This control system used an AOA bias of \(8.9deg\) as well as an increased lateral stick to rudder interconnect gain of 3.19.[1] The stick-to-differential-tail gain was increased by moving the \(\alpha\) breakpoints from \(14deg\) to \(40deg\) and from \(17deg\) to \(43deg\). The roll-rate damper was increased from 4.0-5.0. Pilots reported a possible PIO condition due to the high controller gains.[1]
The higher LSRI gain had a slightly higher yaw rate magnitude compared to control system B, but otherwise similar performance.[1]
Sources
- _19820005275
Backlinks
[[Control Surface Rate LImits]]
[[F-14 ARI]]
[[F-14 ARI Control System B]]
Pilot-Induced Oscillations