CN208669458U - A kind of solid propellant rocket pours medicine tooling and solid rocket motor grain - Google Patents
A kind of solid propellant rocket pours medicine tooling and solid rocket motor grain Download PDFInfo
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- CN208669458U CN208669458U CN201822135737.0U CN201822135737U CN208669458U CN 208669458 U CN208669458 U CN 208669458U CN 201822135737 U CN201822135737 U CN 201822135737U CN 208669458 U CN208669458 U CN 208669458U
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Abstract
The utility model discloses a kind of solid propellant rockets to pour medicine tooling, including burning chamber shell, the thermal insulation layer being arranged on burning chamber shell inner wall and the star core model that burning chamber shell center is arranged in, the thermal insulation layer includes carbon fiber layer and silastic-layer, and the inner circumferential of the carbon fiber layer cross section is to be joined end to end to constitute by multiple identical first circular arcs；The cross section of the star core model is starriness, and the star core model includes the identical star angle of multiple shapes, and the both sides at each star angle are isometric and parallel to each other, and the end that extends radially out on both sides passes through the second circular sliding slopes.A kind of solid rocket motor grain is also disclosed, which is to pour medicine tooling moulding by casting by described.The utility model is by pouring medicine tooling internal structure design, the shape for pouring the powder column after medicine tooling moulding by casting by this is set to meet target needs, to which the contour structures using powder column achieve the purpose that eliminate remaining medicine, engine operation thrust more gentle, that hangover time is short is provided for engine.
Description
Technical field
The utility model relates to solid propellant rocket Types of Medicine field of structural design, in particular to a kind of solid-rocket starts
Machine pours medicine tooling and solid rocket motor grain.
Background technique
Requirement of the transmitting of solid-rocket to its engine is that the working time is short, is Millisecond, generallys use hollow charge
Structure achievees the purpose that short time job requirement in such a way that neutral burning, thin meat are thick.But common star hole Types of Medicine engine
Powder charge haves the defects that work hangover time is long, according to, the mesh related with powder charge Grain structure the study found that engine operation is trailed
Before, star Types of Medicine are initial combustion face with the inner hole in star hole, and with the burning passage of combustion face, powder charge can finally have a surplus medicine, so as to cause
Motor charge work hangover time is longer, is not able to satisfy the job requirement of engine.
Utility model content
The main purpose of the utility model is to propose that a kind of solid propellant rocket pours medicine tooling and solid propellant rocket
Powder column is poured by this and is designed inside medicine tooling inner insulating layer with the structure of star core model shape specific matching, to meet compound push away
It is cast in the shape that the shape for pouring obtained powder column after curing molding in medicine tooling is required powder column into agent, so as to
To achieve the purpose that the contour structures using powder column eliminate remaining medicine, hair more gentle, that hangover time is short is provided for engine
Motivation working thrust.
To achieve the above object, the utility model adopts the following technical solutions:
Technical solution one
A kind of solid propellant rocket pours medicine tooling, including burning chamber shell, be arranged on burning chamber shell inner wall every
Thermosphere and the star core model that burning chamber shell center is arranged in, the burning chamber shell is in a tubular form；The thermal insulation layer includes carbon fiber
Tie up layer and silastic-layer, the inner wall bonding of the peripheral surface of the silastic-layer and the burning chamber shell, the silastic-layer
Inner peripheral surface connect with the peripheral surface of the carbon fiber layer；The inner circumferential of the carbon fiber layer cross section is by multiple identical
First circular arc joins end to end composition, and the center of circle of each first circular arc is evenly arranged on the center of the carbon fiber layer cross section as circle
On the circle of the heart；The longitudinal centre line of the star core model is conllinear with the central axes of burning chamber shell；The star core model it is transversal
Face is starriness, and the star core model includes the identical star angle of multiple shapes, and the number of the quantity at the star angle and the first circular arc
Measure identical, multiple star angles are uniformly distributed along the center of the cross section of the star core model；The both sides at each star angle are isometric and parallel to each other,
And the end that extends radially out on both sides passes through the second circular sliding slopes；Multiple second circular arcs correspond respectively with multiple first circular arcs, and
Corresponding second circular arc and the first circular arc are concentric.
