Spaceflight titanium alloy fiber composite protective clothing and preparation method thereof

Abstract

The invention relates to the technical field of spaceflight protective clothing, and provides a spaceflight titanium alloy fiber composite protective clothing and a preparation method thereof.The preparation method comprises the steps that materials are pretreated, titanium alloy fibers are sequentially subjected to surface oil removal and acid pickling activation treatment, and then the titanium alloy fibers are immersed into a specific hydrothermal reaction solution to grow ceramic whisker reinforcements in situ; meanwhile, the TC4 titanium alloy powder, the SiC fibers, the Ni-Ti shape memory alloy microwires, the ZrO2-Y2O3 temperature-sensitive ceramic particles, the self-repairing microcapsules and the flexible graphene sensor array are subjected to pretreatment such as activation, annealing and dispersion. A three-dimensional interlocking microstructure is formed through in-situ growth of single crystal aluminum oxide whiskers on the surface of the titanium alloy fiber, the three-dimensional interlocking microstructure is cooperated with the shape memory fitting effect of SMA microwires and the thermal expansion matching effect of temperature-sensitive ceramic particles, the interlayer interface bonding strength is remarkably improved, the stable performance is maintained under an extreme temperature cycle, and the temperature-sensitive ceramic fiber composite material is prepared. And the layering defect of a traditional bonding process is thoroughly overcome.

Description

Technical Field

[0001] This invention relates to the field of aerospace protective clothing technology, specifically to an aerospace titanium alloy fiber composite protective clothing and its preparation method. Background Technology

[0002] Aerospace titanium alloy fiber composite protective suits are core life support equipment for astronauts' extravehicular activities (EVA). They combine the lightweight and high-strength properties of titanium alloys with the heat resistance and radiation resistance of high-performance fibers, enabling them to withstand harsh environments such as space vacuum, extreme temperature differences, micrometeoroid impacts, and particle radiation. Current technologies generally employ a "multi-layered composite" structural design for these suits. For example, the NASAZ-2 spacesuit uses titanium alloy bearings and a composite rigid torso, while China's "Feitian" EVA suit achieves basic weight reduction through the use of titanium alloys and polymer composite materials.

[0003] Although existing aerospace titanium alloy fiber composite protective suits have achieved basic protective functions, they still have defects: poor interlayer bonding stability, the titanium alloy and fiber matrix rely on traditional bonding processes, and are prone to delamination under extreme temperature cycles of -270℃ to 800℃, resulting in a decrease in protective performance; passive and rigid thermal management system, which only relies on multiple layers of heat insulation materials to block heat, cannot dynamically adjust according to environmental changes or the intensity of human activity, and is prone to internal heat accumulation or overcooling; the overall weight and thickness are too large, and the traditional multi-layer functional layer stacking design restricts the astronaut's joint mobility, and fatigue increases significantly after prolonged operation. Summary of the Invention

[0004] To address the shortcomings of existing technologies, this invention provides an aerospace titanium alloy fiber composite protective suit and its preparation method, which solves the problems of weak interlayer bonding, passive thermal management, heavy weight and poor mobility.

[0005] To achieve the above objectives, the present invention provides a method for preparing an aerospace titanium alloy fiber composite protective suit, comprising the following steps: Step 1: Material pretreatment. Titanium alloy fibers are subjected to surface degreasing and acid pickling activation treatments in sequence, and then immersed in a specific hydrothermal reaction solution to grow ceramic whisker reinforcements in situ. At the same time, TC4 titanium alloy powder, SiC fiber, Ni-Ti shape memory alloy microwire, ZrO2-Y2O3 thermosensitive ceramic particles, self-healing microcapsules and flexible graphene sensor array are subjected to activation, annealing and dispersion pretreatments respectively. Step 2: Preparation of the protective outer layer. Using SLM 3D printing technology, the pretreated TC4 titanium alloy powder and SiC fiber are mixed in a preset ratio, printed layer by layer, and then heat-treated to eliminate internal stress. Step 3: Preparation of functional layers, including the preparation of temperature control thermal management layer, self-healing monitoring layer, pressure-bearing layer and comfort inner layer. The temperature control thermal management layer is made of biomimetic woven base fabric of Ni-TiSMA microfilaments and aramid fibers, impregnated with resin containing ZrO2-Y2O3 temperature-sensitive ceramic particles, and integrates micro fluid pipelines and SMA spring actuators. The self-healing monitoring layer is made of self-healing microcapsules and flexible sensor arrays blended in polyurethane resin, coated with polyester fiber mesh and then cured. Step 4: Preparation of multifunctional adaptive sandwich: A flexible graphene aerogel matrix containing boron carbide microparticles is prepared by freeze drying. A microfluidic pipeline of temperature-controlled thermal management layer and an SMA spring actuator are embedded in a pre-set groove in the matrix to form an integrated sandwich. Step 5: Integrated composite: Align and stack the layers in the order of "protective outer layer - multifunctional adaptive interlayer - pressure-bearing layer - self-healing monitoring layer - comfort inner layer", and cure and form using a combination process of "vacuum-assisted resin transfer molding + hot pressing composite". Step Six: Post-processing and integration. The composite preform undergoes edge trimming and burr removal. The life support system interface and sensor data transmission module are installed, and the thermal management control unit is connected. Finally, a comprehensive performance test is conducted.

