CN103967653A - Axial injection end combustion solid-liquid rocket engine structure - Google Patents
Axial injection end combustion solid-liquid rocket engine structure Download PDFInfo
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- CN103967653A CN103967653A CN201410175370.9A CN201410175370A CN103967653A CN 103967653 A CN103967653 A CN 103967653A CN 201410175370 A CN201410175370 A CN 201410175370A CN 103967653 A CN103967653 A CN 103967653A
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Abstract
The invention discloses an axial injection end combustion solid-liquid rocket engine structure which comprises an engine head cover, a solid propellant shell, a solid propellant heat insulating layer, end combustion solid propellants, a spray pipe shell and a spray pipe heat insulating layer. The engine head cover is mounted at the front end of the solid propellant shell, the spray pipe shell is mounted at the rear end of the solid propellant shell, the engine head cover is provided with an air inlet channel, the end combustion solid propellants are coaxially arranged in the solid propellant shell, a constant volume cavity is formed between the front end faces of the end combustion solid propellants and the rear end face of the engine head cover, each end combustion solid propellant is provided with a plurality of axial injection holes with small diameters, the flow rate of oxidizing agents in the injection holes is high, and combustion reaction only occurs at the end faces of the end combustion solid propellants; the joint between the solid propellant shell and the engine head cover and the joint between the solid propellant shell and the spray pipe shell are respectively provided with a sealing structure, so that air impermeability of an engine is guaranteed; the heat insulating layers are arranged in the solid propellant shell and the spray pipe shell, so that thermal protection performance of the engine during operation is guaranteed. Thus, performance of the engine is improved, meanwhile the filling fraction of the engine is improved, the slenderness ratio of the engine is reduced, and the application rage of engine is widened.
Description
Technical field
The present invention relates to solid-liquid rocket technical field, specifically, is a kind of axially injection end combustion solid-liquid rocket structure.
Background technique
Compared with the solid or liquid propellant rocket engine of current extensive use, it is propellant agent that solid-liquid rocket adopts liquid oxidizer and solid fuel, having that cost is low, Security good, can carry out thrust adjusting and the advantage such as startup repeatedly, is that space flight advances field to have very much a class motor of development potentiality.
When typical solid-liquid rocket work, oxygenant enters the powder column passage of motor through spray panel, form the zone of flame and burn near powder column side wall surface, and powder column belongs to side burning.Common powder charge medicine shape has circle hole shape, star hole, wheel shape and porous etc.For side burning solid-liquid rocket, along with the increase of engine operating duration, powder charge aisle spare and fuel flow rate constantly change, thereby cause the variation of oxygen combustion ratio, cause the loss of engine performance.Therefore be, the problem that needs solution by the appropriate design of powder charge medicine shape and engine structure being improved to the performance of solid-liquid rocket.Meanwhile, typical side burning solid-liquid rocket has larger aisle spare conventionally, and filling mark is lower, and for enough burning areas are provided, length is longer, and slenderness ratio is larger, and it is subject to certain restrictions in application area.
Summary of the invention
In order to address the above problem, the present invention proposes a kind of axially injection end combustion solid-liquid rocket structure, can in engine working process, keep burning area constant, maintains the constant of oxygen combustion ratio, improves engine performance; Improve the filling mark of motor simultaneously, reduce architecture quality, reduce motor slenderness ratio, expand engine application scope.
A kind of axially injection end combustion solid-liquid rocket structure, comprises motor skull, powder column housing, powder column heat insulation layer, end-burning grain, jet pipe housing and jet pipe heat insulation layer.
Described powder column housing front end is installed motor skull, and jet pipe housing is installed in rear end; Motor head covers has gas-entered passageway, for the supply of oxygenant.Jet pipe housing, for expansion and the acceleration ejection of products of combustion, produces motor power.End-burning grain is coaxially arranged in powder column housing, has the spray orifice that connects two ends on axially.Between end-burning grain front-end face and motor head cover back-end face, have certain cavity volume, buffering is shunted and provided to each spray orifice that enters end-burning grain for oxygenant.
When engine operation, the spray orifice of oxygenant in end-burning grain sprays into firing chamber and end-burning grain burns, and because the diameter of spray orifice is very little, makes the oxygenant flow velocity in spray orifice very high, combustion flame cannot be expanded in spray orifice, only burn at the ear end face of end-burning grain.
