Anti-impact nylon fiber for space suits and method for preparing the same

Abstract

The application discloses a kind of anti-impact nylon fibre for spacesuit and its preparation method, comprising: high molecular weight nylon 66 matrix 86.0-92.0wt%, multi-dimensional nano reinforcing phase 1.2-2.0wt%, multifunctional anti-impact microsphere 4.0-7.0wt%, in-situ interface compatibilizer and crosslinking point regulator 0.5-1.2wt%, aerospace-grade multifunctional stabilizing aid: 1.0-2.8wt%;The multi-dimensional nano reinforcing phase is compounded by amino graphene and amino carbon nanotube according to mass ratio 1:3-4;The multifunctional anti-impact microsphere is hollow polysiloxane-titania composite microsphere, the anti-impact nylon fibre for spacesuit and its preparation method disclosed by the application can realize the multifunctional integration of nylon fibre, meet the demand of space suit fibre.

Description

Technical Field

[0001] This invention relates to the field of nylon fibers, and more particularly to an impact-resistant nylon fiber for aerospace clothing and its preparation method. Background Technology

[0002] Spacesuit fibers must simultaneously meet the following requirements: high strength and modulus, high impact resistance, wide temperature range stability, resistance to space radiation, resistance to atomic oxygen, lightweight, low volatility, weavability, and high reliability.

[0003] Nylon fiber is a synthetic fiber, scientifically known as polyamide fiber (PA), and internationally commonly referred to as "Nylon". It is one of the earliest synthetic fibers to be industrially produced in the world.

[0004] Traditional nylon fibers suffer from several drawbacks: weak impact energy dissipation, making them prone to breakage at high speeds; significant low-temperature embrittlement and high-temperature creep; easy agglomeration of nano-reinforcement and weak interfacial bonding; and the inability of conventional spinning processes to achieve structural gradients and functional synergy. Current technologies struggle to achieve a balance between "preserving the intrinsic properties of nylon and integrating multiple functions," thus failing to meet the requirements of spacesuits. Summary of the Invention

[0005] This invention discloses an impact-resistant nylon fiber for spacesuits and its preparation method, aiming to solve the technical problem that existing technologies are unable to achieve the unity of "preservation of intrinsic nylon properties + multi-functional integration" and thus cannot meet the requirements of spacesuits.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: A type of impact-resistant nylon fiber for aerospace applications, comprising: 86.0-92.0 wt% high molecular weight nylon 66 matrix, 1.2-2.0 wt% multidimensional nano-reinforcing phase, 4.0-7.0 wt% multifunctional impact-resistant microspheres, 0.5-1.2 wt% in-situ interface compatibilizer and crosslinking point regulator, and 1.0-2.8 wt% aerospace-grade multifunctional stabilizing agent; the multidimensional nano-reinforcing phase is composed of aminated graphene and aminated carbon nanotubes in a mass ratio of 1:3-4; the multifunctional impact-resistant microspheres are hollow polysiloxane-titanium dioxide composite microspheres.

[0007] In this fiber, nylon 66 itself possesses strong hydrogen bonding, high cohesive energy, compliant aliphatic chains, and high crystallinity orientation ability, making it one of the best matrix materials for synthetic fibers in terms of comprehensive mechanical properties, abrasion resistance, fatigue resistance, processability, and weaving properties. Based on this, a high molecular weight matrix is ​​introduced to enhance the main chain's load-bearing capacity and creep resistance; aminated carbon nanotubes and aminated graphene are introduced to construct a stress transmission network, enabling rapid load dispersion along the fiber's axial and radial directions; hollow composite microspheres are introduced to undergo controllable deformation, collapse, and rebound upon impact, converting instantaneous kinetic energy into deformation energy, interfacial friction energy, and heat dissipation energy; and interfacial covalent bonding eliminates weak interfaces, preventing debonding, pull-out, and rapid expansion of streaks under impact. This achieves the multifunctional integration of nylon fiber, meeting the fiber requirements of aerospace suits.

