24results about "Space suits" patented technology

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.

To provide a dust reduction system for space suits and the like, and more specifically, to provide a dust reduction system using conductive fibers. [Solution] A dust mitigation system ("DMS") is disclosed that includes a textile material having a front surface and a back surface, a plurality of conductive fibers within the textile material, and a plurality of input nodes generally adjacent to either the back surface or the front surface of the textile material. The plurality of conductive fibers are generally parallel to a first direction along the textile material and generally adjacent to the front surface of the textile material, and the plurality of input nodes are in signal communication with the plurality of conductive fibers and configured to receive alternating current ("AC") voltage signals from an input signal source. In response to the plurality of input nodes receiving the AC voltage signals from the input signal source, the plurality of conductive fibers are configured to generate an electric field at the front surface of the textile material and (from the electric field) generate traveling waves that travel along the front surface of the textile material in a second direction that is perpendicular to the first direction.

Systems, methods, and devices are directed to providing charge mitigation via a MXene-based conductive pathway on a spacesuit. In one aspect, a system for planetary exploration to provide charge mitigation on an outer surface of the spacesuit comprises a multilayered fabric including a woven layer, wherein the woven layer includes a first side to face a space environment and an opposing side to face a body of a wearer of the spacesuit and a MXene coating layer applied on the opposing side, wherein the MXene coating layer extends through the thickness the woven layer to conductively couple a first location on an exterior surface of the spacesuit with a second location on the exterior surface of the spacesuit.

The present disclosure relates to a joint assembly configured to define a tubular body having a first end, a second end and a passage therebetween. The tubular body is configured for articulation between a first state in which the first end and second end are in a first orientation with respect to one another, and a second state in which the first end and second end are in a second orientation with respect to one another. The body comprises a flexible bladder arranged between opposing supports, each of the bladder and the supports being ring-shaped so as to define an aperture, the respective apertures forming part of the passage. The bladder defines a chamber, and the chamber is partially filled with a fluid which moves within the chamber during articulation of the tubular body from said first state to said second state in order to maintain a constant internal volume of the joint assembly.

The invention discloses an organic flexible electronic skin structure and an irradiation protection efficiency evaluation system, method, equipment, medium and product thereof, and relates to the field of aerospace protection materials, the evaluation system comprises a signal acquisition module and a processing module; the signal acquisition module comprises an organic flexible electronic skin structure; the organic flexible electronic skin structure comprises an irradiation absorption layer, a conductive composite film layer and a flexible sensing circuit layer which are sequentially stacked, the signal acquisition module is used for acquiring irradiation dose values of different positions of the outer surface of the space suit; and the processing module is used for determining irradiation dose distribution according to the irradiation dose value in combination with the calibration data, and determining an irradiation protection efficiency evaluation result and a corresponding risk level by using an irradiation protection efficiency evaluation model according to the irradiation dose distribution. According to the invention, monitoring-evaluation integration of the surface of the space suit is realized.

An embodiment provides a protective suit system that is configured for protecting an occupant in extreme environments. The system may comprise a base layer to be worn on the occupant that is configured for thermal regulation of the occupant, the base layer including a biomarker sensor network for monitoring one or more biomarkers of the occupant. The system may also comprise an outer layer to be worn over the base layer, the outer layer including an exoskeleton structure sized so that the occupant can fit within the exoskeleton structure, and an exoskeleton covering that covers and is secured to the exoskeleton structure. The system may also comprise a data storage system that can store data generated by the biomarker sensor network.

The present application relates to a kind of distributed extravehicular spacesuit with self-repairing and resource in-situ replacement function, belong to astronaut life support and energy management technical field, the present application is set in spacesuit helmet heat control circulating system one, spacesuit ontology sets heat control circulating system two and energy and resource supply system, heat control circulating system is modularized and distributed in head, chest, abdomen and limbs, integrates two kinds of temperature control mode of carbon dioxide sublimer and phase-change radiator, can in-situ utilize carbon dioxide in Mars atmosphere and sublimate heat dissipation, significantly reduce the water heat sink resource load carried from earth, effectively disperses system weight;Abdomen and limbs are provided with standardized plug-in interface, support oxygen cylinder, battery and water tank and other key consumable modules are replaced quickly in extravehicular site, realize the real-time supply to consumable resource and the on-site replacement maintenance to failed resource storage module or phase-change temperature control component, do not need to disassemble entire system to ensure sustained cruising.

A composite material comprising a first shielding layer (210); at least one metal containing layer (208) over the first shielding layer; and a second shielding layer (206) over said at least one metal containing layer opposite of the first shielding layer; wherein the first shielding layer (210) and the second shielding layer (206) each and / or in combination with other layers of the composite material provide the composite material with radiation shielding characteristics.