[0006] Preferably, in step one, the hydrothermal reaction solution is an aqueous solution of aluminum nitrate and urea, the aluminum ion concentration is 0.1-0.3 mol / L, the molar ratio of urea to aluminum ions is 3:1-5:1, the hydrothermal reaction temperature is controlled at 180-220℃, the reaction time is 6-24h, and the generated ceramic whiskers are single-crystal alumina whiskers with a length of 5-30 μm and an aspect ratio ≥10.

[0007] Preferably, in step one, the SiC fibers are cut to a length of 5-10 mm, subjected to plasma surface activation treatment with parameters of 300 W power and 5 min time, the Ni-TiSMA microfilaments have a diameter of 0.05-0.1 mm, and are annealed at 500 °C for 1 h. The self-healing microcapsules are prepared by in-situ polymerization, with urea-formaldehyde resin as the wall material and bisphenol A epoxy resin and ethylenediamine curing agent as the core material, and the particle size screening range is 100-500 μm.

[0008] Preferably, in step two, the mass ratio of TC4 titanium alloy powder to SiC fiber is 7:3 to 8:2, the SLM3D printing parameters are laser power 150 to 200W, scanning speed 500 to 800 mm / s, layer thickness 0.05 to 0.1 mm, scanning spacing 0.1 to 0.2 mm, and heat treatment conditions are 800℃ for 2 hours, followed by furnace cooling to room temperature.

[0009] Preferably, in step three, the biomimetic weaving angle of the temperature-controlled thermal management layer is 30° to 60°, the solid content of ZrO2-Y2O3 temperature-sensitive ceramic particles in the resin is 40 to 50 wt%, the pre-curing condition after impregnation of the base fabric is 80°C for 1 hour, the amount of self-healing microcapsules added to the polyurethane resin is 3 to 8 wt%, the curing condition is 100°C for 2 hours, the pressure-bearing layer is made of aramid fiber fabric impregnated and dried, the epoxy resin has a solid content of 30 wt%, and the drying condition is 60°C for 1 hour.

[0010] Preferably, in step four, the density of the flexible graphene aerogel matrix is ​​10–50 mg / cm³. 3 The mass fraction of boron carbide microparticles is 5% to 15% of the aerogel matrix, the phase transformation temperature Af point of the SMA spring actuator is set to 28℃±2℃, and the recovery stress in the austenitic phase is ≥15MPa.

[0011] Preferably, in step five, the hot-pressing composite parameters are: temperature 120–150°C, pressure 5–8 MPa, holding time 30–60 min, heating rate 5°C / min, and the resin used for vacuum-assisted resin transfer molding is cyanate ester resin or polyimide precursor resin. The curing regime is as follows: heating to 120–150°C at a rate of 1–2°C / min, holding at temperature and pressure for 1–2 h, then heating to 180–220°C, holding at temperature and pressure for 2–4 h, and maintaining the pressure at 0.3–0.6 MPa.

[0012] Preferably, in step six, the performance testing includes: a temperature cycling test of -270℃ to 800℃, a micrometeoroid impact test of 5km / s, a pressure maintenance test of 120kPa per hour, a self-repair efficiency test for ≤2mm damage, a sensor response test of 6 parameters, and an interlayer peel strength test.

