CN202954896U - Rocket engine jet pipe expanding section - Google Patents
Rocket engine jet pipe expanding section Download PDFInfo
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- CN202954896U CN202954896U CN 201220673590 CN201220673590U CN202954896U CN 202954896 U CN202954896 U CN 202954896U CN 201220673590 CN201220673590 CN 201220673590 CN 201220673590 U CN201220673590 U CN 201220673590U CN 202954896 U CN202954896 U CN 202954896U
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- extending section
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- jet pipe
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Abstract
The utility model relates to a jet pipe carbon/carbon expanding section which is combined by adopting carbon/carbon composite materials and cloth based reinforcement composite materials (or fiber reinforcement composite materials), and is pressurized, cured and molded. Compared with a traditional jet pipe expanding section, such as carbon cloth/phenolic aldehyde-high-silicon-oxygen cloth/phenolic aldehyde composite wound product expanding sections, the jet pipe carbon/carbon expanding section has the advantages of light weight, light intensity and the like, and is of great application significance in reducing the weight of a jet pipe, and improving performances of the jet pipe and a rocket engine.
Description
Technical field
The utility model relates to a kind of nozzle divergence cone, is specifically related to a kind of rocket tube extending section.
Background technique
Rocket tube mainly is comprised of several parts such as larynx lining, extending section, heat insulation layer and jet pipe housings.Wherein extending section mainly plays a part to make combustion gas to accelerate and produce thrust, it is ablative heat protection member main in jet pipe, general anti-ablation and the thermal-protective material of using processed, its proportion in whole jet pipe weight is very large, therefore extending section selects high-strength material and lighting design for alleviating jet pipe weight, improves nozzle performance very important.
The anti-ablation that the tradition nozzle divergence cone is commonly used and thermal-protective material mainly contain carbon cloth/phenolic aldehyde winding material, high silica cloth/phenolic aldehyde winding material, carbon cloth/phenolic aldehyde-Gao silica cloth/phenolic aldehyde composite winding material, carbon fiber reinforced phenol formaldehyde resin moulding material, high-siloxy fibre enhancing phenolic resin moulding material, high-siloxy fibre-carbon fiber reinforced phenol formaldehyde resin composite coining material etc.
The model utility content
The technical problems to be solved in the utility model is lighting and the designs simplification of Nozzle Design, improves nozzle performance simultaneously.
Reach for achieving the above object other relevant purposes, the utility model provides a kind of inboard rocket tube extending section that adopts carbon/carbon compound material.
Concrete technological scheme is as follows:
A kind of rocket tube extending section, comprise two-part, and inboard is the carbon/carbon compound material extending section, and outer felt is around high silica cloth/phenolic materials layer.
Preferably, described carbon/carbon compound material extending section small end outer mold surface machine adds groove and boss in order to be wound around high silica cloth/phenolic materials.
A kind of rocket tube extending section, comprise two-part, and inboard is the carbon/carbon compound material extending section, and outer felt is around carbon cloth/phenolic materials layer.
Preferably, described carbon/carbon compound material extending section small end outer mold surface machine adds groove and boss in order to be wound around carbon cloth/phenolic materials.
A kind of rocket tube extending section, comprise two-part, and inboard is the carbon/carbon compound material extending section, and outer felt is around carbon cloth/phenolic aldehyde-Gao silica cloth/phenolic composite layer.
Preferably, described carbon/carbon compound material extending section small end outer mold surface machine adds groove and boss in order to be wound around high silica cloth/phenolic aldehyde-carbon cloth/phenolic composite.
Carbon/carbon compound material is the composite material that a kind of intensity is relatively high, density is relatively low.Carbon/carbon compound material is compared with ablative insulative material (as carbon cloth/phenolic aldehyde-Gao silica cloth/phenolic aldehyde composite winding material) and fiber reinforcement phenolic resin composite coining material commonly used, can be made into lightweight, rocket tube extending section simple in structure.The carbon/carbon compound material nozzle divergence cone is compared with traditional nozzle divergence cone, has that ablating rate is low, lightweight, the intensity advantages of higher, for alleviating jet pipe weight, simplify the nozzle structure design, improve nozzle performance and have very important application value.
