Install Steam
login
|
language
简体中文 (Simplified Chinese)
繁體中文 (Traditional Chinese)
日本語 (Japanese)
한국어 (Korean)
ไทย (Thai)
Български (Bulgarian)
Čeština (Czech)
Dansk (Danish)
Deutsch (German)
Español - España (Spanish - Spain)
Español - Latinoamérica (Spanish - Latin America)
Ελληνικά (Greek)
Français (French)
Italiano (Italian)
Bahasa Indonesia (Indonesian)
Magyar (Hungarian)
Nederlands (Dutch)
Norsk (Norwegian)
Polski (Polish)
Português (Portuguese - Portugal)
Português - Brasil (Portuguese - Brazil)
Română (Romanian)
Русский (Russian)
Suomi (Finnish)
Svenska (Swedish)
Türkçe (Turkish)
Tiếng Việt (Vietnamese)
Українська (Ukrainian)
Report a translation problem
When taking off from planets with an atmo, thrust-to-weight does matter, but there are still rules of thumb for how much delta V you need. Without atmo, thrust to weight greater 1 is required, beyond that just a pretty constant amount of delta V.
At the bottom right side of the screen are a few buttons, one of which is dV (it uses the greek letter for delta, a triangle). That button gives you options to change the reference body. So dV for example is pretty much always measured using the vacuum value (all dV maps use this version). For TWR, you'll want to use the relevent reference body (to make sure you can take off from or safely land on a specific moon or planet). If you're on Kerbin or deep space, use Kerbin as the reference, since this value is in g's (a TWR of 2 will accerlerate at 9.81 m/s^2).
Kerbin's gravity can be rounded up to 10 m/s/s so any rocket you make will need at least 10 m/s/s of acceleration (1 TWR) to get off the launchpad.
Having it at least 15 m/s/s or 1.5 TWR works a lot better.
Acceleration can be calculated by dividing mass by thrust so M/F=a.
https://steamcommunity.com/sharedfiles/filedetails/?id=1848144224
dV (in m/s) = 9.81 * engine Isp * Ln( starting spacecraft mass / final spacecraft mass )
So that previous post had a spacecraft with a mass of 6.95 t, or 6,950 kg. Liquid fuel and oxidier mass 5 kg/unit. This craft has 440 Liquid Fuel and 360 Oxidizer, so the total fuel masses 4,000 kg or 4t. The "Terrier" engine has an Isp of 345. So 9.81 * 345 * Ln( 6.95 / ( 6.95 - 4 )) gives us 2,900 m/s dV. The screenshot says it is only 2,899 m/s, but that is only 1 m/s dV off--well within the margin of error.
As a bonus exercise, we can compute how much dV we have with this craft based on monopropellant, once all the Liq/Ox fuel is used up. Monopropellant masses 4 kg/unit. The RCS thrusters have an Isp of 240 in a vacuum. So with 86.52 mono propellant left, we have 293.8 m/s dV to spare.
TWR is easier. To find our acceleration in m/s/s, we take our total thrust (60 kN for a Terrier), and divide it by our mass (6.95t). So this craft accelerates at 8.63 m/s/s. Then we divide that by the world's surface gravity to determine TWR. So on Kerbin, it has a TWR of 0.88--not enough to lift itself off the ground. But on the Mun with its 1.6606 m/s/s surface gravity, it has a TWR of 5.2. ... Okay, that is a little less than what the KSP read-out shows, but that just leads me to suspect it takes altitude into account. The mun's pull at higher altitudes is less, making TWR's higher.
The idea is that my mining ship will refuel itself on the Mun's surface, dock with a ship in orbit, convert any remaining ore into fuel, transfer some fuel to the other vessel, undock, and land again.
I also know that liquid fuel and oxidizer both mass 5 kg/unit, and ore masses 10 kg/unit. The mining ship uses "Poodle" engines with an Isp of 350. 1 metric ton is 1,000 kg. Poodle engines use Liquid fuel & oxidizer in a 9:11 ratio.
I want 1,000 m/s of dV to de-orbit and land. (This is based on altitude, the Mun's gravity, and how much of a safety margin I (the player) desire.)
"Dry" ship mass = 56,040 kg - 5(1733 oxidizer) - 5(1491 liquid fuel) - 10(600 ore) = 33,920 kg = 33.92 t.
Now, let's plug this into the dV equation.
dV = g * Isp * Ln( initial mass / dry mass )
1,000 = 9.81 * 350 * Ln( initial mass / dry mass )
1,000 / ( 9.81 * 350 ) = Ln( initial mass / dry mass )
0.291 = Ln( initial mass / dry mass )
e^0.291 = e^(Ln( initial mass / dry mass ))
1.338 = initial mass / dry mass
1.338 = ( dry mass + fuel mass ) / dry mass
1.338 = ( 33.92t + fuel mass ) / 33.92t
1.338 * 33.92t = 33.92t + fuel mass
45.39t - 33.92t = fuel mass
11.47t = fuel mass
Now we need to convert fuel from total mass into units of liquid fuel and oxidizer.
liquid fuel (in units) = total fuel mass (in kg) * (9 units / 20 total equivalent units) / 4 kg per unit
oxidizer (in units) = total fuel mass (in kg) * (11 units / 20 total equivalent units) / 4 kg per unit