18 results about "Gravitational field" patented technology

An unidentified aerial phenomena field disturbance detector includes an accelerometer configured to measure a gravitational field surrounding the unidentified aerial phenomena field disturbance detector; a magnetometer configured to measure a magnetic field surrounding the unidentified aerial phenomena field disturbance detector; a microwave frequency detector configured to measure a specific band of microwave frequencies surrounding the unidentified aerial phenomena field disturbance detector; a controller; and an optical indicator configured to optically communicate information to a user of the unidentified aerial phenomena field disturbance detector. The controller determines a change in the gravitational field surrounding the unidentified aerial phenomena field disturbance detector when generates gravitational field values are outside a predetermined range of non-event field values. The controller controls the optical indicator to optically communicate the determined change in the gravitational field surrounding the unidentified aerial phenomena field disturbance detector.

The invention relates to a geological fracture recognition method based on multi-source geophysical data and a computer system, and solves the problem of high-precision recognition of tiny fractures and complex fracture zones. The method comprises the following steps: acquiring gravitational field model data, full-tensor gravity gradient data and aeromagnetic data of a target area, and carrying out gridding processing, pole conversion processing and edge expansion preprocessing on the data; performing boundary identification calculation on the preprocessed data by adopting a traditional physical field multi-derivative algorithm to generate a first group of boundary information A; carrying out boundary recognition calculation on the preprocessed data by adopting a gravity and full-tensor gravity gradient combined derivative algorithm (an enhanced total horizontal gradient derivative algorithm, a combined derivative algorithm and a combined oblique derivative algorithm) to generate a second group of boundary information B, and carrying out boundary recognition calculation on the preprocessed data by adopting an image edge detection algorithm to generate a second group of boundary information B; generating a third group of boundary information C; and carrying out weighted fusion on the three groups of boundary information to obtain a final fracture identification result.

The invention provides an island small landslide early warning method based on gravity sensing and a related device. The method comprises the following steps: respectively collecting gravity data and environment interference data of a target island in real time by using a gravity sensing sensor array and an environment sensing sensor; performing interference correction on the gravity data based on the environment interference data to obtain corrected gravity data; mapping the corrected gravity data into a three-dimensional coordinate system of the target island, and generating a gravity field space distribution matrix; based on the gravitational field spatial distribution matrix, marking an area with gravity anomaly in the target island as a potential anomaly area; and performing prediction based on gravity data corresponding to the potential abnormal area in the corrected gravity data by using the trained landslide early warning model, and performing small landslide early warning on the target island when determining that the predicted landslide occurrence probability is greater than a preset early warning threshold. According to the invention, high-sensitivity and extreme-weather-resistant real-time monitoring and accurate early warning of small landslides of islands and reefs can be realized.

A method for direct measurement and profiling of electromagnetic energy from a star at a known distance from the observer entails collecting photons from the star with a camera through a telescope or lens of a given aperture area up to the known full well depth of the camera's image sensor, determining the time needed to reach the sensor's full well depth, using that collection time and the sensor's bandgap and sensitivity characteristics at full well depth to calculate the energy received per second through the aperture area, determining the number of aperture areas needed to cover the surface area of a sphere with a radius equal to the star's distance, and determining the total energy output of the star by multiplying the determined electromagnetic energy received through the aperture area by the number of apertures needed.

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 discloses a geocentric orbit space gravitational wave detection-oriented earth free oscillation waveform rapid generation method and system, which are used for solving the problems that the calculation process of the existing earth free oscillation waveform generation method is complicated, the time consumption is serious, the requirements of rapid noise evaluation and elimination in a task are difficult to meet, and the reliability is poor. And the calculation efficiency of the earth free oscillation waveform is low. The method comprises the following steps: acquiring earth gravitational field parameters and an inter-satellite instantaneous distance, and constructing an inter-satellite distance measurement acceleration analysis model by adopting a Couwurah linear perturbation method; correcting based on an earth free oscillation model, and determining a corrected inter-satellite distance measurement acceleration analysis model; when satellite orbit parameters, a simulation time sequence and earth free oscillation mode parameters are received, distance measurement acceleration signals among multiple satellites are calculated through the correction model; and selecting a target ranging acceleration signal, performing earth oscillation signal extraction on the target ranging acceleration signal by adopting a time delay interference method, and finally outputting a target earth oscillation signal.

