CN112622305A - Self-adaptive flexible control-following expansion section continuous fiber additive manufacturing method - Google Patents
Self-adaptive flexible control-following expansion section continuous fiber additive manufacturing method Download PDFInfo
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- CN112622305A CN112622305A CN202011603456.9A CN202011603456A CN112622305A CN 112622305 A CN112622305 A CN 112622305A CN 202011603456 A CN202011603456 A CN 202011603456A CN 112622305 A CN112622305 A CN 112622305A
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- expansion section
- carbon
- carbon rod
- ablation
- resistant
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3097—Cosmonautical vehicles; Rockets
Abstract
The invention relates to a method for manufacturing a thermal insulation expansion section of a solid rocket engine nozzle, which comprises the following steps: forming a carbon rod framework by using multi-tow carbon fibers, and fixing the end parts of the carbon rod frameworks to the bottom of a planar tool to construct an expansion section female reinforcing structure; the method comprises the following steps of (1) unfolding a plurality of carbon rod frameworks in the direction of the pneumatic molded surface of a spray pipe, determining the spacing between the carbon rod frameworks at the inlet end of an expansion section of the spray pipe, testing the movement space of a 3D printing head in a weaving process, and then winding and furling the carbon rod frameworks by using a first wire roller; winding the carbon fiber tows coated by the thermoplastic resin on a second wire roller, and continuously winding the carbon fiber tows coated by the thermoplastic resin around a carbon rod framework in S2 by using a 3D printing head to form an ablation-resistant expansion section composite structural unit; and coating the exterior of the ablation-resistant expansion section composite structural unit in the S3 with a flexible ablation-resistant heat-insulating material. The invention can solve the problem of microscopic loss of the flexible ablation-resistant thermal protection material in the preparation process of the variable structure expansion section.
Description
Technical Field
The invention relates to a method for manufacturing a thermal insulation expansion section of a solid rocket engine nozzle, in particular to a method for manufacturing a continuous fiber additive material of a self-adaptive flexible controlled expansion section.
Background
The solid rocket engine is an important power device in the field of missile and aerospace delivery, and high-temperature and high-pressure fuel gas flows and expands at high speed in a spray pipe to generate thrust. The existing solid rocket engine adopts a fixed expansion ratio spray pipe (an extension spray pipe is unfolded in place before the engine is ignited and still belongs to the fixed expansion ratio spray pipe), and a fiber reinforced resin matrix composite material is mainly adopted to manufacture a heat insulation expansion section, so that the solid rocket engine has good structural strength and heat insulation performance. The fixed expansion ratio spray pipe is easy to generate low-altitude under-expansion and high-altitude over-expansion phenomena in the severe flight envelope process of crossing airspace, single-stage in-orbit and the like, the non-adaptive loss reaches about 3-6%, and the fixed expansion ratio spray pipe is equivalent to the research result of a new generation of high-energy propellant and is completely offset. In order to effectively reduce the under-expansion specific loss and the over-expansion gas separation flow loss of the gas, structural forms such as a pneumatic plug type spray pipe and the like are mainly adopted, but the structural forms such as a plug cone-annular throat have high requirements on the heat insulation and ablation resistance, and the current technical level is difficult to adapt to long-time cross-airspace flight.
The flexible variable structure self-adaptive control-following adjustment heat insulation expansion section can utilize the rigid support to drive the flexible structure to be continuously adjusted according to the expansion degree of the fuel gas, so that the self-adaptive change of the optimal fuel gas expansion is realized, and the precise regulation and control of the thrust size and the thrust vector of the engine are realized. The prior nozzle adiabatic expansion section mainly adopts thermosetting phenolic resin, and plain woven cloth is overlapped and wound or a needle punched fabric is used as a reinforcing structure. After the resin is cured, the structural rigidity and the product strength are greatly improved, and the resin is not suitable for further development of complex actions such as flexible unfolding and folding. The technology combines the characteristics of advanced flexible thermal protection materials such as hydrogenated butyronitrile and the like, and realizes the high-precision manufacturing of the flexible variable-structure self-adaptive controllable thermal insulation expansion section by utilizing the continuous fiber additive manufacturing technology.
The novel flexible variable structure of the solid rocket adiabatic expansion section is subjected to complex actions such as unfolding and folding in the working process, and needs to be prepared by adopting advanced flexible ablation-resistant heat-insulating materials such as hydrogenated nitrile rubber. The preparation processes of paving, winding, RTM and the like adopted in the production process of the traditional solid rocket composite material need to be subjected to a harsh later hot pressing process, have the problems of insufficient bonding strength of a fiber matrix, high product porosity, deformation of a fiber preform in the hot pressing curing process and the like, and are difficult to adapt to the preparation of an advanced flexible ablation-resistant heat-insulating material.
Disclosure of Invention
The technical problems to be solved by the invention are as follows:
the invention provides a self-adaptive flexible control-following expansion section continuous fiber additive manufacturing method, which aims to effectively solve the problem of microscopic loss of a flexible ablation-resistant thermal protection material in the preparation process of a variable structure expansion section.
