CN-121993318-A - Solid rocket engine combustion chamber shell heat protection sleeve, external protection structure and forming method thereof

CN121993318ACN 121993318 ACN121993318 ACN 121993318ACN-121993318-A

Abstract

The invention discloses a heat protection sleeve, an external protection structure and a forming method thereof of a combustion chamber shell of a solid rocket engine, which belong to the technical field of heat protection structures, wherein the heat protection sleeve comprises a structural layer, interlayer fibers and a heat insulation layer which are sequentially arranged from outside to inside; the structure layer adopts a 2.5D weaving, three-way orthogonal weaving or three-dimensional four-way weaving mode integral weaving structure, the heat insulation layer adopts a quartz glass net tire or a high silica glass net tire combined with a needling mode to form a prefabricated body, the interlayer fiber adopts a stitching or needling mode to introduce normal fiber between the structure layer and the heat insulation layer, and the stitching depth is only up to the surface layer of the heat insulation layer. The invention realizes the integrated molding of the engine shell through the integral braiding prefabricated body and the molding process, greatly shortens the production period, reduces the repair rate, reduces the manpower and energy loss, improves the assembly efficiency, enhances the thermal protection performance, and has good environmental protection performance and strong high temperature resistance.

Inventors

REN LIANG
WANG DONGMEI
JIANG PENGFEI
SUN LI
WANG QIKUN
GAO HONGCHENG

Assignees

北京玻钢院复合材料有限公司

Dates

Publication Date: 20260508
Application Date: 20251226

Claims (5)

1. The heat protection sleeve is characterized by comprising a structural layer, interlayer fibers and a heat insulation layer which are sequentially arranged from outside to inside; The structure layer adopts a 2.5D weaving, three-way orthogonal weaving or three-dimensional four-way weaving mode integral weaving structure, the heat insulation layer adopts a quartz glass net tire or a high silica glass net tire combined with a needling mode to form a prefabricated body, the interlayer fiber adopts a stitching or needling mode to introduce normal fiber between the structure layer and the heat insulation layer, and the stitching depth is only up to the surface layer of the heat insulation layer.
2. The solid rocket engine combustion chamber shell heat protection sleeve according to claim 1, wherein the structural layer is made of high Jiang Danying glass fiber or high silica glass fiber materials, the heat insulation layer is made of quartz glass fiber/high silica glass fiber net tires and chopped fibers, and the interlayer fibers are made of quartz glass fiber yarns or high silica glass fiber yarns.
3. The solid rocket engine combustion chamber shell heat protection sleeve according to claim 1 is characterized in that the heat protection sleeve is fully permeated by liquid resin through Resin Transfer Molding (RTM), vacuum infusion or vacuum introduction, and the liquid resin is barium phenolic resin or other modified ablation resistant resin with good fluidity, and the temperature is set to 60-120 ℃ and the curing time is set to 1-4 hours according to the requirements of a resin system.
4. The outer anti-theft structure of the solid rocket engine combustion chamber shell is characterized by comprising a thermal protection sleeve and a buffer layer which are arranged from outside to inside; The thermal protection sleeve comprises a structural layer, interlayer fibers and a heat insulation layer which are sequentially arranged from outside to inside; The structure layer adopts a 2.5D weaving, three-way orthogonal weaving or three-dimensional four-way weaving mode integral weaving structure, the heat insulation layer adopts a quartz glass net tire or a high silica glass net tire to form a prefabricated body in a combined needling mode, the interlayer fiber adopts a stitching or needling mode to introduce normal fiber between the structure layer and the heat insulation layer, and the stitching depth is only up to the surface layer of the heat insulation layer; The buffer layer comprises a 0.5-1 mm PI foam layer and a 0.1mm epoxy adhesive film which are arranged from outside to inside, wherein an epoxy adhesive is coated on the surface of the PI foam layer, the PI foam layer is aired for 10-20 min to a semi-cured state, the clearance between the thermal protection sleeve and the PI foam layer of the buffer layer is adjusted to be less than 0.1mm, and the PI foam layer is pressurized and cured for 2-4 h at 60 ℃.
5. A method of forming a solid rocket engine combustion chamber housing outer barrier structure as recited in claim 4, comprising the steps of: Step S1, integrally weaving a structural layer by adopting a 2.5D weaving, three-way orthogonal weaving or three-dimensional four-way weaving process; step S2, forming a preform by adopting a quartz glass net tire or a high silica glass net tire in combination with a needling process; S3, introducing normal fibers between the structural layer and the heat insulation layer in a sewing or needling mode, wherein the sewing depth is only up to the surface layer of the heat insulation layer and penetration is avoided; S4, fully penetrating the preform by Resin Transfer Molding (RTM), vacuum infusion or vacuum introduction process, and setting the temperature to be 60-120 ℃ and the curing time to be 1-4 hours according to the requirements of a resin system; Step S5, polishing and cleaning the surface of the combustion chamber composite shell, wherein the polishing and cleaning treatment comprises the steps of adopting a pneumatic polisher to coarsely polish the surface of the fiber winding layer, locally using abrasive paper for 400-600 meshes for fine finishing, and wiping with acetone or isopropanol to remove floating ash, so that the cleaning of a base material is ensured; step S6, attaching an epoxy adhesive film with the thickness of 0.1mm, paving a PI foam layer with the thickness of 0.5-1 mm, brushing an epoxy adhesive on the surface of the PI foam layer, and airing for 10-20 min to a semi-cured state; S7, preassembling a thermal protection sleeve, applying continuous pressure to align the thermal protection sleeve with the end face of the skirt by using a sleeving tool, adjusting the clearance between the thermal protection sleeve and a PI foam layer to be less than 0.1mm, and pressurizing and curing for 2-4 hours at 60 ℃; and S8, cutting the margins at the two ends of the lathe to enable the thermal protection sleeve to be flush with the end faces of the front skirt and the rear skirt, wherein the precision is +/-0.05 mm.

