102 results about "Asteroid" patented technology

The invention relates to an asteroid global terrain three-dimensional reconstruction method for illumination variation, and the method comprises the following steps: inputting an asteroid optical image, estimating the pose of a camera, generating a sparse point cloud, and initializing a Gaussian radiation field; using the image segmentation large model to output a segmentation mask of the asteroid optical image, and pruning the Gaussian radiation field; identifying a shadow region on the surface of the asteroid by combining a # imgabs0 # mixed mask output by a Gaussian radiation field; the camera position, the spherical harmonic coefficient and the Hash code are combined with the angle of the incident light to be input into a neural network, and color values of Gaussian primitives of illumination and shadow areas are regressed; depth normal consistency loss and rotation variance and scale constraint loss are added, optimization of a Gaussian radiation field is jointly supervised in combination with luminosity loss, a Gaussian opacity field is calculated, and a three-dimensional model of the asteroid global terrain is extracted. According to the method, the shadow region on the asteroid can be identified, and the three-dimensional reconstruction precision of the asteroid with surface illumination variation is improved.

The invention discloses a pseudo-spectral convex optimization-based method for optimizing a low-thrust trajectory near an asteroid, which comprises the following steps of: establishing a kinetic equation of an orbital motion of a spacecraft near the asteroid, discretizing the kinetic equation through a flipped Radau pseudo-spectral method, establishing a problem of no gravitational field and no anti-collision constraint, and solving by using a convex optimization method to obtain an initial nominal solution; constructing a gravitational field model in the kinetic equation based on a four-mass-point model, and establishing an asteroid nearby anti-collision model; establishing a convex optimization problem of an anti-collision small-thrust trajectory near the asteroid through convex methods such as nominal value replacement and Taylor expansion; establishing a successive solution model, and obtaining an optimal solution through sequence convex optimization; according to the method, a flipped Radau pseudo-spectrum method and convex optimization combined pseudo-spectrum convex optimization method is adopted, the motion low-thrust trajectory optimization of the spacecraft near the asteroid is realized, and the calculation efficiency is improved by using a four-mass-point gravitational field model.

The invention relates to the technical field of asteroid simulant testing, and discloses an asteroid simulant spinning process dynamic testing device and a testing method.The asteroid simulant spinning process dynamic testing device comprises a fixed table, a rotating table, a driving assembly, five telescopic assemblies and a measuring plate, the rotating table is rotationally arranged on the surface of the fixed table, and the driving assembly is arranged in the fixed table; five telescopic rods are further arranged on the surface of the rotating table, a measuring plate is arranged at the telescopic end of the telescopic assembly, and a measuring sensor facing the asteroid simulant is arranged in the measuring plate; the five telescopic assemblies and the measuring plate are arranged on the surface of the rotating table, the measuring plate corresponds to the asteroid simulant, and a measuring sensor in the measuring plate is matched, so that synchronous acquisition of three-dimensional axial dynamic deformation data and multi-dimensional measurement covering the periphery and the top of the asteroid simulant can be realized; therefore, a three-axis length and time relation curve of the simulant at different rotation rates and a time-varying curve of the flattening and elongated ellipsoid eccentricity rate are accurately obtained.

The invention relates to an asteroid surface fine vision three-dimensional reconstruction method fusing laser radar data. The method comprises the following steps: collecting and sorting visual camera data and laser radar point cloud data; obtaining sparse point cloud for the filtered visual camera data, and initializing a 3D Gaussian grid center by using the sparse point cloud; generating an asteroid instance segmentation mask by combining a visual camera image with sparse point cloud projection point prompt; gaussian volume rendering: optimizing the difference value between the rendered image and the true-value visual camera image; the generated instance segmentation mask is subjected to background Gaussian rejection based on cumulative transparency, Gaussian surface geometric regularization is realized by applying Gaussian depth rasterization, and a rasterization depth value is optimized by taking laser radar point cloud data as supervision. According to the invention, the method can achieve the precise three-dimensional reconstruction of the surface of the asteroid in combination with the laser radar point cloud data under the condition of global or local visual imaging, reduces the manual participation, shortens the reconstruction period of the asteroid, and improves the precision of the three-dimensional reconstruction of the surface of the asteroid.

