160results about How to "High cost-effective" patented technology

An optical device for imaging is disclosed having at least one micro lens field with at least two micro lenses and one image sensor with at least two image detector matrices. The at least two image detector matrices each include a plurality of image detectors and there is an allocation between the image detector matrices and the micro lenses, so that each micro lens together with an image detector matrix forms an optical channel. The center points of the image detector matrices are shifted laterally by different distances, with respect to centroids, projected onto the image detector matrices, of the micro lens apertures of the associated optical channels, so that the optical channels have different partially overlapping detection areas and so that an overlapping area of the detection areas of two channels is imaged onto the image detector matrices offset with respect to an image detector raster of the image detector matrices. Further, an image processing device and a method for optical imaging are described.

Described are computer-based methods and apparatuses, including computer program products, for scalable seamless digital video stream splicing. Data packets in a first video stream of bits are rearranged. Placeholder packets are created in a second video stream of bits. The first video stream of bits and the second video stream of bits are combined to generate a spliced stream by inserting data packets from the first video stream of bits into the placeholder packets in the second video stream of bits.

A light source apparatus including light spectrum-converting materials that emit light primarily over large portions of the 360 nm-480 nm and the 590-860 nm spectral range is provided. This apparatus provides a cooled, high-luminance, high-efficiency light source that can provide a broader spectrum of light within these spectral ranges than has been cost-practical by using many different dominant peak emission LEDs. Up to 15% of the output radiant power may be in the spectral range 350-480 nm in one embodiment of this device, unless a specific separate source and lamp operating mode is provided for the violet and UV. Control methods for light exposure dose based on monitoring and controlling reflected or backscattered light from the illuminated surface and new heat management methods are also provided. This flexible or rigid light source may be designed into a wide range of sizes or shapes that can be adjusted to fit over or around portions of the bodies of humans or animals being treated, or mounted in such a way as to provide the special spectrum light to other materials or biological processes. This new light source can be designed to provide a cost-effective therapeutic light source for photodynamic therapy, intense pulsed light, for low light level therapy, diagnostics, medical and other biological applications as well as certain non-organic applications.

The design of a compact, high-efficiency, high-flux capable compact-accelerator fusion neutron generator (FNG) is discussed. FNG's can be used in a variety of industrial analysis applications to replace the use of radioisotopes which pose higher risks to both the end user and national security. High efficiency, long lifetime, and high power-handling capability are achieved though innovative target materials and ion source technology. The device can be scaled up for neutron radiography applications, or down for borehole analysis or other compact applications. Advanced technologies such as custom neutron output energy spectrum, pulsing, and associated particle imaging can be incorporated.

An air bag module for protection of an occupant within a vehicle during an impact event. The module includes an inflator for generating an inflation gas, an air bag cushion stored in fluid communication with the inflator such that upon generation of the inflation gas the air bag cushion is deployable substantially to the side of the vehicle occupant between the vehicle occupant and the adjacent interior portions of the vehicle. The air bag module further includes a biasing element of flexible character such as a woven or non woven textile which is folded and stored in overlying relation to the air bag cushion. The biasing element is expelled from its stored position upon deployment of the air bag cushion such that the biasing element is disposed between the occupant and the air bag cushion in leading relation to the air bag cushion along the path of deployment of the air bag cushion between the occupant and adjacent interior portions of the vehicle.

Described are computer-based methods and apparatuses, including computer program products, for dynamic rate adjustment to splice video streams. A splicer receives a first compressed video stream of bits and buffers the first video stream of bits in a first buffer. The splicer receives a second compressed video stream of bits to splice into the first compressed video stream. The splicer buffers the second compressed video stream of bits in a second buffer. The splicer determines a departure time for a splice in-point of the second compressed video stream of bits. The splicer adjusts a rate of the first compressed video stream of bits, a rate of the second compressed video stream of bits, or both to achieve the departure time.

