CN109505712A - It is a kind of for measuring the impulse generator of solid propellant rocket combustion instability - Google Patents
It is a kind of for measuring the impulse generator of solid propellant rocket combustion instability Download PDFInfo
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- CN109505712A CN109505712A CN201910034135.2A CN201910034135A CN109505712A CN 109505712 A CN109505712 A CN 109505712A CN 201910034135 A CN201910034135 A CN 201910034135A CN 109505712 A CN109505712 A CN 109505712A
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- propellant
- pulse
- impulse generator
- clock
- cup
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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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
-
- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
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Abstract
本发明涉及一种用于测定固体火箭发动机燃烧不稳定性的脉冲发生器，属于固体火箭发动机技术领域。本发明所述脉冲发生器采用药量调节脉冲大小、推进剂控制时序、将脉冲源与推进剂整合一体安置在T型燃烧器内部的设计方式，脉冲发生器在装药时，脉冲源与推进剂整合为一体，能够通过推进剂的药量来控制脉冲激励的时序，在需要施加激励的时候直接由推进剂点燃，不需要外加点火时序控制装置。脉冲发生器可以添加不同量、不同位置的脉冲源，实现不同需求的脉冲激励，更加简单、安全和可靠。本发明容易操作，成本低廉，具有很好的效果。
The invention relates to a pulse generator for measuring the combustion instability of a solid rocket motor, and belongs to the technical field of solid rocket motors. The pulse generator of the present invention adopts the design method of adjusting the pulse size of the dose, controlling the timing of the propellant, and integrating the pulse source and the propellant inside the T-shaped burner. The propellant is integrated as a whole, and the timing of pulse excitation can be controlled by the amount of propellant. When excitation needs to be applied, the propellant is directly ignited, and no external ignition timing control device is required. The pulse generator can add pulse sources of different amounts and positions to achieve pulse excitation of different needs, which is simpler, safer and more reliable. The present invention is easy to operate, low in cost, and has good effects.
Description
Technical field
The present invention relates to a kind of for measuring the impulse generator of solid propellant rocket combustion instability, more particularly to
One kind measuring pulse generation used in solid propellant rocket rough burning coupling pressure receptance function by T-type burner
Device belongs to Solid Rocket Motor Technology field.
Background technique
With the development of space transporter technology, continuous improvement especially to high-thrust rocket demand is many
More carrier rockets use the solid propellant rocket of big L/D ratio, high filling, high-energy propellant.The common spy of such engine
Point is to be easy to generate flow instability in flow field, and engine combustion stability is constantly deteriorated with the working time, in work
Making latter stage easily there is rough burning phenomenon.Solid propellant rocket rough burning is also known as combustion instability or oscillation combustion
It burns, is one of the thorny problem that reseach of engine frequently encounters in the process, essential characteristic is chamber pressure, burn rate to start
Operatic tunes intrinsic frequency makees period or approximately periodic variation in machine.Rough burning phenomenon will cause inner trajectory curve different
Often, indoor pressure oscillation of burning is coupled with motor body, and the guidance system that will lead to rocket is interfered, if pressure is shaken
It swings amplitude persistently to increase, engine explosions can be caused when serious, are led to disastrous consequence.Traditional theoretical knowledge and engineering method
It is difficult to eliminate such in-engine rough burning phenomenon, therefore, can only be closed for composite propellant coupling pressure response etc.
Key gain mechanism carries out further investigation.
Coupling pressure receptance function, is a characteristic quantity of SOLID PROPELLANT COMBUSTION stability, and estimates solid-rocket
The important parameter of engine combustion stability.Since the 1950s, scientific research personnel is studying always burning response theory,
The mechanism of some rough burnings is gradually understood fully.But since coupling pressure receptance function is frequency, propellant component, combustion
The function of room average pressure etc. is burnt, existing theory can not accurately determine propellant pressure coupling response function, can only pass through
Data needed for test obtains.By the research of decades, the method that many measure coupling pressure receptance function now has been developed,
Middle comparative maturity and the method being widely used are T-type burner impulse methods.
