423 results about "Space radiation" patented technology

Provided herein are methods and systems for designing a radiation treatment for a subject using single arc dose painting. The methods and systems comprise an algorithm or a computer-readable product having the same, to plan the radiation treatment. The algorithm converts pairs of multiple leaf collimation (MLC) leaves to sets of leaf aperture sequences that form a shortest path single arc thereof where the pairs of MLC leaves each aligned to an intensity profile of densely-spaced radiation beams, and connects each single arc of leaf apertures to form a final treatment single arc. Also provided is a method for irradiating a tumor in a subject using single arc dose painting.

The invention discloses an FPGA (Field Programmable Gate Array)-based single event effect test system for a NAND FLASH device and belongs to the technical field of space radiation effect and reinforcement technology. The system comprises a communication interface module, a peripheral control platform, an upper computer, a tested device, an analog source, a power switch and an FPGA, wherein the FPGA comprises a cache module, a control module, an input / output reading and writing module, a sensor input / output module and a detection result module. The system can be used for testing the single event effect of a large-capacity NAND FLASH device to obtain single event effect characteristic parameters, and further the anti-single event effect capability of the tested device can be estimated through the analysis on the obtained parameters.

High Performance cooling systems for cooling a heat source is disclosed. The cooling systems can be air cooling system, liquid cooling system, or space radiation cooling system. Air cooling system includes at least high performance cold plate or cold plates, plenum, liquid pump, and liquid to air heat exchanger. Liquid cooling system includes at least high performance cold plate or cold plates, plenum, liquid pump, and liquid to liquid heat exchanger. Space radiation cooling system includes at least high performance cold plate or cold plates, plenum, liquid pump, and space radiator. Several coolant fluids are available and can be used as a primary system coolant depending on the application.

An antenna device is composed of a metal frame of an electronic device. The free space radiation efficiency and the handheld radiation efficiency are balanced by forming gaps in a bottom metal frame and side metal frames. In a free space scene, the longitudinal mode of the antenna is strong, and the radiation efficiency of the free space is good. When the electronic equipment is held by hand, thetransverse mode of the antenna is strong. The handheld radiation efficiency is good.

A logging system for measuring parameters of earth formation penetrated by a well borehole. Measurements made with the system are not adversely affected by varying pressure encountered a borehole environment. This is accomplished by the use of a main compensation element and a detector compensation element render source and detector geometry invariant to varying pressure. The system is particularly suited for nuclear LWD systems such as back scatter gamma ray density systems. The basic concepts of the system are, however, applicable to other types of nuclear measurement systems that comprise one or more radiation sources, and one or more axially spaced radiation detectors, where system response is a function of source-detector spacing. The basic concepts of the system are also applicable to other types of logging systems, such as electromagnetic and acoustic, where source (transmitter) and sensor (receiver) elements require invariant geometry in order to maximize accuracy of measurements.

The invention provides a vertical modular joint for space manipulator, relating to a modular joint for space manipulator. The invention aims to solve the problems with the prior space manipulator which is big in mass, size and power consumption but small in output torque of unit mass. A driving device of the invention is connected with a crown / Rolex gear series device, the crown / Rolex gear series device and a wave generator (2-3-3) is connected with a hollow transmission shaft (2-2-1), a rigid wheel (2-3-2) is connected with an inner ring support base (2-6-1) of a thin wall bearing two and the inner ring support base (2-6-1) of the thin wall bearing two is connected with an output flange (2-10). The invention has the advantages of high in integration and reliability, light in mass, small in size, low in power consumption, compact in structure, big in output torque of unit mass, high in position output precision and big in anti-bending rigidity, and is applicable to adapting to the environment of strong space radiation, high vacuum and big temperature difference, which has good maintainability and reliable operation performance.

