(!*********************************************************************
Mosel NL examples
=================
file glidert.mos
````````````````
Maximize the total horizontal distance a hang glider flies.
Configure the wind conditions by setting the parameter WIND:
WIND = 0 : no wind
WIND = 1 : thermal uplift 250m ahead (positive in a neighborhood
of 250m but drops to zero exponentially away from this point)
WIND = 2 : wind shear (a rapidly diminishing head wind that may cause
the glider to stall)
Trapezoidal discretization.
Based on AMPL models hang_midpt.mod, shear_midpt.mod, stableair_midpt.mod
Source: http://www.orfe.princeton.edu/~rvdb/ampl/nlmodels/hang/
Reference:
R. Bulirsch, E. Nerz, H.J. Pesch, and O. von Stryk, "Combining Direct and
Indirect Methods in Optimal Control: Range Maximization of a Hang Glider",
in "Optimal Control: Calculus of Variations, Optimal Control Theory and
Numerical Methods", ed. by R. Bulirsch, A. Miele, J. Stoer, and K.H. Well
(1993) Birkhauser
(c) 2013 Fair Issac Corporation
author: S. Heipcke, Mar. 2013
*********************************************************************!)
model "glider"
uses "mmxnlp"
parameters
WIND = 1 ! Wind conditions; possible values: 0, 1, 2
N = 150 ! Number of discretization points
end-parameters
declarations
POS_NODES = 0..N ! Positions
VEL_NODES = 1..N ! Velocity measure points
X_0,Y_0 : real ! Initial position (x,y) of glider
VX_0,VY_0: real ! Initial velocity (x',y') of glider
CL_0: real ! Initial lift coefficient
X_N,Y_N : real ! n_th step position (x,y) of glider
VX_N,VY_N: real ! n_th step velocity (x',y') of glider
CL_N: real ! n_th step Lift coefficient
CL_MIN,CL_MAX: real ! Minimum/maximum value of lift coefficient
UM : real ! Upward wind-velocity coefficient (m/sec)
R : real ! Upward wind-velocity ratio (m)
C0,K : real ! Drag coefficient constants
MASS: real ! Mass of glider & pilot
SPAN: real ! Wing area
RHO : real ! Air density
GRAV: real ! Acceleration due to gravity
WEIGHT: real ! Weight of glider & pilot (= m*g)
dur: mpvar ! Total time for the flight
! State variables:
x,y: array(POS_NODES) of mpvar ! Position at time t
vx,vy: array(POS_NODES) of mpvar ! Velocity at time t
vx_dot,vy_dot: array(POS_NODES) of mpvar ! Derivatives of vx,vy
cLift: array(POS_NODES) of mpvar ! Lift coefficient (control variable)
! Auxiliary expressions
CDrag: array(POS_NODES) of nlctr ! Drag coefficient
X: array(POS_NODES) of nlctr
UpAcc: array(POS_NODES) of nlctr ! Upward wind velocity
HorAcc: array(POS_NODES) of nlctr ! Horizontal air motion
Vx,Vy: array(POS_NODES) of nlctr
Vr: array(POS_NODES) of nlctr ! Velocity relative to the air
Drag: array(POS_NODES) of nlctr ! Drag force (opposite to Vr)
Lift: array(POS_NODES) of nlctr ! Lift force (perpendicular to Vr)
sin_eta: array(POS_NODES) of nlctr
cos_eta: array(POS_NODES) of nlctr
end-declarations
initializations from "glider.dat"
X_0 Y_0 VX_0 VY_0 Y_N VX_N VY_N
UM R C0 K MASS SPAN RHO GRAV CL_MIN CL_MAX
end-initializations
if WIND=2 then
Y_0 := 100; Y_N := 0; VY_N := 0;
end-if
WEIGHT := MASS*GRAV
! Start values
forall(j in POS_NODES) do
setinitval(vx(j), VX_0)
setinitval(vy(j), VY_0)
end-do
forall(j in POS_NODES) do
setinitval(x(j), 5000*j/N) ! 1000*(j-1)/N)
setinitval(y(j), -100*j/N+1000)
end-do
forall(j in POS_NODES) setinitval(cLift(j), (CL_MAX+CL_MIN)/2)
! Trapezoidal discretization
forall(j in VEL_NODES) do
x(j) = x(j-1) + 0.5*(dur/N)*(vx(j) + vx(j-1))
y(j) = y(j-1) + 0.5*(dur/N)*(vy(j) + vy(j-1))
vx(j) = vx(j-1) + 0.5*(dur/N)*(vx_dot(j) + vx_dot(j-1))
vy(j) = vy(j-1) + 0.5*(dur/N)*(vy_dot(j) + vy_dot(j-1))
-100 <= vx(j); vx(j) <= 100
-100 <= vy(j); vy(j) <= 100
end-do
! Wind formulae
forall(j in POS_NODES)
if WIND=1 then ! Upward wind velocity formula
X(j) := (x(j)/R - 2.5)^2
UpAcc(j) := UM*(1-X(j))*exp(-X(j))
elif WIND = 2 then ! Horizontal wind formula
HorAcc(j) := -5*(1+arctan((y(j)-30)/10))
end-if
! Definition of bounds and auxiliary expressions
forall(j in POS_NODES) do
cLift(j) >= CL_MIN
cLift(j) <= CL_MAX
CDrag(j) := C0 + K*cLift(j)^2 ! The drag coeff. depends on the lift coeff.
