CN102080608B - Head test device of multifunctional solid-liquid hybrid rocket engine - Google Patents
Head test device of multifunctional solid-liquid hybrid rocket engine Download PDFInfo
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- CN102080608B CN102080608B CN 201110001239 CN201110001239A CN102080608B CN 102080608 B CN102080608 B CN 102080608B CN 201110001239 CN201110001239 CN 201110001239 CN 201110001239 A CN201110001239 A CN 201110001239A CN 102080608 B CN102080608 B CN 102080608B
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Abstract
The invention discloses a head test device of a multifunctional solid-liquid hybrid rocket engine, belonging to the technical field of solid-liquid hybrid propulsion. The device comprises two sets of conveying system interfaces, two head cover nozzles, two venture tubes, a two-end cavity head cover, a partitioning jet panel and a solid gunpowder igniting box, wherein the two head cover nozzles are welded on the two-end cavity head cover, the two-end cavity head cover is respectively communicated with head cavities partitioned by a baffle plate in the two-end cavity head cover, the two sets of conveying system interfaces are respectively connected with the two head cover nozzles together, the venture tube is arranged in each head cover nozzle, the solid gunpowder igniting box is fixed on the partitioning jet panel through a bolt, and the partitioning jet panel and the two-end cavity head cover are fixed together through a bolt. The device disclosed by the invention can be directly used in tests of single-thrust working conditions and double-thrust working conditions of the solid-liquid hybrid rocket engine and can also be used for researching the influence of different atomizing effects to the combustion performance of the solid-liquid hybrid rocket engine and researching the ignition delay characteristics of the engine.
Description
Technical field
The present invention relates to hybrid rocket engine experimental technique field, be specifically related to a kind of head test device of multifunctional solid-liquid hybrid rocket.
Background technique
Along with the development of space technology, the solid-liquid hybrid technology more and more receives people's concern.Hybrid motor is to adopt liquid oxidizer and solid-fuelled rocket motor, mainly is comprised of liquid oxidizer supply system and engine main body system.Because its fuel and oxygenant separately store and the source is very extensive, have determined Security and Economy that it is good.Hybrid rocket engine is generally selected the nontoxic pollution-free propellant agent, and the specific impulse of propellant agent combination can be easy to reach the above the average of solid propellant rocket.Owing to these reasons, the solid-liquid hybrid technology is more and more used in-flight in space probe, inferior track commerce.
Under many mission requirementses, need to carry out hybrid motor and become thrust design, on the theory, generally coming all is that flow by changing oxygenant reaches this purpose.And in the existing document, carry out the practical engineering application that hybrid motor becomes thrust design by the flow that changes oxygenant, and the design of corresponding engine head testing apparatus, there is not yet relevant report.
Summary of the invention
The problem to be solved in the present invention is: (1) provides hybrid rocket engine dual thrust head test device; (2) satisfying on the basis of last requirement, this testing apparatus need not made amendment, and can be directly used in single thrust test of hybrid rocket engine routine; (3) provide a research platform, can carry out following research: the spray atomization characteristics is on the research of hybrid rocket engine combustion performance impact, the research of engine ignition lag characteristic; (4) all parts can assemble and remove fast, and sealing is effectively reliable.For the problems referred to above, the invention provides a kind of head test device of multifunctional solid-liquid hybrid rocket.
A kind of head test device of multifunctional solid-liquid hybrid rocket comprises: main road upstream transporting system interface, bypass upstream transporting system interface, main road Venturi tube, bypass Venturi tube, skull connecting-tube nozzle, double end chamber skull, subregion spray panel, solid gunpowder igniter cartridge and bypass blanking cover.
The burning chamber shell of described double end chamber skull, subregion spray panel and motor is bolted to connection; Be provided with a toroidal membrane on the skull of described double end chamber, head cavity is separated into center region and annular edge area, be welded with two skull connecting-tube nozzles on the skull of double end chamber, be communicated with respectively center region and annular edge area, be communicated with in the skull connecting-tube nozzle in zone, annular border area the bypass Venturi tube is installed, and be fixedly connected with by the end of bolt assembly with bypass upstream transporting system interface, in the skull connecting-tube nozzle of connection center region the main road Venturi tube is installed, and is fixedly connected with by the end of bolt assembly with main road upstream transporting system interface.
