Search results
Results from the WOW.Com Content Network
An orbit near the craft's planned orbit was established, and the mission continued despite the abort to a lower orbit. [7] [8] The Mission Control Center at Johnson Space Center observed an SSME failure and called "Challenger-Houston, abort ATO." The engine failure was later determined to be an inadvertent engine shutdown caused by faulty ...
This delay resulted in an abnormal orbit and excessive fuel use. The decision was made to scratch the ISS rendezvous/docking since the spacecraft burned too much fuel to reach orbit even after Mission control center fixed the MET clock issue. NASA and Boeing officials placed the spacecraft in a different orbit and the entire flight plan had to ...
Sketch of a circumlunar free return trajectory (not to scale), plotted on the rotating reference frame rotating with the moon. (Moon's motion only shown for clarity) In orbital mechanics, a free-return trajectory is a trajectory of a spacecraft traveling away from a primary body (for example, the Earth) where gravity due to a secondary body (for example, the Moon) causes the spacecraft to ...
NASA and Boeing have been monitoring two issues with the Starliner spacecraft: one with a set of thrusters and the other involving helium leaks in the propulsion system.
In orbital mechanics, the Hohmann transfer orbit is an elliptical orbit used to transfer between two circular orbits of different altitudes, in the same plane. The orbital maneuver to perform the Hohmann transfer uses two engine impulses which move a spacecraft onto and off the transfer orbit.
Animation of InSight 's trajectory InSight · Earth · Mars Mars launch windows and distance from Earth In the context of spaceflight, launch period is the collection of days, and launch window is the time period on a given day, during which a particular rocket must be launched in order to reach its intended target.
In celestial mechanics, the mean anomaly is the fraction of an elliptical orbit's period that has elapsed since the orbiting body passed periapsis, expressed as an angle which can be used in calculating the position of that body in the classical two-body problem.
A two-stage-to-orbit (TSTO) or two-stage rocket is a launch vehicle in which two distinct stages provide propulsion consecutively in order to achieve orbital velocity. It is intermediate between a three-stage-to-orbit launcher and a hypothetical single-stage-to-orbit (SSTO) launcher. At liftoff the first stage is responsible for accelerating ...