350 results about "Space debris" patented technology

The invention relates to the field of satellite operation, and discloses an in-orbit collision avoidance method and device for a constellation system, and the method comprises the steps: enabling a ground system to obtain the ephemeris information of a constellation satellite and space debris; the ground system evaluates the first collision risk of the satellite in the first period time in the future according to the ephemeris information of the constellation satellite and the space debris; when the first collision risk is greater than a first threshold value, the ground system uploads ephemeris information of the space debris to a satellite; the satellite updates a second collision risk in a second period time in the future in real time based on the received space debris ephemeris information and the satellite positioning information; when the second collision risk is greater than a second threshold value, the satellite formulates a corresponding collision avoidance strategy, and orbital maneuver is carried out according to the collision avoidance strategy; and after the avoidance is completed, the satellite actively maneuvers and returns to a nominal position corresponding to satellite ephemeris information, and the connection with the ground system is recovered. According to the invention, the accuracy of collision risk assessment is improved, and the implementability is improved.

The invention discloses a space debris environment three-dimensional network evolution method, and belongs to the field of aerospace. The method comprises the following steps: dividing an LEO orbit into a plurality of space volume elements according to a geocentric distance, right ascension, declination and an area-to-mass ratio, then dividing space objects in each volume element into a plurality of space object groups according to an orbit inclination angle and the area-to-mass ratio, selecting a macroscopic quantity of the density of the object groups as a state variable, and considering multi-source environmental factors such as atmospheric resistance perturbation and the like; and establishing a space debris environment three-dimensional network evolution model by adopting a continuity equation to realize rapid prediction of debris evolution at any position in the space. The method also utilizes the established three-dimensional network evolution model of the space debris environment to predict the low-orbit space debris environment under the sun and geomagnetic activities, and analyzes the influence of the sun and geomagnetic activities on the space debris environment evolution. Satellite launching, space traffic management and space debris treatment can be supported and optimized, and related engineering technical problems are solved.

The invention relates to the technical field of spacecraft orbit control and space safety, and discloses a space debris orbit prediction and avoidance method, which comprises the following steps that: a ground computing center screens candidate targets and generates enhanced data packets for uploading; the spaceborne computer combines real-time navigation data to carry out geometric feature screening, and an instant high-risk target list is generated; controlling the star sensor to execute optical observation, and resolving an optical measurement relative orbit state by utilizing displacement superposition and Kalman filtering; selecting a high confidence coefficient or a conservative probability threshold according to the optical measurement state acquisition condition, and generating an avoidance instruction when the collision probability exceeds the limit; and the propulsion system responds to the instruction to execute avoidance, verifies the effect by confirming the semi-major axis variation and executes track recovery by selecting an aircraft. According to the method, the ground-air collaborative screening and shift superposition enhancement technology is adopted, the problems that the low-precision ephemeris false alarm rate is high and the detection capability of a satellite-borne sensor on a dark and weak target is insufficient are solved, and the accuracy of evasion decision making and the execution reliability are improved.

The present disclosure is a device and methods for satellite trajectory control and collision avoidance. Embodiments of the disclosure are comprised of a smart satellite device performing a process three steps. First, sensors collect data about the satellite's physical landing environment, passing information to satellite's database and processors. Second, the processors manipulate the information with a deep reinforcement learning program to produce instructions. Third, the instructions steer the satellite body by manipulating the satellite's panels for optimal trajectory and collision avoidance. The purpose for the present disclosure is to help solve the space debris problem.

The invention discloses a method for constructing and screening orbital transfer speed increment required by on-orbit service of a pulse thrust spacecraft based on a CW equation, belongs to the field of on-orbit service of spacecrafts, and solves the problem of low precision of a maneuvering orbital transfer strategy of the on-orbit service orbit of the pulse thrust spacecraft. Comprising the following steps: constructing a relative motion equation of a pulsed thrust spacecraft relative to space debris based on a CW equation; inputting the orbital transfer state transfer matrix and the speed transfer matrix into the relative motion equation at the same time to obtain an on-orbit service orbital transfer model; setting a termination state distance constraint, a termination state illumination angle constraint and an orbital transfer speed increment constraint according to task requirements; and inputting all the termination moment position vectors conforming to the termination state distance constraint into the on-orbit service orbital transfer model, and reserving orbital transfer speed increments conforming to the termination state illumination angle constraint and the orbital transfer speed increment constraint to obtain a screened orbital transfer speed increment solution set. According to the invention, the precision of the maneuvering orbital transfer strategy of the on-orbit service orbit of the pulse thrust spacecraft is improved.

