Electromechanically actuated control rod for flight vehicles

A flight vehicle control rod assembly comprising:

• a connecting rod,
• a first end portion having a first actuator that is operably coupled to the connecting rod and operative to extend, retract, or hold a first portion of the connecting rod relative to the first actuator,
• a second end portion opposite the first end portion having a second actuator that is operably coupled to the connecting rod and operative to extend, retract, or hold a second portion of the connecting rod relative to the second actuator,
• wherein the first and second actuators are electromechanical actuators that each include an electric motor, a ballscrew, and a ballnut;
• wherein the ballscrew is operably coupled to the electric motor for being rotated about an axis by the electric motor;
• wherein the ballnut is operably coupled to the connecting rod for common axial movement together;
• and
• wherein the ballscrew and connecting rod are linearly translatable in a direction of the axis in response to rotation of the ballscrew via the electric motor.

A rotor assembly of a helicopter, comprising:

• a plurality of rotor blades having respective control surfaces;
• a swashplate assembly operably coupled to the plurality of blades;
• a control rod assembly operably coupled to the swashplate assembly to effect movement of the control surfaces;
• wherein the control rod assembly includes:
• a first connector operably coupled to the swashplate, and a second connector operably coupled to another structure of the helicopter;
• a connecting rod operably coupled between the first and second connectors;
• and
• an actuator operably coupled to the connecting rod, the actuator being configured to adjust a position of the connecting rod to vary a distance between the first and second connectors.