30 results about "Exterior field" patented technology

A vehicle vision system includes a vehicle having a body surface and a vehicle element generally at the body surface. The vehicle element has a normal distance dimension relative to the body surface of the vehicle. The vehicle vision system includes an imaging device having an exterior field of view generally exterior of the vehicle for capturing images of a region external of the vehicle. An extender element is at the body surface and extends outwardly therefrom, and the vehicle element is disposed at an outer surface of the extender element, whereby the extender element extends the normal distance dimension of the vehicle element for accommodating the imaging device. The imaging device is disposed at least partially within the extender element, whereby the presence of the imaging device in the extender element is at least partially masked or camouflaged by the extender element and the vehicle element.

A vehicle vision system includes a vehicle having a body surface and a vehicle element generally at the body surface. The vehicle element has a normal distance dimension relative to the body surface of the vehicle. The vehicle vision system includes an imaging device having an exterior field of view generally exterior of the vehicle for capturing images of a region external of the vehicle. An extender element is at the body surface and extends outwardly therefrom, and the vehicle element is disposed at an outer surface of the extender element, whereby the extender element extends the normal distance dimension of the vehicle element for accommodating the imaging device. The imaging device is disposed at least partially within the extender element, whereby the presence of the imaging device in the extender element is at least partially masked or camouflaged by the extender element and the vehicle element.

The invention relates to a power supplying device and a method for a near field communication terminal. The device includes a non-contact front end chip, a base band chip, a safety chip, a user recognizing card, a reader / writer, an antenna, a low dropout regulator, a power supply management unit, a battery, a control switch, and a battery voltage detecting circuit; wherein the non-contact front end chip includes a RF rectifying circuit, an exterior field detecting circuit, and a non-contact front end post-treatment part. The device can supply power for a terminal in the mode by combining residual power in the battery and exterior field detection when a mobile phone is in off state so as to enable the terminal to perform simulative functions of the non-contact card normally, thereby fully utilizing the residue power in the terminal battery, improving effective utilization rate of the battery, preventing a user from always carrying a stand-by battery, and reducing the application cost of the terminal.

The invention discloses airplane external illuminating space angle-positioning combining equipment which comprises a tripod (1), a vertical measurement rotating platform (2), a horizontal measurement rotating platform (3), lasers (4), a main measuring rod (5) and an auxiliary measuring rod (6), wherein the tripod can carry out position self locking to realize the height rough adjustment and accurate adjustment of the tripod; a central shaft of the tripod is butted with the vertical measurement rotating platform and the horizontal measurement rotating platform by ejecting screws (19); the lasers are installed at the top ends of central shafts of the vertical measurement rotating platform and the horizontal measurement rotating platform for realizing the alignment of shaft centers of the rotating platforms and a shaft center of a lamp to be measured; the main measuring rod is installed on a rotating platform central shaft, and the auxiliary measuring rod is installed at the other end of the main measuring rod and forms an included angle of 90 degrees with the main measuring rod; the top of the other end of the auxiliary measuring rod is provided with a measuring probe; and the measuring rods rotate by adopting the lamp to be measured as a center along with the rotating platform central shaft for carrying out measurement angle positioning on the lamp to be measured. The combining equipment of the invention realizes the on-board test of the external illuminating lamp needing positioning a space angle, is convenient for carrying out an outfield test and reduces the test guarantee demand and the test cost.

The invention relates to a projection objective which consists of at least seven lenses that are adjacent to air on both sides. The inventive projection objective meets the criteria of the following equations in its totality: u>=12.8°; 100 mm<=LEP<=400 mm; sigmaRBa>=1°; sigmaRBi<=-14°, whereby u is the aperture angle (2u-entire angle) on the illumination side; LEP is the distance from the entrance pupil (on the illumination side) to the object level (the position in the direction of projection from the reference point: object level corresponds to a positive value); sigmaRBa is the angle inclination of the beam in relation to the optical axis in the object space between the object and the 1. lens surface of the objective, said beam limiting the bundle for the field edge (outer field point in the object) towards the outside (away from the optical axis, far from the axis) and sigmaRBi is the angle inclination of the beam in relation to the optical axis in the object space between the object and the 1. lens surface of the objective, said beam limiting the bundle for the field edge (outer field point in the object) towards the inside (towards the optical axis, close to the axis). The angles sigmaRBa and sigmaRBi are positive when the corresponding beams intersect the optical axis in a point which is situated in the opposite direction of projection when seen from the object. Said angles are negative when the beams intersect the optical axis in a point which is situated in the direction of projection when seen from the object.

