10 results about "Periodic orbits" patented technology

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 application discloses a launch time and orbit transfer impulse joint planning method for a moon-earth transfer mission, and the method comprises the following steps: obtaining initial orbit, launch time window, propulsion and reentry corridor and other task constraints, adopting a coarse and fine layered strategy to generate candidate launch time, parameterizing a phase of a periodic orbit and quickly searching for available phase points; selecting a single impulse, two impulses or multiple small impulse templates, constructing candidate combinations, quickly estimating candidate trajectories according to a simplified dynamic model, screening feasible schemes through constraint checking, obtaining optimal initial values through multi-index scoring and local encryption, carrying out trajectory propagation and multi-target iterative correction under a full perturbation high-precision model, and after completing convergence and engineering constraint review, outputting a final trajectory and control command. The application realizes joint optimization of launch time and impulse parameters, considers calculation efficiency and accuracy, is suitable for on-board real-time planning, and can output a moon-earth transfer trajectory meeting reentry corridor and multiple engineering constraints.

The application discloses a binary asteroid hovering probe adaptive control method, and belongs to the technical field of deep space probe control. The bounded periodic orbit of the probe near the equilibrium point is obtained by selecting the orbit initial value, and the probe is kept near the nominal hovering orbit by the adaptive control, so that the fuel consumption of the probe during long-time hovering can be effectively reduced; the weight matrix is dynamically selected on the basis of the linear quadratic optimal control, and at the initial moment, the probe has a large position error from the nominal position, so that the controller outputs a large control force to make the probe reach the target position as soon as possible; when reaching the vicinity of the nominal hovering orbit, the controller only needs to provide a small control force to realize the orbit keeping motion of the probe, and further reduce the fuel consumption of the probe. The position error between the nominal hovering orbit near the equilibrium point and the state of the probe is fuzzified, and the adaptive ability of the probe is improved through the weight selection.

The application discloses a design method of earth-moon periodic orbit robust maintenance point based on Lyapunov index, and particularly relates to the technical field of space, and establishes an equivalent position-velocity error model, converts the introduced initial velocity error into equivalent position error by using the equivalent position-velocity error model, and calculates the Lyapunov index of the initial velocity error of the earth-moon periodic orbit; according to the Lyapunov index of the initial position error of the earth-moon periodic orbit and the Lyapunov index of the initial velocity error of the earth-moon periodic orbit, a deep neural network is used to establish the convergence and divergence sphere of the initial position error and the initial velocity error of the earth-moon periodic orbit; according to the obtained convergence and divergence sphere of the initial position error and the initial velocity error of the earth-moon periodic orbit, a traversal method is used to design the robust periodic position maintenance point of the position error convergence, the velocity error convergence and the simultaneous convergence of the position and velocity error, and the error convergence axis is searched, so as to provide a reference for the control target of the orbit periodic position maintenance strategy.

The invention discloses an earth-moon periodic orbit robust retention point design method based on a Lyapunov exponent, and particularly relates to the technical field of space, an equivalent position speed error model is established, an introduced initial speed error is converted into an equivalent position error by using the equivalent position speed error model, and the equivalent position error is calculated. Calculating an initial velocity error Lyapunov index of the earth-moon periodic orbit; according to the earth-moon periodic orbit initial position error Lyapunov index and the earth-moon periodic orbit initial speed error Lyapunov index, establishing an earth-moon periodic orbit-oriented initial position error and initial speed error convergence ball by using a deep neural network; and according to the obtained earth-moon-oriented periodic orbit initial position error and initial speed error convergence ball, designing a robust periodic position holding point with position error convergence, speed error convergence and position and speed error simultaneous convergence by using a traversal method, and searching an error convergence axis, thereby providing a reference for a control target of an orbit periodic position holding strategy.

The application discloses a design method of a high-mobility stealth satellite communication system and relates to the technical field of satellite communication. The application comprises the following steps: step a: system silence and state presetting: a control center makes a satellite of a space segment enter an electromagnetic silence state, a satellite platform starts surface thermal management and retracts a protruding structure, and an orbit maneuver with no fixed period is planned and executed. The application improves the concealment and survivability of the satellite platform in orbit. By making the satellite enter a silence and survival state and implementing thermal management and shape control, combined with the orbit maneuver with no fixed period, the physical and orbit characteristics of the satellite are difficult to be observed and predicted for a long time, traditional detection and tracking means based on a fixed shape and a periodic orbit are invalid, and exposure risk of space assets is controlled. Meanwhile, communication adopts a "zero handshake" burst access mechanism based on one-time instructions, and open signaling interaction in a link establishment process is completely eliminated.

A gravitational mechanical energy generator comprises a dynamic load lifting system (DLLS) for periodic track arc rotations. The system comprises a motor 1 and a flywheel 2 so that energy can be supp

The invention discloses a design method of a high-maneuverability stealth satellite communication system, and relates to the technical field of satellite communication. The method comprises the following steps: step a, system silent latent and state presetting: a control center enables a satellite in a space section to enter an electromagnetic silent state, a satellite platform starts surface thermal management and retracts a protruding structure, and meanwhile, orbital maneuver without a fixed period is planned and executed; according to the method, the concealment and survivability of the satellite platform existing in orbit are improved, the satellite enters the silent latent state, thermal management and appearance control are implemented, and in combination with orbit maneuver without a fixed period, the physical and orbit characteristics of the satellite are difficult to be stably observed and predicted for a long time; a traditional detection tracking means based on a fixed shape and a periodic track loses efficacy, the exposure risk of space assets is controlled, meanwhile, communication adopts a'zero handshake 'burst access mechanism based on a one-time instruction, and public signaling interaction in the link establishment process is thoroughly eliminated.

The application discloses a bifurcation construction method, system, equipment, medium and program of a clover orbit family in a geolunar three-body system, and belongs to the technical field of aerospace. The method comprises the following steps: constructing a geolunar circular restricted three-body dynamics model according to a geolunar three-body system; obtaining a halo orbit family based on the geolunar circular restricted three-body dynamics model; positioning a halo orbit family bifurcation point, and constructing a transition orbit; obtaining a first clover orbit based on the transition orbit, and extending to obtain a clover orbit family. The application can obtain complex periodic orbit families derived near the libration points L1 and L2 in a restricted three-body system, and quickly constructs the periodic orbit family.

The invention discloses a translation point interferometry constellation initial value design method based on phase optimization, and belongs to the field of aerospace. The implementation method comprises the following steps: establishing a dynamic model of a spacecraft in a translational point interferometry constellation; establishing a representation model of the configuration stability index of the translational point interferometry constellation; the method comprises the following steps: setting feature point states, orbital periods and expected terminal states of three spacecrafts of a translational point interferometry constellation, and generating periodic orbits of the three spacecrafts of the translational point interferometry constellation by using a single-step targeting method and numerical integration; establishing a mapping model of an initial phase parameter and a configuration stability index; and constructing an optimization objective function, establishing a translation point interferometry constellation global collaborative optimization model, and performing optimization by using a differential evolution algorithm to obtain a translation point interferometry constellation initial value. The translation point interferometry constellation meeting the long-term stability is obtained through recursion of the initial value, the long-term stability of the translation point interferometry constellation is achieved according to the constellation configuration, and the detection precision of the translation point interferometry constellation is improved.