This invention relates to a method of installation of an electrocoagulation (EC) system to remove contaminants from wastewater which includes the steps of: (i) measuring conductivity of the wastewater; (ii) from the result obtained in step (i) determining the number of electrically connected electrodes or unipolar electrodes required in the EC system for efficient removal of the contaminants, and (iii) from step (ii) assessing a range of current and/or voltage to be applied to an EC cell included in the EC system.

The invention discloses a method for measuring a high energy laser energy parameter based on a light pressure principle and an apparatus thereof. The method comprises the following steps: a reflector and a deformation rod are arranged on a high energy laser incidence optical path, a plurality of displacement sensors are provided at a back side of a reflector laser incidence direction, micrometricdisplacement of the reflector caused by light pressure in a laser light extraction process is measured in real time, a light pressure value generated by laser is solved, and parameters of the laser such as average power, energy, P-t curve, light spot center of mass change and the like are calculated. According to the method and the apparatus in the invention, light beam is not blocked in usage, an on-line measurement of undistributed transmission of high energy laser is realized, cost-effectiveness of an experiment is raised, simultaneously, a measurement system does not need to bear strong laser irradiation, and the method and the apparatus can be used for high power laser parameter measurement.

The invention relates to an UAV interference system and method based on electromagnetic interference, used for solving the problem that other normal radio communication is influenced by too high interference power and other related frequency devices are suppressed due to the fact that a suppression interference mode adopted in existing electromagnetic interference is in high power full- band coverage. The interference system comprises a reconnaissance sub-system and an interference sub-system; the reconnaissance sub-system comprises an L-band omnidirectional reconnaissance antenna, an S-band omnidirectional reconnaissance antenna, a C-band omnidirectional reconnaissance antenna, a down-conversion processing module, an intermediate-frequency processing module, a frequency hopping signal analysis module, a frequency hopping signal despreading and demodulation module, a guide interference module and a high-speed acquisition storage card; and the interference sub-system comprises an intermediate-frequency modulator unit, a converter unit, a signal filtering, switching and synthesizing unit, an L-band interference power amplification antenna unit, an S-band interference power amplification antenna unit, a C-band interference power amplification antenna unit and a control unit. The invention further provides an interference method based on the interference system.

A method for preparing a hierarchically porous doped carbon material includes the steps of heating a mixture including an etching agent precursor and a pore-generating agent. The pore-generating agent is embedded in a matrix including a carbon source and a dopant source for simultaneously carbonizing the carbon source. The method further includes doping with the dopant and etching the pore-generating agent for obtaining the hierarchically porous doped carbon material.The hierarchically porous doped carbon material can form an electrode, and an energy storage device such as a supercapacitor can include such an electrode. The hierarchically porous doped carbon material can also help form an energy storage and conversion device such as a metal-air battery or a regenerative fuel cell.

Method and apparatus for applying unique composite indicia or markings to a succession of articles, in which each unique composite indicium comprises two or more indicia. At least part of each of the indicia may be co-located at a predetermined location on the article with such co-location being unique or distinct for each composite indicium for each article. The indicium may be overprinted with one or more images, logos or color-schemes. A code (e.g. an alphanumeric string) that is stored in a database may be derived from the composite indicium from one or more mathematical properties. The code may be later accessed for identifying or verifying the article with the indicium.

This invention finds application in the field of the devices and methods for physical or chemical mixing of products and particularly relates to a cartridge for storage and sterile delivery of a two-phase compound. The cartridge comprises a first tubular member (2) which defines a first chamber (3) for storage of a solid phase, having a bottom wall (6) with an opening (7) for the passage of the compound, a second tubular member (9) which defines a second hermetically sealed chamber (12) for storage of a liquid phase, and a piston which sealably slides within the first tubular member (2), means (8) for occluding said opening (7) which comprise at least one rupturable membrane (15) associated to the bottom wall (6).

