202 results about "Orbital control" patented technology

The embodiment of the invention provides a simulation evaluation method and device for a multi-satellite cooperative task, and the method comprises the steps: building a unified time-space reference based on a standard time signal, and building a complete environment disturbance model comprising sunlight pressure, atmospheric resistance and geomagnetic field interference. A fault injection mechanism of load, attitude and orbit control is innovatively designed, and real simulation of multi-satellite cooperative motion is realized. According to the system, a system-level, subsystem-level and component-level multi-level evaluation index system is established, a dynamic weight calculation method based on a task execution state is adopted, and matching analysis of a three-dimensional error curve and a key event time sequence is combined, so that accurate evaluation of multi-satellite cooperative task performance is realized; and a reliable decision basis is provided for space task planning and system optimization.

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

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

The invention provides a constellation phase keeping method and device and electronic equipment, and the method comprises the steps: obtaining the mean root semi-major axis of each satellite in a target constellation in a target epoch, and selecting a satellite with the maximum mean root semi-major axis as a reference satellite; and constellation phase keeping is carried out based on the reference satellite. According to the scheme, only a relatively small period difference needs to be adjusted, the overall orbit adjustment amplitude and frequency can be reduced, and then fuel consumption and the complexity of orbit control operation are reduced; the influence of atmospheric resistance on the reference satellite is relatively small, so that the condition that other satellites frequently perform orbit control due to frequent change of the reference satellite orbit can be reduced; constellation configuration confusion caused by instability of the reference satellite itself is reduced in the face of various perturbation force and environment changes; the operation period of the reference satellite is long, the orbit is relatively stable, and too complex orbit change conditions do not need to be considered when an orbit control strategy is formulated, so that an orbit control algorithm and operation are easier to implement.

The invention relates to the technical field of satellite orbit control, in particular to an earth-moon L2 point Halo orbit satellite semi-analysis attitude adjustment unloading method and device, and aims to improve the calculation efficiency and accuracy of the active unloading attitude of a satellite. Comprising the following steps: determining an initial speed increment required by orbit maintenance based on basic information of a satellite running in a current orbit, and determining an expected speed increment of orbit maintenance in a current orbit maintenance direction based on the initial speed increment; under the reference coordinate system, the attitude adjustment unloading residual speed increment is expressed through the azimuth angle and the pitch angle; under the reference coordinate system, taking the attitude adjustment unloading residual speed increment as an optimization target, optimizing the azimuth angle and the pitch angle, and determining a reference attitude adjustment unloading attitude according to the azimuth angle and the pitch angle obtained through optimization; and acquiring an actual orbit maintaining speed increment in a direction corresponding to the reference attitude adjustment unloading attitude, correcting the reference attitude adjustment unloading attitude according to the actual orbit maintaining speed increment, and determining a target unloading attitude of the satellite.

The invention discloses a multifunctional electric propulsion system of a spacecraft, and relates to the technical field of space propulsion systems. The multifunctional electric propulsion system comprises a gas cylinder module, a fluid management module and a thruster module. The downstream of the gas cylinder module is connected with the fluid management module; the downstream of the fluid management module is connected with the thruster module; the thruster module comprises a Hall thruster, an electric heating type thruster and a cold air thruster. The low-cost working medium gas is utilized, the attitude control system and the orbit control system of the satellite are integrated through modular design and heat flow design, the design and manufacturing difficulty of the satellite is lowered, the launching cost of the satellite is reduced, and meanwhile the integrated control system is combined with an orbit control algorithm, so that intelligent control over the satellite can be achieved.

The present disclosure relates to a method of generating auxiliary data for controlling a satellite travelling in orbit around Earth, the method comprising: receiving tracking data for the satellite; applying an orbit determination algorithm including: estimating an orbit for the satellite based on the tracking data; and predicting, based on the estimated orbit, future ephemerides data of the satellite; generating auxiliary data comprising predicted future ephemerides data; and transmitting the auxiliary data to the satellite for use in the satellite's attitude and orbit control.