The invention provides a multi-station observation segmental arc association method and system for space debris. The method comprises the following steps: establishing an initial orbit of an unidentified segmental arc and an association information database; inputting an observation arc section; calculating an initial orbit of the observation arc section; traversing the initial track of the unidentified arc section and existing entries in the associated information database, sequentially judging whether the current observation arc section is associated with the initial track of the unidentified arc section and the existing entries in the associated information database or not until an associated object is found or all the existing entries are traversed, and if the associated object is found, judging whether the current observation arc section is associated with the existing entries in the associated information database. Modifying the initial track of the unidentified segmental arc and the content of corresponding items in the associated information database; if the associated object is not found, the information of the observed arc section is used as a new record to be inserted into the initial track of the unidentified arc section and the associated information database; the method is easy to implement, different association strategies are adopted for data of different time spans, association time consumption is reduced while association accuracy is guaranteed, and the method is suitable for association between single-station and multi-station observation arc section data.

The system and method for decelerating space objects moving at high velocities are provided. The system comprises at least one closed volume containing a combination of gas, liquid, solid particles, or a mixture thereof. The volume can be transported to the targeted location using a range of means, including a chemical gun, light gas gun, electromagnetic coil gun, superconducting quench gun, a rocket, or a combination thereof. The volume is strategically positioned on the trajectory of the moving object. Upon penetrating the walls of the volume, the object passes through it, experiencing deceleration.

The invention provides a radar and optical observation segmental arc correlation method and system for space debris. A joint probability density function is obtained through a kernel density estimation algorithm. A radar observation arc section and an optical observation arc section are input. And converting the observation data into a geocentric celestial coordinate system. And acquiring system parameters of the observation equipment. Radar observation data and optical observation data are unified to the same dimension, and a distance measurement value weight and an angle measurement value weight are set. And calculating an initial orbit by the radar observation arc section. And calculating a joint objective function corresponding to the current orbit position speed. And if the convergence condition is met, outputting the minimum value of the joint objective function and the orbit position speed corresponding to the minimum value. Otherwise, updating the track position speed, and repeating until the convergence condition is met. And according to the minimum value of the joint objective function and the joint probability density function, judging whether association is carried out, and outputting confidence during association. The method is easy to implement and can be effectively applied to association of the space debris radar and the optical observation arc section.

The invention discloses a fault analysis method for a low earth orbit satellite, and relates to the technical field of electric data analysis. The method comprises the following steps: collecting related data of influence of space debris on low-orbit satellite signal transmission, analyzing the related data of influence of the space debris on low-orbit satellite signal transmission to obtain an influence coefficient of the space debris on low-orbit satellite signal transmission, collecting related data of inter-satellite link network load balancing, and analyzing the related data of influence of the space debris on low-orbit satellite signal transmission. The inter-satellite link network load balancing related data is analyzed to obtain an inter-satellite link network load balancing evaluation coefficient, the IQ signal related data is collected, and the IQ signal related data is analyzed to obtain a difference evaluation coefficient between an IQ signal real-time value and a standard value. According to the invention, the problem that the communication interference between the low-orbit satellite and the ground station is too high in the prior art is solved.

Space debris capture systems include an outer assembly and an inner assembly. The Outer assembly includes an outer membrane and an inner membrane, where, in a deployed state, the outer membrane is separated from the inner membrane by a separation gap. The inner assembly is arranged within the inner membrane of the outer assembly. The inner assembly is formed of a plurality of sheets of material arranged at a plurality of orientations relative to the inner membrane and define a plurality of cells within the outer assembly when in the deployed state. A first group of the cells are defined within surfaces of the plurality of sheets of material and a second group of cells are defined between the surfaces of the inner assembly and an inner surface of the inner membrane.

