Effects of yaw and pitch motion on model attitude measurements
Abstract
This report presents a theoretical analysis of the dynamic effects of angular motion in yaw and pitch on model attitude measurements in which inertial sensors were used during wind tunnel tests. A technique is developed to reduce the error caused by these effects. The analysis shows that a 20-to-1 reduction in model attitude measurement error caused by angular motion is possible with this technique.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- February 1995
- Bibcode:
- 1995STIN...9522109T
- Keywords:
-
- Aircraft Models;
- Angular Velocity;
- Computational Fluid Dynamics;
- Dimensional Measurement;
- Dynamic Response;
- Mathematical Models;
- Pitching Moments;
- Wind Tunnel Tests;
- Yaw;
- Angle Of Attack;
- Approximation;
- Error Correcting Devices;
- Fast Fourier Transformations;
- Inertia;
- Sensors;
- Instrumentation and Photography