CN102426215A - Solid propellant crack expansion testing apparatus - Google Patents
Solid propellant crack expansion testing apparatus Download PDFInfo
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- CN102426215A CN102426215A CN2011102745903A CN201110274590A CN102426215A CN 102426215 A CN102426215 A CN 102426215A CN 2011102745903 A CN2011102745903 A CN 2011102745903A CN 201110274590 A CN201110274590 A CN 201110274590A CN 102426215 A CN102426215 A CN 102426215A
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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 that is used for the solid propellant rocket propellant, specifically, relate to a kind of solid propellant crack expanding test device.Belong to solid propellant rocket and experimental facilities field thereof, be applicable to pressurization in the simulation solid propellant rocket igniting after-burner, the test of observational study solid propellant crack expansion Changing Pattern and influence factor thereof.
Background technology
The solid propellant rocket propellant owing to receive various stress, can crack in production and ignition process.Crackle has significant impact to the combustion characteristics of solid propellant, might blast under the extreme case.At present, both at home and abroad the 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; When having introduced the crack propagation that causes in the research burning RSRMTP-H1148 Main Grain Propellant Crack Initiation Evaluation [R] .AIAA 2005-3601.); A cover high speed video system that adopts, it comprises simulated engine firing chamber, data-acquisition system and firing system three parts.The simulated engine firing chamber is the cylindrical system of an end band transparent organic glass window, and data-acquisition system comprises pressure-measuring system and imaging system.Different crack propagation free volume correspondence propellant test specimen supporting disk separately in this test unit will be the contrast experiment and must change supporting disk, and this can impact impermeability of test unit, and complicated operation.
At document " experimental study and the theoretical analysis [D] of expansion condition during the solid propellant crack burning. " (naval aviation engineering college Master's thesis; 1999.), " research [D] of solid propellant crack burning and expansion. " (naval aviation engineering college Master's thesis; 2000.), " experimental study [J] that propulsion charge crackle internal combustion flows. " (" Push Technology " 2000,21 (5): the mostly employing X ray high-speed real-time fluorescent screen analytic system of introducing 58-60.) (RTR) is as the test macro of crack expansion test.X ray high-speed real-time fluorescent screen analytic system (RTR) is a kind of contactless experimental facilities of studying opaque high-pressure burner or engine interior complex work process, and this system is made up of x ray generator, test engine, high speed video recording system, time controlled system, data acquisition system (DAS), high-speed motion analyser.Its groundwork principle is to utilize the x-ray imaging principle to absorb the course of work of engine interior, utilizes pressure transducer also can obtain pressure-time curve simultaneously.Adopt along the uniform rectangle engine of X ray direction thickness to obtain the background uniform image in this device.But this experimental provision can only carry out the crack propagation experiment under the propellant combustion condition, can not carry out the experiment under the cold air pressurising condition, and the experimental data that provides is abundant inadequately, with the engine actual operating conditions a certain distance is arranged.
Summary of the invention
In order to overcome experiment structure operation complicacy in the prior art; The deficiency that the crack propagation experiment condition is single; The present invention proposes a kind of solid propellant crack expanding test device; This crack expansion test device is realized the repeatedly adjusting of crack propagation free volume through changing the different wedge in angle of inclination; Feed nitrogen and realize the test of crack propagation situation under the cold air pressurising condition; Increase igniter pad and igniter pad lead, realize the test of crack propagation situation under the propellant combustion condition; This apparatus structure is simple, and handling safety is reliable.
The present invention solves its technical matters, and the technical scheme that is adopted is: the crack expansion test device comprises forward flange dish, rear stub, supporting disk, welding tip, view window, preceding O-ring seal, back O-ring seal, propellant test specimen and wedge composition.
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 is equipped with welding tip on two round tube holes, and 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, the view window of oblate cylindricality is fixed on to be between supporting disk and the forward flange dish and closely cooperates; The supporting disk hollow lumen is the simulated engine firing chamber; The propellant test specimen is placed on hollow lumen; The both sides of propellant test specimen use two identical wedges of α angle to fix, and through 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 the burning test specimen, and the rear end is provided with the groove identical with the view window outside diameter, circumferentially is uniformly distributed with along the forward flange dish four through holes are set.
The end face that described rear stub and supporting disk join is provided with two-layer boss, fixing branch support plate and back O-ring seal, and the rear stub other end is the plane, circumferentially is uniformly distributed with along rear stub four through holes are 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 the α angle, and wedge α angle is 10 ° to 30 °.
The use bolt is connected when clamping view window with supporting disk between described forward flange dish and the rear stub, and with the center of propellant test specimen on same axis.
Forward flange dish, rear stub, supporting disk are stainless steel material and process, and the view window material is a quartz glass.
