Abstract
A non-linear mathematical model for coaxial helicopter flight dynamics is established based on the development of a simplified and practical coaxial contra-rotating twin rotor loads model. The mathematical model is used to calculate trims in the steady straight level flight and dynamic responses to different control inputs for the sample coaxial helicopter made in BUAA. The results of trim computation are well in agreement with the data provided from Russia. Numerical simulations show that the non-linear mathematical model captures the motion trend of the sample coaxial helicopter correctly. The correctness of the model is preliminarily validated.
| Original language | English |
|---|---|
| Pages (from-to) | 293-295 |
| Number of pages | 3 |
| Journal | Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica |
| Volume | 24 |
| Issue number | 4 |
| State | Published - Jul 2003 |
Keywords
- Coaxial helicopter
- Flight dynamics
- Helicopter
- Rotor aerodynamics
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