61results about "Cosmonautic crew accomodations" patented technology

The utility model discloses a damping and buffering device, and belongs to the technical field of manned spacecraft seats. The utility model discloses a damping and buffering device which comprises a headrest, a backrest, a seat cushion, a pedal, a shaping pad and a nanometer energy absorption module. The headrest, the backrest, the cushion and the pedal are sequentially and rotatably connected to form a seat framework, and one end of the headrest and one end of the pedal are connected with the interior of application equipment respectively; the nano energy absorption module covers the outer surface of the seat framework; according to the device, the energy absorption effect is improved, when the device is subjected to an external impact load, the nano energy absorption module can absorb most of energy, the impact load can be averagely distributed, the safety of operators is guaranteed, and the problem that a traditional energy absorption device is low in energy absorption density is solved.

A reusable orbital vehicle (14) for a space transport system (10) comprises a fuselage (22) the shape of which widens in a direction extending from the front end (24) of the reusable orbital vehicle to a rear end (26) of said fuselage (22) and inside which there is defined a housing (32), and a crew-evacuation vehicle (34) housed in said housing (32) and oriented in such a way as to be extracted from the housing (32) in a direction (D1) directed from said rear end (26) of the fuselage (22) toward said front end (24) of the reusable orbital vehicle (14).

The invention relates to the area of space science, in particular, to the area of industrialization of outer space and, directly, to the facilities for inserting and moving various objects in circumplanetary cosmic space. It is intended to solve geocosmic problems in industrial-scale volumes - to carry out research and development, special-purpose, touristic and other types of works and services in outer space and stabilize global climate. Artificial orbital ring complex by Yunitski is made in the form of a ring satellite (1), located in a circular orbit (5) around a natural cosmic body (2) in the equatorial (4) plane (3), which comprises: structural frame (7), utilities (8) and communications (9), power units (10), transition galleries (11) positioned in annular housing (12) with protective shell (13), gate chambers (14) with docking units (15), configured to dock with space vehicles (16), residential (19) and research-production (20) units, equipped with systems of control, life support, active and passive (17) protection against the harmful effects of space (18). The structural frame (7) is longitudinally tensioned, and the ring satellite (1) is in circular motion in orbit around the natural cosmic body (2) with velocity V0, m / sec, defined by the ratio: 1≤V0 / V1H≤1.01, where V1H, m / sec, - first space velocity for the equatorial circular orbit of the location of the ring line connecting the centers of mass of the cross sections of the artificial orbital ring complex, at altitude of H0, m, defined by the ratio: 0.02≤H0 / R0≤0.5, where R0, m, - radius of natural cosmic body (2) in equatorial (4) plane (3).

The invention belongs to the field of space cooking equipment, and particularly relates to a frying machine suitable for microgravity and closed space environments, which comprises an elliptical annular wind tunnel structure, a circular truncated cone-shaped centrifugal heating cylinder module, a plurality of solid food material injection bin modules, a liquid injection module, a pot discharge device module and a vacuum pressure regulation module, the oval annular wind tunnel structure comprises a first wind tunnel section, a second wind tunnel section, a third wind tunnel section and fourth wind tunnel sections, the solid food material injection bin module is arranged on the surface of the third wind tunnel section, the third wind tunnel section is provided with an axial flow fan close to the first wind tunnel section, and the circular-truncated-cone-shaped centrifugal heating cylinder module is axially connected between the fourth wind tunnel sections. The plurality of liquid spraying modules are arranged on the surface of the second wind tunnel section, the second wind tunnel section is provided with a pot discharging device module close to the tangential direction of the fourth wind tunnel section, and the vacuum pressure adjusting module is connected with the solid food material injection bin module and the pot discharging device module. The environment cleanness is ensured.

A human waste collection system having a basin (140) defining a basin cavity (150) and a lower end (145) that is configured for being positioned against a floor and an upper end (160) that is displaced further from the plane than the lower end; a storage bag (165) system disposed in the basin cavity; a seat (170) disposed at the upper end of the basin, the seat having a lid (190); a suction system (230) having a first suction conduit (235) extending into the basin cavity, adjacent to the upper end of the basin; a controller (240) having a user interface (245) that has user engageable features to select between operation modes including a first mode for removing menses and solid waste and a second mode for removing urine, wherein: in the first mode, menses and solid waste is collected in the storage bag; and in the second mode, the suction system suctions urine.

