical
The influence of agent burn rate, but the coupling between undeclared overload and rough burning；And it is domestic a large amount of still in needing to pass through
The conceptual phase of influence of the Test Summary overload to burning, for the rough burning of solid propellant rocket in an overload condition
Mechanism is even more that understanding is very few.Coupling between overload condition and the other factors for influencing nonlinear instability burning still needs
It is further to disclose.
Summary of the invention
Still incomplete in order to solve current solid propellant rocket nonlinear instability Theory of Combustion, experimental condition does not consider
Suffered overload condition influences under practical working situation, causes gained rule larger with real working condition gap, and overload condition and
The not yet clear problem of the coupling of rough burning, it is an object of the present invention to provide a kind of solid propellant rockets in ground height
The test method of nonlinear instability burning under overload condition.The operating condition that the present invention can test includes: (1) solid-rocket hair
Motivation in an overload condition, the test of the internal ballistics attributes of rough burning is caused by pulse-triggered；(2) by adjusting high overload
The overload angle of test device obtains different overload conditions from revolving speed, carries out the test under different overload conditions；(3) by changing
Become test variable, carry out solid propellant rocket different overload conditions, operating pressure, propellant Types of Medicine, stability additive,
Nonlinear instability combustion test under conditions of solid propellant rocket length and pulse strength.Pass through the survey to above-mentioned operating condition
Examination, complicated overload of the simulation solid propellant rocket in practical high altitude operation, turning, analyzes complicated overload to non-
The coupling between influence and overload and nonlinear instability combustion effects factor that linear rough burning generates, in turn
Solve the problems, such as correlation engineering.
The purpose of the present invention is what is be achieved through the following technical solutions.
The test method that solid propellant rocket nonlinear instability burns under overload condition disclosed by the invention, in solid
Increase overload condition on the basis of the static instability combustion test of rocket engine ground, the overload condition includes overload angle
θ, overloading acceleration a.By the way that solid propellant rocket is installed in the high overload test device of ground, adjustment high overload test dress
The overload angle, θ and rotational speed omega set make solid propellant rocket have the acceleration of different directions, size, so that work is not
Under same overload condition.After solid propellant rocket ignition operation, it is mounted on the pulse trigger at end socket and generates pulse, touching
The combustion instability phenomenon of solid propellant rocket is sent out, while being passed by standard inner trajectory pressure sensor, high frequency response pressure
Sensor is observed and is recorded to the combustion state in solid propellant rocket.Test variable include overload condition, operating pressure,
Propellant Types of Medicine, stability additive, solid propellant rocket length and pulse strength, by changing above-mentioned test variable item
Part, analysis overload other test variables between coupling, realize to solid propellant rocket in an overload condition non-thread
Property rough burning test.By the test to above-mentioned operating condition, solid propellant rocket is simulated in practical high altitude operation, turning
Complicated overload, analyze influence that complicated overload generates nonlinear instability burning and overload with it is non-linear not
Stablize the coupling between combustion effects factor, and then solves the problems, such as correlation engineering.
Preferably, the ground high overload test device is mainly led by multi-angle measuring device, carrying axle, rotation
Axis, great cantilever, variable-frequency motor, commutator composition.Rotation main shaft is connected by shaft coupling with the output shaft of commutator, has angle speed
The axial rotation that degree is ω, for driving great cantilever to carry out axial rotation.Great cantilever two sides be multi-angle measuring device, mainly by
Link block, connecting rod, fixing piece composition, are installed for realizing the multi-angle of solid propellant rocket.Connecting rod respectively with connection
Block, fixing piece are connected, and length can be adjusted.Fixing piece is for being fixedly mounted solid propellant rocket, and one end is fixed, the other end
It is connected with connecting rod.When connecting pole length change, fixing piece can be rotated along fixing end.Measurand solid propellant rocket is solid
It is scheduled on fixing piece, in test, changes connection pole length, so that the angle between fixing piece axis and testing stand horizontal line is not in
With overload angle, θ, to realize multi-angle overload installation of the ground high overload test device to solid propellant rocket.Pass through tune
Whole variable-frequency motor rotational speed omega drives to solid propellant rocket through transmission main shaft, great cantilever, makes to be fixed on multi-angle measuring device
On solid propellant rocket obtain different size of centrifugal acceleration a, to obtain different overloading accelerations, realize to solid
Test of the body rocket engine under different overload conditions.The overload condition includes overload angle, θ, overloading acceleration a.
