rocket_3dof_trajectory
Calculate a rocket's 3DOF trajectory using numerical integration. Input geometry and launch conditions to obtain altitude, velocity, and performance metrics.
Instructions
Calculate 3DOF rocket trajectory using numerical integration.
Args: rocket_geometry: Rocket geometry parameters launch_conditions: Launch conditions (launch_angle_deg, launch_site, etc.) simulation_options: Optional simulation settings
Returns: Formatted string with trajectory analysis results including max altitude, max velocity, Mach number, apogee time, burnout time, max-Q, total impulse, and specific impulse.
Raises: No exceptions are raised directly; errors are returned as formatted strings. ImportError is caught when rocketry packages are not installed.
Note: The 3DOF equations of motion integrate: dv/dt = (T - D) / m - g * sin(gamma) (along velocity) dgamma/dt = -(g / v) * cos(gamma) (flight path angle) dx/dt = v * cos(gamma) (downrange) dh/dt = v * sin(gamma) (altitude) where T is thrust, D = 0.5 * rho(h) * v^2 * Cd * A_ref is aerodynamic drag with altitude-dependent density, m is instantaneous mass (decreasing during burn), and gamma is the flight path angle. Integration uses a 4th-order Runge-Kutta (RK4) scheme for numerical stability.
Input Schema
| Name | Required | Description | Default |
|---|---|---|---|
| rocket_geometry | Yes | ||
| launch_conditions | Yes | ||
| simulation_options | No |
Output Schema
| Name | Required | Description | Default |
|---|---|---|---|
| result | Yes |