1786 results about "Spaceflight" patented technology

Systems and methods for providing a space launch service platform (SLSP) that integrates artificial intelligence and data analytics to support launch operations. The SLSP may connect to multiple data sources, collect data, and standardize the collected data according to regulatory and operational standards. The SLSP may evaluate launch safety and risks using standardized data and generate a situational analysis for decision-making. The SLSP may provide graphical overlays and decision-support tools to highlight optimal launch windows and potential risks.

The invention provides a dynamic scheduling management method and system for spaceflight measurement and control task resources, and relates to the technical field of spaceflight measurement and control resource scheduling. Defining a task feature vector according to the time sensitivity, the resource demand intensity and the coupling degree between the tasks of the tasks; satellite health parameters, equipment working conditions and environment data are collected in real time through a satellite-ground Internet of Things terminal, and digital twin bodies are constructed; performing priority ranking, resource matching and conflict resolution mechanism on the tasks according to the task feature vectors, performing global optimization scheduling on the spaceflight measurement and control tasks, and executing cross-domain two-stage scheduling during global optimization scheduling; based on bitmap decision matrix calculation, weighting calculation is carried out in combination with task matching values and conflict depths, the priority of conflict tasks is dynamically adjusted, conflicts generated in the scheduling process are dynamically eliminated, and the method can be applied to resource scheduling and optimization of low-orbit satellites and ground stations.

The invention belongs to the technical field of aerospace equipment, and discloses an unfolding mechanism and a spacecraft, and the unfolding mechanism is used for winding and unwinding a curling arm and comprises a bearing part, a rotating shaft and a plurality of guide parts. The rotating shaft is rotationally arranged on the bearing piece, one end of the curling arm is fixed to the rotating shaft, and the rotating shaft is used for winding and unwinding the curling arm. The multiple guiding parts are distributed on the bearing piece along the periphery of the rotating shaft and used for providing guiding in the winding and unwinding process of the winding arm. The curling arm is wound through the rotating shaft, and the curling arm can be unfolded or folded by rotating the rotating shaft, so that the solar wing adopting the unfolding mechanism is simple in overall structure, small in size and capable of meeting the space requirement of a small spacecraft. Comprising the unfolding mechanism is small in size and can meet the requirement of miniaturization design.

The invention belongs to the technical field of plate frames for spaceflight, and particularly relates to a roll bending correction method for a quenched sheet n-shaped frame part for spaceflight, which comprises the following steps: S1, quenching in a linear state; s2, quenching deformation is eliminated, and the geometric dimension is corrected; s3, roll bending and roll correction correction and forming correction are carried out; s4, flatly knocking the sunken part and rolling a small radian; and S5, performing pure manual accurate correction, and detecting and correcting the 90-degree angle of each bent angle part to enable the 90-degree angle of each bent angle part to meet the angle tolerance requirement. The problems of low processing efficiency, high cost, high correction difficulty and the like caused by the defects of distortion, warping, verticality inclination and vertical plate arching deformation are effectively eliminated, and meanwhile, the correction efficiency is improved by nearly 10 times.

The invention relates to a full-automatic test system and method compatible with multi-type component irradiation tests, and the system comprises an irradiation main control board, an irradiation test board and an irradiation load board which are disposed in an irradiation room and are connected through a cable, and an electronic load, a programmable power supply, an upper computer and a digital oscilloscope which are disposed in a test preparation room. The system can compatibly support the irradiation test of the total dose effect and the single event effect, is suitable for the rapid assessment demand of multiple types of COTS components on a large scale, and can meet the urgent demand of the commercial spaceflight field for the evaluation of the radiation resistance of the COTS components.

The invention belongs to the field of complex equipment system design and verification, and discloses a model-based complex equipment system design and verification integrated method, which takes four layers of'demand-behavior-structure-parameter 'as a framework, combines task scene demands, and constructs a full-process design and analysis method of a reusable space launch vehicle system. The method comprises the following steps: decomposing a complex system from demand analysis, performing parameter calibration and performance verification on a model by combining theoretical and experimental data, constructing a reusable space launch vehicle system model, and performing comprehensive analysis and verification of the system; in combination with a three-dimensional virtual environment and a configuration optimization algorithm of the model, performing rapid optimization on various configurations of the aerospace vehicle, and evaluating feasibility and performance of a design scheme; through bidirectional interaction of design and verification models and communication of system-level design and professional-level design, the problems of design and verification separation, insufficient model collaboration and the like in the prior art are solved, and the efficiency and precision of design and verification of a complex equipment system are improved.

