5 results about "Atmospheric drag" patented technology

The application relates to a configuration design method of a three-dimensional orbiting sail with posture stability, and belongs to the field of spacecraft attitude dynamics and structure design.The application is realized by the following method: considering the environmental perturbation of atmospheric resistance, atmospheric resistance moment and gravity gradient moment, an orbit attitude coupling dynamics model of a three-dimensional orbiting sail system is established based on a position vector and Euler angles; the three-dimensional orbiting sail and a spacecraft body are regarded as rigid bodies, and the windward area is considered to be blocked by airflow so as to more accurately describe the orbit movement and attitude movement of the system in the orbiting process; the attitude movement is simplified for the attitude dynamics of the system; the attitude stability of the system in the orbiting process is analyzed by using a phase plane method, a Lyapunov energy function method and other stability analysis methods of nonlinear dynamics systems; the relationship between important structure parameters such as a cone angle and a support rod length of the three-dimensional orbiting sail and the attitude stability is further constructed; and the three-dimensional orbiting sail satisfying the preset attitude stability requirement is obtained based on the relationship, so that the configuration design is realized.

A method and system for optimizing on-board orbit mission sequences based on real-time windward area is disclosed. The system includes a data configuration module, an area mapping module, a high-precision prediction module, and an autonomous feedback optimization module. The data configuration module receives mission sequences and space environment characteristic parameters, and synchronizes the satellite's real-time orbit vector. The area mapping module analyzes the target attitude based on the attitude parameters in the mission sequence and calculates the equivalent windward area corresponding to each mission time period in real time by combining the velocity vector. The high-precision prediction module executes the attitude-coupled variable area HPOP algorithm, incorporating the dynamically calculated equivalent windward area as a key perturbation term into the atmospheric drag calculation, and outputs orbit prediction results reflecting the attitude adjustment impact. The autonomous feedback optimization module performs consistency judgment on the difference between two adjacent recursive results. If the difference does not meet the preset requirements, it autonomously adjusts the mission execution time and mission execution parameters in the mission sequence and feeds them back to the area mapping module for iterative calculation.

This invention discloses a method for calculating the sub-satellite point based on the SGP4 orbital model, relating to the field of satellite navigation and orbit prediction technology. The polar spherical projector of this invention eliminates longitude jumps in latitude >75°, ensuring continuous trajectory output for scenarios such as polar scientific expeditions and glacier monitoring. By directly mapping three-dimensional radial information to generate latitude, it avoids the iterative convergence problem of the ellipsoidal model, ensuring natural symmetry of the North and South Poles coordinates and continuous longitude domain. Second-order differential compensation of the mean anomaly angle, combined with dynamic correction of the Earth's rotational angular velocity, strictly aligns the UTC timestamp with the orbital position. It suppresses the cumulative error generated by traditional linear interpolation at perigee. It enhances adaptability to complex perturbation environments; atmospheric drag vectorization compensation captures real-time aerodynamic direction through relative velocity cross terms, combined with continuous processing of the density index model, significantly improving the orbital attenuation prediction accuracy of low-Earth orbit satellites during geomagnetic storms.

The application discloses a low-orbit satellite parameter adaptive control method with a solar sail driving device, belongs to the technical field of aerospace, and particularly relates to the technical field of low-orbit satellite parameter control. The method solves the technical problem of overcoming the influence of satellite moment of inertia and compensating the influence of SADA disturbance torque and atmospheric resistance torque on the satellite attitude control precision. The method comprises the following steps: constructing a satellite attitude kinematics and dynamics equation in the form of a quaternion, and on the basis, constructing a satellite attitude kinematics and dynamics equation for attitude controller design; defining the error attitude kinematics and dynamics equation of the satellite through an attitude control error and an angle control error; dividing and converting the parameters to be estimated and known state variables, and representing the negative influence of moment of inertia error on the attitude by matrix operation; designing an attitude controller control torque in a manner of combining nonlinear feedback control with adaptive control; and updating the adaptive estimation value in the attitude controller control parameter by using a parameter adaptive law.

The application discloses a method for calculating atmospheric resistance of LEO spacecraft based on posture rotation mode, and relates to the field of wind tunnel test, and comprises the following steps: S1, selecting a corresponding posture rotation mode of the spacecraft according to a scene; S2, calculating the windward area and atmospheric resistance of the posture rotation mode of the spacecraft selected in S1 in a period; and S3, based on the calculation result of S2, calculating the period average atmospheric resistance of the spacecraft in the corresponding posture rotation mode; the method for calculating atmospheric resistance of LEO spacecraft based on posture rotation mode is a fast and efficient algorithm for atmospheric resistance under the operation condition of dynamic change of the in-orbit spacecraft posture, the period average atmospheric resistance is obtained by precisely calculating the atmospheric resistance in the rotation period, and thus an important basic prerequisite is provided for the medium and long term analysis and prediction of the orbit parameters of the LEO spacecraft.