247 results about "Space environment" patented technology

The invention discloses a power transmission line intelligent inspection method and system based on an unmanned aerial vehicle, and relates to the technical field of power transmission line robots, and the method comprises the steps: collecting three-dimensional space environment data of laser point cloud, visible light, infrared and meteorological data through an airborne multi-mode sensing module; constructing a dynamically updated environment digital twinborn model based on the environment digital twinborn model; online path re-planning is carried out by using an improved fast extended random tree algorithm, and static obstacles and dynamic meteorological risks are synchronously avoided; in a multi-machine cooperation scene, distributing inspection subtasks by adopting a greedy partitioning algorithm based on load balancing; performing real-time defect detection and positioning on the tower image by using a multi-scale feature pyramid convolutional neural network through an edge calculation unit; the whole-process automatic closed loop of power transmission line inspection from environment perception, intelligent planning, collaborative operation to defect identification is realized, and the safety, efficiency and accuracy of inspection operation are improved.

The invention relates to the technical field of space operation equipment, in particular to an electric tool applied to on-orbit operation of a space mechanical arm. The high-precision control and the autonomous operation capability of the tail end of the space manipulator on the tool state in a complex space environment are realized, and the reliability, the flexibility and the automation degree of on-orbit operation are greatly improved. Compared with the prior art, the electric tool has the advantages that the structural integration degree, the function expandability and the intelligent feedback control are remarkably improved, and the electric tool is innovatively designed in the aspects of automatic storage of the bit, operation continuity and space environment adaptability; and the execution efficiency and the safety level of on-orbit maintenance and construction tasks of space stations, satellites and other spacecrafts can be effectively improved.

The invention discloses a dual-path non-cooperative spacecraft pose estimation method based on uncertainty perception, and belongs to the technical field of spacecraft pose estimation. According to the method, a dual-path prediction framework based on a shared backbone network is constructed and comprises a geometric reasoning path and a global context sensing path. In the training stage, prediction results of the two paths are aligned through a geometric consistency loss function, and joint optimization is carried out by combining multi-task losses such as key point regression, classification, rotation and translation regression and the like. In the inference stage, the pose estimation result is adaptively fused according to the predicted variance output by each path, when the variance is low, the output of the global context sensing path is directly adopted, otherwise, the key point projections of the two paths are combined, and the final pose is recovered. The method has higher estimation precision, robustness and interpretability in complex space environments such as shielding, illumination variation and large-scale variation, and provides reliable visual navigation support for on-orbit autonomous tasks.

The invention relates to a satellite-borne electronic hardware design guarantee method and system. The method comprises the following steps: determining a satellite-borne hardware guarantee level (SHL) of satellite-borne electronic hardware; integrating a fault mode injection FM I into a design process of satellite-borne electronic hardware, and adjusting the execution depth of the FM I based on the SHL level; and providing a process cutting engine, and realizing adaptive process cutting based on a DO-254 standard according to the SHL level and in combination with the execution depth of the FM I. The system comprises an SHL evaluation module; an FM I management module; a space environment effect knowledge base; and a process cutting engine. According to the method, the problem that the DO-254 standard is insufficient in adaptability in the aerospace field is solved, the reliability design and verification efficiency of satellite-borne electronic hardware is remarkably improved, and the method is suitable for aerospace tasks such as various satellites and deep space probes.

The invention discloses an anomaly detection method and device based on the receiving power of a low-orbit satellite-borne GNSS receiver, and the method comprises the steps: obtaining a source receiving power sequence of the low-orbit satellite-borne GNSS receiver, and carrying out the enhancement processing based on Doppler frequency shift compensation and ionospheric noise filtering, and then generating a to-be-detected receiving power sequence; performing feature extraction on the to-be-detected receiving power sequence and then generating a receiving power feature vector based on a multi-scale entropy feature and a chaotic feature; and comparing the received power feature vector with a pre-constructed dynamic anomaly threshold to generate an anomaly detection result. According to the method, time sequence mismatching caused by frequency shift is overcome, energy distortion caused by ionosphere disturbance is also remarkably weakened, so that the accuracy and sensitivity of a subsequent nonlinear feature extraction process are guaranteed, and particularly, the robustness and effectiveness of GNSS receiving power anomaly detection can be remarkably improved in a complex dynamic space environment.