The application belongs to the technical field of space gravitational wave detection, and specifically discloses a gravitational effect finite element simulation method based on solving gravitational field partial differential equations, which comprises the following steps: inputting a weak form of the gravitational field partial differential equation in a physical field developer of simulation software COMSOL to construct a gravitational field interface plug-in; importing a spacecraft model into the simulation software COMSOL and constructing a space around the spacecraft; inputting a definite condition in the gravitational field interface plug-in; determining a gravitational potential through mesh partitioning and the gravitational field interface plug-in, and determining the gravitational field intensity of the spacecraft and the surrounding space based on the gravitational potential; and performing an integration operation on the test mass in the spacecraft based on the gravitational field intensity of the spacecraft and the surrounding space to determine the gravity and the gravity torque that the test mass receives. Through the application, the self-gravitational effect calculation process can be effectively simplified, and the gravity that an object with any shape receives can be calculated.

The invention relates to a gravity gradiometer comprising at least two vehicles (V1, V2), each comprising an inertial measurement unit (UMI1, UMI2) and a control unit (COM1, COM2) for controlling the vehicles along paths having separate segments for performing inertial-measurement-unit reversals and coupled segments for exchanging inertial measurements. At least one of the electronic control units is arranged so to determine, in particular from the exchanged measurements: a transformation matrix between the inertial reference frames, a correction of the linear-acceleration measurements based on an observed accelerometric model, a correction of the angular-velocity measurements based on an observed gyrometric model, and a gradient of the gravitational field. The invention also relates to a navigation system comprising such a gravity gradiometer.

This application relates to the field of accelerated transport technology, specifically to a cyclic superposition acceleration method and system based on a gravitational field. The method includes: determining the trajectory of a load unit around a natural gravitational field; arranging several acceleration units at intervals along the trajectory; placing the load unit on the trajectory and assigning it an initial velocity; and controlling the acceleration units to provide acceleration energy to the load unit as it passes through them. This application can utilize the natural gravitational environment to achieve stable, low-loss cyclic acceleration, meeting the high-efficiency operation requirements of long-distance transport.

This invention provides a rapid prediction method for lunar orbit rendezvous guidance, achieving high-precision and rapid prediction to meet mission requirements. The prediction method of this invention applies the gravitational field acceleration calculation method used for GPS autonomous orbit determination of Earth orbit satellites to the field of lunar orbit rendezvous. Addressing the problems that the algorithm cannot be directly applied to the design of lunar orbit rendezvous guidance strategies, improvements and upgrades are made one by one, resulting in a high-precision and rapid algorithm suitable for lunar orbit rendezvous flight control missions to meet mission requirements. Specifically, this invention is the first to transplant this algorithm to the field of lunar orbit applications, which is unprecedented. Considering the special characteristics of the lunar gravitational field, where the acceleration measures of various gravitational perturbations are of similar order and cannot be approximated by the J2 term alone, the J22 term perturbation acceleration is added to the algorithm, thereby significantly improving the computational accuracy and numerical stability of the algorithm.

The present application relates to the technical field of measurement, and particularly to a method for measuring speed with a gravitational field as a reference system, which can measure the speed of a substance without an external physical reference system. A reference object having a direct force interaction with the substance is an absolute reference system, such as light or electromagnetic waves propagating in a gravitational field or a substance, which has a direct force interaction with the field or the substance. Relative to the light, the gravitational field and the substance are absolute reference systems of the light. Because of the existence of the absolute reference system, when the substance has a relative speed relative to the field, the speed of the substance itself can be measured by the optical path (the optical path refers to the propagation path length of light or electromagnetic waves) of the field, and this process is the speed measurement with the gravitational field as a reference system.

The invention proposes a Gravitational and Magnetic Force to Electrical Energy Conversion System (GMECS), a solution based on the simple pendulum principle and developed from the successful foundation of the "Large-sized clock, low power consumption" invention (internationally published by WIPO in 2022). GMECS overcomes the inherent challenges of using a simple pendulum for large-scale electricity production by optimally and effectively combining the interaction of the Earth's gravitational field with the powerful magnetic field of Neodymium N52 rare-earth magnets and the controlled variable magnetic field of an electromagnet to generate significant and continuous torque. In this system, the pendulum's oscillation energy, maintained and amplified by a small amount of electrical energy from an external source (e.g., solar power), is converted into mechanical energy through a complex gearbox system comprising a one-way gearbox and a reversing gearbox. This mechanical energy is then transmitted to a speed-increasing gearbox to augment rotational speed, thereby rotating the rotor of a rare-earth magnet generator, producing useful electrical energy. Experiments have demonstrated the system's superior capability to generate 22W of output power with only 8.7W of input power, showing a positive and significant energy amplification factor (COP > 2.5). This additional energy is attributed to the efficient harnessing from the relative motion of the hundreds-of- kilogram pendulum within the Earth's gravitational field and the interaction between the magnetic field of rare-earth magnets and the controlled variable magnetic field of the electromagnet, via the pendulum's resonance mechanism. This successfully addresses technical challenges, including overcoming the inertia of the speed-increasing gearbox, the generator, and the Lenz's Law effect. The GMECS invention has the potential for scalable electricity production, offering significant benefits in energy savings, providing independent distributed power, being environmentally friendly, and having broad applicability in both industrial and agricultural sectors, especially in areas difficult to access traditional energy sources or requiring sustainable energy solutions.

