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

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.