10 results about "Orbital period" patented technology

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.

The application relates to a design method of a moon global positioning constellation based on a lunar space DRO reference orbit, wherein the initial orbit state and the orbit period of any DRO reference orbit in a DRO reference orbit to be deployed are determined based on the initial phase of the DRO reference orbit; the initial orbit state of any satellite to be deployed on the initial phase of the DRO reference orbit is determined based on the orbit state corresponding to the target phase; the orbit period of the any satellite is determined based on the orbit period of the any DRO reference orbit; the target orbit state corresponding to the any satellite is obtained based on the orbit period of the any satellite and the initial orbit state of the any satellite; and the moon global positioning constellation under a four-body model is constructed based on the target orbit state corresponding to each satellite. The moon global positioning constellation constructed by the application has higher stability and higher moon surface coverage capacity compared with the existing near-moon constellation.

This application provides a method, apparatus, electronic device, and storage medium for adjusting the solar array's attitude towards the sun, relating to the field of satellite control technology. The method for adjusting the solar array's attitude towards the sun includes: when the energy output corresponding to the target satellite's position at a preset orbital point is not within a preset energy output range, acquiring the target solar array's attitude information towards the sun and historical attitude information from the previous orbital period adjacent to the current orbital period; determining initial attitude adjustment information based on the target solar array's attitude information and the historical attitude information; determining multiple historical attitude adjustment information corresponding to the initial attitude adjustment information, and determining the target attitude adjustment information based on the multiple historical attitude adjustment information; determining the final solar array's attitude information based on the target attitude adjustment information and the target solar array's attitude information, and controlling the solar array to adjust its attitude based on the final solar array's attitude information.

The application discloses a scanning method and device of a non-cooperative target, electronic equipment and program product, and relates to the technical field of spaceflight measurement and control, wherein the scanning method comprises the following steps: acquiring initial orbit elements of the non-cooperative target, celestial body parameters of a target celestial body and antenna parameters of an antenna; determining the number of beam pointing positions required for the antenna to scan one orbit period of the non-cooperative target based on the initial orbit elements, the celestial body parameters and the antenna parameters; determining an acceleration multiple based on the orbit period of the non-cooperative target, the number of beam pointing positions and the antenna parameters; and generating guide data based on the initial orbit elements and the acceleration multiple, so as to control the antenna to scan the non-cooperative target through the guide data. The application solves the technical problem that the non-cooperative target cannot be efficiently scanned in the related art, thereby reducing the probability of capturing the non-cooperative target.

The application provides a spacecraft pure magnetic control sun safety control method and system based on a magnetic moment device, which comprises the following steps: calculating a normal vector of a rotation shaft plane through a sun vector and a sun-pointing vector of the system, normalizing a magnetic field vector and constructing a unit orthogonal vector in the normal plane, solving an optimal rotation shaft vector in combination with a rotation inertia array, dynamically adjusting a control parameter according to a geometric included angle between the optimal rotation shaft and an inertial angular velocity of the system, superimposing a magnetic control sun pointing directional control amount and a damping control amount to obtain a total control amount. The system comprises vector calculation, optimal rotation shaft solving, control parameter adjustment and magnetic control amount output modules connected in sequence, and can be additionally provided with an execution driving module. The application fully considers the geometric relationship of multiple vectors, avoids attitude oscillation divergence, and can realize a sun pointing directional accuracy of ≤15° in less than one orbit period, thereby guaranteeing the charging of a solar cell array and providing a reliable pure magnetic control scheme for a spacecraft safety mode, and the engineering application value is remarkable.

The application relates to a space target local retrieval and identification method, and belongs to the cross field of space situation awareness, space dynamics and high-performance databases. The steps comprise the following steps: multi-source TLE orbit data and service attribute fusion pretreatment; multi-feature fusion dynamic decision tree adaptive time step allocation based on orbit period, eccentricity and task type; the HEALPix equal-area celestial sphere gridding algorithm is introduced to reduce the three-dimensional continuous observation space to a discrete one-dimensional grid identifier, and a lightweight space-time key-value pair is reconstructed in combination with discrete time slicing; a high-concurrency space-time inverted index is reconstructed by multi-process lock-free sandbox streaming writing and database kernel-level aggregation deduplication; a fast initial screening of candidate targets is realized by constructing an anti-time-space aliasing dynamic safety margin expansion search area; and high-precision target accurate matching identification. The application realizes fast retrieval and high-confidence identification of a large number of space targets with a constant-level time complexity, and significantly improves the real-time response capability of a space situation awareness system.