The invention relates to a selective absorption emission composite material meeting requirements of solar heat collection and radiation refrigeration. The selective absorption emission composite material comprises a substrate, wherein a selective absorption layer and a selective emission layer are sequentially arranged on the substrate; the selective absorption layer has high absorption rate in a solar radiation spectral region with a wavelength of below 3 microns; the selective emission layer has high emission rate in a space radiation refrigeration spectral region with a wavelength of 8-13 microns. The selective absorption emission composite material has the high absorption rate in a spectral region with strong solar radiation in daytime, the low emission rate in medium-far infrared spectral regions, the high emission rate in a spectral region with space radiation refrigeration at night, and the low emission rate in other medium-far infrared spectral regions, thereby obtaining heat by absorbing solar radiation in daytime, obtaining cool energy through space radiation at night, reducing the radiation heat (cold) loss with ground and atmosphere during heat collection in daytime and refrigeration at night, and being capable of efficiently realizing two functions of solar heat collection and radiation refrigeration.

The invention discloses a low-orbit / middle-orbit double-layer satellite optical network structure system. Global coverage low-orbit satellite constellation designed on the basis of a coverage zone method and middle-orbit satellite constellation form a double-layer satellite optical network structure system. The system is connected with at least 76 satellites, wherein, a low-orbit satellite layer is provided with at least 7 orbits, and each orbit is connected with at least 10 satellites; a middle-orbit satellite layer is composed of an outer orbit and an inner orbit, wherein, the outer orbit is respectively connected with the satellites, and the inner orbit is respectively connected with the satellites. The calculation method is as follows: calculating the radius theta of a single satellite covering circle; calculating the halfangle psi of the covering zone; calculating delta B; calculating alpha'; calculating sin alpha; and calculating the distribution of P orbits on the equator. The structure is stable topological structure, the changes of inter-satellite links pitch angle and azimuth angle are smaller than the changes of the inter-satellite links pitch angle and the azimuth angle of the non-zero phase constellation, satellite switch is reduced, satellite-carried resources are saved, and management of the low-orbit satellite layer is effectively strengthened; the middle-orbit satellite constellation is least affected by space radiation, and the system life cycle is lengthened.

The invention discloses an FPGA (Field Programmable Gate Array)-based single event effect test method for a NAND FLASH device and belongs to the field of space radiation effect and reinforcement. The method comprises an upper computer, a 50MHz crystal oscillator, a program configuration port JTAG (Joint Test Action Group), an FPGA control module and an NANF FLASH test module. The test method comprises the following four working modes: 1) static mode; 2) dynamic mode; 3) dynamic reading / writing mode; and 4) dynamic reading / erasing / writing mode. With the method, single event effect test of the large-volume NAND FLASH memory can be realized. Under the condition of an experimental analog source, single event effect characteristic parameters can be efficiently obtained.

The embodiment of the invention relates to the field of communication, and discloses an antenna system and a mobile terminal. The antenna system is applied to the mobile terminal. The antenna system comprises a first feeding point which is arranged on a circuit board, a first millimeter wave array antenna which is electrically connected to the first feeding point, a second feeding point, a secondmillimeter wave array antenna which is electrically connected to the second feeding point, a third feeding point, a third millimeter wave array antenna which is electrically connected to the third feeding point, a fourth feeding point, and a fourth millimeter wave array antenna which is electrically connected to the fourth feeding point, wherein the beam of the first millimeter wave array antennacovers the space (X is more than 0); the beam of the second millimeter wave array antenna covers the space (X is less than 0); the beam of the third millimeter wave array antenna covers the space (Y is more than 0); the fourth millimeter wave array antenna covers the space (Y is less than 0). According to the system, the beam covering range in the surrounding space of the mobile terminal is expanded, so that the space radiation covering rate of the antenna is increased, and the capacity of receiving signals by the mobile terminal is improved.

The invention discloses radiation property testing method and system. The method comprises the following steps of: constructing a notebook computer placing method and a wireless data terminal testing model of the notebook computer; establishing a spheric coordinate system by using an antenna of the wireless data terminal as the origin point, and selecting a testing point in the spheric coordinate system; placing the testing model in a full dark wave chamber to enable the wireless data terminal to work in a data mode, utilizing the measuring antenna to collect the total radiation power in the testing point of the spheric coordinate system, and then obtaining the total radiation power of the wireless data terminal. By using the technical scheme, the invention can truly reflect the influence of the original element coupling of the notebook computer on the space radiation property of the wireless data terminal when the wireless data terminal of the notebook computer is in the data mode, and the system has high truth and is easy to use.