The invention discloses a board self-adaptation parameter configuration method, a BBU, a base station and a base station subsystem (BSS). The method comprises the steps that when the base station is powered on, peripheral boards are connected with main control boards in a physical link mode and board type information is reported to the main control boards by the peripheral boards, or commands for acquiring board configuration information are issued by an operation maintenance center (OMC) in the operation process of the base station, after the peripheral boards receive the commands, the board type information of the peripheral boards is reported to the main control boards; information of positions corresponding to the peripheral boards is acquired by the main control boards through physical link connecting information built between the main control boards and the peripheral boards; the board type information and position information of the peripheral boards are updated to a data base; the board type information and the position information of the peripheral boards are sent to the OMC to ensure that a configuration interface of the base station is updated by the OMC and the received information. According to the board self-adaptation parameter configuration method, the BBU, the base station and the BSS, the problem of incorrect configuration caused by human factors in the using process in an exterior field can be solved and configuration efficiency of the station is improved.

The invention belongs to the testing technology of airplanes, and relates to an outfield testing device of an airplane tail jet flow field. The outfield testing device of the airplane tail jet flow field is characterized by comprising an outfield measurement rake installation mechanism, and the outfield measurement rake installation mechanism is composed of a track (3), a track car (4), a wirerope (5), a pointer (6), a winch (7), a ground scale (8), a fixed pulley (10) and a testing device controller. The outfield testing device of the airplane tail jet flow field meets the requirement for outfield airplane engine jet flow tests.

An engine blade in-situ ultrasonic detection method comprises the following steps: carrying out in-situ detection of an engine blade in the outfield through using a special probe to obtain an A scanning oscillogram on an ultrasonic flaw detector, and determining whether the detected blade in the scanning area of the probe is damaged or not according to the A scanning oscillogram, wherein the special probe concretely comprises a probe body (1), a plug seat (2), a water tube (3), a cable (4) connected with the ultrasonic flaw detector, and a piezoelectric wafer (5). The method realizes the in-situ detection, and has a very prominent economic value, a huge technological application value and excellent technological effects.

The present invention describes a wireless system and method for distributing sensors in large numbers that makes possible the application of a number of algorithms for the extraction of important physical quantities. More specifically, the method involves (a) formation of an electromagnetic waveguide by the application of a polymer, or other dielectric material, on the exterior of the hull of a vessel; (b) insertion of sensors / radio units within the waveguide, the sensors being arranged to sample the fields of interest; and (c) insertion of radio transceiver base stations in the waveguide to communicate and extract data from the sensor / radio units. The wireless system of the present invention is implemented with a very high sensor count whose outputs are processed to recover exterior field quantities without the requirement of direct measurements off of the vessel's structure.

The invention relates to laser pattern projection device and method. It includes SCM controlled laser, scanning tilting mirror, and many parallel lasers. The method includes the following steps: using visual persistence effect to emit the laser from the parallel lasers to the scanning tilting mirror; projecting on the screen after reflecting; using SCM to control emitted laser bright-dark to form static or animate pattern or character. The invention has the advantages of compact structure, simple technology, high display contrast, realizing outdoor long distance projection by night, projecting out laser scroll with animate character or pattern, widely using in indoor outdoor occasions such as exhibition etc.

The invention discloses a virtual polar region method based on invariable grid attitude and velocity information, so as to solve the technical problems of poor navigation verification effects of the existing virtual polar region method. In the technical scheme, non-polar region field test data are converted to a polar region for navigation verification in a grid coordinate system, and through reference information conversion, initial state conversion and inertial sensor data conversion, virtual polar region modeling is completed. Through reference information conversion, initial state conversion and inertial sensor data conversion, a virtual pole simultaneously has two characteristics that the earth rotation is parallel with a gravity vector and fast convergence of the meridian is carriedout, and integrity of the model is improved; the non-polar region field test data are converted to the polar region for navigation verification in the grid coordinate system, the influences of the curvature of the earth are considered, and thus, the attitude and velocity information of a carrier relative to the ground can be ensured to be invariable before and after conversion, the model authenticity and the modeling accuracy are improved, and the effect of real test in a polar region can be achieved.

