155results about "Cosmonautic crew accomodations" patented technology

An aerospace hardware derelict item is salvaged in space, modified, and reused to provide manned facilities in orbit. The hardware packages added onto the salvaged discarded item enhances its value, and incorporates at least the subsystems required to effectively reuse portions of previously discarded launch vehicle components, and other derelict objects in space. The hardware, and technique used reduces the cost of launching comparable hardware to orbit, because of the reuse, and provides a human habitation in orbit. The salvaged items include the external tank of the space shuttle, other derelict orbital hardware, the add-on cargo pod in two forms, and the ability to convert the derelict into a cost effective reusable item. The salvaged hardware is initially capable of contributing mass, length, interior volume, strongback, rotational stability mass, interior pressurized volumes, artificial gravity, and stability with the addition of simple subsystems for salvage, and interior development packages.

A launch vehicle upper-stage escape system is described that allows a crew capsule or a payload capsule to be safely and rapidly separated from a launch vehicle in the event of an emergency using the upper stage main engine for propulsion. During the initial portion of the flight the majority of the propellant mass for the upper stage is stored in the lower stage. This minimizes the mass of the upper stage allowing the upper stage main engine to provide sufficient acceleration to lift the capsule off of the launch vehicle and to move the capsule away from the launch vehicle to a safe distance with sufficient speed in the event of an emergency. It can also be used to lift the crew or payload capsule to a sufficient height for recovery systems to be employed successfully in the event of an on-pad or low-altitude launch emergency.

The invention provides a multifunctional manned lunar surface lander based on modular design, modularization and integral landing and take-off design modes are adopted, and repeated use and extensibleapplication are achieved. The lander comprises a living cabin, wherein the living cabin is in a multifunctional centralized manner, is located on the upper part of the lander and is used for establishing sealing connection with other aircrafts, providing life and working environments for an astronaut and supporting the astronaut in entering and exiting from the cabin; and the lander further comprises a landing cabin, the landing cabin is used for placing a propelling system, electronic equipment and a landing buffering mechanism so that a supporting platform and a buffer energy absorption support can be provided for landing and take-off, and the living cabin and the landing cabin are designed in a modular mode so that different tasks can be executed through the combination of different modules. The manned lunar surface lander is compact in structure and low in requirement for the transport capacity of a carrier rocket, can be used repeatedly, has a multi-task application expansion characteristic, and is beneficial for reducing the cost of the manned lunar-landing comprehensive task.

A geosynchronous Solar Power Satellite System is created by an artificial gravity, closed ecology, multiple use structure in low earth orbit that manufactures modular solar power panels and transmitter arrays. This facility takes empty fuel tanks and expended rocket boosters from launch vehicles that are sent into low earth orbit, and re-manufactures them into structural components. These components are mated to solar cells that are launched from earth. The modular solar panels are transported to geosynchronous orbit by vehicles with ion engines, where the panels are mated to other solar panels to collect power. Structural components are also mated to transmitter elements launched from earth. These are likewise transported to geosynchronous orbit. They are mated to the solar power collecting panels and they beam the collected power back to earth.

This invention provides a mechanism to create an artificial gravitational environment in a toroidal space station in which gravity may vary from zero, of advantage during repairs, manufacturing and research activities, and docking maneuvers, to values greater than one g for preparing astronauts for missions to other planets, or for other purposes. The mechanism couples the rotation of a high density cylinder in the center of the hub to that of the torus through gears such that the total angular momentum of the station is zero, allowing maneuvering of the station to be less complicated since gyroscopic effects are eliminated, and the level of gravity in the torus to be varied without the use of external thrusters. Gears are driven by motors attached to the hubs, providing redundancy for maintenance and emergency operations, with power provided by solar cells, a nuclear power plant, or other means.

A reusable module is affixed atop a reusable orbital vehicle (OV). Various configurations of the reusable module have identical external dimensions in the region of attachment to the OV, aerodynamic characteristics, and mounting configurations to permit interchangeability. Different configurations can accommodate a variety of missions of different type and duration. The module may be a cargo module, a satellite payload module or a passenger module. The passenger module is provided in a variety of configurations to accommodate a different number of passengers and cargo based on mission parameters.

An artificial gravity system and method for a spacecraft including a least one pair of rotatable stages wherein each stage is capable of rotating about at least one structural support in the spacecraft and wherein the rotatable stages in each pair of rotatable stages counter-rotate one another wherein each stage is capable of accommodating a plurality of occupants. The stages may be circular and deployable. The system may also include dynamic balance equipment in each stage consisting of a fluid redistribution design utilizing fluid pumping systems, storage- and reserve-volume tank pairs to redistribute fluid throughout each stage for optimal mass balance, stage- and spacecraft-mounted laser-tracking equipment for redundant speed measurement, drive assembly and a brake motor and wheel assembly, foldable structural support arms capable of reducing the radial space of each stage during takeoff, and an inertial measurement unit capable of detecting overall vehicle rotational rates.