The invention has the advantages that:
1, the axial injection end combustion of the present invention solid-liquid rocket structure, on end-burning grain, have the axial spray orifice that multiple diameters are very little, spray orifice inner oxidizing agent flow velocity is very high not to burn, combustion reaction only occurs in end-burning grain end, the feature of cigarette burning makes motor burning area and oxygen combustion in the course of the work more constant than maintenance, start function to be operated near best oxygen combustion ratio always, improved specific impulse and the performance of motor;
2, the axial injection end combustion of the present invention solid-liquid rocket structure, on end-burning grain, axially the diameter of spray orifice is very little, and end-burning grain aisle spare is little, has improved the filling mark of motor, has reduced motor volume, has reduced motor structure mass;
3, the axial injection end combustion of the present invention solid-liquid rocket structure, owing to having cigarette burning, can increase burning area by increasing end-burning grain diameter, has reduced length and the slenderness ratio of motor, has expanded its application;
4, the axial injection end combustion of the present invention solid-liquid rocket structure, the joint of powder column housing and motor skull and jet pipe housing is provided with sealing configuration, has ensured the tightness of motor;
5, the axial injection end combustion of the present invention solid-liquid rocket structure, powder column housing and jet pipe enclosure interior are equipped with heat insulation layer, have ensured the thermal protective performance (TPP) in engine operation.
Brief description of the drawings
Fig. 1 is the axial injection end combustion of the present invention solid-liquid rocket structural representation;
Fig. 2 is the A-A cross section view of a kind of axial injection end combustion solid-liquid rocket structure shown in Fig. 1.
In figure:
1-motor skull 2-powder column housing 3-powder column heat insulation layer 4-end-burning grain 5-jet pipe housing
6-jet pipe heat insulation layer 7-seal ring A 8-bolt assembly A 9-seal ring B 10-bolt assembly B
11-combustion flame 401-spray orifice
Embodiment
Below in conjunction with drawings and Examples, the present invention is described in further detail.
The axial injection end combustion of the present invention solid-liquid rocket structure, comprises motor skull 1, powder column housing 2, powder column heat insulation layer 3, end-burning grain 4, jet pipe housing 5, jet pipe heat insulation layer 6, seal ring A7, bolt assembly A8, seal ring B9 and bolt assembly B10.
Described powder column housing 2 is columnar structured, and rear and front end has adpting flange; And on powder column housing 2 front ends and rear end end face, have circumferential seal groove, inside is respectively arranged with seal ring A7 and seal ring B9.
Described motor skull 1 front end has gas-entered passageway, and for the supply of oxygenant, oxygenant can be selected the gaseous oxidant such as O2, N2O.On motor skull 1 ear end face, be circumferentially designed with inside and outside two-layer annular boss A and annular boss B.Wherein, internal layer annular boss A is used for coordinating with powder column housing 2 front inner wall, realize the radial location between motor skull 1 and powder column housing 2, and by bolt assembly A8, motor skull 1 is connected with powder column housing 2 front end flange structures, make outer annular boss B be used for coordinating with the seal groove of powder column housing 2 front end end faces, seal ring A7 is compressed, realize the fixing and sealing between powder column housing 2 and motor skull 1.
Described jet pipe housing 5, for having the Rafael nozzle of anterior converging portion and rear portion extending section, for expansion and the acceleration ejection of products of combustion, produces motor power.Jet pipe housing 5 front ends are also designed with a cylindrical section, as firing chamber, carry out combustion reaction for the pyrolysis product of oxygenant and end-burning grain 4.5 front-end face weeks of jet pipe housing upwards have inside and outside two annular boss C and annular boss D; Wherein, internal layer annular boss C is used for coordinating with powder column housing 2 rear end inwalls, realize the radial location between jet pipe housing 5 and powder column housing 2, and by bolt assembly B10, jet pipe housing 5 is connected with powder column housing 2 rear end flange arrangements, outer annular boss D is used for coordinating with powder column housing 2 back-end sealing grooves, seal ring B9 is compressed, realize the fixing and sealing between powder column housing 2 and jet pipe housing 5.On above-mentioned jet pipe housing 5 inwalls, be bonded with jet pipe heat insulation layer 6, formed by resistance to ablative insulative material, in engine working process, play a role in insulation, make jet pipe housing 5 maintain lower temperature.
Described end-burning grain 4 is cylindrical structural, adopts the conventional fuel of solid-liquid rocket to make, as HTPB (end hydroxy butadiene) base fuel, PE (polyethylene) and PMMA (polymethylmethacrylate) etc.On end-burning grain 4 is axial, there is the spray orifice 401 that connects two ends; Spray orifice 401 is evenly arranging in the concentric circumferences in the center of circle taking end-burning grain 4 centers, spray orifice 401 diameters and quantity are determined according to concrete oxidizer flow rate and size of engine, and all the section area sum of spray orifice 401 must be enough little, make oxygenant flow velocity exceed critical flow velocity, thereby only there is cigarette burning in motor; The size of this critical flow velocity is relevant with the selection of propellant agent combination, needs to determine by test.The end-burning grain 4 of said structure is coaxially arranged in powder column housing 2, rear and front end is undertaken spacing by motor skull 1 and the internal layer annular raised head face on jet pipe housing 5 respectively, realize the axially locating of end-burning grain 4 in motor body inside, and making to there is certain cavity volume between end-burning grain 4 front-end faces and motor skull 1 ear end face, buffering is shunted and provided to each spray orifice 401 that enters end-burning grain 4 as oxygenant.Between end-burning grain 4 outer walls and powder column housing 2 inwalls, powder column heat insulation layer 3 is installed, is formed by resistance to ablative insulative material, in engine working process, play a role in insulation, make powder column housing 2 maintain lower temperature.
