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An Algorithm for Solving the Scope of Spacecraft's Launchable Area Under Energy and Time Constraints

A time-constrained and energy-constrained technology, applied in the field of spacecraft orbital dynamics, can solve problems such as difficulty in improving accuracy, large amount of calculation, and large amount of calculation, and achieve the effect of good promotion and application prospects, simple algorithm, and simple engineering implementation.

Active Publication Date: 2022-04-12
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This type of method requires a large amount of calculation, and it is difficult to improve the accuracy. If a more accurate range of the launchable area is required, a very large amount of calculation is required

Method used

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  • An Algorithm for Solving the Scope of Spacecraft's Launchable Area Under Energy and Time Constraints
  • An Algorithm for Solving the Scope of Spacecraft's Launchable Area Under Energy and Time Constraints
  • An Algorithm for Solving the Scope of Spacecraft's Launchable Area Under Energy and Time Constraints

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Experimental program
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Embodiment 1

[0116] (1) Considering that the target spacecraft will pass through the orbital plane of one’s own spacecraft many times in one day, the position of the target spacecraft at each crossing time is taken as the target point, and its radius is used as the radius of the target orbit to calculate the launchable area. The following is the initial value of the orbital elements of the own spacecraft and the target spacecraft:

[0117] Table 1 Statistical table of the initial value of the orbital elements of both sides in the calculation of the launchable area

[0118]

[0119] Such as Figure 12 As shown, the target spacecraft will pass through the orbital plane of its own spacecraft 19 times in one day, and thus the range of the launchable area for 19 times can be obtained. It takes about 0.1s to calculate the crossing time and position, and the corresponding launchable area. It can be seen that as the number of intersections changes, the radius of the target point will also chang...

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Abstract

The invention discloses an algorithm for solving the launch range of a spacecraft under the constraints of energy and time. Firstly, it is judged whether the target point can be reached under the constraint conditions, and then by using the properties of the reachable domain of the circular orbit, by solving the non-linear equations The range of the transfer angle in the case of the maximum pulse, and the transfer time corresponding to the maximum and minimum values ​​of the transfer angle are obtained by means of the method. Then compare the maximum transfer time of the task with the obtained transfer time, and select the solution strategy of the transfer angle range under the time and energy constraints according to different situations. In some cases, it is necessary to calculate the transfer time and the transfer angle range when the pulse size is determined by solving nonlinear equations to determine the final feasible transfer angle range. The algorithm of the invention can greatly improve the calculation speed and precision, the engineering implementation is simple, and the popularization and application prospect is good.

Description

technical field [0001] The invention belongs to the technical field of orbital dynamics of spacecraft, and in particular relates to an algorithm for solving the range of a launchable area of ​​a spacecraft under energy and time constraints. Background technique [0002] In the spacecraft rendezvous mission, the position of the target spacecraft when it passes through the orbital plane of the own spacecraft can be known through orbit forecasting, etc., and the own spacecraft can perform the rendezvous mission by changing orbits in the same plane. The energy and time available for orbit change are often limited, so it is necessary to solve the constraints of orbit change capability and mission time. The initial position collection of the own spacecraft on the initial orbit that can rendezvous with the target spacecraft through maneuvering is the launch area. The current existing solution methods usually traverse the orbit of the own spacecraft to determine whether a certain po...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/10
CPCG06F17/10
Inventor 王悦何钰琛
Owner BEIHANG UNIV