Optimization of Separated Spacecraft Interferometer Trajectories in the Absence of A Gravity-Well Edmund M Kong Prof david w, miller MIT Space Systems Laboratory 20th March 1998 Space Systems Laboratory Massachusetts Institute of Technology

Deployment and Geometry Maintenance Deployable Membranes Used for solar arrays, sunshields, decoys Being researched for apertures starting at RF and eventually going to optical Inflatables First US satellite was inflated (ECHO D) Enables a very large deployment ratio -=deployed over stowed dimension

Outline Launch systems characteristics Launch systems selection process Spacecraft design envelope environments

Earth Orbiting Clusters Edmund M C Kong SSL Graduate Research Assistant Prof david w. miller Director, MIT Space Systems Lab Space 2001 Conference& Exposition Albuquerque August28-30,2001

ADCS Motivation Motivation Sensors GPS star trackers. limb In order to point and slew optical sensors rate gy ros. inertial systems, spacecraft attitude control measurement units provides coarse pointing while

ARGOS Overview Angular Resolution at 2=550 nm: 5 arcsec Wavelength Regime 400-700 nm FOr (Field-of-Regard): 120(full cone)

Introduction Objective: To compare the different imaging configurations for a Separated Spacecraft Interferometer operating from an Earths orbit

《卫星工程》英文版（一） l2_orbital_mech

第九章新产品开发经济分析 9.1科技进步与新产品开发 9.2新产品开发管理概述

主要讨论大跨屋盖结构风荷载的计算 包括水平风力和竖向风力的计算等