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Orbital target simulation handles targeting APIs gracefully after save/resume

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Thorsten Renk 2019-03-11 12:55:35 +02:00
parent 94d90fa85e
commit 4385b734f6
1 changed files with 18 additions and 9 deletions
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27
Nasal/orbital_target.nas
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@ -1,7 +1,7 @@
###########################################################################
# simulation of a faraway orbital target (needs handover to spacecraft-specific
# code for close range)
# Thorsten Renk 2016 - 2019
# Thorsten Renk 2016-2019
###########################################################################
var orbitalTarget = {
@ -19,8 +19,8 @@ var orbitalTarget = {
t.nl_rad = t.node_longitude * math.pi/180.0;
t.initial_nl_rad = t.nl_rad;
var l_tmp = t.l_vec[0];
t.l_vec[0] = -math.sin(t.nl_rad) * l_tmp;
t.l_vec[1] = math.cos(t.nl_rad) * l_tmp;
t.l_vec[0] = math.sin(t.nl_rad) * l_tmp;
t.l_vec[1] = -math.cos(t.nl_rad) * l_tmp;
t.anomaly = anomaly;
t.anomaly_rad = t.anomaly * math.pi/180.0;
t.initial_anomaly_rad = t.anomaly_rad;
@ -28,6 +28,7 @@ var orbitalTarget = {
t.update_time = 0.1;
t.running_flag = 0;
t.elapsed_time = 0.0;
t.delta_time = 0.0;
t.node_drift = -4361.26 * 1./math.pow(t.radius/1000.0 ,2.0) * math.cos(t.inc_rad);
@ -71,6 +72,13 @@ var orbitalTarget = {
me.delta_lon = me.delta_lon + dt * 0.00418333333333327;
me.node_longitude = me.node_longitude + me.node_drift * dt;
me.nl_rad = me.node_longitude * math.pi/180.0;
me.l_vec = [math.sin(me.inc_rad), 0.0, math.cos(me.inc_rad)];
var l_tmp = me.l_vec[0];
me.l_vec[0] = math.sin(me.nl_rad) * l_tmp;
me.l_vec[1] = -math.cos(me.nl_rad) * l_tmp;
},
get_inertial_pos: func {
@ -80,13 +88,14 @@ var orbitalTarget = {
get_inertial_pos_at_time: func (time) {
var anomaly_rad = me.initial_anomaly_rad + time/me.period * 2.0 * math.pi;
var anomaly_rad = me.initial_anomaly_rad + (time - me.delta_time)/me.period * 2.0 * math.pi;
while (anomaly_rad > 2.0 * math.pi)
{
anomaly_rad = anomaly_rad - 2.0 * math.pi;
}
var nl_rad = me.initial_nl_rad + me.node_drift * time * math.pi/180.0;
var nl_rad = me.initial_nl_rad + me.node_drift * (time - me.delta_time) * math.pi/180.0;
return me.compute_inertial_pos(anomaly_rad, nl_rad);
@ -125,22 +134,22 @@ var orbitalTarget = {
# obtain via numerical discretization from two points
var anomaly_rad = me.initial_anomaly_rad + time/me.period * 2.0 * math.pi;
var anomaly_rad = me.initial_anomaly_rad + (time- me.delta_time)/me.period * 2.0 * math.pi;
while (anomaly_rad > 2.0 * math.pi)
{
anomaly_rad = anomaly_rad - 2.0 * math.pi;
}
var nl_rad = me.initial_nl_rad + me.node_drift * time * math.pi/180.0;
var nl_rad = me.initial_nl_rad + me.node_drift * (time - me.delta_time) * math.pi/180.0;
var pos1 = me.compute_inertial_pos(anomaly_rad, nl_rad);
anomaly_rad = me.initial_anomaly_rad + (time + 0.1)/me.period * 2.0 * math.pi;
anomaly_rad = me.initial_anomaly_rad + ((time - me.delta_time) + 0.1)/me.period * 2.0 * math.pi;
while (anomaly_rad > 2.0 * math.pi)
{
anomaly_rad = anomaly_rad - 2.0 * math.pi;
}
nl_rad = me.initial_nl_rad + me.node_drift * (time+0.1) * math.pi/180.0;
nl_rad = me.initial_nl_rad + me.node_drift * ((time - me.delta_time) +0.1) * math.pi/180.0;
var pos2 = me.compute_inertial_pos(anomaly_rad, nl_rad);
var vx = (pos2[0] - pos1[0])/0.1;