The invention relates to the technical field of electromagnetic radiation scanning and positioning, and aims to provide an electromagnetic radiation scanning and positioning method to replace the mechanical scanning technology, so that the electromagnetic radiation strength in each position of a circuit to be tested can be rapidly scanned and detected, a radiation source can be fixed, and continuous scanning and dynamic display can be realized. The method adopts an array type electromagnetic radiation detecting probe and the electronic switch technology, achieves unique spectrum and space scanning functions, and realizes the effects of scanning a selected area in a frequency range, and measuring the radiation circumstance of the whole frequency band in each special position of a tested object so as to obtain complete electromagnetic field information of the tested object. Data acquired by a scanning antenna under the control of electromagnetic scanning test software is subjected to fitting processing, so as to draw an electromagnetic radiation frequency spectrum and a spatial radiation cloud picture. The invention provides the method and equipment for the field of electromagnetic radiation measure, so as to quickly perform two-dimensional electromagnetic radiation scanning and positioning in a real-time manner.

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 and method for determining the density and other properties of a formation surrounding a borehole using a high voltage x-ray generator. One embodiment comprises a stable compact x-ray generator capable of providing radiation with energy of 260 keV and higher while operating at temperatures equal to or greater than 125° C. In another embodiment, radiation is passed from an x-ray generator into the formation; reflected radiation is detected by a short spaced radiation detector and a long spaced radiation detector. The output of these detectors is then used to determine the density of the formation. In one embodiment, a reference radiation detector monitors a filtered radiation signal. The output of this detector is used to control at least one of the acceleration voltage and beam current of the x-ray generator.

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.

The fault-tolerant or self-correcting computer system is disclosed. The computer system that is provided with various sets of protections against failures that may be caused by space radiation, for example. Improved reliability of the system is achieved by scrubbing of the components on a regular schedule, rather than waiting for an error to be detected. Thus, errors that may go undetected for an extended period are not allowed to propagate and further damage the system. Three or more processors are provided to operate in parallel, and a controller is provided to receive signals from the processors and, using a voting logic, determines a majority signal value. In this manner, the controller can detect an error when a signal from one of the processors differs from the majority signal. The system is also provided with a scrubbing module for resynchronizing the processors after a predetermined milestone has been reached. The milestone may be a predetermined time interval or any other event that may be defined by a user.

The embodiments of the invention relate to the communication field and disclose an antenna system and a mobile terminal. The antenna system is applied to the mobile terminal. The antenna system comprises a first feeding point arranged on a circuit board, a first millimeter wave array antenna electrically connected to the first feeding point, a second feeding point, a second millimeter wave array antenna electrically connected to the second feeding point, a third feeding point, a third millimeter wave array antenna electrically connected to the third feeding point, a fourth feeding point and afourth millimeter wave array antenna electrically connected to the fourth feeding point. The wave beam of the first millimeter wave array antenna covers a space where Z is greater than 0. The wave beam of the second millimeter wave array antenna covers a space where the Z is less than 0. The wave beam of the third millimeter wave array antenna covers a space where Y is greater than 0. The wave beam of the fourth millimeter wave array antenna covers a space where the Y is less than 0. In the invention, the wave beam covering range of the antenna system to the spaces surrounding the mobile terminal is increased so that the space radiation covering rate of the antenna system is improved and a capability for the mobile terminal to receive signals is enhanced.

The invention provides a method for a simulation test about the comprehensive space radiation effect of a surface function material for a spacecraft, which belongs to the field of space environment engineering and can be applied to evaluation on the space environment effect of the surface function material for the spacecraft. When the spacecraft is in an on-orbit working, most surface function materials are directly exposed in the on-orbit environment, and the influence of the radiation environment is more severe. The surface function materials are irradiated by electrons, protons, alpha particles and heavy ions with wider energy and flux, and the radiation of all the particles can lead the performances of the surface function materials to be deteriorated. In a long-life design of a satellite, the capability of bearing the influence of the environment with comprehensive space radiation needs to be inspected. The method provided by the invention has an important significance in evaluation on the ground simulation test about the orbit radiation effect of the surface function material for the spacecraft.