Note crack propagation process through view window, extrapolate the speed and the time relation of crack propagation,
Apparatus of the present invention realize that crack propagation situation testing principle is under the cold air pressurising condition: in testing experiment, make the simulated engine firing chamber as far as possible near the truth of engine chamber.The initial crack of prefabricated certain-length on the propellant test specimen that is adopted; Diameter through control storage pressure, air intake valve and throttling orifice plate is controlled by rate of pressure rise and maximum pressure in supporting disk and the formed cavity of test specimen arc-shaped surface.Propellant test specimen both sides and bottom surface are fixed during test, and high pressure draught gets into cavity, and the pressure in the cavity sharply rises, thereby make the initial crack expansion on the test specimen.
Apparatus of the present invention realize that crack propagation situation testing principle is under the propellant combustion condition: in testing experiment, make the simulated engine firing chamber as far as possible near the truth of engine chamber.The initial crack of prefabricated certain-length on the propellant test specimen of simulated combustion chamber employing; Control the rate of pressure rise in the cavity through the size of control ignition cartridge bag and the diameter of throttling orifice plate.Propellant test specimen both sides and bottom surface are fixed, and supercharging behind the instantaneous ignition is lighted propellant and taken fire, and the pressure in the cavity sharply rises, thereby make the initial crack expansion on the test specimen.
In above two kinds of tests; Place wedge in the cavity of the propellant test specimen both sides in the simulated combustion chamber; Through using the wedge at different α angle, regulate the size of free volume between propellant test specimen and supporting disk shell wall face, simulate the rigidity of true motor body to the propellant charge constraint.
Beneficial effect
Solid propellant crack expanding test device of the present invention through changing the different wedge in angle of inclination, is realized the repeatedly adjusting of crack propagation free volume; Feed nitrogen and realize the test of crack propagation situation under the cold air pressurising condition; Increase igniter pad and igniter pad lead, realize the test of crack propagation situation under the propellant combustion condition.Test unit is workable, can obtain two groups of test figures under cold air pressurising condition and the propellant combustion condition respectively, makes test figure more fully full and accurate; The adjusting of free volume is simple between propellant test specimen and supporting disk wall, and a wedge that only needs to place differing tilt angles gets final product, and need not 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 the solid propellant rocket igniting after-burner, observation solid propellant crack spread scenarios, the test of research solid propellant crack expansion Changing Pattern and influence factor thereof.
Description of drawings
Below in conjunction with accompanying drawing and embodiment solid propellant crack expanding test device of the present invention is done further explain.
Fig. 1 is the structural representation of solid propellant crack expanding test device of the present invention.
Fig. 2 is the synoptic diagram of simulated engine of the present invention firing chamber.
Fig. 3 is the wedge position view.
Fig. 4 is a supporting disk synoptic diagram of the present invention.
Fig. 5 is a supporting disk left view of the present invention.
Fig. 6 is a forward flange dish synoptic diagram of the present invention.
Fig. 7 is a rear stub synoptic diagram of the present invention.
Among the figure:
1. O-ring seal 9. supporting disk walls 10. wedges before the O-ring seal 2. rear stub 3. welding tips 4. forward flange dishes 5. supporting disks 6. view windows 7. propellant test specimens 8. after
Embodiment
Present embodiment is a kind of solid propellant crack expanding test device.Comprise back O-ring seal 1, rear stub 2, welding tip 3, forward flange dish 4, supporting disk 5, view window 6, propellant test specimen 7, preceding O-ring seal 8, supporting disk wall 9, wedge 10.
Fig. 1 is the structural drawing of solid propellant crack expanding test device 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 is equipped with welding tip on two round tube holes, and 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, the view window 6 of oblate cylindricality is fixed on to be between supporting disk and the forward flange dish 4 and closely cooperates; Supporting disk 5 hollow lumen are the 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 use two identical wedges 10 of α angle to fix; Through 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 the burning test specimen, and the rear end is provided with the groove identical with the view window outside diameter, circumferentially is uniformly distributed with along forward flange dish 4 four through holes are set, and is as shown in Figure 6.
Be wide at the top and narrow at the bottom referring to Fig. 2, Fig. 3 wedge cross section; 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 the α angle, and wedge α angle is 10 ° to 30 °.
Like Fig. 4, shown in Figure 5, on the propellant test specimen 7 that is adopted with the initial crack of the prefabricated certain-length of pocket knife.Directly control rate of pressure rise through the size of control ignition electric charge and the larynx of throttling orifice plate.In the test, sample both sides and bottom surface are fixed, and after the igniting, propellant takes fire, and the pressure in the cavity sharply rises, thereby make the initial crack expansion on the sample.In above two kinds of tests; In the cavity of propellant sample both sides, place wedge; Through using the wedge 10 at different α angle, regulate the size of free volume between propellant test specimen 7 and booster chamber's housing, simulate the rigidity of true motor body to the propellant charge constraint.
