13 results about "Gravitation" patented technology

The invention provides a method for displaying a hotspot keyword. The method comprises the steps of obtaining the hotspot keyword, generating a display body used for displaying the hotspot keyword, implanting the hotspot keyword into the display body, and controlling the display body with the implanted keyword to move towards the bottom end of a rotated web page in a gravity falling mode after the web page where the display body with the implanted keyword is located is rotated. The invention further provides a device and a browser for displaying the hotspot keyword. The display body is generated by obtaining the hotspot keyword, the hotspot keyword is implanted into the display body, and after the web page where the display body with the implanted keyword is rotated, the display body with the implanted keyword moves towards the bottom end of the rotated web page in the gravity falling mode. Therefore, dynamic and stereoscopic display of the hotspot keyword is achieved, the display effect is improved, the visual sense is enriched, and the interaction performance is high.

The invention provides a multifunctional cycle power generation system and method by a gravity lever. The system comprises a supporting rack and a balance weight arranged on the supporting rack and slidably matched with the supporting rack, wherein engines are arranged on one side or two sides of the balance weight; the input shaft of each engine is connected to a transmission shaft; two or more single-directional clutches are fixedly connected to the middle of the transmission shaft; the locking directions of the single-directional clutches are same, gears are fixed to the peripheries of thesingle-directional clutches, and a rack matched with each gear to drive the transmission shaft to rotate is arranged next to each single-directional clutch; at least one pair of racks is arranged on the upper part and the lower part, separately, the racks and the balance weight which reciprocates are in driving movement and the balance weight is arranged on the supporting rack to swing through a lifting mechanism in a reciprocating manner. As the balance weight which swings in the reciprocating manner pulls the racks to drive the transmission shaft to rotate in the single direction, multiple engines can be driven synchronously to generate electricity synchronously, and the power needed by a supporting rack lifting device is alleviated greatly by means of a swing mode like to a lever, so that the energy sources are saved and the power generation efficiency is improved greatly.

In the current space navigation, communication, and defense technologies, it is difficult to integrate local control of time, gravity operation, use of dark matters, and communication with the outer space (the Buddhist monk Tenkai's gyrus), and intergalaxy communication, ultrahigh-speed movement, and creation of a time acceleration / deceleration space cannot be realized by modern technologies.SOLUTION: The present invention is a future note related to an ultra-future space technology capable of integrally operating time, gravity, and material behavior by performing local and large-scale dark matter control by a BHc / WHc gate based on a dark matter fluid space model and a space gate theory.SELECTED DRAWING: None

A kind of relative navigation reference deviation calibration method of star and pulsar information fusion is disclosed, which comprises the following steps: configuring a star angular distance measuring sensor and an X-ray detector on a spacecraft; observing stars by the star angular distance measuring sensor to extract navigation information contained in two kinds of relativistic effects, i.e., star aberration caused by the movement of the spacecraft and light deflection caused by celestial gravitational field; observing pulsars by the X-ray detector to obtain pulse arrival time difference observations; combining spacecraft and earth orbit dynamics model to predict the state; processing star angular distance and pulse arrival time difference observations by an extended Kalman filter to correct the state prediction value, and obtaining the estimation of the spacecraft position and velocity, the geocenter position and velocity, and the sensor system error parameters, so as to realize the calibration of two kinds of reference deviations, i.e., earth ephemeris error and sensor system error. The present application provides a new way to improve the performance of relativistic navigation system.

The invention relates to the technical field of satellite orbits, in particular to a sun-synchronous orbit dip angle offset calculation method and device, equipment and a medium. According to the method, an orbit perturbation equation containing earth non-spherical gravity and atmospheric damping perturbation is constructed, and the influence of semi-major axis attenuation caused by atmospheric resistance on the inclination angle offset is considered. According to the method, the influence of atmospheric damping on the orbit height and different orbit height maintaining strategies are comprehensively considered, more accurate orbit injection parameters are calculated in combination with the prior art, and a more reliable guarantee is provided for subsequent on-orbit normal operation of a spacecraft. In the initial stage of orbit design, more accurate spacecraft orbit injection parameters can be calculated by introducing more perturbation models. The orbit height maintaining strategy is also considered, which means that the later-stage spacecraft in-orbit operation and maintenance cost is also considered, the engineering implementation is more reliable, the result is more accurate, and meanwhile, flexible adjustment can be realized by fully combining actual conditions.

A planetary learning device is provided. The device is comprised of a body that may take various geometric shapes resembling celestial objects, such as planets or stars, and may incorporate phosphorescent materials and LEDs for simulating natural celestial phenomena. The device also includes at least one speaker for providing audio content related to the celestial object, with facts or scientific data being played via a removable memory card or streamed wirelessly. The body can be charged through a docking station, which may include a rotating platform to simulate planetary motion. Additionally, the device features sensors for interactive functionality and may include an augmented reality application for enhanced learning. A vibration motor can further simulate seismic activity or gravitational forces, offering an immersive educational experience.

The invention relates to a method for calculating the east gradient of a sea area disturbing gravity prime component, and provides a method for calculating the east gradient of the sea area disturbing gravity prime component aiming at the disturbing gravity prime component auxiliary navigation requirement of an inertial navigation system under the constraint of a sea area motion carrier position error. And constructing a sea area perturbation gravitational prime component east gradient calculation model based on a completely normalized global gravitational potential coefficient by utilizing a physical geodetic boundary value theory to realize sea area perturbation gravitational prime component east gradient calculation. The invention aims to improve the disturbance gravity prime unitary component aided navigation capability of the inertial navigation system under the constraint of the position error of the motion carrier and improve the navigation precision of the inertial navigation system.