The invention discloses a wireless router control method and device and a wireless router applying the same. Data flow between the wireless router and a terminal is monitored in real time, when the real-time data flow is smaller than a preset flow lower limiting value, real-time transmitting power of the wireless router is reduced, resource consumption of the wireless router is reduced on the premise that the signal transmitting quality is not affected, and space radiation quantity is reduced.

The invention discloses a space electromagnetic intensity distribution analysis method, which comprises the following steps of: 1, determining an observation and test space region according to space electromagnetic intensity analysis requirements, and meshing the region, wherein a test point in subsequent steps can be selected from mesh regions; 2, calculating a relative distance and a relative direction between the point and each piece of equipment according to the position of the test point; 3, calculating a time-domain signal of the test point according to a formula for a composite signal by utilizing calculation results obtained by the step 2; 4, performing Fourier transform on the time-domain composite signal obtained by the step 3 to obtain the frequency-domain energy distribution of the space composite signal at the test point; and 5, repeating the steps 2 to 4 for the whole observation and test region to obtain the composite electromagnetic radiation intensity data of a space radiation source of the observation and test region. According to the method, the distribution of the space electromagnetic intensity can be analyzed more accurately and efficiently.

The fault-tolerant or self-correcting computer system is disclosed. The computer system that is provided with various sets of protections against failures that may be caused by space radiation, for example. Improved reliability of the system is achieved by scrubbing of the components on a regular schedule, rather than waiting for an error to be detected. Thus, errors that may go undetected for an extended period are not allowed to propagate and further damage the system. Three or more processors are provided to operate in parallel, and a controller is provided to receive signals from the processors and, using a voting logic, determines a majority signal value. In this manner, the controller can detect an error when a signal from one of the processors differs from the majority signal. The system is also provided with a scrubbing module for resynchronizing the processors after a predetermined milestone has been reached. The milestone may be a predetermined time interval or any other event that may be defined by a user.

A plasma processing apparatus includes: a processing container which defines a processing space; a microwave generator; a dielectric having an opposing surface which faces the processing space; a slot plate formed with a plurality of slots; and a heating member provided within the slot plate. The slot plate is provided on a surface of the dielectric at an opposite side to the opposing surface to radiate microwaves for plasma excitation to the processing space through the dielectric based on the microwaves generated by the microwave generator.

The invention discloses a thermal control film with controllable emissivity. The thermal control film comprises a substrate, a high-reflectivity layer with reflectivity of greater than or equal to 0.8, a high-emissivity layer with infrared emissivity of 0.3-0.7 and a protection layer, wherein the high-reflectivity layer, the high-emissivity layer and the protection layer are sequentially arranged on the substrate surface from inside to outside. The thermal control material disclosed by the invention can realize control of different absorption / emission ratios as well as lightweight design, and is applicable to a new-generation controllable-emissivity thermal control coating for spacecraft with the characteristics of light weight, small miniaturization and whole-spacecraft isothermality; and moreover, the thermal control film has the advantages of simple structure, low cost, convenience in preparation and high stability of space environment, meets different needs for emissivity at different parts of the spacecraft surface and satisfies the requirement for improving the space radiation resistance of the thermal control material.

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.

The invention discloses a dynamic multi-frequency multi-beam spatial arbitrary scanning reflection array comprising a feed source horn, a stacked multilayer reflective array, and a control excitation module loaded on the array. A reflective array unit can be constructed flexibly at a reconfigurable surface loaded at each layer of array to meet work requirements at different frequency bands in different space radiation directions, thereby realizing multi-band work and arbitrary-direction radiation of beams. On the basis of the multi-layer structure, multi-frequency work is realized and spatial beam directions in respective operating frequencies can be designed respectively to realize a frequency-division and beam-division effect. The reflective array units in the array can be regulated dynamically and dynamic scanning of reflected beams in any spatial direction can be realized.

