37 results about "Geographical latitude" patented technology

The invention relates to a satellite orbit maintenance and control method based on two lines of radicals, which comprises the following steps of: calculating two lines of radical data disclosed by a satellite by utilizing a SGP4 orbit determination model, calculating and obtaining a geographical latitude and a geographical longitude of a sub-satellite point of the satellite and comparing with an agreed ground nominal track. Through taking the duration of a first sample opposite to an orbit epoch moment as an independent variable and taking the ground track distance difference as a variable, all samples are subjected to quadratic curve fitting by using an average method; the difference delta at between an actual value of a satellite orbit semi-major axis and a nominal value by a latest sample moment as well as the average attenuation rate of the satellite orbit semi-major axis within the time interval of the sample are calculated and obtained through a fitting polynomial coefficient; and finally, the next orbit control time Tc as well as the control quantity delta af required to be used are predicted and obtained by utilizing a fitted secondary curve and an allowable drift range [-delta Lmax and delta Lmax] to ensure that the position of an actual ground track within the satellite next drift period opposite to a ground nominal track is within the allowrable drift range.

The invention discloses an initial attitude acquisition method for a ground test for soft lunar landing by using a SINS (serial inertial navigation system), and belongs to the field of lunar exploration. The method comprises the following specific steps: firstly, arranging a fixed azimuth mirror near a test field, and by adopting the azimuth mirror for buffering, obtaining an attitude transformation matrix of a tester control coordinate system relative to a sky northeast coordinate system of the test field; then, through a geographical latitude of an observation point of the test field, obtaining a transformation matrix of the sky northeast coordinate system of the test field relative to a geocentric coordinate system, so that a transformation matrix C6 of the tester control coordinate system relative to the geocentric coordinate system is obtained, and then an attitude Q0 quaternion at an initial time T0 is obtained finally; starting from the initial time T0, carrying out attitude extrapolation by using gyro measurement data; and obtaining an attitude Qk during a k(th) control period, carrying out real-time output on the Qk until the tester attitude extrapolation process is completed and a landing test begins, wherein the Qk at the moment is taken as an initial attitude of a tester. The method disclosed by the invention is applicable to the ground test for lunar landing.

The invention relates to an automatic latitude measuring and calculating and automatic precision compensating method of a pendulum gyro north seeker. The method is characterized in that the geographic latitude is resolved by utilizing the pendulum period measured by an alidade of the pendulum gyro north seeker under a non-tracking state, and the directive coefficient is calculated, so that the precision compensation of deviation brought about by torsion zero deviating from true north is completed, and the method comprises the four steps of calibrating the relationship coefficient of the period and the latitude, starting a north seeking process, measuring the period under the non-tracking state, resolving the latitude by the non-tracking period, and correcting the torsion zero deviation automatically. Compared with the prior art, the automatic latitude measuring and calculating and automatic precision compensating method of the pendulum gyro north seeker has the advantages that in actual applications, the latitude is not required to be input before measurement, and the directive coefficient is also not required to be calibrated and calculated; through the constant coefficient relationship of the period and the latitude, which is calculated in advance in a calibrating site, the latitude at the site can be resolved only by measuring the non-tracking pendulum period of a measured site, and further a measurement result is corrected. The method can be widely applied to the fields of aviation, aerospace, geodetic measurement, guided missile aiming and the like.

A method for estimating the geographical latitude, longitude and elevation of a mobile electronic telecommunication device (TD) is provided. The method draws random information over a given time period from multiple responders. A triangulation and signal quality analysis is performed to determine the possible location of the TD. Using the statistical information and its analysis the location (x, y and z coordinates) as well as the velocity and acceleration of the device is estimated. The present invention provides extremely accurate location information.