The invention relates to a transformer substation unmanned aerial vehicle mounting automatic load changing cooperative control method and system, and the method comprises the steps: building a transformer substation three-dimensional space environment model, and fusing the electromagnetic interference field intensity distribution characteristics and the meteorological disturbance characteristics through the three-dimensional space environment model; constructing a mounting device dynamic behavior model of the unmanned aerial vehicle, wherein the mounting device dynamic behavior model comprises a mounting device constraint parameter set of mechanical arm joint motion constraints and mounting object deformation compensation coefficients; calling the three-dimensional space environment model and the mounting device dynamic behavior model to implement co-simulation verification based on a load switching path planning instruction of the unmanned aerial vehicle; and when a path conflict feature or a load instability feature is detected in the co-simulation verification process, it is determined that co-simulation verification is not passed, and the mounting device constraint parameter set is reconfigured and updated, so that co-simulation verification is passed. The method can adapt to the complex environment of the transformer substation, guarantees smooth mounting and changing operation of the unmanned aerial vehicle, and is suitable for the operation and maintenance scene of the transformer substation.

The invention discloses an on-orbit automatic focusing method for a spaceborne space target observation camera, relates to the technical field of space application of spaceborne cameras, and solves the problems of poor real-time performance and insufficient unattended operation adaptability of a manual focusing technology in the existing focusing technology. And meanwhile, in the automatic focusing technology, the hardware structure is complex, the space environment adaptability is weak, satellite-borne platform resources are limited and difficult to deploy, and focusing is difficult in a severe out-of-focus scene. According to the invention, the realization of automatic focusing is divided into a coarse adjustment stage and a fine adjustment stage. A large step pitch is adopted in the coarse tuning stage, rapid crossing is achieved, and an area adjacent to a positive focus position is rapidly positioned; in the fine adjustment stage, small step pitch is adopted, fine adjustment is achieved, and the peak position is accurately locked. The contradiction between the search speed and the positioning precision is balanced. When far away from the positive focus, a large-step-pitch fast approximation peak region is used, so that the number of iterations and the number of image acquisition frames are greatly reduced; when the focus is approached, small step pitch is switched for fine tuning, and the final precision is ensured.

The invention relates to a ground test gravity unloading device for simulating a space microgravity environment. A base is fixedly arranged at the bottom of a fixed frame; a suspension system is arranged above the base and comprises a fixed pulley block mounted on the fixed frame, a pull rope is wound on the fixed pulley block, the bottom of one end of the pull rope is connected with a dynamometer through a tension spring, and the bottom of the other end of the pull rope is wound on a winch mounted on the base; the hoisting system comprises an external excitation device which is suspended right above the detected object; the displacement sensing system comprises a displacement sensor. The device is simple in principle and construction mode, has a relatively ideal controlled unloading mode, has the test advantage of controllable fine adjustment, is mainly used for simulating a space micro-vibration / microgravity environment to carry out a ground test, reproduces a space environment on the ground to the greatest extent so as to verify the functions and performance of a spacecraft and components thereof, and has a wide application prospect. For example, whether the vibration isolator can work reliably on orbit is verified, so that the on-orbit risk is remarkably reduced, the research and development cycle is shortened, and huge cost is saved.

The invention relates to the technical field of thermal control of commercial spaceflight unfolding mechanisms, in particular to a deformable liquid metal thermal control commercial spaceflight flexible unfolding mechanism which comprises a flexible unfolding mechanism body and a flexible fluid circulation pipeline integrated inside or on the surface of the flexible unfolding mechanism body and synchronously folded and unfolded along with the flexible unfolding mechanism body. The fluid driving and heat exchange unit is arranged in the non-flexible area of the spacecraft platform or the body and is connected with the flexible fluid circulation pipeline to form a closed circulation loop; wherein the flexible fluid circulation pipeline is filled with a liquid metal working medium. The liquid metal working medium has high thermal conductivity and flow characteristics, and is matched with the vein-shaped / grid-shaped microtube array, so that the temperature of each region of the flexible unfolding mechanism can be quickly balanced, and structural stress deformation caused by temperature gradient is effectively eliminated; and the adaptive capacity of the mechanism in extreme space environments such as high and low temperature alternation and intense radiation is greatly improved.

