Burn renders a nominal *looking* Hohmann transfer in my example, but …

…the final orbit is MUCH higher than it should

cmd/mission/example.toml

@@ -1,7 +1,6 @@
 [mission]
-start = "2015-02-03 15:16:17" # or JDE
-end = "2015-03-03 15:16:17" # or JDE
-step = "10s" # Must be parsable by Go's time.
+start = "2015-02-03 00:00:00" # or JDE
+end = "2015-02-15 00:00:00" # or JDE
 
 [spacecraft]
 name = "MRO"
@@ -10,12 +9,12 @@ dry = 500
 
 [orbit]
 body = "Earth"
-sma = 7000
-ecc = 0.01
-inc = 10.6
-RAAN = 36
-argPeri = 36
-tAnomaly = 1
+sma = 6469
+ecc = 0.0
+inc = 0.0
+RAAN = 0.0
+argPeri = 0.0
+tAnomaly = 90
 #position = [] #[x, y, z]
 #velocity = [] #[xdot ydot zdot]
 
@@ -31,10 +30,16 @@ J4 = true
 bodies = ["Earth", "Sun", "Venus", "Jupiter"]
 
 [burns.0]
-date = "2015-02-10 15:16:17" # or JDE
-V = 1
-N = 2
-C = 3
+date = "2015-02-03 00:30:00" # or JDE
+V = 2.457038
+N = 0
+C = 0
+
+[burns.1]
+date = "2015-02-03 05:45:20"
+V = -1.478187
+N = 0
+C = 0
 
 [measurements]
 output = "meas.csv"

cmd/mission/main.go

@@ -22,7 +22,6 @@ const (
 
 var (
 	scenario string
-	timeStep time.Duration
 	verbose  bool
 )
 
@@ -48,10 +47,6 @@ func main() {
 	// Read Mission parameters
 	startDT := confReadJDEorTime("mission.start")
 	endDT := confReadJDEorTime("mission.end")
-	timeStep = viper.GetDuration("mission.step")
-	if verbose {
-		log.Printf("[conf] time step: %s\n", timeStep)
-	}
 
 	// Read spacecraft
 	scName := viper.GetString("spacecraft.name")
@@ -113,11 +108,11 @@ func main() {
 		if burnDT.After(endDT) || burnDT.Before(startDT) {
 			log.Printf("[WARNING] burn scheduled out of propagation time")
 		} else if verbose {
-			log.Printf("added: %s", sc.Maneuvers[burnDT])
+			log.Printf("Scheduled burn %s @ %s", sc.Maneuvers[burnDT], burnDT)
 		}
 	}
 
-	smd.NewMission(sc, scOrbit, startDT, endDT, perts, false, smd.ExportConfig{}).Propagate()
+	smd.NewMission(sc, scOrbit, startDT, endDT, perts, false, smd.ExportConfig{AsCSV: false, Cosmo: true, Filename: scName}).Propagate()
 }
 
 func confReadJDEorTime(key string) (dt time.Time) {

mission.go

@@ -290,6 +290,17 @@ func (a *Mission) Func(t float64, f []float64) (fDot []float64) {
 	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.done {
+			a.Vehicle.logger.Log("level", "info", "subsys", "astro", "date", a.CurrentDT, "thrust", "impulse", "v(km/s)", maneuver.Δv())
+			Δv[0] += maneuver.V
+			Δv[1] += maneuver.N
+			Δv[2] += maneuver.C
+			maneuver.done = true
+			a.Vehicle.Maneuvers[a.CurrentDT.Truncate(StepSize)] = maneuver
+		}
+	}
 	// d\vec{R}/dt
 	fDot[0] = f[3]
 	fDot[1] = f[4]

spacecraft.go

@@ -72,13 +72,6 @@ func (sc *Spacecraft) Accelerate(dt time.Time, o *Orbit) (Δv []float64, fuel fl
 	thrust := 0.0
 	fuel = 0.0
 	Δv = make([]float64, 3)
-	// Check if any impulse burn, and execute them if needed.
-	if maneuver, exists := sc.Maneuvers[dt.Truncate(StepSize)]; exists {
-		sc.logger.Log("level", "info", "subsys", "astro", "date", dt, "thrust", "impulse", "v(km/s)", maneuver.Δv(), "orbit", o, "period", o.Period())
-		Δv[0] += maneuver.V
-		Δv[1] += maneuver.N
-		Δv[2] += maneuver.C
-	}
 	for _, wp := range sc.WayPoints {
 		if sc.EPS == nil {
 			panic("cannot attempt to reach any waypoint without an EPS")