The invention relates to a transport system (1) intended to be installed on a space launcher (100) comprising:an aircraft (2) which comprises propulsion means configured to propel the aircraft (2) in a direction of flight, and at least one seat (4) intended to receive a passenger which is movable in rotation about an axis (0) perpendicular to the direction of flight of the aircraft (2), an acceleration sensor being installed on each at least one seat (4) to measure the acceleration of each at least one seat (4);a passenger interface for each at least one seat (4) which comprises a screen intended to display images to the passenger installed on said at least one seat (4), the screen being coupled to said at least one seat (4) so to remain fixed relative to said at least one seat (4);a control unit (6) which is connected to the acceleration sensor and to said at least one seat (4), the control unit (6) being configured to calculate a load factor experienced by the passenger installed on the at least one seat (4) from the acceleration of said at least one seat (4), the control unit (6) being configured to monitor the rotation of the at least one seat (4) during the operation of the transport system (1) in order to maintain the position of the seat (4) fixed relative to the load factor experienced by the passenger throughout the flight.

Waste collection and processing systems for use in low-gravity environments include a toilet having a bowl and a lid, the toilet configured to receive solid human waste; a liquid waste collection system comprising a liquid waste receptacle configured to receive liquid human waste; a first waste tank fluidly coupled to the toilet; a second waste tank fluidly coupled to the liquid waste collection system; a third waste tank fluidly coupled to the liquid waste collection system, wherein the first waste tank, the second waste tank, and the third waste tank are each configured to be operated between reclamation modes of operation and collection modes of operation; and a waste outlet configured to selectively receive an airflow from each of the first waste tank, the second waste tank, and the third waste tank.

The present application relates to the field of aerospace technology, in particular to a kind of spaceship carbon-oxygen water circulation life support system, including oxygen circulation module, water circulation module, monitoring module and control module, oxygen circulation module provides oxygen, and carbon dioxide is converted into harmless substance, water circulation module provides drinking water, bath water, coolant and the water source of other water needed equipment, monitoring module monitors environmental data in spaceship, control module obtains environmental data, and adjusts oxygen circulation module and water circulation module according to environmental data. Through carbon-oxygen water circulation, realize the recycling of resources in the spaceship, greatly reduce the dependence on external resources, improve the autonomy and sustainability of the spaceship, due to the stability and suitability of the spaceship internal environment, can guarantee the health of astronauts, reduce the occurrence of disease, improve the survival rate of astronauts.

The utility model relates to a water replenishing device and cooking equipment, which can automatically replenish water in a microgravity environment so as to continuously generate steam to steam food and meet the taste and taste requirements of passengers. The water supplementing device comprises a water storage bag which comprises a flexible bag body used for storing water, an exhaust connector arranged on the flexible bag body and a water outlet connector arranged on the flexible bag body; the exhaust assembly comprises an exhaust pipe connected with the exhaust connector and an air pump arranged on the exhaust pipe; the water absorption piece is provided with a porous structure, and the water absorption piece is provided with a first end part which is inserted into the water outlet interface, a second end part which is arranged in the steaming tool, and a middle part which extends from the first end part to the second end part; and the flexible bag body is used for conveying water stored in the flexible bag body into the steaming tool under the capillary action.

Described is an apparatus for improving user physiological states in a spacecraft. The apparatus can include releasable layers, a bladder integral to the releasable layers, rails to connect the releasable layers to the spacecraft, and a controller configured to control environmental conditioning or the physiological conditioning thereby improving physiological states of a user.

The utility model relates to a steam generator and cooking equipment, which can generate high-temperature steam in a microgravity environment to cook food and meet the taste and taste requirements of passengers. The steam generator comprises a water supply pipe which is provided with a water supply flow channel and a plurality of capillary holes communicated with the water supply flow channel; the water absorption piece is fixedly connected to the water supply pipe so as to cover the capillary holes, and the water absorption piece is provided with a porous structure and is used for absorbing water under the capillary action; and the heating piece is arranged on the water absorption piece and is used for heating the water absorption piece to generate steam.

A workstation for microgravity environments is provided that prevents objects from floating around inside a spacecraft. The workstation includes a downdraft table that has a plenum chamber with an inlet and an outlet. A fan is disposed in the plenum chamber for drawing air into the plenum via the inlet, and exhausting air from the plenum via the outlet. A metal grate is disposed across the inlet, and an air resistive stack is disposed on an outer side of the metal grate. The air resistive stack includes an inner resistive layer disposed on the metal grate and an outer resistive layer disposed on the inner layer. The workstation improves a user's ability to perform many activities in a microgravity environment.

This application relates to a rice steaming bag and cooking device. The rice steaming bag includes a main body and a lid. The main body has an open placement cavity. The main body includes a circumferential surface defining the placement cavity. The circumferential surface includes a sealing layer, a gel layer, and a breathable layer arranged sequentially from the outside to the inside. The sealing layer is made of a sealing material, the gel layer is made of hydrogel, and the breathable layer has vents communicating with the placement cavity. The gel layer is exposed to the placement cavity through the vents. The lid is placed on the main body and covers the open cavity when the lid is closed. The end faces of the main body (excluding the circumferential surface) and / or the end faces of the lid have vents communicating with the outside. This solution can be applied to microgravity environments, such as space, to steam rice in a microgravity environment. Only washed rice grains need to be placed in the rice steaming bag beforehand; no additional water is needed, making the rice steaming process convenient and simple.