Described subregion spray panel has one mounting groove for the assembling toroidal membrane at the corresponding position of toroidal membrane; The solid gunpowder igniter cartridge is fixed on the subregion spray panel.Described bypass upstream transporting system interface connects bypass upstream transporting system and receives liquid oxidizer, and main road upstream transporting system interface connects main road upstream transporting system and receives liquid oxidizer; Described bypass blanking cover when single thrust working condition tests, is used for bypass upstream transporting system interface is sealed.
Advantage of the present invention and good effect are:
(1) during the dual thrust working condition tests, in the constant situation of upstream transporting system supply pressure, by selecting the Venturi tube in different larynxs footpath, can realize the regional allocation of hybrid rocket engine flow;
(2) break-make by control bypass upstream transporting system oxygenant valve such as phase I main road, bypass valve are with opening, second stage seals bypass upstream transporting system interface, bypass upstream transporting system valve closes, and can realize the work of motor variable-flow, and then realizes motor dual thrust operating mode;
(3) can study different atomizing diameters to the impact of solid-liquid rocket combustion performance by the spray panel of changing different spray pore size and distributions;
(4) be bolted between subregion spray panel and the solid gunpowder igniter cartridge, easy disassembly can by changing the igniter quantity of igniter cartridge, be studied the startup time-delay characteristics of motor under the different ignition conditions;
(5) the present invention introduces the design philosophy of " subregion control flow " and " subregion control spray atomizing " in the hybrid rocket engine design for the first time, reaches the purpose that realizes complex function.
Description of drawings
Fig. 1 is the structural representation of the head test device of multifunctional solid-liquid hybrid rocket of the present invention;
Fig. 2 is the schematic representation of toroidal membrane in the skull of double end chamber in the testing apparatus of the present invention;
Fig. 3: (a) be the structural representation of the toroidal membrane assembling of subregion spray panel and double end chamber skull; (b) be the schematic representation of spray panel inner ring and outer ring;
Fig. 4: (a) be the structural representation of bypass upstream transporting system interface in the testing apparatus of the present invention; (b) be the structural representation of main road upstream transporting system interface in the testing apparatus of the present invention.
Among the figure:
Embodiment
Further specify the present invention below in conjunction with accompanying drawing.
As shown in Figure 1, the head test device of multifunctional solid-liquid hybrid rocket of the present invention mainly comprises: bypass upstream transporting system interface 2, main road upstream transporting system interface 20, bypass Venturi tube 6, main road Venturi tube 19, skull connecting-tube nozzle 7, double end chamber skull 18, subregion spray panel 17, solid gunpowder igniter cartridge 16 and bypass blanking cover 22.
As shown in Figure 1, multifunctional solid-liquid hybrid rocket head test device of the present invention consists of an integral body take double end chamber skull 18 and subregion spray panel 17 as core.Burning chamber shell 11 is assembled together by gluing with burning heat insulation layer 12, is the assembly that is connected with engine head experimental setup of the present invention on the hybrid rocket engine.Double end chamber skull 18, subregion spray panel 17 are fixedly connected with by bolt 10 with burning chamber shell 11.Be welded with two skull connecting-tube nozzles 7 on the double end chamber skull 18,7 li of two skull connecting-tube nozzles are installed respectively bypass Venturi tube 6 and main road Venturi tube 19, one end of bypass upstream transporting system interface 2, main road upstream transporting system interface 20 each use bolt assembly 5 to be connected with a skull connecting-tube nozzle 7, and adopt o RunddichtringO A3, o RunddichtringO B4 sealing.Solid gunpowder igniter cartridge 16 is fixed on the subregion spray panel 17 by tack cross screw bolt 14, arranges o RunddichtringO C13 between tack cross screw bolt 14 and bolt hole, plays the effect that prevents that liquid oxidizer from revealing.Bypass blanking cover 22 is used for bypass upstream transporting system interface 2 is sealed when single thrust working condition tests.As depicted in figs. 1 and 2, be provided with a toroidal membrane 23 in the double end chamber skull 18, head cavity is separated into two zones, be center region and annular edge area, the skull connecting-tube nozzle 7 that is connected with bypass upstream transporting system interface 2 is communicated with the annular edge area, and the skull connecting-tube nozzle 7 that is connected with main road upstream transporting system interface 20 is communicated with the center region.Be furnished with o RunddichtringO C8 and o RunddichtringO F15 between double end chamber skull 18 and the subregion spray panel 17, be furnished with o RunddichtringO D9 between subregion spray panel 17 and the burning chamber shell 11, play the effect of sealing.
