76 results about "Radiation pressure" patented technology

Provided herein are methods and system for enabling a navigation receiver to generate receiver specific satellite orbital models based on relatively small sets of parameters obtained from a server. In an embodiment, a set of parameters for a satellite includes a force parameter (e.g., solar radiation pressure), initial condition parameters (e.g., satellite position and velocity at a time instance) and time correction coefficients, which the receiver uses in a numerical integration to predict the position of the satellite. The set of parameters needed for the integration is small compared to current methods which require transmission of a complete set of ephemeris and other parameters for each satellite. Since the set of parameters is relatively small, it requires less communication resources to transmit compared to current methods. Further, the integration based on the small set of parameters enables the receiver to predict satellite orbits with low computational load.

In a radiation-pressure elastography technique for transmitting a ultrasound focused beam into a test object body and diagnosing the hardness thereof, it is required to consider high sensitivity and safety.In the present invention, the focused beam is transmitted to two positions as a means for displacing a tissue and exciting a shear wave. In addition, time control is performed in such a manner that a transmit beam serves as a burst-chirp signal, and ultrasound waves are transmitted and received while sweeping a transmit frequency. On this occasion, when the distance between the two focused points and the transmit frequency become integral multiple of the wavelength, two waves interfere with each other, thereby obtaining a large amplitude. Furthermore, when the transmit frequency becomes equal to a resonance frequency peculiar to the tissue, the amplitude also becomes larger. Accordingly, a small intensity of transmit waveform enhances sensitivity. In addition, transmission using the burst-chirp signal facilitates widening of a bandwidth of the transmit frequency, enabling usage of a frequency highly sensitive for a target measurement site. Optional number of focused points and arbitrary positions thereof allow a wide area to be covered.

A nano-optomechanical transducer provides ultrabroadband coherent optomechanical transduction based on Mach-wave emission that uses enhanced photon-phonon coupling efficiencies by low impedance effective phononic medium, both electrostriction and radiation pressure to boost and tailor optomechanical forces, and highly dispersive electromagnetic modes that amplify both electrostriction and radiation pressure. The optomechanical transducer provides a large operating bandwidth and high efficiency while simultaneously having a small size and minimal power consumption, enabling a host of transformative phonon and signal processing capabilities. These capabilities include optomechanical transduction via pulsed phonon emission and up-conversion, broadband stimulated phonon emission and amplification, picosecond pulsed phonon lasers, broadband phononic modulators, and ultrahigh bandwidth true time delay and signal processing technologies.

This invention relates to a method and device for generating cold atomic beam. Said method includes heating hot atom source in vacuum chamber to form atomic saturated vapor pressure atmosphere, cooling hot atom by three-D MOT to below 200uk and trapped to form cold atomic cloud, by the quarter wave plate reflection mirror in MOT the laser radiation pressure being unbalanced to make cold atom emitting along said direction, four tape arranged straight line set with contrary current direction is set in atom beam emission direction, which makes the atom emitted to forward to obtain cold atom beam with low speed, large flux and small transverse speed, laser beam vertical with atom beam set in the direction of cold atom emitting for atom beam state preparation to realize state concordant emitted cold atom beam.

A system for orienting particles in a microfluidic system includes one or more radiation pressure sources arranged to expose particles to radiation pressure to cause the particles to adopt a particular orientation in the fluid. A system for sorting particles in a microfluidic system includes a detection stage arranged to detect at least one difference or discriminate between particles in the fluid flow past the detection stage, and one or more radiation pressure sources past which the particles move sequentially and a controller arranged to switch radiation energy to cause a change in direction of movement of selected particles in the fluid flow to sort the particles. The particles may be biological particles such as spermatazoa. The radiation pressure may be optical pressure and may be from one or more waveguides which may extend across a channel of the microfluidic system.

