158results about "Cosmonautic radiation protection" patented technology

A device for protecting against arcing events solar array panels and control equipment supplying a main power bus is provided. The control equipment comprises a regulator for controlling a solar array voltage (VS) and includes a power dump stage for shunting the solar array voltage as a function of a control signal. The device comprises a voltage drop detection circuit for generating a voltage drop detection signal (VD) when a voltage drop is detected in the solar array voltage (VS), and an arc-quenching circuit comprising a system for generating an output signal (VO) which is applied as the control signal to the power dump stage so as to shunt the solar array voltage (VS) when a voltage drop is detected by the voltage drop detection circuit.

An In Orbit Transportation & Recovery System (IOSTAR™) (10) One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

A system for transportation and storage of cargo in space includes one or more platforms. The platforms are operable to hold multiple removable propellant tanks and rendezvous with one or more other platforms in space. The platforms also include one or more thruster systems and positioners. Each positioner has an effector operable to grip a band disposed around each propellant tank. Each positioner is operable to facilitate the transfer of the multiple removable propellant tanks between platforms during the rendezvous.

An In Orbit Transportation & Recovery System (IOSTAR™) (10). One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot.

The invention discloses a spatial expandable ground plane device, comprising folding ring rods, ring rod connecting joints, folding rib rods, rib rod connecting joints, ring-rib connecting joints and rib frame connecting joints. The folding ring rods and the folding rib rods can be expanded from a vertical furled state to a horizontal working state through the ring rod connecting joints and the rib rod connecting joints. The ring-rib connecting joints and the rib frame connecting joints connect a ring structure with a rib structure to become a furled / expanded integral structure. A wire mesh or an aluminum-plated thin film is bound with the integral structure, so as to form the spatial expandable ground plane device. In a bound furled state, torsion springs in the ring rod connecting joints and the rib rod connecting joints store elastic potential energy; after binding is removed, the elastic potential energy of the torsion springs is transformed into driving energy so as to drive the ring rods and the rib rods to be expanded and locked automatically. The device has excellent comprehensive performance indexes of low surface density, high configuration precision and high ingathering rate, which can be used as an expandable support device in outer space or on ground.

The invention provides an anti-total-dose shielding device, which comprises a first low Z layer, a high Z layer and a second low Z layer, wherein the first low Z layer is used for moderating and shielding primary electrons, the high Z layer is used for scattering electrons and absorbing secondary bremsstrahlung photons, and the second low Z layer is used for absorbing photoelectrons and back scattered electrons generated in high Z materials and restraining secondary photoelectron emission and electron back scattering generated by action of X-rays and materials. The first low Z layer is the outmost layer and close to the space outside a satellite, and the second low Z layer is the innermost layer and close to a component to be shielded. The first low Z layer and the second low Z layer are made of materials formed by elements of atomic numbers smaller than or equal to 30. The thickness of the first low Z layer ranges from 1 to 3mm, and the thickness of the second low Z layer ranges from 0.2 to 0.4mm. The high Z layer is made of materials formed by elements of atomic numbers larger than or equal to 50, and the thickness of the high Z layer ranges from 0.1 to 0.3mm.

There is provided a radiation shield device for providing radiation protection to an area, such as a manned vehicle. The radiation shield device comprises a magnetic field generator, such as a solenoid, of superconductive material that provides a magnetic field around the area to shield the area from radiation. The magnetic field generator preferably comprises at least one trapezoidal portion to provide substantially isotropic protection to the area. A thermal control system, comprising a limited amount of coolant or a refrigeration cycle, is included to control a temperature of the superconductive material during operation of the magnetic field generator. A magnetic shield device may also be provided between the magnetic field generator and the area to be shielded from radiation to substantially shield the area from the magnetic field generated by the magnetic field generator.

A flexible space structure such as a solar array is composed of multiple solar cell modules (SCMs) each supporting an arrangement of solar cells on a frontside layer and incorporating a backside layer with a surface opposite from the frontside layer having a conductive coating. A selected portion of the SCMs have structural ground extension harnesses intermediate the frontside layer and backside layer. Conductive tapes secure vertically adjacent SCMs by attachment to the conductive coating and electrical jumpers interconnect the structural ground extension harnesses across gapped hinge lines of laterally adjacent SCMs.

