Low Earth Orbit Rendezvous Strategy for Lunar Missions

Cates,; Cirillo,; Stromgren,

doi:10.1109/wsc.2006.323220

Cited by 9 publications

(6 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…To assist in the reliability analysis, NASA has been developing an integrated methodology to analyze launch and assembly reliability. This work builds upon previous analyses performed for the Space Shuttle and International Space Station Programs [3,4,5], the Constellation Program [6,7], the Review of Human Space Flight Plans Committee [8], studies performed in 2011 on launch and assembly reliability for human exploration missions to near-Earth asteroids [9] and studies performed in 20 12 on launch and assembly reliability for human exploration of Mars [10].…”

Section: Introductionmentioning

confidence: 83%

International human mission to Mars: Analyzing a conceptual launch and assembly campaign

Cates

Stromgren²,

Arney³

et al. 2014

2014 IEEE Aerospace Conference

Self Cite

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 83%

International human mission to Mars: Analyzing a conceptual launch and assembly campaign

Cates

Stromgren²,

Arney³

et al. 2014

2014 IEEE Aerospace Conference

Self Cite

View full text Add to dashboard Cite

“…This work builds upon previous analyses performed for the Constellation program [1,2] and for the Review of Human Space Flight Plans Committee [3].…”

mentioning

confidence: 84%

Launch and assembly reliability analysis for human space exploration missions

Cates¹,

Gelito²,

Stromgren³

et al. 2012

2012 IEEE Aerospace Conference

View full text Add to dashboard Cite

Abstract-NASA's future human space exploration strategy includes single and multi-launch missions to various destinations including cis-lunar space, near Earth objects such as asteroids, and ultimately Mars. Each campaign is being defined by Design Reference Missions (DRMs). Many of these missions are complex, requiring multiple launches and assembly of vehicles in orbit. Certain missions also have constrained departure windows to the destination. These factors raise concerns regarding the reliability of launching and assembling all required elements in time to support planned departure. This paper describes an integrated methodology for analyzing launch and assembly reliability in any single DRM or set of DRMs starting with flight hardware manufacturing and ending with final departure to the destination. A discrete event simulation is built for each DRM that includes the pertinent risk factors including, but not limited to: manufacturing completion; ground transportation; ground processing; launch countdown; ascent; rendezvous and docking, assembly, and orbital operations leading up to transdestination-injection. Each reliability factor can be selectively activated or deactivated so that the most critical risk factors can be identified. This enables NASA to prioritize mitigation actions so as to improve mission success.

show abstract

“…To assist in the reliability analysis, NASA has been developing an integrated methodology to analyze launch and assembly reliability. This work builds upon previous analyses performed for the Space Shuttle and International Space Station Programs [3,4,5], the Constellation Program [6,7], the Review of Human Space Flight Plans Committee [8], and studies performed in 2011 on launch and assembly reliability for human exploration missions to near-Earth asteroids [9].…”

Section: Introductionmentioning

confidence: 82%

Launch and assembly reliability analysis for Mars human space exploration missions

Cates

Gelito

Stromgren³

et al. 2013

2013 IEEE Aerospace Conference

View full text Add to dashboard Cite

Abstract-NASA's long-range goal is focused upon human exploration of Mars. Missions to Mars will require campaigns of multiple launches to assemble Mars Transfer Vehicles in Earth orbit. Launch campaigns are subject to delays, launch vehicles can fail to place their payloads into the required orbit, and spacecraft may fail during the assembly process or while loitering prior to the Trans-Mars Injection (TMI) burn. Additionally, missions to Mars have constrained departure windows lasting approximately sixty days that repeat approximately every two years. Ensuring high reliability of launching and assembling all required elements in time to support the TMI window will be a key enabler to mission success. This paper describes an integrated methodology for analyzing and improving the reliability of the launch and assembly campaign phase. A discrete event simulation involves several pertinent risk factors including, but not limited to: manufacturing completion; transportation; ground processing; launch countdown; ascent; rendezvous and docking, assembly, and orbital operations leading up to TMI. The model accommodates varying numbers of launches, including the potential for spare launches. Having a spare launch capability provides significant improvement to mission success.

show abstract

Low Earth Orbit Rendezvous Strategy for Lunar Missions

Cited by 9 publications

References 2 publications

International human mission to Mars: Analyzing a conceptual launch and assembly campaign

International human mission to Mars: Analyzing a conceptual launch and assembly campaign

Launch and assembly reliability analysis for human space exploration missions

Launch and assembly reliability analysis for Mars human space exploration missions

Contact Info

Product

Resources

About