Station-keeping of small amplitude motions around the collinear libration point in the real Earth–Moon system

2011 ◽  
Vol 47 (7) ◽  
pp. 1127-1134 ◽  
Author(s):  
Xiyun Hou ◽  
Lin Liu ◽  
Jingshi Tang
Keyword(s):  
Small Amplitude ◽  
Libration Point ◽  
Station Keeping ◽  
Moon System ◽  
The Real ◽  
Collinear Libration Point

scholarly journals A Modified Targeting Strategy for Station-Keeping of Libration Point Orbits in the Real Earth-Moon System

2019 ◽  
Vol 2019 ◽  
pp. 1-11
Author(s):  
Yang Jin ◽  
Bo Xu
Keyword(s):  
State Transition ◽  
Libration Point ◽  
Three Body Problem ◽  
Station Keeping ◽  
Moon System ◽  
The Real ◽  
Libration Point Orbits ◽  
Triangular Libration Points ◽  
Three Body ◽  
Targeting Strategy

In this paper, a modified targeting strategy is developed for missions on libration point orbits (LPOs) in the real Earth-Moon system. In order to simulate a station-keeping procedure in a dynamic model as realistic as possible, LPOs generated in the circular restricted three-body problem (CRTBP) are discretized and reconverged in a geocentric inertial system for later simulations. After that, based on the dynamic property of the state transition matrix, a modified strategy of selecting target points for station-keeping is presented to reduce maneuver costs. By considering both the solar gravity and radiation pressure in a nominal LPO design, station-keeping simulations about fuel consumption for real LPOs around both collinear and triangular libration points are performed in a high-fidelity ephemeris model. Results show the effectivity of the modified strategy with total maneuver costs reduced by greater than 10% for maintaining triangular LPOs.

scholarly journals Modified Chebyshev-Picard Iteration Methods for Station-Keeping of Translunar Halo Orbits

2012 ◽  
Vol 2012 ◽  
pp. 1-18 ◽  
Author(s):  
Xiaoli Bai ◽  
John L. Junkins
Keyword(s):  
State Transition ◽  
Libration Point ◽  
Picard Iteration ◽  
Station Keeping ◽  
Computationally Efficient ◽  
Time Intervals ◽  
Reference Orbit ◽  
Halo Orbits ◽  
The Earth ◽  
Iteration Methods

The halo orbits around the Earth-MoonL2libration point provide a great candidate orbit for a lunar communication satellite, where the satellite remains above the horizon on the far side of the Moon being visible from the Earth at all times. Such orbits are generally unstable, and station-keeping strategies are required to control the satellite to remain close to the reference orbit. A recently developed Modified Chebyshev-Picard Iteration method is used to compute corrective maneuvers at discrete time intervals for station-keeping of halo orbit satellite, and several key parameters affecting the mission performance are analyzed through numerical simulations. Compared with previously published results, the presented method provides a computationally efficient station-keeping approach which has a simple control structure that does not require weight turning and, most importantly, does not need state transition matrix or gradient information computation. The performance of the presented approach is shown to be comparable with published methods.

Calculating the periods of radio signal transmission between two spacecrafts through the Venus atmosphere in the problem of studying its composition

2019 ◽  
Author(s):  
K.S. Fedyaev ◽  
V.V. Koryanov ◽  
S.A. Bober ◽  
V.A. Zubko ◽  
A.A. Belyaev
Keyword(s):  
Radio Signal ◽  
Initial Conditions ◽  
Libration Point ◽  
Signal Transmission ◽  
Energy Costs ◽  
The Sun ◽  
Initial State ◽  
Collinear Libration Point ◽  
Small Spacecraft ◽  
Atmosphere Of Venus

The paper considers calculating the periods of radio signal transmission through the atmosphere of Venus between a small spacecraft placed in a limited orbit in the vicinity of the collinear libration point of the Sun-Venus system and a Venus orbiter. The problem arises in the framework of the project under discussion to study the atmosphere of Venus. The possibility of transfers of these spacecrafts to the required orbits under various initial conditions is also studied. The impulses required for transferring to the specified orbits at the selected initial state vector, the most suitable for solving this problem are calculated. The duration and the number of transmission periods depending on the location of one of the spacecrafts in a limited orbit in the vicinity of the libration point L1 or L2 of the Sun-Venus system are analyzed. The influence of the shape of the orbiter near-Venusian orbit on the character and duration of the periods of transmission through the atmosphere of Venus is investigated. It is concluded that the location of a small spacecraft in a limited orbit in the vicinity of the L1 libration point of the Sun-Venus system is more advantageous compared to L2 both in terms of the duration and the number of the transmission periods as well as terms of the necessary energy costs.

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