Hybrid fiber dry winding solid rocket engine shell and preparation method thereof

Abstract

The invention relates to the technical field of rocket motor shell manufacturing, in particular to a hybrid fiber dry winding solid rocket motor shell and a preparation method thereof.The hybrid fiber dry winding solid rocket motor shell comprises a longitudinal high-strength fiber layer, an annular high-strength fiber layer and a longitudinal high-modulus fiber layer; the longitudinal high-strength fiber layers and the longitudinal high-modulus fiber layers are alternately wound with the circumferential high-strength fiber layers respectively; the longitudinal high-strength fiber layer, the longitudinal high-modulus fiber layer and the circumferential high-strength fiber layer all take phenolic aldehyde type cyanate ester as a matrix. The solid rocket engine shell has the advantages that the hybrid fiber winding technology of the high-strength fibers and the high-modulus fibers is adopted, complementary advantages of the high-strength fibers and the high-modulus fibers are achieved, the rigidity of the solid rocket engine shell is remarkably improved, and deformation of the skirt under various working conditions such as axial tension, axial compression, bending and torsion is effectively reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket engine casing manufacturing, and in particular to a mixed fiber dry-winding solid rocket engine casing and a preparation method thereof. Background Art

[0002] Carbon fiber has the characteristics of light weight and high strength, and is widely used in the manufacture of solid rocket engine casings. The traditional manufacturing process uses a fiber wet winding process. The wet winding process is simple, mature and reliable, but it also has disadvantages such as uncontrollable fiber volume content. There are relatively few domestic studies on the dry winding technology of solid rocket engine casings. With the development of carbon fiber solid rocket engine casings, higher and higher requirements are placed on carbon fiber casings. The weight of the engine casing is required to be as low as possible, and the casing is required to withstand high temperatures during the engine casing flight process, and the deformation of the skirt spacing of the engine casing under complex working conditions is required to be as small as possible. Summary of the invention

[0003] In view of this, the present invention aims to provide a mixed fiber dry-wound solid rocket engine casing and a preparation method thereof, which improves the heat resistance of the rocket engine casing and enhances the rigidity of the casing through a longitudinal high-strength carbon fiber layer, a circumferential high-strength carbon fiber layer and a longitudinal high-modulus carbon fiber layer.

[0004] To achieve the above-mentioned purpose, the technical solution created by the present invention is implemented as follows: a mixed fiber dry-winding solid rocket engine casing, including a longitudinal high-strength fiber layer, a circumferential high-strength fiber layer and a longitudinal high-modulus fiber layer, the longitudinal high-strength fiber layer and the longitudinal high-modulus fiber layer are alternately wound with the circumferential high-strength fiber layer respectively; the longitudinal high-strength fiber layer, the longitudinal high-modulus fiber layer and the circumferential high-strength fiber layer are all based on phenolic cyanate ester.

[0005] Furthermore, the longitudinal high-strength fiber layer and the circumferential high-strength fiber layer both use T700-T1200 grade fibers; the longitudinal high-modulus fiber layer uses M40-M60 grade fibers; Furthermore, during the winding process of the longitudinal high-strength fiber layer, the longitudinal high-modulus fiber layer and the circumferential high-strength fiber layer, the winding tension is 30N-60N.

[0006] Furthermore, the width of the prepreg used in the longitudinal high-strength fiber layer, the longitudinal high-modulus fiber layer and the circumferential high-strength fiber layer is 6 mm-10 mm.

[0007] Furthermore, the longitudinal high-strength fiber layer is the innermost layer of the solid rocket engine casing and serves as the starting layer for winding.

[0008] Furthermore, the thickness calculation formula of the longitudinal high-strength fiber layer and the longitudinal high-modulus fiber layer is: ; ; ; in, —Total thickness of longitudinal high-strength fiber layer, —Fiber utilization coefficient of longitudinal high-strength fiber layer, —Fiber utilization coefficient of longitudinal high modulus fiber layer, - Bursting pressure provided by the longitudinal high-strength fiber layer, —Total thickness of longitudinal high modulus fibers, —Longitudinal high modulus fiber layer performance coefficient, —Longitudinal high modulus fiber bundle yarn tensile strength, - Winding angle, —Burst pressure provided by longitudinal high-strength fiber layer —bursting pressure provided by the longitudinal high modulus fiber layer, P—shell bursting pressure, R—shell radius.