There is provided a radiation shield device for providing radiation protection to an area, such as a manned vehicle. The radiation shield device comprises a magnetic field generator, such as a solenoid, of superconductive material that provides a magnetic field around the area to shield the area from radiation. The magnetic field generator preferably comprises at least one trapezoidal portion to provide substantially isotropic protection to the area. A thermal control system, comprising a limited amount of coolant or a refrigeration cycle, is included to control a temperature of the superconductive material during operation of the magnetic field generator. A magnetic shield device may also be provided between the magnetic field generator and the area to be shielded from radiation to substantially shield the area from the magnetic field generated by the magnetic field generator.

An apparatus having a composite sea-based structure with a first carbon nanotube infused material and a second carbon nanotube infused material. The first and second carbon nanotube infused materials each having a range of carbon nanotube loading selected to provide different functionalities.

A retractable rigid dome for protecting a feature, such as a docking mechanism, a hatch or other equipment on an exterior surface of a space vehicle, includes a plurality of rigid arcuate segments, each having opposite ends respectively pinioned at opposite sides of the feature at about the surface of the vehicle for rotational movement about an axis of rotation extending through the opposite ends thereof and through an arcuate path of rotation extending over the feature. The radial sizes of the segments are staggered such that, in a fully deployed position of the dome, in which adjacent segments are rotated apart from each other at a maximum relative angle therebetween, the segments combine to form an arcuate shield over the feature, and in a retracted position of the dome, in which adjacent segments are rotated together at a common angle relative to the surface of the vehicle, the segments are nested in radial alignment with each other.

A telecommunication satellite with geostationary orbit comprises an upper module, a lower module, and a lateral module, disposed in a storage configuration between the upper module and the lower module, and deployed to an operational configuration of the satellite in the orbit by a rotation in relation to an axis Z oriented towards the earth in the operational configuration. The lateral module comprises two substantially plane and mutually parallel main surfaces, termed dissipative surfaces, able to dissipate by radiation a quantity of heat generated by facilities of the satellite; the dissipative surfaces being, in the operational configuration, held in a manner substantially parallel to the plane of the orbit, making it possible to limit the solar flux received by the dissipative surfaces and to optimize the quantity of heat dissipated by the lateral module.

An apparatus having a composite air-based structure with a first carbon nanotube infused material and a second carbon nanotube infused material. The first and second carbon nanotube infused materials each having a range of carbon nanotube loading selected to provide different functionalities.

The electromagnetic field shielding apparatus of the present invention includes the electromagnetic field detection coil 21 for detecting an AC leakage electromagnetic field and the parallel resonance circuit 22-24 whose circuit constants are predetermined so that the resonance frequency matches the frequency of the electromotive force induced by the electromagnetic field detection coil 21. The resistor 24 of the parallel resonance circuit 22-24 consumes energy so that the strengths of the magnetic and electrical fields passing through the electromagnetic field detection coil 21 are suppressed.

A system is configured to shield an interior chamber of a structure. The system may include a power source, an outer shield assembly operatively connected to the power source and coupled to an outer wall of the structure, and an inner shield assembly surrounding the internal chamber. The outer shield assembly generates a magnetic field through and around the structure. The inner shield assembly deflects radiation particles away from the interior chamber and re-directs portions of the magnetic field around the interior chamber.

There is provided a radiation shield device for providing radiation protection to an area, such as a manned vehicle. The radiation shield device comprises a magnetic field generator, such as a solenoid, of superconductive material that provides a magnetic field around the area to shield the area from radiation. The solenoid preferably defines an axial length that is substantially smaller than a diameter of the solenoid. A thermal control system, comprising a limited amount of coolant or a refrigeration cycle, is included to control a temperature of the superconductive material during operation of the magnetic field generator. A magnetic shield device is also provided between the magnetic field generator and the area to be shielded from radiation to substantially shield the area from the magnetic field generated by the magnetic field generator.

A cryogenically cooled radiation shield device and method are provided to shield an area, such as the capsule of a space vehicle, from radiation. A cryogenically cooled radiation shield device may include at least one first coil comprised of a superconducting material extending about the area to be shielded. The cryogenically cooled radiation shield device also includes a first inner conduit extending about the area to be shielded from radiation. The at least one first coil is disposed within the first inner conduit. The cryogenically cooled radiation shield device also includes a first outer conduit extending about the area to be shielded from radiation. The first inner conduit is disposed within the first outer conduit. The cryogenically cooled radiation shield device also includes a first cryogen liquid disposed within the first inner conduit and a second cryogen liquid, different than the first cryogen liquid, disposed within the first outer conduit.

