41results about "Space suits" patented technology

Self-adaptive fabrics for space applications are provided. In one aspect, a fabric for use in space includes a structural fabric and a plurality of synthetic fibers woven into a self-adaptive fabric. The self-adaptive fabric is attached to the structural fabric. Each of the synthetic fibers includes a plurality of hollow cells containing a trapped gas. The synthetic fibers are formed of a material having a sufficient elasticity such that the diameter of each of the synthetic fibers is configured to increase when the environmental pressure decreases.

Systems and methods for assisting movement of a user and / or a base connected to one or more robotic limbs are described herein. Forces may be applied to one or more robotic limbs to control movement of the base. The base may be attached to a user, or other payload, and forces applied to the base due to externally applied forces, such as those applied by a user interacting with an environment, may result in reactionary forces being applied to the one or more robotic limbs. These forces may be detected and used to determine one or more commands for operation of the one or more robotic limbs. Optionally, the robotic limbs may include one or more end effectors which may removably couple or otherwise be held substantially stationary relative to an environment to form a closed loop kinematic chain.

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.

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.

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.

A pressure suit includes a communication unit, pressure actuators, and a control unit. The communication unit is configured to receive first data relating to the user's posture. The pressure actuators are located at different locations of the pressure suit and correspond to respective body parts, and are configured to selectively apply variable pressures on the respective body parts of the user when the pressure suit is worn by the user. The control unit configured to process the first data in or near real time and to selectively operate the pressure actuators in or near real time, so as to apply a desired pressure profile on the body of the user according to the posture of the user indicated by the first data, in order to create a venous blood pool that is similar to a venous blood pool that the user would have on Earth for the same posture.

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 invention discloses a lunar suit dust removal system and method based on electrets. The present invention sets an electret friction high-voltage generating module on the inner layer of the lunar suit, utilizes the astronaut's movement to frictionally polarize the electret, and generates a corresponding low-energy, high-amplitude voltage pulse to excite the outermost embedded flexible electrode module of the lunar suit to create a strong alternating standing wave electric field to drive away charged lunar dust. For small particles of charged lunar dust, a stripping polarization effect is used to generate stripping polarization charges on the bipolar electret body film, and a power-free uniform electric field is created between the bipolar electret and the electrode array to remove residual charged lunar dust. The present invention can achieve low power consumption, high electrostatic safety, and wide coverage to remove charged lunar dust. It can also prevent the charged lunar dust from secondary adhesion. It has the characteristics of good stability and high applicability, and is suitable for removing and protecting charged lunar dust adhered to the surface of the lunar suit.

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.

To produce vibration-based directional synthetic ambient sound in space.SOLUTION: A system includes a vibration detector to detect a location of vibration and identify a frequency of the vibration. The system also includes a controller to generate audio corresponding to the frequency of vibration detected by the vibration detector, and one or more speakers configured to provide the audio as directional sound.SELECTED DRAWING: Figure 2

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.

One embodiment provides a protective clothing system configured to protect an occupant in an extreme environment. The system may include a base layer configured for regulating the occupant's temperature and worn by the occupant, the base layer including a biomarker sensor network for monitoring one or more biomarkers of the occupant. The system may also include an outer layer worn over the base layer, the outer layer including an exoskeleton structure sized such that the occupant fits within the exoskeleton structure and an exoskeleton cover secured to the exoskeleton structure. The system may also include a data storage system capable of storing data generated by the biomarker sensor network.

An inductive power transfer system includes a receiver (130) to supply the inductive power to a battery (120), and a mobile charge platform (145) to transport a transmitter (150) to generate the inductive power. An atmospheric suit (105) includes a battery (120) to power at least one subsystem of the atmospheric suit, and a receiver (130) to receive inductive power from a transmitter (150) to recharge the battery (150).

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.

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.

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.

A magnetically controlled bouncing dust removal microstructure space suit relates to the technical field of space suits. The purpose of the present invention is to remove lunar dust from space suits and prevent lunar dust from causing damage to astronauts. The space suit proposed by the present invention includes an electromagnetic coil and a magnetically controlled bouncing mechanism; the magnetically controlled bouncing mechanism includes an outer magnetically controlled bouncing mechanism and an inner magnetically controlled bouncing mechanism; the outer magnetically controlled bouncing mechanism is sewn to the outermost layer of the space suit; the inner magnetically controlled bouncing mechanism is sewn between the outermost layer of the space suit and the thermal insulation layer; the electromagnetic coil is used to control the inner and outer magnetically controlled bouncing mechanisms to vibrate and remove dust. Large-particle lunar dust is removed by using the outer magnetically controlled bouncing mechanism, and small-particle lunar dust is captured by using the inner magnetically controlled bouncing mechanism. The present invention is suitable for space suits with dust removal function.

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.