CN107023419B - A kind of Solid Rocket Motor combustion chamber shell lightweight connector - Google Patents
A kind of Solid Rocket Motor combustion chamber shell lightweight connector Download PDFInfo
- Publication number
- CN107023419B CN107023419B CN201710306059.7A CN201710306059A CN107023419B CN 107023419 B CN107023419 B CN 107023419B CN 201710306059 A CN201710306059 A CN 201710306059A CN 107023419 B CN107023419 B CN 107023419B
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- CN
- China
- Prior art keywords
- connector
- combustion chamber
- chamber shell
- rocket motor
- solid rocket
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
- F02K9/343—Joints, connections, seals therefor
Abstract
The present invention relates to a kind of Solid Rocket Motor combustion chamber shell lightweight connectors, including the inner surface and the outer surface, it is characterised in that the spatial radial section of the inner surface and the outer surface envelope of the connector is engraved structure.The engraved structure can be to open up weight loss groove；It can also be frame-type, as support construction, the inner surface and the outer surface of the connector is covered using covering for inside setting ring muscle, floor；It can also be dot matrix, inside uses dot matrix structural support, and the inner surface and the outer surface of the connector is covered using covering.Compared with prior art, the present invention drop；Low joint quality significantly reduces solid propellant rocket passiveness quality in the case where not influencing connector load performance.
Description
Technical field
The invention belongs to solid propellant rocket field more particularly to a kind of Solid Rocket Motor combustion chamber shell lightweights
Connector.
Background technique
The traditional structure forms of Solid Rocket Motor combustion chamber shell joint are monolithic construction, and connector includes inner surface
And outer surface, the spatial radial section of the inner surface and the outer surface envelope are solid construction, it can also be non-gold that material, which can be metal,
Belong to, metal has aluminium alloy, titanium alloy, high-strength steel, nonmetallic there are fibre resin based composites.With solid propellant rocket ruler
It is very little increase, operating pressure improve, for adapt to environmental condition, it is necessary to increase Solid Rocket Motor combustion chamber shell joint thickness and
Width causes connector weight larger, and accounting is very big in Solid Rocket Motor combustion chamber shell quality, becomes solid-rocket hair
Motivation passiveness quality main source.
Summary of the invention
The present invention is directed to overcome prior art defect, it is therefore an objective to provide a kind of Solid Rocket Motor combustion chamber shell lightweight
Connector.
To achieve the above object, a kind of Solid Rocket Motor combustion chamber shell lightweight connector that the present invention uses, including
The inner surface and the outer surface, it is characterised in that the spatial radial section of the inner surface and the outer surface envelope of the connector is hollow out knot
Structure.
Optionally, the engraved structure is to open up weight loss groove.
Preferably, the weight loss groove is filled up using lightweight resistance to compression filler.
Preferably, hollow glass micropearl is mixed in the lightweight resistance to compression filler.
Optionally, the engraved structure is frame-type, and inside setting ring muscle, floor are as support construction, the connector
The inner surface and the outer surface using covering cover.
Preferably, filled and process in the engraved structure frame gap.
Optionally, the engraved structure is dot matrix, and inside uses dot matrix structural support, the inner surface of the connector
It is covered with outer surface using covering.
A kind of Solid Rocket Motor combustion chamber shell lightweight connector of the invention, compared with prior art, connector it is interior
Surface and the spatial radial section of outer surface envelope are engraved structure, reduce the part mass, are not influencing connector force-bearing property
In the case where energy, solid propellant rocket passiveness quality is significantly reduced.
Detailed description of the invention
Fig. 1 is a kind of Solid Rocket Motor combustion chamber shell lightweight connector of the embodiment of the present invention 1, and engraved structure is
Open up loss of weight slot structure schematic diagram；
Fig. 2 is a kind of Solid Rocket Motor combustion chamber shell lightweight connector of the embodiment of the present invention 2, and engraved structure is
Tower structure schematic diagram；
Fig. 3 is a kind of Solid Rocket Motor combustion chamber shell lightweight connector of the embodiment of the present invention 3, and engraved structure is
Dot matrix structural schematic diagram；
Fig. 4 is the part the A dot matrix engraved structure view of Fig. 3.
