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In astrodynamics, the term delta-v, literally "change in velocity" (see symbol delta), has a specific meaning: it is a scalar which takes units of speed that measures the amount of "effort" needed to carry out an orbital maneuver, i.e., to change from one trajectory to another.

- $Delta\{v\}\; =\; int\_\{t\_0\}^\{t\_1\}\; \{frac$
{m}}, dt>

Where

- $T$ is the instantaneous thrust

- $m$ is the instantaneous mass

In the absence of external forces, and when thrust is applied in a constant direction this simplifies to:

- $=\; int\_\{t\_0\}^\{t\_1\}$
, dt = | {v}_1 - {v}_0 |>

which is simply the magnitude of the change in velocity.

For rockets the 'absence of external forces' usually is taken to mean the absence of atmospheric drag as well as the absence of aerostatic back pressure on the nozzle and hence the vacuum Isp is used for calculating the vehicle's delta-v capacity via the rocket equation, and the costs for the atmospheric losses are rolled into the delta-v budget when dealing with launches from a planetary surface.

When designing a trajectory, delta-v is used as an indicator of how much propellant will be required. Propellant usage is an exponential function of delta-v in accordance with the rocket equation.

It is not possible to determine delta-v requirements from conservation of energy by considering only the total energy of the vehicle in the initial and final orbits since the propellant carries energy away in the exhaust (see also below); as well as propellant being used up in a burn. For example, most spacecraft are launched in an orbit with inclination fairly near to the latitude at the launch site, to take advantage of the earth's rotational surface speed. If it is necessary, for mission-based reasons, to put the spacecraft in an orbit of different inclination, a substantial delta-v is required, though the specific kinetic and potential energies in the final orbit and the initial orbit are equal.

When rocket thrust is applied in short bursts the other sources of acceleration may be negligible, and the magnitude of the velocity change of one burst may be simply approximated by the delta-v. The total delta-v to be applied can then simply be found by addition of each of the delta-vs needed at the discrete burns, even though between bursts the magnitude and direction of the velocity changes due to gravity, e.g. in an elliptic orbit.

For examples of calculating Delta-v, see Hohmann transfer orbit, gravitational slingshot, and Interplanetary Superhighway. It is also notable that large thrust can reduce gravity drag.

Delta-v is also required to keep satellites in orbit and is expended in propulsive orbital stationkeeping maneuvers. Since the propellant load on most satellites cannot be replenished, the amount of propellant initially loaded on a satellite may well determine its useful lifetime.

See also .

Due to the relative positions of planets changing over time, different delta-vs are required at different launch dates. A diagram that shows the required delta-v plotted against time is sometimes called a Porkchop plot. Such a diagram is useful since it enables calculation of a launch window, since launch should only occur when the mission is within the capabilities of the vehicle to be employed.

Delta-v is typically provided by the thrust of a rocket engine, but can be created by other reaction engines. The time-rate of change of delta-v is the magnitude of the acceleration caused by the engines, i.e., the thrust per total vehicle mass. The actual acceleration vector would be found by adding thrust per mass on to the gravity vector and the vectors representing any other forces acting on the object.

The total delta-v needed is a good starting point for early design decisions since consideration of the added complexities are deferred to later times in the design process.

The rocket equation shows that the required amount of propellant dramatically increases, with increasing delta-v. Therefore in modern spacecraft propulsion systems considerable study is put into reducing the total delta-v needed for a given spaceflight, as well as designing spacecraft that are capable of producing a large delta-v.

Increasing the Delta-v provided by a propulsion system can be achieved by:

- staging
- increasing specific impulse
- improving mass fraction

Additionally raising thrust levels (when close to a gravitating body) can sometimes improve delta-v.

C3 | Escape orbit |

GEO | Geosynchronous orbit |

GTO | Geostationary transfer orbit |

L5 | Earth-Moon fifth Lagrangian point |

LEO | Low Earth orbit |

- Delta-v budget
- Gravity drag
- Orbital maneuver
- Orbital stationkeeping
- Spacecraft propulsion
- Specific impulse
- Tsiolkovsky rocket equation

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Last updated on Sunday August 31, 2008 at 08:30:19 PDT (GMT -0700)

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This article is licensed under the GNU Free Documentation License.

Last updated on Sunday August 31, 2008 at 08:30:19 PDT (GMT -0700)

View this article at Wikipedia.org - Edit this article at Wikipedia.org - Donate to the Wikimedia Foundation

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