CN109838321A - A kind of solid propellant rocket rear head insulating structure and forming method - Google Patents
A kind of solid propellant rocket rear head insulating structure and forming method Download PDFInfo
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- CN109838321A CN109838321A CN201711202704.7A CN201711202704A CN109838321A CN 109838321 A CN109838321 A CN 109838321A CN 201711202704 A CN201711202704 A CN 201711202704A CN 109838321 A CN109838321 A CN 109838321A
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Abstract
The present invention discloses a kind of solid propellant rocket rear head insulating structure and forming method, belongs to solid propellant rocket thermal protection structure heat insulation layer and designs and manufactures field.Rear head insulating structure is difficult to meet lightweight simultaneously at present, the requirement of anti-ablation and antiscour high efficient production and low cost, the present invention is to be insulated ontology as structural support, setting is distributed in convergence big end position after lightweight rubber heat-insulating material is preforming, setting is distributed in convergence narrow passage position after solidified resin class heat-insulating material is preforming, junction, to overlap joint, forms to form integral structure using staged step transition using molding die tooling one piece heat cure.It was verified that each interfacial bonding of rear head insulating structure that the present invention is prepared is reliable, shaping efficiency is high, product good combination property, can preferably meet the synthesis requirement of engine rear head heat insulating construction simultaneously.
Description
Technical field
The invention belongs to solid propellant rocket thermal protection structure heat insulation layers to design and manufacture field, be related to a kind of solid fire
Arrow engine rear head insulating structure and forming method.
Background technique
With the traction that solid propellant rocket high-performance, low cost use, the design of thermal protection structure and molding side
Method increasingly requires reliable adaptability.Rear head as solid propellant rocket important feature component will generally be held
It is rapidly washed away by worse at engine high-temperature high-speed fuel gas stream ablation and convergence, use environment is very severe, while also wanting
Meet other synthesis requirements, such as the consumption for reducing engine power, engine structure is when meeting requirement
Lightweight as far as possible；High-quality and high-efficiency is inexpensive as far as possible in the fabrication process.
Rear head insulating structure design and processes molding at present is generally formed using homogenous material, and it is excellent cannot to take into account synthesis
Gesture, or formed using different function material, it needs to be separately formed different function material, is bonded assembling after processing respectively, deposits
More in molding procedure process, the process-cycle is long, at high cost, the interface combinations bonding reliability feature high not as good as straight forming.Base
In this, the present invention is specifically proposed.
Summary of the invention
The purpose of the present invention is to provide a kind of solid propellant rocket rear head insulating structure and forming methods.It is this
Structure and forming method be using difference stress advantage performance uncured heat-insulating materials after preforming, be correspondingly arranged distribution
Stress the position of performance requirement in rear head insulation ontology difference, using integrally curing of molding die and curing apparatus
Molding can better meet the requirement and manufacture high-quality and high-efficiency low cost requirement of engine rear head heat insulating construction；Due to
It is the molding integral structure of heat cure, each interfacial bonding is reliable, and molding quality and manufacture efficiency have compared with other methods
The raising of essence.
In order to realize the above technical effect, the present invention uses technical solution as described below:
A kind of solid propellant rocket rear head insulating structure comprising insulation ontology 1, the lightweight for restraining big end position
The anti-ablation antiscour heat insulation layer 3 of rubber heat insulation layer 2 and convergence narrow passage.Wherein insulation ontology is as structural support, lightweight
The convergence big end position of insulation ontology is arranged in rubber heat insulation layer, and insulation ontology is arranged in anti-ablation and antiscour heat insulation layer
Narrow passage position is restrained, the junction being distributed after two kinds of materials are preforming, to overlap joint, utilizes tooling using staged step transition
Mold and interchangeable heat press-molding apparatus carry out one piece heat cure on insulation ontology and form to form integrated overall structure.
