The Control And Use Of Libration Point Satellites

This work presents the state-of-the-art in numerical and analytical techniques as well as future trends associated with "mission design" for libration point orbits. It contains papers explaining theoretical developments and their applications, including the accurate description of some actual libration point missions of ESA and NASA. The existing software in the field and some applications beyond the neighbourhood of the Earth are also presented. Special emphasis is placed on the use of dynamical system methodology in the libration-point-orbits mission design.

This book presents the state of the art in numerical and analytical techniques as well as future trends associated with mission design for libration point orbits. It contains papers explaining theoretical developments and their applications, including the accurate description of some actual libration point missions of ESA and NASA. The existing software in the field and some applications beyond the neighborhood of the Earth are also presented. Special emphasis is placed on the use of dynamical systems methodology in the libration-point-orbits mission design. Contents:Mission Analysis and Operations:Orbit Determination Issues for Libration Point Orbits (M Beckman)Libration Point Missions, 1978–2002 (D W Dunham & R W Farquhar)Herschel, Plank and GAIA Orbit Design (M Hechler & J Cobos)The SOHO Mission L1 Halo Orbit Recovery from the Attitude Control Anomalies of 1998 (C E Roberts)Dynamics Around the Libration Points:New Results on Computation of Translunar Halo Orbits of the Real Earth–Moon System (M A Andreu)Astrodynamical Applications of Invariant Manifolds Associated with Collinear Lissajous Libration Orbits (J Cobos & J J Masdemont)Halo Orbits in the Sun–Mars System (I Gacka)Libration Point Orbits: A Survey from the Dynamical Point of View (G Gómez et al.)Software Tools:Software Architexture and Use of Satellite Tool Kit's Astrogator Module for Libration Point Orbit Missions (J Carrico & E Fletcher)An Architecture for a Generalized Spacecraft Trajectory Design and Optimization System (C Ocampo)Solar System Dynamics and Applications:Restricted Four and Five Body Problems in the Solar System (F Gabern & À Jorba)One Kind of Collision Orbits Related to Lagrangian Libration Points (A E Rosaev)Statistical Theory of Interior–Exterior Transition and Collision Probabilities (S Ross)Smaller Alignment Index (SALI): Determining the Ordered or Chaotic Nature of Orbits in Conservative Dynamical Systems (Ch Skokos et al.)and other papers Readership: Researchers in aerospace engineering, mechanics, nonlinear science, chaos and dynamical systems. Keywords:Libration Point;Astrodynamics;Halo Orbits;Mission Design;Three-Body Problem;Solar System Dynamics;Trajectory Design

This book studies several problems related to the analysis of planned or possible spacecraft missions. It is divided into four chapters. The first chapter is devoted to the computation of quasiperiodic solutions for the motion of a spacecraft near the equilateral points of the Earth-Moon system. The second chapter gives a complete description of the orbits near the collinear point, L 1, between the Earth and the Sun in the restricted three-body problem (RTBP) model. In the third chapter, methods are developed to compute the nominal orbit and to design and test the control strategy for the qua

A growing interest in formation flying satellites demands development and analysis of control and estimation algorithms for station-keeping and formation maneuvering. This thesis discusses the development of a discrete linear-quadratic- regulator control algorithm for formations in the vicinity of the L2 sun-earth libration point. The development of an appropriate Kalman filter is included as well. Simulations are created for the analysis of the station-keeping and various formation maneuvers of the Stellar Imager mission. The simulations provide tracking error, estimation error, and control effort results. From the control effort, useful design parameters such as AV and propellant mass are determined. For formation maneuvering, the drone spacecraft track to within 4 meters of their desired position and within 1.3 millimeters per second of their desired zero velocity. The filter, with few exceptions, keeps the estimation errors within their three-sigma values. Without noise, the controller performs extremely well, with the drones tracking to within several micrometers. Bach drone uses around 1 to 2 grams of propellant per maneuver, depending on the circumstances.

In this book the problem of station keeping is studied for orbits near libration points in the solar system. The main focus is on orbits near halo ones in the (Earth+Moon)-Sun system. Taking as starting point the restricted three-body problem, the motion in the full solar system is considered as a perturbation of this simplified model. All the study is done with enough generality to allow easy application to other primary-secondary systems as a simple extension of the analytical and numerical computations.