The invention relates to a space debris intelligent detection method and device based on spatio-temporal feature fusion. The method comprises the following steps: acquiring a training sample composed of multiple frames of images containing space debris target labels and / or fixed star target labels; inputting the training sample into a multi-frame detection network; the information fusion module is used for performing fusion extraction on multiple frames of images in the training sample to obtain preliminary time-space semantic information; the backbone network performs deep spatiotemporal semantic extraction according to the preliminary spatiotemporal semantic information to obtain multi-scale spatiotemporal semantic information; the neck module adjusts and fuses the multi-scale space-time semantic information to obtain fusion features; the detection head outputs a prediction result according to the fusion feature; and performing reverse training on the multi-frame detection network to perform space debris target detection on the to-be-detected multi-frame image according to the trained multi-frame detection network. By adopting the method, the problem of insufficient information utilization of a current single-frame image target detection algorithm can be solved.

The invention discloses a star-sky dim and small target detection method fusing coordinate attention and a convolutional feedforward neural network, and belongs to the technical field of dim target detection. The method comprises the steps of obtaining a starry sky image data set, outputting an enhanced feature map by applying a coordinate attention mechanism, constructing a network model fusing the coordinate attention mechanism and a ConvFFN module through the ConvFFN module of a convolutional feedforward neural network, training a verification model based on simulation data, and finally outputting the centroid position and bounding box information of a target. According to the method, features are extracted in the transverse and longitudinal directions through a coordinate attention mechanism, the feature expression ability of a weak and small target in a low signal-to-noise ratio environment is effectively enhanced, the detection precision is remarkably improved, the omission ratio is reduced, the calculation efficiency is improved by combining the lightweight structure of ConvFFN and deep convolution optimization, and the method is suitable for large-scale popularization and application. A reliable and efficient detection solution is provided for astronomical observation and space debris monitoring.

The embodiment of the invention provides a collision avoidance method and device, equipment and a storage medium, which can be applied to the technical field of space debris, and the method comprises the steps: determining a plurality of time intervals for a spacecraft to execute collision avoidance on at least one dangerous object within a set time period; for any time interval, determining at least one avoidance strategy in the time interval based on the initial orbit of the spacecraft and the operation orbit of the at least one dangerous object; the evasion strategy comprises a target pulse moment and a target evasion speed pulse applied to the spacecraft at the target pulse moment; predicting whether a dangerous object with a new collision risk exists or not after the at least one avoidance strategy is executed; and the avoidance strategy without the new collision risk is determined as the target avoidance strategy, so that accurate avoidance of at least one dangerous object by executing the avoidance strategy once is realized, and the collision avoidance calculation automation and intelligence are improved.

The invention relates to an intelligent space debris detection method and device based on morphological feature difference learning. The method comprises the following steps: acquiring a training sample composed of a single-frame image containing a space debris target label and / or a fixed star target label, and inputting the training sample into a space debris detection network, the space debris detection network comprises a plurality of coding blocks, a context adjustment module, a hybrid convolution self-attention unit, decoding blocks corresponding to the number of the coding blocks and a fusion prediction unit, and reverse training is performed on the space debris detection network according to the space debris target label and / or the fixed star target label of the training sample and the prediction result to obtain a fusion prediction result; and carrying out space debris target detection on a to-be-detected single-frame image according to the trained space debris detection network. By adopting the method, the problem of poor single-frame image target detection effect of a current deep learning algorithm can be solved.

Container for collecting space debris. Space debris ingress through container's openable access port. A barrier deployment mechanism has a rotatable roll of flexible material on a frame assembly. A barrier translation mechanism translates the frame assembly towards or away from the access port to adjust the size of the compartment. When unwound, the roll forms a compartment for containing the space debris within the interior of the container, thus forming an obstruction between the compartment and access port.

