222 results about "Starlight" patented technology

A system and method for focusing electromagnetic energy on a moving target. Generally, the inventive system sends a pilot beam to a target and analyzes a return wavefront to ascertain data with respect to any distortions and other phase and/or amplitude information in the wavefront. This information is then used to pre-distort an output beam by so that it is focused on the target by the intervening distortions. In an illustrative embodiment, the pilot beam is provided by a beacon laser mounted off-axis with respect to the output beam. The reflected wavefront is received through a gimbaled telescope. Energy received by the telescope is detected and processed to ascertain wavefront aberrations therein. This data is used to predistort a deformable mirror to create an output beam which is the phase conjugate of the received wavefront. In a first alternative embodiment, a nonlinear optical phase-conjugate mirror is employed to generate the required wavefront-reversed replica of the received wavefront. The system further includes an arrangement for modulating the output beam to confuse the target. In a second alternative embodiment, the system is adapted to examine atmospheric distortions of starlight to predistort the output beam. The alternative embodiment offers a faster response time and a lower susceptibility to detection.

A fiber optic illuminated starlight scene on a headboard. By using a plurality of optical fibers (22) lighted by an illuminator (20) and the optical fiber/visible end (16) are positioned flush with front panel (12) decorative scene (14) a realistic rendition of a starlight scene is created. The optical fibers/visible ends (16) placement and dispersion in the decorative scene (14) along with the distance and angle of the optical fibers (22) to the illuminator makes each individual optical fiber/visible end (16) appear as starlight.

The invention relates to a satellite starlight refraction navigation error determination and compensation method. The method comprises the following steps: firstly, generating data of a satellite orbit by virtue of STK software; establishing a satellite attitude planning model; determining an actual observation visual field, and simulating an observation star map comprising refraction stars and non-refraction stars; calculating to obtain the tangential height h of the refraction stars; calculating to obtain the tangential height h'' of the refraction stars with errors of refraction angles and errors of an atmospheric model, wherein tangential height errors are mainly caused by the measurement precision errors of the refraction angles and the errors of the atmospheric model; calculating to obtain the position of a satellite under a geocentric inertial coordinate system; and performing filtration by an extended Kalman filtration method, and outputting a starlight refraction navigation estimated position and position errors. The method provided by the invention can realize accurate prediction of navigation precision of a satellite starlight refraction navigation system, and is comprehensive in error analysis and accurate and reliable in results.

The invention is a space measurement technology, involving the improvement to the star sensor calibration method. The invention uses the calibration system which comprising the air cushion platform, single star starlight simulator, star sensor, two-dimensional axial turntable and data processing computer, and its steps are: 1. establish the star sensor imaging model; 2. parameters calibrating. The invention uses no deviation strip to calibration focus and radial distortion coefficient, eliminating the internal parameter estimation effect by the external installation error; the method has simple model and small computing volume, particularly applied to the star sensor calibration based on radial distortion.

The invention discloses airborne starlight of a coupling inertial position error and an independent navigation method of inertial composition. In the method, firstly theoretical analysis is carried out on an attitude integrated observation principle in navigation under an aviation airborne geography department, an attitude observation linearization measurement equation under a geography departmentis established, inter-conversion relation between the attitudes from an inertial system to the geography department measured and output by a star sensor (star light) is analyzed, a coupling error model between the attitudes under the inertial system measured and output by the star sensor and the attitudes under the geography department calculated and output by the inertial navigation is established through introducing an inertial navigation position error conversion matrix, and finally aviation airborne starlight based on the modeling thoughts of the coupling inertial position error and a mathematical model of an inertial integrated navigation system are designed, and a KF filtering method is adopted to optimally estimate the error state of the inertial navigation. The invention has high-accuracy in navigation, and can give full play to the estimation function of the attitude measurement equation under the geography department on error state amount of the aviation airborne inertial navigation system.

The method includes steps: building up kinematical equation of earth satellite orbit based on rectangular coordinate system; building up measurement equation based on angular distance of starlight as measuring quantity; building up discrete type extended Kalman filtering equation to determine whether extended Kalman filtering is divergent; using prognostic filtering residual to determine whether extended Kalman filter is divergent; if yes, then the method carries out estimating statistic characteristics of noise; otherwise, carrying out calculation according to standard extended Kalman filtering program. The invention solves issue that divergence of noise filter caused by inaccurate determination of statistic characteristics of noise influences on navigation accuracy. Advantages are: independent, flexible and simple, and high precision. The invention is especially suitable to earth application satellite needed high navigation accuracy in resource, weather areas etc.

