국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	COMPASS Final Report: Lunar Relay Satellite (LRS)
저자	Oleson, Steven R.;; McGuire, Melissa L.
Keyword	AEROSPACE SYSTEMS;; ANTENNA DESIGN;; AVIONICS;; COSTS;; LUNAR COMMUNICATION;; PARABOLIC REFLECTORS;; PARAMETERIZATION;; POLAR ORBITS;; RELAY SATELLITES;; RISK ASSESSMENT;; SATELLITE DESIGN;; SPACECRAFT PROPULSION;; TEMPERATURE CONTROL
URL	http://hdl.handle.net/2060/20120007106
보고서번호	NASA/TM-2012-217140
발행년도	2012
출처	NTRS (NASA Technical Report Server)
ABSTRACT	The Lunar Relay Satellite (LRS) COllaborative Modeling and Parametric Assessment of Space Systems (COMPASS) session was tasked to design a satellite to orbit in an elliptical lunar polar orbit to provide relay communications between lunar South Pole assets and the Earth. The design included a complete master equipment list, power requirement list, configuration design, and brief risk assessment and cost analysis. The LRS is a half-TDRSS sized box spacecraft, which provides communications and navigation relay between lunar outposts (via Lunar Communications Terminals (LCT)) or Sortie parties (with user radios) and large ground antennas on Earth. The LRS consists of a spacecraft containing all the communications and avionics equipment designed by NASA Jet Propulsion Laboratory s (JPL) Team X to perform the relay between lunar-based assets and the Earth. The satellite design is a standard box truss spacecraft design with a thermal control system, 1.7 m solar arrays for 1 kWe power, a 1 m diameter Ka/S band dish which provides relay communications with the LCT, and a Q-band dish for communications to/from the Earth based assets. While JPL''s Team X and Goddard Space Flight Center s (GSFC) I M Design Center (IMDC) have completed two other LRS designs, this NASA Glenn Research Center (GRC) COMPASS LRS design sits between them in terms of physical size and capabilities.