In orbital mechanics, the characteristic energy Cβ (pronounced βCβthreeβ) quantifies the excess kinetic energy a spacecraft has after escaping the gravity of its departure body. It is defined as the square of the hyperbolic excess velocity vβ, measured far from the planet.
The hyperbolic excess velocity results from the difference between the spacecraftβs departure speed v and the local escape speed vββc at the departure radius r. The escape speed depends on the bodyβs gravitational parameter ΞΌ and the distance from its centre.
Because Cβ is expressed in units of (kmΒ²/sΒ²), a positive value indicates a true escape trajectory, while a value of zero corresponds to a parabolic escape. Mission designers use Cβ to size launch vehicles and to compare interplanetary transfer options.
What is C3 energy in space?
How do you calculate hyperbolic excess velocity vβ?
What does C3 energy tell us about a spacecraft’s trajectory?
How is the gravitational parameter ΞΌ used in this calculation?
Can C3 energy be negative?
What is the unit of C3 energy?
How does C3 energy relate to delta-v requirements?
Results are for informational purposes only and do not constitute professional advice.
