def limits(self):
"""FLIGHT ENVELPOE"""
# summarize minimum speeds - ac in ground mode might be pushing back
self.vmin = (self.phase == 1) * self.vmto + (self.phase == 2) * self.vmic + (self.phase == 3) * self.vmcr + \
(self.phase == 4) * self.vmap + (self.phase == 5) * self.vmld + (self.phase == 6) * -10.
# maximum altitude: hmax/act = MIN[hmo, hmax+gt*(dtemp-ctc1)+gw*(mmax-mact)]
# or hmo if hmx ==0 ()
# at the moment just ISA atmosphere, dtemp = 0
c1 = self.dtemp - self.ctct1
# if c1<0: c1 = 0
# values above 0 remain, values below are replaced through 0
c1m = np.array(c1 < 0) * 0.00000000000001
c1def = np.maximum(c1, c1m)
self.hact = self.hmax + self.gt * c1def + self.gw * (self.mmax -
self.mass)
# if hmax in OPF File ==0: hmaxact = hmo, else minimum(hmo, hmact)
self.hmaxact = (self.hmax == 0) * self.hmo + (
self.hmax != 0) * np.minimum(self.hmo, self.hact)
# forwarding to windtools
# forwarding to windtools
bs.traf.limspd, \
bs.traf.limspd_flag, \
bs.traf.limalt, \
bs.traf.limalt_flag, \
bs.traf.limvs, \
bs.traf.limvs_flag = calclimits(vtas2cas(bs.traf.pilot.tas, bs.traf.alt), \
bs.traf.gs, \
self.vmto, \
self.vmin, \
self.vmo, \
self.mmo, \
bs.traf.M, \
bs.traf.alt, \
self.hmaxact, \
bs.traf.pilot.alt, \
bs.traf.pilot.vs, \
self.maxthr, \
self.Thr, \
self.D, \
bs.traf.tas, \
self.mass, \
self.ESF, \
self.phase)
return
def limits(self):
"""FLIGHT ENVELPOE"""
# summarize minimum speeds - ac in ground mode might be pushing back
self.vmin = (self.phase == 1) * self.vmto + (self.phase == 2) * self.vmic + (self.phase == 3) * self.vmcr + \
(self.phase == 4) * self.vmap + (self.phase == 5) * self.vmld + (self.phase == 6) * -10.
# maximum altitude: hmax/act = MIN[hmo, hmax+gt*(dtemp-ctc1)+gw*(mmax-mact)]
# or hmo if hmx ==0 ()
# at the moment just ISA atmosphere, dtemp = 0
c1 = self.dtemp - self.ctct1
# if c1<0: c1 = 0
# values above 0 remain, values below are replaced through 0
c1m = np.array(c1<0)*0.00000000000001
c1def = np.maximum(c1, c1m)
self.hact = self.hmax+self.gt*c1def+self.gw*(self.mmax-self.mass)
# if hmax in OPF File ==0: hmaxact = hmo, else minimum(hmo, hmact)
self.hmaxact = (self.hmax==0)*self.hmo +(self.hmax !=0)*np.minimum(self.hmo, self.hact)
# forwarding to tools
# forwarding to tools
bs.traf.limspd, \
bs.traf.limspd_flag, \
bs.traf.limalt, \
bs.traf.limalt_flag, \
bs.traf.limvs, \
bs.traf.limvs_flag = calclimits(vtas2cas(bs.traf.pilot.tas, bs.traf.alt), \
bs.traf.gs, \
self.vmto, \
self.vmin, \
self.vmo, \
self.mmo, \
bs.traf.M, \
bs.traf.alt, \
self.hmaxact, \
bs.traf.pilot.alt, \
bs.traf.pilot.vs, \
self.maxthr, \
self.Thr, \
self.D, \
bs.traf.cas, \
self.mass, \
self.ESF, \
self.phase)
return
def limits(self):
"""Flight envelope""" # Connect this with function limits in performance.py