Coupling pressure receptance function is measured using T-type burner impulse method, is substantially exactly to install two for T-type burner
Impulse generator.The working principle of T-type burner impulse method is, in the combustion process of test specimen and burning just at the end of, respectively
Apply pulsatile once.Since test specimen gain is less than damping, the oscillation that two subpulses are excited exponentially decays.For the first time
The attenuation constant of pulse includes the gain of combustion face and the damping of the operatic tunes, and the second subpulse contains only damping.If it is assumed that main combustion period
Damping with moment after burning be it is identical, then the gain coefficient for firing face can be calculated by the attenuation constant of two subpulses
Out.Therefore, the pulse excitation twice of impulse generator is crucial and important.
Currently, the existing and auxiliary work of T-type burner impulse generator, predominantly additional pulse-triggered motivates dress
Set, there are system complex, it is cumbersome, reliability is low the problems such as.
Summary of the invention
The purpose of the invention is to overcome the deficiencies of existing technologies, a kind of new impulse generator is proposed, for passing through T
Type burner impulse method research solid propellant rocket combustion instability phenomenon.
Impulse generator of the present invention, using dose adjust impulse magnitude, Propellant Control timing, by clock with push away
It is integrally placed in the design method of T-type burner internal into agent integration, eliminates common applying pulse triggering exciting bank system
The defect that system is complicated, reliability is low greatly simplifies overall structure.The impulse generator is in powder charge, clock and propellant
It integrates, the timing of pulse excitation can be controlled by the dose of propellant, structure is simple.The impulse generator can be with
Addition not same amount, different location clock, realize the pulse excitation of different demands, simpler, safety and reliable.This pulse
Generator is directly designed in T-type burner combustion chamber interior, is directly lighted, is not required to by propellant when needing and applying excitation
Additional igniting sequential control device is wanted, structure is simple, and it is easy to operate, it is low in cost, there is good effect.
The purpose of the present invention is what is be achieved through the following technical solutions.
It is a kind of for measuring the impulse generator of solid propellant rocket combustion instability, including propellant, clock
And clad.
Propellant and clock are wrapped by layer package, and take " propellant-arteries and veins collectively as the powder charge of impulse generator
Rush source " alternately mode is disposed, and close zero-clearance each other.
The outermost side of impulse generator is cup-shaped propellant, and rim of a cup is outward.Cup-shaped propellant selects tested rocket
Propellant plays the role of establishing first pressing in the moment of igniting, and explosive payload is according to building pressure effect and from igniting to closest arteries and veins
The time interval that impulse is encouraged determines that the time interval size of the pulse excitation is artificial by those skilled in the art according to measurement demand
Setting.
The particular number of non-outermost propellant and clock is determined according to the number of pulse required in continuous mode.
The explosive payload of each non-outermost propellant determines, the time interval is big according to the time interval of its adjacent two sides pulse excitation
Demand is manually set rootlet by those skilled in the art according to surveying and determination.The explosive payload of each clock, by pulse required in continuous mode
Size is motivated to determine that position is determined by required pulse sequence.It is achieved in pulse spacing and the multiple pulses of different time
Excitation.
The clad, it is desirable that propellant and clock outermost layer can be wrapped up tightly, it is made only to reserve cup-shaped end face,
Ensure entire powder charge cigarette burning in T-type burner.In whole installation process, the mode wrapped up in powder charge is taken, most
The end face for only reserving cup-shaped propellant eventually, accomplishes that clad sufficiently wraps up the powder charge of impulse generator.
When measurement, impulse generator is placed in one end in T-type burner.
Beneficial effect
Compared with prior art, the present invention has following characteristics:
(1) this impulse generator is clock and propellant entirety powder charge, is integrally designed, and structure is simple；
(2) this impulse generator is directly positioned in T-type burner, does not need additional igniting sequential control device, system
Simply, reliability is high；
(3) this impulse generator can adjust powder charge according to different pulse excitation demands, and control is simple；
(4) it fabricates at low cost；
(5) easy to operate, it is easy to maintain.
