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

AAE 450 Spring 2008 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 * v e + ( p e – p a ) * A e Trajectory Optimization 2

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

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

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

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

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