CN102854284B - Solid fuel regression rate test device - Google Patents
Solid fuel regression rate test device Download PDFInfo
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- CN102854284B CN102854284B CN201210332659.8A CN201210332659A CN102854284B CN 102854284 B CN102854284 B CN 102854284B CN 201210332659 A CN201210332659 A CN 201210332659A CN 102854284 B CN102854284 B CN 102854284B
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Abstract
The invention discloses a solid fuel regression rate test device. According to the invention, a combustion chamber with a rectangular recess structure is adopted. An igniter is arranged on the front of an upper cap, and communicates with the combustion chamber. A pressure measurement port is fixed on the middle of the upper cap, and communicates with the combustion chamber. An air inlet pipe is connected to a balancing chamber. An air inlet plate is positioned between the balancing chamber and the combustion chamber. A Laval sprayer nozzle is fixed on the back part of the combustion chamber. A fixing slot is positioned at a central part on the bottom in the combustion chamber. An agent column is placed in the fixing slot, and testing can be carried out. During the operation of the test device, combustion chamber pressure intensity and oxidant flow are both adjustable. Through the changes on the pressure intensity and the flow, a functional relationship between a burning rate and the pressure intensity and the oxidant flow can be obtained, such that test complexity can be effectively reduced. The test device provided by the invention has the advantages of simple structure, low cost, easy processing, and safe and reliable operation. With the test device, the solid fuel regression rate of a hybrid rocket motor can be tested. The test device has low requirements on various propellants. Once a propellant is prepared into a rectangular body, testing can be carried out by using the test device provided by the invention.
Description
Technical field
The present invention relates to a kind of solid fuel regression rate test device, belong to hybrid rocket engine and technical field of measurement and test, for the regression rate test under different oxidizer flow rate condition of hybrid rocket engine fuel.
Background technology
In recent years, hybrid rocket engine is safe and reliable because of it, nontoxic pollution-free, and cost is low and can repeatedly start and the feature such as adjustable thrust and enjoy the concern of researchist.Do not contain in solid-liquid rocket or only contain a small amount of oxygenant, solid fuel powder column burns with the liquid state or gaseous oxidizer flowing through its surface, the regression rate on motor grain surface is very low, this can affect the burning efficiency of engine, then affect engine performance, improve the key that regression rate becomes development solid-liquid engine.When solid-liquid rocket powder column energy utilization efficiency and burning, the consumption ratio (oxygen/combustion ratio) of constituent element is relevant, therefore estimating the regression rate of fuel, determining oxygen/combustion than just seeming very important.
A kind of multi-target-line dynamic combustion performance testing system for solid propellant is disclosed in Chinese patent 201110039791.5, comprise firing chamber and distribution unit, measurement and control unit and data acquisition process unit, firing chamber and distribution unit comprise firing chamber, calibration cell, high-pressure nitrogen bottle, buffering nitrogen cylinder, related valve pipeline, nitrogen supercharging pump and the many targets line medicine frame in order to fixing sample, and there are a firewire binding post, earth terminal and 6 ~ 10 target line binding posts in many targets line medicine frame one end in firing chamber; Data acquisition process unit is used for the scheduling of each functional block of measurement and control unit and control, and the analyzing and processing of test data and data management.This test macro can show that solid propellant sample is in certain pressure intensity scope internal combustion speed, fires fast pressure coefficient, temperature sensitivity of burning rate.
Multi-target-line dynamic combustion performance testing system for solid propellant can be good at actual conditions when burning close to solid propellant rocket, is dynamically fired speed.But target collimation method but can not be used for the regression rate of test fuel, because do not contain in fuel or only contain small amounts agent, when using the test of target collimation method, fuel will be placed in the device of high-concentration oxygen, and fire fuel such as to be blasted possibly at the dangerous accident in this case.In solid-liquid engine, oxygenant is flowing, and the oxygenant that target collimation method surveys combustion speed is static, so target collimation method can not be used for measuring the regression rate of solid-liquid motor fuel.
A kind of optical fiber solid/mixed rocket engine powder column regression rate testing sensor is described in United States Patent (USP) 5107129, solid fuel tank wall or hybrid rocket engine insert the fibre bundle of binding different length, are expanded to the edge of center pit by fuel powder column wall.Powder column burns in the normal fashion, extends to housing peripheral from center.Can see ignition flame at optical fiber afterbody, fiber is adjacent with flame.Fibre bundle is used for judging regression rate and igniting left side powder column amount.The fibrous ring of a branch of different length is to encirclement powder column, and then get back to case surface, light emitting diode is positioned at the afterbody of each fiber, and photodetector is at another side afterbody simultaneously.When optical fiber uses together with light source, a light receiving element is at afterbody simultaneously, and in any stage of burning, when fiber afterbody is destroyed by powder column igniting, the light from light source can be got back to optical inductor and be used for establishing regression rate and powder column surplus.
