267 results about "Space debris" patented technology

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 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 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.

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.

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 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.

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 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.

The invention provides a capturing net based on space protection, and belongs to the field of on-orbit spacecraft service, the capturing net comprises a hexahedral satellite main body, a fixed connecting device, an unlocking device, an unfolding antenna and an unfolding net, the fixed connecting device is arranged outside the hexahedral satellite main body, the unfolding antenna is hinged to the fixed connecting device, the unlocking device comprises a multi-stage unlocking mechanism, and the unfolding net is arranged in the hexahedral satellite main body. The unlocking mechanisms are arranged on the fixed connecting device and the unfolding antenna, the fixed connecting device and the unfolding antenna are locked in a folded state, the unlocking mechanisms act in sequence to achieve unfolding of the unfolding antenna, and the unfolding net is arranged in the unfolding antenna and is unfolded along with the unfolding antenna to complete fragment capturing. According to the space debris capturing device, space debris of various sizes and irregularity can be captured, kinetic energy of a captured object is effectively reduced by means of the material characteristics of the unfolding net, firm capturing is achieved, and the success rate of capturing the space debris is greatly increased.

The invention discloses a high-storage-ratio folding method for a large conical film structure, and belongs to the technical field of space debris removal and satellite light shields. The problems that an existing plane deorbit sail is poor in attitude stability and low in deorbit efficiency are solved. Comprising the following steps: S1, drawing equidistant circumferential folding lines on a conical film structure, wherein the circumferential folding lines comprise a circumferential ridge line and a circumferential valley line; s2, circumferential folding is carried out, axial compression is carried out along the axis of the cone, and then circumferential contraction is carried out; and S3, folding from a cone to a cylinder. The three-dimensional conical film sail can be folded into the three-dimensional conical film sail which is high in posture stability, relatively high in unfolding reliability and capable of correcting the posture, and the folding efficiency is high.

The utility model discloses space junk capturing equipment, and belongs to the technical field of spaceflight. Comprising a metal shell and a controller installed on the metal shell, the metal shell serves as a containing cavity of a mechanical arm, a data collecting unit connected with the controller is arranged on the metal shell, and a mechanical arm fixing frame is installed in the metal shell; the mechanical arm is connected with the controller through the driving module, the fixed end of the mechanical arm is connected with the mechanical arm fixing frame, and the free end of the mechanical arm is stored in the metal shell or extends out of the metal shell in a telescopic and foldable mode. And a manipulator is mounted at the head of the free end of the mechanical arm and is used for capturing space junk fragments. According to the space junk capturing device, a mechanical arm and existing intelligent control are combined, space junk can be accurately captured, efficiency is high, and the defects that traditional capturing equipment cannot be stored, is prone to being lost, is difficult to fold and unfold, and is low in accuracy are overcome.

The invention discloses a space debris target detection and positioning method based on dynamic programming and multi-hypothesis testing, and the method comprises the following steps: carrying out the preprocessing of an obtained space debris image, and obtaining a candidate point state set under different time frames; in the preprocessing, a denoising segmentation extraction channel and a lightweight CNN target extraction channel are divided according to a statistical local signal-to-noise ratio; obtaining a plurality of motion paths corresponding to each candidate point according to the candidate point state sets under different time frames; and for each candidate point, generating an initial hypothesis set according to the corresponding multiple motion paths, and processing the initial hypothesis set through Kalman filtering to obtain the position of the candidate point. According to the method, the detection precision of the dark and weak target is remarkably improved, the false alarm rate is reduced, the real-time performance of detection is improved, and the method is suitable for real-time monitoring scenes. The research result provides effective technical support for improving the operation safety of the spacecraft.

The invention discloses a large-view-field image space debris detection method based on in-orbit adaptation, and the method comprises the steps: obtaining a to-be-detected large-view-field starry sky image, inputting the large-view-field starry sky image into a trained space debris detection model, and obtaining a target detection result for the large-view-field starry sky image; the space debris detection model comprises a coupling factor evaluation module, a sparse hybrid expert processing module, a knowledge accurate correction module and a detection result output module; according to the invention, through cooperative work of a plurality of modules, expert models in different fields are controlled by using a plurality of different levels of image degradation evaluation indexes so as to realize effective response to different factors, and meanwhile, a knowledge accurate correction module is introduced so as to realize finer adaptive processing. According to the method, the target detection performance of the large-view-field detection image in a complex space environment is remarkably improved.

The invention relates to the technical field of spacecraft observation, provides a space debris early warning method and system, and solves the technical problem that a space debris collision probability calculation result cannot meet a high-precision requirement in a calculation process in the prior art. The method comprises the following steps: acquiring a space debris original set; obtaining a first space debris set; calculating all dangerous time windows of the target spacecraft and the space debris in the first space debris set; obtaining a second space debris set; calculating the closest moment of the target spacecraft and the space debris in the second space debris set and the closest time interval when the relative minimum distance between the target spacecraft and the space debris is smaller than the collision distance threshold; calculating the collision probability of the target spacecraft and the space debris in the second space debris set; and outputting collision probability information of the space debris in the second space debris set.