The invention belongs to the technical field of aerospace asteroid defense, and relates to a variable mass gravitational traction deflection asteroid orbit full-flow design method based on real working condition constraint, which comprises the following steps of: obtaining orbit elements corresponding to a target asteroid according to initial conditions; substituting into a high-precision numerical integration model, and calculating perigee moments and perigee distances under the condition that the gravitational traction action is not applied; according to the early warning time requirement, the carrying capacity and the real engineering constraint, a genetic algorithm and sequential quadratic programming are used, the maximum perigee deflection distance serves as a target, and a transmitting window is optimized and solved; and substituting the optimized emission window into the high-precision deflection efficiency numerical integration model, and outputting the asteroid perigee deflection distance. According to the method, comprehensive analysis is carried out in combination with early warning time, emission capability and actual working conditions from the perspective of a whole-process task, so that the authenticity and engineering applicability of a calculation result are ensured.

A compact vibratory burrowing probe, particularly beneficial in low gravity space exploration environments, uses lateral or stirring-like vibrations to fluidize a surrounding regolith, thereby decreasing the penetration resistance, and compensating for the light overhead weight to improve the burrowing action of the probe into the surface of the terrain of explored moons, planets, or asteroids. Included is a novel vibratory mechanism capable of imparting the novel lateral or stirring vibration, as well as a more conventionally oriented longitudinal vibration.

The invention relates to the technical field of asteroid motion simulation, and discloses a simulation experiment device suitable for a gravel pile asteroid, the simulation experiment device comprises a vacuum assembly, a suspension assembly, an objective table, a three-phase winding and a camera, the suspension assembly is arranged in the vacuum assembly, and the objective table is arranged at the top of the suspension assembly; the objective table is used for placing a gravel pile asteroid simulant, a three-phase winding is further arranged on the objective table, and a camera is arranged in the vacuum assembly, located at the top of the gravel pile asteroid simulant and used for shooting the movement condition of the gravel pile asteroid simulant; the gravel pile asteroid simulant is placed on the objective table and is in a vacuum state, the gravel pile asteroid simulant is suspended and rotated through the suspension assembly and the three-phase winding, the movement condition of an asteroid in a real state can be simulated, recording can be carried out through the camera, and follow-up observation and analysis are facilitated.

A factory for manufacturing useful products while orbiting is space uses concentrated solar energy, high vacuum, and the low temperatures available in a space environment. Gyroscopic forces from rotating machinery are carefully controlled. Liquids, gases, and solid minerals are separated from asteroid and lunar regolith resources.

This invention provides a method and system for high-fidelity physical modeling and detection performance evaluation of space targets, relating to the field of deep space exploration technology. The method first acquires the relative motion parameters of the spacecraft and the asteroid, as well as camera parameters, and determines the static apparent magnitude based on observation geometry and the asteroid's physical characteristics. Then, it calculates the angular velocity modulus through relative velocity, combines it with camera parameters to obtain tail parameters, and quantifies the equivalent magnitude loss and effective apparent magnitude based on a piecewise model. Subsequently, it constructs a two-dimensional parameter grid of focal length and exposure time, calculates the effective signal-to-noise ratio and detection margin for each combination, and selects the optimal parameters using a heatmap. Finally, it generates a high-fidelity simulation image and feeds back the observation values ​​to the guidance, navigation, and control system via a UDP asynchronous interface. This invention achieves quantitative assessment of tail loss and automated parameter optimization, balancing high fidelity and real-time performance, and improving detection accuracy and system reliability.

This is a self-replicating nanofactory which uses nano-electron lithography to assemble copies of itself along with nanoscale precise products. The device is 100 nm×100 nm×100 nm in size making it a type of nanomachine that assembles products being a nanofactory. The device is composed of carbon nanotubes, silicon carbide and silica which are naturally available in the form of carbon dioxide and silicon dioxide on many planets and asteroids in the universe. This device uses sugar to power itself as the carbon based nanomachines being cells and bacteria use as a power source which can be naturally sourced in a environment as well.NameCityStateCountryWestPendletonINUSNanoroboticsLLCAssignee:West Nanorobotics LLCAppl. No.:63 / 474,335Filed:Aug. 9, 2022