Preferably, obtaining different overload angles by adjusting the angle theta between fixing piece axis and testing stand horizontal line
θ, while variable-frequency motor rotational speed omega is adjusted, finally obtain different size of overload condition: solid propellant rocket mass center to shaft
Axle center distance is L, at this time centrifugal acceleration a suffered by solid propellant rocket are as follows: a=L ω2.By solid propellant rocket institute
By acceleration of gravity compared with centrifugal acceleration very little, therefore can ignore that.Face somewhere, acceleration a and combustion face folder are fired in propellant
Angle is θ, is 90 ° of-θ with combustion face normal direction angle.Therefore, face normal acceleration a is firedn=acos (90 ° of-θ)=L ω2sinθ；
Combustion face tangential acceleration an=acos θ=L ω2cosθ.Therefore, by adjusting adjustment variable-frequency motor rotational speed omega and connector shaft to
Angle theta between horizontal line obtains different overload conditions, realizes non-under different overload conditions to solid propellant rocket
The test of linear rough burning performance.
Preferably, the rough burning of the solid propellant rocket is by pulse-triggered.The pulse being mounted at end socket
Trigger generates pulse, and pulse number is selected as three times.
Preferably, the influence that pressure burns to nonlinear instability when having overload for test, it will be to solid during test
The operating pressure of body rocket engine is adjusted；Influence of the stability additive to rough burning when having overload to test,
Part propellant is replaced with different stability additives, and carries out Experimental Comparison.Propellant Types of Medicine when having overload for test
Influence to combustion state, solid propellant rocket select different Types of Medicine to be tested.Solid-rocket is sent out when having overload for test
The influence of motivation length or frequency of oscillation to combustion state, selects the solid propellant rocket of different length to be tested.
The test method that solid propellant rocket nonlinear instability burns under overload condition, optimization test method include such as
Lower step:
Step 1: before on-test, debugging solid propellant rocket end-sealing device, and whether test line is intact,
Sensor whether reasonable installation, can work normally.
Step 2: determining test variable according to test requirements document, selects suitable propellant Types of Medicine, combustion chamber pressure, solid
Rocket engine length and propellant formulation.
Step 3: it is overloaded according to test and requires to determine solid propellant rocket overload angle, θ and device rotary speed ω.By solid
Rocket engine is installed in high overload test device, adjusts the angle theta between connector and testing stand horizontal line, completes solid
The multi-angle installation of rocket engine ground overload.
Step 4: starting high overload test device, when turntable reaches both constant speed rotational speed omegas, solid propellant rocket into
Row igniting.Solid propellant rocket has the overload condition of test requirements document at this time.
Step 5: in 1s, 2s, 3s after solid propellant rocket work starts, impulse generator generates different three times
The pulse signal of intensity, triggering solid propellant rocket nonlinear instability burning.
Step 6: the inner trajectory for recording the solid propellant rocket course of work by standard inner trajectory pressure sensor is bent
Line.
Step 7: solid propellant rocket stops working, and closes high overload test device, removes solid propellant rocket.
Step 8: change test variable, repeat step 3 to step 7, realize that solid-rocket starts under different overload conditions
The experimental test of the nonlinear instability burning of machine.
Further include step 9: by the test to above-mentioned operating condition, simulate solid propellant rocket in practical high altitude operation, turn
Complicated overload when curved, analyze influence that complicated overload generates nonlinear instability burning and overload with it is non-thread
Coupling between property rough burning influence factor, and then solve the problems, such as correlation engineering.
