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Delta-v Map

Ki kantite chanjman vitès li pran pou deplase ant tè a, orbit, Lune, Mars ak asteroyid.

ESO/S. Guisard (www.eso.org/~sguisard) (CC BY 4.0)

Delta-v Map

Ki kantite chanjman vitès li pran pou deplase ant tè a, orbit, Lune, Mars ak asteroyid. 9.4 / 0 2.45 1.48 3.22 3.13 0.82 1.63 3.61 2.09 0 / 4.1 4.11 9.48 Surface Orbita tè ba(200 km) Orbit transferegeostationary Orbitgeostationary Escape Transfè nan Lune Orbita lunè ba(100 km) Surface Lune Transfè nan Mars Orbita Mars (300km) Mars surface Near-Earthasteroid (Bennu) Orbita Ceres
Total delta-v

Eta

    Valè yo se yon sèl-wout, manoeuvres impulsif ideyal si pa te make tankou tipik. Misyon reyèl ajoute pèt ak chanjman plan.

    Tablè done (altènatif tèks)
    Tout lyen sou kat la
    Soti nanTo→←Kijan li te fèt
    SurfaceOrbita tè ba (200 km) 9.4 km/s 0 km/s (ka itilize aerobraking) typical (publi): Delta-v budget (Wikipedia, with its cited references), typical values including lossesLansman nan orbit: sou 7.8 km / s nan vitès orbital plis pèt yo nan gravite ak rezistans lè a.
    Orbita tè ba (200 km)Orbit transfere geostationary 2.45 km/s 2.45 km/s (ka itilize aerobraking) Kalkile (ideal): Hohmann perigee burn, 200 km to 35,786 km altitude, equatorial
    Orbit transfere geostationaryOrbit geostationary 1.48 km/s 1.48 km/s Kalkile (ideal): Hohmann apogee burn, no plane changeSi yon satelit lanse soti nan yon sit ki lwen equator la, li pral chanje ang orbit li ak kèk santèn mèt pa segonn.
    Orbita tè ba (200 km)Escape 3.22 km/s 3.22 km/s (ka itilize aerobraking) Kalkile (ideal): Escape speed minus circular speed at 200 km
    Orbita tè ba (200 km)Transfè nan Lune 3.13 km/s 3.13 km/s (ka itilize aerobraking) Kalkile (ideal): Raise apogee to the Moon's mean distance
    Transfè nan LuneOrbita lunè ba (100 km) 0.82 km/s 0.82 km/s Kalkile (ideal): Patched conic capture into a 100 km lunar orbit
    Orbita lunè ba (100 km)Surface Lune 1.63 km/s 1.63 km/s Kalkile (ideal): Circular speed at 100 km (ideal, no gravity losses; real landings need more)
    Orbita tè ba (200 km)Transfè nan Mars 3.61 km/s 3.61 km/s (ka itilize aerobraking) Kalkile (ideal): Earth-Mars Hohmann departure from 200 km, Oberth effect included
    Transfè nan MarsOrbita Mars (300 km) 2.09 km/s (ka itilize aerobraking) 2.09 km/s Kalkile (ideal): Capture into a 300 km circular Mars orbit
    Orbita Mars (300 km)Mars surface 0 km/s (ka itilize aerobraking) 4.1 km/s typical (publi): Delta-v budget (Wikipedia, with its cited references), typical values including lossesAteri a itilize majorite fwa atmosfè a (kouch chalè ak parachutes); mòn lan tounen nan orbit se valè ki pi komen.
    Orbita tè ba (200 km)Near-Earth asteroid (Bennu) 4.11 km/s 4.11 km/s (ka itilize aerobraking) Kalkile (ideal): Heliocentric Hohmann 1 au to Bennu's semi-major axis, coplanar (ignores its 6 degree inclination and its eccentricity); departure from 200 km LEO
    Orbita tè ba (200 km)Orbita Ceres 9.48 km/s 9.48 km/s (ka itilize aerobraking) Kalkile (ideal): Heliocentric Hohmann 1 au to Ceres, coplanar (ignores its 10.6 degree inclination); departure from 200 km LEO, capture into a 200 km Ceres orbit

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