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  2. Delta-v - Wikipedia

    en.wikipedia.org/wiki/Delta-v

    Delta-v (also known as " change in velocity "), symbolized as and pronounced deltah-vee, as used in spacecraft flight dynamics, is a measure of the impulse per unit of spacecraft mass that is needed to perform a maneuver such as launching from or landing on a planet or moon, or an in-space orbital maneuver. It is a scalar that has the units of ...

  3. Orbital inclination change - Wikipedia

    en.wikipedia.org/wiki/Orbital_inclination_change

    The delta-v required is the vector change in velocity between the two planes at that point. However, maximum efficiency of inclination changes are achieved at apoapsis, (or apogee), where orbital velocity is the lowest. In some cases, it can require less total delta-v to raise the satellite into a higher orbit, change the orbit plane at the ...

  4. Delta-v budget - Wikipedia

    en.wikipedia.org/wiki/Delta-v_budget

    Delta- v in feet per second, and fuel requirements for a typical Apollo Lunar Landing mission. In astrodynamics and aerospace, a delta-v budget is an estimate of the total change in velocity (delta- v) required for a space mission. It is calculated as the sum of the delta-v required to perform each propulsive maneuver needed during the mission.

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  6. Hohmann transfer orbit - Wikipedia

    en.wikipedia.org/wiki/Hohmann_transfer_orbit

    The diagram shows a Hohmann transfer orbit to bring a spacecraft from a lower circular orbit into a higher one. It is an elliptic orbit that is tangential both to the lower circular orbit the spacecraft is to leave (cyan, labeled 1 on diagram) and the higher circular orbit that it is to reach (red, labeled 3 on diagram).

  7. Q-guidance - Wikipedia

    en.wikipedia.org/wiki/Q-guidance

    Q-guidance. Q-guidance is a method of missile guidance used in some U.S. ballistic missiles and some civilian space flights. It was developed in the 1950s by J. Halcombe Laning and Richard Battin at the MIT Instrumentation Lab. Q-guidance is used for missiles whose trajectory consists of a relatively short boost phase (or powered phase) during ...

  8. Geostationary transfer orbit - Wikipedia

    en.wikipedia.org/wiki/Geostationary_transfer_orbit

    For a typical GTO with a semi-major axis of 24,582 km, perigee velocity is 9.88 km/s and apogee velocity is 1.64 km/s, clearly making the inclination change far less costly at apogee. In practice, the inclination change is combined with the orbital circularization (or " apogee kick ") burn to reduce the total Δ V {\displaystyle \Delta V} for ...

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