A communication quantization distributed spacecraft formation control method comprises the following steps: establishing a spacecraft dynamic model near an asteroid, modeling a gravitational field near the asteroid by adopting a polyhedron method, constructing a spacecraft formation near a balance point in the gravitational field, and establishing a relative kinematic model of the spacecraft formation; a logarithm quantizer is constructed to quantify state variables transmitted between spacecrafts, a distributed spacecraft formation controller based on communication quantization is constructed, and finally, the quantized state variables are input into the controller to obtain a spacecraft formation deployment strategy. According to the method, the formation control strategy of the spacecrafts near the asteroid is improved by quantifying the communication information, and the distributed spacecraft formation controller based on communication quantification is constructed, so that the problem that the formation communication frequency and the data transmission rate of the existing formation control method near the asteroid are too harsh is solved.

The present invention discloses a target structure registration measurement method and system for planet and asteroid exploration. The method is implemented by a time-of-flight camera installed on a satellite. The method comprises: receiving images and depth information of the surface environment of a target star body collected regularly by the time-of-flight camera, fusing the images and depth information, and generating three-dimensional point cloud data; filtering the three-dimensional point cloud data to obtain denoised three-dimensional point cloud data, and storing the denoised three-dimensional point cloud data in a data list; extracting effective area information from the denoised three-dimensional point cloud data to obtain data of the effective point cloud area; then performing iterative closest point method registration to obtain a transformation matrix; extracting the denoised three-dimensional point cloud from the data list, transforming it using the transformation matrix, and obtaining registered overall three-dimensional point cloud data; and extracting features from the registered overall three-dimensional point cloud data to obtain distance information, position information, and shape information of the surface of the target star body.

The invention provides a method and a device for monitoring a near-earth asteroid, belongs to the technical field of universe navigation, and can realize full-range monitoring of the near-earth asteroid in a relatively large range. The method comprises the following steps: determining a nominal orbit of a detection spacecraft according to an earth revolution orbit, solar center gravity and a genetic algorithm; acquiring a fuel consumption index function of the detection spacecraft; and based on the nominal orbit, the fuel consumption index function and a linear quadratic regulator, determining the control acceleration required by the detection spacecraft to run on the nominal orbit.

The present application relates to a kind of asteroid global terrain three-dimensional reconstruction method for illumination change, comprising the following steps: input asteroid optical image, estimate camera pose and generate sparse point cloud, initialize Gaussian radiation field;Using image segmentation large model outputs the segmentation mask of asteroid optical image, prunes Gaussian radiation field;In combination with the mixed mask output by Gaussian radiation field, identify the shadow area of asteroid surface;The camera position, spherical harmonic coefficient and hash coding are combined into incident light angle, input into neural network, and the color value of Gaussian cell of illumination and shadow area is regressed;Add depth normal consistency loss and rotation variance and scale constraint loss, combine photometric loss to jointly supervise the optimization of Gaussian radiation field, calculate Gaussian opacity field, extract the three-dimensional model of asteroid global terrain.The present application can identify the shadow area on asteroid, improve the three-dimensional reconstruction precision of asteroid with surface illumination change.

The present invention belongs to the field of aerospace asteroid defense technology and relates to a full-process design method for variable-mass gravitational traction deflection of an asteroid orbit based on real-world operating constraints. The method comprises the following steps: obtaining the orbital elements corresponding to the target asteroid based on initial conditions; substituting them into a high-precision numerical integration model to calculate the perigee moment and perigee distance without gravitational traction; optimizing the launch window using a genetic algorithm and sequential quadratic programming, with the goal of maximizing the perigee deflection distance, based on warning time requirements, launch capacity, and real-world engineering constraints; and substituting the optimized launch window into a high-precision deflection efficiency numerical integration model to output the asteroid's perigee deflection distance. This method, based on the full-process mission perspective, conducts a comprehensive analysis combining warning time, launch capacity, and actual operating conditions to ensure the authenticity and engineering applicability of the calculation results.

A factory for manufacturing useful products while orbiting is space uses concentrated solar energy, high vacuum, and the low temperatures available in a space environment. Gyroscopic forces from rotating machinery are carefully controlled. Liquids, gases, and solid minerals are separated from asteroid and lunar regolith resources.