Its assembling process of solid propellant crack expanding test device of the present invention is following:
(1) discoid rear stub 2 is kept flat, assemble the supporting disk 5 of hollow cylinder above that, hollow parts is the simulated engine firing chamber, and its inner propellant test specimen 7 of placing contains welding tip 3 on it, between the two with 1 sealing of back O-ring seal;
(2) preceding O-ring seal 8 is assemblied in the shown position in the supporting disk 5, simultaneously the propellant test specimen of making 7 is inserted the inner chamber (being the simulated engine firing chamber) of supporting disk 5, the appropriate location in the supporting disk is fixed the both sides of test specimen with two wedges then;
(3) columniform view window 6 is closely cooperated be assemblied in the groove of supporting disk 5, and suitable compressing;
(4) the discoid forward flange dish 4 of assembling compresses forward flange dish 4, rear stub, and both are connected with bolt, tightens and guarantees non-loosening.
Experiment process under the cold air condition:
With the some propellant test specimens 7 of the Mold Making of definite shape; Crackle in the prefabricated certain-length size of the groove middle position of propellant test specimen 7; Get wherein one and insert in the booster chamber, place a pair of wedge 10 in its both sides, accomplish the assembling of a whole set of test unit then; After assembling is accomplished, be required to be the supporting air supply system of test unit during cold air pressurising test, the magnet valve that Connects Power at the air flow inlet place of cold air pressurising, air flow outlet connects upward pressure sensor and throttling orifice plate.Open solenoid valve, accomplish the pressurising process.
Experiment process under the burning condition:
With the some propellant test specimens of the Mold Making of definite shape; At the crackle of the prefabricated certain-length of the groove middle position of all samples size, get wherein one and insert in the booster chamber, place a pair of wedge 10 in its both sides; Connect firing circuit, accomplish the assembling of a whole set of test unit then; During the 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, to place igniter pad; And draw the igniter pad lead; Make solenoid valve be in closed condition, the igniter pad that ignites is accomplished burning test.
Observe the expansion process of initial crack on the captured propellant sample of high-speed camera, and the characteristics of record crack propagation; Change the size of igniting electric charge, the larynx footpath of throttling orifice plate and the degree of tilt of wedge, do contrast test, the record test figure.
Claims (5)
1. solid propellant crack expanding test device; Comprise forward flange dish, rear stub, supporting disk, welding tip, view window, preceding O-ring seal, back O-ring seal, propellant test specimen and wedge; It is characterized in that: described supporting disk is hollow oblate cylindricality; Before and after the hollow lumen that connects be 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, and the view window of oblate cylindricality is fixed on to be between supporting disk and the forward flange dish and closely cooperates; The supporting disk hollow lumen is the simulated engine firing chamber; The propellant test specimen is placed on hollow lumen; The both sides of propellant test specimen use two identical wedges of α angle to fix, and through using the wedge at different α angle, regulate the size of free volume between propellant sample and burning chamber shell.
2. solid propellant crack expanding test device according to claim 1; It is characterized in that: the front end of described forward flange dish is provided with the window of observing the burning test specimen; The rear end is provided with the groove identical with the view window outside diameter, circumferentially is uniformly distributed with along the forward flange dish four through holes are set.
3. solid propellant crack expanding test device according to claim 1; It is characterized in that: the end face that described rear stub and supporting disk join is provided with two-layer boss; Fixing branch support plate and back O-ring seal; The rear stub other end is the plane, circumferentially is uniformly distributed with along rear stub four through holes are set.
4. solid propellant crack expanding test device 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, and the degree of tilt face of wedge and the side of propellant test specimen form the α angle, and wedge α angle is 10 ° to 30 °.
5. solid propellant crack expanding test device according to claim 1 is characterized in that: the use bolt is connected when clamping view window with supporting disk between described forward flange dish and the rear stub, and with the center of propellant test specimen on same axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201110274590.3A CN102426215B (en) | 2011-09-15 | 2011-09-15 | Solid propellant crack expansion testing apparatus |
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| CN201110274590.3A CN102426215B (en) | 2011-09-15 | 2011-09-15 | Solid propellant crack expansion testing apparatus |
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| CN102426215A true CN102426215A (en) | 2012-04-25 |
| CN102426215B CN102426215B (en) | 2014-04-16 |
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| CN201110274590.3A Expired - Fee Related CN102426215B (en) | 2011-09-15 | 2011-09-15 | Solid propellant crack expansion testing apparatus |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103575594A (en) * | 2013-11-14 | 2014-02-12 | 哈尔滨工程大学 | Device for testing compression resistance of aluminum ice solid propellant |
| CN104502397A (en) * | 2014-12-31 | 2015-04-08 | 河南理工大学 | Visual coal sample tank used in high-pressure low-temperature environment and using method thereof |
| CN105067523A (en) * | 2015-08-03 | 2015-11-18 | 南京理工大学 | Solid propellant flame segmentation 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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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103575594A (en) * | 2013-11-14 | 2014-02-12 | 哈尔滨工程大学 | Device for testing compression resistance of aluminum ice solid propellant |
| CN104502397A (en) * | 2014-12-31 | 2015-04-08 | 河南理工大学 | Visual coal sample tank used in high-pressure low-temperature environment and using method thereof |
| CN105067523A (en) * | 2015-08-03 | 2015-11-18 | 南京理工大学 | Solid propellant flame segmentation device |
| 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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| CN102426215B (en) | 2014-04-16 |
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