The invention relates to a manned spacecraft on-orbit health state evaluation method, which comprises the steps of manned spacecraft on-orbit state evaluation: evaluating the on-orbit state of manned spacecraft key equipment according to telemetry parameter evolution characteristics representing manned spacecraft function indexes; evaluating the technical capability of the manned spacecraft: before the manned spacecraft executes a key on-orbit task, evaluating whether a cabin sealing function, an attitude control function, an orbit control function, a docking function, and a mechanical arm and a pressure relief and recompression device related to execution of the key task are normal or not; carrying out task evaluation on the manned spacecraft: carrying out task execution condition evaluation on a key on-orbit task during the on-orbit operation period of the manned spacecraft; reliability and safety evaluation: evaluating the on-orbit safety, reliability, maintainability and life condition of the manned spacecraft, and identifying internal and external risks possibly existing in the long-term on-orbit operation period; and guarantee condition evaluation: evaluating whether the ground flight control team guarantee condition meets the flight control task requirement or not.

The invention discloses an intelligent magneto-rheological track for robot-assisted machining and application thereof, and the intelligent magneto-rheological track comprises a magneto-rheological unit module which is made of a magneto-rheological material, the magneto-rheological material is packaged in a flexible film, and a coil unit for generating a magnetic field is wound outside the flexible film; and the track control system can control the magnetic field size and the magnetic field distribution of each position of the magnetorheological unit module according to the corresponding relation of the appearance, the shape and the magnetic field of the magnetorheological unit module, and the magnetorheological unit module is adjusted to have the required appearance and the required shape. The magnetic field of the magneto-rheological unit module is regulated and controlled, so that the magneto-rheological unit module can have the rigidity required by operation and operation of the robot, and the magneto-rheological unit module can be regulated to be in the set shape and shape, so that the magneto-rheological unit module can adapt to working faces of various different shapes and different robots; and the robot can be used for machining in large-curvature areas such as aircraft surface skins and narrow space scenes such as air inlet channels.

The invention discloses an orbit control safety shutdown time calculation method suitable for deep space exploration, and belongs to the field of deep space exploration. The method comprises the steps that firstly, the theoretical speed increment of orbit control is calculated, and a sinking engine, an orbit control engine, an attitude control engine and related engine thrust and specific impulse parameters are determined; secondly, the actual orbit control speed increment is obtained, and the orbit control nominal starting time length is determined; thirdly, calculating time error deviation, and giving out engine shutdown forbidding time and forced shutdown time in the orbit control process; if the task is a conventional orbit control task, taking the two times as final safe shutdown time; for the orbit control task related to safety, multiple groups of shutdown forbidding time and forced shutdown time under the nominal working condition and the pulling deviation working condition are given, and finally the safety shutdown time of the orbit control task related to safety is determined. According to the method, the track safety and task safety of the detector are ensured by selecting proper shutdown forbidding time and forced shutdown time.

The invention discloses a camera imaging control method and device for midnight sunlight avoidance, and belongs to the field of spacecraft attitude orbit control. The method comprises the steps of judging whether a satellite is currently in a midnight sunlight avoidance stage; when the satellite is not in the midnight sunlight avoidance stage, if the midnight sunlight avoidance condition is met, initializing to enter the midnight sunlight avoidance stage, and setting the satellite to quickly maneuver to a preset target avoidance trajectory; when the satellite is in the midnight sunlight avoidance stage, if the satellite receives an imaging instruction meeting the requirement, the satellite is maneuvered to an imaging point for imaging, and otherwise, the satellite is maintained to run on a target avoidance track; and when the satellite is in the imaging state of the midnight sunshine avoidance stage, if the satellite is in a sunshine receiving state, quickly maneuvering the satellite to the target avoidance track, otherwise, maintaining the imaging state of the satellite. According to the invention, the imaging safety of the camera during the midnight avoidance period can be realized, and the use efficiency of the camera load and the user experience are improved.

