AAE450 Senior Spacecraft Design Mark Cunningham Mark Cunningham Week 10: March 29 th, 2007...
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Mark Cunningham AAE450 Senior Spacecraft Design Mark Cunningham Week 10: March 29 th , 2007 Communications Team Final Presentation Slides – First Draft
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AAE450 Senior Spacecraft Design Mark Cunningham Communication Satellite Masses GangaleMars Primary Mars Secondary GPS Number of Satellites2123 Satellite Mass (mt) (on orbit wet mass) IMLEO (mt) per satellite (satellite and orbital insertion propulsion mass) Total IMLEO for all satellites: 85 mt GPS Secondary CAD courtesy of Steve Kassab
Transcript of AAE450 Senior Spacecraft Design Mark Cunningham Mark Cunningham Week 10: March 29 th, 2007...
Mark Cunningham
AAE450 Senior Spacecraft Design
Mark CunninghamWeek 10: March 29th, 2007
Communications Team
Final Presentation Slides – First Draft
Mark Cunningham
AAE450 Senior Spacecraft Design
Communication Satellite Masses
Monopropellant hydrazine is used for station keeping and LOX-LH2 is used for the orbital insertion propulsion system.
PrimaryGangale
CAD courtesy of Steve Kassab
Mark Cunningham
AAE450 Senior Spacecraft Design
Communication Satellite Masses
Gangale Mars Primary
Mars Secondary
GPS
Number of Satellites 2 1 2 3
Satellite Mass (mt)(on orbit wet mass)
2.6 3.0 2.5 1.5
IMLEO (mt) per satellite(satellite and orbital insertion propulsion mass)
11.7 14.5 12.3 7.4
Total IMLEO for all satellites: 85 mt
GPS Secondary
CAD courtesy of Steve Kassab
Mark Cunningham
AAE450 Senior Spacecraft Design
Back Up Slides
Mark Cunningham
AAE450 Senior Spacecraft Design
Station Keeping and Propulsion Mass
Attitude control and propulsion system masses are calculated using the rocket equation from ΔV required, Isp, payload mass, and an assumed structural coefficient of ε = .1.
Monopropellant hydrazine (Isp = 220 s) is used for station keeping and LOX-H2 (Isp = 450 s) is used for the propulsion system.
Station keeping and travel ΔV’s gotten from James Goppert’s analysis.
Mark Cunningham
AAE450 Senior Spacecraft Design
Station Keeping and Propulsion Mass
Mark Cunningham
AAE450 Senior Spacecraft Design
Payload
Solar array mass is derived from Ryan Scott’s Solar Array Sizing Code arraysize.m. Thermal mass provided by Rick Hutchinson. Structure mass derived from Brandon Anderson’s commsat.m.
Mark Cunningham
AAE450 Senior Spacecraft Design
References
• Larson, Wiley J. and Pranke, Linda K., Human Space Flight, McGraw-Hill Companies, January 2000, Chapter 27.
• http://exploration.grc.nasa.gov/education/rocket/rktpow.html
• http://exploration.grc.nasa.gov/education/rocket/rktwtp.html
• http://homepage.mac.com/sjbradshaw/msc/attitude.html
• http://cs.space.eads.net/sp/SpacecraftPropulsion/MonopropellantThrusters.html