A kind of solid propellant rocket according to the present utility model pours medicine tooling, this pours medicine tooling and pours for composite propellant
Injection forming, carbon fiber layer are that carbon fiber wound and solidified on specific mold is molding, form the periphery of carbon fiber layer cross section
Rounded, inner circumferential forms one layer of silicon rubber of molding in the peripheral surface of carbon fiber layer, forms silastic-layer, silicon in setting shape
The peripheral surface of rubber layer is bonded by the inner wall of binder and burning chamber shell；Carbon fiber layer and silastic-layer constitute heat-insulated
Layer, and the star core model of setting is then longitudinally inserted into the cavity inside carbon fiber layer, guarantee the longitudinal center of the star core model
Line is conllinear with the longitudinal centre line inside carbon fiber layer, thus constitutes solid propellant rocket and pours medicine tooling.
Further, the thermal insulation layer can also completely cut off the heat generated when powder column burning, bear 5s or more combustion gas and wash away
Without destroying, so as to protect burning chamber shell.
Preferably, arc-shaped transition between the two neighboring star angle of the star core model.
Preferably, the quantity at the star angle of the star core model is 4.
Technical solution two
A kind of solid rocket motor grain, the powder column are provided centrally with star-shaped through hole, and the star-shaped through hole includes more
A star angle, and the shape at each star angle is identical；Multiple star angles are circumferentially uniformly distributed along the center of the star-shaped through hole, and the two of each star angle
Side is isometric and parallel to each other, and the end that extends radially out on both sides passes through third circular sliding slopes；The periphery of the powder column cross section is by more
A 4th circular arc, which joins end to end, to be constituted, and the quantity of the 4th circular arc is identical as the quantity at the star angle, each 4th circular arc
Shape is identical and the center of circle of each 4th circular arc is on the circle using the center of the powder column cross section as the center of circle；Multiple described
Four circular arcs correspond respectively with multiple third circular arcs, and corresponding 4th circular arc and third circular arc are concentric.
A kind of solid rocket motor grain according to the present utility model, the powder column are by composite propellant medicine slurry along solid
Rocket engine pour carbon fiber layer inner wall in medicine tooling be poured, solidify, form after obtain.First in the interior weekly form of carbon fiber layer
One layer of adhesive glue is smeared on face, then by the inside of composite propellant medicine slurry injection carbon fiber layer, after cured, by star core model
It extracts, obtains shaped charge；And Burr removal, leveling are removed into two end faces of shaped charge, finally on two end faces of powder column
By binder bonding silicone rubber, silastic-layer is formed, which is used to that grainend is prevented to burn.Medicine is completed in this way
The production of column, and the inner circumferential shape of carbon fiber layer cross section determines the peripheral shape of powder column cross section, star core in the production
The peripheral shape of mould determines the internal via shape of powder column, therefore needs to design the inner circumferential shape of thermal insulation layer and the periphery shape of star core model
Shape meets the structure of setting matching relationship, then composite propellant injection pouring in medicine tooling with this spline structure, curing molding
The shape of the powder column obtained afterwards is the shape of required powder column, which is in the combustion chamber initial combustion face with star inner hole, with
Combustion face along passage line burning, burn last nothing left medicine, eliminates remaining medicine to reach by changing powder column contour structures
Purpose further shortens engine operation hangover time to Millisecond, reaches the job requirement of engine.
Preferably, arc-shaped transition between the two neighboring star angle of the star-shaped through hole.
A kind of solid rocket motor grain according to the present utility model, between the two neighboring star angle of the star-shaped through hole
Why arc-shaped transition is considered from technological angle, and arc can be concentrated to avoid stress.
Preferably, the quantity at the star angle of the star-shaped through hole is 4.
Detailed description of the invention
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Or attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is only
It is some embodiments of the utility model, for those of ordinary skill in the art, in the premise not made the creative labor
Under, the structure that can also be shown according to these attached drawings obtains other attached drawings.
Fig. 1 is that the solid propellant rocket of the utility model one embodiment pours medicine tooling cross-sectional view；
Fig. 2 is the solid rocket motor grain cross-sectional view of the utility model one embodiment.
Appended drawing reference respectively indicates: 1- burning chamber shell, 2- thermal insulation layer, 21- carbon fiber layer, 22- silastic-layer, 3- star
Core model, the first circular arc of 4-, the second circular arc of 5-, 6- powder column, 7- third circular arc, the 4th circular arc of 8-.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describing, it is clear that described embodiment is only a part of the embodiment of the utility model, rather than all
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are not making creative work premise
Under every other embodiment obtained, fall within the protection scope of the utility model.
