117 results about "Solar angle" patented technology

This invention generally relates to automated shade systems that employ one or more algorithms to provide appropriate solar protection from direct solar penetration; reduce solar heat gain; reduce radiant surface temperatures; control penetration of the solar ray, optimize the interior natural daylighting of a structure and optimize the efficiency of interior lighting systems. The invention additionally comprises a motorized window covering, radiometers, and a central control system that uses algorithms to optimize the interior lighting of a structure. These algorithms include information such as: geodesic coordinates of a building; solar position; solar angle solar radiation; solar penetration angles; solar intensity; the measured brightness and veiling glare across a surface; time, solar altitude, solar azimuth, detected sky conditions, ASHRAE sky models, sunrise and sunset times, surface orientations of windows, incidence angles of the sun striking windows, window covering positions, minimum BTU load and solar heat gain.

An apparatus and method for initiating a search mode of a mobile device based on the light information in the environment of the mobile device is described herein. The light information may include at least one of color temperature or illuminance, which may be used to determine if the environment of the mobile device is indoors or outdoors. A threshold may be predetermined or adjusted based on received position assistance information. The position assistance information may include at least one of time, day, solar angle, motion information, location information, or weather information.

The invention relates to a method for improving the orbit-transferring safety of an inclined orbit satellite, wherein the problem of energy-source shortage of the inclined orbit satellite in the period of orbit-transferring motorization under the condition of high solar angles is solved through the reasonable adjustment of flight events by considering the condition of solar altitude angles in the designing process of a flight program, and meanwhile, flight-control operation can be simplified. The discharging time of a storage battery in the period of orbit-transferring ignition can be shortened by designing the flight program according to the method, so that the load power in the power-supplying period of the storage battery is reduced, therefore the discharging depth of the storage battery is reduced, the energy-source safety of the satellite is ensured, and a launch window is not limited by solar illumination angles.

The invention provides a guide rule designing method in yaw gesture control over a satellite. The method comprises the following steps that firstly, the track solar angle (an angle beta for short) and a sun vector under a track system are calculated; secondly, when the angle beta is larger than or equal to a given threshold value, a target yaw angle is calculated according to a current track system sun vector, and when the angle beta is smaller than the given threshold value, the target yaw angle is calculated according to a hypothesis sun vector with the angle beta being an assigned angle; thirdly, when the angle beta crosses zero and when it is met the condition that the target yaw angle is a small angle at the same time, a calculation method of the target yaw angle is switched.

A method for obtaining satellite solar angle and time on the basis of satellite orbit characteristics comprises the following steps: (1) according to the satellite sun-synchronous orbit characteristics, calculating the orbit inclination angle from the height of the satellite orbit; (2) according to the number of satellite orbits, calculating the longitude and Beijing time of sub-satellite point of the position where a satellite descending orbit intersects the equator, and converting the Beijing time into the local time so as to obtain the time of the position; (3) calculating to obtain the local times of any latitude where the satellite sub-satellite point pass; (4) according to the orbit injection error of satellite orbit inclination angle and the daily change rate of satellite orbit inclination angle during the operation process, calculating to obtain the change of satellite local time and actual local times of any latitude; (5) calculating to obtain the actual local time after satellite side-sway; (6) calculating to obtain the solar altitude, solar azimuth, and the Beijing time of an observation site. The provided method can precisely obtain the solar altitude, solar azimuth, and imaging time of a satellite according to a remote sensing satellite nominal orbit and changes thereof without knowing the satellite ephemeris data and specific imaging time.

The invention provides a self-power wireless simulation solar angle sensor, belonging to the spacecraft attitude measurement sensor technical field. The sensor is characterized in that the sensor comprises a solar angle sensor unit, a power support unit and a wireless communication unit. The solar angle sensor unit comprises four parts of a front end optical system, a solar angle sensor, a conditioning circuit and an external cavity body. The power support unit comprises two parts of a power collecting device and a power management circuit. The wireless communication unit comprises an A/D converting circuit which is connected with the conditioning circuit and used for receiving solar angle information and a wireless communication circuit. The self-power supply and the pure wireless simulation solar sensor are realized in the invention. A two-dimensional position sensitive detector (PSD) is adopted as the solar angle sensor which has the advantages of high precision, simple structure, small size and no externally physically connected electric interface. Therefore, the self-power wireless simulation solar angle sensor is beneficial for the integrated design of an application system.

