meetings - Space Flight Mechanics Committee

In this paper, novel families of highly non-Keplerian orbits for spacecraft utilising solar sail
at linear order are investigated in the Earth-Moon circular restricted three-body problem.
Firstly, it is assumed implicitly that the solar sail is a perfect reflector. The orbits were
accomplished by using an optimal choice of the sail pitch angle, which maximize the outof-plane
distance. Thereafter, the resulting effects of the non-ideal flat sail model have been
computed and compared with an ideal solar sail. The main effect of the non-perfect sail is to
reduce the out-of-plane displacement.
10:45 AAS Station-Keeping Strategies for Satellite Constellation
13-445 Hongzheng Cui, Beijing Aerospace Control Center; Geshi Tang, Beijing Aerospace
Control Center; Jianfeng Yin, Beihang University; Hao Huang, Beihang University;
Chao Han, Beihang University
This paper firstly introduces the concepts on control box and control reference for absolute
and relative station-keeping, how to determine the control reference, and the uniform
control flow for different station-keeping strategies. And then, studies the different stationkeeping
control-laws for Walker constellation, including different orbital regions. The
demonstration experiments concerning different station-keeping strategies are carried out
with initial orbit element errors and control tolerance based on Constellation Station
Keeping Kit (CSKK), which is recently designed and developed recently at BACC for
satellte constellation operation demonstration.
11:05 AAS Global Damping Configuration of Large Space Truss Structure Based on
13-446 Energy Finite Element Analysis
Lu Zhou, China Academy of Space Technology (CAST); Yue Wang, Beihang
University; Xinbing Hou, China Academy of Space Technology (CAST); Humei
Wang, China Academy of Space Technology (CAST)
This article adopts the energy finite element method to study the ability of dampers which
absorb and dissipate vibration energy in different locations, and optimizes the global
configuration with the dissipation energy factor. Firstly, we establish the energy equations
the truss and its connection. And then transform the energy function by the Fourier to the
function for using the finite element conveniently. Secondly, configuring different location
of different damper, we analyze the dynamic performance of the whole truss structure based
on the energy finite element method. Finally, we optimize the configuration by adding the
modified modal dissipation energy factor.
23 rd AAS / AIAA Space Flight Mechanics Meeting Page 99