The utility model has the advantages that
1, the test method that solid propellant rocket nonlinear instability burns under overload condition disclosed by the invention, passes through
Improvement to ground static instability burn test method makes solid propellant rocket work using ground high overload test device
Make while different overload conditions, causes nonlinear instability to burn by pulse-triggered, and record inner trajectory by sensor
Performance realizes solid propellant rocket in an overload condition, the solid propellant rocket of rough burning is caused by pulse-triggered
The test of internal ballistics attributes.
2, the test method that solid propellant rocket nonlinear instability burns under overload condition disclosed by the invention, passes through
The angle theta between variable-frequency motor rotational speed omega and fixing piece axis and testing stand horizontal line is adjusted, makes to be fixed on multiangular measurement dress
The solid propellant rocket set obtains different overload conditions, realizes to solid propellant rocket under different overload conditions
Test.
3, under overload condition disclosed by the invention solid propellant rocket nonlinear instability burn test method, pass through
Adjust each test variable: overload size, overload angle, propellant Types of Medicine, combustion chamber pressure, stability additive, solid fire
Arrow motor length and pulse strength, influence and overload condition that test overload condition burns to nonlinear instability and its
Coupling between his nonlinear instability combustion effects factor.
4, under overload condition disclosed by the invention solid propellant rocket nonlinear instability burn test method, pass through
Solid propellant rocket is installed on ground high overload test device by the improvement to ground static instability burn test method
On, the complicated overload faced during simulated flight, it is non-linear not that realization is more bonded actual solid propellant rocket
Stablize combustion measurement, and then solves the problems, such as correlation engineering.
Detailed description of the invention
The drawings herein are incorporated into the specification and constitutes a part in this specification, shows and meets reality of the invention
Example is applied, and is used to explain the principle of the present invention together with specification.
Fig. 1 is the burn test method of solid propellant rocket nonlinear instability under overload condition disclosed by the invention
Flow chart；
Fig. 2 is the experimental rig that solid propellant rocket nonlinear instability burns under overload condition disclosed by the invention
Figure；
Wherein: 2-1- multi-angle mounting device, 2-2- fixing piece, 2-3- connecting rod, 2-4- carrying axle, 2-5- rotation master
Axis, 2-6- commutator output shaft, 2-7- commutator, 2-8- variable-frequency motor, 2-9- link block, 2-10 are great cantilever；
Fig. 3 is the overload schematic diagram at propellant disclosed by the invention combustion face；
Fig. 4 is solid propellant rocket structure chart disclosed by the invention；
Wherein: 4-1- ignites the torch, 4-2- solid propellant rocket end socket, 4-3- shell, 4-4- propellant loading, 4-5- spray
Pipe；
Fig. 5 is special designing end socket test device installation diagram disclosed by the invention；
Wherein: 5-1- ignites the torch, 5-2,5-3,5-4- impulse generator, 5-5- standard inner trajectory pressure sensor, 5-6,
5-7- high frequency response pressure sensor, 5-8,5-9,5-10 are pulse sensor, 5-11- end socket；
Fig. 6 is overload disclosed by the invention and the inner trajectory curve signal under non-overloaded state, under the conditions of pulse-triggered
Figure.
Specific embodiment
Objects and advantages in order to better illustrate the present invention with reference to the accompanying drawing do further summary of the invention with example
Explanation.
As shown in Fig. 2, the examination that solid propellant rocket nonlinear instability burns under overload condition disclosed in the present embodiment
Proved recipe method increases overload condition on solid propellant rocket ground on the basis of static instability combustion test, described to cross carrier strip
Part includes overload angle, θ, overloading acceleration a.By the way that solid propellant rocket to be installed in the high overload test device of ground, adjust
The overload angle, θ and rotational speed omega of whole high overload test device make solid propellant rocket have the acceleration of different directions, size
Degree, so that work is under different overload conditions.After solid propellant rocket ignition operation, it is mounted on the pulse at end socket and touches
Send out device and generate pulse, trigger the combustion instability phenomenon of solid propellant rocket, at the same by standard inner trajectory pressure sensor,
High frequency response pressure sensor is observed and is recorded to the combustion state in solid propellant rocket.Test variable includes overload
Condition, operating pressure, propellant Types of Medicine, stability additive, solid propellant rocket length and pulse strength, on changing
Test variable condition, the coupling between analysis overload and other test variables are stated, solid propellant rocket is being overloaded in realization
Under the conditions of nonlinear instability combustion test.By the test to above-mentioned operating condition, solid propellant rocket is simulated in practical height
Complicated overload when idle job, turning, analyze influence that complicated overload generates nonlinear instability burning and
Coupling between overload and nonlinear instability combustion effects factor, and then solve the problems, such as correlation engineering.
