AAE 450 Spring 2008 Scott Breitengross Jan 24, 2008 Trajectory group, delta V Delta V determination.

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Presentation transcript:

AAE 450 Spring 2008 Scott Breitengross Jan 24, 2008 Trajectory group, delta V Delta V determination

AAE 450 Spring 2008 Assumptions  All Juno 1* rocket inputs except mass  Mass = 5kg  Linear-Tangent Steering Law** (2 nd,3 rd stages only)  Kennedy Space Center Launch  Cd =.6 for entire launch Trajectory *Juno 1 inputs provided by Daniel Chua **Created by Amanda Briden and Junichi Kanehara

AAE 450 Spring 2008 ΔV Calculations Trajectory Future Work  Refine optimization code, include ΔV_steering  Multi-model comparison Launch TypeΔV_LEO (320 km) ΔV_GravΔV_DragΔV_Earth help 3-Stage Vertical Launch7715 m/s203 m/s10260 m/s410 m/s ΔV_Total* = m/s * From trajectory code created by Amanda Briden, Junichi Kanehara and Scott Breitengross

AAE 450 Spring 2008 References  Nesrin Sarigul-Klijn, Ph.D., Christopher Noel1, B.S., and Marti Sarigul-Klijn2, Ph.D. “Air Launching Earth- to-Orbit Vehicles: Delta V gains from Launch Conditions and Vehicle Aerodynamics” AIAA Journal AIAA January pp 3-7.  Wade, M. “Jupiter C,” 26 October 2005 [ Trajectory

AAE 450 Spring 2008 ΔV EquationsTrajectory