The invention relates to the technical field of space on-orbit robots, in particular to a reconfigurable rigid-flexible coupling space on-orbit assembly robot which comprises a spacecraft cluster, a lifting type parallel robot, a flexible cable system, a flexible cable driving platform, a mechanical arm module and a bistable self-adaptive clamping jaw module. A spacecraft cluster is used as a base, and the modular reconfigurable characteristic is achieved; the lifting type parallel robot located at the bottom of the spacecraft cluster executes position and posture fine adjustment of the spacecrafts by dynamically adjusting the position and posture of a movable platform of the lifting type parallel robot, when an assembly task is executed, the spacecraft cluster reaches a designated position, the relative position and posture between the spacecrafts in the spacecraft cluster are adjusted according to the requirement of the assembly task, and reconstruction of the robot is achieved; the multi-stage and multi-task on-orbit operation adaptive capacity is achieved, on-orbit operation of a variable-size and unstructured space target can be effectively executed, and the operation stability and robustness in the unstable space environment are remarkably enhanced.

The invention discloses a high-reliability satellite service software solidification, verification and loading method and system, and belongs to the technical field of satellite service software, bootloader guide software and on-orbit single particle protection. The problems that satellite service software in an on-orbit program storage area is overturned, the ground does not perceive, and autonomous recovery cannot be achieved after overturning are solved. The method comprises a processing and checking strategy of a satellite service software program, a starting strategy of guiding software and a processing strategy after a program storage area is overturned. The method specifically comprises the following steps of: after a satellite service source program is processed, reading program files of three storage areas in sequence, judging the program of each area through a calculation checksum mode, and if all the programs cannot run, taking out a complete program in a bitwise two-out-of-three mode to run; after the satellite service software is reset, the overturned condition is repaired through verification and moving operation; and when the satellite service program runs, repairing is completed through an overturning detection mechanism. The method is suitable for curing, checking and loading the satellite service software of the high-orbit satellite in a more complex space environment.

The invention discloses a target detection network radiation hardening method for a space spacecraft AI chip, and belongs to the technical field of neural network radiation resistance. The method comprises the following steps: acquiring a target detection network model; a Dropout enhancement model and an exponential bit quantization optimization model are adopted respectively; and carrying out target detection in a space environment by adopting the optimized model. According to the method, the robustness of the neural network in the space radiation environment can be remarkably improved, the reasoning precision and speed of the model can be kept, the problem of reliable operation of the deep learning model in the space environment is solved, and the stability and task success rate of a spacecraft intelligent system are optimized. Aiming at the problem of single event upset caused by high-energy particle radiation in a space environment, the invention provides a training-reasoning collaborative optimization strategy, and provides reliable guarantee for AI application on a spacecraft.

The invention discloses a space false target system based on an inflatable structure and a deployment method thereof. Relates to the technical field of spacecraft protection, and the system comprises a load cabin and a storage cabin, the storage cabin is internally provided with a camouflage module, and the load cabin is internally provided with an inflation module used for inflating the camouflage module, a power supply module used for supplying power and a posture regulation and control module used for controlling the posture; the storage cabin is composed of a plurality of folding plates and can be automatically unfolded so as to release the camouflage modules in the storage cabin. According to the deployment method, satellite release is carried out along with the following steps of attitude adjustment, inflation and the like. Rapid unfolding is achieved through the folding type storage cabin and the torsional spring hinge, rapid deployment and stable control are achieved in combination with the inflation module and the posture regulation and control module, and the problems that a traditional system is complex in deployment, low in unfolding efficiency and insufficient in posture adjustment are solved; the system has the advantages of rapid deployment, compact structure, stable and reliable attitude and suitability for a dynamic space environment.