The accompanying drawing explanation
Fig. 1 has demonstrated a kind of rocket tube extending section structural representation that the present invention proposes.
Shown in figure, mark is as follows: 1, carbon/carbon compound material extending section; 2, high silica cloth/phenolic materials layer.
Embodiment
Below by instantiation, the utility model is described further.
Consult Fig. 1.It should be noted that, the diagram provided in the present embodiment only illustrates basic conception of the present invention in a schematic way.
A kind of rocket tube extending section that the present invention proposes, be applied to solid propellant rocket, its extending section material is carbon/carbon compound material and high silica cloth/phenolic aldehyde winding material or carbon cloth/phenolic aldehyde winding material or carbon cloth/phenolic aldehyde-Gao silica cloth/phenolic aldehyde composite winding Material cladding, and through the cure under pressure moulding.
Embodiment 1
Use carbon/carbon compound material and high silica cloth/phenolic materials to prepare the concrete steps of nozzle divergence cone of solid propellant rocket as follows:
Carbon/carbon compound material extending section 1 blank adopt alternately " without latitude cloth circumferentially be wound around-without latitude cloth generatrix direction laying-charcoal felt laying " moulding process, the technological method by vapor deposition increases density of material.
Carbon/carbon compound material extending section blank is adopted to contact method ultrasonic flaw detection and x-ray detection inspection, get rid of subsurface defect and affect other defect that product is used;
According to the Exit Cone of Solid Rocket Nozzle structure shape, the main technological method that adopts turning, outer mold surface in carbon/carbon compound material extending section blank is carried out to machine to be added, particularly the small end outer mold surface wants machine to add several places groove and boss, because of the characteristic of material itself with for guaranteeing the dimensional accuracy of product, the amount of feed less of each turning;
Carbon/carbon compound material extending section after machine has been added is heat-treated, the stress that the releaser added-time produces, and profile in it is carried out to densification;
According to the Exit Cone of Solid Rocket Nozzle structure shape, be wound around high silica cloth/phenolic materials layer 2 in carbon/carbon compound material extending section outer mold surface, and through the cure under pressure moulding; The groove of described carbon/carbon compound material extending section small end outer mold surface and boss have been wound around high silica cloth/phenolic materials outward in front just, have just guaranteed that the position of carbon/carbon compound material extending section in engine working process keeps and structural integrity;
According to the Exit Cone of Solid Rocket Nozzle structure shape, carbon/carbon compound material and the high silica cloth/composite article outer mold surface of phenolic materials winding are carried out machine and add, a segment structure shape of final molding design point;
Adopt the contact method ultrasonic flaw detection, the combination interface situation of carbon/carbon compound material extending section and high silica cloth/phenolic materials winding product is checked, do not allow the phenomenon of unsticking.
The tensile strength of extending section carbon/carbon compound material (axially) is not less than 90MPa, compression strength (axially) and is not less than that 150MPa, flexural strength (axially) are not less than 150MPa, interlaminar shearing strength is not less than 55MPa, and high silica cloth/phenolic aldehyde, carbon cloth/phenolic aldehyde or carbon cloth/phenolic aldehyde-Gao silica cloth/phenolic aldehyde composite winding goods (GJB3402-1998) performance is tensile strength (axially), is not less than 29MPa, compression strength (axially) and is not less than that 55MPa, flexural strength (axially) are not less than 44MPa, interlaminar shearing strength is not less than 14MPa.Extending section weight can reduce by 40% left and right, and jet pipe weight can reduce by 20% left and right.
Above-mentioned instantiation is to special instruction of the present utility model, and protection domain of the present utility model is not limited to above-mentioned instantiation.For example, the utility model is not only applicable to solid propellant rocket, is equally applicable to liquid propellant rocket engine, hybrid motor etc.Request scope of the present utility model is limited with claims.
Claims (6)
1. a rocket tube extending section, is characterized in that, described extending section comprises two-part, and inboard is the carbon/carbon compound material extending section, and outer felt is around high silica cloth/phenolic materials layer.
2. a kind of rocket tube extending section according to claim 1, is characterized in that, described carbon/carbon compound material extending section small end outer mold surface machine adds groove and boss in order to be wound around high silica cloth/phenolic materials.