The invention relates to the technical field of weld joint alignment tolerance detection of special equipment, spaceflight, bridges, ships, wind power and the like, such as containers, pipelines, boilers, recreation facilities, hoisting machinery, passenger ropeways and the like. The invention discloses an automatic weld joint alignment tolerance detection method fusing point cloud and image segmentation, which can quickly and accurately measure the alignment tolerance of a weld joint by combining binocular stereoscopic vision, AI and point cloud analysis technologies, and make up for the defects of the traditional detection method in efficiency and accuracy. The method comprises the following specific steps: shooting through a binocular structured light camera to obtain a grey-scale image and a point cloud image which are aligned; segmenting a welding seam on the grey-scale map, generating a position area mask according to the segmented welding seam, and dividing the actual object into an upper welding seam area, a welding seam area and a lower welding seam area; and according to the segmented welding seam, a welding seam boundary mask is extracted, the position mask and the boundary mask are mapped to a point cloud picture, and regional point cloud data and boundaries are obtained.

The invention discloses a multi-satellite cooperative distributed game control method and device, a computer program and a storage medium, belongs to the technical field of spaceflight, and particularly relates to a satellite attitude control and game control method. The problem that in the prior art, resolving of the overall control quantity depends on a center unit, and constraint processing on the size of the microsatellite control torque is not accurate enough is solved. The method comprises the following steps: S1, according to attitude dynamics modeling and pseudo-linearization processing of the combined spacecraft, obtaining a state dependence coefficient model; s2, obtaining a local optimal control strategy of each satellite in the combined spacecraft through a model prediction control method according to the state dependence coefficient model in combination with a dynamic model in a prediction time domain and flywheel constraint conditions; and S3, obtaining a distributed Nash equilibrium solution through a distributed iteration and global coordination method according to the local optimal control strategy of each satellite in combination with communication topology information. The method is suitable for efficient cooperation tasks of large-scale satellite groups and microsatellite systems.

The invention discloses a complex aerospace product man-machine cooperation assembly-oriented body-equipped agent packaging method and device. The method comprises the following steps: a sensing layer realizes multi-modal intention and environment sensing by using a large language model; the reasoning layer analyzes a structured assembly plan sequence through an assembly scene map; and the execution layer converts the target coordinate into a rotation angle to generate an action code. According to the method, the assembly plan sequence is generated according to the sensing result and is automatically converted into the robot execution code through the combination of the body agent packaging and the large language model, so that the self-adaptive capability of the man-machine cooperative assembly process is improved; therefore, the problems of high system integration difficulty, insufficient task adaptability and high-efficiency cooperation difficulty in man-machine cooperation assembly of complex aerospace products are solved.

The invention belongs to the technical field of aerospace engineering, and discloses a flexible radiator which comprises a radiation assembly, the radiation assembly comprises a plurality of radiation plates which are rotationally connected in sequence, each radiation plate comprises a liquid cooling pipe set and a radiation film arranged on the liquid cooling pipe set, and cooling liquid circulates in the liquid cooling pipe set. The material density is low, the structural mass is effectively reduced, a plurality of radiant panels are rotationally connected in sequence, the radiant panels are in a folded state during emission, then a radiator with enough radiation area can be emitted under the condition that the size of a spacecraft is limited, and the heat dissipation requirement of high-power electronic equipment is met.

The invention relates to a spaceflight-carried Chinese tremella aurantialba strain Zhongyu 8 and application thereof, and belongs to the technical field of strain breeding. The spaceflight-carried Chinese tremella aurantialba strain Zhongyu 8 in the application is preserved in the China General Microbiological Culture Collection Center (CGMCC) on December 8, 2024, the preservation number is CGMCC No.41689, the classification name is Chinese tremella aurantialba, and the preservation address is No.3, Yard 1, Beichen West Road, Chaoyang District, Beijing. Compared with the test of wild Chinese golden fungus sporocarp which is not subjected to space carrying and conventional commercially available Chinese golden fungus sporocarp, the Chinese golden fungus sporocarp cultivated by using the Chinese golden fungus strain Zhongyi No.8 disclosed by the invention has the advantage that the total flavone content of the Chinese golden fungus strain Zhongyi No.8 sporocarp is relatively remarkable.

