1AAE 450 Spring 2008 Scott Breitengross Mar 27, 2008 Trajectory group, Delta V, Saturn V, Feasability Determination, 1 kg Final Design Final Presentation

2AAE 450 Spring g Balloon Launch Parameters Trajectory Tables generated from trajectory code output data Orbit Parameters VariableValueUnits Periapsis * km Apoapsis * km Eccentricity Inclination28.5deg Semi-Major Axis km Period sec *Values are from the surface of the Earth. ΔV Breakdown VariableValueUnitsPercent ΔV total 9313m/s -- ΔV drag 6m/s ΔV gravity 1991m/s ΔV Earth assist 411m/s ΔV leo 7727m/s 82.97

3 ΔV Equations  Where μ is the gravitational constant and R p is the Radius of the periapsis from the center of the earth  Where D(t) is the drag profile and m(t) is the mass profile  Where g(t) is the gravity profile and γ (t) is the flight path angle  Where R e is the radius of the Earth, φ is the launch latitude, and t d is time in a day in seconds *all equations generated in Space Propulsion, Analysis and Design Book.

4 200g Additional Data Coefficients for Steering Law VariableValueUnits a e-1 -- b e1 -- a e-3 -- b e0 -- a e b e-1 -- numbers refer to stage number Orbit and model generated by trajectory code

5  Where T(t) is the Thrust profile and m(t) is the mass profile References: Humble, Ronald W., Henry, Gary N., Larson, Wiley J., Space Propulsion Analysis and Design. The McGraw-Hill Companies Inc. St. Louis, Missouri, 1995.