Daedalus 3 Flap Design
States
Dynamics
Constraint
Dynamics equations for Daedalus 3. Y-axis symmetry is assumed.

- Own the aerodynamic flap design for Daedalus 3, a rocket-shaped bellyflop-to-vertical-landing drone at Parsec Rocketry, with responsibility for flap sizing, placement, hinge geometry, and the control-authority spec for the engine-off descent.
- Derived a 4-state nonlinear coupled dynamics model of the bellyflop maneuver (vertical position, vertical velocity, pitch, pitch rate), with flap and body aerodynamic normal- and axial-force terms driving both translation and rotation.
- Identified terminal velocity as the primary design driver, since arrest distance under a T/W near 1.15 scales with the square of terminal velocity, making belly-down drag maximization the core flap-sizing objective.
- Built a nested optimization in Python (scipy) that sweeps hardware variables (forward and aft flap areas, moment arms, hinge offset) around an inner control-schedule tuning loop, integrating the vehicle dynamics via segmented solve_ivp calls with phase-transition events.
- Showed that the full maneuver requires roughly 400 to 600 m of altitude, from a 30 m/s entry up to a terminal-velocity entry, establishing that a complete bellyflop from a self-propelled launch is impractical.