The invention discloses a method for reducing the inclusion degree of metal particles in additive manufacturing of a spaceflight propulsion chamber. The method comprises the following steps that 1, a printing layer data set is constructed; 2, constructing an initial multi-scale graph structure; 3, outputting an inclusion risk probability graph of the current printing layer based on a multi-scale graph growth generation network; 4, inputting the inclusion risk probability graph into a mimicry hummingbird optimization algorithm to generate a path optimization target space; 5, performing path search by adopting a mimicry hummingbird optimization algorithm, and outputting a final scanning path; 6, controlling a laser to perform printing and scanning operation according to the final scanning path; 7, inputting process feedback data into the multi-scale graph growth generation network, and outputting an updated inclusion risk probability graph of a next printing layer; and 8, the step 4 to the step 7 are executed repeatedly till all the printing layers are printed. According to the method, the multi-scale graph growth generation network and the mimicry hummingbird optimization algorithm are fused, and the metal particle inclusion degree is effectively reduced.

The invention provides a PPO-based spacecraft attitude and orbit integrated game control method and device, and the method comprises the steps: building a spacecraft attitude and orbit integrated model, and carrying out the modeling of the interaction process of a tracking spacecraft and a target spacecraft as a non-cooperative zero-sum game; setting a multi-agent deep reinforcement learning framework, wherein the tracking spacecraft and the target spacecraft are respectively configured with an independent strategy network and an independent value network; training is carried out in a double-agent PPO mode, control instructions of orbit thrust and attitude torque are generated through the strategy network, and the state value is evaluated through the value network; and controlling and guiding the behavior of the spacecraft according to the trained strategy. According to the method, the autonomous decision-making capability and cooperative control performance of the spacecraft in complex tasks are effectively improved, and the method is suitable for high-precision aerospace tasks such as interception of non-cooperative targets, autonomous trajectory planning and attitude control.

The invention belongs to the field of aerospace engineering application, and particularly discloses a satellite resource adaptive allocation method and system based on deep intensity learning. The method comprises the steps that a task planning problem model is constructed, ground targets are decomposed into a plurality of optional observation activities based on the model, each ground target corresponds to an independent sub-task in a visible time window of the ground target, and the sub-tasks are defined as meta-tasks; based on the meta-task set, constructing a Markov decision process model; on the basis of a Markov decision process model, a strategy network model based on Transform is adopted, an Actor-Critic algorithm is combined to iteratively optimize a satellite resource allocation strategy for network model parameters, and then a heuristic algorithm is adopted to determine the specific execution sequence and execution time period of each satellite resource provider task. According to the invention, under the condition of limited satellite resources, efficient cooperation of multiple satellites can be realized so as to complete various observation tasks.

The invention is suitable for the technical field of spaceflight, and provides a remote sensing image aircraft target detection method fusing channel attention, and the method comprises the steps: obtaining a to-be-detected satellite remote sensing image, obtaining the target detection result of each block image, and obtaining the target detection result of the satellite remote sensing image. Through multi-scale feature extraction and feature fusion, image information under different scales can be fully utilized, and the target detection precision is improved. According to the method, a large-scale satellite remote sensing image is segmented into a plurality of small-scale block images for processing by adopting a block processing mode, so that the calculation complexity is reduced, and the detection efficiency is improved. Due to the introduction of the self-attention mechanism, the model can pay more attention to key areas in the image, and the robustness of the model to complex backgrounds and shielding conditions is improved.

