Abstract
Unsteady heat input effects are considered for the range cruise of a future hypersonic vehicle equipped with a turbo/ram jet engines combination. A realistic mathematical model for describing the unsteady heat effects has been developed. It is coupled to the model for the dynamics of the vehicle. To compute the heat load in hypersonic flight, several points on the vehicle surface are treated simultaneously. A two-step technique consisting of an efficient optimization algorithm and an ordinary differential equations (ODE) solver is applied to generate a solution. The results show that the heat load can be significantly reduced, with only a small increase in fuel consumption.
| Original language | English |
|---|---|
| Pages (from-to) | 307-313 |
| Number of pages | 7 |
| Journal | Asian Journal of Control |
| Volume | 8 |
| Issue number | 4 |
| DOIs | |
| State | Published - Dec 2006 |
Keywords
- Hypersonic vehicle
- Optimal control
- Thermal protection system
- Trajectory optimization
- Unsteady heat effects