CN102426215B - Solid propellant crack expansion testing apparatus - Google Patents
Solid propellant crack expansion testing apparatus Download PDFInfo
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- CN102426215B CN102426215B CN201110274590.3A CN201110274590A CN102426215B CN 102426215 B CN102426215 B CN 102426215B CN 201110274590 A CN201110274590 A CN 201110274590A CN 102426215 B CN102426215 B CN 102426215B
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Abstract
The invention discloses a solid propellant crack expansion testing apparatus. The testing apparatus is a simulated engine combustion chamber. A propellant sample is placed in the chamber. The propellant sample is fixed in a supporting plate cavity. Two sides of the sample are fixed by using two wedge blocks. A cylindrical observation window is assembled between the supporting plate and a front flange. The observation window and the supporting plate form a tight fit. The observation window and the front flange form a tight fit. The front flange and a back flange are connected with four symmetrically arranged bolts. Two through holes are provided on the top of the supporting plate. Two welding tips are respectively arranged in the two through holes. The welding tips are respectively connected with a solenoid valve and a throttle orifice plate. The testing apparatus is advantaged in simple structure, safe operation, and reliable operation. The apparatus is especially suitable to be used in a test for simulating a combustion chamber supercharging process after a solid rocket engine is ignited, observing a solid propellant crack expansion situation, researching a solid propellant crack expansion variation regularity and an influence factor thereof.
Description
Technical field
The present invention relates to a kind of test unit for solid propellant rocket propellant, specifically, relate to a kind of crack extension tester for solid propellant.Belong to solid propellant rocket and experimental facilities field thereof, be applicable to simulate pressurization in solid propellant rocket igniting after-burner, the test of observational study Crack Growth In Solid Propellants Changing Pattern and influence factor thereof.
Background technology
Solid propellant rocket propellant, in production and ignition process, owing to being subject to various stress, can crack.Crackle has significant impact to the combustion characteristics of solid propellant, under extreme case, likely blasts.At present, both at home and abroad scientific research personnel has carried out a large amount of relevant crackle burnings to solid propellant and has expanded the experimental study of mechanism, restraining factors, has designed multiple crackle simulation test device.
Existing disclosed document (Todd E.Earnest, RSRMTP-H1148 Main Grain Propellant Crack Initiation Evaluation[R] .AIAA 2005-3601.) in introduced when the Crack Extension that research burning causes, the a set of high speed video system adopting, it comprises simulated engine firing chamber, data-acquisition system and firing system three parts.Simulated engine firing chamber is the cylindrical system of one end band transparent organic glass window, and data-acquisition system comprises pressure-measuring system and imaging system.In this test unit, different Crack Extension free volume correspondence propellant test specimen supporting disk separately, be contrast experiment and must change supporting disk, and this can impact the impermeability of test unit, and complicated operation.
At document " experimental study and the theoretical analysis [D] of expansion condition during solid propellant crack burning. " (naval aviation engineering college Master's thesis, 1999.), " solid propellant crack burning and the research [D] of expanding. " (naval aviation engineering college Master's thesis, 2000.), " experimental study [J] that propulsion charge crack combustion is mobile. " (< < Push Technology > > 2000, 21 (5): the at a high speed real-time fluorescent screen analytic system (RTR) of the mostly employing X ray of introducing 58-60.) is as the test macro of crack expansion test.The at a high speed real-time fluorescent screen analytic system (RTR) of X ray is a kind of contactless experimental facilities of studying opaque high-pressure burner or engine interior complex work process, and this system is comprised of x ray generator, test engine, high speed video recording system, time controlled system, data acquisition system (DAS), high-speed motion analysis instrument.Its groundwork principle is to utilize x-ray imaging principle to absorb the course of work of engine interior, utilizes pressure transducer also can obtain pressure-time curve simultaneously.In this device, adopt rectangle engine along X ray direction even thickness to obtain the uniform image of background.But this experimental provision can only carry out the Crack Extension experiment under propellant combustion condition, can not carry out the experiment under cold air pressurising condition, the experimental data providing is abundant not, has a certain distance with engine actual operating conditions.
Summary of the invention
In order to overcome, in prior art, test structure operation complexity, the deficiency that Crack Extension experiment condition is single, the present invention proposes a kind of crack extension tester for solid propellant, this crack expansion test device, by changing the different wedge in angle of inclination, is realized the repeatedly adjusting of Crack Extension free volume; Pass into nitrogen and realize the test of Crack Extension situation under cold air pressurising condition; Increase igniter pad and igniter pad wire, realize the test of Crack Extension situation under propellant combustion condition; This apparatus structure is simple, and handling safety is reliable.
The present invention solves its technical matters, and the technical scheme adopting is: crack expansion test device comprises that forward flange dish, rear stub, supporting disk, welding tip, view window, front O-ring seal, rear O-ring seal, propellant test specimen and wedge form.
