13 results about "Earth's rotation" patented technology

This invention provides a satellite onboard orbit conversion method and system. The method includes: calculating the corrected Julian day at the current time and calculating the Greenwich Mean Sidereal Time Angle based on the corrected Julian day; converting the Greenwich Mean Sidereal Time Angle into radians; calculating the Earth rotation matrix from the J2000 system to the WGS84 system based on the converted radians; pre-calculating the Earth nutation and precession correction matrices as modifiable parameters for satellite commands and updating them periodically; calculating the conversion matrix from the J2000 system to the WGS84 system based on the Earth nutation and precession correction matrices and the Earth rotation matrix; and calculating the satellite position and velocity in the WGS84 system based on the conversion matrix, thereby realizing the satellite onboard orbit conversion. This invention addresses the need for converting EP satellite onboard orbit information from an inertial frame to the WGS84 coordinate system, meets the requirements for short message stand-alone operation, and can provide a reference for on-orbit conversion of other satellites.

To provide a compact and easy-to-use azimuth detection method, azimuth detection device, and surveying device. [Solution] The system includes a sensor unit 7 that detects tilt and rotation relative to the horizontal, and a flywheel 18 provided on the sensor unit that has a rotation axis extending in the vertical direction. The flywheel is rotated at a constant speed, and the flywheel is tilted to generate a gyroscopic moment in order to counteract the change in tilt that occurs in accordance with the rotation of the Earth, and the direction of the Earth's axis (north or south) can be determined from the direction of the gyroscopic moment.

The invention relates to a method for determining an azimuth angle (α) between a sensitive axis (z) of a quantum-based NMR gyroscope (100) and a geographic north direction (N), the method comprising aligning the sensitive axis (z) of the quantum-based NMR gyroscope (100) in a first measurement direction, which in particular runs substantially parallel to an Earth's surface, and determining a first Earth rotation (ω). R ), aligning the sensitive axis (z) of the quantum-based NMR gyroscope (100) in at least one second measurement direction, which in particular is essentially parallel to the Earth's surface and which differs from the first measurement direction, and determining at least one second Earth rotation, and determining the azimuth angle (α) from the first Earth rotation (ω) R ) and at least one second Earth rotation. The invention further relates to a gyrocompass (10).

At present, the world is suffering from air pollution due to thermal power generation, sea level rise due to atmospheric temperature rise, land sinking due to rising of the sea level, and public nuisance due to nuclear power generation, such as spent depleted uranium, plutonium, and.gamma.-ray radioactive materials. In order to solve these problems, inexhaustible visible-light wave power generation of sunlight radiation energy and a Huang Daozhou converter are integrated.SOLUTION: The secondary coil of the ecliptic transformer according to the present invention may be connected to a country having a shortage of electric power at night due to the rotation of the earth and a country having a shortage of electric power due to a large amount of power consumption even in the daytime via the shortest conductor on the same longitude to transmit and receive electric power.SELECTED DRAWING: Figure 1

This invention discloses a method for calculating the sub-satellite point based on the SGP4 orbital model, relating to the field of satellite navigation and orbit prediction technology. The polar spherical projector of this invention eliminates longitude jumps in latitude >75°, ensuring continuous trajectory output for scenarios such as polar scientific expeditions and glacier monitoring. By directly mapping three-dimensional radial information to generate latitude, it avoids the iterative convergence problem of the ellipsoidal model, ensuring natural symmetry of the North and South Poles coordinates and continuous longitude domain. Second-order differential compensation of the mean anomaly angle, combined with dynamic correction of the Earth's rotational angular velocity, strictly aligns the UTC timestamp with the orbital position. It suppresses the cumulative error generated by traditional linear interpolation at perigee. It enhances adaptability to complex perturbation environments; atmospheric drag vectorization compensation captures real-time aerodynamic direction through relative velocity cross terms, combined with continuous processing of the density index model, significantly improving the orbital attenuation prediction accuracy of low-Earth orbit satellites during geomagnetic storms.

The invention provides a heterogeneous orbit constellation configuration regression period determination method and system, and the method comprises the steps: finding a group of coprime operation turns and regression number for each satellite, and enabling the operation turns and the regression number to meet the condition that the ratio of the operation turns to a first set parameter is equal to the ratio of the regression number to a second set parameter, the regression period of the satellite can be obtained; wherein the first set parameter is the sum of the average change rate of the perigee argument and the average change rate of the mean anomaly; the second set parameter is the difference between the earth rotation angular velocity and the right ascension precession rate of the ascending node; and calculating the least common multiple of the time periods of all satellites to obtain the regression period of the constellation. The method has the advantages that compared with a traditional method, the efficiency is improved by 13.3% when compatibility analysis is carried out on the regression cycle calculated through the method, and the maximum interference level in the regression cycle is consistent with that of annual simulation.