The application discloses a high-precision space target orbit prediction method based on numerical fitting, and relates to the technical field of space target orbit prediction.The frequency domain decomposition of the application is combined with a harmonic compensation model to completely eliminate seasonal system drift caused by the gravitation of the sun and the moon; high-frequency components are stripped of attitude noise through light pressure parameterization and smooth difference to avoid the transmission of perturbation coupling error; a harmonic order adaptive mechanism captures the main disturbance term with the least amount of calculation; least square batch estimation realizes one-time solution of coefficients; template library preloading technology effectively compresses the time consumption of new target initialization; in addition, the application introduces a geomagnetic modulation factor to dynamically suppress compensation distortion during magnetic storms, and a sliding window mechanism guarantees real-time updating of coefficients, and stable prediction is still maintained under extreme events; photometric curve inversion is adopted instead of attitude measurement to make non-cooperative target prediction possible; tangential component directional compensation ensures the stability of the orbit plane and reduces satellite position fuel consumption.

The present application discloses a small celestial body offset efficiency evaluation method based on state transition tensor, and belongs to the field of spacecraft orbit mechanics. The method of the present application is as follows: a multi-body system dynamics model is established, the impact geometry of the small celestial body relative to the earth is calculated, and the state transition tensor of the small celestial body orbit is derived, so as to quickly calculate the influence of the initial state change of the small celestial body on the impact geometry, and obtain the orbit offset caused by the impact of the impactor when the earth's gravity is dominant after the small celestial body approaches the earth; the second-order state transition tensor is used to obtain the orbit offset of the small celestial body after a period of time, and the high-efficiency quantitative evaluation of the offset efficiency of the small celestial body after being impacted by the impactor is realized. By fixing the velocity deviation and changing the position and direction of the applied deviation, the optimal change direction corresponding to the optimal offset efficiency of the small celestial body orbit can be determined. The present application has the advantages of high evaluation accuracy and high efficiency, and is suitable for offset strategy selection and efficiency evaluation of small celestial body defense tasks.

The application discloses a kind of small celestial body overall stress analysis method, comprising the following steps: (1) for small celestial body, its boundary is, a spherical surface is set to its complete encirclement outside small celestial body, the three-dimensional space surrounded by spherical surface is recorded as;(2) the spherical surface is discretized, generates triangular grid, the area and unit normal vector of each triangle element are calculated, and are recorded as and;(3) the gravity vector of triangle element center is obtained, and is recorded as;(4) is substituted into formula (), and the resultant force that small celestial body is received is calculated.

This invention discloses a precise orbit determination and astronomical ranging method based on equivalent optical path bending correction using celestial body motion position offset, relating to the fields of aerospace telemetry and control and astronomical observation technology. This invention is based on the premise that light always travels in a straight line, abandoning the traditional approach of modeling light beams by gravitational self-deflection and spacetime curvature. It utilizes the fixed duration of light propagation, during which high-speed motion of celestial bodies generates misalignment of transmission and reception points, forming a real physical mechanism of equivalent optical path bending at the measurement level. The method models and calculates the offset and time delay corresponding to the equivalent bending, corrects errors in the original measured data, calculates the true absolute position of the target, deduces the orbit, and implements pre-orbit compensation for the satellite. This invention conforms to objective physical laws, has high correction accuracy, significantly reduces the frequency of satellite orbit fine-tuning, saves fuel and manual maintenance costs, requires no hardware modifications, and can be widely applied in aerospace telemetry and control, deep space exploration, and astronomical observation.

The embodiment of the invention provides a device for judging the motion balance state of an object based on attractive force and magnetic force, which analyzes the interaction among a plurality of objects in periodic motion, particularly uniform circular motion, based on the attractive force and magnetic force, so as to predict the information of the objects, such as the motion direction, the motion plane and the motion period when the objects reach the balance state. In a specific embodiment, the formation reason of a galaxy disc shape is analyzed, the inclination angle of earth rotation is calculated, and the possibility of developing a corresponding gravitational magnetic device by referring to an existing electromagnetic device is analyzed.

The invention discloses a potential threat asteroid-based virtual impact earth asteroid data set generation method, system and product. The method comprises the following steps: inputting orbit data of a real potential threat asteroid group, and setting impact time; solving a corresponding earth position, and calculating and generating initial orbit elements of a virtual impact body including ascending node longitude, near point argument and true anomaly under a heliocentric two-body dynamic model on the basis that the impact occurs at the ascending node or the descending node; with the initial orbital element as an initial value, correcting the orbital element of the virtual impactor by adopting a differential correction algorithm in a high-precision dynamic model of the solar system, so as to accurately impact the earth at the impact time; a planetary gravity capture model is adopted to optimize an impact orbit, and the perigee height of a virtual impact body is corrected to a proper range; carrying out reverse recursion on the optimized perigee orbit parameters to the outside of the earth gravity influence ball, converting the position speed into orbit elements, and obtaining the sun center orbit elements before the virtual impactor impacts the earth; and obtaining a data set.