The invention relates to a connecting rod configuration separation mechanism for pressing and releasing a stacked satellite assembly, and belongs to the technical field of spaceflight separation mechanisms, the connecting rod configuration separation mechanism comprises a stacking device and pressing separation devices, the stacking device is installed on the corner of each satellite of the stacked satellite assembly, each pressing separation device comprises a pressing mechanism and a rotating mechanism, and the rotating mechanism is installed on the stacking device. The pressing mechanisms are installed on the stacking device of the top satellite, the rotating mechanism is installed on the stacking device of the bottom satellite, the satellites are sequentially stacked through the stacking devices on the corners to form a stacked satellite combination, each pressing mechanism comprises two pressing rods, the pressing mechanisms are connected with the rotating mechanism through the two pressing rods, and the rotating mechanism is connected with the rotating mechanism through the two pressing rods. According to the mechanism, reliable compression connection of a plurality of stacked satellites can be achieved, the action of the mechanism is released from constraint during separation, separation of the stacked satellites is achieved, and the mechanism has the advantages of being simple in structure, large in bearing capacity, small in separation impact, large in separation margin and the like.

The invention discloses a microwave laser hybrid link radio star calibration device and method suitable for deep space exploration, and relates to the field of spaceflight deep space exploration. Pointing calibration of a microwave and laser hybrid link of a deep-space large-aperture antenna is completed through radio star calibration, firstly, after pointing calibration and stable tracking of the microwave link are conducted on the microwave link, fine tracking is conducted on the laser link, pointing calibration of the laser link is completed, respective pointing error correction coefficients are formed, and real-time correction of antenna pointing is achieved. Microwave laser link hybrid radio star calibration is not limited by distance and geographical conditions, and real-time calibration can be realized; the beam of the laser link is narrower than that of the microwave link, the calibration precision is higher, and the system pointing precision and the photoelectric axis consistency precision can be improved. The method is simple in design, high in generalization, low in implementation difficulty and convenient to implement and popularize.

A cabin virtual docking method based on actually measured point cloud data belongs to the technical field of spaceflight docking, and comprises the following steps: acquiring original point cloud data of a cabin structural member; inputting the initial point set into a feature extraction network; the key features comprise decoding features and coding features, the coding features are obtained through the feature processing block, and the decoding features are obtained through the feature recovery block; inputting the extracted key features into a feature segmentation network, segmenting the key features by the feature segmentation network according to categories, and performing parameter fitting on the segmented key features; optimizing matching indexes of the key characteristics after parameter fitting to obtain pose adjustment amounts of the upper cabin section and the lower cabin section so as to realize alignment of butt joint end surfaces and axis superposition of positioning pin holes; and virtual docking between the cabin sections is carried out by using the pose adjustment amount. According to the method, the cabin surface data are directly obtained through measurement, error accumulation is avoided, accurate calculation of the initial relative poses of the two cabins is achieved, and an efficient and reliable solution is provided for high-precision butt joint.

The invention relates to the technical field of spaceflight material forming, in particular to a tension control winding process of a spaceflight carbon fiber composite launch canister, which comprises pretreatment, winding forming, curing and post-treatment. The method comprises the following steps: S1, coating a release agent and a modified coating after processing a core mold, carrying out plasma treatment and eliminating stress; the carbon fiber filaments are soaked in resin containing nanometer components, and are pre-stretched after a hot melting reaction; s2, closed-loop tension control is conducted, winding is conducted according to segmented angles, and modified resin is coated between layers to be overlapped in a crossed mode; s3, stepwise heating and curing, dynamically regulating the pressure and introducing inert gas; and S4, polishing after hydraulic demolding, carrying out sand blasting, carrying out transition layer and ceramic coating, and carrying out multi-dimensional detection. According to the process, the mechanical property and environmental adaptability of the launch canister are improved, the process precision is high, defects are reduced, the forming time is shortened, the rework rate and cost are reduced, the spaceflight requirement is met, and the process is suitable for batch production.

The invention relates to the technical field of spaceflight, in particular to a flat plate type satellite configuration. The flat plate type satellite configuration comprises a first mounting plate, a second mounting plate opposite to the first mounting plate and a frame clamped between the first mounting plate and the second mounting plate, and the first mounting plate and the second mounting plate are arranged on the two opposite sides of the frame; the frame comprises a plurality of edge beams connected end to end and a plurality of middle beams detachably fixed to the inner sides of the edge beams, and the interior of the frame is divided into a plurality of containing spaces used for containing satellite single machines through the middle beams. According to the flat plate type satellite configuration, the frame is clamped between the first mounting plate and the second mounting plate, the bearing capacity can be improved, the manufacturing difficulty and cost are reduced through detachable connection of the middle beams and the edge beams, and protection can be provided for the satellite single machine through the containing space.