The technical scheme adopted by the invention is as follows:
a self-adaptive flexible controlled expansion section continuous fiber additive manufacturing method comprises the following steps:
s1: forming a carbon rod framework by using multi-tow carbon fibers, and fixing the end parts of the carbon rod frameworks to the bottom of a planar tool to construct an expansion section female reinforcing structure;
s2: the method comprises the following steps of (1) unfolding a plurality of carbon rod frameworks in the direction of the pneumatic molded surface of a spray pipe, determining the spacing between the carbon rod frameworks at the inlet end of an expansion section of the spray pipe, testing the movement space of a 3D printing head in a weaving process, and then winding and furling the carbon rod frameworks by using a first wire roller;
s3: winding the carbon fiber tows coated by the thermoplastic resin on a second wire roller, and continuously winding the carbon fiber tows coated by the thermoplastic resin around a carbon rod framework in S2 by using a 3D printing head to form an ablation-resistant expansion section composite structural unit;
s4: and coating the exterior of the ablation-resistant expansion section composite structural unit in the S3 with a flexible ablation-resistant heat-insulating material.
Further, the carbon fiber is T800 or T1000.
Further, in S3, as the carbon fiber tows coated with the thermoplastic resin gradually move up and down, the carbon rod skeleton is positioned by laser, and the winding density of the carbon fiber tows coated with the thermoplastic resin is adjusted.
Further, the flexible ablation-resistant heat-insulating material adopts hydrogenated nitrile rubber.
The invention has the following beneficial effects:
the prior solid rocket engine adiabatic expansion section is prepared by adopting a resin base or a carbon/carbon composite material, and the structural strength of the expansion section is high. But under the complex working conditions of across airspace, high overload maneuver and the like, the engine has no self-adaptive random control and regulation capacity, and the non-adaptive loss of the engine reaches 3% -6%. According to the invention, a flexible variable structure self-adaptive random control adjustment heat insulation expansion section is prepared by utilizing a continuous fiber additive manufacturing technology and combining a light flexible heat protection material, so that an aircraft can drive a flexible structure to continuously adjust by utilizing a rigid support according to the expansion degree of fuel gas of an engine, the self-adaptive change of the optimal fuel gas expansion is realized, and the precise regulation and control of the thrust magnitude and the thrust vector of the engine are realized.
Drawings
FIG. 1: a schematic view of a circular cross section at the bottom of the expansion section plane tool;
FIG. 2: the skeleton carbon fiber is unfolded upwards;
FIG. 3: expanding section weaving schematic diagram;
wherein: 1. the manufacturing method comprises the following steps of (1) fixing a circular cross section by inner-layer skeleton carbon fibers, (2) dragging tracks of continuous fiber hot-melt resin additive manufacturing nozzles, and (3) fixing a circular cross section by outer-layer skeleton carbon fibers, (4) a third wire roller, 5) thermoplastic resin wires, 6) continuous fibers, 7) a second wire roller, 8 nozzles and 9.3D printing heads.
Detailed Description
In order to make the objects and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the following examples. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
A self-adaptive flexible controlled expansion section continuous fiber additive manufacturing method comprises the following steps:
s1: as shown in fig. 1, a carbon rod skeleton is formed by using multi-filament carbon fibers, ends of the multi-filament carbon rod skeleton are fixed at the bottom of a planar tool to construct an expansion section female-direction reinforcing structure, and in the arrangement process, it should be noted that inner profiles and outer profiles are fixed with circular cross sections, and multi-layer circular cross sections can be arranged, wherein in some embodiments, carbon fibers can be adopted, the carbon fibers adopt T800, and in other embodiments, the carbon fibers adopt T1000;
s2: as shown in fig. 2, a plurality of carbon rod frameworks are unfolded according to the direction of the pneumatic molded surface of the spray pipe, the spacing between the carbon rod frameworks at the inlet end of the expansion section of the spray pipe is determined, the movement space of the 3D printing head in the weaving process is tested, and then the carbon rod frameworks are wound and collected by using a first wire roller;
s3: as shown in fig. 3, the carbon fiber tows coated by the thermoplastic resin are wound on the second wire roller, and the carbon fiber tows coated by the thermoplastic resin are continuously wound around the carbon rod framework in S2 by using the 3D printing head to form an ablation-resistant expansion section composite structural unit, wherein the carbon rod framework is positioned by laser as the carbon fiber tows coated by the thermoplastic resin gradually accumulate and move upwards, and the winding density of the carbon fiber tows coated by the thermoplastic resin is adjusted;
s4: coating the exterior of the composite structural unit of the ablation-resistant expansion section in the S3 with a flexible ablation-resistant heat-insulating material, wherein in some embodiments, the flexible ablation-resistant heat-insulating material adopts hydrogenated nitrile rubber.