[0008] A method for preparing impact-resistant nylon fiber for aerospace clothing, characterized by the following specific steps: S1: In-situ activation and high-stability dispersion of nano-reinforcing phase: Aminated graphene and aminated carbon nanotubes are dispersed by high-speed shearing and power ultrasonic coupling, and activated in-situ with silane to obtain highly dispersed nanocomposite powder; S2: Precise metering and low-temperature high-mixing of multiple components: Nylon 66 chips, nanoparticles, composite microspheres, compatibilizers and stabilizing agents are uniformly mixed at low temperature in a high-speed mixer; S3: Twin-screw gradient melt blending and in-situ interfacial bonding: Twin-screw extrusion is used. The process involves gradient melt blending, vacuum devolatilization, in-situ interfacial covalent bonding, and granulation to obtain spinning masterbatch; S4: High-precision drying and melt pressure stabilization conveying: The masterbatch is dried to a moisture content of ≤20ppm and then melt-pressurized and conveyed; S5: Gradient temperature field spinning and ring-blowing gradient cooling: The nascent fiber is formed through gradient temperature field spinning and ring-blowing gradient cooling; S6: Multi-stage variable temperature and stress synergistic drawing: Three-stage variable temperature and stress synergistic drawing, with a total draw ratio of 7.0-9.0; S7: Relaxation heat setting and low-volatility surface treatment: Relaxation heat setting and low-volatility oiling are performed, followed by winding to obtain the finished fiber.

[0009] In this preparation method, hollow microspheres, nano-carbon phase, and irradiated additives are sensitive to high temperature, strong shear, and high oxygen environments. Conventional processes can easily cause microspheres to break, resulting in the loss of buffering, lightweighting, and barrier functions; nano-phase agglomeration, resulting in the loss of network reinforcement; and additive decomposition, leading to excessive volatility and performance failure. The method of this invention addresses these issues by: low-temperature high-mixing and gentle melt blending, resulting in a microsphere breakage rate of ≤1.5%; nitrogen protection and high-vacuum devolatilization throughout the process to inhibit thermo-oxidative aging and reduce volatiles; and graded stretching and gradual loading to avoid instantaneous high stress that could cause internal defects in the fiber.

[0010] In a preferred embodiment, during in-situ silane activation in S1, a silane coupling agent is added, and the reaction is carried out at 70-95°C for 2-4 hours. The solvent is then removed under reduced pressure to obtain monodisperse, highly active, and non-agglomerated nanocomposite powder. In S2, the high-speed mixer is set to mix at 1000-2000 r / min for 15-30 min, and the temperature is controlled to be ≤80℃. In S3, the temperature settings in the twin-screw extruder are as follows: Zone I 255-265℃, Zone II 268-278℃, Zone III 276-288℃, Zone IV 275-285℃, and Die head 270-278℃; In step S5, the melt is extruded through a circular shaped spinneret, forming a near-field gradient temperature field below the spinneret. In S6, the nascent fibers undergo three stages of drawing: stage one at 80-95°C with a draw ratio of 3.2-4.5; stage two at 110-125°C with a draw ratio of 1.6-2.4; and stage three at 130-145°C with a draw ratio of 1.1-1.6. In step S7, relaxation and shaping are performed at 145-165℃, with a relaxation rate of 2.0%-6.0%.

[0011] This preparation method can flexibly adapt to the aerospace needs of various specifications, functions, and scenarios. It has strong process versatility. This invention achieves "one method, multiple series of products" through adjustable components, adjustable process parameters, and adjustable structure. It can control impact resistance and lightweight by adjusting the microsphere content; control strength and modulus by adjusting the nano-phase ratio; control flexibility, rigidity, and dimensional stability by adjusting stretching and shaping; and adapt to weaving, friction, breathability, and composite requirements by adjusting the cross-section.

[0012] As described above, a type of impact-resistant nylon fiber for aerospace clothing comprises: 86.0-92.0 wt% high molecular weight nylon 66 matrix, 1.2-2.0 wt% multidimensional nano-reinforcing phase, 4.0-7.0 wt% multifunctional impact-resistant microspheres, 0.5-1.2 wt% in-situ interface compatibilizer and crosslinking point regulator, and 1.0-2.8 wt% aerospace-grade multifunctional stabilizing agent. The multidimensional nano-reinforcing phase is composed of aminated graphene and aminated carbon nanotubes in a mass ratio of 1:3-4. The multifunctional impact-resistant microspheres are hollow polysiloxane-titanium dioxide composite microspheres. The impact-resistant nylon fiber for aerospace clothing and its preparation method provided by this invention achieve the technical effect of realizing the multifunctional integration of nylon fiber and meeting the fiber requirements of aerospace clothing. Attached Figure Description

[0013] Figure 1 This is a flowchart illustrating the preparation method of impact-resistant nylon fiber for aerospace clothing proposed in this invention. Detailed Implementation

[0014] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0015] The impact-resistant nylon fiber for spacesuits disclosed in this invention and its preparation method are mainly applied to the use of spacesuits.

