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Aiming at the problem of the precise design of the direct transfer trajectory of Mars probe, this paper proposes an algorithm of fast differential correction.
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We present the optimized design of preliminary interplanetary transfer trajectory for two kinds of missions.
A design and optimal method of transfer trajectory for asteroid Ivar is discussed in this paper.
To reduce the total mission velocity increments further, a procedure is developed which minimizes total velocity increments for this scheme of transfer trajectory for asteroid Ivar.
The emphasis is put on the design and optimization of preliminary interplanetary transfer trajectory for the mission in this paper.
The transfer trajectory for rendezvous with asteroid Ivar is designed by means of Earth gravity assist with deep space maneuver (Delta-VEGA) technology.
To demonstrate the orbit transfer capabilities of the concurrent controller, a smooth elliptical orbit transfer trajectory for co-planar circular orbits is designed.
The transfer trajectory consists of launch of the spacecraft from Earth to a halo orbit and transfer phase from the halo orbit to the vicinity of the targeted sub-L1 point.
The proposed optimal transfer trajectory consists of an active part with low-thrust propulsion and a passive coasting part with no thrust or fuel consumption.
This paper presents a detailed analysis on the equatorial inclination of Earth parking orbits associated with transfer trajectories to lunar libration point orbits.
Previous to the transfer trajectory design, the existence of this kind of transfer trajectory is checked from the point of view of energy.
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