A system includes multi-module satellites designed to autonomously or semi-autonomously perform experiments in a space environment for investigators. Each multi-module satellite includes multiple testing modules each associated with a different investigator. Each testing module includes a testing computer that runs experiments. A main flight computer on the multi-module satellite communicates with the testing computers for each module, passing information between the testing computers and a main control system. To perform an experiment in a testing module, the multi-module satellite system collects and stores observation data from sensors of the testing module, controls a controller of the testing module to perform the experiment, transmits the observation data from the testing module to an application associated with the testing module via a main control system, and executes instructions receives from the application via the main control system by controlling the controller of the testing module based on the received instructions.

The invention discloses a GEO and SSO cross-platform satellite high-energy proton data collaborative calibration method based on a solar proton event, and the method comprises the steps: obtaining high-energy proton observation data and space environment disturbance parameter data of GEO and SSO, and carrying out the preprocessing, and obtaining high-energy proton data, satellite space-time position data and environment parameters of a unified flux type; screening high-energy proton data during the event period according to the sun proton event definition to obtain a plurality of event data sets and grouping the event data sets; performing alignment processing on the screened high-energy proton data of the GEO and the SSO; based on the power law spectrum characteristics of the solar proton event, constructing the energy matching relation of each energy channel of GEO and SSO, and determining the effective energy and energy interval of each energy channel of SSO through point-by-point spectrum fitting and statistical inversion; and recalculating the differential flux of the GEO in a corresponding energy channel by using the calibrated effective energy, establishing a point-by-point scatter matrix of the two types of satellite data, and performing linear fitting and correlation analysis to realize calibration.

The application discloses a kind of satellite-borne infrared emissivity differential measurement method and device using cold black background, belong to spacecraft thermal control and material on-orbit testing technical field, purpose is to eliminate environmental stray radiation and conduction heat leakage interference, realize material emissivity high-precision in-situ on-orbit test.The application relies on deep space cold black environment and differential disturbance thought, supporting layout emissivity known standard unit and unit to be measured, make two in consistent light thermal condition, respectively establish transient heat balance equation.Because two kinds of units are consistent, such as common-mode interference of stray radiation, conduction heat leakage, two formula difference can be removed interference term, only keep and emissivity related radiation heat loss term.Through the design of different thermal control conditions (such as balance heating, constant temperature control, dynamic heating), the real emissivity of the material to be measured is solved.The application is suitable for in-situ, high-precision measurement of the infrared emissivity of spacecraft surface materials, especially intelligent thermal control materials such as thermochromic materials in space environment.

The present application belongs to the field of ground simulation facilities, and particularly relates to a gravity level ground simulation device and method for extraterrestrial environment welding. The device comprises a general control system, a vacuum system, an outer pipe assembly and a gravity level control mechanism. The general control system can control various parameters during the operation of the device. The vacuum system and the gravity level control mechanism provide two space environment characteristics of high vacuum and different levels of gravity for experiments requiring space simulation. The vacuum degree in the device can reach 10 ‑4 Pa, which can simulate the high vacuum environment in space. The adjustment of different gravity levels of 0-4g0 can ensure that the device has the ability to simulate the gravity of various extraterrestrial planets. Moreover, the device has the advantages of flexible and stable gravity level, high experimental repetition rate, low cost, high safety, etc. and can be used to study the basic welding theory under different gravity levels in space environment, thereby filling the blank of the gravity level ground simulation device specially used for extraterrestrial environment welding.

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.

Embodiments of the present application provide a space target orbit prediction method, a prediction device, an electronic device and a medium. The method comprises: obtaining two-line orbital elements of a space target at a current time, space environment data and perturbation coefficients, the perturbation coefficients being coefficients in a space target orbit prediction model; correcting the two-line orbital elements and / or the perturbation coefficients based on a pre-trained parameter correction model, the two-line orbital elements, the perturbation coefficients and the space environment data, to obtain corrected data, the corrected data comprising corrected two-line orbital elements and / or corrected perturbation coefficients; and predicting orbit information of the space target at a preset future time based on the space target orbit prediction model and the corrected data. The method makes the predicted orbit information more accurate.

