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How far is Mars from Earth, and how long would a trip with people take?

Research question: How far is Mars from Earth and how long does a crewed trip take with today's rockets and launch windows?

The records show Mars and Earth come closest at about 54 to 56 million km and can be as far apart as 401 million km 346. Earth-Mars launch windows recur every 26 months, and each launch period lasts only a few weeks 1419. With chemical propulsion, a crewed trip takes at least about 7 to 10 months, and a Hohmann transfer takes about 9 months of travel 217. The minimum-energy crewed round trip totals about 34 months, and shorter 400 to 450 day round trips need significantly more energy 1821. The 70 to 90 day transit figure applies to nuclear thermal propulsion, not today's chemical rockets, and the newest facts date from 2026, which matches the current date 58.

Checked 2026-10-19. Only documented and supported facts are used.
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Sources

[1] supported
Mars's orbit has a semimajor axis of 1.524 astronomical units, about 228 million km from the Sun.
"Mars has an orbit with a semimajor axis of 1.524 astronomical units (228 million km) (12.673 light minutes)"
Orbit of Mars
[2] supported
Crewed Mars missions using chemical propulsion take around 7-10 months at a minimum.
"However, crewed missions to Mars using chemical propulsion take around 7-10 months at a minimum, posing significant challenges for crew health and mission reliability."
Feasibility and Parametric Analysis of Nuclear Thermal Propulsion for Crewed Earth-Mars Transfers (2026)
[3] supported
The distance between Mars and Earth at closest approach varies between about 54 and 103 million km because of the planets' elliptical orbits.
"The distance at close approach varies between about 54 and 103 million km (34 and 64 million mi) due to the planets' elliptical orbits, which causes comparable variation in angular size ."
Mars
[4] supported
The closest distance between Mars and Earth is about 56 million km.
"56 million km is the closest distance between Mars and Earth"
Orbit of Mars
[5] supported
Nuclear Thermal Propulsion could reduce crewed Mars transit to 70-90 days during the optimal launch window.
"These results show that NTP can feasibly reduce travel times to 70-90 days during the optimal launch window while achieving a hyperbolic excess velocity, or V-infinity of 10 km/s."
Feasibility and Parametric Analysis of Nuclear Thermal Propulsion for Crewed Earth-Mars Transfers (2026)
[6] supported
At their furthest, Mars and Earth can be as far as 401 million km apart.
"At their furthest Mars and Earth can be as far as 401 million km (249 million mi) apart."
Mars
[7] supported
In 2003 the minimum Earth-Mars distance was 55.76 million km, closer than any such encounter in almost 60,000 years.
"in 2003 the minimum distance was 55.76 million km, nearer than any such encounter in almost 60,000 years (57,617 BC)"
Orbit of Mars
[8] supported
Nuclear Thermal Propulsion offers a significant reduction in transit time compared with chemical propulsion while remaining consistent with current reactor technology.
"NTP offers a significant reduction in transit time when compared to chemical propulsion but remains consistent with current reactor technology and demonstrated technological advancements."
Feasibility and Parametric Analysis of Nuclear Thermal Propulsion for Crewed Earth-Mars Transfers (2026)
[9] supported
Mars comes into opposition from Earth, the close-approach alignment used for launch timing, about every 2.1 years.
"Mars comes into opposition from Earth every 2.1 years."
Mars
[10] supported
Earth-Mars distance at opposition ranges from about 0.68 AU when Mars is near aphelion to about 0.37 AU when Mars is near perihelion.
"Oppositions range from about 0.68 AU when Mars is near aphelion to only about 0.37 AU when Mars is near perihelion."
Orbit of Mars
[11] supported
The average time between successive Mars oppositions (its synodic period) is about 780 days, but the gap can range from 764 to 812 days.
"The average time between the successive oppositions of Mars, its synodic period, is 780 days; but the number of days between successive oppositions can range from 764 to 812."
Mars
[12] supported
The Earth-Mars synodic period, which sets the recurring cycle of close oppositions and favorable launch timing, is 780 days.
"during that 780-day synodic period"
Orbit of Mars
[13] supported
The delta-v needed to transfer between Mars and Earth is the second lowest of any planet for Earth, which is relevant to trip energy requirements.
"The gravitational potential difference and thus the delta-v needed to transfer between Mars and Earth is the second lowest for Earth."
Mars
[14] supported
For Earth-Mars missions using a Hohmann transfer, launch windows occur every 26 months.
"For a mission between Earth and Mars , for example, these launch windows occur every 26 months."
Hohmann transfer orbit
[15] supported
The lowest-energy way to reach Mars is a Hohmann transfer orbit, which takes roughly 9 months one way, plus about 500 days waiting at Mars for the return window.
"The lowest energy transfer to Mars is a Hohmann transfer orbit , a conjunction class mission which would involve a roughly 9-month travel time from Earth to Mars"
Human mission to Mars
[16] supported
For a Mars trip using a simple low-energy Hohmann transfer, launch opportunities recur according to the synodic period, which is 780 days (about 2.1 years) for Mars.
"for example, in the case of Mars, the period is 780 days (2.1 years)."
Launch window
[17] supported