The invention relates to a separation free bioanalytical assay method for measuring an analyte from a biological fluid or suspension comprising of microparticles as a bioaffinity binding solid phase, a biospecific secondary reagent labelled with a two-photon fluorescent dipyrrometheneboron difluoride dye, focusing the laser into the reaction suspension, measuring two-photon excited fluorescence from single microparticles when they randomly float or are guided by the radiation pressure of the excitation laser through the focal volume of the laser beam using a two-photon fluorescent dipyrrometheneboron difluoride dye. The dye has the structure (II): Either at least one of groups R1, R2, R3, R4, R5, R6 and R7 is a substituted or unsubstituted phenyl, thienyl, pyrrolyl, furanyl, oxazolyl, isoxazolyl oxadiazolyl, imidazolyl, benzoxazolyl, benzothiazolyl, benzimidazolyl, benzofuranyl, indolyl, conjugated ethenyl, dienyl or trienyl group, and at least one of the groups R1, R2, R3, R4, R5, R6 or R7 is substituted to yield a chemically reactive group that can be used for selective covalent linkage to other molecules, and at least one of the groups R1, R2, R3, R4, R5, R6 or R7 is substituted to yield a water-solubilizing group, and the remaining groups of R1, R2, R3, R4, R5, R6 and R7 are each independently selected from the group consisting of hydrogen, halogen, alkyl, cyano, carboxy, each of which can optionally be substituted; or groups R1, R2, R3, R5, R6 and R7 are substituted or unsubstituted alkyl groups, R4 is a hydrogen or a substituted or unsubstituted alkyl, and at least one of the groups R1, R2, R3, R4, R5, R6 or R7 is substituted to yield a chemically reactive group that can be used for selective covalent linkage to other molecules; and at least one of the groups R1, R2, R3, R4, R5, R6 or R7 is su

A GNSS ultra-tight coupling (UTC) receiver architecture applicable to space borne orbit platforms is described. A receiver in accordance with this architecture retains the rotational motion sensors typically found in an inertial measurement unit (IMU) of a conventional UTC receiver, but replaces the IMU accelerometer sensors with precise orbital dynamics models to predict the translational motion of the platform center of gravity (CG). Drag and radiation pressure may be modeled as well. The various models can be implemented in software. The IMU rotational sensors are retained for compensation of the GNSS antenna lever arm effect due to platform rotation.

Fuel less ACS for solar sails, using furl- and unfurl able ballast-sail-foil-segments for simultaneously displacement of center of mass and center of solar radiation pressure into opposite directions to each other.Solar-Sail-Launch-System for direct launch of the System-Sail including already docked in daughter units and payload in the sailcraft's central docking station.Unlike todays launch able solar sail designs the System-Sail features ample solar cell arrays and additional SEP-thruster-units for steering and propulsion, while the solar sail rather serves for longtime fuel less attitude controls and station keeping.The SEP-Sailcraft may also serve as a carrier-ship for daughter-units in asteroid exploration missions and is able to deliver prospector landers back to LEO with furled in foils.

An east-west position keeping and angular momentum unloading combined control method includes: first, analyzing effects of earth non-spherical perturbation, solar radiation pressure perturbation and the like on a satellite orbit and received by a static orbit satellite, meanwhile estimating the effect of angular momentum unloading on the satellite orbit, then comparing effects of the earth non-spherical perturbation and the angular momentum unloading on the flat longitude drift rate to determine the unloading moment, considering the effect on the eccentricity ratio, and eliminating the possibility of multiple solutions at the unloading moment to determine the optimum unloading moment. The method is favorable for east west position keeping and enables the eccentricity rate to be small as much as possible. The method is applicable to the static orbit satellite needing a thruster to unload the angular momentum in a centralizing mode. By means of the method, the east west position keeping times can be reduced, a propellant is saved, the satellite task time is increased, and the service life of the satellite is prolonged.

Fuel less ACS for solar sails, using furl- and unfurl able ballast-sail-foil-segments for simultaneously displacement of center of mass and center of solar radiation pressure into opposite directions to each other.Solar-Sail-Launch-System for direct launch of the System-Sail including already docked in daughter units and payload in the sailcraft's central docking station.Unlike todays launch able solar sail designs the System-Sail features ample solar cell arrays and additional SEP-thruster-units for steering and propulsion, while the solar sail rather serves for longtime fuel less attitude controls and station keeping.The SEP-Sailcraft may also serve as a carrier-ship for daughter-units in asteroid exploration missions and is able to deliver prospector landers back to LEO with furled in foils.

A method and device for generating power using radiation pressure is described. The device comprises a turbine generator in which the turbine comprises optical resonant cavities or waveguides. The turbine rotates as a result of the force applied to the resonant cavities or waveguides by the radiation pressure of the circulating laser beam. Because of the amplification of the power of the input laser beam through resonant enhancement, the Photon Turbine Generator (PTG) has the potential for overunity efficiency (i.e., power output exceeding power input), lasting until the laser pumping mechanism or gain medium degrades or expires. The PTG may be built on either a macroscopic or microscopic scale. The PTG can provide clean, efficient, long-lasting power for diverse applications (e.g., energy, transportation, and electronic devices), while also supplying electricity to meet its own operational needs (e.g., laser pump power).

