CN102854284A - Solid fuel regression rate test device - Google Patents
Solid fuel regression rate test device Download PDFInfo
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- CN102854284A CN102854284A CN2012103326598A CN201210332659A CN102854284A CN 102854284 A CN102854284 A CN 102854284A CN 2012103326598 A CN2012103326598 A CN 2012103326598A CN 201210332659 A CN201210332659 A CN 201210332659A CN 102854284 A CN102854284 A CN 102854284A
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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 proving installation, belong to hybrid rocket engine and technical field of measurement and test, be used for the regression rate test under different oxidizer flow rate conditions 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 characteristics such as thrust is adjustable and enjoy researchist's concern.Do not contain or only contain a small amount of oxygenant in the solid-liquid rocket, the solid fuel powder column burns with the liquid state or the gaseous oxidizer that flow 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.Solid-liquid rocket powder column energy utilization efficiency is more relevant than (oxygen/combustion than) with the consumption of when burning constituent element, so estimates the regression rate of fuel, determines oxygen/combustion than just seeming very important.
A kind of multi-target-line dynamic combustion performance testing system for solid propellant is disclosed in the 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 in order to fixing many targets line medicine frame of sample, many targets line medicine frame one end has a firewire binding post, earth terminal and 6～10 target line binding posts in the firing chamber; The data acquisition process unit is used for scheduling and the control of each functional block of measurement and control unit, and the analyzing and processing of test data and data management.This test macro can draw the solid propellant sample in certain pressure intensity scope internal combustion speed, the strong coefficient of combustion ram compression, temperature sensitivity of burning rate.
Actual conditions when multi-target-line dynamic combustion performance testing system for solid propellant can be good at burning near solid propellant rocket are dynamically fired speed.But the target collimation method but can not be used for the regression rate of test fuel, because do not contain or only contain a small amount of oxygenant in the fuel, fuel will place in the device of high-concentration oxygen when using the test of target collimation method, in this case the fire fuel dangerous accident such as blast possibly.Oxygenant flows in the solid-liquid engine, and the oxygenant of target collimation method survey combustion speed is static, so the target collimation method can not be used for measuring the regression rate of solid-liquid motor fuel.
Introduced a kind of optical fiber solid/mixed rocket engine powder column regression rate testing sensor in the United States Patent (USP) 5107129, solid fuel tank wall or hybrid rocket engine insert the fibre bundle of binding different length, expand to the edge of center pit by fuel powder column wall.Powder column burns with normal mode, extends to the shell periphery from the center.Can see ignition flame at the optical fiber afterbody, fiber and flame are adjacent.Fibre bundle is used for judging regression rate and igniting left side powder column amount.Then the fibrous ring of a branch of different length gets back to case surface to surrounding powder column, and light emitting diode is positioned at the afterbody of each fiber, and photodetector is at the another side afterbody simultaneously.When optical fiber and light source use together, a light receiving element,, can be got back to optical inductor from the light of light source and be used for establishing regression rate and powder column surplus when the fiber afterbody is destroyed by the powder column igniting in any stage of burning at afterbody simultaneously.
Optical fiber solid/mixed rocket engine powder column regression rate testing sensor is the regression rate of test fuel accurately, need to adopt special fiber as induction and transmission equipment, and diode, photodetector, this all so that cost greatly improve, while optical fiber, diode, the use of photodetector also can the increasing system complexity and difficulties of operation, and environment, the factors such as temperature also are difficult to avoid on the impact of light, and the high temperature during simultaneously fuel combustion can make medium be heated, and light decomposes all and can the accuracy of test be exerted an adverse impact.
Summary of the invention
For fear of the deficiency that prior art exists, overcome the rocket engine fuel regression rate and measure hard problem, the present invention proposes a kind of solid fuel regression rate proving installation, the firing chamber of adopting rectangular groove structure, propellant is made rectangular parallelepiped and is tested; Proving installation when work combustion chamber pressure, oxidizer flow rate is all adjustable, by change pressure, flow obtains firing speed and pressure, the funtcional relationship between the 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 preferably solid-liquid rocket solid fuel regression rate.