In the present invention, lightweight rubber heat insulation layer is rubber heat-insulating material, preferably ethylene propylene diene rubber class heat insulating material
Material or nitrile rubber class heat-insulating material；Anti-ablation and antiscour heat insulation layer are the fiber of resistance to ablation or fabric, it is preferable that described is resistance to
Ablation fiber or Fabric composites are carbon fiber wire or fabric or high silica fiber or fabric, the carbon fiber wire or are knitted
Object, high silica fiber or fabric using it is preceding diluted with amine phenolic resin with ethyl acetate after dilution impregnate, more preferably
The maceration extract of ground, the carbon fiber wire or fabric, high silica fiber or fabric be ammonia phenolic resin using ethyl acetate according to
The concentration dilution of mass ratio 3:1 obtains, and resin is more equal in carbon fiber wire or fabric, high silica fiber or fabric coating at this time
It is even；Insulation ontology is metal material.
The present invention also provides a kind of forming methods of solid propellant rocket rear head heat insulation layer, specifically include following step
It is rapid:
1) unvulcanized low-density rubber-type heat-insulating material is preforming, preforming temperature 50 C~90 DEG C, pressure is by pre-
Molding die bearing area and equipment calculation of pressure pressure are 5Mpa~20MPa, preforming time 3min~10min；
2) the uncured heat-insulating material with anti-ablation antiscour is preforming, preforming temperature 70 C~90 DEG C, pressure
Power is 5Mpa~20Mpa, preforming time 0.5h~1h by preforming tool bearing area and equipment calculation of pressure pressure, is closed
Equipment heating, the demoulding of pressure maintaining cooled to room temperature；
3) when being put into insulation ontology after two kinds of heat-insulating materials are preforming, setting after low-density rubber type heat insulation layer is preforming
At convergence big end position, anti-ablation and antiscour heat insulation layer it is preforming after setting at convergence narrow passage position, junction has point
Preforming step-wise transition step is not corresponded to, is interweaved naturally integrally by secondary heating cure under pressure technical process.
Preferably, the interface of the light heat-insulating coating for use and insulation ontology carries out bonding processing, and bonding is using corresponding insulation
The adhesion process of layer glue kind material adaptation is known or industry mature technology；The boundary of anti-ablation and antiscour heat insulation layer and insulation ontology
It does not do bonding processing or coats adhesive identical with light heat-insulating coating for use and the insulation interface of ontology in face.
Preferably, the combination of the step-wise transition step is to overlapping mode, and interface does not have to pre-treating adhesive
Stick.
Preferably, in the secondary heating cure under pressure technique, 150 DEG C of secondary heating cure under pressure forming temperature~
160 DEG C, time 1h~1.5h, pressure is 5Mpa~8MPa by preforming tool bearing area and equipment calculation of pressure pressure.
As a kind of embodiment preferred for this invention, the molding of the solid propellant rocket rear head heat insulation layer
Method specifically includes:
1) unvulcanized low-density rubber-type heat-insulating material in advance at preforming temperature 70 C, time 7min, pressure is by pre-
Molding die bearing area and equipment calculation of pressure pressure are 13MPa；
2) the uncured heat-insulating material with anti-ablation antiscour is preforming, 80 DEG C of preforming temperature, pressure is by pre-
Molding die bearing area and equipment calculation of pressure pressure are 13Mpa, time 0.8h, to the time after pass hull closure heat, pressure maintaining
Cooled to room temperature demoulding；
3) when being put into insulation ontology 1 after two kinds of heat-insulating materials are preforming, the setting of low-density rubber type heat insulation layer 2 is distributed in
Big extreme direction position is restrained, anti-ablation and the preforming rear distribution setting of antiscour heat insulation layer 3 are restraining narrow passage direction position,
Junction, which has, respectively corresponds preforming step-wise transition step 4, is interweaved naturally by secondary heating cure under pressure technical process
One.
In the secondary heating cure under pressure technique, 155 DEG C, time 1.3h of secondary heating cure under pressure forming temperature,
Pressure is 7MPa by preforming tool bearing area and equipment calculation of pressure pressure.