Systems and methods for operating a vehicle in an environment that requires an astronaut in the vehicle to wear a spacesuit, are presented. The vehicle may be a lunar rover or a rover to be used on Mars. An astronaut will be in a spacesuit while in the vacuum of the Moon. This vacuum or thin atmosphere will give rise to a pressure differential between the inside and the outside of the spacesuit. This pressure differential reduces the flexibility of the spacesuit, such that the joints of the spacesuit resist bending or flexing. Spacesuit stiffness is substantially reduced while an astronaut is in a pressurizable cabin of the vehicle, where the pressure differential can be reduced or eliminated. The spacesuit may provide all necessary life support while the cabin of the rover provides a cabin pressure that is substantially the same as the pressure in the spacesuit.

The covering includes an outer material, a plurality of conductive fibers, and a fastening material. The outer material includes a front surface and a back surface, and the conductive fibers are disposed between the front surface and the back surface. The conductive fibers are configured to receive a voltage that causes the conductive fibers to repel and remove dust from the surface of the outer material. The fastening material is bonded to the back surface of the outer material and facilitates removably attaching the outer material to an article.

Disclosed herein are devices, systems, and processes for providing water collection and filtration of user wastewater for return as potable drinking water. Systems described include ones with a plurality of layers having a top layer with water permeable fabric, a first middle layer with an antimicrobial material, a second middle layer with activated carbon, a bottom layer having a water impermeable material, an osmotic filter configured to filter the collected bodily fluid from the bodily fluid collection system; and a mechanical device configured to move the filtered fluid from the osmotic filter.

Embodiments of the present disclosure relate to processes for making carbon nano material fiber and / or fabric products. Such products may have new and / or improved properties compared to similar products and are cheaper to make according to embodiments of the present disclosure.

To provide an extravehicular mobility unit eliminating the need for connection and removal of a battery.SOLUTION: An extravehicular mobility unit (EMU) includes a resonant coil on a surface of the EMU to be coupled to a second resonant coil affixed to a structure via a resonant magnetic field. The EMU also includes a receiver in the EMU coupled to the resonant coil to provide a direct current (DC) voltage based on the resonant magnetic field. A battery in the EMU is charged based on the DC voltage.SELECTED DRAWING: Figure 4

This application discloses an organic flexible electronic skin structure and its radiation protection effectiveness assessment system, method, equipment, medium, and product, relating to the field of aerospace protective materials. The assessment system includes a signal acquisition module and a processing module. The signal acquisition module includes the organic flexible electronic skin structure, which comprises a radiation absorption layer, a conductive composite thin film layer, and a flexible sensing circuit layer stacked sequentially. The signal acquisition module is used to acquire radiation dose values ​​at different locations on the outer surface of a spacesuit. The processing module is used to determine the radiation dose distribution based on the radiation dose values ​​and calibration data, and based on the radiation dose distribution, uses a radiation protection effectiveness assessment model to determine the radiation protection effectiveness assessment result and the corresponding risk level. This application achieves integrated monitoring and assessment of the spacesuit surface.

The present disclosure relates to a joint assembly configured to define a tubular body having a first end, a second end and a passage therebetween. The tubular body is configured for articulation between a first state in which the first end and second end are in a first orientation with respect to one another, and a second state in which the first end and second end are in a second orientation with respect to one another. The body comprises a flexible bladder arranged between opposing supports, each of the bladder and the supports being ring-shaped so as to define an aperture, the respective apertures forming part of the passage. The bladder defines a chamber, and the chamber is partially filled with a fluid which moves within the chamber during articulation of the tubular body from said first state to said second state in order to maintain a constant internal volume of the joint assembly.

The invention discloses a self-adjusting liquid-filled spaceflight anti-G suit and a regulation and control method thereof. A liquid pressurizing system and a physiological monitoring system are combined. Physiological parameters such as electrocardio, blood pressure and respiration are monitored in real time and compared with baseline physiological data obtained under the standard earth gravity, and when the real-time data deviates from a baseline and exceeds a preset deviation threshold value, liquid is controlled to be injected into a distributed liquid filling bag from a liquid storage device on the side face of a seat through a liquid filling pipeline; liquid pressure distribution changing in the longitudinal direction of the human body is formed on the chest, the waist and abdomen, the thighs and the shanks; when the physiological data return to the safety range and lasts for preset time, the lower hem backflow opening is opened, and the liquid flows back to gradually relieve pressure. The pair of anti-G anti-static pressure shoes is fast in response, smooth in pressure distribution, capable of relieving blood deposition of lower limbs and improving blood supply of the brain, capable of achieving the anti-G effect and wearing comfort and suitable for astronaut protection under different overload working conditions.