Shown in (a) among Fig. 3, open mounting groove one on the subregion spray panel 17, cooperate with the toroidal membrane 23 of double end chamber skull 18, adopt o RunddichtringO F15 sealing between the two; Zone on the subregion spray panel 17 is divided into spray panel outer ring 29 and spray panel inner ring 30 by the relative position with mounting groove; Shown in (b) among Fig. 3, on spray panel outer ring 29 and spray panel inner ring 30, size according to two stage required thrusts in the dual thrust conditions researching, determine required oxidizer flow rate, determine again spray panel assignment of traffic scheme, and then definite spray area, behind the selected spray orifice aperture, arrange respectively some spray orifices, according to the ejector filler of different tests purpose choice for use different pore size; In addition, the spray orifice of the different spray aperture D of all right choice for use is processed a kind of spray panel such as D from the every 0.1mm of 0.6mm-1.2mm, studies spray atomizing diameter to the impact of hybrid motor combustion performance.
Such as (a) of Fig. 4 and (b), bypass upstream transporting system interface 2 forms identical with the structure of main road upstream transporting system interface 20, all formed with flange 27 by connecting-tube nozzle 24, bellows 25,28, pressing plate 26, pressing plate 26 is actively socketed on the flange 27, connecting-tube nozzle 24 boss and bellows 25, the welding of 28 1 ends, bellows 25,28 the other ends and the welding of flange 27 boss.Bypass bellows 25, main road bellows 28 play the effect of buffering.Main road upstream transporting system interface 20 is usually located at same plane with the outlet of bypass upstream transporting system interface 2, for the consideration of installing, the bypass bellows 25 of bypass upstream transporting system interface 2 slightly is longer than the main road bellows 28 of main road upstream transporting system interface 20.Pressing plate 26 is actively socketed on the flange 27, and is movable, the installation of convenience and skull connecting-tube nozzle 7, and the installation that can avoid bringing because of processing, welding error is to direct problem.Bypass Venturi tube 6 and main road Venturi tube 19 1 ends all stretch in the flange 27, and the other end stretches into respectively in two zones in the double end chamber skull 18.
During the dual thrust working condition tests, bypass upstream transporting system interface 2 connects bypass upstream transporting system 1 and receives liquid oxidizer, and main road upstream transporting system interface 20 connects main road upstream transporting system 21 and receives liquid oxidizer.Liquid oxidizer enters testing apparatus of the present invention from main road upstream transporting system interface 20 and bypass upstream transporting system interface 2, by using bypass Venturi tube 6, the main road Venturi tube 19 in different larynxs footpath, the assignment of traffic of 18 two zoness of different of control double end chamber skull; The break-make of the liquid oxidizer valve by control main road upstream transporting system 1 and bypass upstream transporting system 21, with opening, second stage bypass valve closes such as phase I main road, bypass valve, realizes the work of dual thrust operating mode; During single thrust working condition tests, transporting system interface 1 usefulness bypass blanking cover 20 in bypass upstream is sealed, does not use the annular edge area, and liquid oxidizer only enters the center region, realizes single operating mode work.
