CN-122014988-A - Composite gas cylinder support structure and processing method thereof

CN122014988ACN 122014988 ACN122014988 ACN 122014988ACN-122014988-A

Abstract

The invention relates to the technical field of aerospace high-pressure gas cylinder supporting structures and processing, and discloses a composite gas cylinder support structure and a processing method thereof, wherein the composite gas cylinder comprises a titanium alloy TA2 lining, a carbon fiber winding reinforcing layer and a support, and the support is a TC4 titanium alloy integral support; the titanium alloy TA2 lining is formed by adopting an inserting structure through electron beam welding by an upper half shell and a lower half shell. Compared with the prior art, the composite gas cylinder support structure and the processing method thereof have the advantages that an integrated support design is matched with an integrated connection mode of a carbon fiber winding fixing layer to replace mechanical/welding connection of a traditional titanium alloy support, the connection strength and the integral rigidity of the support and a gas cylinder are improved, the adverse effect of circumferential compression stress on a pressure container is avoided due to the design of a flat ellipsoidal seal head, the annular bursting pressure of the gas cylinder is far higher than the working pressure requirement due to the accurate longitudinal design of a ring 6 of a carbon fiber winding reinforcing layer, and the requirement of aerospace high-pressure working conditions is met.

Inventors

ZHAO SHUAI
HE HAIYAN
GUAN NINGNING
ZHAO SHUANG
MENG LILI
TAI SHENGHUI
LI DANDAN
LI ZHAOJUN
LENG XIAOWEI
WANG JIANMIN
XIA ZHIMING
XU CHAO

Assignees

辽宁美托科技股份有限公司

Dates

Publication Date: 20260512
Application Date: 20260410

Claims (9)

