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  2. Gravity loss - Wikipedia

    en.wikipedia.org/wiki/Gravity_loss

    For instance, gravity loss on a rocket of mass m would reduce a 3mg thrust directed upward to an acceleration of 2g. However, the same 3 mg thrust could be directed at such an angle that it had a 1 mg upward component, completely canceled by gravity, and a horizontal component of mg× 3 2 − 1 2 {\displaystyle {\sqrt {3^{2}-1^{2}}}} = 2.8 mg ...

  3. Thrust-to-weight ratio - Wikipedia

    en.wikipedia.org/wiki/Thrust-to-weight_ratio

    The thrust-to-weight ratio of a rocket, or rocket-propelled vehicle, is an indicator of its acceleration expressed in multiples of gravitational acceleration g. [ 5 ] Rockets and rocket-propelled vehicles operate in a wide range of gravitational environments, including the weightless environment.

  4. Tsiolkovsky rocket equation - Wikipedia

    en.wikipedia.org/wiki/Tsiolkovsky_rocket_equation

    A rocket's required mass ratio as a function of effective exhaust velocity ratio. The classical rocket equation, or ideal rocket equation is a mathematical equation that describes the motion of vehicles that follow the basic principle of a rocket: a device that can apply acceleration to itself using thrust by expelling part of its mass with high velocity and can thereby move due to the ...

  5. Mass ratio - Wikipedia

    en.wikipedia.org/wiki/Mass_ratio

    In aerospace engineering, mass ratio is a measure of the efficiency of a rocket.It describes how much more massive the vehicle is with propellant than without; that is, the ratio of the rocket's wet mass (vehicle plus contents plus propellant) to its dry mass (vehicle plus contents).

  6. Specific impulse - Wikipedia

    en.wikipedia.org/wiki/Specific_impulse

    The specific impulse of a rocket can be defined in terms of thrust per unit mass flow of propellant. This is an equally valid (and in some ways somewhat simpler) way of defining the effectiveness of a rocket propellant. For a rocket, the specific impulse defined in this way is simply the effective exhaust velocity relative to the rocket, v e ...

  7. Propellant mass fraction - Wikipedia

    en.wikipedia.org/wiki/Propellant_mass_fraction

    In rockets for a given target orbit, a rocket's mass fraction is the portion of the rocket's pre-launch mass (fully fueled) that does not reach orbit.The propellant mass fraction is the ratio of just the propellant to the entire mass of the vehicle at takeoff (propellant plus dry mass).

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    mail.aol.com

    Get AOL Mail for FREE! Manage your email like never before with travel, photo & document views. Personalize your inbox with themes & tabs. You've Got Mail!

  9. Rocket (web framework) - Wikipedia

    en.wikipedia.org/wiki/Rocket_(web_framework)

    Form Data - Rocket allows the user to define a Serde model, and use it to parse the Form Data, and pass it as native rust object to the route handler. Request Guards - the route handlers can contain a special kind of parameters named "Request Guard"s that are meant to prevent the code inside the handler to be called in case a certain condition ...