Described supporting disk is hollow oblate cylindricality, the hollow lumen that front and back connect is two big or small frame structures of stack up and down, the top of supporting disk is provided with two round tube holes that communicate with hollow lumen, two round tube holes structure that is in the shape of the letter V, on two round tube holes, welding tip is installed, two welding tips are connected with throttling orifice plate with solenoid valve separately, the annular groove of O-ring seal before the front end face of supporting disk is provided with and places, flat columniform view window is fixed between supporting disk and forward flange dish and is and closely cooperates; Supporting disk hollow lumen is simulated engine firing chamber, propellant test specimen is placed on hollow lumen, the both sides of propellant test specimen are used two identical wedges of α angle to fix, and by using the wedge at different α angle, regulate the size of free volume between propellant sample and burning chamber shell.
The front end of described forward flange dish is provided with the window of observing burning test specimen, and rear end is provided with the groove identical with view window outside diameter, along forward flange dish is circumferentially uniform four through holes is set.
On the end face that described rear stub and supporting disk join, be provided with two-layer boss, fixed support dish and rear O-ring seal, rear stub other end is plane, along rear stub is circumferentially uniform four through holes is set.
Described wedge cross section is wide at the top and narrow at the bottom, and one side has the trapezoidal shape of degree of tilt, and the thickness of wedge is identical with the thickness of propellant test specimen, and the degree of tilt face of wedge and the side of propellant test specimen form α angle, and wedge α angle is 10 ° to 30 °.
While clamping view window with supporting disk between described forward flange dish and rear stub, use bolt to be connected, and with the center of propellant test specimen on same axis.
Forward flange dish, rear stub, supporting disk are stainless steel material and make, and view window material is quartz glass.
By view window, record crack propagation process, extrapolate the speed of Crack Extension and the relation of time,
The principle that apparatus of the present invention realize Crack Extension situation test under cold air pressurising condition is: in testing experiment, make simulated engine firing chamber approach as far as possible the truth of engine chamber.The initial crack of prefabricated certain length on the propellant test specimen adopting; By controlling the diameter of storage pressure, air intake valve and throttling orifice plate, control by rate of pressure rise and maximum pressure in supporting disk and the formed cavity of test specimen arc-shaped surface.During test, propellant test specimen both sides and bottom surface are fixed, and high pressure draught enters cavity, and the pressure in cavity sharply rises, thereby make the initial crack expansion on test specimen.
The principle that apparatus of the present invention realize Crack Extension situation test under propellant combustion condition is: in testing experiment, make simulated engine firing chamber approach as far as possible the truth of engine chamber.The initial crack of prefabricated certain length on the propellant test specimen adopting in simulated combustion chamber; By controlling the size of igniter pad and the diameter of throttling orifice plate, control the rate of pressure rise in cavity.Propellant test specimen both sides and bottom surface are fixed, and supercharging after instantaneous ignition is lighted propellant and taken fire, and the pressure in cavity sharply rises, thereby make the initial crack expansion on test specimen.
In above two kinds of tests, in the cavity of the propellant test specimen both sides in simulated combustion chamber, place wedge, by using the wedge at different α angle, regulate the size of free volume between propellant test specimen and supporting disk shell wall face, carry out the rigidity of Reality simulation motor body to propellant charge constraint.
Beneficial effect
Crack extension tester for solid propellant of the present invention, by changing the different wedge in angle of inclination, realizes the repeatedly adjusting of Crack Extension free volume; Pass into nitrogen and realize the test of Crack Extension situation under cold air pressurising condition; Increase igniter pad and igniter pad wire, realize the test of Crack Extension situation under propellant combustion condition.Test unit is workable, can obtain respectively two groups of test figures under cold air pressurising condition and propellant combustion condition, makes test figure more fully full and accurate; Between propellant test specimen and supporting disk wall, the adjusting of free volume is simple, only needs to place the wedge of differing tilt angles, do not need to make the supporting disk of different free volumes.Apparatus of the present invention are simple in structure, handling safety is reliable, be specially adapted to simulate pressurization in solid propellant rocket igniting after-burner, observation Crack Growth In Solid Propellants situation, the test of research Crack Growth In Solid Propellants Changing Pattern and influence factor thereof.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, crack extension tester for solid propellant of the present invention is described in further detail.
Fig. 1 is the structural representation of crack extension tester for solid propellant of the present invention.
Fig. 2 is the schematic diagram of simulated engine of the present invention firing chamber.
Fig. 3 is wedge position view.
Fig. 4 is supporting disk schematic diagram of the present invention.
Fig. 5 is supporting disk left view of the present invention.
Fig. 6 is forward flange dish schematic diagram of the present invention.