The invention discloses a model library-based spaceflight radio frequency signal quality multi-domain evaluation and compensation method, and belongs to the technical field of wireless communication. The implementation method comprises the steps of determining signal system parameters based on various CCSDS standards and a spaceflight protocol system, extracting related parameters of spaceflight standards in a time-frequency domain, generating standard time-frequency domain radio frequency signals, converting the standard time-frequency domain radio frequency signals into a related domain, a modulation domain, an energy domain and a polarization domain, and establishing spaceflight radio frequency signal sub-model libraries of the domains; obtaining a time-frequency domain measured signal through a receiver, integrating time domain information and frequency domain information, and constructing a time-frequency domain sub-evaluation model; constructing a multi-domain comprehensive evaluation model by adopting a parallel data transmission mode and a weight data processing method; calculating the weight of the evaluation result of each domain through an entropy weight method, and obtaining a comprehensive quality evaluation result of the spacecraft radio frequency signal; and based on the distortion coefficient, a robust signal equalization algorithm is adopted to process the signal, the influence of the distortion effect on the signal quality is compensated, and the robustness and the anti-interference capability of signal transmission are improved.

The invention discloses a carrier rocket flight load analysis method based on flight measurement data, and relates to the technical field of spaceflight, and the method comprises the steps: measuring a flight load in a rocket flight process, and obtaining actual flight strain data and actual flight trajectory data; according to the actual flight strain data and a pre-constructed load-strain corresponding relation, calculating a rocket body total load of each station on the rocket body; calculating the rocket body static load of each station in the actual flight process by using the actual flight trajectory data; subtracting the corresponding static load of the rocket body from the total load of the rocket body at each station to obtain the dynamic load of the rocket body at each station; and optimizing the flight load dynamic load theoretical calculation method by using the rocket body static load of each station and the rocket body dynamic load of each station to obtain an optimized flight load calculation method. The rocket body structure load in the actual flight process can be obtained through load measurement in the flight process, and therefore the static load of actual flight and the dynamic load of actual flight are obtained in a back-stepping mode.

The invention relates to the field of artificial intelligence, in particular to a rocket trajectory optimization and real-time adjustment system based on artificial intelligence, which comprises a trajectory prediction module, a real-time adjustment control module and an intelligent monitoring module, and is characterized in that a jumping mechanism is introduced into the trajectory prediction module, so that interference of an intermediate state is effectively reduced, and key time steps are directly concerned; a forward diffusion and inverse process denoising mechanism is introduced, so that the sensitivity of the model to noise is effectively reduced; in the real-time adjustment control module, the attitude and thrust of the rocket are automatically adjusted based on model predictive control, the solving process is more efficient, the calculation complexity is reduced, the decision-making speed is increased by optimizing a target function to minimize state deviation and adopting a constrained quadratic programming problem, the trajectory optimization and real-time adjustment capability of the rocket is remarkably improved, and the real-time adjustment of the rocket is realized. And powerful support is provided for realizing complex aerospace tasks.

The invention relates to a spaceflight-carried schizophragma integrifolium strain Kungsu No.3 and application thereof, and belongs to the technical field of strain breeding. The spaceflight-carried schizophyllum commune strain No.3 is preserved in the China General Microbiological Culture Collection Center (CGMCC) on August 9, 2024, the preservation number is CGMCC No.41428, the classification name of the spaceflight-carried schizophyllum commune strain is schizophyllum commune, and the preservation address is No.3, Yard 1, Beichen West Road, Chaoyang District, Beijing. Compared with cultivation of strains which are not subjected to spaceflight carrying, the Kunzhou No.3 strain is fast in hypha germination, fast in growth, crisp in sporocarp, free of or few in spores, light pink to pink, high in conversion rate, short in period and suitable for industrial cultivation.

The invention discloses a double-pulse engine shell winding process preparation method, and belongs to the technical field of spaceflight. Comprising the following steps that S1, a mold pressing end socket and a combined core mold are installed; s2, paving a heat insulation layer, and prevulcanizing the heat insulation layer; s3, a winding program is set, and carbon fiber winding is carried out; s4, curing is conducted; s5, mounting an external hanging piece; s6, winding and fixing an external hanging piece; s7, slitting and machining; s8, mounting an interlayer fixing seat; and S9, integral machining is conducted. The manufacturing method is applied to manufacturing of the double-pulse engine shell and has the advantages of being short in production and manufacturing period, low in cost and good in product quality consistency.