A static multi-optical-path star simulator comprises a flange and at least four starlight pipes, wherein each starlight pipe can produce a simulation star, optical spectrum and brightness of each starlight pipe can be separately adjusted, the starlight pipes are installed on the flange by an angular adjustment mechanism, optical axles of two arbitrary star pipes are not parallel, relative angle between two arbitrary star pipes can be adjusted in a range not smaller than 10 degrees, a large amount of simulation constellations with different constructions can be produced, brightness and spectral characteristic of all asterions can be different, geometrical similarity between two arbitrary simulation constellations is relatively low, and physical characteristics of actual star field can be well simulated.

The invention relates to an in-orbit calibration method of star sensor lens distortion and a satellite attitude determination method based on starlight vector correction. The invention relates to an in-orbit calibration method of star sensor lens distortion and a satellite attitude determination method. The invention aims at solving a problem of incapability of calibrating a temperature distortion term of an existing calibration method, and a problem of low precision of an existing satellite attitude determination. The star sensor lens distortion in-orbit calibration method comprises the steps that: an included angle between fixed star incident light and a lens optical axis is obtained by calculation according to target fixed star imaging point coordinates and a star sensor lens distortion formula; a light vector direction of the target fixed light is obtained according to the included angle of the incident light and the lens optical axis; and in-orbit calibration of star sensor lens distortion is carried out according to a principle that the included angles of light vector directions of a plurality of target fixed stars are fixed. The attitude determination method comprises the steps that: a target fixed star starlight vector is obtained by calculation according to the target fixed star imaging point coordinates and the star sensor lens distortion formula obtained by calibration; and satellite attitude is determined through star map matching. The methods provided by the invention are applied in the technical field of satellite attitude determination.

The invention relates to a standard starlight simulator and a stray light PST (point source transmittance) optical detection system containing the same. The standard starlight simulator comprises a light source, an iris diaphragm, a dodging instrument, a star point plate and a collimation system; the iris diaphragm is arranged on the incident optical path of the light source; the dodging instrument is arranged on the output optical path of the iris diaphragm; the star point plate is arranged above the dodging instrument; and the collimation system is arranged on the output optical path of the star point plate. The invention provides the standard starlight simulator which can greatly enlarge the range of the simulated stellar magnitude and realize accurate measuring and calibrating under pianissimo light environment and has high measurement accuracy, and the stray light PST (point source transmittance) optical detection system containing the simulator.

An automatic celestial navigation system for navigating both night and day by observation of K-band or H-band infrared light from multiple stars. A preferred embodiment uses three telescopes with each of the three telescopes rigidly mounted with respect to each other and rigidly mounted on a movable platform such as a ship or airplane with each telescope being directed at a substantially different portion of sky. Telescope optics focuses, onto the pixel array of a sensor, H-band or K-band light from stars in the field of view of each telescope. The system also includes an inclinometer, an accurate timing device and a computer processor having access to cataloged infrared star charts. The processor is programmed with special algorithms to use image data from the infrared sensors, inclination information from the inclinometer, time information from the timing device and the cataloged star charts information to determine positions of the platform. At least two telescopes pointed far enough from the sun detect stars. Direction information from two stars is needed for locating the platform with respect to the celestial sphere. The computer is also preferably programmed to use this celestial position information to calculate latitude, longitude and absolute azimuth, all of which may be displayed on a display device such as a monitor. In a preferred embodiment each of the three telescopes are fixed on a moving ship and views a 0.5×0.4 degree region of the sky for H-band starlight from stars with brightness greater than 6.4 H-band magnitude. Located stars are then compared with star positions from the star catalog within a selected 5×5 degree region of the sky. A correlation of the data from the three telescopic measurements determines the position of the ship to a precision of 30 meters.