[0016] Reference Figure 1 A type of impact-resistant nylon fiber for aerospace applications, comprising 86.0-92.0 wt% high molecular weight nylon 66 matrix, 1.2-2.0 wt% multidimensional nano-reinforcing phase, 4.0-7.0 wt% multifunctional impact-resistant microspheres, 0.5-1.2 wt% in-situ interface compatibilizer and crosslinking point regulator, and 1.0-2.8 wt% aerospace-grade multifunctional stabilizing agent; the multidimensional nano-reinforcing phase is composed of aminated graphene and aminated carbon nanotubes in a mass ratio of 1:3-4; the multifunctional impact-resistant microspheres are hollow polysiloxane-titanium dioxide composite microspheres.

[0017] Reference Figure 1 A method for preparing impact-resistant nylon fiber for aerospace clothing includes the following specific steps: S1: In-situ activation and high-stability dispersion of nano-reinforcing phase: Aminated graphene and aminated carbon nanotubes are dispersed by high-speed shearing and power ultrasonic coupling, and activated in-situ with silane to obtain highly dispersed nanocomposite powder; S2: Precise metering and low-temperature high mixing of multiple components: Nylon 66 chips, nanoparticles, composite microspheres, compatibilizers and stabilizing agents are uniformly mixed at low temperature in a high-speed mixer; S3: Twin-screw gradient melt blending and in-situ interfacial bonding: A twin-screw extruder gradient melt blending method is used to achieve uniform mixing of nylon 66 chips, nanoparticles, composite microspheres, compatibilizers and stabilizing agents; S4: High-precision drying and melt pressure stabilization conveying: The masterbatch is dried to a moisture content of ≤20ppm and then melt pressure stabilization conveying. S5: Gradient temperature field spinning and ring blowing gradient cooling: The nascent fiber is formed by gradient temperature field spinning and ring blowing gradient cooling. S6: Multi-stage variable temperature and stress synergistic drawing: Three-stage variable temperature and stress synergistic drawing, with a total draw ratio of 7.0-9.0. S7: Relaxation heat setting and low-volatility surface treatment: Relaxation heat setting and low-volatility oiling, followed by winding to obtain the finished fiber.

[0018] Reference Figure 1In a preferred embodiment, in S1, during in-situ silane activation, a silane coupling agent is added, and the reaction is carried out at 70-95℃ for 2-4 hours. The solvent is then removed under reduced pressure to obtain monodisperse, highly active, and non-agglomerated nanocomposite powder. In S2, the high-speed mixer is set to 1000-2000 r / min for 15-30 min, with the temperature controlled ≤80℃. In S3, the temperature settings in the twin-screw extruder are as follows: Zone I 255-265℃, Zone II 268-278℃, Zone III 276-28℃. 8℃, Zone IV 275-285℃, head 270-278℃; In S5, the melt is extruded through a circular shaped spinneret, forming a near-field gradient temperature field below the spinneret; In S6, the nascent fiber undergoes three stages of stretching, with the first stage at 80-95℃ and a stretch ratio of 3.2-4.5; the second stage at 110-125℃ and a stretch ratio of 1.6-2.4; and the third stage at 130-145℃ and a stretch ratio of 1.1-1.6; In S7, the fiber is relaxed and set at 145-165℃ with a relaxation rate of 2.0%-6.0%.

[0019] Example 1: Typical Median Formulation of Aerospace-Grade Impact-Resistant Nylon Fiber 1.1 Raw material composition (weight percentage) High molecular weight nylon 66 matrix: 89.0 wt% Multidimensional nano-reinforced phase (aminated graphene:aminated carbon nanotubes = 1:3): 1.6 wt% Hollow polysiloxane-titanium dioxide composite microspheres: 5.5 wt% Multifunctional epoxy-siloxane interface compatibilizer: 0.9 wt% Aerospace-grade multifunctional stabilizing additives (hindered amine light stabilizer, nano-silicon carbide, rare earth oxides, high-temperature antioxidants, low-volatility lubricants): 3.0 wt% The total weight of all components is 100 wt%.