The present invention describes a wireless system and method for distributing sensors in large numbers that makes possible the application of a number of algorithms for the extraction of important physical quantities. More specifically, the method involves (a) formation of an electromagnetic waveguide by the application of a polymer, or other dielectric material, on the exterior of the hull of a vessel; (b) insertion of sensors / radio units within the waveguide, the sensors being arranged to sample the fields of interest; and (c) insertion of radio transceiver base stations in the waveguide to communicate and extract data from the sensor / radio units. The wireless system of the present invention is implemented with a very high sensor count whose outputs are processed to recover exterior field quantities without the requirement of direct measurements off of the vessel's structure.

The invention relates to a star gazing testing device for evaluating the thermal stability of star sensors. The device comprises an integrated support, a precise temperature control instrument, a wind-proof protection cover and a testing industrial personal computer. The integrated support is of an axisymmetric structure, included angles of the normal between every two mounting faces on the integrated support are identical, and the same star sensors are correspondingly arranged on all the mounting faces; the precise temperature control instrument comprises an electric heating sheet and a thermistor, the electric heating sheet and the thermistor are pasted to the mounting faces of the outer side faces and bottom faces of shading covers of all the star sensors, and temperature collection andloop control are conducted; the wind-proof protection cover covers the exterior of the integrated support provided with the star sensors and is installed on an out-field star gazing testing platform;the testing industrial personal computer and the integrated support are arranged at intervals and connected with all the star sensors through cables. The invention further provides a star gazing testing method for evaluating the thermal stability of the star sensors. According to the device, through technical means such as common mounting reference, initiative temperature control and heat insulation and wind prevention, by using the characteristic of consistent thermal stability of the same star sensors, the accurate and effective quantitative evaluation method for the thermal stability of the star sensors is provided.

A system for reducing spike noise in a perpendicular recording medium having a soft underlayer is provided. The system radially biases the soft underlayer to substantially eliminate domain walls therein. In a first embodiment of the system, a permanent magnetic bias ring is disposed generally adjacent to the soft underlayer and a magnetic circuit is formed between the magnetic ring and the soft underlayer. Other embodiments include a concentric stationary magnetic flux return disk to extend the radial distance of the flux path. In alternative embodiments, a ferromagnetic spindle assembly is modified to produce a radiation pattern that has a net radial exterior field that biases the adjacent soft underlayer of the medium. The entire assembly can be shielded from external magnetic fields in the disk drive. Further, the shielding may operate as part of the magnetic circuit.

The invention discloses a system and a method for detecting air leakage on a combination surface of an engine case. The system for detecting air leakage on the combination surface of the engine case comprises a temperature measuring instrument and a data acquisition display, wherein the temperature measuring instrument is fixed, and the measuring range of the temperature measuring instrument is covered by the surface of the case to be measured; the data acquisition display converts the temperature data acquired by the temperature measuring instrument into a thermal image for display. The method for detecting air leakage on the combination surface of the engine case comprises the following steps: 1. a plurality of temperature measuring instruments are adopted, so that the measuring range ofthe temperature measuring instrument is covered by the surface of the case to be measured, and an engine starts to work to scan the joint surface of the mounting edge of the case to be measured; 2, the temperature data detected by the temperature measuring instrument is transmitted to the data acquisition display; 3, the thermal image displayed by a display is acquired, the position of the air leakage is judged according to the color difference of the thermal image at different positions, and if the color of a certain part is inconsistent with the color of other parts in the same color area,the part is the air leakage part. The system and method for detecting air leakage on the combination surface of the engine case is used for determining whether the combined surface of the case leaks or not and the leaking part in the bench test run and the field use, and adopts a targeted control measure to improve the use reliability of the engine.