The invention belongs to the technical field of spaceflight measurement and control and artificial intelligence, and particularly relates to a high-precision low-orbit satellite forecasting method and system, and the method comprises the steps: obtaining the observation data of a low-orbit satellite, and the parameter data of the earth center gravitational force and non-spherical gravitational force perturbation; the method comprises the following steps: decomposing observation data of a low-orbit satellite into long-term trend data, medium-term fluctuation data and short-term change data; constructing a long-term dynamic model, and fitting the long-term trend data and the long-term dynamic model to obtain a long-term fitting result; constructing a medium-term dynamic model, and fitting the medium-term fluctuation data and the long-term dynamic model to obtain a medium-term fitting result; constructing a short-term dynamic model, and fitting the short-term change data with the short-term dynamic model to obtain a short-term fitting result; fusing the fitting results to obtain a satellite orbit state fitting result; and updating parameters of all the dynamic models, and calculating orbit forecast information of the low-orbit satellite. And the orbit forecasting precision of the low-orbit satellite is effectively improved.

Spacecraft servicing systems include a spacecraft servicing device and at least one mission extension pod comprising at least one spacecraft servicing component. The spacecraft servicing device is configured to transfer the at least pod to a target spacecraft in order to service the target spacecraft with the at least one spacecraft servicing component of the at least one pod. Spacecraft servicing pods configured to be supplied to a spacecraft with a spacecraft servicing device include at least one spacecraft servicing component.

A method for measuring displacement thickness and momentum loss thickness of a highly compressible turbulent boundary layer belongs to the technical field of spaceflight tests, and comprises the following steps: acquiring boundary layer velocity field distribution for a boundary layer flow field at a specific position of a flat plate model in a hypersonic wind tunnel capable of continuously operating; wall surface temperature distribution after model heat balance is obtained according to the specific position of the flat plate model; boundary layer velocity field distribution and wall surface temperature distribution of a specific flow direction station are utilized, temperature distribution and density distribution of flow in a boundary layer in the normal direction are obtained by introducing related hypotheses, and then the displacement thickness and the momentum loss thickness are calculated according to the temperature distribution and the density distribution. The problem of obtaining the displacement thickness and the momentum loss thickness of the boundary layer in the wind tunnel environment from the test angle is solved.

The invention discloses a ground station intelligent equipment management and control system and method for spaceflight measurement and control, and the system comprises a data collection and display module, an intelligent scheduling module, a task execution module, a receiving and forwarding module and the like. Providing a measurement and control plan conflict resolution scheme; satellite macro parameters are configured and automatically issued; receiving, storing, cleaning and forwarding telemetering and remote control data in real time, and generating and pushing a measurement and control task operation report; all the modules cooperate with each other to automatically execute a measurement and control task. Through conflict detection and automatic resolution of the intelligent scheduling module, macro parameter automatic configuration / issuing / unloading of the task execution module and data autonomous processing of the receiving and forwarding module, full-automatic execution of the measurement and control task is realized, the task execution efficiency is improved, manual operation errors are avoided, and the spaceflight measurement and control task efficiency is remarkably improved.

The invention discloses a multi-dimensional authority management method and system of a spaceflight document management system. The multi-dimensional authority management method of the spaceflight document management system comprises the following steps: confirming a front-end user interface; confirming a database layer; confirming a back-end service layer; constructing a permission model in the back-end service layer; determining a multi-dimensional permission division strategy in the back-end service layer; establishing an authority dynamic adjustment mechanism in the back-end service layer; and establishing an authority auditing and monitoring mechanism in the back-end service layer. According to the invention, fine permission division can be carried out according to the dimensions of positions, positions, specialties, model positions and the like of the users. And the authority can be automatically or manually adjusted, so that the timeliness and the accuracy of the authority are ensured. And a perfect authority auditing and monitoring mechanism is established, the authority use condition of the user is recorded and inquired in real time, and the safety and compliance of the system are improved.