As shown in Figure 1, can study different atomizing diameters to the impact of solid-liquid rocket combustion performance by the subregion spray panel 17 of changing different spray pore size and distributions; By changing the igniter quantity of some solid gunpowder gunpowder box 16, can study the startup time-delay characteristics of motor under the different ignition conditions.
Claims (7)
1. the head test device of a multifunctional solid-liquid hybrid rocket, it is characterized in that this testing apparatus mainly comprises bypass upstream transporting system interface (2), main road upstream transporting system interface (20), bypass Venturi tube (6), main road Venturi tube (19), skull connecting-tube nozzle (7), double end chamber skull (18), subregion spray panel (17), solid gunpowder igniter cartridge (16) and bypass blanking cover (22);
Described double end chamber skull (18), subregion spray panel (17) are fixedly connected with by bolt (10) with the burning chamber shell (11) of motor; Be provided with a toroidal membrane (23) on the described double end chamber skull (18), head cavity is separated into center region and annular edge area, be welded with two skull connecting-tube nozzles (7) on the double end chamber skull (18), be communicated with respectively center region and annular edge area, the inner bypass Venturi tube (6) that is equipped with of skull connecting-tube nozzle (7) that is communicated with zone, annular border area, and be fixedly connected with by the end of bolt assembly (5) with bypass upstream transporting system interface (2), the inner main road Venturi tube (19) that is equipped with of skull connecting-tube nozzle (7) that is communicated with the center region, and be fixedly connected with by the end of bolt assembly (5) with main road upstream transporting system interface (20);
Described subregion spray panel (17) has one mounting groove for assembling toroidal membrane (23) at the corresponding position of toroidal membrane (23); Solid gunpowder igniter cartridge (16) is fixed on the subregion spray panel (17); Described bypass upstream transporting system interface (2) connects bypass upstream transporting system (1) and receives liquid oxidizer, and main road upstream transporting system interface (20) connects main road upstream transporting system (21) and receives liquid oxidizer; Described bypass blanking cover (22) when single thrust working condition tests, is used for bypass upstream transporting system interface (2) is sealed.
2. the head test device of a kind of multifunctional solid-liquid hybrid rocket according to claim 1, it is characterized in that, described bypass upstream transporting system interface (2) and main road upstream transporting system interface (20), by connecting-tube nozzle (24), bellows (25,28), pressing plate (26) forms with flange (27), described pressing plate (26) is actively socketed on the flange (27), bellows (25,28) a end is with the boss welding of connecting-tube nozzle (24), and the boss of the other end and flange (27) welds together; The bellows (25) that bypass upstream transporting system interface (2) is set is longer than the bellows (27) of main road upstream transporting system interface (20), so that bypass upstream transporting system interface (2) is positioned at same plane with main road upstream transporting system interface (20); Described pressing plate (26) is fixedly connected with skull connecting-tube nozzle (7) by bolt assembly (5).
3. the head test device of a kind of multifunctional solid-liquid hybrid rocket according to claim 1 and 2, it is characterized in that, described bypass Venturi tube (6) and main road Venturi tube (19), one end all stretches in the flange (27), and the other end all stretches in the double end chamber skull (18).
4. the head test device of a kind of multifunctional solid-liquid hybrid rocket according to claim 1, it is characterized in that, described subregion spray panel (17), the joint of itself and double end chamber skull (18), joint with burning chamber shell (11), with and the assembly connection place of upper mounting groove and toroidal membrane (23), all be furnished with o RunddichtringO (8,9,15) and seal.
5. the head test device of a kind of multifunctional solid-liquid hybrid rocket according to claim 1, it is characterized in that, described skull connecting-tube nozzle (7), itself and bypass Venturi tube (6) joint, with main road Venturi tube (19) joint, with bypass upstream transporting system interface (2) joint, and with the joint of main road upstream transporting system interface (20), all adopt o RunddichtringO (3,4) sealing.
6. the head test device of a kind of multifunctional solid-liquid hybrid rocket according to claim 1, it is characterized in that, described solid gunpowder igniter cartridge (16), it is by tack cross screw bolt (14)) be fixed on the subregion spray panel (17), between tack cross screw bolt (14) and bolt hole, be furnished with o RunddichtringO (13) sealing.