if WIND=1 then
Vy(j) := vy(j) - UpAcc(j)
else
Vy(j) := vy(j)
end-if
if WIND=2 then
Vx(j) := vx(j) - HorAcc(j)
else
Vx(j) := vx(j)
end-if
Vr(j) := sqrt(Vx(j)^2 + Vy(j)^2)
Drag(j) := 0.5*CDrag(j)*RHO*SPAN*Vr(j)^2
Lift(j) := 0.5*cLift(j)*RHO*SPAN*Vr(j)^2
sin_eta(j) := Vy(j)/Vr(j)
cos_eta(j) := Vx(j)/Vr(j)
vx_dot(j) is_free
vy_dot(j) is_free
end-do
dur >= 10; dur <= 200
! Initial and final states
x(0) = X_0
y(0) = Y_0
vx(0) = VX_0 - if(WIND=2, 2.5*(1+arctan((Y_0-30)/10)), 0)
vy(0) = VY_0
y(N) = Y_N !or: >=
vx(N) = VX_N !or: >=
vy(N) = VY_N !or: >=
! Equations of motion: F = m*a
! (eta denotes the angle between Vr and the horizontal plane)
forall(j in VEL_NODES) do
newt_x(j) := vx_dot(j) = (-Lift(j)*sin_eta(j) - Drag(j)*cos_eta(j))/MASS
newt_y(j) := vy_dot(j) = (Lift(j)*cos_eta(j) - Drag(j)*sin_eta(j) - WEIGHT)/MASS
end-do
! Monotonicity condition
forall(j in VEL_NODES) x(j) >= x(j-1)
! Limit velocity to levels that are supportable for the pilot
forall(j in POS_NODES) do
-3 <= vx_dot(j); vx_dot(j) <= 3
-3 <= vy_dot(j); vy_dot(j) <= 3
end-do
! Setting up and solving the problem
setparam("xnlp_verbose", true)
! Check the presence of Knitro; this example needs the interior point solver
if hasfeature("XPKNTLib") then
setparam("xnlp_solver", 1) ! Preselect Knitro as solver
else
writeln("This example requires Knitro")
exit(1)
end-if
maximize(x(N))
! Test whether a solution is available
nlstat:=getparam("XNLP_STATUS")
if nlstat<>XNLP_STATUS_LOCALLY_OPTIMAL and nlstat<>XNLP_STATUS_OPTIMAL then
writeln("No solution found.")
exit(0)
end-if
! Solution display
forall(i in POS_NODES)
writeln("xy(",i,") = (", getsol(x(i)), ",", getsol(y(i)), ")")
writeln("Max distance flown: ", getsol(x(N)))
writeln("Total flight time : ", getsol(dur))
end-model
|
(!*********************************************************************
Mosel NL examples
=================
file glidert_graph.mos
``````````````````````
Maximize the total horizontal distance a hang glider flies.
Configure the wind conditions by setting the parameter WIND:
WIND = 0 : no wind
WIND = 1 : thermal uplift 250m ahead (positive in a neighborhood
of 250m but drops to zero exponentially away from this point)
WIND = 2 : wind shear (a rapidly diminishing head wind that may cause
the glider to stall)
Trapezoidal discretization.