The ground high overload test device by multi-angle measuring device 2-1, variable-frequency motor 2-8, commutator 2-7, turn
Dynamic main shaft 2-5, carrying axle 2-4, great cantilever 2-10 composition.Rotate the output shaft 2-6 phase that main shaft 2-5 passes through shaft coupling and commutator
Even, the axial rotation for being ω with angular speed, for driving great cantilever 2-10 to carry out axial rotation.The two sides great cantilever 2-10 are more
Angle measurement unit 2-1 is mainly made of link block 2-9, connecting rod 2-3, fixing piece 2-2, starts for realizing solid-rocket
The multi-angle of machine is installed.Connecting rod 2-3 is connected with link block 2-9, fixing piece 2-2 respectively, and length can be adjusted.Fixing piece 2-2
For solid propellant rocket to be fixedly mounted, one end is fixed, and the other end is connected with connecting rod 2-3.When connecting rod 2-3 length changes
When change, fixing piece 2-2 can be rotated along fixing end.Measurand solid propellant rocket is fixed on fixing piece 2-2, in test,
Change connecting rod 2-3 length, so that the angle between fixing piece 2-2 axis and testing stand horizontal line is in different overload angle, θs, from
And realize multi-angle overload installation of the ground high overload test device to solid propellant rocket.By adjusting variable-frequency motor 2-8
Rotational speed omega drives to solid propellant rocket through transmission main shaft 2-5, great cantilever 2-10, makes to be fixed on multi-angle measuring device 2-1
On solid propellant rocket obtain different size of centrifugal acceleration a, to obtain different overloading accelerations, realize to solid
Test of the body rocket engine under different overload conditions.The overload condition includes overload angle, θ, overloading acceleration a.
As shown in figure 3, obtaining different overloads by adjusting the angle theta between fixing piece 2-2 axis and testing stand horizontal line
Angle, θ, while variable-frequency motor 2-8 rotational speed omega is adjusted, finally obtain different size of overload condition: solid propellant rocket mass center
It is L, at this time centrifugal acceleration a suffered by solid propellant rocket to rotating shaft core distance are as follows: a=L ω2.Since solid-rocket is sent out
The very little compared with centrifugal acceleration of acceleration of gravity suffered by motivation, therefore can ignore that.Propellant fire face somewhere, acceleration a with
Combustion face angle is θ, is 90 ° of-θ with combustion face normal direction angle.Therefore, face normal acceleration a is firedn=acos (90 ° of-θ)=L ω2sinθ；Combustion face tangential acceleration an=acos θ=L ω2cosθ.Therefore, by adjusting adjustment variable-frequency motor rotational speed omega with connect
Angle theta between part axial direction and horizontal line obtains different overload conditions, realizes and crosses carrier strip different to solid propellant rocket
The test of nonlinear instability combustibility under part.