Description

Solid rocket engine combustion chamber shell heat protection sleeve, external protection structure and forming method thereof Technical Field The invention belongs to the technical field of heat-proof structures, in particular to a thermal protection sleeve, an external protection structure and a forming method of a solid rocket engine combustion chamber shell. Background Aiming at the severe working condition that a solid rocket engine shell bears 800-1000 ℃ pneumatic heating under high Mach number flight (Ma=6-7), the current ablation heat protection technology relies on epoxy external heat protection coatings and rubber external heat protection coatings, but the two external heat protection coatings have inherent defects that the long-term reliability of the epoxy coatings (high strength and low elongation) is difficult to ensure due to the crack/falling risk of the storage period, and the rubber coatings (high elongation and low strength) are easy to mechanically damage in assembly. In addition, the traditional serial spraying technology restricts the production efficiency and limits the feasibility of large-scale application of equipment. The invention aims to break through the bottleneck of the prior art through material system optimization and process route innovation, and realize low-cost and high-reliability upgrading of the heat-proof structure. Disclosure of Invention The invention aims to overcome the defects in the prior art and provide a solid rocket engine combustion chamber shell heat protecting sleeve, an external protecting structure and a forming method thereof, wherein the integral forming of the engine shell is realized through an integral braiding prefabricated body and a forming process, the production period is greatly shortened, the repair rate is reduced, the manpower and energy loss are reduced, meanwhile, the assembly efficiency is improved, the heat protecting performance is enhanced, and the solid rocket engine combustion chamber shell heat protecting sleeve is good in environmental protection performance and strong in high temperature resistance. In order to achieve the above purpose, the invention is realized by adopting the following technical scheme: in a first aspect, the invention provides a solid rocket engine combustion chamber shell heat protection sleeve, which comprises a structural layer, interlayer fibers and a heat insulation layer which are sequentially arranged from outside to inside; The structure layer adopts a 2.5D weaving, three-way orthogonal weaving or three-dimensional four-way weaving mode integral weaving structure, the heat insulation layer adopts a quartz glass net tire or a high silica glass net tire combined with a needling mode to form a prefabricated body, the interlayer fiber adopts a stitching or needling mode to introduce normal fiber between the structure layer and the heat insulation layer, and the stitching depth is only up to the surface layer of the heat insulation layer. Furthermore, the structural layer is made of high Jiang Danying glass fiber or high silica glass fiber materials, the heat insulation layer is made of quartz glass fiber/high silica glass fiber net tyre and chopped fiber reinforcement, and the interlayer fiber is made of quartz glass fiber yarns or high silica glass fiber yarns. Further, the thermal protection sleeve fully permeates liquid resin by adopting Resin Transfer Molding (RTM), vacuum infusion or vacuum introduction process, and the liquid resin adopts barium phenolic resin or other modified ablation-resistant resin with good fluidity, and the temperature is set to be 60-120 ℃ and the curing time is set to be 1-4 hours according to the requirements of a resin system. In a second aspect, the invention provides an external anti-theft structure of a combustion chamber shell of a solid rocket engine, which comprises a thermal protection sleeve and a buffer layer which are arranged from outside to inside; The thermal protection sleeve comprises a structural layer, interlayer fibers and a heat insulation layer which are sequentially arranged from outside to inside; The structure layer adopts a 2.5D weaving, three-way orthogonal weaving or three-dimensional four-way weaving mode integral weaving structure, the heat insulation layer adopts a quartz glass net tire or a high silica glass net tire to form a prefabricated body in a combined needling mode, the interlayer fiber adopts a stitching or needling mode to introduce normal fiber between the structure layer and the heat insulation layer, and the stitching depth is only up to the surface layer of the heat insulation layer; The buffer layer comprises a 0.5-1 mm PI foam layer and a 0.1mm epoxy adhesive film which are arranged from outside to inside, wherein an epoxy adhesive is coated on the surface of the PI foam layer, the PI foam layer is aired for 10-20 min to a semi-cured state, the clearance between the thermal protection sleeve and the PI foam layer of the buffer