1. The composite gas cylinder support structure comprises a composite gas cylinder and is characterized by comprising a titanium alloy TA2 lining (1), a carbon fiber winding reinforcing layer (2), a support (3), a pasting disc (4) and a carbon fiber winding fixing layer (5); The support (3) is a TC4 titanium alloy integral support, one side of the patch (4) is provided with the support (3), the inside of the support (3) is provided with a titanium alloy TA2 lining (1), the outer wall of the titanium alloy TA2 lining (1) is wound with a carbon fiber winding reinforcing layer (2), and the outer side of the support (3) is wound with a carbon fiber winding fixing layer (5); The titanium alloy TA2 lining is formed by adopting an inserting structure to weld an upper half shell and a lower half shell through electron beams, the outer profiles of the upper half shell and the lower half shell are ellipsoids, and a bus equation is The wall thickness of the cylinder body of the titanium alloy TA2 lining is 0.7mm, the bottom thickness of the sealing head is 2.5mm, the bottom height of the sealing head is 41.47mm, the inner diameter D i of the lining is 165.5mm, the design requirement of the flat ellipsoidal sealing head is met by 0.5-2H/D i -0.7071, and H is the bottom height; The carbon fiber winding reinforcing layer (2) comprises a circumferential winding layer and a spiral winding layer, the carbon fiber winding reinforcing layer is prepared by adopting a wet fiber winding forming process, the circumferential winding layer is 16 rings, the thickness of a single layer is 0.208mm, the total thickness is 3.328mm, the spiral winding layer is 6 longitudinal, the thickness of the single layer is 0.202mm, the total thickness is 2.424mm, and the total thickness of the carbon fiber winding reinforcing layer is 5.76mm; The TC4 titanium alloy integral support is fixed at the preset position of the bottle body of the composite gas bottle through a special tool, the special tool has the functions of gas bottle winding and support positioning, a carbon fiber winding fixed layer (5) is wound outside the integral support, the winding thickness of the carbon fiber winding fixed layer (5) is 1mm, the fiber weight is 0.035kg, and the support is tightly held by the bottle body through adjusting fiber tension during winding.
2. The composite gas cylinder support structure according to claim 1, wherein the material performance parameters of the titanium alloy TA2 lining meet the tensile strength Not less than 400MPa, specified non-proportional extension strength R p0.2 not less than 275MPa, elongation after break The outer diameter of the titanium alloy TA2 lining is less than or equal to phi 168.7mm, the length is less than or equal to 202mm, the weight is less than or equal to 0.7kg, and the volume is 2.835L.
3. The composite gas cylinder support structure according to claim 1, wherein the carbon fiber winding reinforcing layer (2) and the carbon fiber winding fixing layer (5) are made of CCF1000G high-strength carbon fibers, and the CCF1000G high-strength carbon fibers are designed and used with parameters of 5800MPa of tensile strength, 280GPa of elastic modulus, 2.2% of elongation at break and 450G/km of linear density, the carbon fiber winding resin content is 22% -28%, and the tension control precision of each yarn in the winding process is 5%.
4. The composite gas cylinder support structure according to claim 1, wherein the TC4 titanium alloy integral support is subjected to low-power inspection, has no cracks, pores and inclusion defects and segregation, and is subjected to 100% ultrasonic flaw detection to meet the A-level requirement.
5. The composite gas cylinder support structure according to claim 1, wherein the integral structure parameters of the composite gas cylinder and TC4 titanium alloy integral support meet the total weight of 1.875kg, the total outer diameter phi 187.5+/-0.1 mm, the total length of 202mm, the working pressure of 70MPa and the bursting pressure of more than or equal to 120MPa, and the helium mass spectrum leak detection result is smaller than 。
6. The composite gas cylinder support structure according to claim 1, wherein a plurality of folding angles (31) are arranged at the bottom end of the support (3), a pasting disc (4) is attached to the end face, away from the titanium alloy TA2 liner (1), of each folding angle (31), through holes are formed in the surface of each folding angle (31) and aligned with the through holes in the surface of each pasting disc (4), each pasting disc (4) is connected with the bottle mouth of the titanium alloy TA2 liner (1) in a threaded mode, a plurality of pairs of protruding pieces (32) are arranged at the top end of the support (3), and grooves (33) used for being wound by carbon fiber winding fixing layers are formed in the surface, away from the titanium alloy TA2 liner (1), of each protruding piece (32).
7. The method for processing the composite gas cylinder support structure according to any one of claims 1 to 6, which is characterized by comprising the following three parts of a lining forming process, a support forming process and a gas cylinder integral winding and curing process, wherein the method comprises the following specific steps of: s1, forming a lining: 1.1, processing a seal head, namely blanking a titanium alloy TA2 bar stock, annealing, rough turning, stress relief annealing, finish turning an inner arc, finish turning an outer arc, finish turning a bottle neck/tail top, cleaning with alcohol, and checking a finished product to obtain an upper half shell seal head and a lower half shell seal head; 1.2, welding the inner lining, namely welding and forming the upper and lower half-shell assemblies by adopting an electron beam, and obtaining the titanium alloy TA2 inner lining through laser marking, stress relief annealing, performance detection, welding line ray detection, volume weight detection, helium detection airtight test, alcohol cleaning, cleanliness detection and final detection; s2, forming a bracket: the TC4 titanium alloy bar is subjected to raw material in-plant inspection, blanking, machining, grinding and finished product detection to obtain an integral bracket, and the machining process adopts a plurality of times of small-quantity machining modes to ensure the product precision; S3, integrally winding and solidifying the gas cylinder: 3.1, after the titanium alloy lining is subjected to corrosion prevention treatment, winding a carbon fiber winding reinforcing layer by adopting a wet fiber winding forming process, firstly completing 16-ring circumferential winding, then completing 6-longitudinal spiral winding, and controlling the tension layer by layer through electronic tension in the winding process, thereby controlling the resin proportion and the resin consumption; 3.2, after the carbon fiber winding reinforcing layer is solidified, positioning the integral bracket at a preset position of the bottle body through a special tool, winding the carbon fiber winding fixing layer and solidifying, and controlling the thickness of the fixing layer to be 1mm; 3.3, grinding, self-tightening, water pressure test, acoustic emission test, airtight test, helium mass spectrum leak detection, identification, cleanliness inspection and finished product detection to obtain the finished product composite gas cylinder support structure.
8. The method for processing the composite gas cylinder support structure according to claim 7, wherein tension control of carbon fiber winding in the step 3.1 is performed to ensure that the lining is not unstable in the winding process and is not wrinkled and deformed in the gas cylinder deflation process, the curing process in the step 3.2 is a key process, and furnace temperature process parameters are required to be strictly controlled.
9. The method for processing a composite gas cylinder support structure according to claim 7, wherein the detection of the finished product in the step 3.3 is required to meet the requirements that the overall weight is less than or equal to 2kg, the volume is more than or equal to 2.8L, the bursting pressure is more than or equal to 120MPa, and the helium mass spectrum leak detection result is smaller than And extracting a finished product according to technical requirements after the detection is qualified, and performing an identification test.