[0013] A space-age titanium alloy fiber composite protective suit includes, from the outside to the inside, a protective outer layer, a multifunctional adaptive interlayer, a pressure-bearing layer, a self-healing monitoring layer, and a comfort inner layer. The protective outer layer is a composite material of TC4 titanium alloy powder with in-situ grown ceramic whisker reinforcement and SiC fiber 3D printed in-situ. The multifunctional adaptive interlayer includes a flexible graphene aerogel matrix containing boron carbide microparticles and a temperature control thermal management unit integrated therein. The self-healing monitoring layer is a polyurethane composite layer loaded with self-healing microcapsules and a flexible graphene sensor array. The comfort inner layer is a needle-punched composite material of bamboo charcoal fiber and polylactic acid fiber. Each layer is integrally composited and can be linked with the space life support system through wireless and wired backup modules.

[0014] Preferably, the flexible sensor array can monitor six parameters in real time: temperature, pressure, radiation dose, oxygen concentration, human heart rate, and skin humidity.

[0015] This invention provides an aerospace titanium alloy fiber composite protective suit and its preparation method. It has the following beneficial effects: 1. This invention forms a three-dimensional interlocking microstructure by growing single-crystal alumina whiskers in situ on the surface of titanium alloy fibers. This, combined with the shape memory bonding effect of SMA microfilaments and the thermal expansion matching effect of temperature-sensitive ceramic particles, significantly improves the interlayer interface bonding strength and maintains stable performance under extreme temperature cycling, thus completely solving the delamination defects of traditional bonding processes.

[0016] 2. This invention integrates SMA phase change drive and microfluidic pipeline zonal adjustment through a temperature control thermal management unit, which can quickly respond to environmental temperature differences and dynamically adjust the coolant flow rate according to the body surface temperature, accurately balance the heat demand of different body parts, avoid heat accumulation or overcooling, and improve the thermal comfort of astronauts during extravehicular activities.

[0017] 3. This invention integrates four functions—heat insulation, buffering, radiation protection, and deformation coordination—through a multifunctional graphene aerogel interlayer, replacing traditional multi-layer independent functional layers. Combined with SLM3D printing and biomimetic weaving technology, it optimizes the overall weight and joint mobility of the protective suit, reduces human fatigue after prolonged wear, and effectively extends the time astronauts spend outside the spacecraft.

[0018] 4. This invention integrates microcapsules loaded with a two-component repair agent into a self-healing monitoring layer. The repair agent can be released autonomously at minor damage sites to complete the repair, preventing the risk of depressurization caused by the expansion of damage and improving reliability in complex space environments. The flexible sensor array on this layer can monitor key parameters in real time and work in conjunction with the aerospace life support system to achieve anomaly warning, providing all-weather protection for astronauts. In addition, the integration of multiple advanced processes reduces traditional bonding steps and lowers manufacturing costs. Furthermore, the combination of 3D printing and biomimetic weaving technology supports personalized customization, further improving the adaptability of the protective clothing. Attached Figure Description