The invention discloses a system for measuring the center of mass of a missile. The system comprises a measuring instrument, two bridge type weighing sensors, two supporting brackets and connecting rods; the two supporting brackets are connected through the connecting rods and are used for supporting the missile; the two bridge type weighing sensors are arranged on the two supporting brackets and are used for weighing the missile; graduated scales are arranged on the connecting rods; the connecting rods can connect and fix the two supporting brackets at different distances; and the measuring instrument is connected with the two bridge type weighing sensors, is used for acquiring and processing data and is used for displaying the position of the center of mass of the missile. With the system, out-field targeting hanging point test work of the missile is facilitated, the hanging point can be positioned quickly, the system is high in integrity and simple to operate, and the reliability and the practicability of out-field application are sufficiently guaranteed.

The invention relates to an outfield high-light floodlight with the function of explosion prevention, which can be used in wide occasions, such as squares, stadiums, golf courses, large-scale buildings, container yards, harbors, docks and the like. The outfield high-light floodlight with the function of explosion prevention comprises a light source (9), a light body (20) and a transparent member fixed on the light body (20), wherein the transparent member comprises outer-layer toughened glass (4) and inner-layer toughened glass (7) between which a gap is reserved. By using the outfield high-light floodlight with the function of explosion prevention, the surface temperature of the transparent member can be lowered, thereby the integral surface temperature of the outfield high-light floodlight with the function of explosion prevention is controlled, and personal injury accidents, such as high-temperature scalds and the like, are avoided. In addition, as the outfield high-light floodlight has a double-layer or multi-layer hollow glass structure, the surface temperature of the light is fully controlled, and the using performance and the safety of the light are maintained.

The invention discloses a plane weighing system comprising an attitude measuring component, a weight measuring component and a control calculating part. The attitude measuring component and the weight measuring module are connected with the control calculating part through a wireless transmission device. The attitude measuring component is arranged on the body of a plane, the weight measurement component is arranged on a jack, and the plane is arranged on the jack. By means of traditional technology, through a reasonable design, the field portable plane weighing system is developed. The system can quickly weigh a plane of a few tons to several hundred tons and can achieve aircraft weighing and calculation of longitudinal center of gravity, transverse center of gravity and vertical center of gravity without the need of a horizontal plane top.

An engine blade in-situ ultrasonic detection method comprises the following steps: carrying out in-situ detection of an engine blade in the outfield through using a special probe to obtain an A scanning oscillogram on an ultrasonic flaw detector, and determining whether the detected blade in the scanning area of the probe is damaged or not according to the A scanning oscillogram, wherein the special probe concretely comprises a probe body (1), a plug seat (2), a water tube (3), a cable (4) connected with the ultrasonic flaw detector, and a piezoelectric wafer (5). The method realizes the in-situ detection, and has a very prominent economic value, a huge technological application value and excellent technological effects.

The present invention provides a simple method for measurement of the sweepback angles of a missile wing. Three datum points A, B and C which are not located on the same line are arranged at the upper of the missile wing, lines are scribed on the missile wing and a projectile body, a rope and a ruler are employed to measure the distances among the datum points and the distances between the datum points to the Dk; a coordinate system is built in a plane ABC; and the space coordinate values of all the feature points Dk and the sweepback angles of the missile wing are obtained through calculation according to the geometric equation, and the confidence interval of the sweepback angles of the missile wing is calculated according to the measurement precision of the ruler. The simple method for measurement of sweepback angles of the missile wing employs common tools to measure the sweepback angles of the missile wing, is easy to realize and is not high in the requirement of the measurement environment, and is very suitable for measurement of the sweepback angles of the missile wing in the field conditions; the simple method for measurement of sweepback angles of the missile wing can replace an expensive three dimensional measuring machine or a three-dimensional measurement machine to measure the sweepback angles of the missile wing so as to observably save the measurement cost; and the simple method for measurement of sweepback angles of the missile wing can calculate the confidence interval of the sweepback angles of the missile wing so as to provide reference data for an emission decision.

The invention discloses a determination method of an aero-engine installation center surface. The method is characterized by using an equal water level principle and adopting a transparent PVC transparent plastic U-shaped pipe, a horizontal laser ray instrument and a length measuring instrument to calibrate aero-engine measuring points, wherein a deviation of 4 front and rear measuring points and an installation center surface P is less than or equal to 1mm; and through the four measuring points, identifying the aero-engine installation center surface. The method is suitable for aero-engine delivery inspection, airplane assembling engine review inspection and loading inspection under an aero-engine outfield usage condition and a good practical engineering value is possessed.