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 the rectangle loam cake is arranged at top, and the loam cake front and back ends has screw, and lighter is positioned at the loam cake front portion and is connected with the firing chamber, and the pressure measurement mouth is fixedly mounted on the loam cake middle part and communicates with the firing chamber; There is screw in chamber front end section, and draft tube is fixed on the counter balance pocket front end and is connected with chamber front end section, and inlet plate is between counter balance pocket and firing chamber; Laval nozzle is fixed on the firing chamber rearward end by the jet pipe cover; Draw-in groove is positioned at inner bottom surface middle part, firing chamber, and powder column is placed in the draw-in groove.
Described draw-in groove be two rectangular parallelepipeds respectively perpendicular to the firing chamber inner bottom surface, two ends are adjacent to two side in the firing chamber, spacing is identical with grain length in the draw-in groove, the draw-in groove height is half of powder column height.
Described inlet plate is discoid, and there is flaring type air admission hole at the center, is evenly equipped with the identical flaring type air admission hole of a plurality of sizes according to air feeding in center hole extension.
Inner Wall of Combustion Chamber posts thermofin.
The principle of solid fuel regression rate proving installation of the present invention: namely oxygenant enters counter balance pocket from storage tank through draft tube, enters the firing chamber from counter balance pocket via inlet plate again.Powder column is housed in the firing chamber, and powder column equally is made into rectangle with the firing chamber, and powder column is that fuel does not contain or only contain a small amount of oxygenant, and clad is posted in powder column side and bottom surface, only has upper face to burn.The rectangular body powder column of the thick e of the certain meat of burning in the rectangle engine, the record powder column is from lighting the used time t of all burnt, then the regression rate r of computing fuel.Flow G with oxygenant according to the regression rate r of experiment fuel
0Relevant, r=aG wherein
0 n, a is constant.Directly change the flow of oxygenant by the larynx that changes jet pipe, repeatedly test, obtain under the different oxidizer flow rate conditions, the regression rate of fuel draws regression rate r and oxidizer flow rate G according to data
0Between funtcional relationship.The feature of this proving installation maximum is to adopt rectangle engine and rectangle powder column (common all employings right cylinder engine and cylinder powder column): because in the process of powder charge burning, melting may occur in powder column, and right cylinder can produce distortion at melting after-burning face, and burning irregular may set off an explosion and unsafe conditions.The rectangular body powder column also can only be kept the single face burning in the situation that melting occurs, combustion front can not change.
Beneficial effect
Solid fuel regression rate proving installation of the present invention, the firing chamber of adopting rectangular groove structure, lighter is installed in the loam cake front portion and is connected with the firing chamber; The pressure measurement mouth is fixed on the loam cake middle part and communicates with the firing chamber; Draft tube connects counter balance pocket, and inlet plate is between counter balance pocket and firing chamber; Laval nozzle is fixed on the rear portion, firing chamber; Position in the middle of draw-in groove is positioned on the inner bottom surface of firing chamber, powder column is placed in the draw-in groove and tests; Proving installation when work combustion chamber pressure, oxidizer flow rate is all adjustable, by change pressure, flow obtains firing speed and pressure, the funtcional relationship between the 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 preferably solid-liquid rocket solid fuel regression rate.Proving installation requires low to various propellants, but equal use test device is tested as long as propellant is made cuboid.
Description of drawings
Below in conjunction with drawings and embodiments a kind of solid fuel regression rate of the present invention proving installation is described in further detail.
Fig. 1 is solid fuel regression rate proving installation synoptic diagram of the present invention.
Fig. 2 is the left view of solid fuel regression rate proving installation of the present invention.