When engine operation, the spray orifice 401 of oxygenant in end-burning grain 4 sprays into firing chamber and end-burning grain 4 burns, because the diameter of spray orifice 401 is very little, make the oxygenant flow velocity in spray orifice 401 very high, combustion flame 11 cannot be expanded in spray orifice 401, only burn at the ear end face of end-burning grain 4.
Claims (6)
1. an axial injection end combustion solid-liquid rocket structure, is characterized in that: comprise motor skull, powder column housing, powder column heat insulation layer, end-burning grain, jet pipe housing and jet pipe heat insulation layer;
Described powder column housing front end is installed motor skull, and jet pipe housing is installed in rear end; Motor head covers has gas-entered passageway; End-burning grain is coaxially arranged in powder column housing, between front-end face and motor head cover back-end face, has certain cavity volume; On end-burning grain is axial, there is the spray orifice that connects two ends.
2. a kind of axially injection end is fired solid-liquid rocket structure as claimed in claim 1, it is characterized in that: described jet pipe housing adopts Rafael nozzle, and jet pipe housing front end is also designed with a cylindrical section as firing chamber.
3. a kind of axially injection end is fired solid-liquid rocket structure as claimed in claim 1, it is characterized in that: between described end-burning grain outer wall and powder column inner walls, powder column heat insulation layer is installed.
4. a kind of axially injection end is fired solid-liquid rocket structure as claimed in claim 1, it is characterized in that: in described jet pipe inner walls, be bonded with jet pipe heat insulation layer.
5. a kind of axially injection end is fired solid-liquid rocket structure as claimed in claim 1, it is characterized in that: spray orifice evenly arranges in the concentric circumferences taking end-burning grain center as the center of circle.
6. a kind of axially injection end is fired solid-liquid rocket structure as claimed in claim 1, it is characterized in that: on described powder column housing front end and rear end end face, have circumferential seal groove, inside is respectively arranged with seal ring A and seal ring B; On motor head cover back-end face, be circumferentially designed with inside and outside two-layer annular boss A and annular boss B; Wherein, internal layer annular boss A is used for coordinating with powder column housing front inner wall, and by bolt assembly A, motor skull is connected with powder column housing front end flange structure, make outer annular boss B be used for coordinating with the seal groove of powder column housing front end end face, seal ring A is compressed, realize the fixing and sealing between powder column housing and motor skull; Upwards there is inside and outside two annular boss C and annular boss D jet pipe housing front-end face week; Wherein, internal layer annular boss C is used for coordinating with powder column housing rear end inwall, and by bolt assembly B, jet pipe housing is connected with powder column housing rear end flange arrangement, outer annular boss D is used for coordinating with powder column housing back-end sealing groove, seal ring B is compressed, realize the fixing and sealing between powder column housing and jet pipe housing.