3. a rocket tube extending section, is characterized in that, described extending section comprises two-part, and inboard is the carbon/carbon compound material extending section, and outer felt is around carbon cloth/phenolic materials layer.
4. a kind of rocket tube extending section according to claim 3, is characterized in that, described carbon/carbon compound material extending section small end outer mold surface machine adds groove and boss in order to be wound around carbon cloth/phenolic materials.
5. a rocket tube extending section, is characterized in that, described extending section comprises two-part, and inboard is the carbon/carbon compound material extending section, and outer felt is around carbon cloth/phenolic aldehyde-Gao silica cloth/phenolic composite layer.
6. a kind of rocket tube extending section according to claim 5, is characterized in that, described carbon/carbon compound material extending section small end outer mold surface machine adds groove and boss in order to be wound around high silica cloth/phenolic aldehyde-carbon cloth/phenolic composite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220673590 CN202954896U (en) | 2012-11-26 | 2012-11-26 | Rocket engine jet pipe expanding section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220673590 CN202954896U (en) | 2012-11-26 | 2012-11-26 | Rocket engine jet pipe expanding section |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202954896U true CN202954896U (en) | 2013-05-29 |
Family
ID=48460473
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220673590 Expired - Lifetime CN202954896U (en) | 2012-11-26 | 2012-11-26 | Rocket engine jet pipe expanding section |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202954896U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106365666A (en) * | 2015-07-20 | 2017-02-01 | 上海航天设备制造总厂 | Guided missile solid rocket engine carbon/carbon composite material invisible two-dimensional nozzle manufacturing method |
| CN106979095A (en) * | 2017-05-08 | 2017-07-25 | 湖北航天技术研究院总体设计所 | The integrated jet pipe and its manufacture method of a kind of global formation |
| CN108044854A (en) * | 2017-12-14 | 2018-05-18 | 晋西工业集团有限责任公司 | A kind of double glazing fiber reinforced thermoset plastics semi-solid preparation forming method |
| CN108145996A (en) * | 2017-12-14 | 2018-06-12 | 晋西工业集团有限责任公司 | A kind of double glazing fiber reinforcement thermosetting molding semi-solid preparation forming method |
| CN108590890A (en) * | 2018-03-30 | 2018-09-28 | 上海空间推进研究所 | Engine jet pipe extended segment and lance system |
| CN111997781A (en) * | 2020-07-17 | 2020-11-27 | 上海复合材料科技有限公司 | Composite material diffusion section forming method based on RTM (resin transfer molding) process semi-cured surface |
-
2012
- 2012-11-26 CN CN 201220673590 patent/CN202954896U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106365666A (en) * | 2015-07-20 | 2017-02-01 | 上海航天设备制造总厂 | Guided missile solid rocket engine carbon/carbon composite material invisible two-dimensional nozzle manufacturing method |
| CN106979095A (en) * | 2017-05-08 | 2017-07-25 | 湖北航天技术研究院总体设计所 | The integrated jet pipe and its manufacture method of a kind of global formation |
| CN106979095B (en) * | 2017-05-08 | 2019-10-08 | 湖北航天技术研究院总体设计所 | A kind of integrally formed integrated jet pipe and its manufacturing method |
| CN108044854A (en) * | 2017-12-14 | 2018-05-18 | 晋西工业集团有限责任公司 | A kind of double glazing fiber reinforced thermoset plastics semi-solid preparation forming method |
| CN108145996A (en) * | 2017-12-14 | 2018-06-12 | 晋西工业集团有限责任公司 | A kind of double glazing fiber reinforcement thermosetting molding semi-solid preparation forming method |
| CN108590890A (en) * | 2018-03-30 | 2018-09-28 | 上海空间推进研究所 | Engine jet pipe extended segment and lance system |
| CN108590890B (en) * | 2018-03-30 | 2019-12-06 | 上海空间推进研究所 | Nozzle system |
| CN111997781A (en) * | 2020-07-17 | 2020-11-27 | 上海复合材料科技有限公司 | Composite material diffusion section forming method based on RTM (resin transfer molding) process semi-cured surface |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130529 |
|
| CX01 | Expiry of patent term |