Difference between revisions of "Cheat sheet"

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Calculation of a rocket's &Delta;v, taking an atmosphere into account. &Delta;v<sub>out</sub> is the amount of &Delta;v required to leave a body's atmosphere, '''not''' reach orbit. This equation is useful to figure out the actual &Delta;v of a stage that transitions from atmosphere to vacuum.
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Calculation of a rocket's &Delta;v, taking an atmosphere into account. &Delta;v<sub>out</sub> is the amount of &Delta;v required to leave a body's atmosphere, ''not'' reach orbit. This equation is useful to figure out the actual &Delta;v of a stage that ''transitions'' from atmosphere to vacuum.
  
 
<math>\Delta{v}_T = \frac{\Delta{v}_{atm} - \Delta{v}_{out} \frac{m}{s^2}}{\Delta{v}_{atm}} \cdot \Delta{v}_{vac} + \Delta{v}_{out} \frac{m}{s^2}</math>
 
<math>\Delta{v}_T = \frac{\Delta{v}_{atm} - \Delta{v}_{out} \frac{m}{s^2}}{\Delta{v}_{atm}} \cdot \Delta{v}_{vac} + \Delta{v}_{out} \frac{m}{s^2}</math>

Revision as of 23:15, 2 July 2013

Kerbal Space Program rocket scientist's cheat sheet: Delta-v maps, equations and more for your reference so you can get from here to there and back again.

Mathematics

Delta-v (Δv)

Basic calculation

→ See also: Tutorial:Advanced Rocket Design

Basic calculation of a rocket's Δv. Use the atmospheric and vacuum thrust values for atmospheric and vacuum Δv, respectively.

Transitional (true) Δv

Body Δvout
Kerbin 1000 m/s2
other bodies' data missing

Calculation of a rocket's Δv, taking an atmosphere into account. Δvout is the amount of Δv required to leave a body's atmosphere, not reach orbit. This equation is useful to figure out the actual Δv of a stage that transitions from atmosphere to vacuum.

Maps

Various fan-made maps showing the Δv required to travel to a certain body.

Total Δv values

Δv change values

Δv nomogram

Thrust to weight ratio (TWR)

→ See also: Terminology

This is Newton's Second Law. If the ratio is less than 1 the craft will not lift off the ground.

Combined specific impulse (Isp)

If the Isp is the same for all engines in a stage, then the Isp is equal to a single engine. If the Isp is different for engines in a single stage, then use the following equation:

See also

Links to collections of reference material.