A planetary low energy transfer orbit method based on equilibrium point periodic orbit

Abstract

The invention discloses a planet low-energy orbit capture method based on a balance point and a periodic orbit, and relates to an orbit capture method, and belongs to the technical field of aerospace. The method uses characteristics of a balance point, a periodic orbit, and invariant manifold in a sun-plant-detector three-body system to realize capture of a detector by a planet. The method comprises: firstly, applying first engine driving at height of a pericenter which is relatively low relative to the planet, to enter a stable manifold in the three-body system, and sliding to the periodic orbit without power along the manifold, using the orbit as a parking orbit; then using an unstable manifold of the periodic orbit to get close to the planet, selecting an unstable manifold whose pericenter height is the same with that of a target orbit, and applying second engine driving when reaching the pericenter, to realize planet capture. Speed increment required by the method is low, flexibility is high, and the method is suitable for orbit capture of different planets. By using the characteristic of the periodic orbit, the planet can be observed in a capture process, so as to increase data of planet observation in a detection task.

Description

Technical field [0001] The invention relates to a planet capture orbit method, and relates to a capture orbit method when a detector's interplanetary orbit reaches the vicinity of a target planet and is captured by a planet and enters a mission orbit, and belongs to the field of aerospace technology. Background technique [0002] Planetary exploration is one of the important fields of deep space exploration. The orbiting detection of planets is an important means and main way of planet detection. It requires the detector to reach the vicinity of the target celestial body after interstellar navigation and be captured by the planet to form an orbit. Whether it can be successfully captured by the target planet will determine the success or failure of the detection mission and the quality of the detection. [0003] The current design of planetary transfer orbits mainly includes the direct braking transfer method at the pericenter and the transfer method using atmospheric resist...

AI Technical Summary

Problems solved by technology

Moreover, the design of the transfer orbit is greatly affected by the density of the atmosphere, which requires more accurate atmospheric data, and is currently rarely used

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