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Post by Br. Marius on Mar 5, 2015 18:28:37 GMT
The blade flapping equation in hover is given as follows, where \(\Delta\theta\) is the pitch actuation caused by a feedback system in the form of \(\Delta\theta=\beta_{3c}cos(3\psi)\). Using Fourier coordinate transformation convert these equations into the fixed frame coordinates for a 4-bladed rotor.
\(\ddot{\beta}+\frac{\gamma}{8}\dot{\beta}+\nu_{\beta}^2\beta=\frac{\gamma}{8}\Delta\theta-\frac{\gamma}{6}\lambda\)
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Post by Deleted on Mar 9, 2015 12:58:11 GMT
This is what I have so far for problem 2. Was unsure how to approach the feedback system in the governing equation. How are you guys dealing with it and if possible why? |
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Post by Br. Marius on Mar 10, 2015 0:43:01 GMT
Right now I'm treating \(\beta_{3c}\) as a constant in the pitch input term (because it is) which leaves me with \(\Sigma cos(3\psi)\). In the b0 equation, that goes to zero because of the relations in equation 2.90 of the notes. Haven't gotten to the others yet, but I'll see what happens when I do.
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Post by Deleted on Mar 10, 2015 16:02:41 GMT
Thanks for the response. I ended up doing the same and this is the equations that I got. |
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Post by Deleted on Mar 10, 2015 16:20:22 GMT
Yep, same thing I got. Though looks like there are some minor typos in the first and last equations where the flap frequency isn't squared.
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Post by Br. Marius on Mar 10, 2015 18:54:16 GMT
Same here too. I like it when we all agree.
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