The invention discloses a large-area base station out-of-service alarm monitoring method and system. The method comprises the following steps: S1) acquiring alarm information of wireless base stations of the whole network in real time; S2) normalizing the alarm information of the wireless base stations of the whole network to obtain normalized alarm information; S3) classifying the base stations into a plurality of same-size squares on according to the geographical longitudes and the geographical latitudes, wherein the base stations in the same square are neighbor base stations, and creating a neighboring relation mapping table for each base station; S4) creating a relation chain for the neighbor base stations; and S5) judging whether a large-area base station out-of-service alarm is formed or not according to the change of the number of the base stations on the chain. The invention has the advantages that whether the base stations are out of service in a large area or not can be accurately judged and signal islands or dead zones caused by out-of-service base stations can be avoided.

The invention discloses a simplified design and calculation method of morphological feature parameters of a solar-greenhouse building space, and belongs to the field of energy-saving design of facility agriculture buildings. When a geographical latitude of a construction project site, a vegetable production critical-period which a greenhouse needs to ensure and a span of the solar greenhouse which needs to be constructed are determined, optimal design values of the morphological feature parameters, such as a high-span ratio of the solar greenhouse, rear-roof projection length and north-wall height under a corresponding span condition, of the solar-greenhouse building space can be calculated and obtained according to the method of the invention by consulting local average outdoor-air temperature and daily average total solar radiation amount in the corresponding period. Calculation results show that during an overwintering production period of solar greenhouses, the amount of heat which needs to be provided to the ''optimal-design greenhouse'' is 8340 MJ under a condition of ensuring that greenhouse environment temperature is not lower than 8 DEG C, and is decreased by 14.7% as compared with 9670MJ of the ''current greenhouse'', an energy-saving effect is significant, and an advantageous condition is provided for fully utilizing solar energy or other renewable energy sources as supplemental heat sources by the greenhouse.

The invention relates to a disc projection and splicing method for large view field space to ground observation images and belongs to the space remote sensing detection technology field. The method mainly comprises steps that a conversion matrix between a geocentric coordinate system GEO and a projection disc coordinate system OPC is calculated; a disc projection grid is established on a reference spherical surface in the OPC coordinate system; latitudes and longitudes of grid points and a grid center point are calculated and are then further converted to the GEO coordinate system; the actual projected image point number of two-dimensional array Np storage grid points and a main intensity value of actual projected image points of the two-dimensional array Np storage grid points are calculated; a look vector under each image point satellite coordinate system is calculated and is gradually converted to the OPC coordinate system, and a projection image data matrix, a grid point geographical latitude and longitude data matrix and a grid point center geographical latitude and longitude data matrix are lastly acquired. The method is advantaged in that time sequence observation images are projected and spliced to one grid of the reference spherical surface, so spatial distribution of observation objects can be actually and accurately described through the projection images.

The invention discloses a method for measuring a latitude by utilizing a pendulum gyroscope, which particularly comprises the following steps of: 1, arranging the pendulum gyroscope at a certain station point; 2, measuring a swing period of the pendulum gyroscope; and 3, calculating the geographic latitude of the station point by using an external computer according to the obtained swing period of the gyroscope. The method of the invention has the advantages of simpleness, no need of large-scale ground-to-air connection survey, capability of independently measuring the latitude, higher late-time data processing speed and capability of monitoring variation of the latitude in real time.

The invention belongs to science popularization and teaching instruments, and particularly relates to a celestial sphere instrument with a horizontal height and azimuth angle adjusting mechanism. Theadjusting mechanism arranged in the celestial sphere model of the celestial sphere instrument can adjust a polar axis of the celestial earth to form an arbitrary included angle with a ground plane model so as to meet the requirement of demonstrating the motion operation condition of celestial bodies in any geographical latitude; the polar axis and the ground plane model of the celestial sphere instrument can be freely, conveniently and quickly installed and adjusted to any geographical latitude to be demonstrated along with a meridian circle for global use. According to the celestial sphere instrument, a horizon height circle, an azimuth angle line, an azimuth angle disc, a zenith vertical line and the like are arranged in the celestial sphere model, so that accurate numerical values of horizon height and azimuth angles of any celestial body at any geographical latitude position at any time can be accurately demonstrated and given, great convenience is brought for astronomical observation to find a target as soon as possible, great correct and clear guidance is given to astronomical lovers searching stars, and great help is given to astronomical teaching.

