Config file for project. Also change maneuver frame to RNC

cmd/mission/finalprj/finiteburn.toml

@@ -0,0 +1,170 @@
+[mission]
+start = "2016-10-16 16:20:06" # or JDE
+end = "2016-10-19 12:00:00" # or JDE
+step = "1s" # Must be parsable by golang's ParseDuration
+
+[spacecraft]
+name = "TGO"
+fuel = 500
+dry = 500
+
+[orbit]
+body = "Mars"
+sma = 55855.7
+ecc = 0.8690
+inc = 74.0
+RAAN = 0.0
+argPeri = 0.0
+tAnomaly = 180
+
+[error] # To generate datasets only
+probability = 0 # i.e. 1% of calls to SetState will have an error
+position = 1.0 # sigma for Gaussian
+velocity = 0.1 # sigma for Gaussian
+
+[perturbations]
+J2 = true
+J3 = false
+J4 = false
+bodies = ["Earth", "Sun", "Venus", "Jupiter"]
+
+[burns.0]
+date = "2016-10-19 00:00:00"
+R = 0
+N = -0.10
+C = 0
+
+[burns.1]
+date = "2016-10-19 00:00:01"
+R = 0
+N = -0.15
+C = 0
+
+[burns.2]
+date = "2016-10-19 00:00:02"
+R = 0
+N = -0.35
+C = 0
+
+[burns.3]
+date = "2016-10-19 00:00:03"
+R = 0
+N = -0.35
+C = 0
+
+[burns.4]
+date = "2016-10-19 00:00:04"
+R = 0
+N = -0.35
+C = 0
+
+[burns.5]
+date = "2016-10-19 00:00:05"
+R = 0
+N = -0.35
+C = 0
+
+[burns.6]
+date = "2016-10-19 00:00:06"
+R = 0
+N = -0.35
+C = 0
+
+[burns.7]
+date = "2016-10-19 00:00:07"
+R = 0
+N = -0.35
+C = 0
+
+[burns.8]
+date = "2016-10-19 00:00:08"
+R = 0
+N = -0.35
+C = 0
+
+[burns.9]
+date = "2016-10-19 00:00:09"
+R = 0
+N = -0.35
+C = 0
+
+[burns.10]
+date = "2016-10-19 00:00:10"
+R = 0
+N = -0.35
+C = 0
+
+[burns.11]
+date = "2016-10-19 00:00:11"
+R = 0
+N = -0.35
+C = 0
+
+[burns.12]
+date = "2016-10-19 00:00:12"
+R = 0
+N = -0.35
+C = 0
+
+[burns.13]
+date = "2016-10-19 00:00:13"
+R = 0
+N = -0.35
+C = 0
+
+[burns.14]
+date = "2016-10-19 00:00:14"
+R = 0
+N = -0.35
+C = 0
+
+[burns.15]
+date = "2016-10-19 00:00:15"
+R = 0
+N = -0.35
+C = 0
+
+[burns.16]
+date = "2016-10-19 00:00:16"
+R = 0
+N = -0.35
+C = 0
+
+[burns.17]
+date = "2016-10-19 00:00:17"
+R = 0
+N = -0.35
+C = 0
+
+[burns.18]
+date = "2016-10-19 00:00:18"
+R = 0
+N = -0.35
+C = 0
+
+[burns.19]
+date = "2016-10-19 00:00:19"
+R = 0
+N = -0.35
+C = 0
+
+[burns.20]
+date = "2016-10-19 00:00:20"
+R = 0
+N = -0.05
+C = 0
+
+[measurements]
+enabled = false
+output = "output/meas.csv"
+stations = ["builtin.DSS34", "Other"]
+
+[station.Other]
+name = "Other station"
+altitude = 100
+elevation = 10
+latitude = 0
+longitude = 0
+range_sigma = 0.1
+rate_sigma = 0.1
+#planet = "Mars"

cmd/mission/main.go

@@ -112,10 +112,10 @@ func main() {
 	// Maneuvers
 	for burnNo := 0; viper.IsSet(fmt.Sprintf("burns.%d", burnNo)); burnNo++ {
 		burnDT := confReadJDEorTime(fmt.Sprintf("burns.%d.date", burnNo))
-		V := viper.GetFloat64(fmt.Sprintf("burns.%d.V", burnNo))
+		R := viper.GetFloat64(fmt.Sprintf("burns.%d.R", burnNo))
 		N := viper.GetFloat64(fmt.Sprintf("burns.%d.N", burnNo))
 		C := viper.GetFloat64(fmt.Sprintf("burns.%d.C", burnNo))
-		sc.Maneuvers[burnDT] = smd.NewManeuver(V, N, C)
+		sc.Maneuvers[burnDT] = smd.NewManeuver(R, N, C)
 		if burnDT.After(endDT) || burnDT.Before(startDT) {
 			log.Printf("[WARNING] burn scheduled out of propagation time")
 		} else if verbose {

mission.go

@@ -308,18 +308,18 @@ func (a *Mission) Func(t float64, f []float64) (fDot []float64) {
 	tmpOrbit = NewOrbitFromRV(R, V, a.Orbit.Origin)
 	bodyAcc := -tmpOrbit.Origin.μ / math.Pow(Norm(R), 3)
 	_, _, i, Ω, _, _, _, _, u := tmpOrbit.Elements()
-	Δv = Rot313Vec(-u, -i, -Ω, Δv)
 	// Check if any impulse burn, and execute them if needed.
-	if maneuver, exists := a.Vehicle.Maneuvers[a.CurrentDT.Truncate(StepSize)]; exists {
+	if maneuver, exists := a.Vehicle.Maneuvers[a.CurrentDT.Truncate(a.step)]; exists {
 		if !maneuver.done {
 			a.Vehicle.logger.Log("level", "info", "subsys", "astro", "date", a.CurrentDT, "thrust", "impulse", "v(km/s)", maneuver.Δv())
-			Δv[0] += maneuver.V
+			Δv[0] += maneuver.R
 			Δv[1] += maneuver.N
 			Δv[2] += maneuver.C
 			maneuver.done = true
-			a.Vehicle.Maneuvers[a.CurrentDT.Truncate(StepSize)] = maneuver
+			a.Vehicle.Maneuvers[a.CurrentDT.Truncate(a.step)] = maneuver
 		}
 	}
+	Δv = Rot313Vec(-u, -i, -Ω, Δv)
 	// d\vec{R}/dt
 	fDot[0] = f[3]
 	fDot[1] = f[4]

prop.go

@@ -500,19 +500,19 @@ func NewHohmannΔv(target Orbit) HohmannΔv {
 
 // Maneuver stores a maneuver in the VNC frame
 type Maneuver struct {
-	V, N, C float64
+	R, N, C float64
 	done    bool
 }
 
 // Δv returns the Δv in km/s
 func (m Maneuver) Δv() float64 {
-	return math.Sqrt(m.V*m.V + m.N*m.N + m.C*m.C)
+	return math.Sqrt(m.R*m.R + m.N*m.N + m.C*m.C)
 }
 
 func (m Maneuver) String() string {
-	return fmt.Sprintf("burn [%f %f %f] km/s -- executed: %v", m.V, m.N, m.C, m.done)
+	return fmt.Sprintf("burn [%f %f %f] km/s -- executed: %v", m.R, m.N, m.C, m.done)
 }
 
-func NewManeuver(V, N, C float64) Maneuver {
-	return Maneuver{V, N, C, false}
+func NewManeuver(R, N, C float64) Maneuver {
+	return Maneuver{R, N, C, false}
 }