The application relates to the technical field of satellite task planning, and discloses a multi-constraint satellite task planning method and system based on U-Net. The method comprises the following steps: acquiring orbit parameter information of a target satellite; constructing multi-source constraint adjustment; constructing a unified gridded multi-channel feature set; constructing a three-dimensional sample feature vector based on an orbit period and a snake-shaped arrangement mode; generating a corresponding binary label feature vector; and outputting a satellite task planning prediction result. Compared with the prior art, the method can solve the technical problems that the prior art relies on manual rules to formulate tasks, is difficult to cope with multi-source heterogeneous constraint fusion and large-scale sample parallel processing, and especially under the conditions that task windows overlap densely or ground resources conflict seriously, the prior art cannot realize fast and efficient imaging task planning. Due to the three-dimensional space-time representation of multi-constraint information and the introduction of the U-Net model with a coding and decoding jump structure, the intelligent level of satellite imaging task planning is improved.

This manual provides a method and apparatus for constructing a stratigraphic geochronology framework, applicable to the field of oil and gas exploration technology. By extracting and utilizing corresponding uranium-free natural gamma curves from well logging data of the target formation to replace conventional natural gamma (GR) curves, the propagation and amplification effects of uranium-related non-astronomical disturbances in spectral analysis, period screening, and astronomical tuning processes can be effectively reduced, improving the stability and reliability of orbital period identification and tuning results. Furthermore, by introducing a processing flow for the identification, tuning, and verification of astronomical cycle signals, a suitable absolute astronomical timescale can be quickly and accurately determined. Based on this absolute astronomical timescale, a high-resolution and effective stratigraphic geochronology framework can be accurately and efficiently constructed. This framework can then be used to accurately assess unconventional oil and gas intervals in the target area, effectively guiding oil and gas exploration and development in the target region.

This invention discloses a method, apparatus, equipment, and medium for identifying organic-rich shale strata, comprising: acquiring well logging data corresponding to completed wells in the area to be analyzed; performing multi-window spectral analysis on the well logging data to determine multiple different astronomical orbit periods corresponding to the well logging data; performing Gaussian bandpass filtering on each different astronomical orbit period to obtain the long eccentricity period, short eccentricity period, and slope period corresponding to each different astronomical orbit period; establishing the correspondence between each formation and each long eccentricity period, short eccentricity period, and slope period; and identifying organic-rich shale strata based on the lithological organic carbon data of each formation in the completed wells and the corresponding relationships. This invention accurately and rapidly identifies the sedimentary characteristics of shale strata at different astronomical orbit period scales and finely characterizes organic-rich shale strata at different levels.

This invention discloses an optimization method for low-thrust transfer between circular orbits based on piecewise constant yaw angle guidance, belonging to the field of spacecraft orbit control technology. The implementation method of this invention is as follows: the low-thrust transfer process is divided into a transfer segment, a drift segment, and an adjustment segment; a piecewise constant yaw angle guidance strategy is proposed, using latitude argument angles α, β, γ as switching points, dividing each orbital period into four arc segments, maintaining a constant yaw angle and thrust switching state within each arc segment; based on the Gaussian perturbation equation, analytical solutions are derived for the long-term changes of the orbital semi-major axis, orbital inclination, and right ascension of the ascending node under this strategy and perturbation influence; the parameters of the optimal drift orbit are estimated based on the impulse assumption; a mixed-integer nonlinear programming model is established with the objective of minimizing the total velocity increment, and based on the dynamic relationship that "inclination changes are only generated by the thrust of arc segment 1," the model is transformed into several nonlinear programming sub-problems for solution, obtaining near-optimal guidance parameters. This invention avoids tedious numerical integration, significantly improves the efficiency of orbit design and optimization, and the resulting transfer scheme has fuel consumption close to the theoretical optimum. Moreover, the algorithm is robust and suitable for rapid orbit design tasks such as large-scale constellation deployment.