The invention provides an orbit game system and method combining reinforcement learning and optimal control, and the system comprises an initialization problem setting module, an optimization solving module, a reinforcement learning module, a virtual environment module and a loop execution module. And solving a spacecraft orbit control quantity based on a CW equation by using an optimization solving module, and generating a final control strategy in combination with a TD3 algorithm in the reinforcement learning module. The system provided by the invention considers J2 perturbation influence in a virtual environment, continuously iterates and optimizes a control strategy, realizes an efficient and reliable orbit pursuit game under incomplete information and nonlinear disturbance, and is suitable for a multi-spacecraft autonomous decision-making task in a complex space environment.

The invention discloses a satellite orbit control method based on a continuous time near-end strategy optimization reinforcement learning algorithm, and the method comprises the following steps: 1, determining an action, namely acceleration, taken by a satellite, and the execution time of the action based on the continuous time near-end strategy optimization reinforcement learning algorithm; and step 2, realizing satellite orbit control based on the action taken by the satellite and the execution time obtained in the step 1. The advanced near-end strategy optimization reinforcement learning algorithm (PPO) and the continuous time control framework are combined, a high-precision, stable and energy-efficiency-optimized satellite orbit control solution is provided, remarkable technical advancement and wide application prospects are achieved, and powerful technical support is provided for future space exploration and satellite operation.

The invention discloses a high-orbit remote autonomous rendezvous orbital transfer method and system based on sequential quadratic programming, and the method comprises the steps: setting initial parameters; establishing an aircraft precise dynamic model; determining an orbital transfer strategy; constructing a nonlinear programming model according to the orbital transfer strategy; according to the nonlinear programming model and the initial parameters, adopting a sequential quadratic programming method to obtain orbital transfer parameter initial values; and according to the orbital transfer parameter initial value, adopting a Newton iteration method to obtain an orbital control parameter which accurately meets a terminal condition under a perturbation condition. According to the method, the calculation amount in the orbit control parameter solving process is greatly reduced while the model precision is guaranteed.

The invention discloses a satellite autonomous orbit phase networking and maintaining method. Relates to the technical field of spacecraft orbit control, in particular to the technical field of satellite autonomous orbit phase networking and maintenance. The technical problems of constellation configuration autonomy and precision improvement in the spacecraft orbit control field are effectively solved. The method comprises the following steps: 1, autonomously calculating a phase deviation sequence of a satellite passing through an ascending node through a time sequence of the satellite passing through the ascending node; 2, recording the current phase deviation once after the satellite passes through the ascending node every time, and calculating an orbit deviation parameter by adopting a least square estimation method; 3, performing a unilateral limit cycle control strategy on the satellite; 4, calculating through an orbit control strategy to obtain orbit control time; 5, splitting the orbit control demand into a plurality of orbit control tasks, and planning the execution time of the orbit control tasks according to the uploaded load business; and 6, automatically returning to the step S1 after the execution of the orbit control tasks is completed.

The invention is applied to the field of satellite constellation design, and particularly discloses a regional remote sensing satellite constellation optimization method based on an improved crayfish algorithm, which comprises the following steps: S1, selecting an orbit observed in a specific region, the orbit needing to meet the average revisit time and the task requirement; the number of satellites meets the task requirement, the orbit height meets the task requirement, and the remote sensing constellation design objective function is S2: mathematical optimization model, and the orbit control parameters of the satellite constellation can be determined according to the six elements of the satellite orbit. According to the regional remote sensing satellite constellation optimization method based on the improved crayfish algorithm, a population initialization improvement strategy and a refraction reverse learning strategy are set, the convergence speed and optimization precision of the algorithm are improved, initial initialization classification is performed on a population through the population initialization improvement strategy, solution individuals are uniformly distributed, and the optimization efficiency is improved. The subsequent initial optimization efficiency of the population is improved, a reverse learning strategy is refracted, the search range of the algorithm is expanded, and the accuracy of the method is improved.