The invention discloses a space target disintegration moment judgment method based on debris distance characteristics, solves the problem of how to improve the judgment accuracy of the space target disintegration moment, and belongs to the field of space target disintegration time inversion. Comprising the following steps: calculating the relative distance of each group of debris pairs in a target space debris set at any time through an Euclidean distance formula, and constructing an average relative distance equation; determining a time window according to prior information of a disintegration event, and iteratively solving a preliminary disintegration moment through a rough search method and a golden section method based on an average relative distance equation; through a density clustering algorithm, adaptively eliminating noise fragments at the initial disintegration moment, then reserving a main cluster fragment set, and constructing a corrected average relative distance equation of the main cluster fragment set; a local window is obtained with the initial disintegration moment as the center, the space target disintegration moment is iteratively solved through a rough search method and a golden section method on the basis of a corrected average relative distance equation, and the disintegration moment positioning efficiency is improved.

A method for rendezvous with an orbiting object comprising: launching a tug and a servicer into a client orbit; separating the servicer from the tug; and docking the servicer with a client. A system for rendezvous with an orbiting object comprising: a first spacecraft comprising a tug capable of towing a second spacecraft, wherein the second spacecraft is a servicer configured to dock with a tumbling client orbiting object.

The invention relates to a method for calculating the degree of polarization of complex space debris, in particular to a method for calculating the degree of polarization of complex space debris based on a micro-facet pBRDF model, and solves the technical problem that an existing method for calculating the degree of polarization is poor in authenticity and accuracy. According to the complex space debris polarization degree calculation method based on the micro-facet pBRDF model provided by the invention, aiming at the characteristics of multi-shape and multi-material coupling of complex space debris, on the basis of the modeling thought of complex refractive index, specular reflection, diffuse reflection and volume scattering of different structural materials of the complex space debris; the albedo projection area is adopted as a reflection contribution coefficient calculated by the total light intensity of reflected light of the complex space debris, and a micro-surface element pBRDF model of different structures and different reflection contribution coefficients of the complex space debris is established, so that the model is closer to the multi-shape and multi-material characteristics of the real space debris; and the polarization degree of the complex space debris calculated based on the micro-facet pBRDF model is more accurate.

The invention provides a space debris angle-measurement-only short-arc rapid initial orbit determination method and a space debris angle-measurement-only short-arc rapid initial orbit determination system. The method comprises the following steps: S1, acquiring space debris angle-only segmental arc observation data; and S2, performing polynomial fitting on the observation data. And S3, calculating the pointing vector of the space debris relative to the observation station in the J2000 geocentric celestial coordinate system at the midpoint moment of the arc section. And S4, calculating the change rate of the pointing vector at the midpoint moment of the arc section. And S5, determining the distance at the midpoint moment of the arc section and the initial value of the distance change rate. And S6, calculating an objective function corresponding to the initial value. Step S7, if the target function does not reach the convergence condition, calculating a target function gradient corresponding to the current distance and the distance variation rate, updating the current distance and the distance variation rate, and executing steps S6 to S7; and if the target function reaches the convergence condition, calculating the corresponding position and speed. The implementation process is simple and easy to implement, and the method can be effectively applied to the space debris angle-only short arc initial orbit.

The invention provides a space station maintenance simulation system and method, and relates to the technical field of digital twinning, and the system comprises a space station environment simulation construction module which is used for constructing a simulation environment of a space station through a mixed reality technology according to the sun illumination, the atmospheric radiation in the morning and evening period and space debris orbit parameters; the model adaptability reconstruction module is used for performing three-dimensional model rendering on the white mold basic structure to obtain a space station model; the space station damage condition simulation module is used for constructing an impact damage three-dimensional image through the collected impact historical data between the space debris and the space station, and superposing the impact damage three-dimensional image to the space station model; the space station maintenance scheme selection module is used for recommending a mechanical arm maintenance scheme or an astronaut out-of-cabin maintenance scheme according to the impact damage three-dimensional image, the fault report condition and a real pre-judgment analysis strategy input by a user; simulation construction of a space station environment is realized on the basis of a virtual mixed reality technology, and the cost of extravehicular maintenance training of the space station is saved.

