Helicopter force feel actuator automatic static null compensation

• US 4,382,281 A
• Filed: 08/08/1980
• Issued: 05/03/1983
• Est. Priority Date: 08/08/1980
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Fowler, Donald W., Clelford, Douglas H., Brand, Raymond J.
• Primary Examiner(s): Chin, Gary
• Application Number:
  US06/176,833
• Time in Patent Office: 998 Days
• Field of Search: 364/424, 364/571, 244/178, 244/194, 244/223, 244/17.13, 318/628
• US Class Current: 701/3
• CPC Class Codes: G05D 1/0061 for transition from automatic pilot to manual pilot and vice versa
• CPC Class Codes: G05D 1/0858 specially adapted for vertical take-off of aircraft

Abstract

A bias voltage, which can be added to force commands applied to a helicopter control stick actuator, to compensate for static null offset errors, is generated as the average of the summation or integral of actuator pressure, or pressure differential, sensed while the force is moved from a first position which is halfway aft through null to a second position which is halfway forward and back through null to the first position, the pressure readings which are averaged being taken only through the central portion of the motion, the motion being controlled to be extremely slow compared to normal permissible stick motion.

Claims

1. An aircraft control stick actuator system comprising:

a servo valve controlled hydraulic actuator connected to the control stick and operable to provide forces to the stick of a magnitude and direction proportional to electric signals provided to said servo valve;

pressure sensor means connected to said hydraulic force actuator to provide a pressure signal indicative of the force applied to said control stick;

means providing a position signal indicative of the position of the control stick;

means providing an aircraft on ground signal in response to the aircraft being on the ground;

means for providing a force nulling signal when control stick force feel actuator null offset error compensation bias is desired to be generated; and

signal processing means operative in response to presence of said aircraft on ground signal and said force nulling signal, for providing to said servo valve, in response to said position signal, desired stick position command signals to cause the control stick to move from a first position which is a significant fraction of control stick authority in one direction through null to a second position which is a significant fraction of control stick authority in a second direction and thence back through null to said first position, and responsive to said position signal and said pressure signal during a significant portion of control stick motion between said first and second positions for providing a static null signal which is indicative of the average pressure represented by the pressure signal during said significant portion of control stick motion.

2. A force feel actuator system according to claim 1 wherein said signal processing means provides said desired stick position command signals in a manner to cause the control stick to move between said first and second positions at a rate which is very small in comparison with the normal rate of permissible stick motion.