Hang Glider: Difference between revisions
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! Symbol !! Value !! Description | ! Symbol !! Value !! Description | ||
|- | |- | ||
| align=center | <math> | | align=center | <math>x_0</math> || align=right | 0 || Initial horizontal position | ||
|- | |- | ||
| align=center | <math> | | align=center | <math>y_0</math> || align=right | 1000 || Initial altitude | ||
|- | |- | ||
| align=center | <math> | | align=center | <math>y_f</math> || align=right | 900 || Final altitude | ||
|- | |- | ||
| align=center | <math> | | align=center | <math>v_{x,0}</math> || align=right | 13.23 || Initial horizontal velocity | ||
|- | |||
| align=center | <math>v_{x,f}</math> || align=right | 13.23 || Final horizontal velocity | |||
|- | |||
| align=center | <math>v_{y,0}</math> || align=right | -1.288 || Initial vertical velocity | |||
|- | |||
| align=center | <math>v_{y,f}</math> || align=right | -1.288 || Final vertical velocity | |||
|- | |||
| align=center | <math>u_c</math> || align=right | 2.5 || | |||
|- | |||
| align=center | <math>r_c</math> || align=right | 100 || | |||
|- | |||
| align=center | <math>c_0</math> || align=right | 0.034 || | |||
|- | |||
| align=center | <math>c_1</math> || align=right | 0.069662 || | |||
|- | |||
| align=center | <math>S</math> || align=right | 14 || Wing area | |||
|- | |||
| align=center | <math>\rho</math> || align=right | 1.13 || Air density | |||
|- | |||
| align=center | <math>m</math> || align=right | 100 || Mass of the glider | |||
|- | |||
| align=center | <math>g</math> || align=right | 9.81 || Gravitational constant | |||
|} | |} | ||
Revision as of 10:05, 25 November 2025
| Hang Glider | |
|---|---|
| State dimension: | 1 |
| Differential states: | 4 |
| Discrete control functions: | 2 |
The Hang Glider problem is a classical benchmark in optimal control. This description is taken from [1].
It consists of steering a hang glider from an initial horizontal position and altitude to a target altitude while maximising the horizontal distance travelled. The glider dynamics incorporate lift, drag, gravity, and the effect of a thermal updraft. The control variable is the lift coefficient , which modulates the aerodynamic lift and influences the trajectory through the thermal region.
Mathematical formulation
with the auxiliary equations:
Parameters
These fixed values are used within the model:
| Symbol | Value | Description |
|---|---|---|
| 0 | Initial horizontal position | |
| 1000 | Initial altitude | |
| 900 | Final altitude | |
| 13.23 | Initial horizontal velocity | |
| 13.23 | Final horizontal velocity | |
| -1.288 | Initial vertical velocity | |
| -1.288 | Final vertical velocity | |
| 2.5 | ||
| 100 | ||
| 0.034 | ||
| 0.069662 | ||
| 14 | Wing area | |
| 1.13 | Air density | |
| 100 | Mass of the glider | |
| 9.81 | Gravitational constant |
Reference Solutions
Here is one local solution to the above control problem.
- Reference solution plots
-
States and discretized control for a local optimum.
Miscellaneous and Further Reading
This formulation and a detailed description can be found in [1].
References
[1] Caillau, J.-B., Cots, O., Gergaud, J., & Martinon, P. OptimalControlProblems.jl: a collection of optimal control problems with ODE's in Julia. https://github.com/control-toolbox/OptimalControlProblems.jl/blob/main/ext/Descriptions/robbins.md