The application relates to an asteroid selection method and device, computer equipment and a storage medium. The method comprises the following steps: first, dividing the orbit of a target detector into a first time period to obtain a plurality of time periods after division; then, dividing each time period into a second time period to obtain a plurality of sub-time periods corresponding to each time period; then, clustering asteroids around the target detector in each sub-time period to obtain a plurality of clustered asteroid sets; then, determining a candidate asteroid set corresponding to each sub-time period according to the position information of each asteroid in each clustered asteroid set in each sub-time period; and finally, selecting a candidate asteroid set corresponding to a sub-time period from the candidate asteroid sets corresponding to each time period to construct a target asteroid set. The asteroids screened by the above method can achieve higher navigation accuracy.

The present invention discloses a method and device for estimating the internal dielectric constant of an asteroid based on a single-station orbital radar, relating to the field of planetary exploration. The method primarily comprises: separating diffraction waves from single-station orbital radar recordings, determining the number of diffraction points within the asteroid and the range of values ​​for the scanned dielectric constant; setting a diffraction point and a scanned dielectric constant value within the asteroid, solving the eikonal equation to obtain the travel time of the diffraction wave, and calculating the superposition energy of the diffraction waves within a fixed time window starting from the travel time; repeating the previous steps until all positions within the asteroid and the range of values ​​for the scanned dielectric constant are traversed; selecting several local maxima from all the superposition energies, determining the diffraction point positions and scanned dielectric constant values ​​corresponding to all the maxima; and interpolating the results to obtain the dielectric constant distribution within the asteroid. Implementing the method and device for estimating the internal dielectric constant of an asteroid based on a single-station orbital radar provided by the present invention can quickly and accurately obtain the internal dielectric constant distribution of the asteroid.

The invention provides a K / Ar method dating experiment method without quality correlation. A related test system comprises a controllable excitation X-ray tube, an X-ray energy disperse spectroscopy and a control and data acquisition computer, the method comprises the following steps: firstly, preprocessing a sample to be tested, optimizing components of a test system, then carrying out system test, and finally processing test data. The method has the advantages that the influence of non-uniform contents of K and Ar elements in the sample on dating precision is avoided, dating can be directly carried out for in-situ analysis of samples without Ar isotope interference or extraterrestrial celestial bodies, and Ar isotope measurement does not need to be carried out by other instruments. Compared with the traditional K and Ar discrete dating technology, the method provided by the invention has the advantages of less resource demand, high measurement precision and simple and fast implementation process, and is especially suitable for extraterrestrial celestial body in-situ dating in vacuum environments such as the moon and the asteroid.

The present invention belongs to the technical field of probe attitude tracking control, and specifically relates to a method for attitude tracking control of a probe orbiting an asteroid based on adaptive iterative learning. The method comprises the following steps: Step 1: The probe mathematical model outputs two state variables, namely attitude and angular velocity; Step 2: The attitude and angular velocity are fed back to the input of the control system, and the error attitude and error angular velocity are respectively subtracted from the given desired attitude and desired angular velocity; Step 3: A probe attitude tracking error system is established based on the two error states, where the uncertainty and external interference in the system are regarded as total disturbances and estimated using an adaptive law; Step 4: An attitude tracking controller is designed based on an adaptive iterative learning algorithm. The present invention proposes a design method for an adaptive iterative learning controller based on an all-wheel drive system approach and sliding mode control. The designed adaptive iterative learning controller has excellent control performance and a small number of adjustment parameters.

The invention discloses an asteroid internal structure three-dimensional reverse time migration imaging method based on a single-station radar, and belongs to the technical field of planet detection, and the method comprises the steps: estimating wavelets from the observation data of the single-station radar; constructing an asteroid three-dimensional dielectric model based on a velocity analysis result and prior information; selecting a group of transmitting and receiving source positions, and performing forward modeling by taking wavelets as excitation sources to obtain forward transmission wave fields of electric field components at all moments; interchanging the positions of the transmitting source and the receiving source, and performing forward modeling by taking radar observation data as an excitation source to obtain a corresponding back propagation wave field; zero-delay cross-correlation is carried out on the forward and backward propagation wave fields, and an imaging result of a single source point is obtained; repeating the three steps until the imaging results of all the source points are obtained; and superposing imaging results of all source points, and suppressing low-frequency noise through Laplace filtering to obtain a high-resolution three-dimensional imaging result. By implementing the method provided by the invention, the three-dimensional internal structure of the asteroid can be quickly and accurately obtained, and then a reliable basis is provided for analyzing the origin and evolution of the asteroid.

