11 results about "Gravitational wave" patented technology

A system can produce localized spacetime distortions, gravitational waves, sudden transitions in the index of refraction and optical path length changes via high-energy plasma formation. The system includes a high-energy spark-gap arrangement, where an electrical discharge between tungsten tips produces extremely high energy densities in a localized region. The system is tunable and can be driven by either constant or time-varying voltage sources, allowing for different distortion profiles and electromagnetic emission patterns. The system can operate in various environments, including air, inert gases such as helium, and even in vacuum conditions. Multiple spark-gap assemblies can be arranged to create customized distortion shapes and enhanced field effects.

The invention discloses a multi-target collaborative optimization design method for a space gravitational wave telescope and the space gravitational wave telescope, and solves the technical problem that an existing space gravitational wave telescope design method is difficult to consider wavefront quality, TTL noise suppression, backward stray light control and engineering installation and adjustment feasibility at the same time. The method is characterized in that TTL noise is used as a direct optimization target parallel to a wavefront error, and a space gravitational wave telescope with high robustness on angular jitter and platform micro-vibration is designed by using a minimum Prewitt gradient weighted joint optimization algorithm.

This application discloses a method and system for real-time inference and parameter inversion of gravitational wave events based on deep learning. The method includes: constructing a physics-instrument dual-manifold decoupled network; extracting physics signal features and instrument noise features from time-frequency spectra; introducing physical manifold constraints and orthogonally decoupling the features in the latent space; performing parameter inversion on the decoupled physics features using a conditionally normalized flow model; and verifying the consistency of the inference results by regenerating the waveform in reverse and analyzing the residuals. This application distinguishes between high-eccentricity gravitational wave signals and detector transient noise, improving recognition accuracy and reducing false alarm rate.

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 discloses a gravitational wave detection formation configuration long-term stability prediction method and system based on Fourier series, and belongs to the technical field of spaceflight science and technology. The method comprises the following steps: firstly, obtaining an initial value and a prediction time length of each spacecraft orbit element in a formation, and extracting orbit element long-term item data by solving an orbit element perturbation differential equation set and utilizing a double average method; establishing a Fourier series model of a spacecraft orbit element long-term item; a semi-analytical model for describing the long-term change rate of the arm length, the respiratory angle and the directional angle of the configuration stability is constructed by further combining the space geometrical relationship between spacecrafts, the semi-analytical model comprises a linear part and a non-linear part, and the non-linear part comprises a composite function representing the influence of the lunar gravitational perturbation; and establishing a semi-analytic prediction relationship between the initial orbit element and the initial orbit element and the prediction duration of the spacecraft. According to the invention, rapid and direct prediction of the long-term stability of the formation configuration is realized.

This invention belongs to the aerospace field and relates to a method for estimating the inter-satellite arm length of three satellites based on capacitive Kalman filtering. The method involves: for the primary satellite and two secondary satellites in a three-satellite gravitational wave detection formation, employing formation-specific nonlinear dynamics modeling, estimating the relative states between the primary and secondary satellites based on capacitive Kalman filtering, and thus obtaining the arm length information between the satellites to achieve three-satellite inter-satellite arm length estimation. This invention effectively suppresses the numerical divergence problem caused by matrix ill-conditioning in traditional Kalman filtering by manipulating the square root of the covariance matrix instead of the original matrix. The capacitive rule achieves third-order accuracy approximation while requiring only a linearly increasing number of sampling points, significantly outperforming computationally expensive methods such as particle filtering. This method is particularly suitable for scenarios with strong nonlinearity and weak observability in satellite dynamics models.

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.

A system can produce localized spacetime distortions, gravitational waves, sudden transitions in the index of refraction and optical path length changes via high-energy plasma formation. The system includes a high-energy spark-gap arrangement, where an electrical discharge between tungsten tips produces extremely high energy densities in a localized region. The system is tunable and can be driven by either constant or time-varying voltage sources, allowing for different distortion profiles and electromagnetic emission patterns. The system can operate in various environments, including air, inert gases such as helium, and even in vacuum conditions. Multiple spark-gap assemblies can be arranged to create customized distortion shapes and enhanced field effects.

This invention discloses a method, system, and product for estimating the arm length of a Taiji mission considering satellite relative motion compensation. The method includes: reading ephemeris data of key gravitational bodies during the simulation period, establishing the orbital dynamics equations of the satellite formation, solving the equations using a high-precision numerical integration algorithm, and outputting satellite orbit simulation data; generating basic measurements including noise and satellite-to-solar measurements based on the satellite orbit simulation data, and correcting the inter-satellite distance measurements in the basic measurements by optical signal propagation time to achieve satellite relative motion compensation and outputting high-precision observation data; receiving the high-precision observation data, combining it with the orbital dynamics equations of the satellite formation, recursively updating and optimizing the state variables of the satellite formation based on a Kalman filter algorithm, and outputting a high-precision estimate of the inter-satellite arm length; and visualizing the estimated satellite arm length and its error. This invention significantly improves the autonomy and reliability of space gravitational wave detection missions.

This invention discloses a design method for the thermal control system of a primordial gravitational wave detection telescope, belonging to the field of primordial gravitational wave detection technology. The method includes: S1. Preliminarily determining the receiver's main structure, materials, and connection methods based on the detection target; S2. Analyzing system heat leakage and determining the cooling power of the refrigerator; S3. Establishing a thermo-structure coupling model using Comsol and performing temperature field and thermal deformation simulations; S4. Comparing the simulation results with design specifications, and iteratively optimizing if not met; S5. Determining the final thermal control implementation scheme. This invention, through systematic thermal design and multiphysics simulation iteration, effectively reduces system heat leakage, ensures stable operation of the focal plane detector within the 100mK temperature range, and meets structural stress and optical path accuracy requirements, providing a reliable thermal control design method for primordial gravitational wave detection.