[0020] 1.2 Detailed description of preparation steps (1) In-situ activation and high-stability dispersion of nano-reinforced phase Aminated graphene and aminated carbon nanotubes were added to a dispersion vessel at a mass ratio of 1:3, along with an environmentally friendly polar dispersion medium. A high-speed shearing device was activated at a rotation speed of 5000 r / min, and simultaneous ultrasonic treatment at 1100 W was performed for 80 min to fully exfoliate and deagglomerate the nanophase, forming a uniform and stable suspension. Subsequently, a measured amount of silane coupling agent was added, and the temperature was raised to 85℃ and maintained for 3 h to achieve in-situ activation of the nanophase surface and introduction of active sites. After the reaction, the solvent was removed by vacuum distillation, and the mixture was dried, pulverized, and sieved to obtain monodisperse, highly active nanocomposite powder with no significant agglomeration, and a particle size controlled below 200 nm.

[0021] (2) Multi-component low-temperature high-mixing The dried high-molecular-weight nylon 66 chips, nanocomposite powder, hollow polysiloxane-titanium dioxide composite microspheres, multifunctional epoxy-siloxane compatibilizer, and aerospace-grade stabilizing additives were precisely metered according to the specified ratio and fed into a horizontal high-speed mixer. The mixing speed was set to 1500 r / min, and the mixing time was 20 min. The entire process was carried out with jacket cooling and temperature control to ensure that the material temperature did not exceed 75℃, preventing the hollow microspheres from softening or cracking due to heat or the additives from decomposing prematurely, and ensuring that all components were macroscopically uniformly mixed under mild conditions.

[0022] (3) Twin-screw gradient melt blending and in-situ interfacial bonding A co-rotating twin-screw extruder with an aspect ratio (L / D) of 55 was used, with five temperature gradients: Zone I 260℃, Zone II 272℃, Zone III 282℃, Zone IV 280℃, and die head temperature 275℃. The screw speed was set to 320 r / min, and the system vacuum degree was ≤-0.09 MPa, to achieve full melting and plasticization, small molecule devolatilization, bubble removal, and in-situ interfacial covalent bonding reaction between the nanophase, microspheres, and nylon matrix. After the melt was filtered through multiple layers of filters, it was underwater pelletized, dehydrated, and dried to obtain a highly uniform masterbatch specifically for spinning.

[0023] (4) High-precision drying and melt pressure stabilization and conveying The masterbatch is transferred to a vacuum drum dryer and dried under negative pressure until the moisture content is ≤18 ppm to avoid high-temperature hydrolysis and yarn breakage during spinning. After drying, it is transferred to a screw extrusion melting system, which, together with a high-precision dynamic metering pump and a two-stage filter group, achieves stable melt pressure, stable flow, and impurity-free delivery, ensuring the continuity of the spinning process.

[0024] (5) Gradient temperature field spinning and ring blowing gradient cooling The melt is extruded through a circular spinneret, with a near-field gradient temperature field set below the spinneret: an upper 120°C slow cooling zone to delay rapid cooling of the melt, promote initial orientation of molecular chains, and reduce internal stress; and a lower 5°C rapid cooling zone to quickly solidify and shape the nascent fibers, inhibit spherulite formation, and improve cross-sectional uniformity. The annular airflow speed, temperature, and humidity are precisely controllable to ensure consistent filament cooling.

[0025] (6) Multi-stage variable temperature and variable stress synergistic stretching The nascent fibers enter a three-stage drawing system, employing a combination of gradient temperature and gradient draw ratio: the first-stage drawing temperature is 90℃ with a draw ratio of 3.8; the second-stage drawing temperature is 118℃ with a draw ratio of 2.0; and the third-stage drawing temperature is 140℃ with a draw ratio of 1.3, with the total draw ratio controlled at around 9.0. Through progressively increasing the temperature and loading, a high degree of molecular chain orientation and gradient crystalline structure are achieved, balancing strength, toughness, and impact resistance.

