Flight Control Elevator and Rudder Actuation
project name

Flight Control Elevator and Rudder Actuation

For a Future Helicopter

description

Flight control actuators for a future vertical lift (FVL) aircraft.

CaseStudy14Problem Statement
This system, located in the helicopter tail, is weight sensitive and requires aggressive dynamic performance greater than 10 Hz open loop small amplitude frequency response. The performance and packaging demands of the vehicle required a compact design. Other requirements included a 270 VDC EMA solution with 10 Hz small amplitude frequency response capable of over 600 pounds of output force while operating at high speed, all while exposed to extreme conditions and a continuously hot soaked bay ambient environment. Budget constraints demanded minimizing development costs, requiring the development of a similar actuation design for the rudder and elevator.

Solution
Ingenium developed linear electromechanical actuator (EMA) for use as the primary FCA for a modern helicopter platform which utilizes flight control surfaces for the elevator and rudder control.   The actuators and system architecture are tailored derivatives of hardware provided for a previous program. Working closely with the airframe manufacturer and flight control electronics provider, Ingenium optimized all aspects of the design to utilize minimum power while providing maximum performance throughout the entire flight regime.  Through numerous design iterations the team was able to arrive at an acceptable baseline architecture which then became the basis for designing both the rudder and elevator actuators. Working cooperatively with the customer’s aerodynamicists and the actuator control unit (ACU) provider, the engineering teams matured the requirements and finalize EMA performance details.

Results & Outcome
Ingenium Aerospace is currently in development of the elevator and rudder actuators for this vehicle. The units have been designed to meet or exceed all of the mission objectives for the elevator and rudder control actuation.