Rotor control system

• US 4,678,401 A
• Filed: 01/24/1986
• Issued: 07/07/1987
• Est. Priority Date: 01/24/1986
• Status: Expired due to Fees

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Maciolek, Joseph R., Bradford, Michael P.
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US06/822,353
• Time in Patent Office: 529 Days
• Field of Search: 416/32, 416/143, 416/169 R, 416/170 B, 244/7 R, 244/7 A, 244/17.11, 244/17.13
• US Class Current: 416/32
• CPC Class Codes: B64C 27/24 with rotor blades fixed in flight to act as lifting surfaces
• CPC Class Codes: B64C 27/50 Blades foldable to facilitate stowage of aircraft

Abstract

A helicopter rotor control system (13) including a stop azimuth controller (32) for establishing the value of a deceleration command (15'"'"') to a deceleration controller (23), a transition azimuth predictor (41) and a position reference generator (55), which are effective during the last revolution of said rotor (14) to establish a correction indication (38) to adjust the deceleration command (15'"'"') to ensure that one of the rotor blades (27) stops at a predetermined angular position.

Claims

1. A control system for slowing the angular velocity and halting the rotary motion of a helicopter rotor at a selected azimuth position with a rotor brake, said rotor including a plurality of blades for rotatably carrying said helicopter, said control system comprising a deceleration controller for controlling the operation of the rotor brake, a deceleration command means for establishing a deceleration command indication for directing the operation of said deceleration controller, a detection means for establishing motion indications of said helicopter rotor, said indications including velocity and position indications, said detection means being responsive to the motion of said helicopter, a feedback means for differentiating said velocity indication to establish a deceleration value of the rotor, and means for reducing said deceleration command indication by the amount of said deceleration value and providing the difference to said deceleration controller, wherein said control system is characterized in that it further comprises means for determining a predicted stop azimuth position of said rotor, and adjustment means for adjustment of the value of said predicted stop azimuth position to a selected stop azimuth.

2. The control system of claim 1, further characterized in that it comprises a means for predicting a stop value of a selected one of said blades in view of the current deceleration and velocity of said rotor, and a position reference generator producing an indication of the closest one of a number of discrete, equally spaced angular values corresponding to the number of blades on said helicopter, said closest one of said angular values being closer to the predicted stop value for said selected blade, than any other of said angular values.

3. The control system of claim 2, characterized in that the difference between said predicted stop value and said closest one of said angular values establishes a position error for adjusting said deceleration command value.

4. The control system of claim 1, characterized in that said deceleration command is adjusted only during the time of last rotation of said rotor before coming to a halt.