Helicopter force-feel and stability augmentation system with parallel servo-actuator

• US 7,108,232 B2
• Filed: 02/05/2004
• Issued: 09/19/2006
• Est. Priority Date: 02/05/2004
• Status: Active Grant

• Current Assignee: Hoh Aeronautics, Inc.
• Original Assignee: Hoh Aeronautics, Inc.
• Inventors: Hoh, Roger H.
• Primary Examiner(s): Collins, Timothy D.
• Application Number:
  US10/772,990
• Publication Number:
  US 20050173595A1
• Time in Patent Office: 957 Days
• Field of Search: 244/220, 244/221, 244/75.R, 244/223, 244/229, 244/234
• US Class Current: 244/223
• CPC Class Codes: B64C 13/0427 for actuating trim
• CPC Class Codes: B64C 13/507 with artificial feel
• CPC Class Codes: B64C 27/56 characterised by the control initiating means, e.g. manually actuated
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A force-feel system is implemented by mechanically coupling a servo-actuator to and in parallel with a flight control system. The servo-actuator consists of an electric motor, a gearing device, and a clutch. A commanded cockpit-flight-controller position is achieved by pilot actuation of a trim-switch. The position of the cockpit-flight-controller is compared with the commanded position to form a first error which is processed by a shaping function to correlate the first error with a commanded force at the cockpit-flight-controller. The commanded force on the cockpit-flight-controller provides centering forces and improved control feel for the pilot. In an embodiment, the force-feel system is used as the basic element of stability augmentation system (SAS). The SAS provides a stabilization signal that is compared with the commanded position to form a second error signal. The first error is summed with the second error for processing by the shaping function.

Claims

1. A force-feel system for providing tactile feedback to a cockpit-flight-controller mechanically coupled to a control surface in a helicopter which does not require apparatus to be inserted into a break in an existing flight control system and which does not require a mechanical spring and a trim-motor, thereby reducing the weight and cost of a force-feel system and making it practical to implement a force-feel system and a stability augmentation system in light-weight helicopters, the system comprising:

a feedback loop around a cockpit-flight-controller, the feedback loop configured to apply a force to the cockpit-flight-controller proportional to a deflection of the cockpit-flight-controller from a first position, the feedback loop including;

a position sensor configured to measure a second position of the cockpit-flight-controller;

a flight control device coupled to the position sensor, the flight control device configured to calculate the deflection and to determine the force based on a shaping function; and

a servo-actuator mechanically connected to and in parallel with a flight control system, the servo-actuator configured to apply the force to the cockpit-flight-controller and to be back-driven by the cockpit-flight-controller.

2. The force-feel system of claim 1, further comprising an attitude sensor coupled to the flight control device to provide an indication of attitude, wherein the feedback loop is further configured to apply the force to the cockpit-flight-controller based on an attitude error.

3. The force-feel system of claim 1, wherein the position sensor is configured to measure the second position relative to the first position of the cockpit-flight-controller.

4. The force-feel system of claim 1, wherein the position sensor is configured to measure the actual position of the cockpit-flight-controller for at least one of the first position and the second position.

5. A force-feel system for providing tactile feedback to a cockpit-flight-controller mechanically coupled to a control surface in a helicopter which does not require apparatus to be inserted into a break in an existing flight control system, the system comprising:

a feedback loop around a cockpit-flight-controller, the feedback loop configured to apply a force to the cockpit-flight-controller proportional to a deflection of the cockpit-flight-controller from a first position, the feedback loop including;

a position sensor configured to measure a second position of the cockpit-flight-controller;

a flight control device coupled to the position sensor, the flight control device configured to calculate the deflection and to determine the force based on a shaping function; and

a servo-actuator mechanically connected to and in parallel with a flight control system, the servo-actuator configured to apply the force to the cockpit-flight-controller and to be back-driven by the cockpit-flight-controller;

wherein the force-feel system does not include a mechanical spring or a trim motor.