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. The specific energy of a hyperbolic trajectory orbit is positive.

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

See also: Characteristic energy

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

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

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, always a negative number for hyperbolas.

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.

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.

v • d • e

Orbits

Types

General	Box · Circular · Non-inclined · Elliptic (Highly Elliptical) · Graveyard · Hyperbolic trajectory · Inclined · Osculating · Parabolic trajectory · Capture · Escape · Semi-synchronous · Subsynchronous · Synchronous · Parking
Geocentric	Geosynchronous · Geostationary · Sun-synchronous · Low Earth · Medium Earth · Molniya · Near equatorial · Moon · Polar · Tundra
Other	Areosynchronous · Areostationary · Halo · Lissajous · Lunar · Heliocentric · Heliosynchronous