CN104564424A - Material for back-wall insulating layer of throat liner of solid rocket engine - Google Patents
Material for back-wall insulating layer of throat liner of solid rocket engine Download PDFInfo
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- CN104564424A CN104564424A CN201310501751.7A CN201310501751A CN104564424A CN 104564424 A CN104564424 A CN 104564424A CN 201310501751 A CN201310501751 A CN 201310501751A CN 104564424 A CN104564424 A CN 104564424A
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- Prior art keywords
- insulation layer
- solid rocket
- heat insulation
- backing
- throat
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Abstract
The invention provides material for a back-wall insulating layer of a throat liner of a solid rocket engine. The material comprises 4 to 8% of high-silica prepreg volatile, 23 to 41% of barium-phenolic resin and not greater than 73% of soluble resin; the material is applied generally to the back-wall insulating layer of carbon-carbon throat liner material; the throat liner and a back liner are in clearance fit, ranging from 0.03 mm to 0.06 mm; raw materials of the material are green and energy efficient, the material is lower in price, good in insulating performance and high in specific strength, and the material can function in well insulating the nozzle throat of the solid rocket engine.
Description
Technical field
The present invention relates to field of compound material, particularly a kind of material for solid propellant rocket larynx backing wall heat insulation layer.
Background technique
The jet pipe throat lining material of current middle-size and small-size solid propellant rocket generally adopts antiscour, anti-yaw damper composite material of good performance, and at the better composite material of jet pipe throat lining back wall parcel heat-insulating property, remain in suitable happy temperature range to reach nozzle throat outside wall temperature in engine working process, do not occur heating up too fast to such an extent as to affecting the situation that jet pipe outer remaining parts normally works.Throat's back wall heat insulation layer material many employings asbestos/phenolic aldehyde, graphite and carbon/phenolic aldehyde etc.Can enter out pyrolysis gas after asbestos/phenolic aldehyde is heated, must arrange ease gas passage during design, the complexity adding laryngeal structure reduces the margin of safety of laryngeal structure, and asbestos can produce harmful dust harm operator ' s health in course of working.The anti-compression properties of graphite material is weak, under high pressure easily occurs that crackle even ruptures, affects engine health work.Carbon/phenolic materials is expensive, and cost is higher.
Summary of the invention
The object of the invention is for the deficiency in above-mentioned technology, provide one to have enough mechanical ratio intensity, possess outstanding heat-insulating property and the relatively low nozzle throat back wall heat insulation layer material of manufacture cost.
A kind of heat insulation layer material for solid rocket motor nozzle larynx backing wall provided by the present invention, comprising: high silica prepreg cloth fugitive constituent 4 ~ 8%, ba phenolic resin content 23 ~ 41%, soluble resin content≤73%.
Further, the manufacturing process of heat insulation layer is winding process, and winding process is wound in parallel or oblique winding process.
Further, throat liner material adopts carbon-carbon composite.
Further, be Spielpassung between larynx lining and backing (back wall heat insulation layer), Spielpassung amount is between 0.03mm ~ 0.06mm.
Further, backing thickness is not less than 10mm.
The larynx backing wall heat insulation layer backing adopting this material to make, reliable heat-shielding performance can be provided to keep nozzle throat outside wall temperature to be suitable for for throat, itself specific strength is also high, can not occur crackle because of the effect of High Temperature High Pressure, and relative low price, be the elite clone making jet pipe backing.
Embodiment
Hereafter nozzle throat back wall heat insulation layer material provided by the invention is described further in conjunction with the embodiments.
First embodiment
For a heat insulation layer material for solid rocket motor nozzle larynx backing wall, comprising: high silica prepreg cloth fugitive constituent, the ba phenolic resin of 25%, the soluble resin of 71% of 4%.
Second embodiment
For a heat insulation layer material for solid rocket motor nozzle larynx backing wall, comprising: the high silica prepreg cloth fugitive constituent of 7 %, the ba phenolic resin of 40%, the soluble resin of 53%.
3rd embodiment
For a heat insulation layer material for solid rocket motor nozzle larynx backing wall, comprising: the high silica prepreg cloth fugitive constituent of 7 %, the ba phenolic resin of 32%, the soluble resin of 61%.
The backing that the present invention produces is winding product, and winding process also can adopt oblique winding for wound in parallel.Throat liner material generally adopts carbon-carbon composite, and be Spielpassung between larynx lining and backing, Spielpassung amount is between 0.03mm ~ 0.06mm.Backing thickness is not less than 10mm.
