def update(self):
self.a=util.scale_a()
self.M0=self.V0/self.a
if self.diag:
print "V: ",self.V0
if self.diag:
print "Mach: ", self.M0
self.shell.update(self.M0)
CT,CN,CM=shell.analyse(self.a0,mode="rad")
self.CL=CN*np.cos(self.a0)-CT*np.sin(self.a0)
self.CD=CT*np.cos(self.a0)+CN*np.sin(self.a0)
if self.para and self.T_sim>=self.para_t:
self.CD+=self.para_CD
if self.diag:
if self.para and self.T_sim>=self.para_t:
print "Para Deployed: True"
print "CL, CD: ",self.CL,self.CD
self.q=0.5*util.scale_height(self.R0-Re)[2]*self.V0**2 # dynamic pressure
if self.diag:
print "Dyn P: ",self.q
if self.para and self.T_sim>=self.para_t:
self.D0=self.q * self.S * (self.CD-self.para_CD) + self.q * self.para_S * self.para_CD
else:
self.D0=self.q * self.S * self.CD # aerodynamic force
self.L0=self.q * self.S * self.CL # aerodynamic force
if self.diag:
print "Lift, Drag : ",self.L0,self.D0
self.g0=-self.grav(self.R0-Re,0,0)
self.ydot0 = 0# -(self.V0/self.R0 - self.g0/self.V0)*np.cos(self.y0) + self.L0/(self.m*self.V0)
#print self.ydot0
self.q_data.append(self.q)
self.rho_data.append(util.scale_height(self.R0-Re)[2])
self.ydot_data.append(self.ydot0)
# coeff = ec.coeff() vehicle = ev.Test_vehicle() entrySim = Entry(orb,vehicle,coeff) K_ref=348.8 #kg/m2 ### Position stuff V0 = 11.2*1000 # m/s inital velocity R0 = 200*1000+6052*1000 # m inital altitude X0 = 70.75 *np.pi/180. # rad inital heading tau0 = -106.58 *np.pi/180 # rad inital latitude delta0= -22.3* np.pi/180. # rad inital longitude ### Misc stuff g0=grav(R0,tau0,delta0) rho0 =util.scale_height(R0-6052*1000)[2] ### angle stuff y0 = -10*np.pi/180. # rad inital gamma, flight path angle, must be positive for convergence ydot0 = -0.001*np.pi/180. # rad/s inital change in flight path angle m0 = 10*np.pi/180. # rad inital roll p0 = 0.001*np.pi/180. # rad/s inital roll rate a0 = 40*np.pi/180. # rad inital pitch q0 = 0*np.pi/180. # rad/s inital pitch rate b0 = 10*np.pi/180. # rad inital yaw r0 = 0.001*np.pi/180. # rad/s inital yaw rate