Systems and methods for achieving pristine microgravity in low earth orbit (LEO) using electric propulsion. Long-duration, low thrust, electric thrusters provide a constant thrust force for a pristine microgravity environment within a given volume of a space vehicle experiencing drag forces in LEO. Large space vehicles in LEO configured to be pressurized for human habitation, for instance having a mass of at least 40,000 kg and an internal volume of at least 400 m3, can use the electric propulsion systems and methods to achieve a quasi-steady acceleration less than or equal to 1.0 μg for durations of 180 consecutive days or longer.

To integrate a large number of propulsion force generating devices accompanied by an air current as reaction in a propulsion force direction while avoiding the air current.SOLUTION: In one embodiment of the present invention, a centrifugal force is applied to the air flow in a direction perpendicular to the direction of the propulsive force, and the path of the air flow is controlled so that the air flow does not hit other components of the stack. As a propulsive force generating device, there is a technique for obtaining a propulsive force by breaking the balance of atmospheric pressure in the device by diffraction of gas molecules derived from the wave nature of matter waves based on the quantum theory. Since this technology is in the field of fine technology including nano-technology, the device size is small, and it is necessary to integrate a large number of devices in order to obtain a practical driving force. A practical propulsion force can be obtained by the accumulation method of the present invention.SELECTED DRAWING: Figure 18

A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.

A seat system for use in a crew escape system of a space transport vehicle comprises a seat having a backrest with a supporting surface. The seat is configured to be installed in a cabin area of the crew escape system so it can rotate about a first axis between a first position where the seat faces a first direction, and a second position where faces a second direction that is opposed to the first direction. The seat system further comprises a control unit configured to control a rotation of the seat at least between the first position and the second position in dependence on at least one signal which is indicative of a trajectory of the crew escape system.

To improve the energy efficiency of a space station.SOLUTION: A space station according to an embodiment includes a management area, a living area arranged around the management area, a connection part for connecting the management area and the living area, and a drive part for rotating the living area around the management area to generate predetermined gravity in the living area. A space station includes a power generation part for generating power on the basis of rotation of a motor of a drive part.SELECTED DRAWING: Figure 3

The invention discloses a repeated unfolding and folding device for an astronaut seat, and belongs to the technical field of aerospace. The device comprises a base, a supporting rod mechanism, a mounting plate and a locking mechanism, wherein the supporting rod mechanism is hinged between the base and the mounting plate; the locking mechanism comprises a locking piece and a locking seat; the lock piece comprises a lock body, a lock shaft, a lock cap and a spring, the lock body is arranged on the mounting plate, a shaft limiting part is arranged on the lock shaft, the spring is arranged on the lock shaft in a sleeving mode and located between the shaft limiting part and the mounting plate or the lock body, one end of the lock shaft stretches out of the mounting plate to be connected with the lock cap, and the other end of the lock shaft can stretch out of the lock body to be matched with the lock hole of the lock seat. The seat posture adjusting device is simple and compact in structure and convenient to adjust, has high stability and reliability in an unfolded locking state, can stably support the handle, is low in height in a folded storage state, does not interfere the astronaut with entering and exiting the astronaut seat when the handle is moved to the shoulder or head position of the astronaut, and does not affect the astronaut to control the seat posture adjusting device.

A space station includes a housing that defines an interior space. An inner chamber is located in the interior space and defines an inner cavity that is sealable from the remainder of the interior space. At least one bulkhead is arranged in the interior space to partition the interior space into at least two compartments that are hermetically sealable from one another. One compartment can be accesses from another compartment via the inner cavity of the inner chamber. The inner cavity is sealable against each compartment. Openings in an outer surface of the housing enable crew members to leave a damaged compartment through the opening. Thus, alternative routes exist to leave a damaged compartment, i.e., either through the inner cavity or through the opening in the outer surface of the housing. When one compartment is damaged, the adjacent compartments are still operative because they are sealed from the damaged compartment.

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 application discloses a space station folding cabin interconnecting device, which comprises a cabin interconnecting device, a base connecting assembly, a base end connecting rod assembly, a folding assembly, a handrail end connecting rod assembly and a handrail connecting assembly; one end of the cabin interconnecting device is provided with a cabin interconnecting device base, and the other end is provided with an extravehicular handrail one; the cabin interconnecting device base is provided with a cabin wall mounting interface, a device butt joint interface and a primary positioning anti-drifting ball pit one; the base connecting assembly comprises an angle adjusting mechanism and an angle adjusting limiting mechanism, and the angle adjusting mechanism comprises a ball head, a half-ball bowl, a ball bowl stop ring and a ball joint sleeve. In the application, the base connecting assembly, the base end connecting rod assembly, the folding assembly, the handrail end connecting rod assembly and the handrail connecting assembly can be used in a space on-orbit environment influenced by multiple factors such as microgravity, thermal cycle, solar radiation, particle radiation and atomic oxygen, and the safety of astronauts in on-orbit erection and use transfer is fully considered.