Wherein, 1- inner surface, the outer surface 2-, 12- spatial radial section, 121- weight loss groove, 21- ring muscle, 22- floor, 31-
Rod piece, 32- upper and lower panel.
Specific embodiment
The invention will be further described With reference to embodiment.
Embodiment 1: a kind of Solid Rocket Motor combustion chamber shell lightweight connector, as shown in Figure 1, including inner surface and outside
Surface, the spatial radial section of the inner surface and the outer surface envelope of the connector is the engraved structure for opening up weight loss groove, described to connect
The material of head is metal, and weight loss groove is circumferentially spaced uniformly to be opened up, then is filled out using lightweight resistance to compression filler by mould pressing process mode
Full weight loss groove, becomes overall structure, lightweight resistance to compression filler can be made of rubber, resin, composite material etc., and can be in above-mentioned material
Hollow glass micropearl is mixed in material, further decreases filling material density.
Embodiment 2: a kind of Solid Rocket Motor combustion chamber shell lightweight connector, as shown in Fig. 2, including inner surface and outside
The spatial radial section on surface, the inner surface and the outer surface envelope of the connector is engraved structure, and engraved structure is frame-type, interior
Ring muscle, floor is arranged as support construction in portion, and the inner surface and the outer surface of connector is covered using covering, becomes overall structure, full
Sufficient structural bearing intensity and toughness requirement.When being manufactured using metal material, ring muscle, floor are processed respectively, inner supporting structure is welded
It is connected in entirety, then welds upper and lower covering, eventually becomes overall structure；The molding of 3D printing manufacturing process can also be used.Using fiber
It when polymer matrix composites manufacture, is formed using RTM or vacuum introducing technology, to fill bubble in gap convenient for process implementing
Foam.
Embodiment 3: a kind of Solid Rocket Motor combustion chamber shell lightweight connector, as shown in figure 3, including inner surface and outside
Surface, the spatial radial section of the inner surface and the outer surface envelope of the connector are dot matrix engraved structure, and inside uses dot matrix
Formula structural support eventually becomes overall structure as shown in figure 4, the inner surface and the outer surface of connector is covered using covering.Dot matrix knot
Structure is a kind of ordered porous structural, and for microstructure similar to crystal lattice structure, making material is model molecule dot matrix configuration system
The orderly ultralight porous periodic network structural material produced, has the characteristics that periodicity, macroporosity, self-balancing, has
The advantages of high specific stiffness, specific strength, saves material under the conditions of identical structural bearing, and connector passiveness quality is effectively reduced.
Metal lattice structure fabrication process can be used investment casting, the deformation method of forming, metal wire knitted method, wire and take
Connect construction from part, increasing material manufacturing method.
Hot pressing, pultrusion or RTM technique can be used in composite material dot matrix structure, first manufacture rod piece, and machine direction can be whole
Along rod piece direction, upper and lower panel is then remanufactured, finally forms lattice structure for rod piece is be bonded with panel.The technology is easily realized certainly
Dynamicization is conducive to produce in enormous quantities.
Claims (4)
1. a kind of Solid Rocket Motor combustion chamber shell lightweight connector, including the inner surface and the outer surface, it is characterised in that described
The spatial radial section of the inner surface and the outer surface envelope of connector is engraved structure；
The engraved structure is to open up weight loss groove；
The weight loss groove is filled up using lightweight resistance to compression filler；
Hollow glass micropearl is mixed in the lightweight resistance to compression filler.
2. Solid Rocket Motor combustion chamber shell lightweight connector according to claim 1, it is characterised in that described engraves
Hollow structure is frame-type, and as support construction, the inner surface and the outer surface of the connector uses covering for inside setting ring muscle, floor
Covering.
3. Solid Rocket Motor combustion chamber shell lightweight connector according to claim 2, it is characterised in that described engraves
Filled and process in hollow structure frame gap.