Referring to Fig.1, a kind of solid propellant rocket of the utility model embodiment pours medicine tooling, including burning chamber shell 1,
The thermal insulation layer 2 being arranged on 1 inner wall of burning chamber shell and the star core model 3 that 1 body center of combustion chamber shell is set, the combustion chamber
Shell 1 is in a tubular form；The thermal insulation layer 2 include carbon fiber layer 21 and silastic-layer 22, the peripheral surface of the silastic-layer 22 with
The inner wall of the burning chamber shell 1 bonds, the peripheral surface of the inner peripheral surface of the silastic-layer 22 and the carbon fiber layer 21
Connection；The inner circumferential of 21 cross section of carbon fiber layer is to be joined end to end to constitute by multiple identical first circular arcs 4, and each first
The center of circle of circular arc 4 is evenly arranged on using the center of 21 cross section of carbon fiber layer as on the circle in the center of circle；The longitudinal direction of the star core model 3
Center line is conllinear with the central axes of burning chamber shell 1；The cross section of the star core model 3 is starriness, and the star core model 3 wraps
Containing the identical star angle of multiple shapes, and the quantity at the star angle is identical as the quantity of the first circular arc 4, and multiple star angles are along the star
The center of the cross section of core model 3 is uniformly distributed；The both sides at each star angle are isometric and parallel to each other, and both sides extend radially out end by the
The connection of two circular arcs 5；Multiple second circular arcs 5 correspond respectively with multiple first circular arcs 4, and corresponding second circular arc 5 and first
Circular arc 4 is concentric.
In the embodiment above, this pours medicine tooling for composite propellant moulding by casting: carbon fiber is in specific mold
Wound and solidified obtains carbon fiber layer 21 after molding, which forms 21 cross section of carbon fiber layer in the range of 1~1.5mm
Periphery it is rounded, inner circumferential in setting shape, form carbon fiber layer 21 peripheral surface on be molded one layer of silicon rubber, formed silicon rubber
Glue-line 22, for the thickness degree in the range of 0.5~1.0mm, then carbon fiber layer 21 and silastic-layer 22 constitute thermal insulation layer 2, and
The peripheral surface of silastic-layer 22 is bonded by the inner wall of binder and burning chamber shell 1, then indulges the star core model 3 of setting
Cavity to the inside of insertion carbon fiber layer 21, the longitudinal centre line for guaranteeing the star core model 3 and the longitudinal direction inside carbon fiber layer 21
Centerline collineation, in this way production form solid propellant rocket and pour medicine tooling.
Further, the thermal insulation layer 2 can also completely cut off the heat generated when powder column 1 burns, bear 5s or more combustion gas punching
Brush is without destroying, so as to protect burning chamber shell 1.
A kind of embodiment according to the present utility model, arc-shaped transition between the two neighboring star angle of the star core model 3.
A kind of embodiment according to the present utility model, the quantity at the star angle of the star core model 3 are 4.
Referring to Fig. 2, a kind of solid rocket motor grain of the utility model embodiment, the powder column 6 is provided centrally with
Star-shaped through hole, the star-shaped through hole includes multiple star angles, and the shape at each star angle is identical；Multiple star angles are along the star-shaped through hole
Center it is circumferentially uniformly distributed, the both sides at each star angle are isometric and parallel to each other, and the end that extends radially out on both sides is connected by third circular arc 7
It connects；The periphery of 6 cross section of powder column is joined end to end by multiple 4th circular arcs 8 to be constituted, the quantity of the 4th circular arc 8 and institute
The quantity for stating star angle is identical, and the shape of each 4th circular arc 8 is identical and the center of circle of each 4th circular arc 8 is horizontal with the powder column 1
The center in section is on the circle in the center of circle；Multiple 4th circular arcs 8 correspond respectively with multiple third circular arcs 7, and right
The 4th circular arc 8 and third circular arc 7 answered are concentric.