[0026] (7) Relaxation heat setting and low-volatility surface treatment After stretching, the fibers enter the heat-setting channel at 155℃ with a relaxation rate of 4.0%, eliminating internal stress and improving dimensional stability and adaptability to high and low temperature environments. After setting, aerospace-grade low-volatility, oil-free surface treatment is performed to reduce friction, improve bundle bonding and weaving performance, and finally stabilize and wind into shape to obtain finished aerospace-grade impact-resistant nylon fiber.

[0027] 1.3 Main Performance Results The tensile strength is 6.7 cN / dtex, the elongation at break is 23%, and the modulus is 190 GPa. The energy absorption of the drop hammer impact is 140% higher than that of ordinary nylon. The strength retention rate is 92% at -196℃ and the modulus retention rate is 86% at 200℃. The strength retention rate is 90% after 1000 h of vacuum ultraviolet irradiation. The atomic oxygen mass loss rate is 0.07 mg / cm². The TML is 0.78% and the CVCM is 0.07%. The linear density deviation rate is ±1.2%, the strength CV is 2.1%, the microsphere breakage rate is 1.0%, and the spinning breakage rate is ≤1 time / 10kg. The overall performance meets the requirements for the use of flexible protective layers in extravehicular spacesuits.

[0028] Example 2: High-strength, high-modulus aerospace nylon fiber 2.1 Raw material composition (weight percentage) High molecular weight nylon 66 matrix: 91.0 wt% Multidimensional nano-reinforced phase: 2.0 wt% Hollow polysiloxane-titanium dioxide composite microspheres: 4.0 wt% Multifunctional epoxy-siloxane interface compatibilizer: 1.0 wt% Aerospace-grade multi-functional stabilizer: 2.0 wt% The total weight of all components is 100 wt%.

[0029] 2.2 Characteristics of the preparation process This embodiment focuses on improving the axial load-bearing capacity and modulus of the fiber. The proportion of nano-reinforcing phase is appropriately increased, while the amount of microspheres is reduced to minimize the dilution effect on the modulus. The mixing temperature is controlled at 70–75°C, and the screw speed is 300 r / min to ensure sufficient dispersion of the nano-phase. The temperature of the spinning slow cooling zone is increased to 125°C to extend the orientation induction time; the total three-stage draw ratio is increased to 9.0 to strengthen molecular chain orientation; the heat setting temperature is 160°C, and the relaxation rate is 3.0%, ensuring high crystallinity while reducing internal residual stress.

[0030] 2.3 Main Performance Results It has a tensile strength of 7.2 cN / dtex, a tensile elongation of 20%, and a modulus of 210 GPa; a strength retention rate of 90% at -196℃ and a modulus retention rate of 84% at 200℃; an ultraviolet irradiation intensity retention rate of 88% and an atomic oxygen mass loss rate of 0.08 mg / cm²; a TML of 0.82% and a CVCM of 0.08%; a linear density deviation rate of ±1.3% and a strength CV of 2.5%, making it suitable for use in the main restraint layer of spacesuits and high-load-bearing structural sections.

[0031] Example 3: High-impact cushioning nylon fiber for aerospace applications 3.1 Raw material composition (weight percentage) High molecular weight nylon 66 matrix: 86.0 wt% Multidimensional nano-reinforced phase: 1.5 wt% Hollow polysiloxane-titanium dioxide composite microspheres: 7.0 wt% Multifunctional epoxy-siloxane interface compatibilizer: 1.2 wt% Aerospace-grade multifunctional stabilizer: 4.3 wt% The total weight of all components is 100 wt%.

[0032] 3.2 Characteristics of the preparation process This embodiment aims to protect against space debris impacts by significantly increasing the content of hollow composite microspheres, thereby enhancing energy absorption and buffering capabilities. The mixing process utilizes a lower temperature, controlled below 70°C, to reduce shear strength and protect the integrity of the microspheres. The twin-screw temperature is slightly reduced, and the rotation speed is lowered to 280 r / min to minimize microsphere breakage caused by strong shear. The spinning cooling gradient is gentler, and the stretching distribution is more uniform, avoiding internal defects caused by high stress. The setting relaxation rate is increased to 5.0%, further enhancing toughness and deformation dissipation capabilities.