The invention provides a high-surface-mass ratio spacecraft orbit dynamics analysis method and belongs to the field of spacecraft orbit dynamics. The high-surface-mass ratio spacecraft orbit dynamics analysis method comprises the following steps: respectively modeling solar radiation pressure, atmospheric resistance, earth shadow and other perturbative forces; then establishing a dynamic model of a whole system based on a Hamilton's principle. According to the high-surface-mass ratio spacecraft orbit dynamics analysis method provided by the invention, the effects of the solar radiation pressure and the atmospheric resistance on a high-surface-mass ratio spacecraft are respectively analyzed, and meanwhile, an equilibrium orbit under the combined action of the perturbative forces is also obtained via analysis. Orbit elements are not needed to suffer from average processing; therefore, the precision is higher, and the understanding is easy. The high-surface-mass ratio spacecraft orbit dynamics analysis method provided by the invention can be used for not only high-surface-mass ratio spacecraft orbit analysis around the ground, but also high-surface-mass ratio spacecraft orbit analysis around other planets, so that the application scope is wide.

The present invention provides a method for the attitude control of satellites in elliptic orbits or satellites initially placed in circular orbits perturbed to elliptic orbits due to environmental disturbances. The method relies on the application of solar radiation pressure to provide the desired torque for the satellite attitude control. The satellite is equipped with two-oppositely placed light-weight solar panels extending away from the satellite along a predetermined direction (satellite body fixed Y-axis). By rotating one of these solar panels or both of them through desired angles about their axis using the respective driver motors as per the simple open-loop control law, the torque about the satellite axis is developed to achieve the desired attitude performance. The open-loop control law is derived using an analytical approach to neutralize the excitation caused by eccentricity and it is implemented via analog logic based on the information of sun angle and satellite position provided by the sensors. The present invention significantly improves the performance of the satellite by a factor of more than 20 times approximately in general and it only requires the rotation of the solar panels by fraction of a degree for particular system parameters. Thus, the semi-passive nature of the present invention makes it attractive for future space applications.

The invention discloses a method for autonomous ephemeris prediction of a GPS receiver. The method comprises the following steps: step one, computing a location speed vector of a satellite in ephemeris effective time according to input broadcast ephemeris as an observation value of precise orbital determination; step two, performing precise orbital determination according to the observation value,computing by utilizing an orbital determination program to obtain a precise location speed vector at initial moment of an orbital determination segmental arc, and a satellite area-mass ratio in a solar radiation pressure model parameter; step three, performing orbital forecast, taking the precise location speed at the initial moment of the orbital determination segmental arc as the starting, taking the satellite area-mass ratio as the satellite equivalent area-mass ratio parameter to perform orbit extrapolation, and extrapolating to turn-on moment; and step four, fitting the location speed quantity at the turn-on moment as the broadcast ephemeris to give out the forecast ephemeris, and directly applying the forecast ephemeris to positioning resolution of a receiver location. The first positioning duration of the receiver not in warm start is greatly shortened, a requirement on a chip storage space is reduced, and the cost control of the chip is convenient.

The invention relates to a method and a device for carrying out charging and discharging upon storage batteries by using ultrasonic waves. With the method and device, ultrasonic waves with certain intensity are generated by using an ultrasonic generator; a prepared storage battery is placed in an ultrasonic wave transmission path; with high-frequency vibration and radiation pressure of the ultrasonic waves, effective stirring is formed in the electrolyte in the storage battery; and with the stirring of the electrolyte, reaction molecule movements therein are driven, such that storage battery oxidation-reduction reaction is promoted. With the method and the device provided by the invention, storage battery oxidation-reduction reaction intensity can be substantially improved, a complete reaction status can be reached more rapidly, and oxidation-reduction reactions at different positions on the surface of the solid substrate of the storage battery are more consistent. The device has the advantages of simple structure and low cost. Core elements comprise only an ultrasonic resonator element and a corresponding resonant circuit. The operation is simple, and automaton can easily be realized. The method and the device can be applied for storage batteries with water-based electrolyte systems, such as lead-acid batteries.

The present invention relates to an anti-interference filtering method of a drag-free satellite attitude channel. Aiming at the drag-free satellite attitude channel of multi-source interference consisting of an atmospheric drag torque, an solar radiation pressure torque, a gravity gradient torque, inertia uncertainty, actuating mechanism noise, measurement noise, model uncertainty and the like, the method comprises: firstly, building a mathematical model including the drag-free satellite attitude channel of multi-source interference; secondly, building a mathematical model of an external environment interference torque; thirdly, designing an anti-interference filter aiming at the drag-free satellite attitude channel; and finally, designing an optimal controller to perform feedback control. The anti-interference filtering method of a drag-free satellite attitude channel is high in anti-interference capability, is high in control precision and the like, and is able to be used in the drag-free satellite attitude channel.

