Accurate data are necessary for the identification of aerodynamic parameters at high angle of attack and in spinning flight. Modern sensors and microelectronic devices are employed in a stall/ spin data acquisition system that will be tested in a Schweizer 2-32 sailplane. This instrumentation package will use a quaternion-based “strapdown IMU” algorithm to derive vehicle attitude from angular rate data, and it will use fault-detection logic to identify inflight sensor failures. Details of the system and flight test program are presented, together with results of preflight digital simulation analysis.
|Original language||English (US)|
|Number of pages||12|
|Journal||IEEE Transactions on Aerospace and Electronic Systems|
|State||Published - Jan 1 1983|
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Electrical and Electronic Engineering