Fig. 3 is the inlet plate synoptic diagram of solid fuel regression rate proving installation of the present invention.
Fig. 4 is the inlet plate cut-open view.
Fig. 5 is A-A place cut-open view.
Among the figure:
1. draft tube 2. counter balance pocket 3. inlet plates 4. lighters 5. firing chambers 6. draw-in grooves, 7. powder columns, 8. pressure measurement mouths, 9. Laval nozzles
Specific embodiments
Present embodiment is a kind of solid fuel regression rate proving installation.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 proving installation of the present invention comprises 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 the rectangle loam cake is arranged at top, and there is screw the loam cake rear and front end, and is fastening by screw and firing chamber 5, and firing chamber 5 inwalls post thermofin.Integrated igniter 4 be installed in loam cake anterior with firing chamber 5 in be connected; Pressure measurement mouth 8 is fixedly mounted on the loam cake middle part, communicates with firing chamber 5 by the aperture that covers; Firing chamber 5 leading sections have screw, and draft tube directly passes in the counter balance pocket 2, are connected with firing chamber 5 leading section screws, and inlet plate 3 is installed between counter balance pocket 2 and the firing chamber 5; Inlet plate 3 is discoid, and there is flaring type air admission hole at the center, is evenly equipped with the identical air admission hole of a plurality of sizes in the form of a ring according to air feeding in center hole extension.Laval nozzle 9 is fixed on 5 rear portions, firing chamber by step-like jet pipe cover, and jet pipe can be dismantled, and conveniently adopts different jet pipes in test, and Nozzle throat also can be regulated simultaneously.Draw-in groove 6 is two rectangular parallelepipeds perpendicular to position in the middle of on 5 bottom surfaces, firing chamber, and two ends, the left and right sides are adjacent to 5 sides, firing chamber, and powder column 7 is placed in the draw-in groove 6, and distance equals grain length between the draw-in groove, and the draw-in groove height is half of powder column height; Draw-in groove keeps shape invariance except fixing powder column in the time of also can making powder column generation melting.Powder column is that fuel does not contain or only contain a small amount of oxygenant, and rectangle powder column side and bottom surface coat, and 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 the firing chamber 5, then, 4 igniting of engine ignition device, record the thick solid-fuelled burning pressure curve of certain meat by pressure measurement mouth 8 during engine operation, obtain powder column burning time, calculate the regression rate of fuel in conjunction with grain web thickness; By changing oxidizer flow rate, obtain different oxidizer flow rate fuel regression rates, simulate regression rate and oxidizer flow rate funtcional relationship.In addition, also can obtain fuel regression rate under the different pressure by changing combustion chamber pressure, the relation of research pressure and regression rate is further optimized the regression rate formula.Proving installation can be tested the solid-fuelled regression rate of different component, lays the first stone for improving solid-liquid rocket powder column energy utilization efficiency.
The concrete steps of testing fuel regression rate under the different oxidizer flow rates are as follows:
(1) makes some propellant samples with rectangular mould, and fire-retardant coating is carried out on its other surfaces except upper surface, burn by the combustion in parallel layer rule during with the assurance propellant combustion.According to the requirement of experiment oxidizer flow rate, pressure and collimation experiment, the number of the propellant sample that calculating should be processed is to guarantee obtaining at least 3 groups of effective experimental datas under each oxidizer flow rate, each pressure conditions;
(2) get wherein powder column, the meat of record propellant is thick to be e, inserts in the firing chamber 5, powder column 7 samples is fixed in the draw-in groove 6, and finishes the assembling of a whole set of test unit; Connect igniting and proving installation, check and guarantee that lighter and pressure measurement mouth 8 are working properly;
(3) before on-test, check whether gas admittance valve is in closed condition, guarantee that gas admittance valve cuts out, adjust the larynx footpath of jet pipe 9, so that oxidizer flow rate is definite value; During on-test, open gas admittance valve, make oxygenant enter counter balance pocket 2 interior even mixing by draft tube 1, again by in inlet plate 3 flowing in combustion chambers 5 to fixed pressure, open pressure measurement mouth 8, and so that pressure measurement mouth 8 is in test mode;
(4) igniting; Cut-in point firearm 4 carries out engine ignition, and records the time t1 that powder charge takes fire; Observe the powder charge combustion process, treat the powder column all burnt record time t2 of this moment, 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 of making 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, powder charge t burning time calculates the combustion speed r of powder charge, records combustion speed r and the corresponding oxidizer flow rate G0 of each propellant sample, according to the funtcional relationship that these data fittings go out to fire fast r and oxidizer flow rate G0, calculate burning rate coefficient a;
(8) finish above process, the dismounting experimental provision uses in order to test next time, and the regression rate test experiments is finished.