In the embodiment above, 6 length of powder column is not more than 180mm, and outer diameter is not more than 40mm, which is by multiple
Close Composite Propellant Slurry along solid propellant rocket pour 21 inner wall of carbon fiber layer in medicine tooling be poured, solidify, form after obtain.It is first
One layer of adhesive glue is first smeared in the inner peripheral surface of carbon fiber layer 21, then by composite propellant medicine slurry injection carbon fiber layer 21
Star core model is after cured extracted in inside, obtains shaped charge, and Burr removal, whole is removed in two end faces of shaped charge 6
It is flat, finally by binder bonding silicone rubber, silastic-layer is formed, the thickness degree is in the range of 0.5~1.0mm, the silicon rubber
Glue-line is used to prevent 6 cigarette burning of powder column.Complete the production of powder column 6 in this way, and in the production carbon fiber layer cross section it is interior
All shapes determine the peripheral shape of powder column cross section, and the peripheral shape of star core model determines the internal via shape of powder column, therefore needs
The peripheral shape of the inner circumferential shape and star core model that design thermal insulation layer meets the structure of setting matching relationship.And thermal insulation layer 2
Inner circumferential shape is determined by the inner circumferential shape of carbon fiber layer 21, so the specific mold for wound and solidified carbon fiber is must
It must meet certain condition.It illustrates herein: if, set the quantity at the star angle of the star-shaped through hole of 6 cross-section center of powder column
It is 4, accordingly, it is desirable that the periphery of 6 cross section of powder column must be joined end to end to constitute by 4 the 4th circular arcs 8, and 4 the 4th
The one-to-one correspondence of circular arc 8 and 4 third circular arc 7 is simultaneously concentric, then, selection is used for the specific mold of wound and solidified carbon fiber layer 21
It must be such that the inner circumferential shape of molding 21 cross section of carbon fiber layer matches with the peripheral shape of 6 cross section of powder column, meanwhile, selection
Meet the star core model of specific matching care with 21 inner circumferential shape of carbon fiber layer, thus carbon fiber layer Mold Making carbon fiber layer
21, the outer weekly form of carbon fiber layer 21 obtains silastic-layer 22,22 peripheral surface of silastic-layer is bonded in using molding silicon rubber
1 inner wall of burning chamber shell, thus constitutes combustion chamber；It is made of the combustion chamber and star core model and pours medicine tooling, by composite propellant
Medicine slurry is injected this and is poured in medicine tooling, and the shape for the powder column 6 that curing molding obtains meets the shape of set powder column.The powder column 6
It is in the combustion chamber initial combustion face with star inner hole, as combustion face is along passage line burning, burn last nothing left medicine, to reach
The purpose of remaining medicine is eliminated by changing powder column contour structures, is further shortened engine operation hangover time to Millisecond, is reached
To the job requirement of engine.
Embodiment according to the present utility model, arc-shaped transition between the two neighboring star angle of the star-shaped through hole.
In the embodiment above, why arc-shaped transition is from process corner between the two neighboring star angle of the star-shaped through hole
What degree considered, arc can be concentrated to avoid stress.
Embodiment according to the present utility model, the quantity at the star angle of the star-shaped through hole are 4.
The above is only the preferred embodiment of the present invention, and therefore it does not limit the scope of the patent of the utility model,
It is all under the inventive concept of the utility model, equivalent structure made based on the specification and figures of the utility model becomes
It changes, or directly/be used in other related technical areas indirectly and be included in the scope of patent protection of the utility model.
Claims (6)
1. a kind of solid propellant rocket pours medicine tooling characterized by comprising burning chamber shell (1) is arranged in combustion chamber shell
The star core model (3) of thermal insulation layer (2) on body (1) inner wall and setting at burning chamber shell (1) center；
The burning chamber shell (1) is in a tubular form；
The thermal insulation layer (2) include carbon fiber layer (21) and silastic-layer (22), the peripheral surface of the silastic-layer (22) and
The inner wall of the burning chamber shell (1) bonds, the inner peripheral surface of the silastic-layer (22) and the carbon fiber layer (21) it is outer
Perimeter surface connection；
The inner circumferential of carbon fiber layer (21) cross section is to be joined end to end to constitute by multiple identical first circular arcs (4), and each
The center of circle of first circular arc (4) is evenly arranged on using the center of the carbon fiber layer (21) cross section as on the circle in the center of circle；
The longitudinal centre line of the star core model (3) is conllinear with the central axes of burning chamber shell (1)；
The cross section of the star core model (3) is starriness, and the star core model (3) includes the identical star angle of multiple shapes, and
The quantity at the star angle is identical as the quantity of the first circular arc (4), center of multiple star angles along the cross section of the star core model (3)
It is uniformly distributed；The both sides at each star angle are isometric and parallel to each other, and the end that extends radially out on both sides is connected by the second circular arc (5)；
Multiple second circular arcs (5) correspond respectively with multiple first circular arcs (4), and corresponding second circular arc (5) and the first circle
Arc (4) is concentric.
2. a kind of solid propellant rocket according to claim 1 pours medicine tooling, which is characterized in that the star core model
(3) arc-shaped transition between two neighboring star angle.
3. a kind of solid propellant rocket according to claim 1 pours medicine tooling, which is characterized in that the star core model
(3) quantity at star angle is 4.