Heat insulation layer material for solid rocket motor nozzle larynx backing wall provided by the invention is for certain tactics air-to-air missile.In certain tactics air-to-air missile engine jet pipe, adopt this material as throat's back wall heat insulation layer, larynx lining adopts felt carbon-carbon composite.Throat's outside wall temperature is at rocket engine ground test, and all can keep suitable temperature in Missile Ground test and altitude test, the steering gear flat for jet pipe outside provides safe working environment, and the decomposition after engine test does not all occur crackle in dissecting.
Advantage of the present invention adopts the nozzle throat back wall heat insulation layer of this material manufacture not only to have good heat-shielding performance, and have enough specific strengths, not easily occur crackle, and manufacturing process is simple, relative inexpensiveness in the process of engine operation.
Although the present invention with preferred embodiment openly as above; but it is not for limiting the present invention; any those skilled in the art without departing from the spirit and scope of the present invention; the Method and Technology content of above-mentioned announcement can be utilized to make possible variation and amendment to technical solution of the present invention; therefore; every content not departing from technical solution of the present invention; the any simple modification done above embodiment according to technical spirit of the present invention, equivalent variations and modification, all belong to the protection domain of technical solution of the present invention.
Claims (5)
1. for a material for solid rocket motor nozzle larynx backing wall heat insulation layer, it is characterized in that, comprising: high silica prepreg cloth fugitive constituent 4 ~ 8%, ba phenolic resin content 23 ~ 41%, soluble resin content≤73%.
2. the material for solid rocket motor nozzle larynx backing wall heat insulation layer according to claim 1, is characterized in that, the manufacturing process of heat insulation layer is winding process, and winding process is wound in parallel or oblique winding process.
3. according to claim 1 and the material for solid rocket motor nozzle larynx backing wall heat insulation layer required described in 2, it is characterized in that, throat liner material adopts carbon-carbon composite.
4. the material for solid rocket motor nozzle larynx backing wall heat insulation layer according to claim 1, is characterized in that, be Spielpassung between larynx lining and backing, Spielpassung amount is between 0.03mm ~ 0.06mm.
5. the material for solid rocket motor nozzle larynx backing wall heat insulation layer according to claim 1, it is characterized in that, backing thickness is not less than 10mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310501751.7A CN104564424A (en) | 2013-10-23 | 2013-10-23 | Material for back-wall insulating layer of throat liner of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310501751.7A CN104564424A (en) | 2013-10-23 | 2013-10-23 | Material for back-wall insulating layer of throat liner of solid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104564424A true CN104564424A (en) | 2015-04-29 |
Family
ID=53081312
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310501751.7A Pending CN104564424A (en) | 2013-10-23 | 2013-10-23 | Material for back-wall insulating layer of throat liner of solid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104564424A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1198491A (en) * | 1967-07-17 | 1970-07-15 | Hitco | Unitary Bodies an Method of Making the Same |
| CN101121291A (en) * | 2007-09-19 | 2008-02-13 | 西安航天复合材料研究所 | Method for solidifying cloth band winding phenoic composite material product |
| CN102555103A (en) * | 2011-12-29 | 2012-07-11 | 西安航天复合材料研究所 | Preparation method for domestic carbon cloth pre-impregnated adhesive tape |
| CN202360245U (en) * | 2011-11-21 | 2012-08-01 | 湖北航天技术研究院总体设计所 | Simplified combined nozzle structure of engine |
-
2013
- 2013-10-23 CN CN201310501751.7A patent/CN104564424A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1198491A (en) * | 1967-07-17 | 1970-07-15 | Hitco | Unitary Bodies an Method of Making the Same |
| CN101121291A (en) * | 2007-09-19 | 2008-02-13 | 西安航天复合材料研究所 | Method for solidifying cloth band winding phenoic composite material product |
| CN202360245U (en) * | 2011-11-21 | 2012-08-01 | 湖北航天技术研究院总体设计所 | Simplified combined nozzle structure of engine |
| CN102555103A (en) * | 2011-12-29 | 2012-07-11 | 西安航天复合材料研究所 | Preparation method for domestic carbon cloth pre-impregnated adhesive tape |
Non-Patent Citations (2)
| Title |
|---|
| 中国航天工业总公司: "《碳纤维/酚醛-高硅氧纤维/酚醛复合模压制品规范》", 26 April 1995, article "预混料" * |
| 张麟 等: "HGB改性酚醛/高硅氧布复合材料的制备及性能", 《工程塑料应用》 * |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150429 |
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| RJ01 | Rejection of invention patent application after publication |