The invention belongs to the technical field of renewable energy and air conditioners and discloses a heat collection-radiation device and a refrigeration system thereof. The device comprises a support and a heat collection-radiation unit, the heat collection-radiation unit comprises a heat collection part and a radiation heat part, the heat collection part comprises a reflection mirror and a heatcollection pipe, and the reflection mirror reflects sunlight heat and accumulates the sunlight heat on the heat collection pipe for heating; the radiation heat part comprises a cooling pipe and selective radiation thin film, the selective radiation thin film transmits an electromagnetic wave, the electromagnetic wave penetrates through an atmospheric window, heat is radiated to the outer space, and the temperature in the cooling pipe is lowered. The invention further discloses the refrigeration system. The system comprises the heat collection-radiation device, an absorption-type refrigerationdevice and a cold water tank, the absorption-type refrigeration device and the cold water tank are connected with the two ends of the heat collection-radiation device respectively, during daytime, after heating of the heat collection-radiation device, the refrigeration device is driven to conduct refrigeration, and at night, the heat collection-radiation device is used for radiating heat to the outer space for refrigeration. By means of the heat collection-radiation device, the defects are overcome that sunlight cannot be used at night, and the refrigeration effect through space radiation during daytime is poor. The refrigeration process of near-zero energy consumption is achieved.

The invention relates to composite sol and a method for preparing a material for an anti-radiation space suit by use of the same. The silicon oxide-aluminum oxide composite sol comprises silicon oxide sol and aluminum oxide sol; the silicon oxide sol comprises tetraethoxysilane, gamma-(methacryloxy)propyltrimethoxylsilane, absolute ethyl alcohol, hydrochloric acid and N,N-dimethylformamide; and the aluminum oxide sol comprises aluminum isopropoxide, distilled water and nitric acid. Meanwhile, the invention also relates to a material for a space suit prepared by use of the silicon oxide-aluminum oxide composite sol and a preparation method. Through the composite sol provided by the invention, a space composite structure is formed between silicon oxide and aluminum oxide to guarantee the stability, density and flexibility of a membrane layer; after irradiation in a space radiation environment, the generation of cracks and micropores is avoided on the surface of the aluminum oxide-silicon oxide composite membrane; and the material for an anti-radiation space suit can bear long-time radiation in the space radiation environment.

The invention relates to a GaAs solar battery life predicting method under space radiation environment, belonging to the space environment engineering field and spacecraft solar battery array design field; the relation of non-ionizing energy loss and incident electron energy of electrons in the solar battery material is analog-commutated by utilizing a Geant4 software radiation transportation tool box, so as to obtain the relation curve of battery damage coefficient and displacement damage dose; particle flux energy spectrum of a GEO orbit and attenuation spectrum after penetrating through a quartz glass cover sheet are analog-commutated; a life predicting model of the solar battery is built under the GEO orbit radiation environment by utilizing the solar battery damage coefficient obtained by a ground simulation test and the displacement damage dose of a space orbit, obtained by analog commutation. In the invention, by utilizing the displacement damage dose method, the effect of different space radiation environment to the attenuation of the battery performance parameter can b predicted, so as to predict the in-orbit service life of the solar battery, determine the characteristic curve and save the test expense and time.

The invention discloses a radio energy transmission system in an enclosed space, and a control method for the radio energy transmission system. The system comprises the enclosed space, a radio energy transmitter, and at least one radio energy receiver. The boundary of the enclosed space is made of metal or a material which can achieve the total reflection of microwaves in a certain frequency range. The radio energy transmitter is excited in the enclosed space to form microwave electromagnetic standing waves, searches and determines an optimal working frequency point through the frequency scanning in a certain range. The radio energy receivers are distributed at the antinodes of the microwave electromagnetic standing waves and parts nearby the antinodes, captures radio energy from the electromagnetic standing waves, and converts the radio energy into DC electric energy for charging electronic equipment. According to the scheme of the invention, the radio energy transmission system avoids space radiation loss in an electromagnetic wave transmission process, also avoids disturbance on region external electronic equipment from electromagnetic waves and the damages to a human body, and can make the most of a three-dimensional space to carry out the high-efficiency radio charging of a plurality of pieces of electronic equipment.