The invention discloses a navigation solution method realized based on an atomic gyroscope navigation system. The method comprises the following steps of S1, constructing coordinate systems for navigation solution, S2, defining navigation parameters including geographic longitude, geographic latitude, geographic height, north speed, east speed, vertical speed and carrier attitude angle, and related physical parameters including platform attitude angle and accelerometer installation misalignment angle, S3, solving the position and the speed of the atomic gyroscope navigation system, and solving the geographic longitude, the geographic latitude, the geographic height, the north speed, the east speed and the vertical speed of the carrier, and S4, calculating the attitude angle of the carrier according to the navigation parameters. According to the atomic gyroscope navigation system and the navigation solution method thereof, a framework of an inertial navigation system for the atomic gyroscope and the navigation solution method of the atomic gyroscope are provided for the first time, the application of the atomic gyroscope in the inertial navigation system is expanded, the error value between each piece of navigation data resolved by the navigation solution steps and actually measured navigation data is small, the precision is high, and the effectiveness and the practicability are high.

The invention relates to a network equipment loophole geographical distribution evaluation system and a network equipment loophole geographical distribution evaluation method and belongs to the information security technical field. The system comprises a geographical distribution evaluation system management center; the geographical distribution evaluation system management center includes an IP address scanning module, an IP address/geographical latitude and longitude conversion module and a geographical distribution concentration ratio calculation module. According to the system and method of the invention, distribution in a network equipment loophole perspective is converted into distribution in a geographical perspective, and therefore, the implementation of safety measures of management institutions in different regions can be mastered and learned more clearly, and the effectiveness of safety management in a whole area can be calculated in a quantified manner.

The invention discloses a gyro measuring instrument being capable of automatically acquiring a geographic latitude and automatically seeking north. The gyro measuring instrument comprises a centeringleveling system, a microcomputer system, a collimating system, a gyro system, and a precision angle measuring and a rotary system. When the instrument is in use, the gyro system measures a geographiclatitude of a to-be-measured point; the gyro system measures a by-north corner of the instrument; and then the collimating system collimates a target point accurately and measures a horizontal rotation angle to calculate a true north angle of a to-be-measured side. According to the invention, problems that the traditional gyro directional instrument cannot obtain the geographical latitude automatically and gyro orientation cannot be performed under the condition of having unknown latitude are solved. The instrument has advantages of high automation degree, simple operation, high orientation precision, strong adaptability of the instrument environment and high anti-interference ability and the like.

The invention relates to the field of internet information processing, and particularly to an enterprise location information acquisition and analysis method used for vertical searching. According to the method of the invention, geographical information of an enterprise is acquired through invoking data interfaces of public platforms, relevant verification and completion are carried out through the information acquired on at least two map platforms, latitude and longitude information with higher credibility is found out to use the same as the geographical latitude and longitude information corresponding to the enterprise, and the accuracy of a result of enterprise latitude and longitude information collection is improved; the acquired information is stored into a distributed file system; and technical support of data acquisition is provided for analysis, querying, business expansion and value mining of a geographical area and location of the enterprise and analysis and mining of hidden geographical region and geographical commerce values.

The invention discloses a sun illumination compensation value calculation method. The method comprises the following steps: obtaining the size, geographic longitude interval, geographic latitude interval, shooting date, shooting moment and shooting position elevation of an optical remote sensing image of a geostationary orbit satellite; calculating the direct radiation intensity and the scatteredradiation intensity of the shooting position of the geostationary orbit satellite optical remote sensing image according to the remote sensing image size, the geographic longitude interval, the geographic latitude interval, the shooting date, the shooting moment and the shooting position elevation; calculating the total solar radiation intensity of the optical remote sensing image of the geostationary orbit satellite according to the direct radiation intensity and the scattered radiation intensity; aiming at the geostationary orbit satellite optical remote sensing images corresponding to different shooting dates, different shooting time and different shooting positions, calculating the difference value between the corresponding solar total irradiation intensities to obtain the solar illumination compensation value between the pixels of each geostationary orbit satellite optical remote sensing image. The method is low in calculation complexity, high in operation speed and easy for engineering realization.