Abstract
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) |
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Pages (from-to) | 59-70 |
Number of pages | 12 |
Journal | IEEE Transactions on Aerospace and Electronic Systems |
Volume | AES-19 |
Issue number | 1 |
DOIs | |
State | Published - Jan 1983 |
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Electrical and Electronic Engineering