The initial control laws for the X-29A used equally weighted sources from a single nose boom and two side probes. [^1] These 3 sources gave total pressure measurements. [^1] Strong forebody vortices caused up to -1.5 inHg errors in the side probes in which the aircraft was actually traveling faster than indicated. [^1] This was fixed by adding a 1.5 inHg bias to the side probes as the sensitivity to the high gain was larger than the low gain. [^1] The AOA was used as a primary gain scheduling parameter and feedback to longitudinal and lateral axes.[^1]
Sources
- R. Clarke, J. J. Burken, J. T. Bosworth, and J. E. Bauer, “X-29 Flight Control System: Lessons Learned”.
Backlinks
Air-Data Sensors
[[Angle of Attack]]
Angle of Attack Sensors
Gain Scheduling
X-29 Flight Control System
[[X-29A]]