Abstract
A non-dimensional optimization model was established for endo atmospheric hypersonic vehicles, and an enhanced adjoint method for solving the two-point boundary value problem was proposed with its algorithm convergence proved. The method was applied to the solution trajectory optimization problems in the ascent phase when a solid rocket powered hypersonic spacecraft flies in the dense atmosphere. With the bending moment constraints, a set of smooth control variables were obtained indirectly. The simulation results were presented, demonstrating rapidity, effectiveness and reliability of this method.
| Original language | English |
|---|---|
| Pages (from-to) | 273-276 |
| Number of pages | 4 |
| Journal | Guti Huojian Jishu/Journal of Solid Rocket Technology |
| Volume | 34 |
| Issue number | 3 |
| State | Published - Jun 2011 |
| Externally published | Yes |
Keywords
- Adjoint method
- Bending moment constraints
- Endoatmospheric flight
- Hypersonic vehicles
- Trajectory optimization
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