[0033] 3.3 Main Performance Results It has a tensile strength of 6.2 cN / dtex, a tensile elongation of 26%, and a modulus of 165 GPa; its drop hammer impact energy absorption is 160% higher than that of ordinary nylon; its strength retention rate is 89% at -196℃ and its modulus retention rate is 82% at 200℃; its UV irradiation intensity retention rate is 87% and its atomic oxygen mass loss rate is 0.06 mg / cm²; its TML is 0.85% and its CVCM is 0.09%; its microsphere breakage rate is 1.5%, making it particularly suitable for spacesuit cushioning layers, outer protective shells, and airbag reinforcement structures.

[0034] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A type of impact-resistant nylon fiber for spacesuits, characterized in that, include: High molecular weight nylon 66 matrix 86.0-92.0 wt%, multi-dimensional nano-reinforcing phase 1.2-2.0 wt%, multifunctional impact-resistant microspheres 4.0-7.0 wt%, in-situ interface compatibilizer and crosslinking point regulator 0.5-1.2 wt%, aerospace-grade multifunctional stabilizing agent: 1.0-2.8 wt%; The multidimensional nano-reinforced phase is composed of aminated graphene and aminated carbon nanotubes in a mass ratio of 1:3-4. The multifunctional impact-resistant microspheres are hollow polysiloxane-titanium dioxide composite microspheres.

2. A method for preparing impact-resistant nylon fiber for spacesuits, used to prepare the impact-resistant nylon fiber for spacesuits as described in claim 1, characterized in that, The specific steps include the following: S1: In-situ activation and high-stability dispersion of nano-reinforced phase: Aminated graphene and aminated carbon nanotubes were dispersed by high-speed shearing and power ultrasonic coupling, and activated in situ by silane to obtain highly dispersed nanocomposite powder. S2: Multi-component precise metering and low-temperature high-speed mixing: Nylon 66 chips, nanopowder, composite microspheres, compatibilizer and stabilizer are mixed uniformly in a high-speed mixer at low temperature; S3: Twin-screw gradient melt blending and in-situ interfacial bonding: The twin-screw extruder is used for gradient melt blending, vacuum devolatilization, and in-situ interfacial covalent bonding to granulate the spinning masterbatch. S4: High-precision drying and melt pressure stabilization conveying: Masterbatch is dried to a moisture content of ≤20ppm and then melted and conveyed under pressure. S5: Gradient temperature field spinning and ring blowing gradient cooling: The nascent fiber is formed by gradient temperature field spinning and ring blowing gradient cooling; S6: Multi-stage variable temperature and stress synergistic drawing: Three-stage variable temperature and stress synergistic drawing, with a total draw ratio of 7.0-9.0; S7: Relaxation heat setting and low-volatility surface treatment: Relaxation heat setting and low-volatility oiling, followed by winding to obtain the finished fiber.

3. The impact-resistant nylon fiber for spacesuits and its preparation method according to claim 2, characterized in that, In S1, during in-situ silane activation, a silane coupling agent is added, and the reaction is carried out at 70-95℃ for 2-4 hours. The solvent is removed under reduced pressure to obtain monodisperse, highly active, and non-agglomerated nanocomposite powder.

4. The method for preparing impact-resistant nylon fiber for aerospace clothing according to claim 2, characterized in that, In S2, the high-speed mixer is set to mix at 1000-2000 r / min for 15-30 min, and the temperature is controlled to be ≤80℃.

5. The method for preparing impact-resistant nylon fiber for spacesuits according to claim 2, characterized in that, In S3, the temperature settings in the twin-screw extruder are as follows: Zone I 255-265℃, Zone II 268-278℃, Zone III 276-288℃, Zone IV 275-285℃, and die head 270-278℃.

6. The method for preparing impact-resistant nylon fiber for aerospace clothing according to claim 2, characterized in that, In step S5, the melt is extruded through a circular spinneret, forming a near-field gradient temperature field below the spinneret.

7. The method for preparing impact-resistant nylon fiber for spacesuits according to claim 2, characterized in that, In S6, the nascent fibers undergo three stages of stretching: stage one at 80-95℃ with a stretching ratio of 3.2-4.5; stage two at 110-125℃ with a stretching ratio of 1.6-2.4; and stage three at 130-145℃ with a stretching ratio of 1.1-1.

6.

8. The method for preparing impact-resistant nylon fiber for spacesuits according to claim 2, characterized in that, In step S7, relaxation and shaping are performed at 145-165℃, with a relaxation rate of 2.0%-6.0%.

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