Optical fiber solid/mixed rocket engine powder column regression rate testing sensor can the regression rate of test fuel accurately, need to adopt special fiber as induction and transmission equipment, and diode, photodetector, this all makes cost greatly improve, optical fiber simultaneously, diode, the use of photodetector also can strengthen the complexity and difficulties of Dynamic System, and environment, the factors such as temperature are also difficult to avoid on the impact of light, and high temperature during fuel combustion simultaneously can make medium be heated, and light decomposition all can exert an adverse impact to the accuracy of test.
Summary of the invention
In order to avoid the deficiency that prior art exists, overcome the problem that rocket engine fuel regression rate measures difficulty, the present invention proposes a kind of solid fuel regression rate test device, and adopt the firing chamber of rectangular groove structure, propellant is made rectangular parallelepiped and tested; Combustion chamber pressure during proving installation work, oxidizer flow rate is all adjustable, and obtain combustion speed and pressure by change pressure, flow, the funtcional relationship between oxidizer flow rate, can reduce the complicacy of test effectively; Apparatus structure is simple, and cost is low, is easy to processing, and handling safety is reliable, can test solid-liquid rocket solid fuel regression rate preferably.
The technical solution adopted for the present invention to solve the technical problems is: comprise draft tube, counter balance pocket, inlet plate, lighter, firing chamber, draw-in groove, pressure measurement mouth, Laval nozzle,
Described firing chamber is rectangular groove structure, and rectangle upper cover is arranged at top, and upper cover front and back ends has screw, and lighter is positioned at upper cover front portion and is connected with firing chamber, and pressure measurement mouth is fixedly mounted on upper cover middle part and communicates with firing chamber; There is screw in chamber front end portion, and draft tube is fixed on counter balance pocket front end and is connected with chamber front end portion, and inlet plate is between counter balance pocket and firing chamber; Laval nozzle is fixed on firing chamber rearward end by jet pipe cover; Draw-in groove is positioned at inner bottom surface middle part, firing chamber, and powder column is placed in draw-in groove.
Described draw-in groove be two rectangular parallelepipeds respectively perpendicular to firing chamber inner bottom surface, two ends are adjacent to two side in firing chamber, and in draw-in groove, spacing is identical with grain length, and draw-in groove height is the half of powder column height.
Described inlet plate is discoid, and there is flaring type air admission hole at center, is evenly equipped with the identical flaring type air admission hole of multiple size according to air feeding in center hole extension.
Inner Wall of Combustion Chamber posts thermofin.
The principle of solid fuel regression rate test device of the present invention: namely oxygenant enters counter balance pocket from storage tank through draft tube, then enter firing chamber from counter balance pocket via inlet plate.Firing chamber is built with powder column, and powder column is equally made into rectangle with firing chamber, and powder column is that fuel does not contain or only containing small amounts agent, clad is posted in powder column side and bottom surface, only has upper face to burn.Burn in rectangle engine the rectangular body powder column of the thick e of certain meat, record powder column from lighting all burnt time t used, the then regression rate r of computing fuel.Experimentally the regression rate r of fuel is the flow G with oxygenant
0relevant, wherein r=aG
0 n, a is constant.Changed the flow of oxygenant by the larynx footpath changing jet pipe, repeatedly test, under obtaining different oxidizer flow rate condition, the regression rate of fuel, draws regression rate r and oxidizer flow rate G according to data
0between funtcional relationship.The maximum feature of this proving installation adopts rectangle engine and rectangle powder column (common all employings right cylinder engine and cylinder powder column): because in the process of powder charge burning, may melting be there is in powder column, and right cylinder can produce distortion in the face of firing after melting, burning irregular may set off an explosion and unsafe conditions.Rectangular body powder column also can only maintain one side burning when there is melting, combustion front can not change.
