Flight control actuation system
First Claim
1. A flight control actuation system for use in a flight control system comprising:
- a controller operable in response to an input for generating a control signal;
an electromechanical actuator responsive to the control signal, for operating a flight control surface; and
a pneumatic actuator for assisting the electromechanical actuator by reducing the load on the electromechanical actuator.
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Accused Products
Abstract
A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities.
13 Citations
45 Claims
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1. A flight control actuation system for use in a flight control system comprising:
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a controller operable in response to an input for generating a control signal;
an electromechanical actuator responsive to the control signal, for operating a flight control surface; and
a pneumatic actuator for assisting the electromechanical actuator by reducing the load on the electromechanical actuator. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 34)
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12-17. -17. (canceled)
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18. A flight control actuation system for use in a flight control system comprising:
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at least one aerodynamic flight control surface;
an electromechanical actuator system adapted to act on each aerodynamic flight control surface;
a pneumatic actuator system adapted to produce a force to act on at least one of the aerodynamic flight control surfaces;
at least one electromechanical actuator associated with a distinct one of the at least one aerodynamic flight control surfaces;
a controller adapted to produce an electrical signal for controlling at least one of the aerodynamic flight control surfaces;
an electrical circuit connected to the at least one electromechanical actuator with at least one electromechanical actuator adapted to receive the electrical signal;
the pneumatic actuator system solely associated with the at least one electromechanical actuator;
the pneumatic actuator system comprising;
a piston;
a pressure vessel;
a vent solenoid valve;
a pressurization solenoid valve; and
a pressure switch;
the vent solenoid valve and pressurization solenoid valve adapted to receive the electrical signal to route a pneumatic pressure;
an actuation device adapted to receive the pneumatic pressure and produce a pneumatic force; and
the actuation device being adapted to continuously actuate the distinct one of the aerodynamic flight control surfaces of a flight vehicle in response to the pneumatic force. - View Dependent Claims (19, 20, 21, 22)
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23-33. -33. (canceled)
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35. A flight control actuation system, comprising:
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a flight control surface for controlling flight of a flight vehicle;
an electromechanical actuator adapted for controlling a position of said flight control surface;
a pneumatic actuator also adapted for controlling the position of said flight control surface;
a pneumatic supply module in communication with said pneumatic actuator; and
a controller in communication with said pneumatic supply module for controlling said pneumatic actuator. - View Dependent Claims (36, 37, 38, 39, 40, 41, 42, 43, 44, 45)
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Specification