[0019] Figure 1 This is a flowchart of the present invention. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] Example: Please see the appendix Figure 1 This invention provides a method for preparing an aerospace titanium alloy fiber composite protective suit, comprising the following steps: Step 1: Material Pretreatment. Titanium alloy fibers undergo surface degreasing and acid pickling activation treatments sequentially. Subsequently, they are immersed in a specific hydrothermal reaction solution for in-situ growth of ceramic whisker reinforcements. Simultaneously, TC4 titanium alloy powder, SiC fibers, Ni-Ti shape memory alloy microwires, ZrO2-Y2O3 temperature-sensitive ceramic particles, self-healing microcapsules, and flexible graphene sensor arrays undergo activation, annealing, and dispersion pretreatments, respectively. The hydrothermal reaction solution is an aqueous solution of aluminum nitrate and urea, with an aluminum ion concentration of 0.1–0.3 mol / L and a urea to aluminum ion molar ratio of 3:1–5:1. The temperature should be controlled at 180–220℃, and the reaction time should be 6–24 h. The generated ceramic whiskers are single-crystal alumina whiskers with a length of 5–30 μm and an aspect ratio ≥10. SiC fibers are cut to a length of 5–10 mm and then subjected to plasma surface activation treatment with parameters of 300 W power and 5 min time. Ni-TiSMA microfilaments have a diameter of 0.05–0.1 mm and are annealed at 500℃ for 1 h. The self-healing microcapsules are prepared by in-situ polymerization, with urea-formaldehyde resin as the wall material and bisphenol A epoxy resin and ethylenediamine curing agent as the core material. The particle size screening range is 100–500 μm. Specifically, for degreasing titanium alloy fibers, a 5wt% sodium hydroxide aqueous solution is used, which is soaked at 60℃ for 20 minutes, followed by rinsing with deionized water until neutral. For acid pickling and activation, a 10wt% hydrochloric acid solution is used, which is soaked at room temperature for 10 minutes, rinsed again, and then dried to ensure that there is no oxide layer or impurities remaining on the fiber surface. During the in-situ polymerization of self-healing microcapsules, the mixture of urea-formaldehyde resin prepolymer and core material is dispersed in an aqueous solution containing 0.5wt% sodium dodecyl sulfate at a stirring rate of 300r / min. During the 60℃ water bath reaction, samples are taken every 2 hours to monitor the particle size. After the reaction, vacuum filtration is used for separation, and the samples are screened and sealed for storage. After drying, the flexible graphene sensor array needs to be pre-calibrated. The sensitivity consistency of each sensing unit is verified by a standard signal source, and units with deviations exceeding ±3% are discarded. Step 2: Preparation of the protective outer layer. Using SLM 3D printing technology, pretreated TC4 titanium alloy powder and SiC fiber are mixed in a preset ratio and printed layer by layer. After heat treatment to eliminate internal stress, the mass ratio of TC4 titanium alloy powder to SiC fiber is 7:3 to 8:2. The SLM 3D printing parameters are: laser power 150 to 200W, scanning speed 500 to 800 mm / s, layer thickness 0.05 to 0.1 mm, scanning spacing 0.1 to 0.2 mm, and heat treatment conditions of 800℃ for 2 hours, followed by furnace cooling to room temperature. Specifically, TC4 titanium alloy powder and SiC fibers are mixed using a twin-screw high-speed mixer at 1500 rpm for 30 minutes to ensure uniform fiber dispersion without agglomeration. SLM 3D printing employs a doctor blade-type powder spreading method, with the powder thickness error controlled within ±0.005 mm. Argon gas (oxygen content ≤500 ppm) is introduced during printing for protection, preventing titanium alloy oxidation. During heat treatment, the temperature is increased to 800℃ at a rate of 5℃ / min, and after holding at that temperature, the furnace is cooled at a rate ≤10℃ / min to prevent secondary internal stress. Step 3: Preparation of functional layers, including the preparation of temperature-controlled thermal management layer, self-healing monitoring layer, pressure-bearing layer and comfort inner layer. The temperature-controlled thermal management layer is made of biomimetic woven base fabric of Ni-TiSMA microfilaments and aramid fibers, impregnated with resin containing ZrO2-Y2O3 temperature-sensitive ceramic particles, and integrates micro-fluidic pipelines and SMA spring actuators. The self-healing monitoring layer is made of self-healing microcapsules and flexible sensor arrays blended in polyurethane resin, coated with polyester fiber mesh and cured. The biomimetic weaving angle of the temperature-controlled thermal management layer is 30° to 60°, the solid content of ZrO2-Y2O3 temperature-sensitive ceramic particles in the resin is 40 to 50 wt%, the pre-curing condition after impregnation of the base fabric is 80℃×1h, the addition amount of self-healing microcapsules in polyurethane resin is 3 to 8 wt%, and the curing condition is 100℃×2h. The pressure-bearing layer is made of aramid fiber fabric impregnated and dried, the epoxy resin has a solid content of 30 wt%, and the drying condition is 60℃×1h. Specifically, the temperature-controlled thermal management layer is biomimetic-knitted using a computerized flat knitting machine with a knitting density of 30 stitches / cm. 2 The weaving direction aligns with the movement trajectory of human joints. Resin impregnation is performed using a roller coating impregnation machine at a pressure of 0.3 MPa to ensure the base fabric fibers are fully saturated with resin. After pre-curing, infrared detection is used to ensure no air bubbles remain. The self-healing monitoring layer is coated using a doctor blade coating machine at a speed of 5 mm / s, with the coating thickness precisely controlled by adjusting the doctor blade gap. After curing, a sensor array continuity test is conducted to ensure stable connection between all sensing units and the data interface. The pressure-bearing layer is impregnated using a vertical impregnation machine, with fabric tension controlled at 50 N to prevent fiber deformation during impregnation. Drying is performed using a forced-air drying oven at a wind speed of 2 m / s to ensure uniform resin curing. Step 4: Preparation of a multifunctional adaptive sandwich layer. A flexible graphene aerogel matrix containing boron carbide microparticles is prepared using a freeze-drying method. Microfluidic channels of a temperature-controlled thermal management layer and an SMA spring actuator are embedded in pre-set grooves within the matrix to form an integrated sandwich layer. The density of the flexible graphene aerogel matrix is ​​10–50 mg / cm³. 3 The mass fraction of boron carbide microparticles is 5% to 15% of the aerogel matrix, the phase transformation temperature Af point of the SMA spring actuator is set to 28℃±2℃, and the recovery stress in the austenitic phase is ≥15MPa. Specifically, the graphene aerogel preparation involves first mixing graphene oxide dispersion with boron carbide microparticles, ultrasonically dispersing for 60 minutes, adding hydrazine reducing agent, and then performing hydrothermal reduction at 95℃ for 12 hours. The mixture is then transferred to a freeze dryer, pre-frozen at -50℃ for 4 hours, and finally dried under a vacuum of 10 Pa for 24 hours to obtain an aerogel matrix of the predetermined density. Groove processing utilizes a laser engraving machine with an engraving accuracy of ±0.1 mm, the depth of which is highly matched to the SMA spring actuator. During installation, high-temperature resistant silicone adhesive is used for fixation, with an adhesive coating thickness of 0.1 mm, cured at 80℃ for 30 minutes to ensure a secure connection between the actuator and the piping. Step 5: Integrated composite: Align and stack the layers in the following order: "protective outer layer - multifunctional adaptive interlayer - pressure-bearing layer - self-healing monitoring layer - comfort inner layer". Use a combination of "vacuum-assisted resin transfer molding + hot-pressing composite" to cure and form the composite. The hot-pressing composite parameters are: temperature 120-150℃, pressure 5-8MPa, holding time 30-60min, and heating rate 5℃ / min. The resin used for vacuum-assisted resin transfer molding is cyanate ester resin or polyimide precursor resin. The curing regime is: heat up to 120-150℃ at a rate of 1-2℃ / min, hold for 1-2 hours, then heat up to 180-220℃, hold for 2-4 hours, and maintain the pressure at 0.3-0.6MPa. Specifically, the layers are positioned using positioning pins and templates with a positioning error ≤0.5mm. Release cloth is laid between each layer to prevent adhesion. Vacuum-assisted resin transfer molding uses a sealed mold. A vacuum is first evacuated to below 1Pa and maintained for 30 minutes to remove air from the mold and preform. The resin injection rate is controlled at 5mL / min, using a stepped injection method, filling the edges first and then advancing towards the center to avoid turbulent air bubbles. During hot-pressing, a pre-pressure of 2MPa is applied for 10 minutes, then the pressure is gradually increased to the set pressure. After heat preservation, the layers are cooled to room temperature at a rate of 3℃ / min to prevent stress concentration between layers. Step Six: Post-processing and Integration. The composite preform undergoes edge trimming and burr removal. The life support system interface and sensor data transmission module are installed, and the thermal management control unit is connected. Finally, a comprehensive performance test is conducted, including: -270℃~800℃ temperature cycling test, 5km / s micrometeoroid impact test, 120kPa pressure maintenance test per hour, ≤2mm damage self-repair efficiency test, sensor response to 6 parameters test, and interlayer peel strength test. Specifically, edge trimming utilizes a CNC cutting machine with a cutting accuracy of ±0.2mm, and polishing is done manually with 400-grit sandpaper until the edges are smooth and burr-free. During life support system interface installation, fluororubber sealing rings are used, with the sealing ring compression controlled at 20%. Interface bolts are tightened to a torque of 20 N·m to ensure no leakage in a vacuum environment. After installation, the sensor data transmission module undergoes a 24-hour continuous power-on calibration. Data stability is verified by simulating space environment parameters (such as extreme temperatures and radiation), and integration is only permitted after successful calibration. Performance testing includes a temperature cycling test consisting of 10 cycles: -270℃ for 2 hours, followed by heating to 800℃ and holding for 2 hours. The micrometeoroid impact test uses a 5mm diameter TC4 steel ball impacting critical areas of the protective suit (such as the chest and joints) at a speed of 5 km / s. The pressure maintenance test is conducted in a vacuum environment simulation chamber, with real-time monitoring of leakage to ensure a leakage rate ≤1×10⁻⁶ within 24 hours. -5 Pa・m 3 / s.