The invention discloses a satellite constellation autonomous deployment method and system, belongs to the technical field of aerospace orbit control, and solves the problems of long deployment period, high personnel investment, slow collision avoidance response, increased orbit safety risk and the like caused by a traditional satellite deployment method. The method comprises the following steps: constructing a constellation network according to initial orbit parameters of a satellite and orbit injection time and orbit parameters of different stages; outputting an optimal deployment strategy of each stage of the constellation through a genetic algorithm; the right ascension of the ascending node and the phase are adjusted to a target position together while the height is deployed in place through a coupling equation, and ignition constraints are constructed; generating an orbital transfer plan according to the thrust and a satellite initial orbit needing to be deployed; an orbital transfer instruction is automatically generated according to the orbital transfer plan; according to on-orbit telemetering, the orbital transfer progress condition is judged, and strategy closed-loop adjustment is carried out; cooperative deployment of multi-orbit-plane satellites is achieved, and fuel and time cost are saved. The method is particularly suitable for multi-orbit-plane collaborative deployment and autonomous management of large-scale satellite constellations.

The invention provides a spacecraft in-orbit attitude control and structural dynamics coupling simulation method and system. The method comprises the following steps: establishing a spacecraft simplified three-dimensional model; defining an analysis step, a moment and a concentrated force, researching an attitude control and flexible structure vibration suppression equation and compiling the equation into a UAMP subprogram, and simulating an attitude control moment and a flexible structure vibration suppression acting force; and finally, evaluating whether the attitude angle precision of the spacecraft and the vibration suppression effect of the flexible structure reach expectations or not. According to the method, the influence of the motion and deformation of each flexible part on the attitude and mass center displacement of the central rigid body during the on-orbit attitude control of the spacecraft is considered, the structural dynamics characteristics of the large-flexibility spacecraft under the on-orbit attitude control condition are disclosed, and a new technical approach is provided for evaluating the structural mechanical property, reliability and pointing precision of the spacecraft.

The present invention discloses a fuel-optimal active drift three-dimensional imaging orbit control method, including: obtaining a drift calculation formula based on the satellite orbit sub-satellite point trajectory coincidence principle and the relationship between the satellite orbit operation period and the semi-major axis; obtaining initial active drift based on the satellite semi-major axis and orbit period principle and the drift calculation formula; obtaining precise active drift control with maximum control pulse interval based on initial active drift control, high-precision absolute orbit prediction method and Newton iteration method; constructing an orbit transfer control fuel consumption model, and realizing fuel optimal control based on precise active drift control and orbit transfer control fuel consumption models. The present invention meets the different task requirements of global complex terrain elevation measurement and three-dimensional imaging, and takes into account the goals of optimal fuel consumption and transfer time.

The application discloses a marine intelligent vertical transportation system and method, and belongs to the technical field of marine transportation. The rear end of the carrying platform is provided with a lifting platform, the bottom end of the lifting platform is provided with two supports for increasing supporting force, the rear end of the lifting platform and the two supports are movably connected with two lifting tracks, a control room is arranged on one side of the carrying platform, two scanning rods are arranged at the entrance of the front end of the carrying platform, and a weighing table and a push plate are arranged in the carrying platform. The application solves the problems of low efficiency, long response time, high safety risk and inability to realize intelligent management, and the overall transportation equipment and the control system are easy to integrate with other intelligent systems of the ship, thereby enhancing the convenience and real-time performance of management, realizing intelligent automatic identification and vertical transportation, improving transportation efficiency, and reducing human operation errors and delays while obtaining basic information of goods, thereby improving the safety of goods transportation.