[0009] Furthermore, the thickness calculation formula of the circumferential high-strength fiber layer is: ; in, —Total thickness of the circumferential high-strength fiber layer, —Fiber utilization coefficient of the hoop high-strength fiber layer, —Tensile strength of hoop high-strength fiber bundle yarn, —winding angle, P—bursting pressure, R—shell radius.

[0010] A method for preparing a hybrid fiber dry-winding solid rocket engine casing, used for preparing the above-mentioned hybrid fiber dry-winding solid rocket engine casing, comprises the following steps: S1. Use a prepreg machine to make longitudinal high-strength fiber prepreg, circumferential high-strength fiber prepreg and longitudinal high-modulus fiber prepreg.

[0011] S2. Grind and apply adhesive to the surface of the previously prepared rocket engine casing core mold.

[0012] S3. After step S2 is completed, the longitudinal high-strength fiber layer and the longitudinal high-modulus fiber layer are alternately wound with the circumferential high-strength fiber layer.

[0013] S4. After winding is completed, the rocket engine casing is pressurized and cured.

[0014] Furthermore, the specific winding method of step S3 is: first, wind at least two layers of longitudinal high-strength fiber layers according to the longitudinal preset winding path, then wind at least one layer of circumferential high-strength fiber layer according to the circumferential preset winding path, then wind at least two layers of longitudinal high modulus fiber layers according to the longitudinal preset winding path, and finally wind at least one layer of circumferential high-strength fiber layer according to the circumferential preset winding path.

[0015] Furthermore, during the winding process, a hot air device is used to heat the longitudinal high-strength fiber prepreg, the circumferential high-strength fiber prepreg and the longitudinal high-modulus fiber prepreg.

[0016] Compared with the prior art, the invention can achieve the following beneficial effects: the invention adopts the mixed fiber winding technology of high-strength carbon fiber and high-modulus carbon fiber, realizes the complementary advantages of high-strength and high-modulus fibers, significantly improves the rigidity of the solid rocket engine casing, and effectively reduces the deformation of the skirt under various working conditions such as axial tension, axial compression, bending, and torsion. At the same time, the phenolic cyanate resin is selected as the matrix material, which significantly improves the heat resistance of the casing compared to the traditional epoxy resin matrix, making it more adaptable to the extreme environment of aerodynamic heating. In addition, the dry winding process is used to prepare the solid rocket engine casing, which not only ensures the stability of the winding line, but also realizes the precise control of the fiber volume content. Compared with wet winding, the fiber volume content of dry winding is lower, which effectively reduces the casing mass, further improves the power-to-weight ratio (PV / W), and enhances the overall performance of the engine. DETAILED DESCRIPTION

[0017] In order to make the purpose, technical solution and advantages of the invention more clear, the invention is further described in detail below in conjunction with specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the invention and do not constitute a limitation of the invention.

[0018] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0019] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships, which are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0020] In the description of the invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the invention can be understood according to specific circumstances.

[0021] The present invention will be described in detail below with reference to the embodiments.

[0022] A hybrid fiber dry-winding solid rocket engine casing provided by an embodiment of the present invention comprises a longitudinal high-strength carbon fiber layer, a circumferential high-strength carbon fiber layer and a longitudinal high-modulus carbon fiber layer, wherein the longitudinal high-strength carbon fiber layer and the longitudinal high-modulus carbon fiber layer are alternately wound with the circumferential high-strength carbon fiber layer. In this embodiment, the longitudinal high-strength carbon fiber layer is the innermost layer of the solid rocket engine casing, serving as the starting layer of the winding.

[0023] First, at least one longitudinal high-strength carbon fiber layer is wound along a longitudinal preset winding path, then at least one circumferential high-strength carbon fiber layer is wound along a circumferential preset winding path, then at least one longitudinal high-modulus carbon fiber layer is wound along a longitudinal preset winding path, and finally at least one circumferential high-strength carbon fiber layer is wound along a circumferential preset winding path. In this embodiment, the longitudinal high-modulus carbon fiber is wound on the outer layer and the longitudinal high-strength carbon fiber is wound on the inner layer, which is more conducive to improving the rigidity of the shell.