Detailed description of the invention
Fig. 1 is 1/4 cross-sectional view of impulse generator isometric in specific embodiment；
Fig. 2 is impulse generator main sectional view in specific embodiment；
Fig. 3 is impulse generator side view in specific embodiment；
Fig. 4 is the general system diagram of T-type burner impulse method in specific embodiment；
Fig. 5 is that the powder charge and pressure in specific embodiment in impulse generator combustion process respond corresponding diagram；
Wherein, 1- cup-shaped propellant, 2- first time clock, 3- column propellant, second of clock of 4-, 5- cladding
Layer, 6- igniter pad, 7- pressure sensor, 8- no pulse source cup-shaped propellant, 9- Iganition control system, 10- data acquisition system
System, 11- power-supply system, 12-T type burner, 13- computer, 14- ignition lead.
Specific embodiment
Below with reference to figure, invention is further described in detail with specific embodiment.
Embodiment
It is a kind of for measuring the impulse generator of solid propellant rocket combustion instability, comprising: cup-shaped propellant 1,
First time clock 2, column propellant 3, second of clock 4 and clad 5, structure composition is as shown in Figure 1.
Cup-shaped propellant 1, first time clock 2, column propellant 3 and second of clock 4, collectively as pulse generation
The powder charge of device, and it is wrapped by the package of layer 5.Propellant and clock require whole powder charge, so that it is guaranteed that combustion process it is continuous, can
It leans on.
Wherein, second of clock 4 is placed in the inner terminal (that is, bottom of impulse generator) of clad 5.At second
The outer end of clock 4 successively disposes column propellant 3, first time clock 2 and cup-shaped propellant 1, and close nothing each other
Gap.As shown in Figure 2.In instrumentation, by 5 gradual perfection of clad, that is, wrapped up in powder charge, finally only reserve cup-shaped and push away
Into the cup-shaped end face of agent 1, accomplish the powder charge of the sufficiently package impulse generator of clad 5, it is therefore an objective to ensure the combustion process of powder charge
Only occur in the end face of impulse generator.The outermost end of impulse generator is that the propellant at igniting, at this is cup-shaped propellant
1, play the role of establishing first pressing in the moment of igniting.
The cup-shaped propellant 1 selects tested propellant, and explosive payload is according to building pressure effect and from lighting a fire to the
The time interval of pulsatile once excitation determines that the time interval of the pulse excitation is by being manually set.
The first time clock 2, the preferred black powder of powder charge and pyrotechnic compound (such as BPN) can be packed using medicine box.Dress
Dose is determined according to impulse magnitude needed for measuring.Wherein, the ratio of black powder and pyrotechnic compound, it is desirable that can be within the scope of Millisecond
All burnt, and the effect of coincidence pulse excitation.The position of clock is determined by the timing of required pulse excitation.
The column propellant 3 selects tested propellant, and explosive payload is according to first time pulse excitation and second
The time interval of pulse excitation determines.
Black powder and pyrotechnic compound are preferably selected in second of clock 4, powder charge, can be packed using medicine box.Powder charge
Amount is determined by required impulse magnitude.Wherein, the ratio of black powder and pyrotechnic compound, it is desirable that can be burnt down in Millisecond range internal combustion
Finish, and the effect of coincidence pulse excitation.The position of clock is determined by the timing of required pulse excitation.
" propellant-clock " can be taken to hand over according to the pulse number needs in continuous mode, in impulse generator
For mode, multiple propellants and clock are disposed.The particular number of non-outermost propellant and clock, according to continuous mode
In required pulse number determine.The explosive payload of each non-outermost propellant, according to the time of its adjacent two sides pulse excitation
Interval determines that the time interval is by being manually set.The explosive payload of each clock, it is true by pulse excitation size required in continuous mode
Fixed, position is determined by required pulse sequence.It is achieved in the pulse spacing of different time and the excitation of multiple pulses.
The clad 5, it is preferred to use polyurethane.Propellant and clock outermost layer can be wrapped up tightly, make it only
Reserve cup-shaped end face, it is ensured that entire powder charge cigarette burning in T-type burner.
As shown in figure 4, utilizing the side of impulse generator of the present invention measurement solid propellant rocket rough burning
Method is as follows:
Impulse generator is integrally placed in one end of T-type burner 12.The other end of T-type burner 12 disposes no pulse
Source cup-shaped propellant 8.No pulse source cup-shaped propellant 8 selects tested propellant, and explosive payload is according to entire burned
The time of journey determines.
