estimate_rocket_sizing
Calculate propellant mass, dry mass, total mass, and structural dimensions for a rocket given target altitude, payload mass, propellant type, and design margin.
Instructions
Estimate rocket sizing requirements for target altitude and payload.
Args: target_altitude_m: Target altitude in meters payload_mass_kg: Payload mass in kg propellant_type: Propellant type ('solid' or 'liquid') design_margin: Design margin factor
Returns: JSON string with sizing estimates including propellant mass, dry mass, total mass, and structural dimensions.
Raises: No exceptions are raised directly; errors are returned as formatted strings.
Note: Sizing uses the Tsiolkovsky rocket equation (ideal rocket equation): delta_V = Isp * g0 * ln(m_initial / m_final) Rearranged to solve for propellant mass: m_prop = m_final * (exp(delta_V / (Isp * g0)) - 1) where Isp is specific impulse and g0 = 9.80665 m/s^2.
Input Schema
| Name | Required | Description | Default |
|---|---|---|---|
| target_altitude_m | Yes | ||
| payload_mass_kg | Yes | ||
| propellant_type | No | solid | |
| design_margin | No |
Output Schema
| Name | Required | Description | Default |
|---|---|---|---|
| result | Yes |