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Title:
The MESSENGER Spacecraft
Authors:
Leary, James C.; Conde, Richard F.; Dakermanji, George; Engelbrecht, Carl S.; Ercol, Carl J.; Fielhauer, Karl B.; Grant, David G.; Hartka, Theodore J.; Hill, Tracy A.; Jaskulek, Stephen E.; Mirantes, Mary A.; Mosher, Larry E.; Paul, Michael V.; Persons, David F.; Rodberg, Elliot H.; Srinivasan, Dipak K.; Vaughan, Robin M.; Wiley, Samuel R.
Affiliation:
AA(Space Department, The Johns Hopkins University Applied Physics Laboratory), AB(Space Department, The Johns Hopkins University Applied Physics Laboratory), AC(Space Department, The Johns Hopkins University Applied Physics Laboratory), AD(Space Department, The Johns Hopkins University Applied Physics Laboratory), AE(Space Department, The Johns Hopkins University Applied Physics Laboratory), AF(Space Department, The Johns Hopkins University Applied Physics Laboratory), AG(Space Department, The Johns Hopkins University Applied Physics Laboratory), AH(Space Department, The Johns Hopkins University Applied Physics Laboratory), AI(Space Department, The Johns Hopkins University Applied Physics Laboratory), AJ(Space Department, The Johns Hopkins University Applied Physics Laboratory), AK(Space Department, The Johns Hopkins University Applied Physics Laboratory), AL(Space Department, The Johns Hopkins University Applied Physics Laboratory), AM(Space Department, The Johns Hopkins University Applied Physics Laboratory), AN(Space Department, The Johns Hopkins University Applied Physics Laboratory), AO(Space Department, The Johns Hopkins University Applied Physics Laboratory), AP(Space Department, The Johns Hopkins University Applied Physics Laboratory), AQ(Aerojet)
Publication:
Space Science Reviews, Volume 131, Issue 1-4, pp. 187-217 (SSRv Homepage)
Publication Date:
08/2007
Origin:
SPRINGER
Keywords:
MESSENGER, Mercury, Spacecraft, Subsystem, Mass, Power
DOI:
10.1007/s11214-007-9269-0
Bibliographic Code:
2007SSRv..131..187L

Abstract

The MErcury Surface, Space ENvironment, GEochemistry, and Ranging (MESSENGER) spacecraft was designed and constructed to withstand the harsh environments associated with achieving and operating in Mercury orbit. The system can be divided into eight subsystems: structures and mechanisms (e.g., the composite core structure, aluminum launch vehicle adapter, and deployables), propulsion (e.g., the state-of-the-art titanium fuel tanks, thruster modules, and associated plumbing), thermal (e.g., the ceramic-cloth sunshade, heaters, and radiators), power (e.g., solar arrays, battery, and controlling electronics), avionics (e.g., the processors, solid-state recorder, and data handling electronics), software (e.g., processor-supported code that performs commanding, data handling, and spacecraft control), guidance and control (e.g., attitude sensors including star cameras and Sun sensors integrated with controllers including reaction wheels), radio frequency telecommunications (e.g., the spacecraft antenna suites and supporting electronics), and payload (e.g., the science instruments and supporting processors). This system architecture went through an extensive (nearly four-year) development and testing effort that provided the team with confidence that all mission goals will be achieved.
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Database: Astronomy
Physics
arXiv e-prints