The invention provides a radar resource dynamic allocation method and system based on multi-task reinforcement learning, and relates to the technical field of multi-agent reinforcement learning multi-beam radar resource allocation, and the method comprises the steps: constructing a matrix through space debris orbit parameters, collision probability and radar detection historical data, and dividing the matrix into high, medium and low threat levels; then, a multi-beam radar system is configured, and different gain beams are distributed for the target according to the threat level; then, a distributed multi-agent reinforcement learning framework is adopted, an agent is deployed for each radar, the agents are combined with related data to generate a collaborative resource allocation strategy, and beam pointing and a scanning period are adjusted; and finally, integrating a threat-driven reward mechanism, calculating a reward weight according to the fragment collision probability, inclining resources to a high-collision-probability target, and realizing strategy adjustment, so that the detection and tracking efficiency of the radar on the space debris can be improved.

The invention relates to a space debris position and speed all-optical rapid measurement system and method, and relates to the technical field of space debris orbit determination cataloguing. The measuring system comprises a laser, a collimating lens, a central reflection spectroscope, a fast scanning mirror, a narrow-band spectroscope, a telephoto lens, space debris and the like. The time series of key parameters such as the angle, the angular velocity, the distance and the velocity of the space debris relative to the observation platform can be measured at the same time, and the method is used for rapidly determining the space debris orbit. According to the invention, an optical camera with a large aperture, a large field of view and a single-photon detector is used, identification and angle measurement of a plurality of dark and weak space debris can be realized, and rapid measurement of the orbital number of the space debris is realized by adopting laser ranging and speed measurement with a common aperture design. Rapid distance measurement and speed measurement of multiple targets in a view field are realized through laser pulse composite modulation and a fast scanning mirror tracking mechanism, and a more effective solution is provided for the initial orbit element measurement problem of unknown space debris.

The invention provides a space debris bistatic detection data fusion method based on a Bayesian rule, and the method comprises the following steps: 1, building a detection model: obtaining a detection probability and detection data distribution through a space-based in-situ simulation detection model and a foundation narrow-beam radar simulation detection model based on the orbit parameters of given space debris; step 2, inputting detection data and performing inversion; and step 3, calculating the number of fragments by using a space debris bistatic detection data fusion method based on a Bayesian rule. According to the method, the limitation of a single observation mode is overcome, and the reliability of environment modeling is improved; compared with a single data source, the data obtained by the two detection modes can complement each other, and the obtained information is more complete; and theoretical support is provided for cooperation of fragment monitoring. Data fusion supports data sharing of space monitoring institutions of different countries and regions to cope with challenges brought by space debris together.

The application provides a variable configuration spacecraft system and method for non-cooperative target capture, and belongs to the field of deep space exploration. The method comprises the following steps: 1) a rigid combination flies to the vicinity of the target; 2) the combination is spun to be expanded into a ring belt; 3) the ring belt envelopes the target; and 4) the ring belt encloses the target. Large space debris and small celestial bodies both belong to non-cooperative targets, and cannot provide special interfaces for assisting capture. It is extremely difficult to develop general control mechanisms and methods to realize reliable capture and stable connection of various targets. In order to solve the problem, the application utilizes the inter-satellite connection to expand a plurality of controllable satellites into a ring-shaped multi-body tether satellite formation system, and carries out ring belt enveloping and then enclosing the tether to realize capture of a non-cooperative target with large scale, complex geometric shape, great uncertainty of motion state and inertia information according to a predetermined trajectory. The application has the advantages of high applicability, flexibility, high intelligence, reusability and small size.

The invention belongs to the technical field of aerospace science, and particularly relates to a lightweight target detection method suitable for a low-light space environment, and the method comprises the steps: 1, constructing a lightweight feature extraction backbone network based on MobileNetV4; 2, realizing multi-scale feature fine fusion in combination with TopkSPPF multi-branch pooling, and introducing a C2PSA attention module to improve the target focusing capability; 3, an EdgeFca module is embedded in the feature fusion stage, wavelet edge extraction and a frequency domain weighting mechanism are fused, and feature expression under low illumination is enhanced; and 4, designing a DNiN decoupling detection head and completing model training optimization. According to the method, the problems of low target detection precision, fuzzy edge, poor anti-noise capability, unsuitability for a satellite-borne edge platform and the like in a low-illumination space environment in the prior art are solved, and the method has a frequency domain modeling capability and an edge enhancement mechanism; and real-time identification and perception of non-cooperative targets such as spacecrafts and space debris can be realized under the condition of limited resources.

The invention relates to the technical field of space non-cooperative target capturing and racemization, in particular to a space non-cooperative target variable-stiffness racemization device based on a dielectric elastomer and application of the space non-cooperative target variable-stiffness racemization device, and the space non-cooperative target variable-stiffness racemization device is suitable for attitude control and racemization operation of space tumbling satellites, space debris and other non-cooperative targets. The supporting assembly comprises a middle shaft, a middle shaft servo motor and a fixing base, the middle shaft vertically penetrates through the fixing base, and the middle shaft servo motor is in transmission connection with the middle shaft and used for driving the middle shaft to rotate around the axis of the middle shaft or driving the middle shaft to pitch in the vertical direction so as to adjust the space posture of the arm rotation eliminating body. Compared with the prior art, the racemization device is high in racemization precision, good in operation flexibility, free of fuel consumption and suitable for long-term space tasks.