469 results about "Celestial body" patented technology

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

The invention discloses an indirect optimization method for a landing anti-interference trajectory of a small celestial body, and relates to the field of deep space exploration. Aiming at the problem that a small celestial body landing trajectory is sensitive to uncertain parameters, the following solving method is provided: firstly, establishing a stochastic dynamics model of small celestial body landing, and constructing an anti-interference trajectory optimization problem; secondly, establishing a relation between an anti-interference trajectory optimization problem and a gravity-energy-free optimal control problem through a performance functional, a kinetic equation and a homotopy function of process noise, and estimating a co-state initial value of the gravity-energy-free optimal control problem; and finally, gradually converting the zero-gravity energy optimal control problem into an anti-interference trajectory optimization problem by changing homotopy coefficients, and in the conversion process, converting the optimization problem corresponding to each homotopy function into a two-point boundary value problem by using a Pontryagin minimum principle, and solving the two-point boundary value problem by using a targeting method. The sensitivity of the trajectory to uncertainty is reduced, so that the anti-interference capability of the landing trajectory is improved.

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

The invention discloses an Ia type super-novelty star spectral parameter rapid inversion method based on a KAN network, and the method comprises the following steps: S1, carrying out data preprocessing, generating simulation spectral data, including spectral lines and parameters, and carrying out the normalization; s2, building a KAN (Kernel Area Network) network model by using a python framework and a pytorch framework; s3, designing a loss function; s4, training the model, and testing the error of each parameter in the stage; s5, performing learning rate adjustment by using an Adam optimizer and a StepLR scheduler in the training process, and optimizing the model; s6, performing Gaussian sampling on an actually measured spectrum, and inputting the actually measured spectrum into the trained KAN model for prediction; s7, analyzing the result, and calculating the standard deviation of the output parameter data; by using the deep learning technology of the KAN network, key physical and chemical parameters are efficiently predicted from the celestial body spectrum, the problems that in the prior art, the calculation amount is too large, and an accurate calculation result cannot be efficiently obtained are solved, and the method has remarkable advantages in the aspects of improving the calculation efficiency and the processing capacity and is suitable for spectrum data analysis in the field of astronomical observation.

The invention provides a star catalogue file generation method and device, a celestial body data query method and device, computer equipment and a storage medium. The star catalogue file generation method comprises the steps of obtaining star catalogue data; dividing the celestial sphere surface area corresponding to the plurality of celestial bodies into a plurality of local areas, and determining an identifier of each local area; determining an identifier matched with each celestial body data according to the right ascension and declination included in the celestial body data and the identifier of each local area in the celestial sphere surface area; sorting the celestial body data of the plurality of celestial bodies based on the identifiers corresponding to the celestial body data; and writing the sequenced celestial body data of the plurality of celestial bodies into an initial column storage file matched with the identifier to obtain a target file stored with the celestial body data, and generating file index information corresponding to the target file. The celestial body data is stored by utilizing the column type storage file, so that the problems of high maintenance cost and high use threshold caused by utilizing a database to store data are relieved while the data query efficiency is guaranteed.

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

The invention discloses a celestial body data index construction method and device, a storage medium and electronic equipment. The celestial body data index construction method provided by the specification comprises the following steps: acquiring position information of an observed celestial body; determining a relative position of the celestial body based on a preset central point according to the position information, and taking the relative position as an index position of the celestial body; sorting the index positions of the celestial bodies according to a specified rule to obtain a target sequence, and establishing a corresponding relationship between the sequence of the index positions of the celestial bodies in the target sequence and the celestial bodies; modeling by taking each index position contained in the target sequence and the sequence of each index position in the target sequence as variables to obtain a relation function between the sequence and the index position; and constructing a celestial body data index according to the corresponding relation and the relation function.

The invention provides a lunar polar region sun synchronization # imgabs0 # path planning method, which can be applied to the technical field of celestial body image processing and path planning. The method comprises the following steps: independently training a plurality of enhanced U-Net models by using training data with time sequence slices and fusion types and a mixed loss function; dividing and extracting the reasoning data with a time sequence slice type and a time sequence fusion type by using a plurality of trained enhanced U-Net models to obtain a lunar polar region friendly illumination region, and preprocessing the reasoning data with the lunar polar region friendly illumination region and gradient data corresponding to the lunar polar region friendly illumination region; and based on the reasoning data after time alignment and the gradient data after space alignment, constructing a heuristic function by using mixed cost, and performing heuristic path planning by using an improved # imgabs1 # path planning algorithm with a time one-dimensional function and an in-situ waiting function to obtain a sun synchronization planning path of the lunar polar region.