The invention relates to a curbside small retailer cart, in particular to a solar panel angle regulation device for the curbside small retailer cart. The solar panel angle regulation device for the curbside small retailer cart is characterized by being capable of flexibly regulating an angle of a solar panel, higher in solar utilization rate and high in practicability. The solar panel angle regulation device for the curbside small retailer cart comprises a ceiling, a storage battery, a guide wheel, a support rod, first springs, an installation plate, a solar panel, installation blocks, slide rails, slide blocks, second springs and first connection rods, wherein the storage battery, the guide wheel and the support rod are sequentially arranged at the bottom of the ceiling from left to right. The solar panel angle regulation device can flexibly regulate the angle of the solar panel through a steel wire rope and is also simple to operate, and the solar panel is longer in light receiving time and more in light amount by adjusting the angle of the solar angle.

A near infrared (NIR) wideband reflector coating designed to start reflecting solar energy wavelengths from at least 1.2 microns in a typical geosynchronous earth orbit or medium earth orbit satellite and from at least 1.3 microns in a typical low earth orbit satellite. Also, the (NIR) wideband reflector coating reflects solar energy wavelengths below 0.35 microns in all three applications. This invention works on triple junction (TJ) solar cells. The performance of at least 1.2-microns is on solar panels with near-normal incident solar angle, typical of Geosynchronous Earth Orbit (GEO) and Medium Earth Orbit (MEO) satellites. The performance of at least 1.3-microns is on solar panels with wide range of incident solar angles, a design requirement for Low Earth Orbit (LEO) satellites.

The invention relates to the field of satellite development, in particular to a satellite configuration design method adapting to one-rocket multi-satellite launching. According to the method, for the illumination characteristic that the solar angle of a low-dip-angle orbit changes in a large range, an outer surface corresponding to the lower bottom of a satellite trapezoidal cross section is improved to be an arch formed by three panels in an enclosing mode to serve as an installing surface for fixing a solar cell array, and iterative optimization is conducted on included angles of the three cell panels. A satellite configuration designed through the method can be equivalent to the satellite configuration formed by a prismoid with a trapezoidal cross section and two slant prismoids with trapezoidal cross sections. The satellite configuration design method adapting to one-rocket multi-satellite launching has the main advantages that a solar wing spreading and driving mechanism is not arranged for each satellite, the weights of the satellites are reduced, and the reliability of the satellites is improved; a flight mission of long-time over-the-ground three-axis stable operation of a low-oblique-angle orbit can be met.

The invention relates to solar power generation devices, in particular to a solar angle-adjustable solar streetlamp power generation device. The solar angle-adjustable solar streetlamp power generation device can automatically clean a solar panel, is high in lighting efficiency and simple in structure. The solar angle-adjustable solar streetlamp power generation device comprises a streetlamp, a swing base, a placing plate, a solar panel, a supporting plate, a collection box, a net plate, a water collection bucket and the like; the swing base is arranged on the top of the streetlamp, and the placing plate is connected to the swing base. Through the water collection bucket, rainwater is subject to flow guide, and is stored through a water tank, through a water pump, water in the water tank is sprayed to the surface of the solar panel, a cleaning mechanism is used for auxiliary cleaning of the solar panel, through a water accumulating tank and a guide pipe, water drops flowing out are subject to flow guide, the solar panel can be automatically cleaned, the lighting efficiency is improved, and the structure is simple and reliable.

A digital sun sensor for stable-spinning micro/nano satellite comprises a detector, an instruction seam, a measuring seam and an electric circuit processing subsystem, wherein the detector is formed with two groups of orthogonal photoelectric coded discs by four photoelectric coded discs and comprises two vertical photoelectric coded discs and two horizontal photoelectric coded discs. The instruction seam is vertical with the measuring seam. The sun light vertical with the measuring seam penetrates the measuring seam and irradiates to the photoelectric coded discs. A voltage signal is output after the sensitization of the photoelectric battery. The included angle between the solar vector direction and the spinning shaft direction of the satellite can be obtained through executing amplifying, comparing, quantifying and matching processing to the signal by the circuit processing subsystem. The invention realizes the digital sun sensor which has the advantages of large viewing field, high precision, small volume and simple structure, and has important practical meaning for realizing high-precision solar zenith measuring by the stable-spinning micro/nano satellite.

