CN104374864B - Propellant burning velocity testing device under a kind of extended state - Google Patents
Propellant burning velocity testing device under a kind of extended state Download PDFInfo
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- CN104374864B CN104374864B CN201410598238.9A CN201410598238A CN104374864B CN 104374864 B CN104374864 B CN 104374864B CN 201410598238 A CN201410598238 A CN 201410598238A CN 104374864 B CN104374864 B CN 104374864B
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Abstract
The invention discloses propellant burning velocity testing device under a kind of extended state, for measuring propellant combustion law in a stretched state.Constant temperature and pressure case is fixed on Working gantry, is filled with heat-insulation layer between constant temperature and pressure case inside and outside wall, and have symmetrical attemperater inside heat-insulation layer, propellant stretching device is fixed in constant temperature and pressure case; Nitrogen cylinder is positioned at Working gantry side, and nitrogen cylinder and constant temperature and pressure case pass through pipeline connection.By heating or cooling the temperature controlled in constant temperature and pressure case, the propellant burning rate of extended state under realization test different temperatures; By in the high-pressure inert gas of nitrogen cylinder input constant temperature and pressure case, pressure in regulating thermostatic constant voltage case, under making it be fixed on given pressure, realizes the propellant burning rate of the extended state of the different pressure of test; The amount of tension of restrained stretching screw rod controls the amount of tension of propellant, the combustion speed of propellant under realization test different stretch state.Proving installation structure is simple, and cost is low, easy for installation.
Description
Technical field
The invention belongs to Solid Rocket Motor Technology field, specifically, relate to propellant burning velocity testing device under a kind of extended state.
Background technology
Solid propellant grain is power source in solid propellant rocket, is again one of its structure member, therefore, the internal ballistics attributes of engine and the architectural characteristic of propellant charge closely related.When solid propellant grain bears external load function, because its stretch modulus is low, there will be large distortion, engine pressure, thrust, working time, total punching etc. can change, and all change relevant with solid propellant combustion rate, fire fast variable effect engine interior combustion gas production rate, thus affect engine internal ballistics attributes.Combustion speed engineering measuring solid propellant has diverse ways, the most generally uses by undersized propellant medicinal strip Specimen Determination combustion speed in Burning velometer, namely traditional target collimation method.A kind of Burning rate testing method of ordinary solid propellant is disclosed in document GJB770A-97 (GJB770B-2005) method 706 " firing fast target collimation method ", its principle is: the boring of coated propellant medicinal strip sample is penetrated target line, under the testing pressure and temperature of regulation, in nitrogen, measure the time needed for after-flame test specimen range length, calculate combustion speed.
The stretching experiment of propellant mostly carries out on the cupping machine having temperature control equipment, for uniaxial stress, instead of the triaxiality of complexity, test specimen generally uses end amonang sample or dumbbell specimen, does the tension test of each rate of extension at each temperature of regulation.
Summary of the invention
In order to avoid the deficiency that prior art exists, the present invention proposes propellant burning velocity testing device under a kind of extended state; By controlling the temperature in constant temperature and pressure case, pressure in regulating thermostatic constant voltage case, the amount of tension of restrained stretching screw rod controls the amount of tension of propellant, realizes test different temperatures, different pressure, the combustion speed of propellant under different stretch state; Test propellant combustion law in a stretched state.
The technical solution adopted for the present invention to solve the technical problems is: comprise constant temperature and pressure case, nitrogen cylinder, propellant stretching device, Working gantry, be characterized in: constant temperature and pressure case is fixed on Working gantry, fill insulant material between constant temperature and pressure case inside and outside wall, two attemperaters lay respectively at inside constant temperature and pressure case adiabator layer, two attemperaters are respectively equipped with water inlet and water delivering orifice, wherein, an attemperater is provided with temperature-measuring port, nitrogen cylinder is positioned at Working gantry side, nitrogen cylinder is connected by pipeline with constant temperature and pressure case, stretching device is positioned at constant temperature and pressure case, be connected by fixed head and constant temperature and pressure case upper end cover, described stretching device comprises base plate, upper plate, stretching screw rod, positioning screw, upper plate ceiling molding, press strip under upper plate, floor strip, upper rail plate, lower guideway plate, measured hole, contiguous block, upper plate and base plate are connected, positioning screw is positioned at base plate one end, floor strip and lower guideway plate are fastened on base plate, lower guideway plate and base plate are located by positioning screw, under upper plate, press strip and lower guideway plate are connected by bolt, stretching screw rod is positioned at the side of positioning screw, stretching screw rod is connected with contiguous block, contiguous block is connected with upper rail plate, upper plate ceiling molding and upper rail plate are connected by bolt, upper plate ceiling molding and floor strip are respectively equipped with measured hole, for target link testing device, floor strip, upper plate ceiling molding coordinates fixing propellant sample with press strip under upper plate, turn stretching screw rod, upper rail plate moves on the track of base plate, realize the loading to propellant sample stress, and carry out Burning rate testing.