# combine minimum speeds and flight phases. Phases initial climb, cruise
# and approach use the same CLmax and thus the same function for Vmin
self.vmto = self.vm_to*np.sqrt(self.mass/bs.traf.rho)
self.vmic = np.sqrt(2*self.mass*g0/(bs.traf.rho*self.clmaxcr*self.Sref))
self.vmcr = self.vmic
self.vmap = self.vmic
self.vmld = self.vm_ld*np.sqrt(self.mass/bs.traf.rho)
# summarize and convert to cas
# note: aircraft on ground may be pushed back
self.vmin = (self.phase==1)*vtas2cas(self.vmto, bs.traf.alt) + \
((self.phase==2) + (self.phase==3) + (self.phase==4))*vtas2cas(self.vmcr, bs.traf.alt) + \
(self.phase==5)*vtas2cas(self.vmld, bs.traf.alt) + (self.phase==6)*-10.0
# forwarding to tools
bs.traf.limspd, \
bs.traf.limspd_flag, \
bs.traf.limalt, \
bs.traf.limalt_flag, \
bs.traf.limvs, \
bs.traf.limvs_flag = calclimits(vtas2cas(bs.traf.pilot.tas, bs.traf.alt), \
bs.traf.gs, \
self.vmto, \
self.vmin, \
self.vmo, \
self.mmo, \
bs.traf.M, \
bs.traf.alt, \
self.hmaxact, \
bs.traf.pilot.alt, \
bs.traf.pilot.vs, \
self.maxthr, \
self.Thr_pilot, \
self.D, \
bs.traf.cas, \
self.mass, \
self.ESF, \
self.phase)
return
def limits(self):
"""Flight envelope""" # Connect this with function limits in performance.py
# combine minimum speeds and flight phases. Phases initial climb, cruise
# and approach use the same CLmax and thus the same function for Vmin
self.vmto = self.vm_to*np.sqrt(self.mass/bs.traf.rho)
self.vmic = np.sqrt(2*self.mass*g0/(bs.traf.rho*self.clmaxcr*self.Sref))
self.vmcr = self.vmic
self.vmap = self.vmic
self.vmld = self.vm_ld*np.sqrt(self.mass/bs.traf.rho)
# summarize and convert to cas
# note: aircraft on ground may be pushed back
self.vmin = (self.phase==1)*vtas2cas(self.vmto, bs.traf.alt) + \
((self.phase==2) + (self.phase==3) + (self.phase==4))*vtas2cas(self.vmcr, bs.traf.alt) + \
(self.phase==5)*vtas2cas(self.vmld, bs.traf.alt) + (self.phase==6)*-10.0
# forwarding to tools
bs.traf.limspd, \
bs.traf.limspd_flag, \
bs.traf.limalt, \
bs.traf.limalt_flag, \
bs.traf.limvs, \
bs.traf.limvs_flag = calclimits(vtas2cas(bs.traf.pilot.tas, bs.traf.alt), \
bs.traf.gs, \
self.vmto, \
self.vmin, \
self.vmo, \
self.mmo, \
bs.traf.M, \
bs.traf.alt, \
self.hmaxact, \
bs.traf.pilot.alt, \
bs.traf.pilot.vs, \
self.maxthr, \
self.thrust_pilot, \
self.D, \
bs.traf.tas, \
self.mass, \
self.ESF, \
self.phase)
return
def limits(self, intent_v, intent_vs, intent_h, ax):
"""FLIGHT ENVELPOE"""
# summarize minimum speeds - ac in ground mode might be pushing back
self.vmin = (self.phase == 1) * self.vmto + (self.phase == 2) * self.vmic + (self.phase == 3) * self.vmcr + \
(self.phase == 4) * self.vmap + (self.phase == 5) * self.vmld + (self.phase == 6) * -10.