Claims (4)
1. A self-adaptive flexible controlled expansion section continuous fiber additive manufacturing method is characterized by comprising the following steps:
s1: forming a carbon rod framework by using multi-tow carbon fibers, and fixing the end parts of the carbon rod frameworks to the bottom of a planar tool to construct an expansion section female reinforcing structure;
s2: the method comprises the following steps of (1) unfolding a plurality of carbon rod frameworks in the direction of the pneumatic molded surface of a spray pipe, determining the spacing between the carbon rod frameworks at the inlet end of an expansion section of the spray pipe, testing the movement space of a 3D printing head in a weaving process, and then winding and furling the carbon rod frameworks by using a first wire roller;
s3: winding the carbon fiber tows coated by the thermoplastic resin on a second wire roller, and continuously winding the carbon fiber tows coated by the thermoplastic resin around a carbon rod framework in S2 by using a 3D printing head to form an ablation-resistant expansion section composite structural unit;
s4: and coating the exterior of the ablation-resistant expansion section composite structural unit in the S3 with a flexible ablation-resistant heat-insulating material.
2. The adaptive flexible controlled expansion segment continuous fiber additive manufacturing method according to claim 1, characterized in that: the carbon fiber adopts T800 or T1000.
3. The adaptive flexible controlled expansion segment continuous fiber additive manufacturing method according to claim 1, characterized in that: and in the step S3, laser positioning is performed on the carbon rod skeleton as the carbon fiber tows coated with the thermoplastic resin gradually accumulate and move upwards, and the winding density of the carbon fiber tows coated with the thermoplastic resin is adjusted.
4. The adaptive flexible controlled expansion segment continuous fiber additive manufacturing method according to claim 1, characterized in that: the flexible ablation-resistant heat-insulating material is hydrogenated nitrile rubber.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011603456.9A CN112622305A (en) | 2020-12-30 | 2020-12-30 | Self-adaptive flexible control-following expansion section continuous fiber additive manufacturing method |
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| CN202011603456.9A CN112622305A (en) | 2020-12-30 | 2020-12-30 | Self-adaptive flexible control-following expansion section continuous fiber additive manufacturing method |
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| CN112622305A true CN112622305A (en) | 2021-04-09 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114437382A (en) * | 2022-03-08 | 2022-05-06 | 内蒙古工业大学 | Thermal protection material, adiabatic expansion section and preparation method thereof |
| CN114964799A (en) * | 2022-04-28 | 2022-08-30 | 南京航空航天大学 | State monitoring system and method under multiple temperature gradients of rocket engine expansion section |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB988930A (en) * | 1960-03-24 | 1965-04-14 | Bristol Aerojet Ltd | Improvements relating to articles with protective covering layers |
| US3358933A (en) * | 1962-09-14 | 1967-12-19 | Aerojet General Co | Rocket nozzle with automatically adjustable auxiliary nozzle portion |
| CN101811365A (en) * | 2009-02-20 | 2010-08-25 | 南京航空航天大学 | Forming method of 2.5-dimensional weaving revolving solid composite material |
| CN102634092A (en) * | 2012-04-13 | 2012-08-15 | 中国兵器工业集团第五三研究所 | Fiber filled anti-ablation hydrogenated nitrile-butadiene rubber |
| CN109914031A (en) * | 2019-03-11 | 2019-06-21 | 陕西元丰纺织技术研究有限公司 | The net shape Preparation Method of three-dimensional high-pressure nozzle precast body |
-
2020
- 2020-12-30 CN CN202011603456.9A patent/CN112622305A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB988930A (en) * | 1960-03-24 | 1965-04-14 | Bristol Aerojet Ltd | Improvements relating to articles with protective covering layers |
| US3358933A (en) * | 1962-09-14 | 1967-12-19 | Aerojet General Co | Rocket nozzle with automatically adjustable auxiliary nozzle portion |
| CN101811365A (en) * | 2009-02-20 | 2010-08-25 | 南京航空航天大学 | Forming method of 2.5-dimensional weaving revolving solid composite material |
| CN102634092A (en) * | 2012-04-13 | 2012-08-15 | 中国兵器工业集团第五三研究所 | Fiber filled anti-ablation hydrogenated nitrile-butadiene rubber |
| CN109914031A (en) * | 2019-03-11 | 2019-06-21 | 陕西元丰纺织技术研究有限公司 | The net shape Preparation Method of three-dimensional high-pressure nozzle precast body |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114437382A (en) * | 2022-03-08 | 2022-05-06 | 内蒙古工业大学 | Thermal protection material, adiabatic expansion section and preparation method thereof |
| CN114964799A (en) * | 2022-04-28 | 2022-08-30 | 南京航空航天大学 | State monitoring system and method under multiple temperature gradients of rocket engine expansion section |
| CN114964799B (en) * | 2022-04-28 | 2023-09-29 | 南京航空航天大学 | State monitoring system and method under multiple temperature gradients of rocket engine expansion section |
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