Claims (4)
1. solid fuel regression rate proving installation 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, and the rectangle loam cake is arranged at top, and the loam cake front and back ends has screw, and lighter is positioned at the loam cake front portion and is connected with the firing chamber, and the pressure measurement mouth is fixedly mounted on the loam cake middle part and communicates with the firing chamber; There is screw in chamber front end section, and draft tube is fixed on the counter balance pocket front end and is connected with chamber front end section, and inlet plate is between counter balance pocket and firing chamber; Laval nozzle is fixed on the firing chamber rearward end by the jet pipe cover; Draw-in groove is positioned at inner bottom surface middle part, firing chamber, and powder column is placed in the draw-in groove.
2. solid fuel regression rate proving installation according to claim 1, it is characterized in that: described draw-in groove is that two rectangular parallelepipeds are respectively perpendicular to the firing chamber inner bottom surface, two ends are adjacent to two side in the firing chamber, and spacing is identical with grain length in the draw-in groove, and the draw-in groove height is half of powder column height.
3. solid fuel regression rate proving installation according to claim 1, it is characterized in that: described inlet plate is discoid, there is flaring type air admission hole at the center, is evenly equipped with the identical flaring type air admission hole of a plurality of sizes according to air feeding in center hole extension.
4. solid fuel regression rate proving installation according to claim 1, it is characterized in that: Inner Wall of Combustion Chamber posts thermofin.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104061089A (en) * | 2014-05-18 | 2014-09-24 | 西北工业大学 | Device and method for testing solid fuel melting characteristics |
| CN104330520A (en) * | 2014-10-30 | 2015-02-04 | 西北工业大学 | Testing device and testing method of constant volume combustion of solid propellant |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| US20110203256A1 (en) * | 2010-02-24 | 2011-08-25 | Chen Yen-Sen | Motor |
| CN102400814A (en) * | 2011-10-27 | 2012-04-04 | 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 |
-
2012
- 2012-09-11 CN CN201210332659.8A patent/CN102854284B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| US20110203256A1 (en) * | 2010-02-24 | 2011-08-25 | Chen Yen-Sen | Motor |
| CN102400814A (en) * | 2011-10-27 | 2012-04-04 | 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 |
Non-Patent Citations (2)
| Title |
|---|
| 吉秋平: "弹用固体燃料冲压发动机性能研究", 《中国优秀硕士论文电子期刊》 * |
| 武渊 等: "氧化剂质量通量对固液火箭发动机中固体燃料退移速率的影响", 《固体火箭技术》 * |
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| CN113417760B (en) * | 2021-06-18 | 2023-11-10 | 西北工业大学 | Solid propellant oxygen combustion split charging coupling combustion transparent window experimental device and experimental method |
| CN114280214A (en) * | 2021-12-03 | 2022-04-05 | 西安近代化学研究所 | Solid propellant combustion surface maintaining device and using method |
| CN114280214B (en) * | 2021-12-03 | 2023-10-20 | 西安近代化学研究所 | Solid propellant combustion surface maintaining device and use method |
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