# maximum altitude: hmax/act = MIN[hmo, hmax+gt*(dtemp-ctc1)+gw*(mmax-mact)]
# or hmo if hmx ==0 ()
# at the moment just ISA atmosphere, dtemp = 0
c1 = self.dtemp - self.ctct1
# if c1<0: c1 = 0
# values above 0 remain, values below are replaced through 0
c1m = np.array(c1 < 0) * 0.00000000000001
c1def = np.maximum(c1, c1m)
self.hact = self.hmax + self.gt * c1def + self.gw * (self.mmax -
self.mass)
# if hmax in OPF File ==0: hmaxact = hmo, else minimum(hmo, hmact)
self.hmaxact = (self.hmax == 0) * self.hmo + (
self.hmax != 0) * np.minimum(self.hmo, self.hact)
# forwarding to tools
self.limspd, self.limspd_flag, self.limalt, \
self.limalt_flag, self.limvs, self.limvs_flag = calclimits(
vtas2cas(intent_v, bs.traf.alt), bs.traf.gs,
self.vmto, self.vmin, self.vmo, self.mmo,
bs.traf.M, bs.traf.alt, self.hmaxact,
intent_h, intent_vs, self.maxthr,
self.thrust, self.D, bs.traf.tas,
self.mass, self.ESF, self.phase)
# Update desired sates with values within the flight envelope
# When CAS is limited, it needs to be converted to TAS as only this TAS is used later on!
allowed_tas = np.where(self.limspd_flag,
vcas2tas(self.limspd, bs.traf.alt), intent_v)
# Autopilot selected altitude [m]
allowed_alt = np.where(self.limalt_flag, self.limalt, intent_h)
# Autopilot selected vertical speed (V/S)
allowed_vs = np.where(self.limvs_flag, self.limvs, intent_vs)
return allowed_tas, allowed_vs, allowed_alt
def limits(self, intent_v, intent_vs, intent_h, ax):
"""Flight envelope""" # Connect this with function limits in performance.py
# combine minimum speeds and flight phases. Phases initial climb, cruise
# and approach use the same CLmax and thus the same function for Vmin
self.vmto = self.vm_to * np.sqrt(self.mass / bs.traf.rho)
self.vmic = np.sqrt(2 * self.mass * g0 /
(bs.traf.rho * self.clmaxcr * self.Sref))
self.vmcr = self.vmic
self.vmap = self.vmic
self.vmld = self.vm_ld * np.sqrt(self.mass / bs.traf.rho)
# summarize and convert to cas
# note: aircraft on ground may be pushed back
self.vmin = (self.phase==1)*vtas2cas(self.vmto, bs.traf.alt) + \
((self.phase==2) + (self.phase==3) + (self.phase==4))*vtas2cas(self.vmcr, bs.traf.alt) + \
(self.phase==5)*vtas2cas(self.vmld, bs.traf.alt) + (self.phase==6)*-10.0
# forwarding to tools
self.limspd, self.limspd_flag, self.limalt, \
self.limalt_flag, self.limvs, self.limvs_flag = calclimits(
vtas2cas(intent_v, bs.traf.alt), bs.traf.gs, \
self.vmto, self.vmin, self.vmo, self.mmo, \
bs.traf.M, bs.traf.alt, self.hmaxact, \
intent_h, intent_vs, self.maxthr, \
self.thrust_pilot, self.D, bs.traf.tas, \
self.mass, self.ESF, self.phase)
# Update desired sates with values within the flight envelope
# When CAS is limited, it needs to be converted to TAS as only this TAS is used later on!
allowed_tas = np.where(self.limspd_flag,
vcas2tas(self.limspd, bs.traf.alt), intent_v)
# Autopilot selected altitude [m]
allowed_alt = np.where(self.limalt_flag, self.limalt, intent_h)
# Autopilot selected vertical speed (V/S)
allowed_vs = np.where(self.limvs_flag, self.limvs, intent_vs)
return allowed_tas, allowed_vs, allowed_alt