It is as shown in Figure 4 to test solid propellant rocket.In order to test influence and mistake of the overload condition to rough burning
Coupling between carrier strip part and other test variables, this test select different overload conditions, operating pressure, stability addition
Agent, propellant Types of Medicine, solid propellant rocket length and pulse strength are tested.Overload condition can be carried out by method above
Change.The influence that pressure burns to nonlinear instability when having overload to test, will be to solid propellant rocket during test
Operating pressure be adjusted.Solid propellant rocket end cap preferably uses Design of Screw Thread, substitutes the mode of locks retaining ring installation,
So that solid propellant rocket maximum is subjected to the pressure of 70MPa, bears bigger intensity, and improve the repetition of solid propellant rocket
Usability.Influence of the stability additive to rough burning when having overload to test, by the different stabilization of 1% propellant
Property additive replace, such as 8 millimeters of aluminium oxide, 90 millimeters of aluminium oxide and 3 millimeters of zirconium carbide equistability additives and are tested
Comparison.Influence of the propellant Types of Medicine to combustion state when having overload to test, solid propellant rocket select different Types of Medicine to carry out
Test, such as: star, cylinder, preceding 2/3rds are star, and rear one third is cylindrical Types of Medicine etc..Had for test
The influence of solid propellant rocket length or frequency of oscillation to combustion state when load, selects the solid propellant rocket of different length
It is tested.For example, length is first selected to be tested for 1.7m solid propellant rocket, solid propellant rocket is basic at this time
Longitudinal frequency is about 330Hz.Change solid propellant rocket length, length is used to carry out for the solid propellant rocket of 0.85m
Test, for solid propellant rocket with about 660Hz oscillation under first longitudinal direction mode, different frequencies are can be obtained in comparative test result at this time
Combustion position under rate.
As shown in figure 5, solid propellant rocket, equipped with specially designed end socket 5-11, end socket is equipped in a standard
It trajectory pressure sensor, two high frequency response pressure sensors and three impulse generators and ignites the torch, for recording inner trajectory
Variation and generation pulse signal.Concrete configuration is as follows: the 5-1 that ignites the torch is located at end socket central location；Device 5-2,5-3 and 5-4 are
Impulse generator, 1s, 2s and 3s after solid propellant rocket work generate the pulse signal of varying strength three times, mesh respectively
Be to test solid propellant rocket to the stability of acoustic perturbation.Solid propellant rocket is divided into two to the response of pulse
Class: 1) solid propellant rocket is stable after the pulse, and the sonication that pulse generates is decayed at any time, such as inner trajectory curve graph 5
In dotted line shown in；2) solid propellant rocket is acutely unstable after the pulse, as shown in solid in inner trajectory curve graph 5.
When test, different test conditions is selected solid propellant rocket, and carry out pulse touching after solid propellant rocket igniting
Hair.If generating, triggering is unstable, and each influence factor that can be burnt to solid propellant rocket nonlinear instability is surveyed
Examination；Device 5-5 is standard inner trajectory pressure sensor；Device 5-6,5-7 are respectively high frequency response pressure sensor；Device 5-8,
5-9,5-10 are pulse sensor.In addition to above-mentioned apparatus, test is also specially provided with pulse firing control channel and high frequency
The band-wise processing of pressure sensor signal.
As shown in fig. 6, left figure is the inner trajectory curve under the conditions of No-mistake Principle, right figure is to have the inner trajectory under overload condition bent
Line.Solid propellant rocket causes combustion instability under the triggering of second pulse, and the variation of p-t curve is as shown in the figure.
The test method that solid propellant rocket nonlinear instability burns under overload condition, specific test procedure are as follows:
Step 1: before on-test, debugging solid propellant rocket end-sealing device, and whether test line is intact,
Sensor whether reasonable installation, can work normally.
Step 2: determining test variable according to test requirements document, selects suitable propellant Types of Medicine, combustion chamber pressure, solid
Rocket engine length and propellant formulation.
Step 3: it is overloaded according to test and requires to determine solid propellant rocket overload angle, θ and device rotary speed ω.By solid
Rocket engine is installed in high overload test device, adjusts the angle theta between connector and testing stand horizontal line, completes solid
The multi-angle installation of rocket engine ground overload.
Step 4: starting high overload test device, when turntable reaches both constant speed revolving speeds, solid propellant rocket is carried out
Igniting.Solid propellant rocket has the high overload condition of test requirements document at this time.
Step 5: in 1s, 2s, 3s after solid propellant rocket work starts, impulse generator generates different three times
The pulse signal of intensity, triggering solid propellant rocket nonlinear instability burning.