Fig. 7 is rear stub schematic diagram of the present invention.
In figure:
1. front O-ring seal 9. supporting disk wall 10. wedges of rear O-ring seal 2. rear stub 3. welding tip 4. forward flange dish 5. supporting disk 6. view window 7. propellant test specimen 8.
Embodiment
The present embodiment is a kind of crack extension tester for solid propellant.Comprise rear O-ring seal 1, rear stub 2, welding tip 3, forward flange dish 4, supporting disk 5, view window 6, propellant test specimen 7, front O-ring seal 8, supporting disk wall 9, wedge 10.
Fig. 1 is the structural drawing of crack extension tester for solid propellant of the present invention.The supporting disk 5 of test unit is hollow oblate cylindricality, the hollow lumen that front and back connect is two big or small frame structures of stack up and down, the top of supporting disk 5 is provided with two round tube holes that communicate with hollow lumen, two round tube holes structure that is in the shape of the letter V, on two round tube holes, welding tip is installed, two welding tips are connected with throttling orifice plate with solenoid valve separately, the annular groove of O-ring seal before the front end face of supporting disk 5 is provided with and places, flat columniform view window 6 is fixed between supporting disk and forward flange dish 4 and is and closely cooperates; Supporting disk 5 hollow lumen are simulated engine firing chamber, propellant test specimen 7 is placed on the hollow lumen of supporting disk 5, the both sides of propellant test specimen 7 are used two identical wedges 10 of α angle to fix, by using the wedge at different α angle, regulate the size of free volume between propellant test specimen and burning chamber shell.
The front end of forward flange dish 4 is provided with the window of observing burning test specimen, and rear end is provided with the groove identical with view window outside diameter, along forward flange dish 4 is circumferentially uniform four through holes is set, as shown in Figure 6.
On the end face that rear stub 2 and supporting disk join, be provided with two-layer boss, fixed support dish 5 and rear O-ring seal 1, rear stub other end is plane, along rear stub 2 is circumferentially uniform four through holes is set, as shown in Figure 7.
Referring to Fig. 2, Fig. 3 wedge cross section, be wide at the top and narrow at the bottom, one side has the trapezoidal shape of degree of tilt, the thickness of wedge 10 is identical with the thickness of propellant test specimen 7, and the degree of tilt face of wedge 10 and the side of propellant test specimen form α angle, and wedge α angle is 10 ° to 30 °.
As shown in Figure 4, Figure 5, on the propellant test specimen 7 adopting, use the initial crack of the prefabricated certain length of pocket knife.By the size of reference mark thermoelectricity lotus and the larynx footpath of throttling orifice plate, control rate of pressure rise.In test, sample both sides and bottom surface are fixed, and after igniting, propellant takes fire, and the pressure in cavity sharply rises, thereby make the initial crack expansion on sample.In above two kinds of tests, in the cavity of propellant sample both sides, place wedge, by using the wedge 10 at different α angle, regulate the size of free volume between propellant test specimen 7 and booster chamber's housing, the rigidity of Reality simulation motor body to propellant charge constraint.
Its assembling process of crack extension tester for solid propellant of the present invention is as follows:
(1) discoid rear stub 2 is kept flat, assemble the supporting disk 5 of hollow cylinder thereon, hollow parts is simulated engine firing chamber, and its inner propellant test specimen 7 of placing containing welding tip 3, seals with rear O-ring seal 1 on it between the two;
(2) front O-ring seal 8 is assemblied in to the shown position in supporting disk 5, the propellant test specimen 7 of making is inserted to the inner chamber (being simulated engine firing chamber) of supporting disk 5 simultaneously, appropriate location in supporting disk, then fixes the both sides of test specimen with two wedges;
(3) columniform view window 6 is closely cooperated and is assemblied in the groove of supporting disk 5, and suitable compression;
(4) assemble discoid forward flange dish 4, compress forward flange dish 4, rear stub, both are connected with bolt, tighten and guarantee non-loosening.
Experiment process under cold air condition:
The some propellant test specimens 7 of Mold Making by definite shape, crackle in the prefabricated certain length size of groove middle position of propellant test specimen 7, get wherein one and insert in booster chamber, in its both sides, place a pair of wedge 10, then complete the assembling of a whole set of test unit; After having assembled, be required to be the supporting air supply system of test unit during cold air pressurising test, at the air flow inlet place of cold air pressurising, connect solenoid valve, air flow outlet connects upward pressure sensor and throttling orifice plate.Open solenoid valve, complete Plenum Process.
Experiment process under burning condition:
The some propellant test specimens of Mold Making by definite shape, at the crackle of the prefabricated certain length size of groove middle position of all samples, get wherein one and insert in booster chamber, in its both sides, place a pair of wedge 10, connect firing circuit, then complete the assembling of a whole set of test unit; During propellant combustion test, need, on the basis of cold air pressurising test unit, in by supporting disk and the formed cavity of test specimen arc-shaped surface, place igniter pad, and draw igniter pad wire, make solenoid valve in closed condition, lead fire cartridge bag, completes burning test.
