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Orbital speed: 7.67 km/s; 27,600 km/h; 17,100 mph [5] Orbital period: 92.9 minutes [6] ... The International Space Station is a product of global collaboration, with ...
A view from the International Space Station in a low Earth orbit (LEO) at about 400 km (250 mi), with yellow-green airglow visible at Earth's horizon, where roughly at an altitude of 100 km (62 mi) the boundary between Earth and outer space lies and flying speeds reach orbital velocities.
In gravitationally bound systems, the orbital speed of an astronomical body or object (e.g. planet, moon, artificial satellite, spacecraft, or star) is the speed at which it orbits around either the barycenter (the combined center of mass) or, if one body is much more massive than the other bodies of the system combined, its speed relative to the center of mass of the most massive body.
The Apollo 10 crew (Thomas Stafford, John W. Young and Eugene Cernan) achieved the highest speed relative to Earth ever attained by humans: 39,897 kilometers per hour (11,082 meters per second or 24,791 miles per hour, about 32 times the speed of sound and 0.0037% of the speed of light). [14]
The station was maintained at an orbit between 296 km (184 mi) and 421 km (262 mi) altitude and travelled at an average speed of 27,700 km/h (17,200 mph), completing 15.7 orbits per day. [ 1 ] [ page needed ] [ 2 ] [ page needed ] [ 3 ]
International Space Station mockup at Johnson Space Center in Houston, Texas. The space station is located in orbit around the Earth at an altitude of approximately 410 km (250 mi), a type of orbit usually termed low Earth orbit (the actual height varies over time by several kilometers due to atmospheric drag and reboosts).
Speed of International Space Station and typical speed of other satellites such as the Space Shuttle in low Earth orbit. 7,777: 28,000: 17,400: 2.594 × 10 −5: Speed of propagation of the explosion in a detonating cord. 10 4: 10,600 38,160 23,713.65 0.00004 Speed of propagation of the explosion of Octanitrocubane (ONC). 11,107: 39,985.2: ...
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 and details of the trajectory and launch vehicle), and gaining altitude.