Abstract: A pneumatic actuation control system includes a pressure controller, an eductor and a valve. The pressure controller is capable of directing an amount of fluid to the contained volume such that a pressure within the contained volume exceeds a pressure external to the contained volume by a predefined positive pressure. The pressure controller can also adjust the pressure within the contained volume when the pressure external to the contained volume changes. The eductor can draw fluid from the contained volume to thereby decrease the pressure within the contained volume. The valve is controllably operable in either a pressure mode or a vacuum mode, where the valve either permits the pressure controller to provide fluid to the contained volume, or permits the eductor to draw fluid from the contained volume. As such, the system provides precision pressure control over a broad range of external pressures while compensating for rapid pressure changes.

Abstract: A pneumatic actuation control system includes a pressure controller, an eductor and a valve. The pressure controller is capable of directing an amount of fluid to the contained volume such that a pressure within the contained volume exceeds a pressure external to the contained volume by a predefined positive pressure. The pressure controller can also adjust the pressure within the contained volume when the pressure external to the contained volume changes. The eductor can draw fluid from the contained volume to thereby decrease the pressure within the contained volume. The valve is controllably operable in either a pressure mode or a vacuum mode, where the valve either permits the pressure controller to provide fluid to the contained volume, or permits the eductor to draw fluid from the contained volume. As such, The system provides precision pressure control over a broad range of external pressures while compensating for rapid pressure changes.

Abstract: Conventional rotorcraft are required to provide a significant amount of anti-torque movement to offset the torque created by the rotor and the right-angle gearbox coupling the rotor to the engine. By vertically integrating the engine in the unmanned rotorcraft of the present invention, the torque component rising from the right-angle gearbox is eliminated. This type of adaptation, however, is generally unacceptable in conventional helicopter integration, since a vertically mounted engine directly under the rotor would deprive the user of critical payload volume at the center of gravity. The radial distribution of payload in the design of the present invention avoids this penalty. Conventional anti-torque systems, including tail rotors, ducted gas, and dual counter rotating rotors produce drag, weight, and efficiency penalties.