Based on AMPL models hang_midpt.mod, shear_midpt.mod, stableair_midpt.mod
Source: http://www.orfe.princeton.edu/~rvdb/ampl/nlmodels/hang/
Reference:
R. Bulirsch, E. Nerz, H.J. Pesch, and O. von Stryk, "Combining Direct and
Indirect Methods in Optimal Control: Range Maximization of a Hang Glider",
in "Optimal Control: Calculus of Variations, Optimal Control Theory and
Numerical Methods", ed. by R. Bulirsch, A. Miele, J. Stoer, and K.H. Well
(1993) Birkhauser
- Graphical representation of results -
(c) 2013 Fair Issac Corporation
author: S. Heipcke, Mar. 2013, rev. Sep 2017
*********************************************************************!)
model "glider (NL)"
uses "mmxnlp", "mmsvg"
parameters
WIND = 1 ! Wind conditions; possible values: 0, 1, 2
N = 150 ! Number of discretization points
end-parameters
declarations
POS_NODES = 0..N ! Positions
VEL_NODES = 1..N ! Velocity measure points
X_0,Y_0 : real ! Initial position (x,y) of glider
VX_0,VY_0: real ! Initial velocity (x',y') of glider
CL_0: real ! Initial lift coefficient
X_N,Y_N : real ! n_th step position (x,y) of glider
VX_N,VY_N: real ! n_th step velocity (x',y') of glider
CL_N: real ! n_th step Lift coefficient
CL_MIN,CL_MAX: real ! Minimum/maximum value of lift coefficient
UM : real ! Upward wind-velocity coefficient (m/sec)
R : real ! Upward wind-velocity ratio (m)
C0,K : real ! Drag coefficient constants
MASS: real ! Mass of glider & pilot
SPAN: real ! Wing area
RHO : real ! Air density
GRAV: real ! Acceleration due to gravity
WEIGHT: real ! Weight of glider & pilot (= m*g)
dur: mpvar ! Total time for the flight
! State variables:
x,y: array(POS_NODES) of mpvar ! Position at time t
vx,vy: array(POS_NODES) of mpvar ! Velocity at time t
vx_dot,vy_dot: array(POS_NODES) of mpvar ! Derivatives of vx,vy
cLift: array(POS_NODES) of mpvar ! Lift coefficient (control variable)
! Auxiliary expressions
CDrag: array(POS_NODES) of nlctr ! Drag coefficient
X: array(POS_NODES) of nlctr
UpAcc: array(POS_NODES) of nlctr ! Upward wind velocity
HorAcc: array(POS_NODES) of nlctr ! Horizontal air motion
Vx,Vy: array(POS_NODES) of nlctr
Vr: array(POS_NODES) of nlctr ! Velocity relative to the air
Drag: array(POS_NODES) of nlctr ! Drag force (opposite to Vr)
Lift: array(POS_NODES) of nlctr ! Lift force (perpendicular to Vr)
sin_eta: array(POS_NODES) of nlctr
cos_eta: array(POS_NODES) of nlctr
end-declarations
initializations from "glider.dat"
X_0 Y_0 VX_0 VY_0 Y_N VX_N VY_N
UM R C0 K MASS SPAN RHO GRAV CL_MIN CL_MAX
end-initializations
if WIND=2 then
Y_0 := 100; Y_N := 0; VY_N := 0;
end-if
WEIGHT := MASS*GRAV
! Start values
forall(j in POS_NODES) do
setinitval(vx(j), VX_0)
setinitval(vy(j), VY_0)
end-do
forall(j in POS_NODES) do
setinitval(x(j), 5000*j/N) ! 1000*(j-1)/N)
setinitval(y(j), -100*j/N+1000)
end-do
forall(j in POS_NODES) setinitval(cLift(j), (CL_MAX+CL_MIN)/2)
! Trapezoidal discretization
forall(j in VEL_NODES) do
x(j) = x(j-1) + 0.5*(dur/N)*(vx(j) + vx(j-1))
y(j) = y(j-1) + 0.5*(dur/N)*(vy(j) + vy(j-1))
vx(j) = vx(j-1) + 0.5*(dur/N)*(vx_dot(j) + vx_dot(j-1))
vy(j) = vy(j-1) + 0.5*(dur/N)*(vy_dot(j) + vy_dot(j-1))
-100 <= vx(j); vx(j) <= 100
-100 <= vy(j); vy(j) <= 100
end-do
! Wind formulae
forall(j in POS_NODES)
if WIND=1 then ! Upward wind velocity formula
X(j) := (x(j)/R - 2.5)^2
UpAcc(j) := UM*(1-X(j))*exp(-X(j))
elif WIND = 2 then ! Horizontal wind formula
HorAcc(j) := -5*(1+arctan((y(j)-30)/10))
end-if
! Definition of bounds and auxiliary expressions
forall(j in POS_NODES) do
cLift(j) >= CL_MIN
cLift(j) <= CL_MAX
CDrag(j) := C0 + K*cLift(j)^2 ! The drag coeff. depends on the lift coeff.
