def limits(self):
"""FLIGHT ENVELPOE"""
# summarize minimum speeds
self.vmin = vmin(self.vmto, self.vmic, self.vmcr, self.vmap, self.vmld, self.phase)
# 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.traf.lspd, self.traf.lalt, self.traf.lvs, self.traf.ama = \
limits(self.traf.desspd, self.traf.lspd, self.vmin, self.vmo, self.mmo,\
self.traf.M, self.traf.ama, self.traf.alt, self.hmaxact, self.traf.desalt, self.traf.lalt,\
self.maxthr, self.Thr,self.traf.lvs, self.D, self.traf.tas, self.mass, self.ESF)
return
def limits(self):
"""Flight envelope"""
# 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/self.traf.rho)
self.vmic = np.sqrt(2*self.mass*g0/(self.traf.rho*self.clmaxcr*self.Sref))
self.vmcr = self.vmic
self.vmap = self.vmic
self.vmld = self.vm_ld*np.sqrt(self.mass/self.traf.rho)
# summarize and convert to cas
# note: aircraft on ground may be pushed back
self.vmin = (self.phase==1)*vtas2cas(self.vmto, self.traf.alt) + \
((self.phase==2) + (self.phase==3) + (self.phase==4))*vtas2cas(self.vmcr, self.traf.alt) + \
(self.phase==5)*vtas2cas(self.vmld, self.traf.alt) + (self.phase==6)*-10.0
# forwarding to tools
self.traf.limspd, \
self.traf.limspd_flag, \
self.traf.limalt, \
self.traf.limvs, \
self.traf.limvs_flag = limits(self.traf.desspd, \
self.traf.gs, \
self.vmto, \
self.vmin, \
self.vmo, \
self.mmo, \
self.traf.M, \
self.traf.alt, \
self.hmaxact, \
self.traf.desalt, \
self.traf.desvs, \
self.maxthr, \
self.Thr, \
self.D, \
self.traf.tas, \
self.mass, \
self.ESF)
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/self.traf.rho)
self.vmic = np.sqrt(2*self.mass*g0/(self.traf.rho*self.clmaxcr*self.Sref))
self.vmcr = self.vmic
self.vmap = self.vmic
self.vmld = self.vm_ld*np.sqrt(self.mass/self.traf.rho)
# summarize and convert to cas
# note: aircraft on ground may be pushed back
self.vmin = (self.phase==1)*vtas2cas(self.vmto, self.traf.alt) + \
((self.phase==2) + (self.phase==3) + (self.phase==4))*vtas2cas(self.vmcr, self.traf.alt) + \
(self.phase==5)*vtas2cas(self.vmld, self.traf.alt) + (self.phase==6)*-10.0
# forwarding to tools
self.traf.limspd, \
self.traf.limspd_flag, \
self.traf.limalt, \
self.traf.limvs, \
self.traf.limvs_flag = limits(self.traf.pilot.spd, \
self.traf.limspd, \
self.traf.gs, \
self.vmto, \
self.vmin, \
self.vmo, \
self.mmo, \
self.traf.M, \
self.traf.alt, \
self.hmaxact, \
self.traf.pilot.alt, \
self.traf.limalt, \
self.maxthr, \
self.Thr, \
self.traf.limvs, \
self.D, \
self.traf.tas, \
self.mass, \
self.ESF)
return
def limits(self):
"""Flight envelope"""
# 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 = vtas2cas(self.vm_to*np.sqrt(self.mass/self.traf.rho), self.traf.alt)
self.vmic = vtas2cas(np.sqrt(2*self.mass*g0/(self.traf.rho*self.clmaxcr*self.Sref)), self.traf.alt)
self.vmcr = self.vmic
self.vmap = self.vmic
self.vmld = vtas2cas(self.vm_ld*np.sqrt(self.mass/self.traf.rho), self.traf.alt)
# summarize
# note: aircraft on ground may be pushed back
self.vmin = (self.phase==1)*self.vmto + ((self.phase==2) + (self.phase==3) + (self.phase==4))*self.vmcr + \
(self.phase==5)*self.vmld + (self.phase==6)*-10.0
# forwarding to tools
self.traf.limspd, self.traf.limalt, self.traf.limvs, self.traf.ama = \
limits(self.traf.desspd, self.traf.limspd, self.vmin, self.vmo, self.mmo,\
self.traf.M, self.traf.ama, self.traf.alt, self.hmaxact, self.traf.desalt, self.traf.limalt,\
self.maxthr, self.Thr,self.traf.limvs, self.D, self.traf.tas, self.mass, self.ESF)
return