The present invention discloses a small-thrust trajectory optimization method near an asteroid based on pseudospectral convex optimization, including: establishing the dynamic equation of the spacecraft's orbital motion near the asteroid, discretizing the dynamic equation by the flipped Radau pseudospectral method, establishing a problem of no-gravitational-field and no-collision constraint, and using a convex optimization method to solve and obtain an initial nominal solution; constructing a gravitational field model in the dynamic equation based on a four-particle model, and establishing a collision avoidance model near the asteroid; establishing a convex optimization problem of small-thrust trajectory for collision avoidance near the asteroid through convexification methods such as nominal value substitution and Taylor expansion; establishing a successive solution model, and obtaining the optimal solution through sequential convex optimization; the present invention adopts a pseudospectral convex optimization method combining the flipped Radau pseudospectral method and convex optimization, realizes the optimization of the small-thrust trajectory of the spacecraft's motion near the asteroid, and improves the calculation efficiency by using the four-particle gravitational field model.

The invention provides a spacecraft autonomous modeling method for an unascertained near-earth asteroid target, and belongs to the technical field of spaceflight technology and application thereof, and the method comprises the steps: carrying out typical target extraction, BRDF (Bidirectional Reflection Distribution Function) measurement and characteristic measurement, and application scene measurement, and generating a digital target set; carrying out data processing on the spacecraft, wherein the data processing comprises on-board processing and on-board verification; carrying out algorithm ground verification, including algorithm correctness verification, algorithm clipping and acceleration, and algorithm edge deployment; the satellite-ground combined on-orbit application is specifically characterized in that when a spacecraft is close to a target, target modeling is carried out, data is acquired based on a sensor for on-device processing, target modeling is completed, then data is newly acquired by the sensor for on-device verification and model updating, and model reconstruction and ground processing are introduced by limiting the number of verification times. According to the method, the modeling accuracy can be improved, and the efficient autonomous modeling capability of the spacecraft is comprehensively formed.

The present disclosure provides a multi-asteroid exploration trajectory generation method, system and storage medium; for the first d time transfer of the multi-asteroid exploration trajectory, the undetermined Fourier coefficients of the position vector function are solved through the boundary conditions of the transfer starting time and the transfer ending time and the preset thrust acceleration constraint, and the corresponding candidate transfer trajectory is generated; wherein the position vector function is obtained by pre-construction using the Fourier series; the candidate transfer trajectory is the trajectory from the first d time transfer of the outgoing asteroid to the candidate target asteroid; according to the transfer cost of each candidate transfer trajectory, the preferred transfer trajectory of the first d time transfer is obtained by screening, and the candidate target asteroid corresponding to the preferred transfer trajectory is taken as the outgoing asteroid of the first d +1 time transfer; and the optimal exploration trajectory is generated according to the preferred transfer trajectories of all transfers. This method can quickly lock the optimal exploration path that can be achieved, greatly shortening the mission planning cycle.

This invention relates to a dynamics-based simulation method for the orbits of target asteroids and impactors, belonging to the technical field of aerospace technology and its applications. The invention aims to address the problems of poor accuracy and stability in existing asteroid impact simulation processes. This invention establishes the asteroid orbital dynamics equations, substituting the position vector into these equations to recursively obtain the asteroid's orbital model; it also establishes the impactor orbital dynamics equations, substituting the impactor's initial three-dimensional position, velocity, and acceleration into these equations, and combining them with the target asteroid's orbital model to recursively obtain the initial orbital model from the impactor's initial position to a distance of S km from the target asteroid; using this initial model, it establishes the full dynamics equations for the final segment of the impactor's orbit, obtaining the orbital model from the impactor's position S km from the target asteroid to the point of impact. This method is primarily used for impactor orbit simulation.

