1 / 7

Brian Erson Attitude Control Systems

Brian Erson Attitude Control Systems. Trans Lunar Phase Alternative Design Comparison. 1. Orbit Transfer Vehicle Stabilization. 2. Mass Layout. Conclusion: Mass difference represents a savings of > 34.6 kg with 3-axis stabilized spacecraft.

Télécharger la présentation

Brian Erson Attitude Control Systems

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.


Presentation Transcript

  1. Brian ErsonAttitude Control Systems Trans Lunar Phase Alternative Design Comparison 1 [Brian Erson] [Attitude]

  2. Orbit Transfer Vehicle Stabilization 2 [Brian Erson] [Attitude]

  3. Mass Layout Conclusion: Mass difference represents a savings of >34.6 kg with 3-axis stabilized spacecraft * Conservative estimate minimally affected by stabilization method 3 [Brian Erson] [Attitude]

  4. Backup Slide 1 Attitude Control Mass Calculations: 3-axis Sun Sensors 0.7 Star Sensors 6.4 Reaction Wheels 6 H2O2 Thrusters 1 Propellant(H2O2)* 26 Total: 40.1 kg Spin Conical Scanner 6 Doppler Device 1 H2O2 Thrusters 1 Propellant(H202)* * 19.1 Total: 27.1 *Prop Mass Includes Lunar Descent 4 [Brian Erson] [Attitude]

  5. Backup Slide 2 • **H2O2 De-Saturation(DS) Mass Calculation: • DS of reaction wheels: • Estimate of DS maneuvers/day: 6 • Reaction wheel max torque: 0.03 N-m • H2O2 Thrust: 9.5 N/kg • Max Mission Length: 365 days • Total Mission DS H2O2 mass: • (365)(6)(1/9.5)(0.03) = 6.9 kg 5 [Brian Erson] [Attitude]

  6. Backup Slide 3 • Other Mass Calculations: • Power: • Masses based on posted Power Group Data • Mass of battery without solar cells based on assumption of >1.2 kW needed to power OTV • Communication: • 3 kg mass based on posted Com Group Data • Thermal: • 3 axis mass based on posted data • Spin stabilized Thermal Protection: • Assume 15 rpm • Mass = [(1/15(17.1))+4*] =~ 5 kg • *Estimated mass of standard thermal protection 6 [Brian Erson] [Attitude]

  7. References • http://sciencelinks.jp/j-east/article/200313/000020031303A0423712.php • http://cat.inist.fr/?aModele=afficheN&cpsidt=4572226 • http://cs.astrium.eads.net/sp/SpacecraftPropulsion/Propellant%20Tanks/Spin_Stabilised%20Tanks.html • http://www.peroxidepropulsion.com/article/5 • http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20050243594_2005246327.pdf • http://www.sandia.gov/ess/Publications/Conferences/2002/ESKRA%20-%20NiMetalHydride.pdf 7 [Brian Erson] [Attitude]

More Related