A spacecraft energy-complementing system based on sunlight reflection comprises an energy-complementing serving spacecraft which projects the sunlight to a battery cell which does not face the sunny side according to the space relation between the sun and a served spacecraft, and extra energy is provided for the served spacecraft. The energy-complementing serving spacecraft comprises a spacecraft body, a sun sensor, a sunlight reflector and a target guiding device. The sun sensor is used for measuring the incoming solar angle, the target guiding device is used for measuring the relative dimensional orientation between the served spacecraft and the energy-complementing serving spacecraft, a star computer on the energy-complementing serving spacecraft is used for calculating the pointing of the sunlight reflector according to the incoming solar angle and the relative dimensional orientation, the sunlight reflector is driven by controlling the attitude maneuver of the energy-complementing spacecraft to arrive at the appointed direction, and the sunlight reflector is used for reflecting the sunlight to the solar cell which does not face the sunny side of the served spacecraft.

The invention relates to a method and system for tracing solar angles of solar lighting boards. The method comprises the following steps of: (1) arranging a plurality of solar lighting boards in an array; (2) installing a solar angle detector on a main board, wherein one lighting board in the array is selected as the main board, and the rest ones are taken as slave boards; (3) controlling the elevation and the azimuth of the main board in a manner that a hydraulic pump drives an ejector rod of a hydraulic oil cylinder; (4) converting the elevation and the azimuth of the main board to two voltage signals with different frequencies by an angle sensor of the main board, and transmitting the voltage signals to control circuits of the slave boards in a time division manner; and (5) performing rectification by the control circuit of each slave board according to the voltage signals with the different frequencies received in a time division manner, and adjusting the gestures of the slave boards in a manner that the hydraulic pump drives the ejector rod of the hydraulic oil cylinder so as to ensure that the slave boards and the main board are same in elevation and azimuth. The system is simple in structure and low in cost and energy consumption, has a good tracing effect, is beneficial to the great improvement on a utilization rate of solar energy, and is energy-saving and environment-friendly.

The invention relates to an efficient solar energy automatic tracking method and device. The method includes the steps that first, the outside weather condition is judged, if it is sunny, a photoelectric detection tracking mode is adopted to achieve solar energy automatic tracking, and if it is cloudy or illumination is not sufficient, a sun angle tracking mode is adopted, and in other words, the solar altitude and the azimuth angle are calculated according to real-time time, and solar energy automatic tracking is achieved according to the calculated solar altitude and the calculated azimuth angle. According to the method and device, a photoelectric detection tracking method is combined with a sun angle tracking method, a solar cell panel can change along with changes of the solar altitude and the azimuth angle, the solar cell panel can be kept perpendicular to solar rays all the time, and therefore the efficiency of solar cells is improved. Not only can the sensitivity of the solar energy tracking device be improved, but also interference of weather and other light sources can not happen to the device easily, and the device is high in stability and small in error.

The invention discloses a folding solar automatic tracking device. The device comprises a control system, a containing box, a multilevel laminated solar wing, a driving device, an adjusting device anda folding support. The control system comprises a single-chip microcomputer control module, a photoelectric detection tracking module and a solar angle tracking module. The photoelectric detection tracking module realizes solar automatic tracking through detecting illumination information. The solar angle tracking module realizes the solar automatic tracking through calculating a real-time solarazimuth and an elevation angle. The single-chip microcomputer control module controls orientation of the multilevel laminated solar wing through the adjusting device. The multilevel laminated solar wing is folded, after being folded, the folding support, the driving device and the adjusting device are arranged in a box body. In the invention, tracking efficiency is increased, a light absorption surface of the solar wing is guaranteed to be vertical to solar incident rays under different weather states and different illumination orientations, repeated unfolding and folding motion of the solar wing is realized and an outdoor power generation supply problem is solved.