Observe the expansion process of initial crack on the captured propellant sample of high-speed camera, and record the feature of Crack Extension; Change the igniting size of electric charge, the larynx footpath of throttling orifice plate and the degree of tilt of wedge, do contrast test, record test figure.
Claims (5)
1. a crack extension tester for solid propellant, comprise forward flange dish, rear stub, supporting disk, welding tip, view window, front O-ring seal, rear O-ring seal, propellant test specimen and wedge, it is characterized in that: described supporting disk is hollow oblate cylindricality, the hollow lumen that front and back connect is two big or small frame structures of stack up and down, the top of supporting disk is provided with two round tube holes that communicate with hollow lumen, two round tube holes structure that is in the shape of the letter V, on two round tube holes, welding tip is installed, two welding tips are connected with throttling orifice plate with solenoid valve separately, the annular groove of O-ring seal before the front end face of supporting disk is provided with and places, flat columniform view window is fixed between supporting disk and forward flange dish and is and closely cooperates, supporting disk hollow lumen is simulated engine firing chamber, propellant test specimen is placed on hollow lumen, the both sides of propellant test specimen are used two identical wedges of α angle to fix, and by using the wedge at different α angle, regulate the size of free volume between propellant sample and burning chamber shell.
2. crack extension tester for solid propellant according to claim 1, it is characterized in that: the front end of described forward flange dish is provided with the window of observing burning test specimen, rear end is provided with the groove identical with view window outside diameter, along forward flange dish is circumferentially uniform four through holes is set.
3. crack extension tester for solid propellant according to claim 1, it is characterized in that: on the end face that described rear stub and supporting disk join, be provided with two-layer boss, fixed support dish and rear O-ring seal, rear stub other end is plane, along rear stub is circumferentially uniform four through holes is set.
4. crack extension tester for solid propellant according to claim 1, it is characterized in that: described wedge cross section is wide at the top and narrow at the bottom, one side has the trapezoidal shape of degree of tilt, the thickness of wedge is identical with the thickness of propellant test specimen, the degree of tilt face of wedge and the side of propellant test specimen form α angle, and wedge α angle is 10 ° to 30 °.
5. crack extension tester for solid propellant according to claim 1, is characterized in that: while clamping view window with supporting disk between described forward flange dish and rear stub, use bolt to be connected, and with the center of propellant test specimen on same axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110274590.3A CN102426215B (en) | 2011-09-15 | 2011-09-15 | Solid propellant crack expansion testing apparatus |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110274590.3A CN102426215B (en) | 2011-09-15 | 2011-09-15 | Solid propellant crack expansion testing apparatus |
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| CN102426215A CN102426215A (en) | 2012-04-25 |
| CN102426215B true CN102426215B (en) | 2014-04-16 |
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| CN104502397B (en) * | 2014-12-31 | 2017-07-21 | 河南理工大学 | A kind of visualization coal sample tank being used under high pressure low temperature environment and its application method |
| CN105067523B (en) * | 2015-08-03 | 2017-09-15 | 南京理工大学 | A kind of Flame of Solid Propellant segmenting device |
| CN106840012A (en) * | 2015-12-07 | 2017-06-13 | 上海新力动力设备研究所 | A kind of strengthen the hair powder charge II interface strain measuring methods based on grating sensing technique |
| CN111077268A (en) * | 2019-12-09 | 2020-04-28 | 上海新力动力设备研究所 | Inspection platform and method for coating quality of liquid heat insulating layer of solid engine |
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Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US6662629B2 (en) * | 2002-04-12 | 2003-12-16 | Atlantic Research Corporation | Propellant test apparatus and method |
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|---|---|---|---|---|
| US4130011A (en) * | 1977-06-14 | 1978-12-19 | The United States Of America As Represented By The Secretary Of The Air Force | Flared sonic end nozzle velocity coupling test burner |
| CN101581649A (en) * | 2009-04-07 | 2009-11-18 | 西安近代化学研究所 | Test device for combustion temperature of solid propellant |
| CN101650358A (en) * | 2009-09-17 | 2010-02-17 | 西安近代化学研究所 | Gunpowder combustion property test device under pressure reduction condition |
| CN202256282U (en) * | 2011-09-15 | 2012-05-30 | 西北工业大学 | Crack extension tester for solid propellant |
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Inventor after: Hu Songqi Inventor after: Liu Yingji Inventor after: Wu Suli Inventor after: Zhang Yan Inventor before: Liu Songqi Inventor before: Liu Yingji Inventor before: Wu Suli |
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