This paper investigates properties of low-thrust hovering, including the feasible region and stability, in terms of the dynamical parameters for elongated asteroids.An approximate rotating mass dipole model, by which the description of the rotational gravitational field is reduced to two independent parameters, is employed to construct normalized dynamical equations. The boundaries of the feasible region are determined by contours representing the magnitude of the active control. The effects of a rotating gravitational field and maximal magnitude of the low thrust on the feasible hovering regions are analyzed with numerical results. The stability conditions are derived according to the forms of the eigenvalues of the linearized equation near the hovering position. The stable regions are then determined by a grid search and the effects of the relevant parameters are analyzed in a parametric way. The results show that a close hovering can be easier to realize near the middle of the asteroid than near the two ends in the sense of both required control magnitude and stability.
Asteroid exploration is currently one of the most concerned topics among international space agencies.Orbital dynamics and navigation are obviously crucial for asteroid exploration.This paper aims to give a brief review on the dynamics,control and navigation of asteroid reconnaissance orbits,including the heliocentric transfer orbit and near asteroid orbit.The developments in optimization techniques of the transfer segment are discussed in detail.We surveyed global researches in this field and made comments on several important progresses.The final section proposed a prospective of future studies with emphasis on the key techniques of these issues in the asteroid exploration missions.
The motion of a surface vehicle on/above an irregular object is investigated for a potential interest in the insitu explorations to asteroids of the solar system.A global valid numeric method,including detailed gravity and geomorphology,is developed to mimic the behaviors of the test particles governed by the orbital equations and surface coupling effects.A general discussion on the surface mechanical environment of a specified asteroid,1620 Geographos,is presented to make a global evaluation of the surface vehicle’s working conditions.We show the connections between the natural trajectories near the ground and differential features of the asteroid surface,which describes both the good and bad of typical terrains from the viewpoint of vehicles’dynamic performances.Monte Carlo simulations are performed to take a further look at the trajectories of particles initializing near the surface.The simulations reveal consistent conclusions with the analysis,i.e.,the openfield flat ground and slightly concave basins/valleys are the best choices for the vehicles’dynamical security.The dependence of decending trajectories on the releasing height is studied as an application;the results show that the pole direction(where the centrifugal force is zero)is the most stable direction in which the shift of a natural trajectory will be well limited after landing.We present this work as an example for pre-analysis that provides guidance to engineering design of the exploration site and routing the surface vehicles.
