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Transfer orbit family initial value searching method and system based on collision zone atlas

A transfer orbit and search method technology, which is applied in the field of initial value search method and system of transfer orbit family, and can solve the problem that distribution cannot be searched and estimated with purpose.

Active Publication Date: 2021-08-13
NAT SPACE SCI CENT CAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The initial value obtained by the current method can calculate the precise transfer orbital, and then can reproduce a related family or families of transfer orbitals on this basis, but the distribution of various transfer orbital families in the phase space cannot be carried out purposefully. search and estimate

Method used

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  • Transfer orbit family initial value searching method and system based on collision zone atlas
  • Transfer orbit family initial value searching method and system based on collision zone atlas
  • Transfer orbit family initial value searching method and system based on collision zone atlas

Examples

Experimental program
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Effect test

Embodiment 1

[0043] like figure 1As shown, Embodiment 1 of the present invention provides a search method for an initial value of a transfer orbital family based on a collision zone map.

[0044] In the circular restricted three-body problem, the rendezvous coordinate system has an origin at the center of mass of the system, and the x-axis is controlled by the main celestial body P 1 Pointing to the small host object P 2 , the z-axis is parallel to the angular momentum vector of the main celestial body motion, and the y-axis is determined by the right-hand rule. For the convenience of analysis and calculation, each physical quantity is dimensionless and magnitude normalized, and the corresponding mass unit is defined as the total mass of the main celestial body, the length unit is the distance between the two main celestial bodies, and the time unit is divided by the movement period of the main celestial body 2π, the system quality parameter is defined as μ=m 2 / m 1 +m 2 , where m 1 ...

example

[0064] In the restricted three-body problem of the earth-moon type, starting from the circular low-earth orbit (Low Earth Orbit, LEO) and transferring to the short-period orbit (Short Periodic Orbit) with an amplitude of β=0.15 near the L4 Lagrangian point ,SPO) as an example, the process of initial value search using this method is as follows:

[0065] For the problem of directly transferring from LEO to SPO, the velocity increment is applied to the point on SPO, and the collision zone map between the Earth and SPO obtained by reverse integration of 5 time units (about 21.7 days) is as follows figure 2 shown. Sampling at the upper boundary of the widest collision zone where the phase angle of the insertion point is 0.2π, the position direction angle, velocity direction angle and linear interpolation results when the disturbance orbit intersects with LEO are as follows image 3 shown.

[0066] The problem of transferring from LEO to SPO with the assistance of lunar gravity ...

Embodiment 2

[0069] Embodiment 2 of the present invention proposes a transfer orbit family initial value search system based on the collision zone map, the system includes: a collision zone map drawing module, a parking orbit integration module, an orientation angle marking module and a transfer orbit initial value output module; in,

[0070] The collision zone map drawing module is used to apply tangential disturbance to points on the target orbit, and integrate the disturbance orbit, mark the disturbance orbit that can hit the main celestial body, and draw the collision between the main celestial body and the target orbit with map;

[0071] The parking orbit integration module is used to respectively take a preset velocity increment interval on both sides of each collision zone, randomly select a number of sample disturbance orbits from the velocity increment interval, and integrate them to the parking orbit;

[0072] The direction angle marking module is used to mark the position direc...

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Abstract

The invention discloses a transfer orbit family initial value searching method and system based on a collision zone atlas. The method comprises the steps: applying tangential disturbance to a point on a target orbit, carrying out the integration of a disturbance orbit, marking the disturbance orbit which can impact a main celestial body, and drawing a collision zone atlas between the main celestial body and the target orbit; respectively taking a preset speed increment interval on two sides of each collision zone, randomly taking a plurality of sampling disturbance orbits from the speed increment intervals, and integrating the sampling disturbance orbits to a parking orbit; marking a position direction angle and a speed direction angle when the sampling disturbance orbit intersects with the parking orbit; performing linear interpolation on the speed increment to find out a transfer orbit initial value tangent to the parking orbit and the target insertion point. According to the method, the distribution positions of various tangential transfer families are systematically estimated, the orbits of various transfer types are quickly searched, the number of the tangential transfer orbits of various types is systematically and intuitively evaluated, and a proper initial value is provided for subsequent accurate solution of the transfer orbits.

Description

technical field [0001] The invention relates to the technical field of transfer orbits in deep space, in particular to a search method and system for an initial value of a transfer orbit family based on a collision zone map. Background technique [0002] For the calculation of the transfer orbit in deep space, since the aircraft is far away from the original central celestial body, the gravitational perturbation of the aircraft by other celestial bodies cannot be ignored at this time, so the calculation using the two-body model has a large error compared with the real gravitational field, while The restricted three-body problem model can better approximate the motion in the actual gravitational field. When calculating the transfer orbit in the three-body problem model, due to the complexity of the gravitational field and the nonlinearity of the system, the system is highly sensitive to the initial value; and due to the complexity of the motion calculation process in the syst...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24G06F17/11
CPCB64G1/242G06F17/11
Inventor 任婧李明涛王有亮
Owner NAT SPACE SCI CENT CAS
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