Compared with prior art, beneficial effect obtained by the present invention is: in same part solid propellant rocket rear head
In thermal protection structure, stress different advantage performance thermally protective materials using having, combination is distributed in insulation after preforming
The corresponding demand position of ontology, integrally, forming method is simple, material circle for the primary molding of heat-pressure curing together under certain condition
Face is bonded to form structure-integrated, reliable in quality, and manufacture efficiency is high, at low cost, the different heat-insulating materials especially having complementary advantages
Performance makes solid propellant rocket rear head heat insulating construction weight relative lightweight, makes to engine passiveness weight raising energy is mitigated
With there is positive contribution, its thermal protective performance can be increased substantially to the insulation position for requiring antiscour anti-ablation, there is product
Excellent comprehensive performance.
Detailed description of the invention
Fig. 1 is that a kind of solid propellant rocket rear head of the invention is insulated sided configuration schematic diagram.
Fig. 2 is a kind of solid propellant rocket rear head heat insulating construction unilateral side enlarged diagram of the invention.
Wherein 1- is insulated ontology, 2- lightweight rubber heat insulation layer, 3- anti-ablation and antiscour heat insulation layer, 4- step-wise transition
Step, the interface of 5- light heat-insulating coating for use and insulation ontology, the interface of 6- anti-ablation and antiscour heat insulation layer and insulation ontology.
Specific embodiment
Technical solution of the present invention is further described below in conjunction with drawings and examples, but the embodiment is not with any
Mode limits the range of the invention patent protection.
A kind of solid propellant rocket rear head insulating structure of embodiment 1 and its forming method
As depicted in figs. 1 and 2, a kind of solid propellant rocket rear head insulating structure of the present invention comprising
It is insulated ontology, lightweight rubber heat insulation layer 2 and anti-ablation antiscour heat insulation layer 3, wherein insulation ontology 1 is used as structural support, gently
The convergence big end position for being distributed in insulation ontology, anti-ablation and the setting distribution of antiscour heat insulation layer 3 is arranged in matter rubber heat insulation layer 2
At the convergence narrow passage position of insulation ontology, for two kinds of material interfaces using 4 transition of staged step to overlap joint, described is light
Matter rubber heat insulation layer and anti-ablation and antiscour heat insulation layer are in preforming rear setting progress whole one on insulation ontology respectively
Secondary heat cure forms to form integral structure.
A kind of above-mentioned solid propellant rocket rear head heat insulation layer forming method, specifically comprises the following steps:
1) unvulcanized low-density rubber-type heat-insulating material in advance at preforming temperature 70 C, time 7min, pressure is by pre-
Molding die bearing area and equipment calculation of pressure pressure are 13MPa, to the time after pass hull closure heat, pressure maintaining naturally cools to
Room temperature demoulding；
2) the uncured heat-insulating material with anti-ablation antiscour is preforming, 80 DEG C of preforming temperature, pressure is by pre-
Molding die bearing area and equipment calculation of pressure pressure are 13Mpa, time 0.8h, to the time after pass hull closure heat, pressure maintaining
Cooled to room temperature demoulding；
3) when being put into insulation ontology 1 after two kinds of heat-insulating materials are preforming, the setting of low-density rubber type heat insulation layer 2 is distributed in
Big extreme direction position is restrained, anti-ablation and the preforming rear distribution setting of antiscour heat insulation layer 3 are restraining narrow passage direction position,
Junction, which has, respectively corresponds preforming step-wise transition step 4, is interweaved naturally by secondary heating cure under pressure technical process
One.The bonding of interface 5 of light heat-insulating coating for use 2 and insulation ontology 1 is public using the adhesion process of corresponding heat insulation layer glue kind material adaptation
Know or industry mature technology；Anti-ablation and antiscour heat insulation layer 3 and the coating of interface 6 for being insulated ontology 1 are be bonded with interface 5 identical
Adhesive.