The application provides a satellite communication power adaptive regulation method, system and device, which divides the space where satellite communication belongs into multiple space grid areas according to a preset space division scale; acquires satellite sensing data, space weather data and near-earth weather data in each space grid area to determine communication link loss evaluation data corresponding to each space grid area; generates space interference summary information according to the loss evaluation data corresponding to each space grid area and location data thereof; and adjusts the transmission power of satellite communication in each space grid area according to the space interference summary information. The method and system of the application collect weather data in the space area and the near-earth area thereof to determine loss evaluation data, and realize dynamic adaptive adjustment of satellite transmission power in each space grid area based on the loss evaluation data, thereby improving the reliability of satellite communication in a complex space environment.

The invention provides a flexible solar cell irradiation attenuation coefficient estimation method comprising the following steps: orbital parameters are combed, and spacecraft orbital parameters and space environment parameters are obtained; based on the orbit parameters and the space environment parameters, establishing an irradiation dose calculation model of the flexible solar cell; performing a ground equivalent test based on the irradiation dose calculated by the irradiation dose calculation model; and determining the irradiation attenuation coefficient of the solar cell in combination with test data and historical data. According to the method for estimating the irradiation attenuation coefficient of the flexible solar cell, the irradiation dose calculation model suitable for the flexible solar cell is constructed, the on-orbit performance attenuation coefficient of the solar cell array can be accurately obtained, and the accuracy of irradiation dose estimation is improved; scientific basis is provided for solar cell array design and on-orbit energy management, and reliability and design rationality of a spacecraft energy system are effectively improved.

The invention relates to a vessel for the long-term storage of DNA in space at a constant temperature of -196 °C. The aim is to protect biological samples – especially DNA – for decades to centuries from the extreme environmental conditions of space, including vacuum, intense radiation, extreme temperature fluctuations and mechanical stresses. The vessel has a three-layered structure: 1. Inner chamber made of boron nitrogen nanotubes (BNNTs) that offer outstanding protection against cosmic radiation, high mechanical strength, chemical inertness and temperature resistance. 2. Middle insulating layer made of aerogel that minimizes heat exchange and keeps the cryogenic temperature constant. 3. Outer protective layer made of titanium, which protects against micrometeorites, It protects against physical impacts and corrosion. Technical advantages: • Long-term stability of DNA through consistently low temperatures. • Effective radiation protection against cosmic and solar radiation. • Excellent thermal insulation thanks to aerogel. • Mechanical robustness due to titanium. Areas of application: • Securing and archiving genetic material for research, space travel and long-term preservation. • Provision of DNA for future scientific or biological restoration projects. Special feature: The capsule is compact, space-compatible, and can be used as part of space missions, space stations, or interplanetary projects.

The invention provides a movable baffle plate for radiometric calibration in vacuum circular mould equipment, which is provided with a base, a movable baffle plate module, a driving guide module, a limiting module and a control module, the base is fixed on a bottom test platform of space environment simulation test equipment, and the movable baffle plate module comprises a framework and an expansion plate heat sink, the framework is used for providing support for the expansion plate heat sink, a rack is arranged below the framework, rolling wheels are symmetrically arranged on the two sides of the rack, the driving guide module is provided with a vacuum motor, a commutator and a gear, the vacuum motor provides power for the gear, and the gear is matched with the rack on the framework. The technical problem that the accuracy of a radiometric calibration result is reduced due to the fact that an existing large spaceflight device or an on-orbit camera is easily affected by blackbody temperature rise radiation when carrying out radiometric calibration is solved. The device can be widely applied to vacuum circular mould equipment tests.

