4 results about "Circular orbit" patented technology

This invention proposes a method and system for remote sensing satellite orbit design based on multi-parameter fuzzy constraints. The method includes: receiving input orbit boundary constraints and design constraints; calculating a series of information about the corresponding orbit based on the altitude range, pixel resolution, revisit constraints, and number of mosaic operations for the sun-synchronous return circular orbit; calculating relevant information that can be directly filtered by subsequent design constraints based on the candidate orbit parameters; filtering the directly filtered relevant information using imaging angle constraints, swath width constraints, and integration time constraints; and filtering the orbit using latitude constraints, marking results that meet and do not meet the constraints. This invention integrates and coordinates multi-domain knowledge related to orbit design and the fragmented steps of orbit design, significantly improving the overall efficiency of satellite design.

The present application relates to the field of satellite communication and information technology, in particular to a shared space-based system and method. The present application provides a near-equatorial orbit low-orbit open shared space-based system, which comprises a low-orbit communication satellite constellation, a space digital base and a resource fusion scheduling center arranged on a near-equatorial orbit. The low-orbit communication satellite constellation comprises a main constellation layer and a network supplement layer. The near-equatorial low-orbit circular orbit is arranged in the main constellation layer, and the near-equatorial medium-orbit circular orbit is arranged in the network supplement layer. The present application eliminates global communication and blind area, improves resource utilization, and has instant response and customization. With the advantages of near-equatorial orbit, space perception load is carried, and the system has the prospects of commercial value closed loop, ecological partner cooperation and sustainable development: the load carrying and resource sharing mechanism is opened, the redundant satellite launch is reduced, and the problem of near-earth orbit congestion is alleviated.

The application discloses a kind of near-circular orbit space target initial orbit determination method based on single optical satellite, belong to space-based situation awareness technical field.The method includes: S1, using two groups of observation data successively, according to the right ascension and declination calculation space target true anomaly angle variation, based on circular orbit assumption through cosine theorem and search iteration estimation space target distance to geocenter within two groups of observation period;S2, repeat S1 for all observation data within period, using elliptical orbit equation and least square method calculates semi-major axis, eccentricity, and iteratively optimizes initial true anomaly;S3, according to semi-major axis, eccentricity and initial true anomaly calculation space target position and certain point velocity vector, utilize initial orbit normal vector and two-body orbit model restores initial orbit;If eccentricity is larger, then using Lambert specific orbit calculation velocity.The method can efficiently generate initial orbit using short arc angle data, avoid iteration not convergent, improve near-circular orbit space target orbit determination accuracy.

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.