The purpose of the present invention is to measure the diameter of particles by placing a detector on the optical axis of a beam radiated from a light source, and detecting the forward-scattered light generated by particles contained in a particle swarm. Furthermore, the purpose of the present invention is the unique, accurate measurement of the diameter of particles while reducing as much as possible the amount of light from the light source that is directly incident without being scattered by the particles. [Solution] The present invention is basically based on the knowledge that particle diameter can be uniquely measured by measuring the maximum forward-scattered light intensity. In order to do so, the radiation pressure of a focused laser beam is used to induce particles contained in the particle swarm to the beam focus position, and the amount of directly incident light which has not be scattered by the particles is reduced as much as possible. The particle diameter measurement device and the particle diameter measurement method use the optical radiation pressure from the incident light to force the particles to move to the beam focus position, and detect the forward-scattered light.

A GNSS ultra-tight coupling (UTC) receiver architecture applicable to space borne orbit platforms is described. A receiver in accordance with this architecture retains the rotational motion sensors typically found in an inertial measurement unit (IMU) of a conventional UTC receiver, but replaces the IMU accelerometer sensors with precise orbital dynamics models to predict the translational motion of the platform center of gravity (CG). Drag and radiation pressure may be modeled as well. The various models can be implemented in software. The IMU rotational sensors are retained for compensation of the GNSS antenna lever arm effect due to platform rotation.

The invention provides a medium orbit sateLLite deorbit method based on soLar radiation pressure. In consideration of the situation that no definite waste sateLLite treatment principLe is estabLishedin the current medium orbit region and the deveLopment prospect of a soLar saiL technoLogy, a disturbing force modeL of waste sateLLites and a Long-term evoLvement modeL of the waste sateLLites are estabLished, Long-term evoLvement conditions with or without soLar saiLs are anaLyzed, the feasibiLity of the condition that the soLar saiLs enter the atmosphere again is verified, infLuences of initiaLorbit parameters on Long-term evoLvement of the waste sateLLites are researched, and references are provided for seLecting appropriate initiaL orbit parameters for entering the atmosphere again.

The invention provides a characteristic analysis method for a capacitive micromachined ultrasonic transducer (CMUT), which aims at performing effective analysis on displacement, acceleration, sound pressure characteristics and receiving characteristics under the circumstances of different emission signals. The characteristic analysis method for the CMUT comprises the step: firstly establishing an infinitesimal state equation SIMULINK model of the CMUT in an emission state and an infinitesimal state equation SIMULINK model of the CMUT in a receiving state, wherein the infinitesimal state equation SIMULINK model of the CMUT in the emission state comprises a CMUT vibration system module and an electrostatic force module, and the infinitesimal state equation SIMULINK model of the CMUT in the receiving state comprises a CMUT vibration system module, an electrostatic force module and a current output module; the electrostatic force module calculates an electrostatic force Fe by determining parameters, such as driving voltage V, an initial gap g0 between an upper electrode and a lower electrode, and displacement; by determining parameters, such as the electrostatic force Fe, equivalent mass, equivalent spring constant K and equivalent impedance R, the CMUT vibration system module establishes a lumped parameter system, calculates vibration displacement and vibration velocity, and outputs the displacement as feedback quantity to the electrostatic force module, thereby multiplying vibration velocity and radiation resistance to calculate sound radiation pressure.

The invention discloses an active noise attenuation system and a sound absorption method on the basis of minimum quadratic sum of reflecting acoustic pressure, and relates to the technology of sound attenuation. The method comprises the following steps that: reflecting acoustic pressure is detected through a sound sensor; piezoelectric ceramic chips are adhered to a panel; certain voltage is applied to the piezoelectric ceramic chips, and due to piezoelectric effects of piezoelectric ceramics, the panel is vibrated; the detected reflecting acoustic pressure and sound radiation pressure caused by panel vibration are expressed as total reflecting acoustic pressure, and the total reflecting acoustic pressure is input into a control filter for filtering; the filtered signal is input into a processor module for calculation; the voltage and frequency applied to the piezoelectric ceramic chips are calculated under the condition of the minimum quadratic sum of the total reflecting acoustic pressure; and the calculated voltage and frequency are sent to the piezoelectric ceramic chips again through a frequency converter. By the active noise attenuation system and the sound absorption method, a good active sound adsorption effect can be achieved.

The present invention relates to lactide preparing process, and is especially microwave radiation and pressure reducing catalysis process of preparing lactide. The process includes the following steps: decompression dewatering water solution of lactic acid material or using lactic acid material directly; adding catalyst and decompressing microwave polymerizing to obtain lactic acid oligomer; decompressing microwave cracking to obtain crude product; and purification to obtain pure lactide. The preparation process has short period within 2 hr, no need of nitrogen protection, high lactide yield, low power consumption, and low production cost.