According to the present invention, there are provided a polarization filter and a sensor system. The polarization filter includes a circularly polarized light-separating layer having a cholesteric liquid crystalline phase fixed therein, in which the circularly polarized light-separating layer is a layer which selectively transmits one of the left-hand circularly polarized light and the right-hand circularly polarized light in the specific wavelength band, a λ/4 phase difference layer for light in the specific wavelength band is disposed on one of the surfaces of the circularly polarized light-separating layer, and the λ/4 phase difference layer includes a first phase difference region and a second phase difference region of which slow axis directions are orthogonal to each other. The sensor system includes the polarization filter, a light source which emits light having a wavelength in the specific wavelength band, and a light-receiving element which can detect light having a wavelength in the specific wavelength band. The polarization filter of the present invention can improve the sensitivity of a sensor system using polarized light, and the sensor system of the present invention has high sensitivity and is extremely cost effective.

The invention provides a near space atmosphere environment detector and an operating method thereof. The detector comprises a load grade system and a booster grade system; the booster grade system comprises a rocket body structure, a booster grade control subsystem and a booster grade power mechanism; the booster grade control subsystem is used for detecting the attitude and motion information of the rocket body structure when the load grade system is separated, and then controls the operation of the booster grade power mechanism according to the attitude and motion information of the rocket body structure, and therefore backward-thrust braking is provided to make the rocket body structure land in the vertical direction; the load grade system comprises a payload bay carried with an environment detection instrument, a load grade control subsystem and a load grade power mechanism; the load grade control subsystem is used for controlling the load grade power mechanism to operate in dependence on detected attitude, height, motion and guidance information, control of flying trajectories of the payload bay, the load grade control subsystem and the load grade power mechanism is achieved, and at least two times of skip flying is achieved.

Secure-digital (SD) type memory cards are produced using one or more prefabricated cover portions and a molded casing portion. A sub-assembly is formed by mounting a printed circuit board assembly (PCBA) onto the cover portion such that the contact pads of the PCBA are exposed through associated windows defined in the cover. The sub-assembly is placed into a cavity formed in a mold assembly, and molten thermoplastic material is then injected into each cavity of the mold assembly under heat and pressure using known injection molding techniques, thereby forming a molded plastic casing portion that secures the PCBA to the cover and completes the memory card housing.

A grooved universal radial seal ring used in a trocar and a trocar are provided. The radial seal ring includes one or more easily-deformable grooves, one or more supporting areas capable of guiding surgical device movement, and a through hole, the supporting areas of the seal ring are connected by the easily-deformable grooves, a thickness of the easily-deformable grooves is much smaller than an average thickness of the supporting areas, so that when a surgical device is inserted along a cone-shaped guiding groove of the supporting areas, the easily-deformable grooves deform first and surround the surgical device because a wall thickness of the easily-deformable grooves is very small, thereby achieving a sealing effect. When the surgical device shakes, the supporting areas separated by the easily-deformable grooves also shake together, but the seal ring formed by the easily-deformable grooves still surrounds the surgical device, thereby always keeping a sealed state and achieving an excellent dynamic sealing effect. Particularly, the thickness of the easily-deformable grooves is small, not only a dynamic sealing effect is excellent, but also surgical device moving resistance is small. The trocar realizes any replacement among surgical devices with diameters being 12 millimeters (mm), 10 mm, and 5 mm, thereby bringing convenience to surgical operation.

The invention relates to an apparatus and method for the geometric factor self-calibration of a laser radar and belongs to the laser atmospheric remote sensing technical field. The device comprises a laser, a main wave pulse generator, a secondary receiving mirror cover, a secondary receiving mirror, a light guide optical fiber, a main receiving mirror cover, a main receiving mirror, a reflex mirror, a red and green dichroic light splitter, a 1064nm narrowband filter, a APD detector, a blue and green dichroic light splitter, a polarization and beam splitting prism, a first 532nm narrowband filter, a first PMT detector, a 355nm narrowband filter, a second 532nm narrowband filter, a second PMT detector, a third PMT detector and an integrated acquisition system. The apparatus and method of the present invention have great advantages in terms of system scale, cost, usability, reliability and the like.