4. Solid Rocket Motor combustion chamber shell lightweight connector according to claim 1, it is characterised in that described engraves
Hollow structure is dot matrix, and inside uses dot matrix structural support, and the inner surface and the outer surface of the connector is covered using covering.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710306059.7A CN107023419B (en) | 2017-05-03 | 2017-05-03 | A kind of Solid Rocket Motor combustion chamber shell lightweight connector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710306059.7A CN107023419B (en) | 2017-05-03 | 2017-05-03 | A kind of Solid Rocket Motor combustion chamber shell lightweight connector |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107023419A CN107023419A (en) | 2017-08-08 |
| CN107023419B true CN107023419B (en) | 2019-05-03 |
Family
ID=59528195
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710306059.7A Active CN107023419B (en) | 2017-05-03 | 2017-05-03 | A kind of Solid Rocket Motor combustion chamber shell lightweight connector |
Country Status (1)
| Country | Link |
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| CN (1) | CN107023419B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111188698A (en) * | 2020-03-13 | 2020-05-22 | 北京星际荣耀空间科技有限公司 | Radiation cooling thrust chamber body structure for liquid rocket engine |
| CN113770667B (en) * | 2021-08-16 | 2024-03-29 | 中国航发贵阳发动机设计研究所 | Process for processing special-shaped spray pipe heat insulation layer craft type tire |
| CN113663633B (en) * | 2021-08-17 | 2022-10-04 | 合肥中科重明科技有限公司 | Novel hydrogen peroxide multistage catalytic decomposition type gas generator |
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|---|---|---|---|---|
| CN1318130A (en) * | 1998-08-19 | 2001-10-17 | 科丹特技术公司 | Rocket assembly ablative materials formed from, as precursor, staple cellulose fibers, and method of insulating or thermall protecting rocket assembly with same |
| US6889496B2 (en) * | 2002-08-12 | 2005-05-10 | Eads Space Transportation Gmbh | Combustion chamber structure and its manufacturing process |
| US7299622B2 (en) * | 2001-12-18 | 2007-11-27 | Volvo Aero Corporation | Component for being subjected to high thermal load during operation and a method for manufacturing such a component |
| CN101331002A (en) * | 2005-12-16 | 2008-12-24 | 空中客车英国有限公司 | Structural element and method of manufacture |
| CN105035359A (en) * | 2015-07-28 | 2015-11-11 | 中国运载火箭技术研究院 | Composite material integrated control surface structure with progressive decrease in rigidity and processing method thereof |
| CN105966596A (en) * | 2016-06-13 | 2016-09-28 | 江西洪都航空工业集团有限责任公司 | Thickness-variable thin-wall skin structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10126926B4 (en) * | 2001-06-01 | 2015-02-19 | Astrium Gmbh | Internal combustion chamber of a ceramic composite material and method of manufacture |
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2017
- 2017-05-03 CN CN201710306059.7A patent/CN107023419B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1318130A (en) * | 1998-08-19 | 2001-10-17 | 科丹特技术公司 | Rocket assembly ablative materials formed from, as precursor, staple cellulose fibers, and method of insulating or thermall protecting rocket assembly with same |
| US7299622B2 (en) * | 2001-12-18 | 2007-11-27 | Volvo Aero Corporation | Component for being subjected to high thermal load during operation and a method for manufacturing such a component |
| US6889496B2 (en) * | 2002-08-12 | 2005-05-10 | Eads Space Transportation Gmbh | Combustion chamber structure and its manufacturing process |
| CN101331002A (en) * | 2005-12-16 | 2008-12-24 | 空中客车英国有限公司 | Structural element and method of manufacture |
| CN105035359A (en) * | 2015-07-28 | 2015-11-11 | 中国运载火箭技术研究院 | Composite material integrated control surface structure with progressive decrease in rigidity and processing method thereof |
| CN105966596A (en) * | 2016-06-13 | 2016-09-28 | 江西洪都航空工业集团有限责任公司 | Thickness-variable thin-wall skin structure |
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| Publication number | Publication date |
|---|---|
| CN107023419A (en) | 2017-08-08 |
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