4 combination of stepped transition shoulder is to overlapping mode, and interface does not have to pre-treating adhesive stick.Institute
In the secondary heating cure under pressure technique stated, 155 DEG C, time 1.3h of secondary heating cure under pressure forming temperature, pressure by advance at
Pattern has bearing area and equipment calculation of pressure pressure is 7MPa.
A kind of solid propellant rocket rear head insulating structure of embodiment 2 and its forming method
The structure of the solid propellant rocket rear head heat insulation layer is the same as embodiment 1.In the present invention, light heat-insulating material
For ethylene propylene diene rubber class heat-insulating material；Anti-ablation antiscour heat-insulating material is the fiber of resistance to ablation or fabric, and ontology is metal material
Matter.
A kind of above-mentioned solid propellant rocket rear head heat insulation layer forming method, specifically comprises the following steps:
1) unvulcanized low-density rubber-type heat-insulating material in advance at preforming temperature 50 C, time 3min, pressure is by pre-
Molding die bearing area and equipment calculation of pressure pressure are 5Mpa,；
2) the uncured heat-insulating material with anti-ablation antiscour is preforming, preforming temperature 70 C, pressure is by pre-
Molding die bearing area and equipment calculation of pressure pressure are 5Mpa, time 0.5h, to the time after pass hull closure heat, pressure maintaining from
So it is cooled to room temperature demoulding；
3) when being put into insulation ontology 1 after two kinds of heat-insulating materials are preforming, the setting of low-density rubber type heat insulation layer 2 is distributed in
Big extreme direction position is restrained, anti-ablation and the preforming rear distribution setting of antiscour heat insulation layer 3 are restraining narrow passage direction position,
Junction, which has, respectively corresponds preforming step-wise transition step 4, is interweaved naturally by secondary heating cure under pressure technical process
One.The bonding of interface 5 of light heat-insulating coating for use 2 and insulation ontology 1 is public using the adhesion process of corresponding heat insulation layer glue kind material adaptation
Know or industry mature technology；6 bonding of the interface processing of anti-ablation and antiscour heat insulation layer 3 and insulation ontology 1 does not require.
4 combination of stepped transition shoulder is to overlapping mode, and interface does not have to pre-treating adhesive stick.Institute
In the secondary heating cure under pressure technique stated, 150 DEG C, time 1h of secondary heating cure under pressure forming temperature, pressure is by preforming
Mold bearing area and equipment calculation of pressure pressure are 5Mpa.
A kind of solid propellant rocket rear head insulating structure of embodiment 3 and its forming method
The structure of the solid propellant rocket rear head heat insulation layer is the same as embodiment 1.In the present invention, light heat-insulating material
For nitrile rubber class heat-insulating material；Anti-ablation antiscour heat-insulating material is high silica fiber or fabric, and ontology is metal material.
A kind of above-mentioned solid propellant rocket rear head heat insulation layer forming method, specifically comprises the following steps:
1) unvulcanized low-density rubber-type heat-insulating material in advance at 90 DEG C of preforming temperature, time 10min, pressure is pressed
Preforming tool bearing area and equipment calculation of pressure pressure are 20MPa；
2) the uncured heat-insulating material with anti-ablation antiscour is preforming, 90 DEG C of preforming temperature, pressure is by pre-
Molding die bearing area and equipment calculation of pressure pressure are 20Mpa, time 1h, to the time after pass hull closure heat, pressure maintaining from
So it is cooled to room temperature demoulding；
3) when being put into insulation ontology 1 after two kinds of heat-insulating materials are preforming, the setting of low-density rubber type heat insulation layer 2 is distributed in
Big extreme direction position is restrained, anti-ablation and the preforming rear distribution setting of antiscour heat insulation layer 3 are restraining narrow passage direction position,
Junction, which has, respectively corresponds preforming step-wise transition step 4, is interweaved naturally by secondary heating cure under pressure technical process
One.The bonding of interface 5 of light heat-insulating coating for use 2 and insulation ontology 1 is public using the adhesion process of corresponding heat insulation layer glue kind material adaptation
Know or industry mature technology；Anti-ablation and antiscour heat insulation layer 3 and the coating of interface 6 for being insulated ontology 1 are be bonded with interface 5 identical
Adhesive.
