Apollo vs Artemis
What a difference half a century makes!
There’s some fairly obvious differences
The major difference in trajectories between the **Saturn V** (used for Apollo lunar missions) and the SLS (used for Artemis missions) lies in the **translunar injection (TLI)** and overall flight path design, which reflect different mission goals, spacecraft capabilities, safety priorities, and efficiency
The most obvious is that Artemis has solid fuel rockets assists the main booster, provided 8.8 million lbs thrust. Saturn V was staged, and at launch produced over 9 million lbs of thrust. Also the orbital path of the Artemis has a very elliptic trajectory where 3rd staged an orbital injection along with the Command Module engines provided the breaking necessary for lunar orbit injection. The Apollo was a much faster path, whereas the Artemis uses a more efficient Hohmann gravitational assist. In addition the Apollo mission computers were not as powerful as most computational speed of most personal iPhones. They, in their moment in time, still using slide rules during Apollo and none of this modern wokeness was ever employed. Those early astronauts who were to pilot the Apollo missions were tested to the limits of human endurance.
Saturn V / Apollo Trajectory (1960s–1970s)
Fast, direct path. After reaching low Earth orbit, the Saturn V’s third stage performed a powerful TLI burn to send the Apollo spacecraft (Command/Service Module + Lunar Module) on a roughly 3 days to lunar injection.
Free-return trajectory option. Many Apollo missions (especially early ones like Apollo 8 or contingencies like Apollo 13) used a path where lunar gravity would naturally slingshot the spacecraft back to Earth if the lunar orbit insertion (LOI) burn failed. This provided a passive safety net.
Low lunar orbit Apollo typically entered a low-altitude orbit (~60–70 miles above the surface) for landing operations or detailed reconnaissance. The overall profile was optimized for speed and crewed lunar landings in a high-risk, high-reward era.
SLS / Artemis Trajectory (2020s–present)
Slower, more energy-efficient path Artemis missions (e.g., Artemis I uncrewed test and planned crewed flights like Artemis II) use a longer **4–6+ day** outbound leg to the Moon. This is closer to a Hohmann transfer orbit, which is more fuel-efficient but takes more time.
Artemis II,flight plan calls for a free-return trajectory, with a distant lunar flyby (thousands of miles from the surface, far higher than Apollo's close approaches). The Moon's gravity naturally redirects Orion back toward Earth with minimal or no additional burns required for return. This prioritizes safety and testing for the new Orion spacecraft and SLS upper stage (Interim Cryogenic Propulsion Stage or future Exploration Upper Stage).
No immediate low lunar orbit for early missions Artemis I used a distant retrograde orbit (DRO) around the Moon—much higher and more stable—for extended testing in deep space, radiation exposure, and thermal conditions. Future crewed landings (e.g., Artemis III) will involve different orbits like Near Rectilinear Halo Orbit (NRHO) around the Gateway station before descending to polar low lunar orbits for south pole landings.
Orion often performs additional maneuvers post-TLI (using its own service module engine) rather than relying solely on the launch vehicle’s upper stage for the full lunar injection.
The mission objectives also change mission trajectories… Apollo focused on quick “flags and footprints” landings in low equatorial orbits. Artemis aims for sustainable exploration (south pole resources, Gateway outpost, Mars prep), so trajectories test new systems, higher distances (Orion has flown farther from Earth than any crew-rated vehicle), and safer abort options.
The paths look very different on diagrams: Apollo as a relatively straight shot with a close lunar pass/orbit, versus Artemis as a more looping, distant figure-eight or high-orbit profile.
