Apparatus for improving the longitudinal or pitching stability of aircraft

• US 4,607,201 A
• Filed: 08/27/1985
• Issued: 08/19/1986
• Est. Priority Date: 08/28/1984
• Status: Expired due to Fees

• Current Assignee: Eurocopter Deutschland Gesellschaft Mit Beschrã¤Nkter Haftung (European Aeronautic Defence and Space Company EADS NV)
• Original Assignee: Messerschmitt-Boelkow-Blohm GmbH (Mercedes-Benz Group AG)
• Inventors: Koenig, Herbert
• Primary Examiner(s): Dobeck, B.
• Application Number:
  US06/769,875
• Time in Patent Office: 357 Days
• Field of Search: 318/584, 318/585, 318/586, 318/580, 318/611, 318/615, 318/616, 318/617, 244/181, 244/220, 244/221, 244/225, 244/228
• US Class Current: 318/584
• CPC Class Codes: G05D 1/0061 for transition from automatic pilot to manual pilot and vice versa
• CPC Class Codes: G05D 1/0816 to ensure stability

Abstract

The control of the longitudinal or pitching stability of aircraft is imprd by providing a corrected control characteristic for the correction adjustment drive which is interposed between the pilot operated control stick and the main control drive, for example for the blade angle adjustment in a helicopter or for the elevator adjustment in fixed wing aircraft. A control linkage (2) is connected on one end to a main control drive (4) for the elevator or rotor blade adjustment and at its other end to the control stick (1). The correction adjustment drive (3) is interposed in the control linkage (2). A displacement pickup (5) measures the control displacement of the control linkage (2) and a flight speed pickup (6) measures the flight speed. To improve the control of the longitudinal or pitching stability without having the corrected control displacements of the control stick (1) become too large, a delay circuit (7) and first differentiating circuit (8) are serially connected downstream of the displacement pickup (5). A second differentiating circuit (9) and a linear amplifier (10) are serially connected downstream of the flight speed pickup (6). A first summing circuit (11) subtracts the output signal of the amplifier (10) from that of the first differentiating element (8). An integrator (13) connected with its output to the correction adjustment drive (3) is connected with its input through a switch (12) to the summing circuit (11). A logic circuit (14) controls a switch (12) so that the switch (12) is closed as soon as the gradient of the function D_T (v), where D_T is the output signal of the delay circuit (7) and v is the flight speed, falls below the amplification factor G of the amplifier (10).

Claims

1. In an apparatus for improving the control of the longitudinal or pitching stability of an aircraft, especially of helicopters, wherein a control linkage is operatively connected at one end to a main control drive (4) for the adjustment of elevator means or of rotor blades, and at the other end to a control stick for said main control drive;

wherein a correction adjustment drive is interposed in the control linkage for lengthening the control linkage in a controlled manner;

the improvement comprising;

displacement pickup means (5) for sensing a control displacement between said correction adjustment drive (3) and said main control drive (4) to provide a displacement representing first signal, flight speed pickup means (6) for sensing the flight speed to provide a speed representing second signal, signal delay means (7) for said first signal from said displacement pickup means (5), first signal differentiating means (8) connected serially to said signal delay means (7) for differentiating the delayed first signal, second differentiating circuit means (9) serially connected to said flight speed pickup means (6) for differentiating said second signal, a linear amplifier (10) serially connected to said second differentiating circuit means (9), first summing circuit means (11) connected for subtracting the output signal of said linear amplifier (10) from the signal provided by said first differentiating circuit means (8), signal integrator circuit means (13), switch means (12) connecting said signal integrator circuit means serially to said first summing circuit means (11), means operatively connecting said correction adjustment drive (3) to said signal integrator circuit means (13), and switch controlling logic circuit means (14) operatively arranged for closing said switch means (12) as soon as a gradient of a function D_T (v), where D_T =the delayed control displacement first signal at the output of said delay means, and wherein v =flight speed, falls below a specifiable limiting value which is identical to an amplification factor G of said linear amplifier (10).

2. The apparatus of claim 1, wherein said controlling logic circuit means (14) comprise a first multiplier (20) connected to receive said differentiated first and second signals from the first and second signal differentiating circuit means (8 and 9), a second multiplier (19) connected to receive the output signals from the second differentiating circuit means (9) and from said linear amplifier (10), a second signal summing circuit means (21) connected for subtracting a product signal of said second multiplier (19) from that of said first multiplier (20), and a switching logic circuit means (22) for closing said switch (12) in response to a negative summation signal from said second signal summing circuit means (21).

3. The apparatus of claim 2, further comprising an amplifier (15) connected serially between an output of said signal integrator circuit means (13) and said control adjustment drive (3).

4. The apparatus of claim 1, further comprising an amplifier (15) connected serially between an output of said signal integrator circuit means (13) and said control adjustment drive (3).