The invention provides a space debris orbit prediction model training method and a space debris orbit prediction method, relates to the technical field of space debris orbit prediction, and is used for solving the technical problem that in the prior art, target information is difficult to effectively extract from sparse data, so that space situation changes cannot be accurately perceived. The space debris orbit prediction model training method comprises the following steps: acquiring historical orbit data of space debris; according to historical orbit data, extracting position residual errors between the prediction state vectors and the reference state vector of the space debris at different moments; generating a multi-dimensional feature data set according to the position residual error; performing data dimension reduction processing on the multi-dimensional feature data set to obtain a sample data set after dimension reduction; and training an initial random forest model through a machine learning algorithm by using the sample data set after dimension reduction, so that the initial random forest model establishes a mapping relationship between the orbit parameters of the space debris and future states, and a space debris orbit prediction model is obtained.

The invention relates to the technical field of aerospace, in particular to a space debris environment quantification method based on risk entropy, and the method comprises the steps: S1, discretizing an evaluation time range into a plurality of time periods, and recording the duration of each time period as delta t; any time period tj can be expressed as tj belongs to [(j-1) * delta t, j * delta t]; j < = N, where N represents the total number of time periods; simulation is carried out, and it is assumed that N + 1 possibilities exist in the in-orbit collision disintegration condition of the space object objk; specifically, if N time periods exist, there is N possibilities for the space object to collide and disintegrate; if the space object is still not disassembled at the end of simulation, judging that N + 1 possibilities exist in collision and disassembly of the space object; s2, calculating a collision probability in a time period; and S3, calculating a risk entropy according to the collision probability, and judging the influence of the space object on the space debris environment according to the risk entropy. The space debris environment quantification method based on the risk entropy can be used for quantification of uncertainty of the space debris environment.

The invention relates to the technical field of digital twinning, and particularly discloses a space debris collision detection digital twinning method and system, and the method comprises the steps: carrying out the grid processing of space debris through a space grid between the earth and the moon; performing space debris collision detection on the space debris by using a grid collision screening algorithm; and according to a space debris collision detection result, screening out space debris which may be collided, and sending out an early warning. According to the method, the space grid collision screening algorithm based on the space grid between the earth and the moon is adopted to carry out collision screening and secondary screening on the space debris, a large number of space debris which cannot be collided can be efficiently rejected, and therefore resources are concentrated to carry out more accurate analysis on high-risk collision.

An object is to more accurately assist avoidance of a collision between space objects such as satellites or space debris in outer space. A recorder processing unit (110) acquires flight forecast information (401) indicating a flight forecast of each of a plurality of space objects (60) from a management business device (40) used by a management business operator that manages the plurality of space objects (60). Based on the acquired flight forecast information (401), the recorder processing unit (110) sets a forecast epoch of an orbit of each of the plurality of space objects (60), a forecast orbital element that identifies the orbit, and a forecast error that is forecast for the orbit, as orbit forecast information (51). The recorder processing unit (110) stores a space information recorder (50) including the orbit forecast information (51) in a storage unit (140).

The invention relates to the technical field of space station fragment protection, in particular to a space station fragment protection device based on an initiating explosive device pressing seat, which comprises a protection assembly, a first connecting assembly and a second connecting assembly, the protection assembly is used for covering a space station cabin, preventing space debris from directly impacting the cabin and bearing the impact of the space station debris. When the fragment protection device is additionally arranged on the ascending area of the mechanical arm in an on-orbit mode, firstly, the universal handle is connected with the first connecting assembly, and an astronaut drives the protection assembly to move to the ascending area of the mechanical arm through the universal handle so as to prevent the protection assembly from drifting at will. And then, a waste initiating explosive device pressing seat is used as an installation point position of the protection assembly, so that the second connection assembly is connected with the initiating explosive device pressing seat, the fragment protection device installation task is completed, the overall fragment protection capacity of the space station is further improved, and the on-orbit service life of the space station is prolonged.

