nro12_200303

nro12_200303 - Electromagnetic Formation Flight Progress...

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Electromagnetic Formation Flight Progress Report: March 2003 Submitted to: Lt. Col. John Comtois Technical Scientific Officer National Reconnaissance Office Contract Number: NRO-000-02-C0387-CLIN0001 MIT WBS Element: 6893087 Submitted by: Prof. David W. Miller Space Systems Laboratory Massachusetts Institute of Technology
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O VERVIEW Description of the Effort The Massachusetts Institute of Technology Space Systems Lab (MIT SSL) and the Lockheed Martin Advanced Technology Center (ATC) are collaborating to explore the potential for an Electro-Magnetic Formation Flight (EMFF) system applicable to Earth-orbiting satellites flying in close formation. Progress Overview At MIT, work on EMFF has been pursued on two fronts: the MIT conceive, design, implement and operate (CDIO) class, and the MIT SSL research group. This report summarizes recent progress made in the MIT SSL research group with regards to analyzing the dynamics of a two-spacecraft electromagnetic formation flying system. It is a follow-up to the work presented in the October 2002 progress report, which introduced the nonlinear and linearized dynamics of such a system. In this report, we summarize our recent findings about the controllability and stability of this system.
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1 Introduction 1. Introduction In this report, we sumarize the dynamics of the electromagnetic formation flying (EMFF) system of spacecraft introduced in the October 2002 progress report [1], and then continue by presenting results from recent controllability and stability analyses performed on simi- lar EMFF systems. In particular, we consider a formation of two spacecraft under no external forces and rotating about a common origin. Each spacecraft contains a specified configuration of fixed electromagnets (EM) and reaction wheels (RW) for use as position and attitude actuators. We begin in Section 2 by reviewing the results presented in [1]. In Sections 3 and 4, respectively, we define and respond to certain questions pertaining to the controlla- bility and stability of the system at hand. We then summarize our results and draw con- clusions in Section 5. 2. Background We begin by reviewing the linearized dynamics of a system similar to those considered in this exercise. Reference [1] describes the dynamics of a two-spacecraft EMFF system, where each spacecraft has a single fixed electromagnet, nominally pointed along the line of sight between the two spacecraft. Each spacecraft also has a single reaction wheel, nominally oriented perpendicular to the plane of rotation of the two spacecraft. Such a system has nine degrees of freedom (or eighteen state variables): T x = (2.1) r ∆φ ∆ψ ∆α 1 ∆α 2 3 ∆β 1 2 3 where r , ∆φ ∆ψ are the relative displacements of the vehicles in curvilinear coordi- , nates depicted in Figures 1 and 2, 1 , ∆α 2 3 are the Euler angles of the first space- craft (denoted spacecraft “A”) about its body-fixed z , y , and x axes, respectively, and 1 , ∆β 2 3 are the corresponding Euler angles of the second spacecraft (denoted spacecraft “B”) about its body-fixed coordinate axes.
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This note was uploaded on 11/08/2011 for the course AERO 16.810 taught by Professor Olivierdeweck during the Winter '07 term at MIT.

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nro12_200303 - Electromagnetic Formation Flight Progress...

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