In the cases of a single stage to orbit ( SSTO ) vehicle or suborbital vehicle, the mass fraction equals the propellant mass fraction; simply the fuel mass divided by the mass of the full spaceship.
22.
Liquid-fuel rockets typically have TNT equivalencies calculated based on the amount of fuel and oxidizer which could realistically intimately combine before igniting explosively; this is often taken to be 10 20 % of the total propellant mass.
23.
In aerospace engineering, the "'propellant mass fraction "'is the portion of a vehicle's mass which does not reach the destination, usually used as a measure of the vehicle's performance.
24.
Conversely, when applied to a single stage, where the propellant mass fraction calculation doesn't include the payload, a higher propellant mass fraction corresponds to a more efficient design, since there is less non-propellant mass.
25.
Conversely, when applied to a single stage, where the propellant mass fraction calculation doesn't include the payload, a higher propellant mass fraction corresponds to a more efficient design, since there is less non-propellant mass.
26.
Conversely, when applied to a single stage, where the propellant mass fraction calculation doesn't include the payload, a higher propellant mass fraction corresponds to a more efficient design, since there is less non-propellant mass.
27.
Explosions from hard starts often cannot happen with purely gaseous propellants, since the amount of the gas present in the chamber is limited by the injector area relative to the throat area, and for practical designs propellant mass escapes too quickly to be an issue.
28.
The specific impulse in terms of propellant mass spent ( multiplying the weight-based " I " sp in seconds by " g " 0 ) is in units of distance per time, which is an artificial velocity called the " effective exhaust velocity ".
29.
An additional expression for the overall structural mass fraction can be found by noting that the payload mass fraction \ left ( \ frac { m _ \ text { pl } } { m _ i } \ right ), propellant mass fraction and structural mass fraction sum to one:
30.
Thus, if it is desired to increase the thrust, say, n-times in the stationary mode, it will be necessary to increase n ^ 2-times the propellant mass flow, and decreasing \ frac { 1 } { n }-times the exhaust velocity.