In various aspects, a power-generating device is provided. The power-generating device may include a three-dimensional structure. The three-dimensional structure may be composed of a conductive material having (i) a magnetically permeable material having a topology that alters Earth's magnetic field such that curl (v×B)≠0, where v is Earth's velocity of rotation and B is the component of Earth's magnetic flux density symmetric about Earth's axis of rotation and (ii) a magnetic Reynolds number less than ten (Rm<10). The three-dimensional structure may be configured to generate power and heat when carried with Earth's rotation via Earth's axially symmetric non-rotating magnetic field.

The invention discloses a method for evaluating the access capability of an artificial satellite to ground targets at different latitudes. Belongs to the field of aerospace dynamics and artificial satellite orbits. The method is based on mathematical modeling, main features of an orbit dynamics physical model are extracted, and the access capability of a satellite constellation to a ground specified latitude target is rapidly evaluated with low calculation cost, including the number of access windows and the total access duration in a given time period. According to the method, satellite motion is simplified into an elliptical orbit dominated by two-body gravitational force, and a static annulus model formed by projection of a satellite side-sway range on the earth surface is introduced; by analyzing the geometrical relationship and the time characteristic that a ground target passes through the annulus along with earth rotation, and combining a satellite orbit period and an earth rotation period, an analytical expression of the access probability, the window number and the time length is deduced. The method can effectively estimate the distribution of the access capability along with the latitude, does not need a large amount of numerical simulation, and remarkably improves the calculation efficiency.

The application provides an on-orbit satellite-ground one-way distance correction method considering the rotation of the earth, and the measuring equipment used comprises: an on-orbit satellite and a ground station; a distance correction module is added in the satellite-ground distance measuring system of the ground station, which comprises: a satellite-ground distance measuring model is established in the satellite-ground distance measuring system of the ground station without considering the rotation of the earth, and the satellite-ground distance without considering the influence factors of the rotation of the earth is obtained by using a relay ranging method; the projection of the displacement of the ground station along the satellite-ground connecting line caused by the rotation of the earth is calculated according to the rotation speed of the earth and the geographical latitude where the satellite-ground station is located; the asymmetric satellite-ground distance is corrected by using the projection distance correction, and high-precision satellite-ground one-way distance is obtained.

The invention discloses a ground velocity excitation-based atomic interference gyroscope scale factor calibration method, which comprises the following steps of: firstly, obtaining an actual measurement value corresponding to an atomic interference gyroscope scale factor according to an earth rotation fitting experiment, establishing a linear model of an input / output relationship of an atomic interference gyroscope, and calculating the scale factor of the atomic interference gyroscope by changing the direction of an inertial measurement unit in a horizontal plane; synchronously recording the output phase of the triaxial cold atom interference gyroscope, obtaining the excitation of the corresponding earth rotation angular velocity to the three axes of the cold atom interference gyroscope according to the excitation of the earth rotation angular velocity to the atom interference gyroscope, and simultaneously obtaining the scale factors of the three gyroscopes of the inertial measurement unit by utilizing least square fitting; according to the method, the calibration factors of the atomic interference gyroscope and the triaxial atomic interference gyroscope in the inertial measurement unit can be synchronously calibrated, and the requirement of the inertial measurement unit based on the cold atom interference gyroscope on calibration conditions during calibration at the present stage is reduced.

This invention discloses a closed-loop celestial object tracking and imaging method and system based on real-time analysis of starry sky images. The invention identifies celestial objects from starry sky images and calculates imaging parameters; based on Earth rotation data and current field-of-view parameters, it calculates the instantaneous linear drift velocity and field rotation angular velocity of the celestial object to be tracked on the image sensor plane. The long-exposure drive signal is compensated based on the calculated instantaneous linear drift velocity and field rotation angular velocity of the current frame and adjacent frames to counteract star point drift during the long exposure process. Alternatively, by calculating the relative displacement and rotation angle between adjacent frames and the current frame in consecutive short-exposure images, each subsequent frame is aligned, and all frames are pixel-level superimposed to synthesize the final long-exposure image. This invention achieves significant simplification in hardware cost and structure, requiring only one imaging unit to complete high-precision pointing calculation and drift compensation.

This invention proposes a method for joint calculation of Earth rotation parameters and short-term forecasting using regional network satellite-ground-satellite joint methods, belonging to the field of satellite navigation technology. This invention utilizes satellite-ground observation data from a limited number of regional stations, along with inter-satellite link measurement data, to perform joint orbit determination and ERP parameter calculation. Considering the limited amount of accumulated ERP data, a real-time short-term ERP forecasting method based on historical calculations is employed, and the method is compared with IERS CO4 for accuracy evaluation.

In various aspects, a power-generating device is provided. The power-generating device may include a three-dimensional structure. The three-dimensional structure may be composed of a conductive material having (i) a magnetically permeable material having a topology that alters Earth's magnetic field such that curl (v x B)≠0. where v is Earth's velocity of rotation and B is the component of Earth's magnetic flux density symmetric about Earth's axis of rotation and (ii) a magnetic Reynolds number less than ten (R m < 10). The three-dimensional structure may be configured to generate power and heat when carried with Earth's rotation via Earth's axially symmetric non-rotating magnetic field.