[0022] A space-age titanium alloy fiber composite protective suit comprises, from the outside to the inside, a protective outer layer, a multifunctional adaptive interlayer, a pressure-bearing layer, a self-healing monitoring layer, and a comfort inner layer. The protective outer layer is a 3D-printed in-situ composite material of TC4 titanium alloy powder with in-situ grown ceramic whisker reinforcement and SiC fiber. The multifunctional adaptive interlayer includes a flexible graphene aerogel matrix containing boron carbide microparticles and an integrated temperature control and thermal management unit. The self-healing monitoring layer is a polyurethane composite layer loaded with self-healing microcapsules and a flexible graphene sensor array. The comfort inner layer is a needle-punched composite material of bamboo charcoal fiber and polylactic acid fiber. All layers are integrally composited and can be linked to the space-age life support system via wireless and wired backup modules. The protective outer layer has an impact resistance ≥1500MPa. 6 The strength retention rate under Gy radiation dose is ≥85%, the thermal conductivity of the multifunctional adaptive interlayer can be adaptively adjusted within the range of 1.2~2.5W / (m・K), the self-healing monitoring layer has a self-repair rate of ≥92% for minor damage, the flexible sensor array can monitor six parameters in real time: temperature, pressure, radiation dose, oxygen concentration, human heart rate, and skin humidity, the overall weight is reduced by more than 25% compared with traditional protective clothing, the joint mobility is increased by 22%, the breathability of the comfortable inner layer is ≥500mm / s, and the moisture absorption and perspiration rate is ≥85%.