The invention provides heat-conducting silicone grease for spaceflight electronic equipment and a preparation method of the heat-conducting silicone grease. The heat-conducting silicone grease is prepared from the following components in parts by weight: 3-8 parts of ethyl silicone oil with the viscosity of 50-1000 mPa.s, 3-8 parts of phenyl silicone oil with the viscosity of 50-1000 mPa.s, 1-5 parts of modified silicone oil, 60-80 parts of zinc oxide with the particle size of 2-7 microns and 15-25 parts of zinc oxide with the particle size of 0.1-1 micron. The invention aims to provide the heat-conducting silicone grease which has high heat-conducting property, good low-temperature resistance and cosmic ray resistance and is stable and reliable, so that the heat dissipation requirement of spaceflight electronic equipment in an extreme space environment is met, and the effective thermal design of the prepared heat-conducting silicone grease can greatly prolong the service life of a spacecraft and improve the working reliability of the spacecraft.

The invention discloses an important data error correction method suitable for an aerospace power supply and distribution single machine. According to the method, the Hamming code principle and the binary coding principle are utilized, and the characteristics of a microcontroller of the aerospace power supply and distribution stand-alone are combined, so that an error correction coding and decoding method is designed. According to the method, the single-machine micro-control system can correct a certain degree of data bit flipping errors under the condition that the data bit flipping errors occur under the influence of space environments such as space single particles, errors of important data caused by the space environments are reduced, and then part of autonomous control operations threatening spacecraft safety are prevented from occurring.

The invention discloses a complete sequence image acquisition method and device of a target spacecraft. The method comprises the steps of obtaining spatial characteristics of a target spacecraft and imaging characteristics of an observation camera, and performing parameterization processing on the spatial characteristics and the imaging characteristics to obtain a target parameterization model and a camera parameterization model; optimizing the model based on a unit area pixel value, and determining a viewpoint planning optimization target; constructing a target constraint by combining the space illumination environment parameters of the on-orbit spacecraft, the camera imaging constraint and the security constraint; constructing an optimization model based on the model, the optimization target and the constraint, and solving to obtain the optimal viewpoint pose of the camera; adjusting a camera track and a posture acquisition image, and updating the target parameterized model according to the image; and iteratively executing the steps, and integrating a plurality of images to obtain a complete sequence image. According to the method, the sequence image quality is improved, high-quality data support is provided for three-dimensional reconstruction, the method adapts to a complex space environment, and the task requirements of space monitoring, resource detection and the like are met.

This invention discloses a method and system for simulating the consistency of droplet generator spreading characteristics between ground and space, used to obtain the spreading characteristics of droplet generators in a vacuum environment. It can equivalently convert ground test results into space test results, solving the problem of equivalent measurement for consistency between ground and space. By scaling down the operating parameters of the jet spreader under rated conditions, it overcomes the adverse effects caused by ground test environment limitations leading to excessively thick droplets that do not match the actual spreading effect in the space environment, thus achieving equivalent measurement for consistency between ground and space. Furthermore, by placing several droplet collectors with the same surface area and material at different locations and measuring the mass increment of multiple droplet collectors, it achieves measurement of liquid film thickness uniformity.

The application relates to a space target behavior recognition method based on multi-modal data fusion, and belongs to the fields of artificial intelligence, computer vision, spaceflight and simulation technology. The method comprises multi-modal data set construction based on a generative adversarial network, multi-modal data feature fusion, and target behavior recognition based on trajectory fitting correlation. The application realizes high-accuracy recognition of target on-orbit behavior in a complex space environment, and provides important support for space obstacle avoidance, autonomous detection and intelligent decision-making of a spacecraft.

The invention provides a ventilation wall test system and method for Mars aircraft testing, and the system comprises a space environment simulator which can simulate the low-pressure and low-temperature environment of Mars, a gravity unloading device which is installed in the space environment simulator, a ventilation wall assembly which is used for generating a controllable simulation wind field, and a ventilation wall driving device. The wind wall assembly is arranged in a wind guide structure of the space environment simulator and comprises a plurality of fan array units, each fan array unit is of a multi-layer series connection structure, the distance between the adjacent fan array units can be adjusted according to the wind speed of the controllable simulation wind field, and each fan array unit comprises a plurality of fans arranged at non-equal intervals. The Mars transient wind field where the to-be-tested unmanned aerial vehicle is located is accurately simulated, and accurate simulation of distribution of the Mars wind field in time and space and low gravity of the Mars is achieved.

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.