Press strip under upper plate ceiling molding, upper plate, floor strip, upper rail plate, lower guideway plate and contiguous block material all adopt stainless steel.
Beneficial effect
Propellant burning velocity testing device under a kind of extended state that the present invention proposes, for measuring propellant combustion law in a stretched state.The temperature in constant temperature and pressure case is controlled, the propellant burning rate of extended state under realization test different temperatures by heating or cooling device; Be connected with the nitrogen cylinder of high-pressure inert gas by constant temperature and pressure case, pressure in regulating thermostatic constant voltage case, under making it be fixed on given pressure, realizes the propellant burning rate of the extended state of the different pressure of test; The amount of tension of restrained stretching screw rod controls the amount of tension of propellant, the combustion speed of propellant under realization test different stretch state.Proving installation structure is simple, and cost is low, conveniently process installation.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, propellant burning velocity testing device under a kind of extended state of the present invention is described in further detail.
Fig. 1 is propellant burning velocity testing device schematic diagram under extended state of the present invention.
Fig. 2 is propellant stretching device schematic diagram of the present invention.
Fig. 3 is propellant stretching device left view of the present invention.
Fig. 4 is propellant stretching device A-A cross-sectional view of the present invention.
Fig. 5 is propellant style schematic diagram.
Fig. 6 is propellant style B-B cross-sectional view.
Fig. 7 is propellant sample position of opening schematic diagram.
C-C: igniting the string holes D-D: the first target string holes E-E: the second target string holes
In figure:
1. constant temperature and pressure case 2. nitrogen cylinder 3. stretching device 4. Working gantry 5. temperature-measuring port 6. water inlet 7. water delivering orifice 8. fixed head 9. base plate 10. upper plate 11. stretches press strip 15. floor strip 16. upper rail plate 17. lower guideway plate 18. propellant sample 19. measured hole 20. contiguous block under screw rod 12. positioning screw 13. upper plate ceiling molding 14. upper plate
Embodiment
The present embodiment is propellant burning velocity testing device under a kind of extended state.
Consult Fig. 1 ~ Fig. 7, propellant burning velocity testing device under the present embodiment extended state, be made up of constant temperature and pressure case 1, nitrogen cylinder 2, stretching device 3, Working gantry 4; Constant temperature and pressure case 1 is fixed on Working gantry 4, nitrogen cylinder 2 is arranged on Working gantry 4 side, nitrogen cylinder 2 is connected by pipeline with constant temperature and pressure case 1, nitrogen cylinder 2 is provided with tensimeter, during work, high-pressure inert gas in nitrogen cylinder 2 transfers in constant temperature and pressure case 1 snubber assembly, ensures the pressure reaching setting in constant temperature and pressure case 1.Fill insulant material between constant temperature and pressure case 1 inside and outside wall, to ensure temperature substantially constant; Two attemperaters are separately installed with inside constant temperature and pressure case 1 adiabator layer, attemperater is bolted on constant temperature and pressure case 1, two attemperaters are respectively equipped with water inlet 6 and water delivering orifice 7, wherein, an attemperater is provided with temperature-measuring port 5, temperature-measuring port 5, in order to measure the temperature in attemperater, ensures temperature substantially constant.Stretching device 3 is arranged in constant temperature and pressure case 1, and fixed head 8 and constant temperature and pressure case upper end cover are connected by bolt, and stretching device 3 and fixed head 8 are bolted.
