guidance/second-stage-flight-flag guidance/upper-stage-flight-flag fcs/throttle-cmd-norm[0] gt 0
simulation/sim-time-sec
-guidance/executive/launch-time
guidance/upper-stage-flight-flag eq 1
guidance/second-stage-flight-flag eq 1
aero/qbar-psf ge 1000.0
guidance/executive/MET ge 999.0
guidance/executive/MET ge 10.0
guidance/executive/MET ge 6.0
guidance/executive/MET ge 999.0
guidance/executive/MET ge 0.0
guidance/executive/current-mode ge 0 guidance/executive/current-mode ge 1 guidance/executive/current-mode ge 2 guidance/executive/current-mode ge 3 guidance/executive/current-mode ge 4
Set the pitch rate dependent on guidance mode.
guidance/executive/current-mode eq 2
guidance/executive/current-mode ge 3
guidance/executive/MET gt 110.0
propulsion/engine[0]/thrust-lbs le 40000.0
guidance/executive/MET gt 110.0
propulsion/engine[1]/thrust-lbs le 40000.0
guidance/executive/left-srb-sep-flag eq 1
guidance/executive/right-srb-sep-flag eq 1 guidance/executive/MET ge 160.0
guidance/executive/MET gt 330.0
propulsion/engine[2]/thrust-lbs le 500.0
propulsion/engine[3]/thrust-lbs le 500.0
propulsion/engine[4]/thrust-lbs le 500.0
propulsion/engine[5]/thrust-lbs le 500.0
guidance/executive/gm
This equation calculates the semimajor-axis length in feet. a = mu/(2*mu/r - v^2)
guidance/executive/gm
2.0
guidance/executive/gm
position/radius-to-vehicle-ft
velocities/eci-velocity-mag-fps
2.0
This equation calculates eccentricity. e = sqrt (1 - [ r v cos(gamma) ]^2 / {a * mu})
1.0 position/radius-to-vehicle-ft velocities/eci-velocity-mag-fps flight-path/gamma-rad 2.0