4. a kind of solid rocket motor grain pours medicine tooling by solid propellant rocket described in claim 1 and pours into
Type, which is characterized in that the powder column (6) is provided centrally with star-shaped through hole, and the star-shaped through hole includes multiple star angles, and each star
The shape at angle is identical；Multiple star angles are circumferentially uniformly distributed along the center of the star-shaped through hole, and the both sides at each star angle are isometric and mutually equal
Row, and the end that extends radially out on both sides is connected by third circular arc (7)；
The periphery of powder column (6) cross section is joined end to end by multiple 4th circular arcs (8) to be constituted, the 4th circular arc (8)
Quantity is identical as the quantity at the star angle, the shape of each 4th circular arc (8) is identical and the center of circle of each 4th circular arc (8) with
The center of powder column (6) cross section is on the circle in the center of circle；Multiple 4th circular arcs (8) and multiple third circular arcs (7)
It corresponds respectively, and corresponding 4th circular arc (8) and third circular arc (7) are concentric.
5. a kind of solid rocket motor grain according to claim 4, which is characterized in that the star-shaped through hole it is adjacent
Arc-shaped transition between two star angles.
6. a kind of solid rocket motor grain according to claim 4, which is characterized in that the star angle of the star-shaped through hole
Quantity be 4.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822135737.0U CN208669458U (en) | 2018-12-19 | 2018-12-19 | A kind of solid propellant rocket pours medicine tooling and solid rocket motor grain |
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| CN201822135737.0U CN208669458U (en) | 2018-12-19 | 2018-12-19 | A kind of solid propellant rocket pours medicine tooling and solid rocket motor grain |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110529288A (en) * | 2019-08-28 | 2019-12-03 | 湖北三江航天江北机械工程有限公司 | Solid propellant rocket, the method and chamber structure for inhibiting medicine more than its powder charge |
| CN110566366A (en) * | 2019-09-02 | 2019-12-13 | 湖北三江航天江河化工科技有限公司 | Combined core mold structure for rocket engine grain molding and use method thereof |
| CN110821709A (en) * | 2019-12-30 | 2020-02-21 | 南京理工大学 | Jet-pipe-free engine charging structure additionally provided with bowl-shaped pressurizing explosive columns |
| CN110985234A (en) * | 2019-12-10 | 2020-04-10 | 湖北三江航天江河化工科技有限公司 | Belt transmission continuous filling and pouring equipment and process for solid rocket engine shell |
| CN112901371A (en) * | 2021-03-31 | 2021-06-04 | 西北工业大学 | Novel square tube solid rocket engine |
| CN114683445A (en) * | 2022-04-18 | 2022-07-01 | 大连理工大学 | Solid rocket engine disassembly-free wing column type grain forming die and forming method |
| CN114953519A (en) * | 2022-03-27 | 2022-08-30 | 西安航天动力技术研究所 | Single-side crack reinforcing simulation piece of manual debonding structure of solid rocket engine and forming method |
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2018
- 2018-12-19 CN CN201822135737.0U patent/CN208669458U/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110529288A (en) * | 2019-08-28 | 2019-12-03 | 湖北三江航天江北机械工程有限公司 | Solid propellant rocket, the method and chamber structure for inhibiting medicine more than its powder charge |
| CN110566366A (en) * | 2019-09-02 | 2019-12-13 | 湖北三江航天江河化工科技有限公司 | Combined core mold structure for rocket engine grain molding and use method thereof |
| CN110566366B (en) * | 2019-09-02 | 2021-07-13 | 湖北三江航天江河化工科技有限公司 | Combined core mold structure for rocket engine grain molding and use method thereof |
| CN110985234A (en) * | 2019-12-10 | 2020-04-10 | 湖北三江航天江河化工科技有限公司 | Belt transmission continuous filling and pouring equipment and process for solid rocket engine shell |
| CN110821709A (en) * | 2019-12-30 | 2020-02-21 | 南京理工大学 | Jet-pipe-free engine charging structure additionally provided with bowl-shaped pressurizing explosive columns |
| CN112901371A (en) * | 2021-03-31 | 2021-06-04 | 西北工业大学 | Novel square tube solid rocket engine |
| CN114953519A (en) * | 2022-03-27 | 2022-08-30 | 西安航天动力技术研究所 | Single-side crack reinforcing simulation piece of manual debonding structure of solid rocket engine and forming method |
| CN114953519B (en) * | 2022-03-27 | 2023-09-15 | 西安航天动力技术研究所 | Single-side crack enhancement simulation piece of artificial debonding structure of solid rocket engine and forming method |
| CN114683445A (en) * | 2022-04-18 | 2022-07-01 | 大连理工大学 | Solid rocket engine disassembly-free wing column type grain forming die and forming method |
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