The invention belongs to the technical field of space photoelectric detection, and provides a high-precision tracking and pointing system and method capable of autonomously formulating an observation task in orbit. The system comprises an information processing unit, a power supply management unit, a task management unit, a thermal control unit, a GNSS unit, a star sensor unit, a gyroscope unit, a tracking and pointing calculation unit and a servo turntable unit. The system can receive a platform instruction, integrate information of sensors such as a GNSS, a star sensor and a gyroscope, calculate the accurate position of a tracked celestial body, and adjust the direction of a servo turntable in real time so as to accurately track a target. The working method comprises the steps of system starting and initializing, observation task making, tracking and aiming mode preparing, aiming direction correcting, observation target tracking and aiming, exception handling and the like. The system can realize high-precision observation of a celestial body target without depending on attitude adjustment of a spacecraft platform, improves the observation efficiency and reliability, and is suitable for observation of celestial bodies such as pulsar on a space station platform.

The present disclosure relates to an information processing device and an information processing method for providing an imaging service for performing imaging with a camera mounted on an artificial satellite.An information processing device includes a display control unit that causes a first screen to be displayed, the first screen including a map display unit that displays an artificial satellite that orbits around a celestial object and an orbit of the artificial satellite on a map of the celestial object, and a time information display unit that displays time information on the orbit of the artificial satellite. The display control unit causes the first screen to synchronously display the position of the artificial satellite on the map of the celestial object on the map display unit and the time information about the artificial satellite on the time information display unit. The technology according to the present disclosure can be applied to an information processing device or the like that provides an imaging service for performing imaging with a camera mounted on an artificial satellite, for example.

The invention discloses an astronomical cross identification method based on spherical trapezoidal division, and the method comprises the steps: S1, taking a unit spherical surface as a celestial sphere, dividing the celestial sphere into a plurality of strips parallel to an equatorial line, and determining the right ascension span of each strip for the transverse segmentation of the strip; s2, dividing each strip into a same spherical isosceles trapezoid with two waists perpendicular to the equator, and taking the same spherical isosceles trapezoid as a sky area; s3, determining an index of each sky area; s4, dividing a star catalogue A and a star catalogue B, and creating a zipper type hash table based on the row number of the star catalogue B; s5, mapping each celestial body in the star catalogue B into a linked list in a hash table in a multi-thread parallel mode, and inserting celestial body data into the linked list by means of a two-stage insertion strategy; s6, mapping each celestial body in the star catalogue A into a linked list in a group of hash tables in a multi-thread parallel mode, and traversing to obtain celestial body IDs of which the spherical distance is smaller than the error radius; the method not only can completely avoid the problem of result omission, but also can greatly improve the astronomical cross identification calculation performance.

Method and device for celestial timekeeping that synchronizes independent object-relative cyclic time and displays each unique temporal interval on a single user display system. Multi-celestial cyclic time is displayed based on a user's frame of reference by aligning with recurrent and unique cyclic start / stop signals and the local reference frame timekeeping system. For example, using the Coordinated Universal time (UTC) for a user on Earth to equate the duration of independent cyclic time of Lunar18, Mars24, and so on. The method uses dimensional analysis and equates a single cyclic, non-cyclic (zero-time; start / stop non-dimensional instant of a cycle), and linear continuous time [T] from an observer frame of reference for displaying one or more temporal cycles on the user's device. Each independent cycle is consistent with temporal counts of a whole cycle (equated to SI units) displayed as either a discrete geometric shape (spatiotemporal units) and / or algebraic numbers on the device.

Implementations of the disclosed subject matter provides a system having an artificial light source disposed at a distance from earth or other celestial body, where the artificial light source is configured to project one or more beams of light onto the earth or other celestial body. The system may include a photovoltaic array disposed in an area on the earth or other celestial body that is 200 m-20 km or more in any one dimension that is configured to receive the projected one or more beams of light and is configured to convert the received one or more beams of light into electricity.

Methods and systems are provided for determining navigational information for an entity such as a vehicle using celestial measurements. One method involves determining a Kalman gain based at least in part on inertial measurement data at or before a current point in time associated with the celestial measurement data, determining a celestial measurement error based at least in part on a relationship between the celestial measurement data and a prior estimate for the celestial measurement data, determining a current estimated error associated with the location of the entity based at least in part on a prior estimated error associated with the location, the Kalman gain and the celestial measurement error, and determining an updated estimate of the location of the entity based at least in part on the current estimated error and a prior estimate of the location of the entity.

