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Allen Guzik Trajectory

Allen Guzik Trajectory. Trajectory Optimization. 1/25. Delta V at Each Latitude. Initial Assessment Only looks at Velocity gained from the rotation of the Earth Assume Launched Vertically and directly East. Trajectory Optimization. 2/25. Location and Wind. Average Wind Velocities 4 m/s

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Allen Guzik Trajectory

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  1. Allen GuzikTrajectory AAE 450 Spring 2008 Trajectory Optimization 1/25

  2. Delta V at Each Latitude • Initial Assessment • Only looks at Velocity gained from the rotation of the Earth • Assume Launched Vertically and directly East AAE 450 Spring 2008 Trajectory Optimization 2/25

  3. Location and Wind • Average Wind Velocities • 4 m/s • 5 m/s • 7 m/s • Launch Locations • Federal • Commercial (Already Approved) • Proposed Map Provided From www.googgle.com, Edited by Allen Guzik AAE 450 Spring 2008 Trajectory Optimization 3/25

  4. Backup Slides • Wind Data Source: Brian Budzinski found the data. (http://www.windstuffnow.com/main/wind_charts.htm) AAE 450 Spring 2008 Trajectory Optimization 4/25

  5. Backup Slides • FAA Launch Locations Source: Kyle Donohue gathered the data (www. faa.gov) AAE 450 Spring 2008 Trajectory Optimization 5/25

  6. Backup Slides • Earth Help Basic Calculation AAE 450 Spring 2008 Trajectory Optimization 6/25

  7. Sample Airplane Launch Trajectory Code Can Now Predict Orbits From an Aircraft Launch Ascent Trajectory Launch Site Initial Height of 12,200 m AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 7/25

  8. ΔV Drag Comparison Purpose Attempt to validate how the trajectory code estimates drag Compare vehicle mass to Δv drag Compare drag from different launching configurations • Assumptions • Same initial steering law conditions • Orbit obtained is not considered • Same dimensions • Conclusions • Lighter Vehicle Increases Δv drag • Airplane and Balloon Launches decrease Δv drag • Trajectory Code handles drag appropriately, however the magnitude of the results need to be verified. AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 8/25

  9. Backup Slides Sample Affect of Atmosphere on Ascent Both Cases are for a GROUND LAUNCH With Atmosphere No Atmosphere AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 9/25

  10. Backup Slides Sample Balloon Ascent 30,500 m AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 10/25

  11. Ψ3 Effect on Trajectory • Purpose • Attempt to understand how changing steering angles affects the resulting trajectory. • Feasibility of spin stabilization of third stage • Will be used to know how to get into orbit for different vehicles. • Help write code for a better trajectory model prediction. • Aid in understanding other launch systems (i.e. plane and balloon) • Assumptions • Only Change Ψ3 • Hold Ψ1 and Ψ2 constant (-15˚, -30˚). • 3 Stage Vehicle (Juno I Inputs) • Ground launch • Payload (5 kg) AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 11/25

  12. Other Plots • Conclusions • Best Results occur at the previous steering angle • Spin stabilized third stage is feasible. AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 12/25

  13. Backup Slides AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 13/25

  14. Backup Slides AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 14/25

  15. Backup Slides AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 15/25

  16. Airplane Trajectory Results Bradley Ferris Junichi Kanehara Example Orbit Too Aggressive for D&C Conclusions - Good airplane launch trajectories are possible - Airplane launches can be cheaper than balloon launches - Unfortunately D&C cannot control trajectory’s prescribed path AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 16/25

  17. Ψ3 Error Sensitivity • Purpose • Find how sensitive the orbit is from an error in Ψ3 • D&C needs this for their controller • Model Used for Analysis • LB-SA-DA-DA • Conclusions • - Perigee is greatly effected by Ψ3 error (1˚ ~= 10% error) • - If there is error, best case is for the error to be more negative AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 17/25

  18. Backup Slides AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 18/25

  19. Backup Slides AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 19/25

  20. Presentation Slides: Ψ3 Effect on Trajectory and Resulting Orbit Angle of Ψ2 • Purpose • Attempt to understand how changing steering angles affects the resulting trajectory. • Feasibility of spin stabilization of third stage • Will be used to know how to get into orbit for different vehicles. • Help write code for a better trajectory model prediction. • Aid in understanding other launch systems (i.e. plane and balloon) • Assumptions • Only Change Ψ3 • Hold Ψ1 and Ψ2 constant (-15˚, -30˚). • 3 Stage Vehicle (Juno I Inputs) • Ground launch • Payload (5 kg) • Conclusions • Best Results occur at the previous steering angle • Spin stabilized third stage is feasible. AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 20/25

  21. Presentation Slides: Ψ3 Error Sensitivity • Purpose • Find how sensitive the orbit is from an error in Ψ3 • D&C needs this for their controller • Model Used for Analysis • LB-SA-DA-DA • Conclusions • - Perigee is greatly effected by Ψ3 error (1˚ ~= 10% error) • - If there is error, best case is for the error to be more negative AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 21/25

  22. Backup Slides (If needed) AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 22/25

  23. Backup Slides (If Needed) AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 23/25

  24. Backup Slides (If Needed) AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 24/25

  25. Backup Slides (If Needed) AAE 450 Spring 2008 AAE 450 Spring 2008 Trajectory Optimization 25/25

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