Propeller blade position controller

• US 5,150,855 A
• Filed: 10/19/1990
• Issued: 09/29/1992
• Est. Priority Date: 10/20/1989
• Status: Expired due to Fees

• Current Assignee: Fokker Aircraft, B.V.
• Original Assignee: Fokker Aircraft B.C.
• Inventors: Kaptein, Dick
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US07/600,445
• Time in Patent Office: 711 Days
• Field of Search: 244/1 N, 244/118.5, 244/129.1, 416/33, 416/34, 416/50, 381/71, 181/206, 364/574, 364/508, 364/474.22, 364/431.01, 364/494, 415/119, 60/39.21, 60/281
• US Class Current: 244/1.00N
• CPC Class Codes: B64C 11/50 Phase synchronisation between multiple propellers
• CPC Class Codes: G10K 11/175 using interference effects; Masking sound

Abstract

System for reducing vibrations in the cabin of an aircraft driven by two or more propellers each having n blades (n being an integer equal or larger than 2) of which the relative phase angle can be adjusted, said system comprising synchrophase means for adjusting said relative phase angle such that a predetermined relative phase angle is maintained. The system furthermore comprises means supplying information about the vibration level at one or more positions within the cabin or thereto related information and for generating a thereto corresponding level signal, and a control unit which in response to said level signal supplies an error signal to the synchrophase means causing the synchrophase means to adjust the blades of the various propellers such that a new relative phase angle is maintained which differs m.(2π/n) radians (m being an integer) from the previous relative phase angle.

Claims

1. A method of reducing vibrations in the cabin of an aircraft driven by a plurality of propellers each having n blades, n being a plural integer, wherein said propellers have a relative phase angle which can be adjusted, the method comprising the steps of:

a) measuring the vibration level at one or more positions within the cabin and generating a vibration level signal corresponding thereto;

b) evaluating an error signal in response to said vibration level signal;

c) optimizing the relative phase angle of the propellers in response to said error signal to a first value at which said measured vibration level is reduced;

d) shifting said propellers relatively through 2π

/n radians to a new relative phase angle where said propellers are substantially in phase and have new relative blade positions;

e) optimizing said new relative phase angle in response to a corresponding vibration level error signal to a second value at which said measured vibration level is reduced; and

f) selecting between said first and second values for improved vibration reduction in the cabin.

2. A method according to claim 1, wherein said propellers each have m blades and wherein steps d) and e) are repeated to generate m optimized relative phase angle values for each of said m blades, step f) being performed to select between all said m values.

3. A method according to claim 2, wherein m is six.

4. A method according to claim 1 which comprises:

comparing said vibration level signal with a prefixed reference value during flight conditions;

evaluating said error signal according to the difference between said vibration level signal and said prefixed reference value;

performing step d) when said error signal exceeds a predetermined threshold value; and

measuring the vibration level again; and

repeating the former steps until said error signal does not exceed said threshold value anymore.

5. A method according to claim 4 performed on an aircraft having four propellers wherein said propellers each have six blades and wherein steps d) and e) are repeated to generate six optimized relative phase angle values one for each of said six blades, steps f) being performed to select between all said six values.