Struct RocketGeometry 

pub struct RocketGeometry {
    pub nose: NoseCone,
    pub tube: BodyTube,
    pub fins: FinSet,
    pub boat_tail: Option<BoatTail>,
    pub roughness_m: f64,
}

A slender rocket: nose cone, body tube, fin set and an optional conical boat-tail.

Fields

nose: NoseCone

Nose cone.

tube: BodyTube

Cylindrical body tube.

fins: FinSet

Aft fin set.

boat_tail: Option<BoatTail>

Optional conical boat-tail aft of the fins.

roughness_m: f64

Roughness height in metres (default 20 µm, painted surface).

Implementations

impl RocketGeometry

pub fn new(nose: NoseCone, tube: BodyTube, fins: impl Into<FinSet>) -> Self

Build with the default painted-surface roughness (20 µm).

pub fn with_roughness(self, roughness_m: f64) -> Self

Set the roughness height in metres.

pub fn with_boat_tail(self, boat_tail: BoatTail) -> Result<Self>

Attach a conical boat-tail at the aft end of the tube. Its forward diameter must match the tube and its aft diameter must be smaller.

pub fn total_length_m(&self) -> f64

Total aerodynamic length (nose + tube + boat-tail).

pub fn max_diameter_m(&self) -> f64

Largest body diameter (nose base or tube).

pub fn ref_area_m2(&self) -> f64

Reference area, π/4·d² of the largest diameter.

pub fn mass_properties( &self, nose_kg: f64, tube_kg: f64, fins_kg: f64, casing: Option<(f64, f64)>, ) -> MassProperties

Combine component masses with the geometry’s component CGs into a dry CG and a pitch-inertia estimate about that CG.

The nose is a solid of revolution (numerically integrated), the tube a thin-walled cylinder, and the fins and optional motor casing point masses; evenly spaced fins add n/2 · m · (r_body + y_cg)² for their radial offset. casing is (mass_kg, CG from the nose tip).

pub fn mass_properties_with_boat( &self, nose_kg: f64, tube_kg: f64, fins_kg: f64, boat_kg: Option<f64>, casing: Option<(f64, f64)>, ) -> MassProperties

mass_properties with an optional boat-tail shell mass (treated as a thin-walled frustum).

pub fn analyze(&self) -> AeroAnalysis

Full analysis. Mach samples at 0.0, 0.2, 0.4, 0.6, 0.8, 0.9, 1.0, 1.1, 1.3, 1.5, 2.0 and 3.0, computed across the transonic and supersonic regimes (no clamp).

Trait Implementations

impl Clone for RocketGeometry

fn clone(&self) -> Self

Returns a duplicate of the value.

fn clone_from(&mut self, source: &Self)

Performs copy-assignment from source.

impl Copy for RocketGeometry

impl Debug for RocketGeometry

fn fmt(&self, f: &mut Formatter<'_>) -> Result

Formats the value using the given formatter.