The invention provides an asteroid star environment reconstruction method based on multi-source heterogeneous data cross-modal fusion. The method comprises the following steps: acquiring visual sequence images, sequence RGB-D images and radar point cloud data in a target space from different distances, angles and scales in real time by using a visual camera, a ToF camera and a laser radar for observing a robot load; performing preliminary reconstruction on a visual sequence image shot by a visual camera to obtain a dense three-dimensional point cloud of a target; fusing the dense three-dimensional point cloud with a currently latest acquired visual sequence image output by a visual camera in a target space from different distances, angles and scales, a sequence RGB-D image output by a ToF camera and radar point cloud data output by a laser radar to obtain a feature point cloud model; if local precise reconstruction needs to be carried out, the feature point cloud model and the exploration robot are used for obtaining local point cloud data through a laser radar loaded by the exploration robot to carry out registration after reaching the surface of the asteroid, and a local reconstruction point cloud model is obtained.

The application discloses a UT transformation-based impact small celestial body orbit terminal state optimization method and belongs to the technical field of aerospace. The application realizes the method as follows: positions and velocities of the earth and small celestial bodies are obtained according to ephemeris and kinematic equations of the small celestial bodies, and the velocity variation of the small celestial body after the impact of a probe is defined as a constant, so that two angles of the velocity change direction of the small celestial body after the impact of the probe are taken as impact design variables; UT transformation is used to perform error evolution of the small celestial body, so that the space-time distribution probability of the target small celestial body in a future period of time is obtained; the space-time distribution probability of the small celestial body is calculated, the instantaneous impact probability under the given impact design is calculated based on a Legendre-Gauss quadrature method, and the overall impact probability of the small celestial body is obtained by integral based on a Newton-Cotes quadrature method; and based on the impact probability calculation method, the impact design variables are optimized in combination with a global optimization algorithm, so that the impact probability of the small celestial body under the optimized variables is the lowest.

The present invention discloses a method for designing an orbit of a kinetic impact mission on a near-Earth asteroid with the optimal deflection effect, comprising the following steps: S1, selecting the initial parameters of the spacecraft, including the departure and arrival times of the spacecraft; S2, designing the spacecraft orbit as a splicing of three segments, namely a large elliptical Earth parking orbit, an Earth escape orbit starting from the large elliptical orbit, and an interplanetary transfer orbit, and calculating the orbit parameters; S3, evaluating the deflection effect of the target near-Earth asteroid; S4, traversing all possible departure and arrival times of the spacecraft, repeating steps S1 to S3, drawing a contour map of the deflection distance versus the departure and arrival times of the spacecraft, and determining the optimal spacecraft launch window from it after eliminating unreasonable times. By adopting a large elliptical Earth parking orbit and screening the spacecraft launch window, the present invention enables the mass and relative velocity of the spacecraft to be relatively large when impacting the asteroid, thereby achieving the optimal asteroid deflection effect.

The invention relates to the technical field of asteroid simulants, and discloses a manufacturing method and a testing method of a gravel heap asteroid simulant, and the manufacturing method comprises the following steps: mixing raw material powder and magnetic powder, putting the mixture into stirring equipment, and wetting; controlling the stirring equipment to rotate so as to obtain a plurality of nuclear particles with different diameters; after the surfaces of the core-shaped particles are coated with an adhesive, the core-shaped particles are bonded and fixed to form spherical particles; and carrying out high-temperature hardening on the spherical particles to obtain the macadam pile asteroid simulant. Compared with the problems of particle interaction model simplification, experimental verification difficulty, high parameter uncertainty, limited computing resources and the like in the existing computer simulation gravel pile asteroid technology, the manufacturing method disclosed by the invention has the advantages that the raw material powder and the magnetic powder are mixed and treated by a special process, so that the physical characteristics of the asteroid can be truly restored; the method is directly used for laboratory experiments to enhance verification capability.

A compact vibratory burrowing probe, particularly beneficial in low gravity space exploration environments, uses lateral or stirring-like vibrations to fluidize a surrounding regolith, thereby decreasing the penetration resistance, and compensating for the light overhead weight to improve the burrowing action of the probe into the surface of the terrain of explored moons, planets, or asteroids. Included is a novel vibratory mechanism capable of imparting the novel lateral or stirring vibration, as well as a more conventionally oriented longitudinal vibration.