Stretching device comprises press strip 14, floor strip 15, upper rail plate 16, lower guideway plate 17, measured hole 19, contiguous block 20 under base plate 9, upper plate 10, stretching screw rod 11, positioning screw 12, upper plate ceiling molding 13, upper plate, base plate 9 is arranged on fixed head by bolt, upper plate 10 and base plate 9 are connected, positioning screw 12 is arranged on base plate 9 one end, floor strip 15 and lower guideway plate 17 are fastened on base plate 9, lower guideway plate 17 and base plate 9 are located by positioning screw 12, under upper plate, press strip 14 and lower guideway plate 17 are connected by bolt, stretching screw rod 11 is arranged on the side of positioning screw 12, stretching screw rod 11 is connected with contiguous block 20, contiguous block 20 is connected with upper rail plate 16, upper plate ceiling molding 13 and upper rail plate 16 are connected by bolt, upper plate ceiling molding 13 and floor strip 15 are respectively equipped with measured hole 19, for target link testing device.Floor strip 15, upper plate ceiling molding 13 coordinate fixing propellant sample 18 with press strip under upper plate 14; Propellant sample 18 is processed into I shape, is convenient to utilize draw-in groove to clamp, and meanwhile, propellant sample 18 punches, wears ignition lead and target line.Turn stretching screw rod 11 during work, upper rail plate 16 moves on the track of base plate 9, realizes the loading to propellant sample 18 stress, carries out Burning rate testing experiment, namely obtains the propellant burning rate under extended state certain under setting working temperature and pressure.
Press strip 14 under upper plate ceiling molding 13, upper plate, floor strip 15, upper rail plate 16, lower guideway plate 17 and contiguous block 20 all adopt stainless steel material to make.
Under test different stretch state, the step of propellant burning rate is as follows:
(1) sample processing; Propellant is processed into the thick I-shaped propellant sample 18 of certain meat by design size, and its surface is carried out fire-retardant coated, burn by combustion in parallel layer rule during to ensure that propellant sample 18 burns; According to the requirement that experiment pressure, dependent variable design and collimation are tested, calculate the number of the propellant sample that should process, to ensure, under each pressure, each strained condition, at least to obtain three effective experimental datas;
(2) ignition lead and target line is worn; Whether the whether complete and clad of inspection clad meets requirement of experiment; To the propellant sample be up to the standards, size is punched to propellant sample on request, wears ignition lead and two target lines after measuring the distance between two target string holes on propellant sample; Causing the failure of an experiment to not make target line blow too early, carrying out multilayer coating structure at two target lines near the adiabatic adhesive tape in the place of propellant;
(3) propellant sample is installed; Propellant sample 18 is fixed in draw-in groove, and empirically requires that turn stretching screw rod 11 is with the dependent variable making propellant sample 18 reach predetermined;
(4) igniting and measurement circuit is connected; Ignition lead and two target lines are received on corresponding electrode, checks and guarantee the connection of ignition circuit and measurement circuit;
(5) firing chamber is assembled; The stretching device 3 that propellant sample 18 is housed is fixed on the fixed head 8 in constant temperature and pressure case 1, and checks the impermeability of firing chamber;
(6) pressurising; Close vent valve successively, open isolation valve and carry out valve, opening the reduction valve of nitrogen cylinder 2, in constant temperature and pressure case 1 snubber assembly, be filled with nitrogen to predetermined pressure;
(7) setup test system; Open testing software, set test parameter, and make test macro be in test mode;
(8) light a fire; Ignition lead applies certain voltage, propellant sample 18 is lighted by ignition lead heat release, obtains propellant burning time, calculate propellant burning rate in conjunction with meat is thick;
(9) close testing software, preserve experimental data and clear up experimental provision;
(10) repeat (3) ~ (9), change the dependent variable be applied on propellant sample 18, until often organize experiment to have three valid data at least; Obtain the Changing Pattern of propellant burning rate under different stretch stress.