The invention relates to a reflector satellite (1) comprising at least one curved reflecting surface (11), characterized in that it comprises at least one support structure (10) connected to at least four positioning and orientation systems (12) of the reflector satellite for achieving attitude and orbit control, said positioning and orientation systems comprising at least one propulsion system, said positioning and orientation systems being synchronized and arranged so as to allow orientation of the reflector satellite along at least two axes of rotation. A satellite assembly comprising a source satellite and a reflector satellite is also described. Abstract figure: Figure 1

This invention relates to the field of spacecraft orbit control technology, and particularly to a spacecraft approach control method based on the fusion of imitation learning and reinforcement learning. The method includes: S1: generating initial and target states, solving for the optimal fuel transfer trajectory offline using a direct method, and constructing an expert dataset; S2: based on the expert dataset, training a neural network controller through imitation learning to obtain a pre-trained model; S3: loading the weights of the pre-trained model, constructing a composite reward function, and training the policy network using a near-end policy optimization algorithm to obtain an optimized policy network model; S4: acquiring relative state data, optimizing the policy network model, and outputting the control quantity for the optimal fuel consumption trajectory transfer in real time. This invention rapidly masters an approximately optimal policy through imitation learning and surpasses the performance of expert data through reinforcement learning, completing control command solutions in milliseconds. It balances terminal control accuracy and fuel consumption optimization, offering advantages such as high solution efficiency, excellent control accuracy, and strong generalization ability.

The present invention discloses a management method for the working mode of chemical propulsion orbit control. Step 1: According to the orbit control data packet, enter the orbit control attitude adjustment mode at the attitude adjustment start time. Step 2: After entering the orbit control attitude adjustment mode, judge whether the attitude adjustment process is normal. If it is normal, continue the attitude adjustment process until the jet start time is reached; if it is abnormal, exit the orbit control and output the reason for exiting the orbit control. Step 3: According to the orbit control data packet, enter the orbit control jet mode at the jet start time. Step 4: After entering the orbit control jet mode, judge whether the jet process is normal. If it is normal, continue the jet process until the jet end time is reached, end the orbit control, and output the reason for exiting the orbit control as: normal end; if it is abnormal, exit the orbit control and output the reason for exiting the orbit control. The chemical propulsion orbit control is divided into two working modes: the orbit control attitude adjustment mode and the orbit control jet mode, which is convenient for clearly tracking the orbit control stage.

The application discloses a method and device for orbit transfer control of a lunar spacecraft, and realizes orbit transfer of the spacecraft into a full-parameter target orbit. The method comprises the following steps: a three-impulse control strategy of a far-lunar maneuver, phase control and period control is designed; based on an orbit plane, an arch line and a perigee height, control time and omnidirectional control impulses for orbit transfer from an initial orbit to a first intermediate orbit are determined; based on an orbit phase, a first tangential impulse for orbit transfer from the first intermediate orbit to a second intermediate orbit is determined; and based on an orbit period, a second tangential impulse for orbit transfer from the second intermediate orbit to the target orbit is determined. The first tangential impulse and the second tangential impulse are taken as variables, and a far-lunar maneuver position vector deviation is taken as a fitness value, and a genetic optimization algorithm is used to solve initial values of the impulses. The method solves the problem of orbit control solution caused by nonlinear enhancement of orbit evolution under perturbation influence and complexity of omnidirectional impulse control parameters.

A method for optimizing spacecraft pulse maneuvers considering collision avoidance. The present invention relates to a method for optimizing spacecraft pulse maneuvers considering collision avoidance. The present invention belongs to the field of satellite orbit control. The purpose of the present invention is to solve the problem that the existing method for solving the optimal collision avoidance pulse time for spacecraft fuel is relatively long. The process is as follows: Step 1, based on the reachable domain envelope model, construct an optimization model for a single pulse collision avoidance problem with a fixed pulse time; Step 2, based on the optimization model of Step 1, use the Newton iteration method to solve the minimum pulse of the spacecraft at a given collision avoidance moment; Step 3, perform a one-dimensional search on the collision avoidance moment in Step 2 to obtain the optimal collision avoidance time, and obtain the minimum pulse with free collision avoidance time based on the optimal collision avoidance time.