The present invention provides a charge monitor for satellites for monitoring build up of electric charge due to charge particle fluxes impinging on the satellite. In one aspect of the invention the charge monitor includes an electrically conducting housing including at least two compartments with each compartment including a dielectric slab contained therein. An electrically conducting electrode is embedded in each dielectric slab a pre-selected distance below a top surface of the dielectric slab, the housing being mountable on a satellite with the top surface of the dielectric slab facing outwardly into space away from the satellite whereby charged particles emitted from sources external to the satellite penetrate the dielectric slab resulting in charge accumulation in each electrically conducting electrode, each electrically conducting electrode being electrically isolated from all other electrically conducting electrodes in the electrically conducting housing. The monitor includes an electrical voltage detector for sensing the floating DC voltage developed on the electrically conducting electrode in each dielectric slab, due to the charge accumulation, and converting the DC voltage into an AC voltage representative of a charge buildup on each electrically conducting electrode.

This invention relates to technology used for creating an enhanced artificial magnetosphere or electromagnetic shield for use in both manned and unmanned spacecraft. The invention includes an Interference Generating Pattern (IGP) which is tuned to the high-frequency radiation of X-rays and gamma rays and a conformal magnetic field. This technology will reduce the exposure of astronauts or other space travelers, as well as radiation-sensitive equipment, to the environmental hazards present therein. The net result will be reduced radiation intensity in order to create a space radiation-free environment as to render space travel safe.

A spacecraft is described which uses a magnetic field source to generate a shield magnetic field to protect the spacecraft from energetic charged particles. The field may be perturbed to increase the effectiveness of the protection. Injection of material into the shield cavity to enhance the local plasma density may also be used.

The invention discloses a radiation-proof thermal control coating. A low-atomic-number material is utilized as a surface coating of the thermal control coating, a medium-atomic-number material is utilized as an intermediate coating of the thermal control coating, and a high-atomic-number material is utilized as a bottom coating of the thermal control coating. Compared with a ZnO coating, the coating disclosed by the invention has the advantages that the radiation protection capability is improved by over 10%, the solar absorption ratio alpha s of the coating is about 0.152 and the thermal emissivity epsilon is about 0.886 and is equivalent to that of a ZnO white paint under the same surface density.

There is provided a radiation shield device for providing radiation protection to an area, such as a manned vehicle. The radiation shield device comprises a magnetic field generator, such as a solenoid, of superconductive material that provides a magnetic field around the area to shield the area from radiation. The solenoid preferably defines an axial length that is substantially smaller than a diameter of the solenoid. A thermal control system, comprising a limited amount of coolant or a refrigeration cycle, is included to control a temperature of the superconductive material during operation of the magnetic field generator. A magnetic shield device is also provided between the magnetic field generator and the area to be shielded from radiation to substantially shield the area from the magnetic field generated by the magnetic field generator.

A method and device of shielding an area from radiation are provided. A radiation shield device may include first and second shells at least partially surrounding the area with the second shell being spaced apart from and further away from the area than the first shell. Both the first and second shells include a plurality of coils that are arranged in paired coil groupings and that encircle the area to be shielded from radiation. The coil groupings of the first shell may be configured to support current flow in an opposite direction to that in which the paired coil groupings of the second shell are configured to support current flow. As such, each coil grouping of the first shell has north and south poles that are correspondingly oppositely positioned from the north and south poles of the paired coil grouping of the second shell.

A shielding device (20) for optical and / or electronic apparatuses (16) is described, wherein said apparatuses may cooperate with incident electromagnetic radiation (X1, X2), in particular for space telescopes, the shielding device including:at least a filter (24, 26) provided for interacting with said incident electromagnetic radiation (X1, X2), for selectively filtering said radiation; anda support structure (22) for the filter.The support structure (22) is an inflatable structure, which is able to achieve an operating stand-by configuration, in which it is substantially folded together, and an active operating configuration, in which it extends along the longitudinal extension axis (ZZ), and is essentially completely unfolded. Furthermore, the filter (24, 26) includes a filter body, which is provided in order to be transversely positioned with respect to said longitudinal extension axis, when the support structure reaches its active operating configuration.