4 combination of stepped transition shoulder is to overlapping mode, and interface does not have to pre-treating adhesive stick.Institute
In the secondary heating cure under pressure technique stated, 160 DEG C of secondary heating cure under pressure forming temperature, time 1h~1.5h, pressure is pressed
Preforming tool bearing area and equipment calculation of pressure pressure are 8MPa.
This rear head insulating structure of the invention and forming method design are selected, and there is difference to stress performance advantage
After uncured heat-insulating material is preforming, it is correspondingly arranged and is distributed in the position that rear head insulation ontology difference stresses requirement,
Using molding die and curing apparatus in certain process conditions integral solidifying next time, it can preferably integrate and meet engine
The requirement and manufacture high-quality and high-efficiency low cost requirement of rear head heat insulating construction.Wherein with efficient and light weight and use reliability
The quality of the preparation-obtained solid propellant rocket rear head heat insulation layer of embodiment 1- embodiment 5 is measured as evaluation criterion,
The reliability of embodiment 1 is higher, and is able to satisfy the standard of efficient and light weight, for the optimal embodiment of the present invention.
Finally, it should be noted that the foregoing is only a preferred embodiment of the present invention, it is not intended to restrict the invention,
Although the present invention is described in detail referring to the foregoing embodiments, for those skilled in the art, still may be used
To modify the technical solutions described in the foregoing embodiments or equivalent replacement of some of the technical features.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (10)
1. a kind of solid propellant rocket rear head insulating structure comprising insulation ontology 1,2 and of lightweight rubber heat insulation layer
Anti-ablation antiscour heat insulation layer 3, wherein insulation ontology is as structural support, with convergent part, lightweight rubber heat insulation layer is set
It sets at the convergence big end position of insulation ontology, the convergence narrow passage portion for being insulated ontology is arranged in anti-ablation and antiscour heat insulation layer
Position, the junction being distributed after two kinds of materials are preforming, to overlap joint, utilize moulds of industrial equipment and interchangeable heat using staged step transition
Press-molding apparatus carries out one piece heat cure on insulation ontology and forms to form integrated overall structure.
2. solid propellant rocket rear head insulating structure according to claim 1, which is characterized in that lightweight rubber
Heat insulation layer is rubber heat-insulating material, and the anti-ablation and antiscour heat insulation layer are the fiber of resistance to ablation or Fabric composites,
The insulation ontology is metal material.
3. solid propellant rocket rear head insulating structure according to claim 2, which is characterized in that the rubber
Class heat-insulating material is ethylene propylene diene rubber class heat-insulating material or nitrile rubber class heat-insulating material；The fiber of resistance to ablation or fabric
Composite material is carbon fiber wire or fabric or high silica fiber or fabric, with amine phenolic resin ethyl acetate before using
Dilution dipping after dilution.
4. solid propellant rocket rear head insulating structure according to claim 3, which is characterized in that the dilution
Liquid is that ammonia phenolic resin is obtained using ethyl acetate according to the concentration dilution of mass ratio 3:1.
5. solid propellant rocket rear head insulating structure according to claim 1 and moulding process, it is characterised in that:
Starting radial position size L general 3mm~8mm of step-wise transition step, the 1/2 of axial docking location B value overall thickness A,
The 1/2 of overlap distance T value overall thickness A.
