Brad Ferris 012408 Trajectory Analyst Modeling Thrust Assistance

Brad Ferris 01/24/08 Trajectory Analyst Modeling Thrust Assistance Provided by Daniel Chua AAE 450 Spring 2008 1

Modeling § Assumptions – Constant mass flow rate, exit velocity, exit pressure – No flow separation § New code structure – Call a function to get thrust at a given time – Apply Thrust Equation T = m_dot * ve + ( pe – pa) * Ae AAE 450 Spring 2008 Trajectory Optimization 2

Results § § Velocity at 320 km, circular orbit: 7. 715 km/s Velocity at 320 km w/o pressure thrust: 5. 296 km/s Velocity at 320 km w/ pressure thrust: 6. 911 km/s Velocity diff. due to pressure thrust: 1. 615 km/s Conclusions and Future Work § Code can now model thrust more accurately § Incorporate data from Propulsion group AAE 450 Spring 2008 Trajectory Optimization 3

Velocity Plots–Without Pressure Thrust Radial Velocity Tangential Velocity Blue – Simulation Velocity Green – Circular Orbit Velocity AAE 450 Spring 2008 Trajectory Optimization 4

Trajectory Plots–Without Pressure Thrust Altitude Trajectory Red – Simulation Altitude Green – Circular Orbit Altitude AAE 450 Spring 2008 Trajectory Optimization 5

Velocity Plots–With Pressure Thrust Radial Velocity Tangential Velocity Blue – Simulation Velocity Green – Circular Orbit Velocity AAE 450 Spring 2008 Trajectory Optimization 6

Trajectory Plots–With Pressure Thrust Altitude Trajectory Red – Simulation Altitude Green – Circular Orbit Altitude AAE 450 Spring 2008 Trajectory Optimization 7