The invention discloses a method for calculating the solar radiation pressure moment of a navigation GEO satellite. The method comprises the following steps of (1) acquiring an input bar, (2) calculating the radiation pressure moment to a satellite body of the sun, (3) calculating the radiation pressure moment to a solar wing of the sun, (4) calculating the radiation pressure moment to an S / L antenna of the sun, (5) conducting Fourier fitting on the radiation pressure moment to the satellite body, the radiation pressure moment to the solar wing and the radiation pressure moment to the antenna to obtain Fourier fitting coefficients of solar radiation pressure moment. The Fourier fitting coefficients of the solar radiation pressure moment are used for conducting overall satellite design, according to the shape of the navigation GEO satellite and the optical property of surface materials, the sheltering factors and the like between parts are considered, the angle of the S / L antenna tilting northwards is considered, meanwhile, a model is established according to the meshed S / L antenna, the solar radiation pressure moment of the navigation GEP satellite is calculated, and the precision of the calculating result of the solar navigation pressure moment of the navigation GEO satellite is guaranteed.

The invention discloses an ecological restoration method for treating a eutrophic water body by utilizing Nuphar sinensis, which is particularly applied to ecological restoration of city park lakes with landscape requirement on a water area and large-scale eutrophicated shallow water lake lakeside zones. The method comprises the following steps of: adopting the Nuphar sinensis as a pioneer species for restoring aquatic vegetation, adopting a subterraneous stem propagation body or seedling vegetative propagation manner in shallow water areas and / or river bank zones, and field planting the Nuphar sinensis in a patchiness distribution manner; in the next year, utilizing a 'centripetal radiation pressure seedling method' to realize rapid expansion of plant groupings so as to form an annular plant grouping; and planting submerged plants in a restoration area, so that the plant cover degree reaches more than 60 percent finally. Compared with a traditional plant material restoration technology, the method has the characteristics of excellent water quality purification effect, simple management and high economic value, has the advantages of ecological features, sightseeing performance and economical efficiency, and has wide popularization and application prospect.

Provided herein are methods and system for enabling a navigation receiver to generate receiver specific satellite orbital models based on relatively small sets of parameters obtained from a server. In an embodiment, a set of parameters for a satellite includes a force parameter (e.g., solar radiation pressure), initial condition parameters (e.g., satellite position and velocity at a time instance) and time correction coefficients, which the receiver uses in a numerical integration to predict the position of the satellite. The set of parameters needed for the integration is small compared to current methods which require transmission of a complete set of ephemeris and other parameters for each satellite. Since the set of parameters is relatively small, it requires less communication resources to transmit compared to current methods. Further, the integration based on the small set of parameters enables the receiver to predict satellite orbits with low computational load.

The invention discloses a steamed bread flavor substance detection method. The method comprises weighing a certain amount of a steamed bread sample, carrying out ultrasonic treatment, putting the steamed bread sample into a sample bottle, inserting an extraction head into the sample bottle, pushing out the extraction fiber head, carrying out headspace part extraction, then inserting the extraction head into a silica gel insulation cushion at a gas chromatography sample introduction port of a gas chromatography / mass spectrometer, carrying out analysis through a splitless mode for 4-5min and analyzing the processed data to determine volatile substance components of a steamed bread sample. A steamed bread subjected to ultrasonic treatment is subjected to solid phase extraction and then flavor substances in the sample is subjected to gas chromatography / mass spectrometry analysis. The sample is subjected to ultrasonic pretreatment before extraction so that supersonic wave radiation pressure intensity improves steamed bread sample substance molecule motion frequency and rate and extraction efficiency is improved. The method has the characteristics of operation simpleness and fastness, good reappearance and less cost and provides a reference method for steamed bread flavor substance detection.

An energy conversion system for extracting energy from the zero-point field of space is disclosed and described. This system includes a primary transducer operatively associated with a secondary transducer. The primary transducer can include a substrate having an arm rotatably coupled to the substrate, while the substrate can be confined to move along a linear oscillatory path. The secondary transducer converts kinetic energy of the substrate and arm to usable energy. The multi-mode motion of the substrate and arm combination is sufficient to impart a momentum influx to rotational motion of the arm.The momentum influx can then be converted to usable energy such as mechanical, electrical and / or thermal energy. As described in more detail herein, the momentum influx appears to be a result of radiation pressure due to scattering in part of the electro-magnetic momentum-energy contained within the zero-point field of space opposite to centripetal acceleration of the arm.