The invention discloses a field mobile illumination trolley which comprises a trolley base, a trolley body vertical rod, a handheld dragging rod, at least one lamp, at least two wheels, cables used for providing illumination sources and at least one pull rod used for adjusting the angle of the lamps and can stretch out and draw back vertically. The wheels are mounted on the lower portion of the trolley base and used for guaranteeing free and stable moving of the field mobile illumination trolley. A supporting frame is arranged at the top end of the trolley body vertical rod, each lamp is in pivot joint with the supporting frame, and the bottom end of the trolley body vertical rod is fixedly connected to the center of the trolley base. The handheld dragging rod is connected to the trolley base in an inserted mode and used for pushing and moving the field mobile illumination trolley. One ends of the cables are inserted in the lamps, and the other ends of the cables are connected with an external power supply. One end of each pull rod is fixedly connected to the trolley base, and the other end of each pull rod is connected with the corresponding lamp. The field mobile illumination trolley is easy and convenient to manufacture, low in cost and high in practicability.

The invention discloses a determination method of an aero-engine installation center surface. The method is characterized by using an equal water level principle and adopting a transparent PVC transparent plastic U-shaped pipe, a horizontal laser ray instrument and a length measuring instrument to calibrate aero-engine measuring points, wherein a deviation of 4 front and rear measuring points and an installation center surface P is less than or equal to 1mm; and through the four measuring points, identifying the aero-engine installation center surface. The method is suitable for aero-engine delivery inspection, airplane assembling engine review inspection and loading inspection under an aero-engine outfield usage condition and a good practical engineering value is possessed.

The invention discloses a method for tailoring low-temperature test conditions of a complete aircraft in a laboratory, comprising the steps of: 1. special temperature screening of an external low-temperature environment; 2. quantitative analysis of the performance of key motion mechanisms of the aircraft in the external low-temperature environment; 3. low-temperature test Preliminary tailoring of conditions; 4. Draw the curve of the performance change of the aircraft's key motion mechanisms under the test temperature of the low temperature environment in the field; 5. Quantitative measurement of the performance of the aircraft's key motion mechanisms in the low temperature environment in the laboratory; The curve of the performance change at the low temperature environmental test temperature in the laboratory; 7. The fitting of the corresponding first curve and the second curve; 8. R-square test for goodness of fit. The invention integrates the action mechanism of the low temperature test on the whole aircraft into the tailoring process, and deeply considers the equivalence analysis and environmental test verification of the natural environment in the outer field and the laboratory in the inner field, and realizes the effective expansion of the tailoring method and thinking, which is real and reasonable.

The invention discloses a method for dividing replaceable units in the field considering development and maintenance. ; Step 3: Solve the optimization target model; Step 4: According to the solution results in Step 3, determine the repair level and repair method of each component in the equipment as the field replaceable unit. The present invention considers the influence of the development stage on the division of the field replaceable units, and comprehensively considers the cost of each part of the equipment from the development to the use and maintenance phase, so that the division is more suitable for the actual situation and more scientific and reasonable. At the same time, the main maintenance tasks at the basic level of the product are clarified by dividing, so that the equipment can be maintained and repaired in time, thereby ensuring the long-term performance of the equipment.

In order to solve the problems that two different missiles are hung on the same plane and a missile launcher cannot be generalized, the generalized research and exploration of the missile launcher are begun in China, ground loading and unloading and detecting as well as air carrying, control and launching of two missiles are finished by using a set of tool and an inspection device under the condition of not changing any parts, thus the purposes of reducing equipment variety, facilitating flight-line maintenance, and shortening second sortie time of the plane are achieved and the generalized requirement of an army on the missile launcher is satisfied. The gas electromagnetic valve is specially researched for the missile launcher, certain-pressure gas is output by a missile launcher system to the gas electromagnetic valve, and the gas electromagnetic valve is sealed or respectively outputs two gases of different flows to the two different missiles at different time after receiving corresponding instructions, so that the loading and unloading, detecting, carrying, control and launching of the two missiles are realized and the generalization of the missile launcher is realized.