Description

Composite gas cylinder support structure and processing method thereof Technical Field The invention relates to the technical field of aerospace high-pressure gas cylinder matching structures and processing, in particular to a composite gas cylinder support structure and a processing method thereof. Background With the rapid development of the aerospace technology, the requirement of the spacecraft on a high-pressure gas cylinder is increasing, and the high-pressure gas cylinder is used as an indispensable key component in the aerospace field, is widely applied to a propulsion system, a fluid management system, a life support system, an environment control system and the like, is used for pressurizing a rocket fuel storage tank, providing a high-pressure gas source for a satellite and guaranteeing the on-orbit safety of astronauts. The performance requirements of the aerospace task on the high-pressure gas cylinder are very strict, the high-pressure gas cylinder is required to have the characteristics of high strength, light weight, corrosion resistance, extreme temperature resistance and environmental suitability, and strict quantization indexes are required to be met, wherein the working pressure can reach more than 70MPa, the weight is not more than 2kg, and the volume is not less than 2.8L. Meanwhile, in order to reduce the emission cost of the spacecraft and improve the overall operation reliability, the material utilization rate, assembly manufacturability and production efficiency of the high-pressure gas cylinder also become core consideration indexes. In the prior art, titanium alloy (such as TA2 or TC 4) is adopted as a lining material for the aerospace high-pressure gas cylinder, an ellipsoidal structure is formed by electron beam welding of the upper half shell and the lower half shell, a composite material reinforcing layer is wound outside the lining to improve structural strength, and a bracket is manufactured by adopting titanium alloy TC4 and is combined with the gas cylinder in a mechanical connection or welding mode. But this technical scheme has certain technical drawback: 1. the traditional metal gas cylinder is designed to meet the high-strength requirement, the wall thickness is often large, the connection structure of the support and the cylinder body is redundant, the whole weight exceeds standard, the whole weight reduction requirement of a spacecraft is not facilitated, the process complexity is high, the welding and forming process is strict, the technological defects such as air holes and layering are easy to generate, the material utilization rate is low, 2, the standardized fixture positioning is lacked, the support mounting precision is difficult to guarantee, 3, fatigue cracks are easy to occur at the welding position and the support connection position of the gas cylinder under the action of high-pressure cyclic load, the tightness is reduced, the air leakage rate exceeds standard, the on-orbit operation reliability of the spacecraft is affected, 4, the interface and support structure design is not integrally optimized, the mounting and maintenance procedures are complicated, and the quick assembly requirement of the spacecraft parts is difficult to meet. Disclosure of Invention The invention aims to provide a composite gas cylinder support structure and a processing method thereof, which are used for solving the problems in the background technology. In order to achieve the aim, the invention provides the technical scheme that the composite gas cylinder support structure and the processing method thereof comprise a composite gas cylinder, wherein the composite gas cylinder comprises a titanium alloy TA2 lining, a carbon fiber winding reinforcing layer, a support, a pasting disc and a carbon fiber winding fixing layer; the support is a TC4 titanium alloy integral support, one side of the patch is provided with a support, the inside of the support is provided with a titanium alloy TA2 liner, the outer wall of the titanium alloy TA2 liner is wound with a carbon fiber winding reinforcing layer, and the outer side of the support is wound with a carbon fiber winding fixing layer; The titanium alloy TA2 lining is formed by adopting an inserting structure to weld an upper half shell and a lower half shell through electron beams, the outer profiles of the upper half shell and the lower half shell are ellipsoids, and a bus equation is The wall thickness of the cylinder body of the titanium alloy TA2 lining is 0.7mm, the bottom thickness of the sealing head is 2.5mm, the bottom height of the sealing head is 41.47mm, the inner diameter D i of the lining is 165.5mm, the design requirement of the flat ellipsoidal sealing head is met by 0.5-2H/D i -0.7071, and H is the bottom height; The carbon fiber winding reinforcing layer comprises a circumferential winding layer and a spiral winding layer, the carbon fiber winding reinforcing layer is prepared by adopting a wet fiber winding forming