if WIND=1 then
Vy(j) := vy(j) - UpAcc(j)
else
Vy(j) := vy(j)
end-if
if WIND=2 then
Vx(j) := vx(j) - HorAcc(j)
else
Vx(j) := vx(j)
end-if
Vr(j) := sqrt(Vx(j)^2 + Vy(j)^2)
Drag(j) := 0.5*CDrag(j)*RHO*SPAN*Vr(j)^2
Lift(j) := 0.5*cLift(j)*RHO*SPAN*Vr(j)^2
sin_eta(j) := Vy(j)/Vr(j)
cos_eta(j) := Vx(j)/Vr(j)
vx_dot(j) is_free
vy_dot(j) is_free
end-do
dur >= 10; dur <= 200
! Initial and final states
x(0) = X_0
y(0) = Y_0
vx(0) = VX_0 - if(WIND=2, 2.5*(1+arctan((Y_0-30)/10)), 0)
vy(0) = VY_0
y(N) = Y_N !or: >=
vx(N) = VX_N !or: >=
vy(N) = VY_N !or: >=
! Equations of motion: F = m*a
! (eta denotes the angle between Vr and the horizontal plane)
forall(j in VEL_NODES) do
newt_x(j) := vx_dot(j) = (-Lift(j)*sin_eta(j) - Drag(j)*cos_eta(j))/MASS
newt_y(j) := vy_dot(j) = (Lift(j)*cos_eta(j) - Drag(j)*sin_eta(j) - WEIGHT)/MASS
end-do
! Monotonicity condition
forall(j in VEL_NODES) x(j) >= x(j-1)
! Limit velocity to levels that are supportable for the pilot
forall(j in POS_NODES) do
-3 <= vx_dot(j); vx_dot(j) <= 3
-3 <= vy_dot(j); vy_dot(j) <= 3
end-do
! Setting up and solving the problem
setparam("xnlp_verbose", true)
! Check the presence of Knitro; this example needs the interior point solver
if hasfeature("XPKNTLib") then
setparam("xnlp_solver", 1) ! Preselect Knitro as solver
else
writeln("This example requires Knitro")
exit(1)
end-if
maximize(x(N))
!**** Solution display ****
! Test whether a solution is available
nlstat:=getparam("XNLP_STATUS")
if nlstat<>XNLP_STATUS_LOCALLY_OPTIMAL and nlstat<>XNLP_STATUS_OPTIMAL then
writeln("No solution found.")
exit(0)
end-if
declarations
xsol, ysol: array(POS_NODES) of real
end-declarations
svgaddgroup("plotw", "Wind", SVG_RED)
svgaddgroup("msg", "Text", SVG_BLACK)
if WIND=1 then
svgaddline("plotw", sum(i in 0..1000) [i, 100*(UM*(1-(i/R - 2.5)^2)*exp(-(i/R - 2.5)^2))])
elif WIND=2 then
svgaddline("plotw", sum(i in 0..1000)[i, 100*(-5*(1+arctan((i-30)/10)))])
else
svgaddrectangle("plotw", 50,50,50,25)
svgaddtext("plotw", 75,100,"No Wind")
end-if
svgsetgraphlabels("Distance", "Force of wind")
svgsave("gliderwind.svg")
svgrefresh
! Uncomment this line to pause after first graphic
svgpause
! Closing the graphical display will interrupt the model execution
if svgclosing then exit(0); end-if
svgerase
forall(i in POS_NODES) do
xsol(i) := getsol(x(i))
ysol(i) := getsol(y(i))
writeln("xy(",i,") = (", getsol(x(i)), ",", getsol(y(i)), ")")
end-do
writeln("Max distance flown: ", xsol(N))
writeln("Total flight time : ", getsol(dur))
svgaddgroup("plot1", "Glider trajectory", SVG_BLUE)
forall (i in POS_NODES) svgaddpoint(xsol(i), 10*ysol(i))
svgaddline(sum(i in POS_NODES) [ xsol(i),10*ysol(i)])
svgsetgraphlabels("Distance", "Height")
svgsave("glidertraj.svg")
svgrefresh
svgwaitclose("Close browser window to terminate model execution.", 1)
end-model
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