6. a kind of forming method of solid propellant rocket rear head heat insulation layer, specifically comprises the following steps:
1) unvulcanized low-density rubber-type heat-insulating material is preforming, preforming temperature 50 C~90 DEG C, pressure is by preforming
Mold bearing area and equipment calculation of pressure pressure are 5Mpa~20MPa, preforming time 3min~10min；
2) the uncured heat-insulating material with anti-ablation antiscour is preforming, preforming temperature 70 C~90 DEG C, pressure is pressed
Preforming tool bearing area and equipment calculation of pressure pressure are 5Mpa~20Mpa, preforming time 0.5h~1h, pass hull closure
Heating, the demoulding of pressure maintaining cooled to room temperature；
3) when being put into insulation ontology after two kinds of heat-insulating materials are preforming, it is arranged after low-density rubber type heat insulation layer is preforming exhausted
The convergence big end position of hot ontology, anti-ablation and antiscour heat insulation layer it is preforming after be arranged in insulation ontology convergence narrow passage portion
Position, junction, which has, respectively corresponds preforming step-wise transition step, natural by secondary heating cure under pressure technical process
Interweave one.
7. the forming method of solid propellant rocket rear head heat insulation layer according to claim 6, which is characterized in that described
Light heat-insulating coating for use and the interface of insulation ontology carry out bonding processing, the interface of anti-ablation and antiscour heat insulation layer and insulation ontology
It does not do bonding processing or coats adhesive identical with light heat-insulating coating for use and the insulation interface of ontology.
8. the forming method of solid propellant rocket rear head heat insulation layer according to claim 6, which is characterized in that described
The combination of step-wise transition step be to overlapping mode, interface does not have to pre-treating adhesive stick.
9. the forming method of solid propellant rocket rear head heat insulation layer according to claim 6, which is characterized in that described
Secondary heating cure under pressure technique in, 150 DEG C~160 DEG C of secondary heating cure under pressure forming temperature, time 1h~1.5h, pressure
Power is 5Mpa~8MPa by preforming tool bearing area and equipment calculation of pressure pressure.
10. the forming method of solid propellant rocket rear head heat insulation layer according to claim 6, which is characterized in that its
Specifically comprise the following steps:
1) unvulcanized low-density rubber-type heat-insulating material in advance at preforming temperature 70 C, time 7min, pressure is by preforming
Mold bearing area and equipment calculation of pressure pressure are 13MPa；
2) the uncured heat-insulating material with anti-ablation antiscour is preforming, 80 DEG C of preforming temperature, pressure is by preforming
Mold bearing area and equipment calculation of pressure pressure are 13Mpa, time 0.8h, to the time after pass hull closure heat, pressure maintaining is natural
It is cooled to room temperature demoulding；
3) when being put into insulation ontology 1 after two kinds of heat-insulating materials are preforming, the setting of low-density rubber type heat insulation layer 2 is distributed in convergence
Big extreme direction position, anti-ablation and the preforming rear distribution setting of antiscour heat insulation layer 3 are in convergence narrow passage direction position, handover
Place, which has, respectively corresponds preforming step-wise transition step 4, is interweaved naturally integrally by secondary heating cure under pressure technical process；
In the secondary heating cure under pressure technique, 155 DEG C, time 1.3h of secondary heating cure under pressure forming temperature, pressure
It is 7Mpa by preforming tool bearing area and equipment calculation of pressure pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201711202704.7A CN109838321B (en) | 2017-11-27 | 2017-11-27 | Rear end socket heat insulation layer structure for solid rocket engine and forming method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711202704.7A CN109838321B (en) | 2017-11-27 | 2017-11-27 | Rear end socket heat insulation layer structure for solid rocket engine and forming method |