Methods, devices, and systems are described for a bracket fixture for securing a load to a soft goods layer in a space habitat. The bracket fixture includes a base having a plurality of sides, the plurality of sides having a pin parallel to its respective side, and an aperture between the pin and the respective side. The bracket fixture further includes a protrusion extending from the base, the protrusion including a fixture element.

In one aspect, a system includes a water stream in fluid communication with an electrolyzer, the electrolyzer including an anode chamber and a cathode chamber, a deep-space oxygen radiator in fluid communication with the anode chamber of the electrolyzer, a low-temperature heat exchanger including an oxygen storage tank in fluid communication with the deep-space oxygen radiator, an electrochemical hydrogen compressor in fluid communication with the cathode chamber, and a hydrogen storage tank in fluid communication with the electrochemical hydrogen compressor via the cooled hydrogen stream, wherein at least a portion of the cooled hydrogen stream is in first fluid communication with the expansion valve and the low-temperature heat exchanger, the hydrogen storage tank is in second fluid communication with the electrochemical hydrogen compressor via the warmed hydrogen stream, and the low-temperature heat exchanger is in fluid communication with the warmed hydrogen stream.

The invention relates to the technical field of aerospace, in particular to a design and manufacturing method for a manned space station with a motor and a West-odd-female-pending spacecraft, a female-pending engine is adopted as a propelling system of the spacecraft, so that the spacecraft can run at a super light speed, the time of the spacecraft traveling in the interstellar is greatly shortened, and meanwhile, the space station is suitable for being popularized and applied. Since the time on the spacecraft becomes slower than the time on the earth, the time expansion effect during travel is reduced, and in addition, the Femon engine does not depend on traditional material fuel, but generates thrust by manipulating the spatial curvature, thereby greatly reducing the weight and volume of the spacecraft and reducing the cost of the spacecraft. Therefore, the technical problem that when an existing space propulsion technology of the spacecraft is used, the power and the propulsion speed are limited, and the requirements for safety, rapidness and high efficiency of the spacecraft during flying cannot be met, so that the spacecraft cannot meet the requirement for long-term exploration of space is solved.

The utility model relates to a microwave steaming device which can enable water to be efficiently changed into water vapor to steam food in a microgravity environment, and the taste and taste requirements of passengers are met. The microwave steaming equipment comprises a microwave generator used for emitting microwaves; the steaming tool is arranged on the microwave emitting side of the microwave generator and used for containing food; the water absorption piece is provided with a porous structure and is used for absorbing water under the capillary action; and the water absorption piece is arranged in the steaming tool, is positioned in the microwave heating area of the microwave generator, and is used for generating water vapor under the action of microwave heating so as to steam the food in the steaming tool.

A seat system (10) for use in a crew escape system (500) of a space transport vehicle (1000) comprises a seat (12) having a backrest (14) with a supporting surface (16) which, when the seat (12) is used by a crew member (106), is suitable to support an upper body of the crew member (106), and being configured to be installed in a cabin area (100) of the crew escape system (500) so as to be rotatable about a first axis (R1) at least between a first position, wherein the supporting surface (16) of the backrest (14) faces a first direction (D1), and a second position, wherein the supporting surface (16) of the backrest (14) faces a second direction (D2), the second direction (D2) being opposed to the first direction (D1). The seat system (10) further comprises a control unit (25) which is configured to control a rotation of the seat (12) at least between the first position and the second position in dependence on at least one signal which is indicative of a trajectory of the crew escape system (500).

The invention relates to an integrated kitchen which comprises a cooking module and an oil smoke processing module, the cooking module comprises a first cooking device and a second cooking device which have different cooking functions, and the first cooking device and the second cooking device are distributed up and down. Both the first cooking equipment and the second cooking equipment are provided with smoke outlets for discharging oil smoke; the oil fume treatment module comprises a main body and a fume exhaust runner, the main body is located on one side of the second cooking equipment and provided with a fume suction opening facing the second cooking equipment, the fume suction opening communicates with the two fume outlets, and an exhaust opening is formed in the end, away from the main body, of the fume exhaust runner and located above the main body and located on one side of the first cooking equipment. According to the scheme, the problems that the space utilization rate is low, operation is complex and cooking fume is difficult to treat due to scattered distribution of cooking equipment in an existing microgravity environment are solved, the space utilization rate and dining efficiency in the capsule body of the space capsule are improved, and the dining environment is improved through cooking fume treatment.