This invention discloses a physical phenomenon experience learning system based on immersive virtual reality technology, comprising at least a hardware perception layer, a software platform layer, a core logic layer, and a functional module layer. In corresponding scenarios, dynamic commands are implemented through the hardware perception layer, and material attribute parameters in the physics dynamics engine are adjusted through the core logic layer to achieve interaction within the scene. This system deeply integrates experiential education concepts with virtual reality technology. By constructing a high-precision physics engine-driven, high-fidelity scene, it reconstructs ideal observation conditions such as resistance-free and customizable gravitational fields in virtual space. This facilitates a more intuitive, vivid, and cost-effective way for primary and secondary school students and the general public to overcome the limitations of real-world time and space, personally conduct classic and surreal physics experiments, effectively enhance their sense of spatial presence, and deepen their understanding of abstract physics knowledge.

The invention provides a dynamic full-link simulation method and system for space gravitational wave detection spacecraft formation. A multi-physical field model, a full-link noise model and drag-free control are fused to carry out system-level simulation. The method comprises the steps that firstly, multi-physics field models such as a temperature field, a magnetic field and a self-gravitational field are established, optical measurement noise and residual acceleration noise models are combined and input to a spacecraft formation orbit dynamics and drag-free control system, then the drag-free control model feeds satellite state information after control back to the multi-physics field models, system-level closed-loop simulation is carried out, and the system-level closed-loop simulation is carried out. State changes of the spacecraft are dynamically analyzed, scientific measurement data are output to evaluate the sensitivity of the spacecraft formation space gravitational wave detection system, a multi-physical field noise transmission rule among an instrument, the spacecraft and the environment is disclosed, and space gravitational wave detection spacecraft formation dynamic full-link simulation is achieved.

The application discloses a design method of a gravity wave detection equilateral triangle formation based on a second-order CW equation, and comprises the following steps: designing a nominal configuration of a gravity wave detection equilateral triangle formation by using a CW equation, to obtain nominal relative positions and nominal relative velocities of three spacecrafts; constructing an optimization design model of the gravity wave detection equilateral triangle formation based on the second-order CW equation, to obtain correction amounts of the gravity wave detection equilateral triangle formation based on the nominal relative positions and the nominal relative velocities; and correcting the relative positions and the relative velocities of the three spacecrafts based on the correction amounts of the gravity wave detection equilateral triangle formation, to obtain a new gravity wave detection equilateral triangle formation. The method realizes correction of the equilateral triangle formation designed based on the CW equation, and reduces divergence of formation arm length and breathing angle in a two-body nonlinear gravitational field.

This invention proposes a cooperative search method for underwater unmanned underwater vehicles (UUVs) based on an improved gravity search algorithm, relating to the field of UUV search. The method includes: deploying multiple virtual particles within the search area to form a gravitational field; dynamically updating the mass and orientation preference states of each particle during the search process; calculating the basic gravitational force acting on each UUV and performing orientation-sensitive corrections to obtain the total attractive force; calculating the repulsive force between the UUVs and modulating the repulsive force to obtain the total repulsive force; synthesizing the total attractive and repulsive forces to obtain the total resultant force, resulting in a new course and velocity; updating the position of the UUVs based on the new course and velocity, detecting and avoiding search area boundaries and obstacles, and updating the state of the detected particles. This invention achieves efficient adaptive cooperative search of an underwater UUV swarm by constructing a gravitational field using virtual particles.

An unidentified aerial phenomena field disturbance detector includes an accelerometer configured to measure a gravitational field surrounding the unidentified aerial phenomena field disturbance detector; a magnetometer configured to measure a magnetic field surrounding the unidentified aerial phenomena field disturbance detector; a microwave frequency detector configured to measure a specific band of microwave frequencies surrounding the unidentified aerial phenomena field disturbance detector; a controller; and an optical indicator configured to optically communicate information to a user of the unidentified aerial phenomena field disturbance detector. The controller determines a change in the gravitational field surrounding the unidentified aerial phenomena field disturbance detector when generates gravitational field values are outside a predetermined range of non-event field values. The controller controls the optical indicator to optically communicate the determined change in the gravitational field surrounding the unidentified aerial phenomena field disturbance detector.