The invention belongs to the technical field of on-orbit spacecrafts, and relates to a large light deformable protective shield for an on-orbit spacecraft. The protective shield is simple and compact in structure, few in transmission path and high in overall reliability. The servo motor is adopted for control, the control precision is high, and remote control or remote sensing control can be achieved. The on-orbit spacecraft can be effectively protected by opening the protective shield, and impact of space debris on the on-orbit spacecraft is avoided or relieved.

The invention relates to the technical field of space debris capture, in particular to an impact disintegration test debris recovery device which comprises a target chamber and a capture structure, a target cavity is formed in the target chamber, and the target cavity is used for containing a simulation target; the capturing structure is arranged on the inner wall of the target cavity and comprises a first capturing layer and a second capturing layer, the second capturing layer covers the inner wall of the target cavity, the first capturing layer covers the face, away from the inner wall of the target cavity, of the second capturing layer, the density of the first capturing layer is smaller than that of the second capturing layer, and the first capturing layer is of a transparent structure. Small-size and small-kinetic-energy tiny fragments are captured by the first capturing layer, large-size and large-kinetic-energy fragments penetrate through the first capturing layer to be captured by the second capturing layer, the number of the tiny fragments entering the second capturing layer is reduced, and therefore positioning and extraction of the large fragments in the second capturing layer based on X-rays and a section method are facilitated. And the first capturing layer is of a transparent structure, so that the difficulty of extracting the tiny fragments is reduced.

The invention provides a space-based optical observation high-orbit space debris short arc initial orbit determination method and system. The method comprises the steps that S1, angle measurement information of imaging of the same unidentified space debris by a space-based optical observation platform is acquired; s2, acquiring observation data according to the observation capability of the space-based optical observation platform, and setting the upper limit and the lower limit of the distance between the high-orbit space debris and the space-based optical observation platform; s3, calculating an actual observation distance upper limit and an actual observation distance lower limit corresponding to the current observation arc section according to the observation data; s4, randomly initializing a plurality of groups of particles within the upper limit and lower limit range of the actual observation distance; s5, calculating a loss function corresponding to each group of particles; s6, updating each group of particles, calculating a loss function corresponding to the updated particles, and recording each group of optimal particles and global optimal particles; and step S7, repeating the step S6 until the cycle quitting condition is met. The method is easy to implement, and the success rate of determining the high-orbit space debris short arc initial orbit can be increased.

The invention provides a correlation method and system for space debris observation data and cataloguing orbit data. The method comprises the following steps: firstly, within a time range of currently processed batch observation data, recurring to an orbit matrix distributed at equal time intervals through an orbit of an orbit recursion cataloguing target, and generating a position interpolation function based on a time sequence and the orbit matrix; and for observation data in a processing time range, firstly unifying the observation data and an observation station position to a J2000.0 inertial coordinate system, and obtaining a multi-target position prediction value corresponding to observation time through an interpolation function. Calculating the difference between the predicted value and the measured value of the observation data; and calculating an associated object and confidence according to the difference. The method is easy to implement, high in efficiency during batch observation data processing and suitable for association of observation data of different observation devices and different types of orbit space debris and catalogued orbit data.

The invention relates to the technical field of aerospace engineering, space robots and intelligent control, and particularly discloses a space debris intelligent capture and treatment method and system based on an SAC algorithm, and the method comprises the steps: obtaining the motion data of a space non-cooperative target and the system parameters of a space robot; constructing a hybrid filtering optimization framework based on the motion data and the system parameters; adjusting a hybrid weight and a noise forgetting factor in the hybrid filtering optimization framework by using an SAC algorithm to obtain self-adaptive estimation of a target attitude; a state space and an action space are defined based on a base of the space robot and a mechanical arm of the space robot respectively, and based on the state space and the action space, a mechanical arm movement path of the space robot is generated through an SAC algorithm in combination with a multi-target reward function; and the self-adaptive estimation of the target attitude is fed back to the motion path of the mechanical arm, dynamic cooperation of filtering and control is achieved, and stable capture of the space non-cooperative target is completed.