HammerUK9 Posted December 25, 2020 Posted December 25, 2020 Merry Christmas all! Just threw a quick graph together based on the Evaluation data - I'm assuming it's a straight addition onto the breakout force. On 11/19/2020 at 7:06 AM, Curly said: This also changes depending on the flap setting. 2.5 inches forward and 3.5 aft in half and full. What's your source for this? I haven't seen it mentioned anywhere else including NATOPS.
Curly Posted December 25, 2020 Posted December 25, 2020 3 hours ago, HammerUK9 said: What's your source for this? I haven't seen it mentioned anywhere else including NATOPS. The 570-100 PRINCIPLES OF OPERATION INTEGRATED FLIGHT CONTROLS NAVY MODEL F/A-18A/B/C/D 161353 AND UP
HammerUK9 Posted December 25, 2020 Posted December 25, 2020 11 hours ago, Curly said: The 570-100 PRINCIPLES OF OPERATION INTEGRATED FLIGHT CONTROLS NAVY MODEL F/A-18A/B/C/D 161353 AND UP That a publicly available doc that a non-American is allowed to read?
HammerUK9 Posted December 28, 2020 Posted December 28, 2020 Found this elsewhere on the DCS forum (quite by chance!) "71. Not Auto Flaps Up Operation. Pitch stick command and pitch trim bias are the pitch command inputs used during control augmentation system (CAS) operation. WITH ROLL-PITCH-YAW COMPUTER CONFIG/IDENT 99 AND UP (A1-F18AC-SCM-000), pitch stick command is limited to 2.5 inches forward and 3.55 inches aft. A trim up or trim down command causes the pitch trim bias to be supplied to the pitch trim integrator. The pitch trim integrator sums the pitch trim bias with the integrator’s previous output to produce the pitch trim integrator signal. Pitch trim integrator signal is limited to 0° trailing edge down and 12° trailing edge up. Pitch outer loop command (if required, refer to WP029 01) and pitch stick command during automatic carrier landing (ACL) operation (if required, refer to WP029 01), are the pitch command inputs during autopilot operation. I'm presuming that's a hardware rather than a software-induced limit?
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