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In astrodynamics and aerospace, a delta-v budget is an estimate of the total change in velocity (delta- v) required for a space mission. It is calculated as the sum of the delta-v required to perform each propulsive maneuver needed during the mission.
- ∆V Budgets for visiting Phobos and Deimos
- Highly Elliptical Staging Orbit
- Min ∆V option for Phobos if aerobrake is not available
- ∆V requirements by transfer option
Problem statement: Upon arrival at Mars, what is the optimal strategy for visiting Phobos, Deimos or both moons on rendezvous and return missions? What are the high-level propulsive ∆V requirements? How beneficial is the use of aerobraking? Applications to both robotic and human missions Phobos and Deimos’ near-circular and equatorial orbits enable...
• Represents an initial orbit a spacecraft would enter through aerocapture after an interplanetary transfer from Earth with Orbital parameters used for periapsis close to Mars’ atmosphere and an arbitrarily high staging orbit in this study apoapsis. • Altitude at Periapsis Independent of heliocentric transfer trajectory from Earth (short-stay, long...
Min ∆V option for Deimos regardless of aerobrake capability
Min ∆V option for Phobos if aerobrake is available
- Cyrus Foster
- 2011
Mar 27, 2024 · The delta-v budget is the total amount of delta-v that a spacecraft must have in order to successfully complete its mission. In simpler terms, it is the fuel required to get a spacecraft from point A to point B in space.
To get to the surface of Mars (given a launch with Mars at conjunction), a Delta-V of 4.5 km/s is required — 4.1 km/s to get to Mars, 0.1 km/s for post-aerocapture orbit adjustments, and 0.4 km/s to slow from post-atmospheric-entry speeds.
Aerojet Rocketdyne (AR) has been analyzing ballistic transfers for Earth to Mars for roundtrip missions over an even grid of departure dates and transfer times during those opportunities.
A science fiction writer using 6 km/s for Earth orbit to Mars orbit has a needlessly high delta V budget. There are capture orbits that take much less delta V to enter and exit. By capture orbit I mean a periapsis as low as possible and apoapsis as high as possible.
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This means that the cost of a long stay human Mars mission is estimated at roughly $300 to $600 billion. The higher cost allows an earlier landing in 2033 but the more restricted budget will postpone it to past 2050.