At 12 both ends powder charge cup-shaped of T-type burner, igniter pad 6 is disposed, and draw through ignition lead 14, with a fire control
System 9 processed is connected, it is ensured that the both ends of T-type burner 12 can light a fire simultaneously.
Selection disposes several pressure sensors 7 in T-type burner 12, for obtaining the pressure of pulse in combustion process
The particular number of response, pressure sensor 7 is selected according to measurement demand, and in this embodiment, placement quantity is 5
It is a.7 output end of pressure sensor is connected with data collection system 10, collects pressure-response data by data collection system 10.
The pressure-response data being collected into is sent into computer 13 and carries out data processing by data collection system 10.
The Iganition control system 9, data collection system 10 and computer 13, are connected with power-supply system 11.
When measurement, implement to light a fire by Iganition control system 9 first, at this point, igniter pad 6 is lighted and the cup-shaped at both ends of igniting
Propellant 1 and no pulse source cup-shaped propellant 8, establish first pressing.
Cup-shaped propellant 1 burnt after a period of time, and the first time clock 2 that ignites generates driving pulse, and continues the column that ignites
Shape propellant 3, second of clock 4 generate driving pulse, and arteries and veins twice occurs in combustion process in T-type burner to realize
Impulse is encouraged.Powder charge and pressure response corresponding diagram in entire combustion process is as shown in Figure 5.
The igniter pad 6 can be packed by ignition charge (black powder and pyrotechnic compound) and igniter head with gauze.
The pressure sensor 7, can choose the water-cooled sensor of precision, high sensitivity, quantity and position is needed by experiment
Ask determining.
The Iganition control system 9, is made of the circuit that ignition controller and igniter head are formed, and control button ignition switch connects
When logical, loop current 3A or so guarantees ignition results.
The data collection system 10, can be made of data collecting card, and the acquisition card request sample frequency is high, transmission is fast
Degree is fast, can satisfy data acquisition demand.
The power-supply system 11, can be used voltage stabilization and current stabilization DC power supply, the power supply be a kind of output voltage it is continuously adjustable,
The high precision DC power supply of pressure stabilizing and current stabilization automatic conversion.
The T-type burner 12, main part are closed at both ends, middle opening a thick walled steel tube, and centre is opened
The mountable variable spray larynx sized nozzles of mouth.
Claims (5)
1. a kind of for measuring the impulse generator of solid propellant rocket combustion instability, including propellant, clock and
Clad；
Propellant and clock are wrapped by layer package, and take " propellant-clock " collectively as the powder charge of impulse generator
Alternate mode is disposed, and close zero-clearance each other；
The outermost side of impulse generator is cup-shaped propellant, and rim of a cup is outward；Cup-shaped propellant selects tested rocket propulsion
Agent plays the role of establishing first pressing in the moment of igniting, and explosive payload is according to building pressure effect and swash from igniting to closest pulse
The time interval encouraged determines that the time interval of the pulse excitation is by being manually set；
The particular number of non-outermost propellant and clock is determined according to the number of pulse required in continuous mode；
The explosive payload of each non-outermost propellant is determined according to the time interval of its adjacent two sides pulse excitation, between the time
Every by being manually set；
The explosive payload of each clock determines that position is true by required pulse sequence by pulse excitation size required in continuous mode
It is fixed；
The clad, it is desirable that propellant and clock outermost layer can be wrapped up tightly, it is made only to reserve cup-shaped end face, it is ensured that
Entire powder charge cigarette burning in T-type burner.In whole installation process, the mode wrapped up in powder charge is taken, final
The end face for reserving cup-shaped propellant accomplishes that clad sufficiently wraps up the powder charge of impulse generator；
When measurement, impulse generator is placed in one end in T-type burner.
2. it is as described in claim 1 a kind of for measuring the impulse generator of solid propellant rocket combustion instability,
It is characterized in that, the clock, black powder and pyrotechnic compound are selected in powder charge；The ratio of black powder and pyrotechnic compound, it is desirable that Neng Gou
All burnt within the scope of Millisecond, and the effect of coincidence pulse excitation.
3. it is as described in claim 1 a kind of for measuring the impulse generator of solid propellant rocket combustion instability,
It is characterized in that, the clock is packed using medicine box.