The invention relates to a calibrating method and device of radar dynamic tracking accuracy. The calibrating method and device of the radar dynamic tracking accuracy comprises a traction cableway, an analog target and a coordinate receiving station, wherein the analog target slides on the cableway through traction of an electric winding machine, when the analog target reflects a radar wave, the analog target locating a self coordinate at the same time, and the analog target sends back location data to the coordinate receiving station. The coordinate receiving station is fixedly installed on the ground, receives the real-time locating data sent back from the analog target, compares the real-time locating data with radar echo location data, and finishes calibration of the radar dynamic tracking accuracy. The calibrating method and device of the radar dynamic tracking accuracy is high in location accuracy, avoids system errors caused by a traditional calibrating method, and is easy and convenient to erect and good in applicability. Through repeated measurement of a radar and repeated comparison, radar system errors can be obtained, so that convenient and reliable calibration to the radar dynamic tracking accuracy is achieved. Calibrating accuracy is improved, and meanwhile calibrating cost of the radar dynamic tracking accuracy is greatly reduced.

The invention discloses a combined environmental disturbance magnetic field shielding system. The system comprises a magnetic shielding chamber based on multiple layers of magnetic conductive materials, a fluctuating magnetic field active compensation device and a geomagnetic active compensation device. The fluctuating magnetic field active compensation device is installed on the outer side of themagnetic shielding chamber based on the multiple layers of magnetic conductive materials, and the geomagnetic active compensation device is installed on the outer side of the magnetic shielding chamber based on the multiple layers of magnetic conductive materials and shares a coil framework with the fluctuating magnetic field active compensation device. The fluctuating magnetic field active compensation device outputs a compensation magnetic field with the same size and opposite direction as the fluctuating magnetic field in the environment interference magnetic field, and the geomagnetic active compensation device is used for compensating the geomagnetic field. According to the invention, a non-uniform stray interference magnetic field can be solved, and the shielding efficiency is improved.

A non-volatile memory device includes a chip of semiconductor material. The chip includes a memory and control means for performing a programming operation, an erasing operation and a reading operation on the memory in response to corresponding external commands. The chip further includes testing means for performing at least one test process including the repetition of at least one of said operations by the control means, and a single access element for enabling the testing means.

The invention discloses a satellite-borne antenna deployable mechanism, and aims to provide a deployable mechanism which is high in positioning precision and stable and reliable in work. According tothe technical scheme, an unlocking mechanism corresponding to a passive drive hinge and a locking mechanism which is located below an extension arm and corresponds to a joint hinge rotating shaft areinstalled on the extension arm, and in the storage state, an antenna reflector is connected with a joint through the passive drive hinge to rotate and then is fixed to the extension arm through the unlocking mechanism, the locking instruction is started, the locking mechanism executes an unlocking action, elastic potential energy of the synchronous gear transmission joint hinge drives the extension arm to slowly rotate around the axis of the synchronous gear transmission joint hinge, the locking mechanism triggers the unlocking action of the unlocking mechanism through an inhaul cable connected with the unlocking mechanism, and the inhaul cable is in linkage with the unlocking mechanism to unlock and release the extension arm; after unlocking, the passive driving hinge slowly rotates to apreset angle according to the rotating direction, the unfolding action of the extension arm and the antenna is completed step by step, and the antenna is locked and kept in a working state.

The invention relates to a multi-rotor fire extinguishing unmanned aerial vehicle (UAV) system, comprising a chassis, engine arms, an undercarriage, motor bases, motors, quick release propeller seats,propellers, a flight control system, a battery pack and a fire extinguishing pod, wherein the engine arms are installed at the periphery of the undercarriage by means of engine arm folding connectionpieces; the undercarriage is installed under a main body of the chassis by means of a connection piece; the motor bases are respectively installed at terminals of the engine arms; the motors are installed on the motor bases; an electronic speed controller is also installed on each motor base; the quick release propeller seats are respectively installed on the motors; the propellers are installedon the quick release propeller seats; the flight control system is installed at the central position of the top of the chassis; the battery pack is installed on the top of the chassis; the fire extinguishing pod is installed under the chassis and is internally filled with fire extinguishing bullets. The multi-rotor fire extinguishing UAV system has the advantages of being simple in structure, easyto manufacture, practical and efficient.