8 results about "Orbit+Face" patented technology

The application relates to a rotation error correction method of a distributed autonomous navigation constellation, and comprises the following steps: S1, each satellite calculates the orbit plane orientation error of the satellite in orbit and distributes the result to all visible satellites in the constellation in real time; S2, each satellite fits a local constellation rotation quantity according to the orbit plane orientation error of the satellite and the collected orbit plane orientation error; S3, each satellite determines a virtual satellite orbit observation quantity according to the local constellation rotation quantity of the satellite; S4, each satellite constructs a conditional constraint equation of virtual observation according to the virtual satellite orbit observation quantity and the second type of non-singularity orbit root number; and S5, each satellite solves the satellite orbit through filtering according to the conditional constraint equation of virtual observation, so that the overall rotation effect of the constellation is inhibited and corrected. The application can inhibit the rotation effect of the constellation, improve the distributed autonomous orbit determination precision of the satellite, does not increase the inter-satellite data interaction communication pressure, and can stably maintain the constellation configuration for a long time.

The application discloses a method for calibrating a roll angle of an emergency anti-solar time of a satellite on the earth, which is beneficial to reestablishing a three-axis attitude of the satellite on the earth. Firstly, an angle between a projection of a sun vector on an orbit plane and an orbit system-X axis is calculated; then, whether a current orbit position meets a requirement is determined according to the angle between the projection of the sun vector on the orbit plane and the orbit system-X axis, and whether an absolute attitude reference is available at present is determined, if the current orbit position meets the requirement and the absolute attitude reference is available at present, the roll angle is calibrated at a current control beat; otherwise, the roll angle is not calibrated at the current control beat; if the roll angle is calibrated at the current control beat, the roll angle is calculated based on the absolute attitude reference; if the roll angle is not calibrated at the current control beat, the roll angle is calculated by using gyro inertia angular velocity integration. The application can provide high-precision and reliable attitude information for reestablishing the attitude of the satellite on the earth.

This invention discloses a method for initial orbit determination of a non-cooperative target under space-based angle-only extremely short arc observation, belonging to the technical field of initial orbit determination. This invention addresses the failure of existing initial orbit determination methods under extremely short arc conditions. The method includes: using the unit normal vector of the target orbital plane as the variable to be optimized; obtaining the relationship between the slant distance and the unit normal vector based on the geometric relationship between the target position vector, the slant distance between the space-based platform and the target position, the target azimuth unit vector, and the space-based platform position vector; transforming the solution of the unit normal vector into the solution of the X-axis and Y-axis components of the unit normal vector based on the normalization characteristics of the unit normal vector, and determining the constraints of the solution; and employing a heuristic algorithm to solve for the X-axis and Y-axis components of the unit normal vector, thereby determining the unit normal vector and achieving initial orbit determination. This invention improves the accuracy and robustness of initial orbit determination.

This invention discloses a large-scale space target collision early warning combination screening method, belonging to the field of space situational awareness. The implementation method is as follows: Preliminary screening of similar targets is performed based on the distance between intersection points on the orbital plane intersection line to quickly reduce the number of satellite combinations to be analyzed; by decomposing the analytical solution considering the minimum relative distance between satellites under J2 perturbation, it is divided into long-term terms and exact solutions; based on the evolution characteristics of the long-term terms, a second screening is performed using the trend characteristics of the long-term terms; a third screening is performed using the analytical exact solution considering the relative distance between satellites under J2 perturbation; based on the results of the third screening, satellite combinations with collision risk are determined, realizing large-scale space target collision early warning combination screening, thereby protecting the safety of space assets. This invention fully considers the long-term evolution characteristics of orbits under perturbation, significantly reducing the calculation time for early warning, and is suitable for rapid screening of long-term collision early warnings for large-scale space targets.

This invention discloses a multi-satellite collaborative computing and task scheduling method and system applicable to constellation-scale evolution. The method includes: acquiring heterogeneous state data of each satellite based on the orbital plane state view of the current time slot, performing unified feature encoding to obtain the feature representation of each satellite, and aggregating them into a global state feature at the orbital plane level; segmenting and encoding each task to be decomposed according to the global state feature to obtain an action vector including the number of sub-task decompositions, the task decomposition scheme, and the satellite allocation scheme for each task to be decomposed; calculating the task completion rate of each priority group based on the action vector and task priority to determine the system-level reward value; updating the state of each satellite according to the computing resources used by each task to be decomposed in the current time slot to generate the orbital plane state view of the next time slot, and then returning to the step of acquiring heterogeneous state data, until all time slots are iterated, and obtaining a task scheduling scheme based on the action vector corresponding to each task to be decomposed in each time slot.

The application discloses a method for constructing a cross-orbit chain topology of a mega-constellation network, and the method comprises the following steps: S1, acquiring the number of uniformly distributed orbit planes in the mega-constellation network P and the number of uniformly distributed satellites in each orbit plane S ; S2, each satellite on each orbit plane establishes an inter-orbit satellite interlink with the satellites adjacent to the orbit plane, meanwhile, each satellite on each orbit plane establishes an inter-orbit satellite interlink with the corresponding satellite on the corresponding orbit plane by selecting at least two cross numbers to form a cross-orbit chain topology of the mega-constellation network, and the greatest common divisor of all cross numbers is 1. The cross-orbit chain topology of the application makes the inter-orbit satellite interlink span the satellites of several orbit planes, under the premise of ensuring global connectivity, significantly improves the long-distance transmission efficiency, breaks through the scale bottleneck of a single-layer constellation, reduces the dependence on the ground gateway station, and makes the mega-constellation network become a high-performance infrastructure complementary to the ground network.

This invention provides a polar-orbiting satellite navigation constellation system, a navigation method, and a user terminal. The polar-orbiting satellite navigation constellation system includes: four orbital planes, each with its intersection point with the equator evenly distributed along the equator, with a longitude interval of 45 degrees between adjacent orbital planes; nine satellites evenly distributed on each orbital plane, with a phase interval of 40 degrees between adjacent satellites; each satellite orbits at an altitude of 80,000–90,000 km and an orbital inclination of 90 degrees. It also employs an isotope power supply system and a redundant cold / hot backup system in the attitude and orbit control system. This invention utilizes a high-orbit scheme that avoids the influence of the Van Allen radiation belts, effectively solving the radiation effects caused by the Earth's radiation belts and increasing the reliability of the navigation system; the use of an isotope power supply system improves the operational lifespan of the navigation system; and the cold / hot redundant backup of the attitude and orbit control system enhances the reliability of the control system.

The present application provides a kind of geostationary orbit plane array camera on-orbit star extraction method and system, comprising: according to the principle of stationary orbit satellite plane array imaging, cold air is star area in the periphery of earth disc chart, and star image slides through camera field of view according to the direction from west to east;According to the basic data of star library, combined with satellite orbit, attitude data and imaging condition, the time of star appearing in field of view and the corresponding angle of camera two-dimensional scanning mechanism can be calculated;In actual star observation process, camera two-dimensional scanning mechanism is pointed to the predetermined position in advance according to the corresponding angle of predetermined observation star, and waits for star to appear;After star enters field of view, try to keep star in field of view range, star moves stably in plane array camera field of view, and continuously adjusts two-dimensional scanning mechanism angle along with the motion track of star, to keep continuous observation to star whole track process.