[0024] The longitudinal high-strength carbon fiber layer, the longitudinal high-modulus carbon fiber layer and the hoop high-strength carbon fiber layer are all based on phenolic cyanate ester. Phenolic cyanate ester is an oligomeric derivative of phenolic and cyanate resins. It has the advantages of high residual carbon, high heat resistance and flame retardancy of phenolic resins, as well as high strength, low linear expansion and density of cyanate resins. In addition, its pre-impregnation process is clean and environmentally friendly, and no small molecules are released during the curing process. It is easy to form a high-density and high-strength structure. The glass transition temperature of phenolic cyanate ester is as high as 400°C. The commonly used matrix is ​​epoxy resin, and the highest glass transition temperature of epoxy resin is about 200°C, which is not applicable to some working conditions with high temperature resistance requirements.

[0025] The longitudinal high-strength carbon fiber layer and the circumferential high-strength carbon fiber layer adopt T700-T1200 grade carbon fiber, specifically T700 grade carbon fiber, T800 grade carbon fiber, T1000 grade carbon fiber, T1200 grade carbon fiber. The longitudinal high-strength carbon fiber layer and the circumferential high-strength carbon fiber layer can adopt the same grade of carbon fiber or different grades of carbon fiber.

[0026] The longitudinal high modulus carbon fiber layer adopts M40-M60 grade carbon fiber, specifically M40 grade carbon fiber, M55 grade carbon fiber, and M60 grade carbon fiber.

[0027] During the winding process of the longitudinal high-strength carbon fiber layer, the longitudinal high-modulus carbon fiber layer and the circumferential high-strength carbon fiber layer, the winding tension is 30N-60N; the width of the prepreg used in the longitudinal high-strength carbon fiber layer, the longitudinal high-modulus carbon fiber layer and the circumferential high-strength carbon fiber layer is 6mm-10mm.

[0028] During the winding process, the longitudinal high-strength carbon fiber layer, the longitudinal high-modulus carbon fiber layer and the hoop high-strength carbon fiber layer are all tested by the tensile strength test of the NOL ring to determine their winding tension, and the tension range is set to 30N to 60N. At the same time, the width of the prepreg used in these carbon fiber layers is controlled between 6mm and 10mm. If the width of the prepreg is too narrow, the winding efficiency will be reduced; and if the prepreg is too wide, it may cause wrinkles during the winding process, affecting the quality and performance of the final product.

[0029] NOL ring refers to a composite annular test piece formed by unidirectional fiber winding.

[0030] In this embodiment, the longitudinal high-strength carbon fiber layer adopts T800-grade carbon fiber; and the longitudinal high-modulus carbon fiber layer adopts M40-grade carbon fiber.

[0031] Furthermore, the calculation formula for the thickness of the longitudinal high-strength carbon fiber layer and the longitudinal high-modulus carbon fiber layer is: ; ; ; in, —Total thickness of longitudinal high-strength fiber layer, —Fiber utilization coefficient of longitudinal high-strength fiber layer, —Fiber utilization coefficient of longitudinal high modulus fiber layer, - Bursting pressure provided by the longitudinal high-strength fiber layer, —Total thickness of longitudinal high modulus fibers, —Longitudinal high modulus fiber layer performance coefficient, —Longitudinal high modulus fiber bundle yarn tensile strength, - Winding angle, —Burst pressure provided by longitudinal high-strength fiber layer —bursting pressure provided by the longitudinal high modulus fiber layer, P—shell bursting pressure, R—shell radius.

[0032] In a burst pressure test, the pressure inside the shell or container is usually gradually increased until it reaches the critical point of rupture. The pressure value at this critical point is defined as the burst pressure.

[0033] Furthermore, the thickness calculation formula of the circumferential high-strength fiber layer is: ; in, —Total thickness of the hoop high-strength fiber layer wound twice, —Fiber utilization coefficient of the hoop high-strength fiber layer, —Tensile strength of hoop high-strength fiber bundle yarn, —winding angle, P—bursting pressure, R—shell radius.

