Struct RocketGeometry 

pub struct RocketGeometry {
    pub nose: NoseCone,
    pub tube: BodyTube,
    pub fins: TrapezoidalFins,
    pub roughness_m: f64,
}

The complete slender geometry.

Fields

nose: NoseCone

Nose cone.

tube: BodyTube

Cylindrical body tube.

fins: TrapezoidalFins

Aft trapezoidal fin set.

roughness_m: f64

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

Implementations

impl RocketGeometry

pub fn new(nose: NoseCone, tube: BodyTube, fins: TrapezoidalFins) -> 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 total_length_m(&self) -> f64

Total aerodynamic length (nose + tube).

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 analyze(&self) -> AeroAnalysis

Full analysis. Mach samples at 0.0, 0.2, 0.4, 0.6, 0.8, 1.0, and 3.0; the last point simply repeats the Mach-1 values (subsonic 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.