Step 6: the inner trajectory for recording the solid propellant rocket course of work by standard inner trajectory pressure sensor is bent
Line analyzes powder charge combustion state.
Step 7: solid propellant rocket stops working, and closes high overload test device, removes solid propellant rocket.
Step 8: change test variable, repeat step 3 to step 7, realize that solid-rocket starts under different overload conditions
The experimental test of the nonlinear instability burning of machine.
Further include step 9: realizing that sunykatuib analysis solid propellant rocket is made in high-altitude by the test to above-mentioned operating condition
The influence that complicated overload when industry, turning generates nonlinear instability burning analyzes complicated overload to non-linear
The coupling between influence and overload and nonlinear instability combustion effects factor that rough burning generates, and then solve
Correlation engineering problem.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technology scope, any changes or substitutions that can be easily thought of, should all contain
Lid is within the scope of the present invention.Therefore, protection scope of the present invention should be based on the protection scope of the described claims.
Claims (7)
1. the test method that solid propellant rocket nonlinear instability burns under overload condition, it is characterised in that: in solid fire
Increasing overload condition on the basis of arrow engines ground static instability combustion test, the overload condition includes overload angle, θ,
Overloading acceleration a；By the way that solid propellant rocket to be installed in the high overload test device of ground, high overload test device is adjusted
Overload angle, θ and rotational speed omega, make solid propellant rocket have different directions, size acceleration, thus work in difference
Overload condition under；After solid propellant rocket ignition operation, be mounted on pulse trigger (5-2) at end socket (5-11),
(5-3), (5-4) generate pulse, trigger the combustion instability phenomenon of solid propellant rocket, while passing through standard inner trajectory pressure
Sensor (5-5), high frequency response pressure sensor (5-6), (5-7) observe the combustion state in solid propellant rocket
And record；Test variable includes that overload condition, operating pressure, propellant Types of Medicine, stability additive, solid propellant rocket are long
Degree and pulse strength are analyzed complicated overload and are generated to nonlinear instability burning by changing above-mentioned test variable condition
Influence and overload and nonlinear instability combustion effects factor between coupling, realization exist to solid propellant rocket
Nonlinear instability combustion test under overload condition.
2. the test method that solid propellant rocket nonlinear instability burns under overload condition as described in claim 1,
It is characterized by the test to above-mentioned operating condition, complicated mistake of the simulation solid propellant rocket in practical high altitude operation, turning
Load state analyzes influence and overload of the complicated overload to nonlinear instability burning generation and burns with nonlinear instability
Coupling between influence factor, and then solve the problems, such as correlation engineering.
3. the test method that solid propellant rocket nonlinear instability burns under overload condition as claimed in claim 1 or 2,
It is characterized by: the ground high overload test device is mainly by multi-angle measuring device (2-1), carrying axle (2-4), rotation
Main shaft (2-5), great cantilever (2-10), variable-frequency motor (2-8), commutator (2-7) composition；Rotation main shaft (2-5) passes through shaft coupling
It is connected with the output shaft (2-6) of commutator, the axial rotation for being ω with angular speed, for driving great cantilever (2-10) to carry out axis
To rotation；The great cantilever two sides (2-10) are multi-angle measuring device (2-1), mainly by link block (2-9), connecting rod (2-3), solid
Determine part (2-2) composition, is installed for realizing the multi-angle of solid propellant rocket；Connecting rod (2-3) respectively with link block (2-
9), fixing piece (2-2) is connected, and length can be adjusted；Fixing piece (2-2) is for being fixedly mounted solid propellant rocket, one end
Fixed, the other end is connected with connecting rod；When connecting pole length change, fixing piece can be rotated along fixing end；Measurand solid
Rocket engine is fixed on fixing piece (2-2), in test, changes connecting rod (2-3) length, so that fixing piece (2-2) axis
Angle between testing stand horizontal line is in different overload angle, θs, to realize ground high overload test device to solid-rocket
The multi-angle of engine overloads installation；By adjusting variable-frequency motor (1-8) rotational speed omega, through transmission main shaft (2-5), great cantilever (2-
10) solid propellant rocket is driven to, obtains the solid propellant rocket being fixed on multi-angle measuring device (2-1) different
The centrifugal acceleration a of size is realized to solid propellant rocket to obtain different overloading accelerations in different overload conditions
Under test；The overload condition includes overload angle, θ, overloading acceleration a.