Claims (2)
1. propellant burning velocity testing device under an extended state, comprise constant temperature and pressure case, nitrogen cylinder, propellant stretching device, Working gantry, it is characterized in that: constant temperature and pressure case is fixed on Working gantry, fill insulant material between constant temperature and pressure case inside and outside wall, two attemperaters lay respectively at inside constant temperature and pressure case adiabator layer, two attemperaters are respectively equipped with water inlet and water delivering orifice, wherein, an attemperater is provided with temperature-measuring port, nitrogen cylinder is positioned at Working gantry side, nitrogen cylinder is connected by pipeline with constant temperature and pressure case, stretching device is positioned at constant temperature and pressure case, be connected by fixed head and constant temperature and pressure case upper end cover, described stretching device comprises base plate, upper plate, stretching screw rod, positioning screw, upper plate ceiling molding, press strip under upper plate, floor strip, upper rail plate, lower guideway plate, measured hole, contiguous block, upper plate and base plate are connected, positioning screw is positioned at base plate one end, floor strip and lower guideway plate are fastened on base plate, lower guideway plate and base plate are located by positioning screw, under upper plate, press strip and lower guideway plate are connected by bolt, stretching screw rod is positioned at the side of positioning screw, stretching screw rod is connected with contiguous block, contiguous block is connected with upper rail plate, upper plate ceiling molding and upper rail plate are connected by bolt, upper plate ceiling molding and floor strip are respectively equipped with measured hole, for connecting test target line, floor strip, upper plate ceiling molding coordinates fixing propellant sample with press strip under upper plate, turn stretching screw rod, upper rail plate moves on the track of base plate, realize the loading to propellant sample stress, and carry out Burning rate testing.
2. propellant burning velocity testing device under extended state according to claim 1, is characterized in that: under upper plate ceiling molding, upper plate, press strip, floor strip, upper rail plate, lower guideway plate and contiguous block material all adopt stainless steel.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410598238.9A CN104374864B (en) | 2014-10-30 | 2014-10-30 | Propellant burning velocity testing device under a kind of extended state |
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| CN201410598238.9A CN104374864B (en) | 2014-10-30 | 2014-10-30 | Propellant burning velocity testing device under a kind of extended state |
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| CN104374864B true CN104374864B (en) | 2016-04-27 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105617945B (en) * | 2016-02-20 | 2018-08-17 | 宋波 | The operational devices of high pressure gas |
| CN106567792B (en) * | 2016-10-27 | 2018-09-07 | 上海新力动力设备研究所 | The device of solid rocket motor grain axial displacement in a kind of measurement ejection process |
| CN107656031B (en) * | 2016-12-12 | 2020-04-14 | 湖北航天化学技术研究所 | High-pressure gas impact loading safety performance testing method for energetic material |
| CN109708145B (en) * | 2019-01-29 | 2020-02-11 | 北京理工大学 | Visual high-pressure combustor for measuring propellant burning speed under multiple swinging angles |
| CN113687013B (en) * | 2021-07-30 | 2022-07-05 | 西北工业大学 | Device for shooting solid propellant combustion test under overload condition |
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| CN1873411A (en) * | 2005-06-03 | 2006-12-06 | 中国科学院力学研究所 | Device for testing deflagrability of condensed fire detonator under condition of high termerature and high pressure |
| CN101509908A (en) * | 2009-01-09 | 2009-08-19 | 北京科技大学 | Combustible burning rate test device in plateau artificial oxygen-enriched environment |
| CN202075268U (en) * | 2011-05-23 | 2011-12-14 | 广东出入境检验检疫局检验检疫技术中心 | Gas fire test device |
| CN103076426A (en) * | 2012-12-20 | 2013-05-01 | 福建中烟工业有限责任公司 | Tobacco combustion device |
| CN103675321A (en) * | 2013-12-11 | 2014-03-26 | 哈尔滨工程大学 | Visualization aluminum ice solid propellant burning rate test system |
| CN104020250A (en) * | 2014-06-24 | 2014-09-03 | 西安近代化学研究所 | Propellant powder volume variation combustion speed testing device |
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2014
- 2014-10-30 CN CN201410598238.9A patent/CN104374864B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1873411A (en) * | 2005-06-03 | 2006-12-06 | 中国科学院力学研究所 | Device for testing deflagrability of condensed fire detonator under condition of high termerature and high pressure |
| CN101509908A (en) * | 2009-01-09 | 2009-08-19 | 北京科技大学 | Combustible burning rate test device in plateau artificial oxygen-enriched environment |
| CN202075268U (en) * | 2011-05-23 | 2011-12-14 | 广东出入境检验检疫局检验检疫技术中心 | Gas fire test device |
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