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This plot shows a ship capable of 1-g (10 m/s 2 or about 1.0 ly/y 2) "felt" or proper acceleration [6] can travel vast distances, although is limited by the mass of any propellant it carries. A spaceship using significant constant acceleration will approach the speed of light over interstellar distances, so special relativity effects including ...
One complete orbit takes 365.256 days (1 sidereal year), during which time Earth has traveled 940 million km (584 million mi). [2] Ignoring the influence of other Solar System bodies, Earth's orbit, also called Earth's revolution, is an ellipse with the Earth–Sun barycenter as one focus with a current eccentricity of 0.0167. Since this value ...
To reach orbit, the rocket must impart to the payload a delta-v of about 9.3–10 km/s. This figure is mainly (~7.8 km/s) for horizontal acceleration needed to reach orbital speed, but allows for atmospheric drag (approximately 300 m/s with the ballistic coefficient of a 20 m long dense fueled vehicle), gravity losses (depending on burn time ...
The next close approach to Earth will be in the year 2047 at a distance of 5 million kilometers, about 13 times the distance between Earth and the Moon. [69] Simulations over a 3-million-year timespan found a probability of the Roadster colliding with Earth at approximately 6%, or with Venus at approximately 2.5%.
In November, the sun's gravity will pull it back into an orbit around the sun — but not that far from Earth. On January 8, 2025, according to NASA, it will skim past Earth at a distance of about ...
For example, as the Earth's rotational velocity is 465 m/s at the equator, a rocket launched tangentially from the Earth's equator to the east requires an initial velocity of about 10.735 km/s relative to the moving surface at the point of launch to escape whereas a rocket launched tangentially from the Earth's equator to the west requires an ...
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 [citation needed] Re-entry from LEO—the delta-v required is the orbital maneuvering burn to lower perigee into the atmosphere, atmospheric drag takes care of the rest.
The delta-v needed is only 3.6 km/s, only about 0.4 km/s more than needed to escape Earth, even though this results in the spacecraft going 2.9 km/s faster than the Earth as it heads off for Mars (see table below). At the other end, the spacecraft must decelerate for the gravity of Mars to capture it. This capture burn should optimally be done ...