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Flight control system employing complementary filter
| Details |
Inventors: Klein, Robert W.;
Assignee: Grumman Aerospace Corporation (Bethpage, NY)
Primary Examiner: Barefoot; Galen
Assistant Examiner:
Attorney, Agent or Firm: Pollock, VandeSande & Priddy
Strake, flap and canard control surfaces of an aircraft are driven by an error signal which is comprised of a pilot stick command signal and feedback components including measured vertical acceleration and pitch rate of the aircraft and a third feedback component derived from a complementary filter. The filter has a high-pass filter section which operates upon canard position data and a low-pass filter section which operates upon pitch rate. A summation of the signals passing both filtering sections is summed with the vertical acceleration and pitch rate feedback signals to form a combined feedback signal. |
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DETAILED DESCRIPTION OF THE INVENTION FIG.
1 schematically illustrates an aircraft 1 having a control surface 2, which may be a canard, such as employed in the X-29 jet aircraft.
An actuator 3 variably positions the control surface 2 by conventional means.
A flight control digital computer 4 of known design includes a number of inputs including a pilot command input and data inputs from accelerometers and gyros, collectively referred to by reference numeral 5.
Thus far, the system described employs conventional components and subsystems to achieve flight control of a control surface.
However, the present invention incorporates position data from the control surface itself, which serves as an additional input 6 to digital computer 4 which, in accordance with the present invention, must perform a complementary filtering function, as will be explained hereinafter.
FIG.
2 is a basic schematic illustration of digital computer 4 which is seen to include the necessary memory and control for achieving the function of a complementary filter 7.
By being provided with canard position data as well as pitch rate data, the complementary filter 7 estimates pitch acceleration; further, the filter simultaneously reduces flight control system noise and improves aircraft stability margins.
An implementation of the present invention is illustrated in FIG.
3.
The flight control circuit illustrated drives a strake actuator 8, flap 9, and canard 10 of the aircraft 1, which was schematically illustrated in FIG.
1 and indicated as a block in FIG.
3, with a corresponding numeral 1.
A pilot command signal on input line 38 is a pilot stick signal (K.
sub.
.
gamma.
) which is multiplied in amplifier 40 by a gain.
The resulting amplified signal is fed to difference point 28 where a number of feedback signals are subtracted from the amplified stick signal.
These feedback signals include vertical acceleration n.
sub.
z, which is detected along output line 70 of a conventional aircraft accelerometer (not shown) followed by amplification in amplifier 30 by a gain factor K
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Gutter-related 