4. the test method that solid propellant rocket nonlinear instability burns under overload condition as claimed in claim 1 or 2,
It is characterized by: obtaining different overload angles by adjusting the angle theta between fixing piece (2-2) axis and testing stand horizontal line
θ, while variable-frequency motor (2-8) rotational speed omega is adjusted, finally obtain different size of overload condition: solid propellant rocket mass center arrives
Rotating shaft core distance is L, at this time centrifugal acceleration a suffered by solid propellant rocket are as follows: a=L ω2；Face somewhere is fired in propellant,
Acceleration a and combustion face angle are θ, are 90 ° of-θ with combustion face normal direction angle；Therefore, face normal acceleration a is firedn=acos
(90 ° of-θ)=L ω2sinθ；Combustion face tangential acceleration an=acos θ=L ω2cosθ；Therefore, by adjusting adjustment variable-frequency motor
(2-8) rotational speed omega and connector shaft obtain different overload conditions, realize to solid-rocket to the angle theta between horizontal line
The test of engine nonlinear instability combustibility under different overload conditions.
5. the test method that solid propellant rocket nonlinear instability burns under overload condition as claimed in claim 1 or 2,
It is characterized by: the rough burning of the solid propellant rocket is by pulse-triggered；The pulse trigger being mounted at end socket
Pulse is generated, pulse number is selected as three times.
6. the test method that solid propellant rocket nonlinear instability burns under overload condition as claimed in claim 1 or 2,
It is characterized by: the influence that pressure burns to nonlinear instability when having overload for test, it will be to solid-rocket during test
The operating pressure of engine is adjusted；Influence of the stability additive to rough burning when having overload to test, by part
Propellant is replaced with different stability additives, and carries out Experimental Comparison；Propellant Types of Medicine are to burning when having overload for test
The influence of state, solid propellant rocket select different Types of Medicine to be tested；Solid propellant rocket is long when having overload for test
The influence of degree or frequency of oscillation to combustion state, selects the solid propellant rocket of different length to be tested.
7. the test method that solid propellant rocket nonlinear instability burns under overload condition as claimed in claim 1 or 2,
It is characterized by comprising following steps,
Step 1: before on-test, debugging solid propellant rocket end-sealing device, and whether test line is intact, sensing
Device whether reasonable installation, can work normally；
Step 2: determining test variable according to test requirements document, selects suitable propellant Types of Medicine, combustion chamber pressure, solid-rocket
Motor length and propellant formulation；
Step 3: it is overloaded according to test and requires to determine solid propellant rocket overload angle, θ and device rotary speed ω；By solid-rocket
Engine is installed in high overload test device, adjusts the angle theta between connector and testing stand horizontal line, completes solid-rocket
The multi-angle installation of engines ground overload；
Step 4: starting high overload test device, when turntable reaches both constant speed rotational speed omegas, solid propellant rocket is carried out a little
Fire；Solid propellant rocket has the overload condition of test requirements document at this time；
Step 5: in 1s, 2s, 3s after solid propellant rocket work starts, impulse generator generates varying strength three times
Pulse signal, triggering solid propellant rocket nonlinear instability burning；
Step 6: the inner trajectory curve of the solid propellant rocket course of work is recorded by standard inner trajectory pressure sensor；
Step 7: solid propellant rocket stops working, and closes high overload test device, removes solid propellant rocket；
Step 8: change test variable, repeat step 3 to step 7, realize solid propellant rocket under different overload conditions
The experimental test of nonlinear instability burning.
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| CN112594095A (en) * | 2020-12-07 | 2021-04-02 | 西安航天动力测控技术研究所 | Solid rocket engine real-time variable-angle centrifugal overload ignition test device |
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