A method (200) comprising: receiving design input data; generating at least one protective suit design based on the design input data; storing the protective suit design as a detailed model in a memory; retrieving a simplified version of at least a portion of the protective suit design; performing a preliminary simulation using the simplified version; comparing a result of the preliminary simulation to a performance criterion; in response to the preliminary simulation failing to meet the performance criterion: performing a comprehensive simulation using at least a portion of the detailed model; in response to the comprehensive simulation failing to meet the performance criterion, iteratively: updating the protective suit design; and repeating the storing, retrieving, performing, and comparing steps using at least a portion of the updated protective suit design; and in response to the result of the preliminary simulation or comprehensive simulation meeting the performance criterion, generating output data.

This invention discloses a multifunctional integrated space physiological countermeasures and movement assistance suit and its control method. The spacesuit includes: a negative pressure fluid regulation system that applies controllable negative pressure to regulate fluid distribution; a biomimetic muscle system that applies controllable torque to simulate muscle exertion; an axial loading system that applies longitudinal compressive stress to simulate bone compression; and a control system that coordinates the operation of each system. In a preferred embodiment, the negative pressure system has multiple sealed zones with the negative pressure value increasing from the head side to the foot side and synchronizing with the cardiac cycle. The biomimetic muscle system can switch between assisted, resistive, and free modes. The axial loading system includes independent subsystems for the cervical spine and trunk-lower limbs. This invention is the first to integrate zoned stepped negative pressure, synchronized cardiac cycle regulation, biomimetic muscle coordination, and graded axial loading into a single wearable system, enabling all-weather simulation of Earth's gravity effects and addressing issues such as head-to-head fluid shift, muscle atrophy, bone loss, and disuse changes in the spine under microgravity.

A fluid pump for generating a fluid stream includes a first actuator with a first vibration element, a second actuator with a second vibration element, and a power source supplying energy to the first and second actuators. The pump further includes a controller that is connected to the source and controls the source to vary the energy supplied to the first and second actuators. The first and second actuators are arranged opposite to each other so that a first movement direction of the first element is inclined with respect to a second movement direction of the second element. The controller controls the source so that the first element moves towards the second actuator and the second element moves towards the first actuator in a synchronous manner and thereby cyclically soaks in a fluid from the surroundings and ejects the fluid in a directed manner.

Disclosed herein are devices, systems, and processes for providing water collection and filtration of user wastewater for return as potable drinking water. Systems described include ones with a plurality of layers having a top layer with water permeable fabric, a first middle layer with an antimicrobial material, a second middle layer with activated carbon, a bottom layer having a water impermeable material, an osmotic filter configured to filter the collected bodily fluid from the bodily fluid collection system; and a mechanical device configured to move the filtered fluid from the osmotic filter.

Composite materials incorporated with shear thickening fluids (STF) are disclosed. The STF-composites are light weight and include high tenacity textiles that dissipate / absorb energy from impact forces and exhibit damage resistance and self-healing functionality. Also disclosed are articles comprising STF-composite materials, such as safety suits and extra-vehicular mobility units, which include STF-intercalated textiles and composites. Methods for Manufacturing STF-composites are also disclosed.

The application discloses a low-power-consumption electromagnetic locking and separating shoe in a zero-gravity or micro-gravity environment, which comprises a magnetic conducting pad, an electromagnetic locking and separating device, a shoe bottom and a shoe face; the shoe face and the shoe bottom are combined to form a shoe body; the front end inside and the rear end inside of the shoe bottom are respectively provided with two cavities, and the two cavities are respectively provided with the electromagnetic locking and separating device; the electromagnetic locking and separating device comprises a fixed iron core group, a movable iron core group and an electromagnetic group; the fixed iron core group and the electromagnetic group are fixedly connected with the shoe bottom, the movable iron core group is arranged between the fixed iron core group and the electromagnetic group, and the movable iron core group is slidably connected with the shoe bottom; when the electromagnetic group is powered, the movable iron core group is pushed to make the movable iron core group adhere to the fixed iron core group, or the movable iron core group is pulled to make the movable iron core group adhere to the electromagnetic group, so that the locking or separation of the shoe body and the magnetic conducting pad is realized. The electromagnetic locking and separating shoe has the advantages of simple structure design, light weight, low power consumption (pulse voltage driving is adopted), low magnetic flux leakage (magnetic circuit is closed when in the locking or separating state) and the like.