Heliocentric frame — Sun at center · Planet orbiting · Spacecraft trajectory
Planet frame — hyperbolic trajectory
Spacecraft speed over time
Mission Design
Speed before flyby:—
Speed after flyby:—
ΔV gain:—
Deflection angle:—
Hyperbolic excess:—
Flyby energy gain:
ΔE = 2Vₚ·v∞·sin(δ/2)
where δ = deflection angle
δ = 2·arcsin(1/e) where e = eccentricity
Oberth effect: Burn at periapsis for maximum ΔE (v² is highest there).
ΔE = 2Vₚ·v∞·sin(δ/2)
where δ = deflection angle
δ = 2·arcsin(1/e) where e = eccentricity
Oberth effect: Burn at periapsis for maximum ΔE (v² is highest there).