Beneficial effect
Solid fuel regression rate test device of the present invention, adopts the firing chamber of rectangular groove structure, and lighter is arranged on upper cover front portion and combustion chamber; Pressure measurement mouth is fixed in the middle part of upper cover and communicates with firing chamber; Draft tube connects counter balance pocket, and inlet plate is between counter balance pocket and firing chamber; Laval nozzle is fixed on rear portion, firing chamber; Draw-in groove is positioned at middle part on the inner bottom surface of firing chamber, and powder column is placed in draw-in groove and tests; Combustion chamber pressure during proving installation work, oxidizer flow rate is all adjustable, and obtain combustion speed and pressure by changing pressure, flow, the funtcional relationship between oxidizer flow rate, can reduce the complicacy of test effectively.Apparatus structure is simple, and cost is low, is easy to processing, and handling safety is reliable, can test solid-liquid rocket solid fuel regression rate preferably.Proving installation requires low to various propellant, proving installation all can be used to test as long as cuboid made by propellant.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of solid fuel regression rate test device of the present invention is described in further detail.
Fig. 1 is solid fuel regression rate test device schematic diagram of the present invention.
Fig. 2 is the left view of solid fuel regression rate test device of the present invention.
Fig. 3 is the inlet plate schematic diagram of solid fuel regression rate test device of the present invention.
Fig. 4 is inlet plate cut-open view.
Fig. 5 is A-A place cut-open view.
In figure:
1. draft tube 2. counter balance pocket 3. inlet plate 4. lighter 5. firing chamber 6. draw-in groove 7. powder column 8. pressure measurement mouth 9. Laval nozzle
Specific embodiments
The present embodiment is a kind of solid fuel regression rate test device.Adopt the firing chamber of rectangular groove structure, propellant is made rectangular parallelepiped and is tested, test solid-liquid rocket solid fuel regression rate.
Consult Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5, solid fuel regression rate test device of the present invention, comprise draft tube 1, counter balance pocket 2, inlet plate 3, lighter 4, firing chamber 5, draw-in groove 6, powder column 7, pressure measurement mouth 8, Laval nozzle 9; Firing chamber 5 is rectangular groove structure, and rectangle upper cover is arranged at top, and there is screw upper cover rear and front end, by screw and firing chamber 5 fastening, firing chamber 5 inwall posts thermofin.Integrated igniter 4 is arranged on upper cover front portion and is connected with in firing chamber 5; Pressure measurement mouth 8 is fixedly mounted on upper cover middle part, is communicated with firing chamber 5 by the aperture covered; There is screw leading section, firing chamber 5, and draft tube directly passes in counter balance pocket 2, and be connected with leading section, firing chamber 5 screw, inlet plate 3 is arranged between counter balance pocket 2 and firing chamber 5; Inlet plate 3 is discoid, and there is flaring type air admission hole at center, is evenly equipped with the identical air admission hole of multiple size in the form of a ring according to air feeding in center hole extension.Laval nozzle 9 is fixed on rear portion, firing chamber 5 by step-like jet pipe cover, and jet pipe can be dismantled, and conveniently adopts different jet pipes in testing, and Nozzle throat is also adjustable simultaneously.Draw-in groove 6 be two rectangular parallelepipeds perpendicular to middle part on bottom surface, firing chamber 5, two ends, left and right are adjacent to side, firing chamber 5, and powder column 7 is placed in draw-in groove 6, and the spacing of draw-in groove equals grain length, and draw-in groove height is the half of powder column height; Draw-in groove, except fixing powder column, also can make to keep shape invariance during powder column generation melting.Powder column is that fuel does not contain or only containing small amounts agent, rectangle powder column side and bottom surface are carried out coated, burn above only having.
Proving installation of the present invention, first the solid fuel that will measure is made into rectangular parallelepiped powder column 7, getting the thick powder column of certain meat is fixed in firing chamber 5, then, engine ignition 4 is lighted a fire, record the thick solid-fuelled burning pressure curve of certain meat by pressure measurement mouth 8 during engine operation, obtain powder column burning time, calculating the regression rate of fuel in conjunction with grain web thickness; By changing oxidizer flow rate, obtaining different oxidizer flow rate fuel regression rate, simulating regression rate and oxidizer flow rate funtcional relationship.In addition, also by changing combustion chamber pressure, fuel regression rate under different pressure is obtained, the relation of research pressure and regression rate, optimization regression rate formula further.Proving installation can test the solid-fuelled regression rate of different component, lays the first stone for improving solid-liquid rocket powder column energy utilization efficiency.