The present application relates to a kind of satellite load observation attitude control and data transmission, orbit control autonomous intelligent planning system and method, the system includes mission guide module, attitude control module, orbit control module and data transmission module;The attitude control module includes several thrusters for satellite attitude control, the orbit control module is used for satellite autonomous orbit control calculation, and carries out satellite orbit control, the data transmission module is used for satellite autonomous data transmission calculation, and satellite data is transmitted to ground;The mission guide module is in system control core, executes load observation task implementation strategy, according to priority reasonably arrange satellite's working time sequence, so that the satellite is intelligently switched between attitude control and data transmission to ground, orbit control, controls satellite autonomous intelligent operation in orbit.Autonomous intelligent planning, autonomous data transmission calculation, autonomous orbit control calculation are beneficial.

The application discloses a kind of distributed multi-curved surface array full airspace beam continuous control methods, comprising: setting satellite TT&C relay trigger event, trigger according to including satellite and TT&C station uplink and downlink state monitoring, orbit control instruction and pre-configured trigger instruction of switching condition;With satellite TT&C relay as the control core of random access node, utilize curved surface array tracking receiver state parameters and the partial satellite orbit information cached, based on TT&C relay trigger event, adaptively trigger curved surface array inter-beam switching process, ensure the continuous tracking of curved surface array to satellite.The present application can realize low-latency and low TT&C resource overhead distributed multi-curved surface array full airspace beam continuous control, support the low-latency TT&C relay demand of satellite in future large-scale constellation, realize on-demand switching without pre-planning, real-time capacity optimization, improve the adaptability to station network resources and the dynamic change of satellite motion state.

The invention relates to the technical field of satellite attitude and orbit control, in particular to a non-inductive coordination control method for quick zero passage of a momentum wheel under a redundant momentum wheel train. The method comprises the following steps: firstly, interpreting the change trend of the rotating speed of the momentum wheel according to the change condition of the rotating speed of the momentum wheel; secondly, judging the zero-crossing state of the momentum wheel according to the rotating speed change trend and the actually measured rotating speed of the momentum wheel; and finally, based on the characteristic of zero motion of the momentum wheel set, applying zero-crossing compensation torque to the momentum wheel in a zero-crossing state to enable the momentum wheel to quickly pass through a rotating speed zero-crossing interval, and applying reverse compensation torque to other momentum wheels to enable the resultant torque of the compensation torque of the momentum wheel set to be zero. The rotating speed of the momentum wheel quickly passes through a zero-crossing interval through a method of increasing zero-crossing compensation torque, and the influence of zero-crossing of the rotating speed of the momentum wheel on the satellite attitude control precision is reduced. The method can be popularized and applied to all satellites with zero-crossing momentum wheel rotating speed and high attitude control precision requirements.

This invention discloses a high-precision periodic orbit maintenance method based on maintenance point rolling optimization, relating to the field of spacecraft orbit control and orbit maintenance technology. Based on a high-precision ephemeris dynamics model, it constructs a maintenance point rolling prediction mechanism, a navigation and execution error model, and a least-squares orbit correction strategy under multi-path point constraints. This application uses the above method to achieve high-precision, low-energy-consumption, and highly robust long-term maintenance of a spacecraft's periodic orbit in a realistic multi-body perturbation environment.

The invention relates to a multi-spacecraft orbit cooperative control strategy for non-cooperative target rendezvous. The multi-spacecraft orbit cooperative control strategy comprises the following steps: step 1, establishing a relative motion equation to describe motion of spacecrafts and non-cooperative targets; 2, establishing a spacecraft orbit control model; 3, solving a spacecraft orbit control strategy; step 4, calculating a state weight matrix of two pursuing parties; and step 5, designing a task allocation scheme of pursuit and escape parties. According to the multi-spacecraft orbit cooperative control strategy for non-cooperative target rendezvous, the state quantities of pursuing and escaping parties are converted into a weight matrix based on an analytic hierarchy process, the matching problem between trackers and escapers is solved by adopting a KM algorithm, and task redistribution is performed on the remaining trackers on the basis to make up for the deficiency of primary distribution.