[0034] A method for preparing a hybrid fiber dry-winding solid rocket engine casing, used for preparing the above-mentioned hybrid fiber dry-winding solid rocket engine casing, comprises the following steps: S1. Use a prepreg machine to make longitudinal high-strength carbon fiber prepreg, circumferential high-strength carbon fiber prepreg and longitudinal high-modulus carbon fiber prepreg.

[0035] S2. Grind and apply adhesive to the surface of the previously prepared rocket engine casing core mold.

[0036] S3. After step S2 is completed, the longitudinal high-strength fiber layer and the longitudinal high-modulus fiber layer are alternately wound with the circumferential high-strength fiber layer.

[0037] S4. After winding is completed, the rocket engine casing is pressurized and cured.

[0038] In this embodiment, an autoclave is used to pressurize and solidify the rocket engine shell. First, starting from room temperature and room pressure, the rocket engine shell is heated and pressurized to (90±5)℃ and 0.2±0.05MPa at a heating rate of 1.5℃ / min and a pressurization rate of 0.02MPa / min, and maintained for 2h±5min. Then, the pressure is kept constant and the temperature is continued to be increased to (110±5)℃, (140±5)℃ and (170±5)℃ at a heating rate of 1.5℃ / min, wherein at the temperature of (110±5)℃ and the temperature of (140±5)℃, each is maintained for 1h±5min, and at the temperature of (170±5)℃, it is maintained for 4h±5min, so as to ensure that the rocket engine shell fully reacts and solidifies in different temperature ranges. After the pressurized curing is completed, the autoclave begins to cool down at a rate of 0.5°C / min until the temperature drops below 50°C. At the same time, the pressure is gradually released, and the pressure reduction rate is controlled at 0.02MPa / min until the pressure is completely released. h is hours and min is minutes.

[0039] Furthermore, the specific winding method of step S3 is: first, wind at least two layers of longitudinal high-strength carbon fiber layers according to the longitudinal preset winding path, then wind at least one layer of circumferential high-strength carbon fiber layer according to the circumferential preset winding path, then wind at least two layers of longitudinal high modulus carbon fiber layers according to the longitudinal preset winding path, and finally wind at least one layer of circumferential high-strength carbon fiber layer according to the circumferential preset winding path.

[0040] Furthermore, during the winding process, a hot air device is used to heat the longitudinal high-strength carbon fiber prepreg, the circumferential high-strength carbon fiber prepreg and the longitudinal high-modulus carbon fiber prepreg.

[0041] The following is a description of the method for preparing a solid rocket engine casing by dry winding of hybrid fibers provided by the present invention in conjunction with a specific embodiment; The surface insulation layer of the solid rocket engine case core mold is treated, and it is polished and brushed with adhesive. After the surface treatment is completed, the solid rocket engine case is prepared by dry winding process. During the winding process, T800-12k carbon fiber is used for longitudinal high-strength carbon fiber and circumferential high-strength carbon fiber, and M40J-12k carbon fiber is used for longitudinal high modulus carbon fiber. The linear density of these three carbon fibers is 450g / km and the bulk density is 1800kg / m³. The prepreg is made of high-strength carbon fiber of T800-12k carbon fiber and phenolic cyanate ester, and high modulus fiber of M40J-12k carbon fiber and phenolic cyanate ester, respectively. The width of the prepreg (i.e., the yarn width) is set to 10mm.

[0042] At the beginning of winding, the initial winding tension is set to 50N, and as the number of winding layers increases, each layer gradually decreases by 1N. At the same time, a hot air device is used for heating during the winding process, and the heating temperature is maintained at 100°C. The winding plies are [±θ / 90° / 90° / ±θ / 90° / 90°]. θ is the geodesic winding angle. The longitudinal high-strength carbon fiber layer and the circumferential high-strength carbon fiber layer both use T800-12k carbon fiber, and the longitudinal high-modulus carbon fiber layer uses M40J-12k carbon fiber. After the winding is completed, the solid rocket engine shell is pressurized by longitudinal circumferential winding using a shrink film. Subsequently, a curing treatment is performed. After the curing is completed, the solid rocket engine shell is demolded and subjected to a water pressure burst test.