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| CN109838321A true CN109838321A (en) | 2019-06-04 |
| CN109838321B CN109838321B (en) | 2021-02-02 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110792529A (en) * | 2019-10-18 | 2020-02-14 | 上海新力动力设备研究所 | Solid rocket engine front head inner heat insulation layer and forming method thereof |
| CN111361061A (en) * | 2020-03-26 | 2020-07-03 | 上海航天化工应用研究所 | Automatic control system for vacuum paster on heat insulating layer of combustion chamber and operation method |
| CN112497587A (en) * | 2020-10-27 | 2021-03-16 | 湖北三江航天江北机械工程有限公司 | Method for forming heat insulating layer of fiber-wound engine end socket |
| CN114179392A (en) * | 2021-11-08 | 2022-03-15 | 湖北三江航天江北机械工程有限公司 | Method for forming large-size end socket heat insulation layer |
| CN114456720A (en) * | 2021-12-14 | 2022-05-10 | 湖北三江航天江河化工科技有限公司 | Method for bonding carbon fiber cloth and Ethylene Propylene Diene Monomer (EPDM) material |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5103637A (en) * | 1990-10-24 | 1992-04-14 | Mitsubishi Heavy Industries, Ltd. | Rocket engine combustion chamber |
| CN202832854U (en) * | 2012-08-17 | 2013-03-27 | 湖北航天技术研究院总体设计所 | Combined type heat protective structure in the rear portion of a solid rocket engine combustion chamber |
| CN104875467A (en) * | 2014-02-28 | 2015-09-02 | 湖北航天化学技术研究所 | Resin-based premix and rocket engine housing synchronous thermal-curing and adhesion method |
| CN104960200A (en) * | 2015-05-15 | 2015-10-07 | 湖北三江航天江河化工科技有限公司 | Rubber-based thermal insulation layer patching method |
| CN105437521A (en) * | 2015-12-04 | 2016-03-30 | 湖北三江航天江北机械工程有限公司 | Seal head heat insulating layer forming method and mold of filament winding engine heat insulating structure |
| CN107351421A (en) * | 2016-07-08 | 2017-11-17 | 湖北航天化学技术研究所 | A kind of solid propellant rocket internal insulation and its forming method |
-
2017
- 2017-11-27 CN CN201711202704.7A patent/CN109838321B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5103637A (en) * | 1990-10-24 | 1992-04-14 | Mitsubishi Heavy Industries, Ltd. | Rocket engine combustion chamber |
| CN202832854U (en) * | 2012-08-17 | 2013-03-27 | 湖北航天技术研究院总体设计所 | Combined type heat protective structure in the rear portion of a solid rocket engine combustion chamber |
| CN104875467A (en) * | 2014-02-28 | 2015-09-02 | 湖北航天化学技术研究所 | Resin-based premix and rocket engine housing synchronous thermal-curing and adhesion method |
| CN104960200A (en) * | 2015-05-15 | 2015-10-07 | 湖北三江航天江河化工科技有限公司 | Rubber-based thermal insulation layer patching method |
| CN105437521A (en) * | 2015-12-04 | 2016-03-30 | 湖北三江航天江北机械工程有限公司 | Seal head heat insulating layer forming method and mold of filament winding engine heat insulating structure |
| CN107351421A (en) * | 2016-07-08 | 2017-11-17 | 湖北航天化学技术研究所 | A kind of solid propellant rocket internal insulation and its forming method |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110792529A (en) * | 2019-10-18 | 2020-02-14 | 上海新力动力设备研究所 | Solid rocket engine front head inner heat insulation layer and forming method thereof |
| CN111361061A (en) * | 2020-03-26 | 2020-07-03 | 上海航天化工应用研究所 | Automatic control system for vacuum paster on heat insulating layer of combustion chamber and operation method |
| CN112497587A (en) * | 2020-10-27 | 2021-03-16 | 湖北三江航天江北机械工程有限公司 | Method for forming heat insulating layer of fiber-wound engine end socket |
| CN114179392A (en) * | 2021-11-08 | 2022-03-15 | 湖北三江航天江北机械工程有限公司 | Method for forming large-size end socket heat insulation layer |
| CN114179392B (en) * | 2021-11-08 | 2024-05-07 | 湖北三江航天江北机械工程有限公司 | Forming method of large-size seal head heat insulation layer |
| CN114456720A (en) * | 2021-12-14 | 2022-05-10 | 湖北三江航天江河化工科技有限公司 | Method for bonding carbon fiber cloth and Ethylene Propylene Diene Monomer (EPDM) material |
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|---|---|
| CN109838321B (en) | 2021-02-02 |
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