Benefits and lessons learned from the use of the compact PCI standard for spacecraft avionics

Conde, R.F.; Haber, Jon; Webbert, R. W.; Redman, Richard; Mellert, J.D.; Bogdanski, J.F.; Ling, Sharon; Hutcheson, D.

doi:10.1109/dasc.2002.1052958

Cited by 5 publications

(1 citation statement)

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“…At that point the approach for both the spacecraft and instruments was firm, the planned launch targeted an optimized March 2004 window (Yen, 2001;McAdams et al, 2002), and backup launches in May 2004 and July to August 2004 were identified. The overall spacecraft concept and all subsystems were designed (e.g., Ercol and Santo, 1999;Ercol et al, 2000;Persons et al, 2000;Wallis and Cheng, 2001;Vaughan et al, 2001;Dakermanji et al, 2002;Krupiarz et al, 2002;Nhan et al, 2002;Conde et al, 2002;Ling et al, 2002;Moore, 2002;OÕShaughnessy and Vaughan, 2003;Krupiarz, 2003; Stilwell et al, 2003;Stratton et al, 2003;Hauck and Finnigan, 2003;Heiligman et al, 2003).…”

Section: Design and Developmentmentioning

confidence: 99%

The MESSENGER mission to Mercury: Development history and early mission status

McNutt

Solomon

Gold

et al. 2006

Advances in Space Research

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Section: Design and Developmentmentioning

confidence: 99%

The MESSENGER mission to Mercury: Development history and early mission status

McNutt

Solomon

Gold

et al. 2006

Advances in Space Research

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The MESSENGER Spacecraft

Leary

Conde

Dakermanji

et al.

The Messenger Mission to Mercury

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The MESSENGER Spacecraft

et al. 2007

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The MErcury Surface, Space ENvironment, GEochemistry, and Ranging (MES-SENGER) 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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Benefits and lessons learned from the use of the compact PCI standard for spacecraft avionics

Cited by 5 publications

References 1 publication

The MESSENGER mission to Mercury: Development history and early mission status

The MESSENGER mission to Mercury: Development history and early mission status

The MESSENGER Spacecraft

The MESSENGER Spacecraft

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