| 摘要 |
PCT No. PCT/FR95/00033 Sec. 371 Date Jul. 1, 1996 Sec. 102(e) Date Jul. 1, 1996 PCT Filed Jan. 11, 1995 PCT Pub. No. WO95/19592 PCT Pub. Date Jul. 20, 1995The invention relates to novel basic architecture for helicopter autopilots, transforming the conventional objective of maintaining fuselage trim to an objective of maintaining airspeed, and without making use of coupler techniques. On each of the pitch and roll control systems, a known fraction of the output signal (24S) from the flight control is injected by being summed with the standard fuselage trim input (1S). The signal (4S) formed in this way possesses the novel static and dynamic properties required for the control loop to make the helicopter statically stable in speed throughout its flight envelope. The novel architecture makes it possible to replace the conventional fuselage trim signal (1S) with an accelerometer signal. The signal (4S) is displayed in particular on a standard "artificial horizon" type instrument (33), thereby making it possible simultaneously to monitor rapid variations of fuselage trim and to control airspeeds.
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