The invention discloses a method for processing a stone surface, which comprises the following processes: the natural stone with a pore is first smoothly milled by a mill. The milled stone is cleanly washed and is dried by a drier or natural wind. A part of the pores is then sealed by a gummed paper according to the needs. The rest pores are filled by the milled powder and then is smoothly milled by the mill. The next process is to tear off the gummed paper in the pore and then a glue solution is coated on the pores. A gold powder or silver powder or other luminous substance is filled on the glue solution. After the glue solution is dried, the surface of the stone is coated by a layer of paint with an ability of butter resistance; finally, a layer of resin is coated on the painted stone surface. After a levigation using the mill, the stone surface is polished and waxed, then the stone with a golden flickering or silver flickering or starlight flicking surface is obtained. The stone manufactured by the process method in the invention has the advantages of simple process, being able to retain the nature characteristic of the natural stone and add the flickering effect.

A chip scale star tracker that captures plane-wave starlight propagating in free space with a wafer-thin angle-sensitive broadband filter-aperture, and directs the light into a waveguide structure for readout. Angular information about the star source is determined from characteristics of the starlight propagating in the waveguide. Certain examples include internal propagation-constant-based baffling to elimination stray light from extreme angles.

The invention discloses a starlight glazed ceramic tile which comprises a green body layer, a ground glaze layer, a chromophoric glaze layer and a dry granular glaze layer from bottom to top. The preparation method comprises the following steps: (1) pressing powder into a green body, and drying the green body at 145-160 DEG C for 1-1.5 hours; (2) cleaning the surface of the green body, and spraying water to the surface of the green body to wet the surface of the green body; (3) applying ground glaze to the surface of the green body; (4) carrying out silk-screen printing to form the chromophoric glaze; (5) performing ink-jet printing of patterns; (6) applying transparent bright dry granules to the brick surface; (7) putting the green body obtained in the step (5) into a kiln, and firing thegreen body for 40-60 minutes at the temperature of 1150-1200 DEG C; and (8) performing soft polishing on the transparent bright dry granules protruding out of the surface of the fired ceramic tile toobtain the starlight glaze ceramic tile. The protruding surface of the ceramic tile is in a fine and soft matte feeling, but the whole ceramic tile is in a flashing spot starlight effect, the patterndefinition is good, the product is extremely attractive, and the blank of the product on the market is filled up.

The present invention provides a super star-light-level high-resolution fixed focus lens which comprises a first lens with convex-concave negative focal power, a second lens with biconcave negative focal power, a third lens with concave-convex positive focal power, a fourth lens with biconvex positive focal power, a fifth lens with convex-concave positive focal power, a sixth lens with convex-concave negative focal power, a seventh lens with biconcave negative focal power, an eighth lens with biconvex positive focal power, a ninth lens with biconvex positive focal power, a tenth lens with convex-concave negative focal power and an eleventh lens with biconvex positive focal power which are orderly arranged from an object side to an image side along an optical axis. 11 specially arranged lenses are adopted, the super star-light-level high-resolution fixed focus lens has a characteristic of ultra large amount of light pass, a wide angle 110 degrees of the field of view angle is supported,and at the same time, the requirements of resolution and imaging can be ensured when the lens is used in an environment of -40 DEG C to 70 DEG C.

The invention belongs to the technical field of ceramic materials, and particularly relates to a wear-resistant antifouling ceramic tile with a starlight diamond effect and a preparation method of thewear-resistant antifouling ceramic tile. The ceramic tile comprises a green body, ground glaze, surface glaze, an ink jet layer, a starlight glaze layer and a glue layer which are sequentially compounded from bottom to top, wherein the starlight glaze layer is prepared from starlight glaze particles; the starlight glaze particles are prepared from, by mass, 10-15 parts of carborundum, 5-10 partsof mullite, 3-6 parts of aluminum oxide, 20-30 parts of potassium feldspar, 10-20 parts of quartz sand, 3-5 parts of zinc oxide, 3-7 parts of barium carbonate and 8-12 parts of calcined talc. According to the wear-resistant antifouling ceramic tile with the starlight diamond effect, the glaze layer is fine and smooth in color, natural and vivid, good in wear resistance, high in antifouling property, high in strength and excellent in mechanical property, and the surface of the wear-resistant antifouling ceramic tile flashes like diamonds.

A decorative lighting string including blinking or twinkling lights spaced apart by at least three feet and preferably approximately six feet on a light string will create the effect of twinkling starlight or flickering firelight when used as part of a decorative scheme, such as Christmas decorations. This decorative lighting display is especially suited for outdoor use and can be effectively used in deciduous trees after they have lost their leaves. Twinkling lights that emit an illuminate of at least 40 lumens are especially suited for outdoor use. A random, irregular lighting pattern in which the lights do not appear to be connected by a light string provides the illusion of twinkling lights suspended in mid-air in a dark or darkening sky.