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| CN201410175370.9A CN103967653B (en) | 2014-04-28 | 2014-04-28 | A kind of axially injection end combustion solid-liquid rocket structure |
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| CN201410175370.9A CN103967653B (en) | 2014-04-28 | 2014-04-28 | A kind of axially injection end combustion solid-liquid rocket structure |
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| CN103967653A true CN103967653A (en) | 2014-08-06 |
| CN103967653B CN103967653B (en) | 2016-06-08 |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104295407A (en) * | 2014-08-13 | 2015-01-21 | 西北工业大学 | Universal booster capable of disengaging automatically without causing disturbance |
| CN104833768A (en) * | 2015-03-11 | 2015-08-12 | 西北工业大学 | Simulation device of thermal insulation layer ablation under condition of particle phase deposition in rocket engine |
| CN106194501A (en) * | 2016-07-08 | 2016-12-07 | 北京航空航天大学 | Spiral Types of Medicine solid-liquid rocket |
| CN106194502A (en) * | 2016-07-15 | 2016-12-07 | 北京航空航天大学 | A kind of solid-liquid Attitude rocket engine |
| CN106837608A (en) * | 2017-04-01 | 2017-06-13 | 北京航空航天大学 | Fire change propulsive solid-liquid rocket structure in a kind of decking end |
| CN107044362A (en) * | 2016-12-07 | 2017-08-15 | 西安近代化学研究所 | A kind of low plumage flame feature engine |
| CN109812696A (en) * | 2019-01-23 | 2019-05-28 | 北京蓝箭空间科技有限公司 | Propellant for space launch vehicle sinks to the bottom energy supply system and carrier rocket |
| CN110080909A (en) * | 2018-12-28 | 2019-08-02 | 湖北航天技术研究院总体设计所 | A kind of jet pipe of solid propellant rocket |
| CN113357051A (en) * | 2021-06-25 | 2021-09-07 | 中国科学院力学研究所 | Internal spiral injection type solid-liquid engine explosive column |
| CN114166991A (en) * | 2021-11-02 | 2022-03-11 | 星河动力(北京)空间科技有限公司 | Single-side multi-outlet testing device for heat insulation layer of rocket engine |
| CN114439649A (en) * | 2021-12-31 | 2022-05-06 | 西安近代化学研究所 | Gunpowder starter capable of effectively reducing occupied space |
| CN114439648A (en) * | 2021-12-31 | 2022-05-06 | 西安近代化学研究所 | Gunpowder starter suitable for engine secondary starting |
| CN114810419A (en) * | 2022-04-29 | 2022-07-29 | 西安近代化学研究所 | Charging configuration capable of effectively increasing combustion surface of explosive column and electric control engine |
| CN114876667A (en) * | 2022-04-27 | 2022-08-09 | 西安零壹空间科技有限公司 | Composite solid rocket engine, charging method and filling equipment |
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Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104295407A (en) * | 2014-08-13 | 2015-01-21 | 西北工业大学 | Universal booster capable of disengaging automatically without causing disturbance |
| CN104833768A (en) * | 2015-03-11 | 2015-08-12 | 西北工业大学 | Simulation device of thermal insulation layer ablation under condition of particle phase deposition in rocket engine |
| CN106194501A (en) * | 2016-07-08 | 2016-12-07 | 北京航空航天大学 | Spiral Types of Medicine solid-liquid rocket |
| CN106194502A (en) * | 2016-07-15 | 2016-12-07 | 北京航空航天大学 | A kind of solid-liquid Attitude rocket engine |
| CN106194502B (en) * | 2016-07-15 | 2018-03-02 | 北京航空航天大学 | A kind of solid-liquid Attitude rocket engine |
| CN107044362A (en) * | 2016-12-07 | 2017-08-15 | 西安近代化学研究所 | A kind of low plumage flame feature engine |
| CN107044362B (en) * | 2016-12-07 | 2018-12-11 | 西安近代化学研究所 | A kind of low plumage flame feature engine |
| CN106837608A (en) * | 2017-04-01 | 2017-06-13 | 北京航空航天大学 | Fire change propulsive solid-liquid rocket structure in a kind of decking end |
| CN110080909A (en) * | 2018-12-28 | 2019-08-02 | 湖北航天技术研究院总体设计所 | A kind of jet pipe of solid propellant rocket |
| CN109812696A (en) * | 2019-01-23 | 2019-05-28 | 北京蓝箭空间科技有限公司 | Propellant for space launch vehicle sinks to the bottom energy supply system and carrier rocket |
| CN113357051A (en) * | 2021-06-25 | 2021-09-07 | 中国科学院力学研究所 | Internal spiral injection type solid-liquid engine explosive column |
| CN114166991A (en) * | 2021-11-02 | 2022-03-11 | 星河动力(北京)空间科技有限公司 | Single-side multi-outlet testing device for heat insulation layer of rocket engine |
| CN114439649A (en) * | 2021-12-31 | 2022-05-06 | 西安近代化学研究所 | Gunpowder starter capable of effectively reducing occupied space |
| CN114439648A (en) * | 2021-12-31 | 2022-05-06 | 西安近代化学研究所 | Gunpowder starter suitable for engine secondary starting |
| CN114439648B (en) * | 2021-12-31 | 2024-04-30 | 西安近代化学研究所 | Gunpowder starter suitable for engine secondary starting |
| CN114876667A (en) * | 2022-04-27 | 2022-08-09 | 西安零壹空间科技有限公司 | Composite solid rocket engine, charging method and filling equipment |
| CN114876667B (en) * | 2022-04-27 | 2023-09-12 | 西安零壹空间科技有限公司 | Composite solid rocket engine, charging method and filling equipment |
| CN114810419A (en) * | 2022-04-29 | 2022-07-29 | 西安近代化学研究所 | Charging configuration capable of effectively increasing combustion surface of explosive column and electric control engine |
| CN114810419B (en) * | 2022-04-29 | 2023-06-09 | 西安近代化学研究所 | Charging configuration capable of effectively increasing explosive column combustion surface and electric control engine |
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