onehundred , rispondendo alla provocazione che diceva che mi fossi inventato tutto , ho risposto che per quel che mi riguarda allora anche cio' che ha scritto lui non ha altresí prove , nomi e cognomi (che io ho poi citato) , che fungano da prova.
Taita , leggitelo.
Autopilot F-104
The automatic flight control system (AFCS) consists of the stability augmentation, autopilot, and automatic pitch control equipment. Through this equipment, the AFCS provides the airplane with automatic stability augmentation about all three-flight axis, autopilot control through aileron and stabilizer to various references, and automatic pitch- up control of the pitch axis.
The stability augmentation system provides maximum stability of the F-104 in any flight attitude or manoeuvre. Rate-sensing gyros detect any sudden change of attitude about the aircraft’s three axis and produce electrical signals proportional to the deviation they have detected. These signals, after being amplified, are send to the proper control surface servo valve which produces the proportional surface adjustment to correct the attitude.
A synchronous transmitter on the servo valve supplies a feedback signal, which cancels the original signal causing any oscillation to be damped.
The trim system is powered and controlled electrically, and the trim actuator output is connected mechanically to its respective servo valve input arm. Energizing the actuator causes the input arm to change position, thereby changing the position of the control surface. In each case, the amount of trim selected limits surface movement in that direction by the same amount. Movement of the servo input linkages by the trim actuators causes deflection of the control surfaces to the trimmed position, but does not affect cockpit control stick and rudder neutral positions. A toggle switch located on the control stick grip, and an auxiliary switch located on the left console are used to control the aileron and stabilizer trim actuators. A three-position toggle switch on the left console is used to adjust rudder trim. Lights are provided to indicate take-off trim positions of the control surfaces. In flight, only the aileron take-off trim light provides an indication of control surface trim. Electro-mechanical actuators position the wing leading and trailing edge flaps. A flexible shaft interconnects the drive motors for each wing to synchronize the flaps and enable one motor to drive both flaps should the other malfunction. The flaps have three pre-set positions: Up, which is zero degrees deflection, or the faired position for the trailing edge flaps, and 3°downward deflection for the leading edge flaps; intermediate position, which is 15° downward deflection for both leading and trailing edge flaps, and is used for take-off or manoeuvring flight; and Land which is 45° downward deflection for the trailing edge flaps, and 30° downward deflection for the leading edge flaps.
Speed brakes, installed on each side of the fuselage aft of the wings, provide a means of reducing airplane speed in flight.
The two speed brakes are hydraulically powered and electrically controlled. They operate in synchronisation, and the pilot may select any position between ”full open” and ”full closed ”.
In event of loss of electrical power should occur, the brakes would close automatically. No position indication is provided.
che l'A\P non funzionava
L'A/P aveva questo difetto , delle volte si sganciava senza preavviso.E' sicuramente perchè non hai avuto modo di conoscere Petrini , che te ne avrebbe parlato dato che è successo a lui personalmente.