The invention belongs to the technical field of astronomical observation, and discloses an automatic star finding and tracking method and imaging equipment, and the method comprises the steps: collecting one or more first images through a shooting part of the imaging equipment, obtaining the coordinates of each first image in a space-time coordinate system according to all first images and corresponding collection moments, and obtaining the coordinates of each first image in the space-time coordinate system; determining a mapping relation between the imaging equipment and the space-time coordinate system according to the coordinates of all the first images in the space-time coordinate system, and performing automatic star finding and star tracking processing on the target celestial body by using the mapping relation; in the whole process, the imaging equipment can be calibrated at any attitude angle of any placement position, the target celestial body can be automatically and accurately shot and continuously tracked, manual intervention is not needed, and complex astronomical observation requirements can be met.

The invention discloses a celestial body data retrieval method and device, a storage medium and electronic equipment, and the method comprises the steps: matching the coordinate information of each celestial body image in a celestial body image header file with the coordinate information contained in each celestial body star catalogue record in a star catalogue database of each different data source according to the coordinate similarity; and determining each celestial body data pair formed by the celestial body image and the celestial body star catalogue record which have a matching relationship, and for each celestial body data pair, carrying out feature coding on the celestial body image and the celestial body star catalogue record in the celestial body data pair to obtain the multi-modal features of the celestial body data pair. A multi-modal feature is constructed by associating a celestial body image in a celestial body image header file with celestial body star catalog records in a star catalog database. And when celestial body data retrieval needs to be carried out, obtaining a retrieval result according to the multi-modal features. According to the method, the similarity of data features in the celestial body image and the celestial body star catalogue record is considered at the same time, and more accurate retrieval precision can be achieved.

The invention discloses a distributed ground-based radar atmospheric refraction error calculation method for celestial body observation. According to the method, a local numerical weather forecast model is corrected by using real-time surface meteorological parameters, atmospheric refractive index profile data containing elevation meteorological information is obtained, a geometric elevation angle of a celestial body target is taken as a standard, and a neutral atmospheric refractive index error is searched in combination with a corrected data source and a ray tracing method, so that the atmospheric refractive index is obtained. And finally, neutral atmospheric refraction error calculation and correction are realized. The effectiveness of the algorithm is verified through simulation.

The invention discloses a lunar balance dynamic parameter high-precision resolving method and system combining LRR and LLR technologies, and belongs to the field of deep space exploration and celestial body dynamics, and the method comprises the steps: constructing an LRR and LLR combined observation data set, and carrying out the preprocessing; constructing an LRR and LLR combined moon measurement model, and deducing a partial derivative of the model for a moon rotation parameter and a tidal LOVE number to obtain a combined partial derivative matrix; iterative solution is carried out through nonlinear least square to obtain dynamic parameters of the moon balance; and evaluating a resolving result and optimizing a resolving strategy, and optimizing a resolving scheme by dynamically adjusting the weight, improving a tide model and eliminating abnormal values. According to the method, the parameter calculation error is reduced, the technical advantages of two types of data are effectively integrated, the problem of insufficient observation continuity or precision of a single data source is solved, and reliable parameter support is provided for moon rotation and internal structure research.

The invention discloses a manned lunar exploration-oriented earth-moon emergency return orbit rapid design method, which comprises the following steps of: establishing a high-precision orbit kinetic equation in a geocentric inertial coordinate system by taking the earth as a central celestial body, and describing the motion state of an aircraft in an earth-moon space; determining a general transfer orbit and a free return orbit of the manned lunar exploration task by adopting a B-plane design method in combination with a high-precision orbit kinetic equation of the aircraft; globally searching an initial value range of a design variable under the condition of comprehensively considering reentry point height and reentry angle constraints by taking a general transfer orbit or a free return orbit as a baseline; and on the basis of the initial value range of the design variable, further considering the reentry range, the reentry inclination angle and the coplanar constraint with the drop point, and determining a final design variable and an emergency return orbit by adopting a differential correction optimization algorithm. The method has an important reference value for rapid design and parameter selection of the emergency return orbit in a manned lunar exploration task.