Test the concrete steps of fuel regression rate under different oxidizer flow rate as follows:
(1) make some propellant samples by rectangular mould, and carry out fire-retardant coated to its other surfaces except upper surface, burn by combustion in parallel layer rule during to ensure propellant combustion.According to the requirement of experiment oxidizer flow rate, pressure and collimation experiment, calculate the number of the propellant sample processed, to ensure, under each oxidizer flow rate, each pressure conditions, at least to obtain 3 groups of effective experimental datas;
(2) get wherein one piece of powder column, the meat of record propellant is thick is e, inserts in firing chamber 5, is fixed in draw-in groove 6 by powder column 7 sample, and completes the assembling of a whole set of test unit; Connect igniting and proving installation, check and guarantee lighter and pressure measurement mouth 8 working properly;
(3) before on-test, check whether gas admittance valve is in closed condition, guarantees that gas admittance valve cuts out, the larynx footpath of adjustment jet pipe 9, makes oxidizer flow rate be definite value; During on-test, open gas admittance valve, make oxygenant enter Homogeneous phase mixing in counter balance pocket 2 by draft tube 1, interior to fixed pressure by inlet plate 3 flowing in combustion chamber 5, open pressure measurement mouth 8, and make pressure measurement mouth 8 be in test mode;
(4) light a fire; Cut-in point firearm 4 carries out engine ignition, and records the time t1 that powder charge takes fire; Observe powder charge combustion process, treat powder column all burnt record time t2 now, the pressure curve that record pressure measurement mouth records;
(5) close proving installation, preserve experimental data, calculate oxidizer flow rate G01 according to Nozzle throat;
(6) get the propellant sample made in (1), change Nozzle throat and change oxidizer flow rate, repeat (2) ~ (5) process, record the time pressure curve of powder charge burning and calculate oxidizer flow rate G0 by Nozzle throat;
(7) according to the thick e of powder charge meat, charge burning time t, calculates the combustion speed r of powder charge, records the combustion speed r of each propellant sample and corresponding oxidizer flow rate G0, go out to fire the funtcional relationship of fast r and oxidizer flow rate G0 according to these data fittings, calculate burning rate coefficient a;
(8) complete above process, dismounting experimental provision uses in order to test next time, and regression rate test experiments completes.
Claims (1)
1. a solid fuel regression rate test device, it is characterized in that: comprise draft tube, counter balance pocket, inlet plate, lighter, firing chamber, draw-in groove, pressure measurement mouth, Laval nozzle, described firing chamber is rectangular groove structure, rectangle upper cover is arranged at top, upper cover front and back ends has screw, lighter is positioned at upper cover front portion and is connected with firing chamber, and pressure measurement mouth is fixedly mounted on upper cover middle part and communicates with firing chamber; There is screw in chamber front end portion, and draft tube is fixed on counter balance pocket front end and is connected with chamber front end portion, and inlet plate is between counter balance pocket and firing chamber; Laval nozzle is fixed on firing chamber rearward end by jet pipe cover; Draw-in groove is positioned at inner bottom surface middle part, firing chamber, and powder column is placed in draw-in groove; Described draw-in groove be two rectangular parallelepipeds respectively perpendicular to firing chamber inner bottom surface, two ends are adjacent to two side in firing chamber, and in draw-in groove, spacing is identical with grain length, and draw-in groove height is the half of powder column height; Described inlet plate is discoid, and there is flaring type air admission hole at center, is evenly equipped with the identical flaring type air admission hole of multiple size according to air feeding in center hole extension.
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| CN201210332659.8A CN102854284B (en) | 2012-09-11 | 2012-09-11 | Solid fuel regression rate test device |
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| CN201210332659.8A CN102854284B (en) | 2012-09-11 | 2012-09-11 | Solid fuel regression rate test device |
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| CN102854284B true CN102854284B (en) | 2015-06-24 |
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| US4124976A (en) * | 1976-07-06 | 1978-11-14 | The United States Of America As Represented By The Secretary Of The Navy | Method for reducing the critical injection parameter in a solid fuel ramjet |
| CN2799873Y (en) * | 2004-07-09 | 2006-07-26 | 李学志 | Combustion type engine |
| CN101924014A (en) * | 2009-06-09 | 2010-12-22 | 北京北方微电子基地设备工艺研究中心有限责任公司 | Air suction device and technological chamber |
| TWI422741B (en) * | 2010-02-24 | 2014-01-11 | Nat Applied Res Laboratories | Motor |
| CN102400814B (en) * | 2011-10-27 | 2013-09-18 | 北京航空航天大学 | Solid-liquid hybrid rocket ramjet for test |
| CN202854103U (en) * | 2012-09-11 | 2013-04-03 | 西北工业大学 | Testing device for regression rate of solid fuel |
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