Delta-v budget

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Delta-v budget (or velocity change budget) is a term used in astrodynamics and aerospace industry for velocity change (or delta-v) requirements for the various propulsive tasks and orbital maneuvers over phases of the space mission.

Sample delta-v budget will enumerate various classes of manoeuvres, delta-v per manoeuvre, number of manoeuvres required over the time of the mission.

In the absence of an atmosphere and landings where the ground is hit with some speed, the delta-v is the same for changes in orbit the other way around: gaining and losing speed cost an equal effort.

1 Launch/landing budget
2 Stationkeeping budget
3 Earth-Moon space budget
4 Interplanetary budget
5 Delta-vs around the Solar System
- 5.1 Abbreviations used
6 See also
7 References
8 External links

Launch to LEO — this not only requires an increase of velocity from 0 to 7.8 km/s, but also typically 1.5–2 km/s for atmospheric drag and gravity drag
Re-entry from LEO

Maneuver	Average delta-v per year [m/s]	Maximum per year [m/s]
Drag compensation in 400–500 km LEO	<25	<100
Drag compensation in 500–600 km LEO	< 5	< 25
Drag compensation in > 600 km LEO		< 7.5
Station-keeping in Geostationary orbit	50 – 55
Station-keeping in L1/L2	30 – 100
Station-keeping in Moon orbit	0 ^[1] – 400
Attitude control (3-axis)	2 – 6
Spin-up or despin	5 – 10
Stage booster separation	5 – 10
Momentum wheel unloading	2 – 6

Delta-v needed to move inside Earth Moon system (speeds lower then Escape velocity) in km/s

From\To	LEO-Ken	LEO-Eq	GEO	EML-1	EML-2	EML-4/5	LLO	Moon	C3
Earth	9.30 - 10.00
Low Earth Orbit (LEO-Ken)		4.24	4.33	3.77	3.43	3.97	4.04	5.93	3.22
Low Earth Orbit (LEO-Eq)	4.24		3.90	3.77	3.43	3.99	4.04	5.93	3.22
Geostationary Orbit (GEO)	2.06	1.63		1.38	1.47	1.71	2.05	3.92	1.30
Lagrangian point 1 (EML-1)	0.77	0.77	1.38		0.14	0.33	0.64	2.52	0.14
Lagrangian point 2 (EML-2)	0.33	0.33	1.47	0.14		0.34	0.64	2.52	0.14
Lagrangian point 4/5 (EML-4/5)	0.84	0.98	1.71	0.33	0.34		0.98	2.58	0.43
Low Lunar orbit (LLO)	1.31	1.31	2.05	0.64	0.65	0.98		1.87	1.40
Moon (Moon)	2.74	2.74	3.92	2.52	2.53	2.58	1.87		2.80
Earth Escape velocity (C3)	0.00	0.00	1.30	0.14	0.14	0.43	1.40	2.80

^[2] ^[3]

From	To	delta-v in km/s
Earth Escape velocity (C3)	Mars Transfer Orbit	0.6
Mars Transfer Orbit	Mars Capture Orbit	0.9
Mars Capture Orbit	Deimos Transfer Orbit	0.2
Deimos Transfer Orbit	Deimos surface	0.7
Deimos Transfer Orbit	Phobos Transfer Orbit	0.3
Phobos Transfer Orbit	Phobos surface	0.5
Mars Capture Orbit	Low Mars Orbit	1.4
Low Mars Orbit	Mars surface	4.1
Earth Escape velocity (C3)	Closest NEO Asteroids^[4]	0.8 - 2.0

According to Marsden and Ross, "The energy levels of the Sun-Earth L1 and L2 points differ from those of the Earth-Moon system by only 50 m/s (as measured by maneuver velocity)."^[5]

Delta-v's in km/s for various orbital manouevers using conventional rockets. Red arrows show where optional aerobraking can be performed in that particular direction, black numbers give delta-v in km/s that apply in either direction. Lower delta-v transfers than shown can often be achieved, but involve rare transfer windows or take significantly longer, see: fuzzy orbital transfers. Not all possible links are shown.

Delta-v's in km/s for various orbital manouevers^[6]^[7] using conventional rockets. Red arrows show where optional aerobraking can be performed in that particular direction, black numbers give delta-v in km/s that apply in either direction. Lower delta-v transfers than shown can often be achieved, but involve rare transfer windows or take significantly longer, see: fuzzy orbital transfers. Not all possible links are shown.

C3	Escape orbit
GEO	Geosynchronous orbit
GTO	Geostationary transfer orbit
L5	Earth-Moon fifth Lagrangian point
LEO	Low Earth orbit

Tsiolkovsky rocket equation

^ Frozen lunar orbits
^ list of delta-v
^ L2 Halo lunar orbit
^ NEO list
^ New methods in celestial mechanics and mission design. Bull. Amer. Math. Soc..
^ table of cislunar/mars delta-vs
^ cislunar delta-vs

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