A Hohmann transfer from Earth to Mars takes about 9 months of travel time.
"A Hohmann transfer orbit also determines a fixed time required to travel between the starting and destination points; for an Earth-Mars journey this travel time is about 9 months."
Hohmann transfer orbit
[18] supported
The minimum-energy Hohmann-type crewed round trip described in the document totals about 34 months.
"This would be a 34-month trip."
Human mission to Mars
[19] supported
Mars launch periods occur roughly every 26 months and last only a few weeks each time.
"a few weeks every 26 months (e.g. Mars launch periods )"
Launch window
[20] supported
Low-energy transfers that account for real engine thrust limits and use the gravity wells of both planets can be more fuel efficient than Hohmann transfers.
"They are also often used for these situations, but low-energy transfers which take into account the thrust limitations of real engines, and take advantage of the gravity wells of both planets can be more fuel efficient."
Hohmann transfer orbit
[21] supported
Shorter Mars mission plans have round-trip flight times of 400 to 450 days, though they require significantly higher energy.
"Shorter Mars mission plans have round-trip flight times of 400 to 450 days"
Human mission to Mars
[22] supported
A fast 245-day (about 8-month) round-trip Mars mission could be possible using on-orbit staging.
"A fast Mars mission of 245 days (8.0 months) round trip could be possible with on-orbit staging."
Human mission to Mars
[23] supported
The 'opposition' class mission, which NASA has pushed toward to reduce astronaut risk, has a short 30-day Martian stay and an overall length of two years.
"NASA has pushed towards higher delta-V “opposition” class missions, which consist of a short 30-day Martian stay and an overall length of two years."
Analysis of electric propulsion propellant type for crewed Mars missions (2026)
[24] supported
In the nuclear-electric-propulsion reference mission, the transit time to Mars is 270 days, with 240 days of electric propulsion burn time.
"In the reference mission, the transit time to Mars is 270 days, with 240 days of EP burn time."
Analysis of electric propulsion propellant type for crewed Mars missions (2026)
[25] supported
The hybrid propulsion architecture's total trip time is 1,100 days, which lets the stage deliver cargo to Mars every other Earth-Mars transit opportunity.
"The 1,100 days total trip time allows the hybrid propulsion stage to deliver cargo to Mars every other Earth-Mars transit opportunity."
Mars Hybrid Propulsion System Trajectory Analysis (2015)
[26] supported
For the first two Mars surface missions in the Evolvable Mars Campaign, the short trip time lets the hybrid propulsion stage be reused for three round-trip journeys to Mars.
"For the first two Mars surface mission in the Evolvable Mars Campaign, the short trip time allows the hybrid propulsion stage to be reused for three round-trip journeys to Mars, which matches the hybrid propulsion stage's designed lifetime for three round-trip crew missions to the Martian sphere of influence."
Mars Hybrid Propulsion System Trajectory Analysis (2015)
[27] supported
The distance between Earth and Mars ranges from 55 to 400 million km over a synodic period of about 26 months.
"Based on the relative orbits of Mars and Earth, the distance between Earth and Mars ranges from 55 to 400 million km over a synodic period of approximately 26 months."
Read "Space Nuclear Propulsion for Human Mars Exploration" at NAP.edu
[28] supported
A Mars mission would involve one-way communication delays between ground control and the crew of up to about 22 minutes, which is an indirect indicator of the large Earth-Mars distance; the document gives no distance or trip duration.
"On a mission to Mars, there will be as long as 22-min one-way communication delays between the ground and the crew, causing major changes to current communication infrastructures."
Mars Mission Communication Delays and Impact on Mission Controller Performance, Workload, and Stress (2025)
[29] supported
Launch requirements for Earth departure vary significantly over the 26-month Earth-Mars cycle, so launch windows differ in difficulty.
"Launch (or Earth departure) requirements vary significantly over this cycle."
Read "Space Nuclear Propulsion for Human Mars Exploration" at NAP.edu
[30] supported
A human Mars mission must minimize interplanetary transit time because of radiation exposure and prolonged weightlessness, which affect crew health.
"For a human Mars exploration mission, it is required to minimize the time-of-flight of the interplanetary trajectories to mitigate the adverse effects of the radiation environment and prolonged weightlessness conditions on the health of the crew."
Propulsive abort trajectory options for a reconnaissance human Mars mission (2020)
[31] supported
Astronauts on a crewed Mars mission may spend as many as 500 days on the planet's surface before returning to Earth.
"The astronauts may spend as many as 500 days on the planet’s surface before returning to Earth."
NASA wants to send humans to Mars in the 2030s − a crewed mission could unlock some of the Red Planet’s geologic mysteries
[32] supported
For crewed conjunction-class (long-stay) missions, each way trip takes typically 180 to 210 days, with about 500 or more days on Mars and total mission time around 900 days.
"For crewed conjunction-class missions, trip times are typically 180 to 210 days each way, stay times on Mars are typically 500 days or more, and total mission time is around 900 days."
Read "Space Nuclear Propulsion for Human Mars Exploration" at NAP.edu