Hyperbolic trajectory

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In astrodynamics or celestial mechanics a hyperbolic trajectory is an orbit with the eccentricity greater than 1. Under standard assumptions a body traveling along this trajectory will coast to infinity, arriving there with hyperbolic excess velocity relative to the central body. Similarly to parabolic trajectory all hyperbolic trajectories are also escape trajectories. Specific energy of hyperbolic trajectory orbit is positive.

1 Hyperbolic excess velocity
2 Velocity
3 Energy
4 See also
5 External links

[edit] Hyperbolic excess velocity

Under standard assumptions the body traveling along hyperbolic trajectory will attain in infinity an orbital velocity called hyperbolic excess velocity ( $v_\infty\,\!$ ) that can be computed as:

$v_\infty=\sqrt{\mu\over{a}}\,\!$

where:

$\mu\,\!$ is standard gravitational parameter,
$a\,\!$ is length of semi-major axis of orbit's hyperbola.

The hyperbolic excess velocity is related to the specific orbital energy or characteristic energy by

$2\epsilon=C_3=v_{\infty}^2\,\!$

[edit] Velocity

Under standard assumptions the orbital velocity ( $v\,$ ) of a body traveling along hyperbolic trajectory can be computed as:

$v=\sqrt{2\mu\left({1\over{r}}+{1\over{2a}}\right)}$

where:

$\mu\,$ is standard gravitational parameter,
$r\,$ is radial distance of orbiting body from central body,
$a\,\!$ is length of semi-major axis.

Under standard assumptions, at any position in the orbit the following relation holds for orbital velocity ( $v\,$ ), local escape velocity( ${v_{esc}}\,$ ) and hyperbolic excess velocity ( $v_\infty\,\!$ ):

$v^2={v_{esc}}^2+{v_\infty}^2$

Note that this means that a relatively small extra delta-v above that needed to accelerate to the escape speed, results in a relatively large speed at infinity.

[edit] Energy

Under standard assumptions, specific orbital energy ( $\epsilon\,$ ) of a hyperbolic trajectory is greater than zero and the orbital energy conservation equation for this kind of trajectory takes form:

$\epsilon={v^2\over2}-{\mu\over{r}}={\mu\over{2a}}$

where:

$v\,$ is orbital velocity of orbiting body,
$r\,$ is radial distance of orbiting body from central body,
$a\,$ is length of semi-major axis,
$\mu\,$ is standard gravitational parameter.

[edit] See also

[edit] External links

v • d • e Orbits
Orbit types	Box orbit • Circular orbit • Ecliptic orbit • Elliptic orbit • Highly Elliptical Orbit • Graveyard orbit • Hyperbolic trajectory • Inclined orbit • Osculating orbit • Parabolic trajectory • Capture orbit • Escape orbit • Semi-synchronous orbit • Subsynchronous orbit • Synchronous orbit
Earth-centered orbits	Geosynchronous orbit • Geostationary orbit • Sun-synchronous orbit • Low Earth orbit • Medium Earth Orbit • Molniya orbit • Near equatorial orbit • Orbit of the Moon • Polar orbit • Polar sun synchronous orbit • Tundra orbit
Other orbits	Areosynchronous orbit • Areostationary orbit • Lissajous orbit • Lunar orbit • Heliocentric orbit • Heliosynchronous orbit
Orbital elements	Inclination ( $i\,\!$ ) • Longitude of the ascending node ( $\Omega\,\!$ ) • Eccentricity ( $e\,\!$ ) • Argument of periapsis ( $\omega\,\!$ ) • Semi-major axis ( $a\,\!$ ) • Mean anomaly at epoch ( $M_o\,\!$ )
Other orbital parameters	True anomaly ( $v\,$ ) • Semi-minor axis ( $b\,$ ) • Linear eccentricity ( $\epsilon\,$ ) • Eccentric anomaly ( $E\,$ ) • Mean longitude ( $L\,$ ) • True longitude ( $l\,$ ) • Orbital period ( $T\,$ )
Orbital maneuvers	Bi-elliptic transfer • Geostationary transfer orbit • Gravitational slingshot • Hohmann transfer orbit • Orbital inclination change • Orbit phasing • Space rendezvous
Other orbital mechanics topics	Apsis • Celestial coordinate system • Delta-v budget • Epoch • Ephemeris • Equatorial coordinate system • Ground track • Interplanetary Transport Network • Kepler's laws of planetary motion • Lagrangian point • List of orbits • n-body problem • Orbit equation • Orbital state vectors • Retrograde and direct motion • Specific orbital energy • Specific relative angular momentum