A kind of optical system of the minitype dynamic starlight simulator belongs to the space detecting technique field. It includes a lamp-house, a illuminating optical lens, a digital minicrystal and a collimating objective group. The digital minicrystal and the collimating objective group are set at the ray axis of the horizontal beam path. The reflecting surface of the digital minicrystal is towards the collimating objective group and on the focal surface of it. The beam path axis composed of the lamp-house and the illuminating optical lens forms certain angle with the horizontal beam path axis and its extension line goes through the center of the digital minicrystal. The lamp-house emits uniform light through the illuminating optical lens and the light is reflected by the digital minicrystal and is sent out by the collimating objective group along the horizontal ray axis. The structure of the optical system is simple; the volume is small; the weight is light. And it is applied conveniently.

The invention discloses an adaptive satellite selection method and system with celestial body interference. The method comprises: obtaining the optical axis information of a star sensor sent by a starlight analog module and formed by an orbit; selecting a optimum interval of observing the refractive starlight; establishing a starlight observation window according to the position of a spacecraft, determining the area of the fixed star observed by the star sensor; analyzing the starlight refraction celestial body interference to select and optimize the starlight observation window; determining an observing star area of the spacecraft according to the obtained starlight observation window to obtain a selectable refraction star range of the spacecraft, predicting the direction and information of the fixed star of which starlight occurs refraction according to the given position and time information of the spacecraft by using a starlight refraction navigation error minimum satellite selection method, and selecting the adaptive navigational star. The adaptive satellite selection method and system with celestial body interference can exclude the celestial body interference according to the given position and time information of the spacecraft, and can predict the direction and information of the fixed star of which starlight refracting accurately, so that the function of selecting the adaptive navigational star is realized.

The present invention offers an improvement to existing canting, slope error, and/or pointing measurement approaches, by using one or more cameras to observe the reflections of points of light in the firmament, such as the reflections of stars and/or planets as visible within the night sky in the heliostat facets. An illustrative heliostat measurement system comprises a plurality of heliostats, and at least one camera that observes at least one heliostat. The heliostats reflect an image of the firmament that can be observed by the at least one camera. The system further comprises (i) at least one captured image of the firmament reflected from at least one of the heliostats; and (ii) a computer comprising programming that determines a heliostat imperfection from the captured image, wherein the heliostat imperfection is selected from at least one of a slope error, a canting error, and a pointing error.

The invention relates to a starlight positioning navigation method based on artificial satellites. Thestarlight positioning navigation method comprises the following steps: firstly, observing three satellites in a space by adopting a star sensor, obtaining position coordinates of the three observed satellites according to satellite ephemeris, and calculating a relative distance between any two satellites; measuring unit direction vectors of three satellites relative to the star sensor by adopting the star sensor, and calculating field angles of any two satellites relative to the star sensor; calculating the relative distance between the star sensor and each satellite; and calculating the position of the star sensor according to the position coordinates of the three satellites and the relative distance between the star sensor and each satellite, thereby realizing the autonomous positioning of the aircraft. According to the invention, the functions of the star sensor are expanded, on the basis of traditional autonomous attitude determination, autonomous positioning is realized, no extra equipment is added, no extra space is occupied, and the method has very high economical efficiency.

The invention provides a deep space probe angle measurement and time delay integrated navigation method based on on-line estimation, and the method comprises the steps: estimating the current positionand speed information of a probe and a reflection celestial body according to the orbit dynamics, and building a system state model through employing the current position and speed information as a system state quantity; obtaining starlight angular distance measurement between the detector and the reflection celestial body as well as between the detector and the background fixed star by using anangle measurement sensor, and establishing a starlight angular distance measurement model; respectively observing the direct sunlight and the reflected sunlight reflected by the reflection celestial body by using two atom frequency discriminators so as to obtain time delay measurement, and establishing a time delay measurement model; obtaining state estimation and error covariance estimation through implicit unscented Kalman filtering, correcting the actual position and speed information of the reflection celestial body, then obtaining the actual position and speed information of the detector,and achieving detector navigation. The influence of the ephemeris error of the reflection celestial body on the navigation precision is inhibited, and the autonomous navigation precision of the detector is improved.