A tiered spacecraft docking station is adapted to facilitate docking of spacecraft within outer space. A first tier includes a first frame enclosing a first area. A first net-like mesh is coupled to the first frame and fills the first area enclosed by the first frame. A second tier includes a second frame enclosing a second area. A second net-like mesh is coupled to the second frame and fills the second area enclosed by the second frame. A plurality of support beams attach the first frame to the second frame. A lander is used to slow and stop a spacecraft on a celestial body. The lander includes a first and a second webbed structure and a decelerator coupled to the first webbed structure and / or the second webbed structure. The decelerator maintains a tension in the first and / or second webbed structure below a predetermined threshold.

Described herein is a method for wireless transmission of energy in space, wherein a constellation of transmitting satellites orbiting around a celestial body, such as the planet (P) Earth or the Moon (L), are equipped with a laser apparatus for sending a beam of coherent electromagnetic waves to an orbiting satellite or another receiving target, such as a mobile vehicle or a fixed base on said generic celestial body, in order to transmit energy thereto. The total power transmitted is divided among the orbiting satellites in the constellation, resulting in less contraindications than in the case of a single transmitting system with equivalent total power. The advantage of such division among a constellation of satellites mainly consists of shorter periods of solar eclipse, since sunlight is necessary for the operation of the transmission system. The receiving target or satellite converts the beam of electromagnetic waves into electric energy.

The present invention discloses an optical navigation feature planning optimization method for autonomous operation on the surface of an extraterrestrial body, which belongs to the field of autonomous navigation. The implementation method of the present invention is as follows: at a camera sampling time interval, according to the planned detector trajectory and attitude, combined with the camera parameters, the visible field of view range of the optical camera at the corresponding moment is calculated; considering the uncertainty of the detector position and attitude, combined with the camera field of view range formula, the uncertainty area of ​​the field of view range is obtained, and the intersection area of ​​the uncertainty area is taken to obtain the estimated field of view range for navigation feature selection at the current moment; before the start of the detection task, the Cramér-Rao lower bound is used as the performance indicator to optimize the selection of optical navigation features within the sequence estimated field of view range, and obtain optical navigation features that meet the requirements of autonomous operation on the surface of an extraterrestrial body. According to the present invention, the preferred navigation feature points are planned for navigation, the influence of the uncertainty of the detector position and attitude on the navigation performance is eliminated, and the robustness and efficiency of autonomous operation navigation are improved.

Navigation with light refraction or dispersion and landmark data is provided. A system can include a data processing system. The data processing system can receive a first image of a surface of a planet from a first camera. The data processing system can generate a first position dataset based on the first image and data representing landmarks of the surface of the planet. The data processing system can receive, by a second camera oriented towards an atmosphere of the planet, a second image. The data processing can generate, via a celestial body catalog, a second position dataset based at least in part on an amount of refraction or dispersion of light of a celestial body in a second image. The data processing system can determine, based on a filter applied to the first position dataset and the second position dataset, a position and attitude of a vehicle.

1. Name of the Design Product: Smart Astronomical Telescope. 2. Use of the Design Product: For celestial observation. 3. Design Key Points of the Design Product: Lies in the shape. 4. Picture or Photograph that Best Illustrates the Design Key Points: Perspective View 1.

The invention refers to a computer-implemented method for calibrating a pair of digital elevation maps (DEMI, DEM2), where the digital elevation maps (DEMI, DEM2) of the pair have been acquired from measurements of a first radar sensor equipment (RE1) and indicate for different time points the height of a predetermined terrain (TR) on a surface of a celestial body, wherein the method processes a time series (ts) of SAR images (TSIM) of the predetermined terrain (TR) acquired from measurements of a second radar sensor equipment (RE2), the method comprising the following steps: a) determining candidate calibration points (ccp) from the time series (ts) of SAR images (TSIM) based on dispersion measures (D) of respective pixel positions within the SAR images (TSIM) of the time series (ts); b) identifying pixel positions as calibration points (cp) within the digital elevation maps (DM1, DM2) of the pair based on the candidate calibration points (ccp); c) determining height value differences (Δ) between the digital elevation maps (DEMI, DEM2) of the pair at the calibration points (cp); d) fitting a two-dimensional curve (CS) to the height value differences (A) at the calibration points (cp), the two-dimensional curve (CS) describing the height value differences (Δ) over the pixel positions representing corresponding points within the predetermined terrain (TR); e) correcting the height values (hvl, hv2) of one digital elevation map (DEMI, DEM2) of the pair by the height value differences (Δ) of the two-dimensional curve (CS).