4. it is as described in claim 1 a kind of for measuring the impulse generator of solid propellant rocket combustion instability,
It is characterized in that, the wrapping layer uses polyurethane.
5. a kind of method using the measurement solid propellant rocket combustion instability of impulse generator described in claim 1,
It is characterized in that:
Impulse generator is integrally placed in one end of T-type burner, the other end placement no pulse source cup-shaped of T-type burner pushes away
Into agent, no pulse source cup-shaped propellant selects tested propellant, and explosive payload is true according to the time of entire combustion process
It is fixed；
At T-type burner both ends powder charge cup-shaped, igniter pad is disposed, and draw through ignition lead, with Iganition control system phase
Even, it is ensured that the both ends of T-type burner can light a fire simultaneously；
Selection disposes several pressure sensors in T-type burner, for obtaining the pressure response of pulse in combustion process, presses
The particular number of force snesor is selected according to measurement demand；Pressure sensor output end is connected with data collection system, by counting
Pressure-response data is collected according to acquisition system；Data collection system counts the pressure-response data being collected into feeding computer
According to processing；
The Iganition control system, data collection system and computer, are connected with power-supply system；
When measurement, implement to light a fire by Iganition control system first, at this point, igniter pad is lighted and the cup-shaped propellant at both ends of igniting
With no pulse source cup-shaped propellant, first pressing is established；
Later, the propellant of impulse generator, clock are successively ignited, to generate driving pulse, are realized in T-type burner
Pulsing motivates in middle combustion process.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910034135.2A CN109505712A (en) | 2019-01-15 | 2019-01-15 | It is a kind of for measuring the impulse generator of solid propellant rocket combustion instability |
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| CN201910034135.2A CN109505712A (en) | 2019-01-15 | 2019-01-15 | It is a kind of for measuring the impulse generator of solid propellant rocket combustion instability |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110594038A (en) * | 2019-08-20 | 2019-12-20 | 西安航天动力技术研究所 | A multiple pulse excitation device |
| CN113153579A (en) * | 2021-05-24 | 2021-07-23 | 北京理工大学 | Pulse trigger for measuring pressure coupling response function of composite propellant |
| CN113217229A (en) * | 2021-05-11 | 2021-08-06 | 中北大学 | Method and system for testing instantaneous nozzle throat diameter |
| CN115013187A (en) * | 2022-06-24 | 2022-09-06 | 哈尔滨工程大学 | Method and die for measuring pressure coupling response function of solid propellant |
| CN115126623A (en) * | 2022-06-09 | 2022-09-30 | 哈尔滨工程大学 | A high pressure external pulse generator for solid rocket motor |
| CN115126623B (en) * | 2022-06-09 | 2025-04-15 | 哈尔滨工程大学 | A high-pressure external pulse generator for solid rocket motors |
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| CN104481735A (en) * | 2014-09-19 | 2015-04-01 | 中国航天科工集团第六研究院二一○所 | Pulse trigger |
| CN107939549A (en) * | 2017-11-08 | 2018-04-20 | 航宇救生装备有限公司 | A kind of miniature multistage pulses thrust solid propellant rocket |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110594038A (en) * | 2019-08-20 | 2019-12-20 | 西安航天动力技术研究所 | A multiple pulse excitation device |
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| CN113217229A (en) * | 2021-05-11 | 2021-08-06 | 中北大学 | Method and system for testing instantaneous nozzle throat diameter |
| CN113217229B (en) * | 2021-05-11 | 2022-02-18 | 中北大学 | Method and system for measuring transient value of nozzle throat diameter |
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| CN115126623A (en) * | 2022-06-09 | 2022-09-30 | 哈尔滨工程大学 | A high pressure external pulse generator for solid rocket motor |
| CN115126623B (en) * | 2022-06-09 | 2025-04-15 | 哈尔滨工程大学 | A high-pressure external pulse generator for solid rocket motors |
| CN115013187A (en) * | 2022-06-24 | 2022-09-06 | 哈尔滨工程大学 | Method and die for measuring pressure coupling response function of solid propellant |
| WO2023245874A1 (en) * | 2022-06-24 | 2023-12-28 | 哈尔滨工程大学 | Solid propellant pressure-coupled response function measurement method and molds |
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