[0043] The above specific implementations do not constitute a limitation on the protection scope of the present invention. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A hybrid fiber dry-winding solid rocket engine casing, characterized in that: It comprises a longitudinal high-strength fiber layer, a hoop-shaped high-strength fiber layer and a longitudinal high-modulus fiber layer, wherein the longitudinal high-strength fiber layer and the longitudinal high-modulus fiber layer are respectively alternately wound with the hoop-shaped high-strength fiber layer; The longitudinal high-strength fiber layer, the longitudinal high-modulus fiber layer and the circumferential high-strength fiber layer are all based on phenolic cyanate.

2. The hybrid fiber dry-winding solid rocket engine casing according to claim 1, characterized in that: The longitudinal high-strength fiber layer and the circumferential high-strength fiber layer both use T700-T1200 grade fibers; the longitudinal high-modulus fiber layer uses M40-M60 grade fibers.

3. The hybrid fiber dry-winding solid rocket engine casing according to claim 1, characterized in that: During the winding process of the longitudinal high-strength fiber layer, the longitudinal high-modulus fiber layer and the circumferential high-strength fiber layer, the winding tension is 30N-60N.

4. The hybrid fiber dry-winding solid rocket engine casing according to claim 1, characterized in that: The width of the prepreg used in the longitudinal high-strength fiber layer, the longitudinal high-modulus fiber layer and the circumferential high-strength fiber layer is 6mm-10mm.

5. The hybrid fiber dry-winding solid rocket engine casing according to claim 1, characterized in that: The longitudinal high-strength fiber layer is the innermost layer of the solid rocket engine casing and serves as the starting layer for winding.

6. The hybrid fiber dry-winding solid rocket engine casing according to claim 1, characterized in that: The calculation formula for the thickness of the longitudinal high-strength fiber layer and the longitudinal high-modulus fiber layer is: ； ； ； in, —Total thickness of longitudinal high-strength fiber layer, —Fiber utilization coefficient of longitudinal high-strength fiber layer, —Fiber utilization coefficient of longitudinal high modulus fiber layer, - Bursting pressure provided by the longitudinal high-strength fiber layer, —Total thickness of longitudinal high modulus fibers, —Longitudinal high modulus fiber layer performance coefficient, —Longitudinal high modulus fiber bundle yarn tensile strength, - Winding angle, —Burst pressure provided by longitudinal high-strength fiber layer —bursting pressure provided by the longitudinal high modulus fiber layer, P—shell bursting pressure, R—shell radius.

7. The hybrid fiber dry-winding solid rocket engine casing according to claim 1, characterized in that: The thickness calculation formula of the circumferential high-strength fiber layer is: ； in, —Total thickness of the circumferential high-strength fiber layer, —Fiber utilization coefficient of the hoop high-strength fiber layer, —Tensile strength of hoop high-strength fiber bundle yarn, —winding angle, P—bursting pressure, R—shell radius.

8. A method for preparing a hybrid fiber dry-wound solid rocket engine casing, used for preparing a hybrid fiber dry-wound solid rocket engine casing as claimed in any one of claims 1 to 7, characterized in that: The following steps are involved: S1. Using a prepreg machine to make longitudinal high-strength fiber prepreg, circumferential high-strength fiber prepreg and longitudinal high modulus fiber prepreg; S2. Grinding and applying adhesive to the surface of the previously prepared rocket engine casing core mold; S3. After step S2 is completed, the longitudinal high-strength fiber layer and the longitudinal high-modulus fiber layer are alternately wound with the circumferential high-strength fiber layer; S4. After winding is completed, the rocket engine casing is pressurized and cured.

9. The method for preparing a solid rocket engine casing by dry winding of hybrid fibers according to claim 8, characterized in that: The specific winding method of step S3 is: first, wind at least two layers of longitudinal high-strength fiber layers according to the longitudinal preset winding path, then wind at least one layer of circumferential high-strength fiber layer according to the circumferential preset winding path, then wind at least two layers of longitudinal high modulus fiber layers according to the longitudinal preset winding path, and finally wind at least one layer of circumferential high-strength fiber layer according to the circumferential preset winding path.

10. The method for preparing a solid rocket engine casing by dry winding of hybrid fibers according to claim 8, characterized in that: During the winding process, a hot air device is used to heat the longitudinal high-strength fiber prepreg, the circumferential high-strength fiber prepreg and the longitudinal high-modulus fiber prepreg.

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