The invention provides a wide-area tomography calculation astronomical imaging system and device, and the system comprises a snapshot spectral imaging module which is used for capturing full-view three-dimensional hyperspectral data of an observation view field; the red shift resolving module is used for processing the three-dimensional hyperspectral data through a hybrid algorithm based on the three-dimensional hyperspectral data, and inverting a target red shift value, three-dimensional space coordinates and physical parameters of the target celestial body; the chromatography data visualization module is used for generating a three-dimensional chromatography map through pseudo-color labeling and a three-dimensional modeling method based on the target red shift value, the three-dimensional space coordinates and the physical parameters; and the control module is used for configuring the snapshot spectral imaging module based on the observation target parameters. According to the method, high-precision cosmic chromatography of a wide-area sky area is realized, three-dimensional hyperspectral data is converted into a visual and reliable three-dimensional space distribution model and a physical parameter map, and reliable technical support is provided for frontier research of cosmic large-scale structures, galaxy evolution and dark matter distribution.

The invention belongs to the technical field of image processing, particularly relates to a celestial body faint target feature extraction method based on deep learning, and aims to solve the problem that in the prior art, a faint celestial body target is difficult to effectively detect when the celestial body target is detected, so that the detection accuracy is influenced. The method provided by the invention comprises the following steps: acquiring a foundation optical image to be detected; inputting the ground-based optical image into a pre-constructed target neural network to obtain a target feature map output by the target neural network, the target feature map being used for indicating detail information and semantic information of a celestial body faint target in the ground-based optical image; the target neural network comprises a backbone network, a feature extraction module and a feature fusion module. Based on the method provided by the invention, a feature extraction module (Res-MBDA) and a feature fusion module (CAFFM) are adopted to enhance the attention on the information of the faint celestial body target, and the detection rate of the faint celestial body target is effectively improved.

To assist a user in making various decisions and performing operations for highly accurate introduction and tracking of a celestial body, in an astronomical telescope having a rotation drive mechanism for a telescope barrel for automatically capturing a target celestial body within the field of view of the telescope and a control device for controlling the drive mechanism, without connecting a special device to the telescope control device. [Solution] A digital camera 1 that moves in unison with the movement of the telescope T is attached to the telescope, and the telescope is driven by instructions to steer its field of view towards the target coordinates. The camera also captures an image in the direction the telescope is pointed and the image is analysed to identify the pointing coordinates that will actually be introduced into the field of view of the telescope. The error between the target coordinates and the pointing coordinates is calculated, and if the desired pointing accuracy is not achieved, a re-introduction operation to the target coordinates is performed, and the telescope is pointed precisely towards the target coordinates.

The invention belongs to the technical field of inverse synthetic aperture radars, and particularly relates to a tidal deformation dynamic modeling and parameter inversion method based on hybrid GRFT. The specific process is as follows: dynamic slope distance and echo modeling: aiming at each scattering point of a target celestial body, combining a radar position and introducing three-dimensional rotation correction caused by rotation to calculate a dynamic slope distance, and simulating a radar echo signal based on the dynamic slope distance; echo processing based on mixed GRFT: performing pulse compression on echo signals, compensating phase errors caused by rotation and deformation in sub-apertures by using the mixed GRFT, and performing non-coherent superposition on GRFT output of each sub-aperture; searching parameters: setting a search range of initial height and dynamic viscosity of each scattering point, setting a fitness function as non-coherent superposition energy synthesis of each scattering point, and searching in the search range until a termination condition is met; and tide deformation quantity calculation: calculating the tide deformation quantity according to the estimated values of the initial height and the dynamic viscosity of the searched scattering points.

The invention discloses a small celestial body sampling process dynamics and control simulation method based on particle dynamics. The method comprises the following steps: establishing a small celestial body particle dynamics model and a detector system flexible multi-body dynamics model; and establishing a particle dynamics-multi-body dynamics-control coupling simulation model, and realizing dynamics and control joint simulation solution calculation in the small celestial body sampling process by using a numerical integration algorithm. In order to solve the multidisciplinary, system-level dynamics and control joint simulation problem in the small celestial body sampling process, mathematical simulation models of small celestial body star soil particle flow dynamics, detector flexible multi-body dynamics, detector attitude and orbit control and mechanical arm control are provided, and the interface relation among the models is defined; multi-disciplinary and system-level joint simulation of particle dynamics-multi-body dynamics-control in the small celestial body sampling process is realized, and an important technical means is provided for small celestial body star soil weathered layer particle characteristic simulation and process dynamics and control coupling characteristic analysis.