[0023] Based on the aforementioned aerospace titanium alloy fiber composite protective suit, experiments were conducted, and the following table of data was obtained:

[0024] As shown in the table, a new type of aerospace titanium alloy fiber composite protective suit has achieved breakthroughs in interlayer stability, thermal management, self-healing, intelligence, and lightweighting, which can meet the stringent requirements of aerospace missions such as deep space exploration.

[0025] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A method of making a space titanium alloy fiber composite protective garment, characterized in that, The method comprises the following steps: Step 1: material pretreatment, the titanium alloy fiber is sequentially subjected to surface oil removal, pickling activation treatment, then immersed in a specific hydrothermal reaction solution to grow ceramic whisker reinforcing body in situ, and the TC4 titanium alloy powder, SiC fiber, Ni-Ti shape memory alloy microfilament, ZrO2-Y2O3 temperature-sensitive ceramic particle, self-repairing microcapsule and flexible graphene sensor array are respectively subjected to activation, annealing, dispersion and other pretreatments; Step 2: preparation of a protective outer layer, the pretreated TC4 titanium alloy powder and SiC fiber are mixed in a preset ratio, and then layer-by-layer printing is performed to form a product, and the product is subjected to heat treatment to eliminate internal stress; Step 3: preparation of a functional layer, including preparation of a temperature control and thermal management layer, a self-repairing monitoring layer, a pressure bearing layer and a comfortable inner layer, wherein the temperature control and thermal management layer is made of Ni-Ti SMA microfilament and aramid fiber bionic woven cloth, impregnated with resin containing ZrO2-Y2O3 temperature-sensitive ceramic particles, and integrated with a micro fluid pipeline and an SMA spring actuator, the self-repairing monitoring layer is obtained by blending self-repairing microcapsules and flexible sensor array in polyurethane resin, and then coating polyester fiber mesh and curing; Step 4: preparation of a multifunctional adaptive interlayer, a flexible graphene aerogel matrix containing boron carbide particles is prepared by freeze-drying, and the micro fluid pipeline and the SMA spring actuator of the temperature control and thermal management layer are embedded in the preset groove of the matrix to form an integrated interlayer; Step 5: integrated compounding, the protective outer layer, the multifunctional adaptive interlayer, the pressure bearing layer, the self-repairing monitoring layer and the comfortable inner layer are aligned and stacked in sequence, and a combined process of vacuum-assisted resin transfer molding and hot pressing is used for curing and forming; Step 6: post-treatment and integration, the edge of the composite blank is trimmed, burrs are polished, a life support system interface and a sensor data transmission module are installed, a thermal management control unit is connected, and finally overall performance detection is performed.

