Measuring Moment of Inertia of RC Helicopter

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Discussion Overview

The discussion focuses on measuring the moment of inertia of a remote-controlled helicopter about its three principal axes at the center of gravity. Participants explore experimental setups and methods for accurately determining this property, including the use of gyros and accelerometers for measurement.

Discussion Character

  • Exploratory
  • Technical explanation
  • Experimental/applied

Main Points Raised

  • One participant outlines equations relating angular accelerations to moments about each axis and moments of inertia, emphasizing the need for an experimental method.
  • Another participant suggests that measuring the principal axes can be done via a referenced article, indicating that the method may not be straightforward but is feasible.
  • A later post mentions the availability of additional resources from Space Electronics that could assist in measuring properties like moment of inertia and center of gravity.

Areas of Agreement / Disagreement

Participants do not reach a consensus on the best experimental method, and multiple approaches are discussed without resolution on which is superior.

Contextual Notes

The discussion does not clarify the specific assumptions or limitations of the proposed methods, nor does it resolve the uncertainties regarding the torque applied to the helicopter during measurements.

williamshipman
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Hi guys.

I am trying to measure the moment of inertia of a remote controlled helicopter about its 3 principle axes at the centre of gravity. In all of the literature I have read relating to this project, everyone just glosses over this part. What I need to figure out is an experimental setup and method.

I have the following 3 equations that relate the moment about each axis and the 3 angular velocities to the angular accelerations. All of these equations are with respect a fixed axis system centred at the centre of gravity.
p_dot=M_x/I_xx -rq/I_xx (I_zz-I_yy )
q_dot=M_y/I_yy -rp/I_yy (I_xx-I_zz )
r_dot=M_z/I_zz -pq/I_zz (I_yy-I_xx )

p_dot, q_dot and r_dot are the angular accelerations. The angular velocities are p (roll), q (pitch) and r (yaw). The moments about each axis are M_x, M_y and M_z and the moments of inertia are I_xx, I_yy and I_zz.

So far, I have thought of putting the helicopter on a table and rotating it about one axis, then repeating the procedure for the other 2 axes. This has the small problem that, if the table rotates at a constant rate, the dot terms are zero. If the table is accelerating, then this could work but how would I know what the torque applied to the helicopter is?

I forgot to mention, the helicopter will be fitted with gyros to measure the orientation and accelerometers for the linear and angular accelerations. Thanks for your help.
 
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It's not the easiest way to do things, but it is definitely doable. I guess it all boils down to how accurate you want to get. You can measure the principal axes via the method in the attached article. The off diagonal elements you can then calculate.

Go to this thread for the article:
https://www.physicsforums.com/showthread.php?t=222753
 


Thanks very much for the info Fred, that was exactly what I was looking for.
 


Its now a few months later and I thought I'd post this. FredGarvin gave a paper from Space Electronics in the other thread he links to. Space Electronics has published a number of other papers on their website that explain how to measure various properties, like the moment of inertia and center of gravity. Anyone who is struggling with such work should look at their website http://www.space-electronics.com" .
 
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