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| [[File:Porkchop plot.gif|thumb|right| Representative porkchop plot for the 2005 Mars launch opportunity. The horizontal axis is departure dates, and the vertical axis is arrival dates. A given contour represents a constant C<sub>3</sub> solution. The center of the porkchop is the optimal solution for the lowest C<sub>3</sub>.]]
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| A '''porkchop plot''' (also '''pork-chop plot''') is a chart that shows contours of equal [[characteristic energy]] (C<sub>3</sub>) against combinations of launch date and arrival date for a particular interplanetary flight.<ref name="Goldman">{{cite web
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| |author=Goldman, Elliot
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| |url=http://ccar.colorado.edu/asen5050/projects/projects_2003/goldman/
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| |title=Launch Window Optimization: The 2005 Mars Reconnaissance Orbiter (MRO) Mission
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| |publisher=[[Colorado Center for Astrodynamics Research]]
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| |accessdate=2007-12-30}}</ref>
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| By examining the results of the porkchop plot, engineers can determine when launch opportunities exist (a ''[[launch window]]'') that is compatible with the capabilities of a particular spacecraft.<ref>[http://mars.jpl.nasa.gov/spotlight/porkchopAll.html "Porkchop" is the First Menu Item on a Trip to Mars], [[NASA]]. Accessed December 30, 2007.</ref> A given contour, called a '''porkchop curve''', represents constant C<sub>3</sub>, and the center of the porkchop the optimal minimum C<sub>3</sub>. The [[orbital elements]] of the solution, where the fixed values are the departure date, the arrival date, and the length of the flight, were first solved mathematically in 1761 by [[Johann Heinrich Lambert]], and the equation is generally known as ''[[Lambert's problem]]'' (or ''theorem'').<ref name="Goldman"/>
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| == Math ==
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| The general form of ''Characteristic Energy'' can be computed as:
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| :<math>C_3=v_{\infty}^2\,\!</math>
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| where
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| :<math>v_{\infty} \,</math> is the [[Orbital speed|orbital velocity]] when the orbital distance tends to infinity. Note that, since the kinetic energy is <math>\frac{1}{2}mv^2</math>, C<sub>3</sub> is in fact equal to twice the magnitude of the [[specific orbital energy]] (<math>\epsilon</math>) of the escaping object.
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| == Use ==
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| For the [[Voyager program]], engineers at [[JPL]] plotted around 10,000 potential trajectories using porkchop plots, from which they selected around 100 that were optimal for the mission objectives. The plots allowed them to reduce or eliminate planetary encounters taking place over the [[Thanksgiving]] or [[Christmas]] holidays, and to plan the completion of the mission's primary goals before the end of the [[fiscal year]] 1981.<ref>{{cite book
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| |url=http://books.google.com/books?id=UYlfQvFHn7MC&pg=PA27&dq=pork.chop+curve&ie=ISO-8859-1&sig=X9Wj1DIPV3L3xQv72XdQvt_CHzA#PPA21,M1
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| |title=Into the Black: JPL and the American Space Program, 1976-2004
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| |author=Peter J. Westwick
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| |year=2007
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| |publisher=[[Yale University Press]]
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| |isbn=0-300-11075-8}}</ref>
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| ==See also==
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| * [[Launch window]]
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| * [[Specific orbital energy]]
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| * [[Orbit]]
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| * [[Parabolic trajectory]]
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| * [[Hyperbolic trajectory]]
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| ==References==
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| {{Reflist}}
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| ==External links==
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| *[http://marsprogram.jpl.nasa.gov/spotlight/porkchopAll.html JPL Introduction to Porkchop plots]
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| [[Category:Plots (graphics)]]
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| [[Category:Astrodynamics]]
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| {{spacecraft-stub}}
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I am Oscar and I completely dig that title. Bookkeeping is her working day occupation now. For a while she's been in South Dakota. One of the issues he enjoys most is ice skating but he is having difficulties to discover time for it.
Feel free to surf to my web blog :: std testing at home