A two-part seat (10) providing full body support that is specific for each crew member (30) on an individual basis. The two-part construction for the seat (10) can accommodate many sizes and shapes for crewmembers (30) because it is reconfigurable and therefore reusable for subsequent flights. The first component of the two-part seat construction is a composite shell (12) that surrounds the crewmember's entire body and is generically fitted to their general size in height and weight. The second component of the two-part seat (10) is a cushion (20) that conforms exactly to the specific crewmember's entire body and gives total body support in more complex environment.

The invention provides a joint type portable feet limiter comprising a limiting pedal, a yaw adjusting joint mechanism, a deflection adjusting joint mechanism and a pitch adjusting joint mechanism. The yaw adjusting joint mechanism comprises a yaw indexing positioning unit. The limiting pedal is mounted on the upper portion of the yaw adjusting joint mechanism. The deflection adjusting joint mechanism is connected to the lower portion of the yaw adjusting joint mechanism. The deflection adjusting joint mechanism comprises a deflection indexing positioning unit. The pitch adjusting joint unit is connected to the lower portion of the deflection adjusting joint mechanism and comprises a pitch indexing positioning unit. A loading limiting mechanism, used for overload protection, and a rapid mounting connector mechanism, used for connecting with other equipment, are mounted on the pitch adjusting joint mechanism. By the use of the feet limiter, a supporting platform is provided for a spaceman to perform real-time pose adjustment in space, operation motions for large-angle pose adjustment are fewer, and physical exhaustion of the spaceman is avoided.

Method and arrangement for adjusting nitrogen and oxygen concentrations within regions of an aircraft. The method includes separating nitrogen from ambient air onboard an aircraft thereby establishing a high-concentration nitrogen supply and then dispensing high-concentration nitrogen from the supply to a fire-susceptible, non-habitable region of the aircraft where the high-concentration nitrogen is reservoired thereby decreasing the capability for the atmosphere therein to support combustion. Oxygen is also separated from the ambient air thereby establishing a high-concentration oxygen supply that is dispensed to an occupant cabin of the aircraft thereby increasing the level of oxygen concentration within the cabin to a level greater than the naturally occurring concentration of oxygen at the experienced internal cabin pressure. When it is determined that reduced oxygen concentration is required in the occupant cabin, the reservoired high-concentration nitrogen is moved into the passenger cabin diluting the oxygen-elevated environment.

An actuatable emergency exit door with a door actuating device that comprises at least two connection rods that are pivotally mountable to an associated structural frame that is adapted for accommodating the actuatable emergency exit door in closed state, the at least two connection rods being provided for enabling an opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening, wherein at least one door-mounted goose neck-shaped structure is mountable to the associated structural frame for enabling an initial translational opening movement and subsequently a swiveling opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening. The invention is further related to an aircraft or space craft with a pressurized cabin having such an actuatable emergency exit door.

The invention discloses a stretch-draw type expansible space capsule section skeleton structure, and relates to the field of manned space flight. The problems that an existing space capsule section islarge in structure mass and hard to expand or convey are solved. A base is a circular base, a central stretchable core column mechanism is perpendicularly arranged in the center of the base, the central stretchable core column mechanism is sleeved with a whole stretch-draw frame structure, multiple pairs of connecting frames are evenly arranged on the base, the whole stretch-draw frame structureis connected with the base through multiple pair of connecting frames, the axis of the whole stretch-draw frame structure coincides with the axis of the central stretchable core column mechanism, andthe whole stretch-draw frame structure is a net-shaped stretchable structure composed of a plurality of rod pieces and a plurality of ropes, wherein the appearance of the net-shaped stretchable structure is cylindrical; the rod pieces of the whole stretch-draw frame structure are all stretchable rod pieces, the whole frame can be expanded by means of stretching and retracting of the rod pieces, and meanwhile, the central stretchable core column mechanism is expanded under the drive of external force. The stretch-draw type expansible space capsule section skeleton structure is high in expansibility and the folding space is normal.

The invention discloses an assisting method and device for movements in space. According to the assisting method and device, the moving ability of astronauts can be effectively enhanced. According to the method, an external skeleton system is coupled on a space suit. The external skeleton system comprises a profiling mechanical structure, a man-machine interface system, a control system, an actuator and an energy power system. The man-machine interface system senses and sends moving states and moving intensions of the astronauts to the control system, the control system processes information and sends instructions to the actuator, and the actuator drives the profiling mechanical structure to assist in supporting of astronaut loads or providing of boosting power for movements of the astronauts, accordingly, energy consumption of the astronauts is greatly reduced, the bearing ability, the moving ability of upper and lower limbs and the information processing ability of the astronauts are improved, the adaptability of the astronauts to severe environments is enhanced, and the astronauts are assisted in completion of various space operations. Besides, by the aid of the profiling mechanical structure, astronaut bodies can be protected, the astronauts are prevented from being injured, and the assisting method and device are suitable for popularization in the of astronaut space operation devices.

