Difference between revisions of "F-8 aircraft"
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== Reference solutions == | == Reference solutions == | ||
| − | The optimal objective value of this problem given in Sager 2005<bibref>Sager2005</bibref> is <math>T = 5.73406</math>. An even better solution is <math>T = 5.72865</math> that corresponds to the rightmost plot. | + | The optimal objective value of this problem given in Sager 2005<bibref>Sager2005</bibref> is <math>T = 5.73406</math>. An even better solution is <math>T = 5.72865</math> that corresponds to the rightmost plot. The optimal solution of bang-bang type switches five times, starting with <math>w(t) = 1</math>. The lengths of the six intervals of this optimal solution are |
| + | |||
| + | 0: 1.02382E-01 | ||
| + | 1: 1.92805E+00 | ||
| + | 2: 1.66460E-01 | ||
| + | 3: 2.73073E+00 | ||
| + | 4: 3.29934E-01 | ||
| + | 5: 4.71077E-01 | ||
<gallery caption="Reference solution plots" widths="240px" heights="167px" perrow="3"> | <gallery caption="Reference solution plots" widths="240px" heights="167px" perrow="3"> | ||
Revision as of 22:59, 7 November 2008
| F-8 aircraft | |
|---|---|
| State dimension: | 1 |
| Differential states: | 3 |
| Discrete control functions: | 1 |
| Interior point equalities: | 6 |
The F-8 aircraft control problem is based on a very simple aircraft model. The control problem was introduced by Kaya and Noakes in 2003<bibref>Kaya2003</bibref> and aims at controlling an aircraft in a time-optimal way from an initial state to a terminal state.
The mathematical equations form a small-scale ODE Model. The interior point equality conditions fix both initial and terminal values of the differential states.
The optimal integer control functions shows bang bang behavior. The problem is furthermore interesting as it should be reformulated equivalently.
Contents
Mathematical formulation
For ![t \in [0, T]](https://mintoc.de/images/math/e/6/6/e66a2b7fedcba80ccb192b87440f8d9c.png)
almost everywhere the mixed-integer optimal control problem is given by
![\begin{array}{llcl}
\displaystyle \min_{x, w, T} & T \\[1.5ex]
\mbox{s.t.} & \dot{x}_0 &=& -0.877 \; x_0 + x_2 - 0.088 \; x_0 \; x_2 + 0.47 \; x_0^2 - 0.019 \; x_1^2 - x_0^2 \; x_2 + 3.846 \; x_0^3 \\
&&& - 0.215 \; w + 0.28 \; x_0^2 \; w + 0.47 \; x_0 \; w^2 + 0.63 \; w^3 \\
& \dot{x}_1 &=& x_2 \\
& \dot{x}_2 &=& -4.208 \; x_0 - 0.396 \; x_2 - 0.47 \; x_0^2 - 3.564 \; x_0^3 \\
& x(0) &=& (0.4655,0,0)^T, \\
& x(T) &=& (0,0,0)^T, \\
& w(t) &\in& \{-0.05236,0.05236\}.
\end{array}](https://mintoc.de/images/math/5/8/a/58adecfe648018c173faf841aae8ef0d.png)
is the angle of attack in radians, 
is the pitch angle, 
is the pitch rate in rad/s, and the control function 
is the tail deflection angle in radians. This model goes back to Garrard<bibref>Garrard1977</bibref>.
In the control problem, both initial as terminal values of the differential states are fixed.
Reformulation
The control w(t) is restricted to take values from a finite set only. Hence, the control problem can be reformulated equivalently to
![\begin{array}{llcl}
\displaystyle \min_{x, w, T} & T \\[1.5ex]
\mbox{s.t.} & \dot{x}_0 &=& -0.877 \; x_0 + x_2 - 0.088 \; x_0 \; x_2 + 0.47 \; x_0^2 - 0.019 \; x_1^2 - x_0^2 \; x_2 + 3.846 \; x_0^3 \\
&&& - \left( 0.215 \; \xi + 0.28 \; x_0^2 \; \xi + 0.47 \; x_0 \; \xi^2 + 0.63 \; \xi^3 \right) \; w \\
&&& - \left( - 0.215 \; \xi - 0.28 \; x_0^2 \; \xi + 0.47 \; x_0 \; \xi^2 - 0.63 \; \xi^3 \right) \; (1 - w) \\
& \dot{x}_1 &=& x_2 \\
& \dot{x}_2 &=& -4.208 \; x_0 - 0.396 \; x_2 - 0.47 \; x_0^2 - 3.564 \; x_0^3 \\
& x(0) &=& (0.4655,0,0)^T, \\
& x(T) &=& (0,0,0)^T, \\
& w(t) &\in& \{0,1\},
\end{array}](https://mintoc.de/images/math/c/0/c/c0c97a4a00928a88780813123801c279.png)
with 
. Note that there is a bijection between optimal solutions of the two problems.
Reference solutions
The optimal objective value of this problem given in Sager 2005<bibref>Sager2005</bibref> is 
. An even better solution is 
that corresponds to the rightmost plot. The optimal solution of bang-bang type switches five times, starting with 
. The lengths of the six intervals of this optimal solution are
0: 1.02382E-01 1: 1.92805E+00 2: 1.66460E-01 3: 2.73073E+00 4: 3.29934E-01 5: 4.71077E-01
- Reference solution plots
Optimal relaxed control on a coarse control discretization grid and corresponding differential states.
Optimal relaxed control on a fine, adaptively chosen control discretization grid and corresponding differential states.
Optimal integer control and corresponding differential states.
Source Code
C
The differential equations in C code:
double x1 = xd[0]; double x2 = xd[1]; double x3 = xd[2]; double u0 = -0.05236; double u1 = 0.05236; double f00, f10, f20; double f01, f11, f21; f00 = - 0.877*x1 + x3 - 0.088*x1*x3 + 0.47*x1*x1 - 0.019*x2*x2 - x1*x1*x3 + 3.846*x1*x1*x1 - 0.215*u0 + 0.28*x1*x1*u0 + 0.47*x1*u0*u0 + 0.63*u0*u0*u0; f10 = x3; f20 = - 4.208*x1 - 0.396*x3 - 0.47*x1*x1 - 3.564*x1*x1*x1 - 20.967*u0 + 6.265*x1*x1*u0 + 46*x1*u0*u0 + 61.4*u0*u0*u0; f01 = - 0.877*x1 + x3 - 0.088*x1*x3 + 0.47*x1*x1 - 0.019*x2*x2 - x1*x1*x3 + 3.846*x1*x1*x1 - 0.215*u1 + 0.28*x1*x1*u1 + 0.47*x1*u1*u1 + 0.63*u1*u1*u1; f11 = x3; f21 = - 4.208*x1 - 0.396*x3 - 0.47*x1*x1 - 3.564*x1*x1*x1 -20.967*u1 + 6.265*x1*x1*u1 + 46*x1*u1*u1 + 61.4*u1*u1*u1; rhs[0] = u[0]*f01 + (1-u[0])*f00; rhs[1] = u[0]*f11 + (1-u[0])*f10; rhs[2] = u[0]*f21 + (1-u[0])*f20;
Miscellaneous and Further Reading
See <bibref>Kaya2003</bibref> and <bibref>Sager2005</bibref> for details.
References
<bibreferences/>
