caspervk/kOS-scripts
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Fix error caused by bug in the kOS language (?).

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This commit is contained in:
Casper V. Kristensen 2018-07-28 00:58:17 +02:00
parent 738f581155
commit d353debe5a
Signed by: caspervk
GPG key ID: B1156723DB3BDDA8
2 changed files with 4 additions and 5 deletions
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5
launch.ks
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@ -80,7 +80,6 @@ function launch {
wait until APOAPSIS > target_orbit_altitude.
lock THROTTLE TO 0.
unlock_control().
print "--- CIRCULARIZE ---".
@ -95,7 +94,7 @@ function launch {
local node is NODE(TIME:SECONDS + ETA:APOAPSIS, 0, 0, 0).
// Burn magnitude in the prograde direction is the difference between the required velocity to acheive circular orbit at apoapsis altitude and our velocity at apoapsis
local required_velocity is orbital_velocity_from_ap_pe(APOAPSIS, target_orbit_altitude, target_orbit_altitude).
local required_velocity is orbital_velocity_from_ap_pe(APOAPSIS, APOAPSIS, target_orbit_altitude).
set node:PROGRADE to required_velocity - VELOCITYAT(SHIP, TIME:SECONDS + ETA:APOAPSIS):ORBIT:MAG.
add node.
@ -118,7 +117,7 @@ function calculate_launch_azimuth {
local inertial_azimuth is ARCSIN(COS(target_orbit_inclination) / COS(launch_site_latitude)). // azimuth in inertial space, that is, disregarding the rotation of the body
local equatorial_rotational_velocity is (2 * CONSTANT:PI * BODY:RADIUS) / BODY:ROTATIONPERIOD.
local target_orbit_velocity is orbital_velocity_from_ap_pe(APOAPSIS, target_orbit_altitude, target_orbit_altitude).
local target_orbit_velocity is orbital_velocity_from_ap_pe(target_orbit_altitude, target_orbit_altitude, target_orbit_altitude).
local launch_vector_x_component is target_orbit_velocity * SIN(inertial_azimuth) - equatorial_rotational_velocity * COS(launch_site_latitude).
local launch_vector_y_component is target_orbit_velocity * COS(inertial_azimuth).

4
lib/equations.ks
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@ -42,9 +42,9 @@ function orbital_velocity {
// http://www.orbiterwiki.org/wiki/Front_Cover_Equations
// https://en.wikipedia.org/wiki/Vis-viva_equation
parameter altitude.
parameter semi_major_axis is semi_major_axis().
parameter sma is semi_major_axis().
return SQRT(BODY:MU * ((2 / (altitude+BODY:RADIUS)) - (1 / semi_major_axis))). // add body radius because KSP measures altitude from the surface
return SQRT(BODY:MU * ((2 / (altitude+BODY:RADIUS)) - (1 / sma))). // add body radius because KSP measures altitude from the surface
}
function orbital_velocity_from_ap_pe {