The invention discloses a connecting device applied between an outboard handle of a spacecraft and an exposed load. The connecting device comprises an outboard-handle connecting device and an exposed-load connecting device; the outboard handle of the spacecraft and the exposed load are peripheral equipment; the outboard-handle connecting device and the exposed-load connecting device are connected; the exposed-load connecting device comprises a load mounting port and a load fastening and positioning assembly; the load mounting port consists of a spherical structure and a load mounting structure, and is in integral design; the load mounting structure is fixed with the exposed load; the load fastening and positioning assembly fixes the spherical structure by utilization of a fixing manner of pretightening force; and the outboard-handle connecting device fixes the handle by utilization of the fixing manner of pretightening force. Through the adoption of the connecting device disclosed by the invention, guiding mounting, reliable fixation, precise positioning and overload protection of the exposed load and the outboard handle are realized, so that the connecting device provides a technical support for rapidly mounting the exposed load and the outboard handle at set outboard positions.

The spacecraft structure is provide, the spacecraft structure for the spacecraft includes, a center fuselage, right wing side fuselage, left wing side fuselage, front wings, and rear wings of Arch-Wings, vertical winglets, and the first levels, the fuselage has a cross-section of substantially flat floor fuselage shape, being is wide enough to provide lifting force.The front wings of the Arch-Wings are disposed horizontally in rear portions of the fuselage the vertical winglets are disposed the top of the rear fuselage the first level disposed fuel tank storage, plurality of landing gear bays, cockpit with control panel, various avionic instruments, cabin doors.The top of the rear fuselage disposed jet-power plants and further more at compartment of the Arch-Wings disposed rocket power plants.The fuselage provide lifting force and the wings provides lifting force and steering force, he whole structure of spacecraft comprises carbon fiber honey comb composite molded structure which is makes the spacecraft lighter weight and shear strong.At the front portion of wing body compartment of the Arch-Wings comprises retro rocket power plant with covered door, and under belly of the Arch-Wings disposed pontoon systems which could provide float at sea port.

A method for making an opening in the bladder of an inflatable modular structure. The structure has a core comprised of a fore and aft assembly separated by a longeron. There is an inflatable bladder and a restraint layer that are secured to the core. The restraint layer is comprised of two circumferential strap assemblies; each attachedly fastened at opposing ends of a radial strap assembly, and has an opening for a window. The restraint layer fits over the bladder. The bladder is inflated and the restraint layer is used along with a window template to locate the position of the window on the bladder. The bladder is deflated, the template is removed, and the identified portion of the bladder is cut away. The method may then be repeated.

A berth arrangement, especially for means of transport, is described, comprising a plurality of single berths (1) which are arranged in rows in a successive, superimposed and mutually offset fashion and receive at least one reclining seat (6), and which berths form a sitting room (2) and a foot room (3) starting out from the sitting room (2), with the height of the foot room being smaller than the sitting room height. In order to provide advantageous constructional conditions it is provided that the respective ceilings (5) and floors (4) of the sitting rooms (2) correspond to the negative shapes of the floors (10) and ceilings (9) of the foot space (3).

The invention discloses a gas-filled unfolded article storing cabin, relating to an article storing cabin for a space station. The invention aims to solve the problem that the existing spacecraft is not provided with a garbage collecting cabin dedicated for collecting garbage and waste articles. The framework of the storing cabin comprises an annular gas tube and a gas-filled supporting tube, wherein the gas-filled supporting tube is connected between every two annular gas tubes; the outside of the framework formed by the annular gas tube and the gas-filled supporting tube is coated with skin; the inner part of the framework formed by the annular gas tube and the gas-filled supporting tube is provided with an lining; the annular gas tube and the gas-filled supporting tube adopt a structure capable of being rigidized and unfolded after aeration; the annular gas tube and the gas-filled supporting tube can take the inflation pressure as a driving force to be unfolded along an axial direction; the annular gas tube and the gas-filled supporting tube, the skin and the lining are electrified and solidified or solidified by space thermal radiation or ultraviolet radiation in the space environment, thereby forming stable article storing cabin meeting the structure rigidity requirement.

Disclosed is a modular, human-crewed interplanetary spacecraft that is assembled in cislunar space. It is primarily comprised of a hollowed-out asteroid; five expandable habitation modules, one of which is expanded inside the asteroid cavity; two docking and airlock nodes; two landing craft suitable for exploring celestial bodies; structural support members; truss structures; robotic arms; a propulsion module; and shielding curtains that are filled with pulverized asteroidal material and attached to the truss structure. This configuration provides substantial radiation and meteoroid shielding. Upon completion of their mission, the crew will use the robotic arms to disconnect and mate (1) the asteroid containing the control module, (2) the forward docking and airlock node, and (3) the propulsion module. This crew-return vehicle will return to cislunar space. The remaining expandable modules with trusses, robotic arms, and landing craft will remain in the destination orbit to serve as a space station for future missions.