The invention discloses a magnetic control sun capturing method in consideration of a solar angle change rate and a variable control factor weight. The method comprises the steps of calculating a solar angle, a solar angular velocity and modulus of a magnetic vector change rate; performing sun vector calculation validity determining; when sun vector calculation is effective, performing moment application direction calculation based on a flywheel rotation starting offset finishing condition; performing magnetic moment application direction calculation, and calculating an included angle betweenthe magnetic moment and the moment direction; determining whether the included angle between the magnetic moment and the moment direction is in a range between an upper limit and a lower limit; when the included angle between the magnetic moment and the moment direction is in the range between the upper limit and the lower limit, calculating a magnetic control output according to a rate and solarangle control and solar angle speed compensation algorithm; and performing amplitude limitation on a magnetic control output magnetic moment.

The invention discloses an APS digital sun sensor sun angle calculating method. The sun angle calculating method comprises the steps that the sun facula position of a digital sun sensor is read; an initial sun incidence angle is calculated according to the sun facula position; iterative computation is performed by combining the initial sun incidence angle with the calibration parameters of the digital sun sensor to obtain a sun incidence angle; a corrected two-dimensional sun angle is calculated. The APS digital sun sensor sun angle calculating method greatly improves the sun angle calculation accuracy through sun angle correction and iterative computation of the sun sensor and facilitates improvement of satellite attitude precision.

The invention discloses a solar classroom applicable to solar energy supply. Taking a four-storey teaching building as an example, the solar classroom is characterized in that solar cell panels (1) are arranged on a southern wall, a western wall and roof balconies of the solar teaching building and can be controlled by an industrial controller (3) to be adjusted according to change of the solar angle, so that sunlight can be absorbed to the greatest extent; Fresnel lenses (2) are arranged at edges of a roof, reflectors (2) are arranged on the outer side of each storey of the building, and concave lenses (16) are arranged in each classroom; light rays are gathered via the Fresnel lenses (2), and are guided to the concave lenses (16) in the classrooms via light tanks and the reflectors (2), and each integral classroom is brightened; and the brightness of the inside of each classroom can be controlled by adjusting angles of the Fresnel lenses (2) via the industrial controller (3).

The invention provides a wireless self-powered digital sun sensor comprising a power module, an MEMS (micro electro mechanical system) light leading-in device, a CMOS (complementary metal oxide semiconductor) image detector and an electronic system, wherein the power module is used for supplying power to the wireless self-powered digital sun sensor; the MEMS light leading-in device comprises at least one group of asymmetrical hole patterns; the CMOS image detector is located below the MEMS light leading-in device and used for detecting light led by the MEMS light leading-in device and outputting row light intensity information of a sensing unit of the detector; the electronic system is used for managing energy supplied by the power module, calculating solar angles of two axes according to the row light intensity information and outputting the solar angles of two axes to an upper computer. The sun sensor is high in minimization and autonomous modularization degree, flexible and convenient to use, self-powered, capable of realizing wireless communication and capable of improving the measurement calculation accuracy of the solar angles of the two axes.

The invention provides a tracking method and device for a solar tracker. The method includes: controlling a solar panel of the solar tracker to move to a first place according to the current time parameters and the current position of the solar tracker; determining the second position of the solar panel according to the parameters obtained by a solar angle sensor of the solar tracker; judging whether the corresponding angle difference of the second position and the first position is in the preset angle range; rectifying the corresponding angle of the first position subject to the corresponding angle of the second position when the corresponding angle difference of the second position and the first position is in the preset angle range according to judgment. By means of the tracking method and the tracking device, the problem that the system is unstable caused by the fact that the hybrid control solar tracker in the prior art is greatly influenced by the environment, and the effect of improving the stability of the solar tracker is improved.

The invention provides an integrated micro-nano satellite electronic system. The integrated micro-nano satellite electronic system comprises a satellite core electronic unit, a solar wing driving mechanism, a three-axis gyroscope, a three-axis magnetometer, a simulated solar goniometer, a three-axis integrated micro flywheel, a magnetic torquer, a thermistor, a heater, an initiating explosive device, a measurement and control antenna, a GNSS antenna and a data transmission antenna. The satellite core electronic unit is provided with any one or more of the following interfaces: an analog quantity acquisition interface, a motor drive interface, an initiating explosive device driving interface, a heater drive interface, a magnetotorquer drive interface, a CAN bus interface, a high-speed datatransmission interface, and a radio frequency interface. A traditional satellite subsystem type integration mode is replaced, a satellite core electronic unit serves as an information and energy center, components with other functions are matched, satellite composition is simplified, and miniaturization, light weight and high integration design of the micro-nano satellite is facilitated.