2. The method of making a space titanium alloy fiber composite protective garment according to claim 1, wherein, In step 1, the hydrothermal reaction solution is an aqueous solution of aluminum nitrate and urea, the aluminum ion concentration is 0.1-0.3 mol / L, the molar ratio of urea to aluminum ions is 3:1-5:1, the hydrothermal reaction temperature is controlled at 180-220℃, the reaction time is 6-24h, the generated ceramic whisker is single crystal alumina whisker, the length is 5-30μm, and the aspect ratio is ≥10.

3. The method of making a space titanium alloy fiber composite protective garment according to claim 1, wherein, In step 1, the SiC fiber is cut to a length of 5-10mm, and is subjected to plasma surface activation treatment with a power of 300W for 5min, the Ni-Ti SMA microfilament has a diameter of 0.05-0.1mm and is subjected to annealing treatment at 500℃ for 1h, the self-repairing microcapsule is prepared by in-situ polymerization, the wall material is urea-formaldehyde resin, the core material is bisphenol A epoxy resin and ethylenediamine curing agent, and the particle size is screened in the range of 100-500μm.

4. The method of making a space titanium alloy fiber composite protective garment of claim 1, wherein, In step 2, the mass ratio of the TC4 titanium alloy powder to the SiC fiber is 7:3-8:2, the SLM3D printing parameters are laser power 150-200W, scanning speed 500-800mm / s, layer thickness 0.05-0.1mm, scanning interval 0.1-0.2mm, the heat treatment conditions are 800℃×2h, and the product is cooled to room temperature in the furnace.

5. The method of making a space titanium alloy fiber composite protective garment of claim 1, wherein, In the third step, the bionic weaving angle of the temperature control thermal management layer is 30-60°, the solid content of ZrO2-Y2O3 temperature-sensitive ceramic particles in the resin is 40-50wt%, the pre-curing condition of the impregnated base cloth is 80℃×1h, the addition amount of the self-repairing microcapsule in the polyurethane resin is 3-8wt%, the curing condition is 100℃×2h, the pressure-bearing layer is aramid fiber fabric impregnated with epoxy resin with a solid content of 30wt%, and the drying condition is 60℃×1h.

6. The method of making a space titanium alloy fiber composite protective garment of claim 1, wherein, The density of the flexible graphene aerogel base body in the fourth step is 10-50 mg / cm 3 The mass fraction of the boron carbide particles is 5%-15% of the aerogel base body, the phase transition temperature Af point of the SMA spring actuator is set to 28℃±2℃, and the recovery stress in the austenitic phase state is ≥15MPa.

7. The method of making a space titanium alloy fiber composite protective garment of claim 1 wherein, In the fifth step, the hot-pressing composite parameters are temperature 120-150℃, pressure 5-8MPa, holding time 30-60min, and heating rate 5℃ / min, the resin used in vacuum-assisted resin transfer molding is cyanate ester resin or polyimide precursor resin, and the curing system is as follows: heating at a rate of 1-2℃ / min to 120-150℃, holding and pressurizing for 1-2h, then heating to 180-220℃, holding and pressurizing for 2-4h, and maintaining the pressure at 0.3-0.6MPa.

8. The method of making a space titanium alloy fiber composite protective garment of claim 1, wherein, In the sixth step, the performance detection includes: -270℃-800℃ temperature cycle test, 5km / s micro-meteoroid impact test, 120kPa pressure maintenance test per hour, ≤2mm damage self-repairing efficiency test, 6-parameter response test of the sensor, and interlayer peeling strength test.

9. A space titanium alloy fiber composite protective clothing prepared by the method of any one of claims 1-8. The application relates to a space suit, which comprises the following layers from outside to inside: a protective outer layer, a multifunctional adaptive interlayer, a pressure-bearing layer, a self-repairing and monitoring layer, and a comfortable inner layer. The flexible sensor array can monitor 6 parameters in real time, including temperature, pressure, radiation dose, oxygen concentration, human heart rate, and skin humidity.

10. The aerospace titanium alloy fiber composite protective garment of claim 9, wherein, ​

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