7. the head test device of a kind of multifunctional solid-liquid hybrid rocket according to claim 1, it is characterized in that, described subregion spray panel (17), it is divided into outer ring and inner ring by the relative position with mounting groove, on outer ring and inner ring, according to the assignment of traffic scheme, arrange respectively some spray orifices, according to the ejector filler of different tests purpose choice for use different pore size.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110001239 CN102080608B (en) | 2011-01-05 | 2011-01-05 | Head test device of multifunctional solid-liquid hybrid rocket engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110001239 CN102080608B (en) | 2011-01-05 | 2011-01-05 | Head test device of multifunctional solid-liquid hybrid rocket engine |
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| CN102080608A CN102080608A (en) | 2011-06-01 |
| CN102080608B true CN102080608B (en) | 2013-04-03 |
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| CN 201110001239 Expired - Fee Related CN102080608B (en) | 2011-01-05 | 2011-01-05 | Head test device of multifunctional solid-liquid hybrid rocket engine |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106481482B (en) * | 2015-08-26 | 2018-07-06 | 上海宇航***工程研究所 | A kind of miniature liquid engine solar heat protection flow-guiding structure |
| CN107035568B (en) * | 2017-03-29 | 2018-08-10 | 北京航空航天大学 | Hydrogen peroxide solid-liquid rocket subregion quick response catalytic bed |
| CN111664257B (en) * | 2019-09-30 | 2021-09-14 | 蓝箭航天空间科技股份有限公司 | Valve structure of liquid rocket engine and liquid rocket engine |
| CN114252268B (en) * | 2021-12-15 | 2022-11-29 | 北京航空航天大学 | Gas generator head cavity filling test device with gas blowing and test method |
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| US2703962A (en) * | 1952-09-30 | 1955-03-15 | Delwyn L Olson | Rocket engine injector head |
| GB903840A (en) * | 1960-08-26 | 1962-08-22 | United Aircraft Corp | Rocket injector head |
| US3132481A (en) * | 1959-06-23 | 1964-05-12 | United Aircraft Corp | Injector head for liquid rocket |
| DE2828249A1 (en) * | 1978-06-28 | 1980-01-03 | Messerschmitt Boelkow Blohm | Rocket combustion chamber flow control - has one, or two diametrically opposed cylindrical slide valves with round head in duct |
| CN1034438A (en) * | 1988-01-21 | 1989-08-02 | 中国人民解放军国防科学技术大学 | The method for designing of flow-controllable vapor-etched venturi |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10015369C2 (en) * | 2000-03-28 | 2003-07-03 | Astrium Gmbh | Tri-coaxial injection element |
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2011
- 2011-01-05 CN CN 201110001239 patent/CN102080608B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2703962A (en) * | 1952-09-30 | 1955-03-15 | Delwyn L Olson | Rocket engine injector head |
| US3132481A (en) * | 1959-06-23 | 1964-05-12 | United Aircraft Corp | Injector head for liquid rocket |
| GB903840A (en) * | 1960-08-26 | 1962-08-22 | United Aircraft Corp | Rocket injector head |
| DE2828249A1 (en) * | 1978-06-28 | 1980-01-03 | Messerschmitt Boelkow Blohm | Rocket combustion chamber flow control - has one, or two diametrically opposed cylindrical slide valves with round head in duct |
| CN1034438A (en) * | 1988-01-21 | 1989-08-02 | 中国人民解放军国防科学技术大学 | The method for designing of flow-controllable vapor-etched venturi |
Non-Patent Citations (2)
| Title |
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| 冯喜平等.旋转发动机燃烧室头部气-固两相流场结构分析.《计算机仿真》.2010,第27卷(第9期),第33-36页. |
| 旋转发动机燃烧室头部气-固两相流场结构分析;冯喜平等;《计算机仿真》;20100930;第27卷(第9期);第33-36页 * |
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