Abstract: A bidirectional electroosmotic pump may be provided. The bidirectional electroosmotic pump may be made of materials that are biocompatible and non-ferrous. The bidirectional electroosmotic pump may be part of an implantable medical device for the purpose of medicine delivery. The bidirectional electroosmotic pump may contain a working fluid and may facilitate the delivery of a separate payload fluid. In an exemplary embodiment, the bidirectional pump may contain bellows which may allow the pump to deliver the payload fluid through a series of valves and/or catheters. In another embodiment the bidirectional electroosmotic pump may contain a pump sensing mechanism to monitor the state of the pump.

Abstract: A fueling control system for providing fuel from a vehicle to an aircraft, and a method of providing fuel from a fuel vehicle to an aircraft are disclosed herein. The fueling control system includes a pressure transducer for sensing back pressure in a fluid path to a fuel tank of an aircraft, and a digital controller coupled to the pressure transducer for receiving the back pressure in the fluid path and controlling fuel flow in the fluid path to the aircraft. The method includes the steps of sensing back pressure in a fluid path from the aircraft; receiving the sensed back pressure by a digital controller; and controlling fuel flow to the aircraft in the fluid path based on the sensed back pressure.

Abstract: A fuel delivery system of an aircraft refueling vehicle that is configured to distribute fuel from a hydrant pit valve at an airport. The fuel delivery system includes a first hose including a coupler that is configured to be fluidly connected to a hydrant pit valve at an airport to receive fuel from the hydrant pit valve. A fuel passageway is fluidly coupled to the first hose. An on-board fuel tank is fluidly coupled to the fuel passageway. A second hose is fluidly coupled to the fuel passageway. The second hose includes a nozzle that is configured to be coupled to a refueling point on an aircraft to distribute fuel into a fuel tank of an aircraft. A valve is coupled to the fuel passageway to control the flow of fuel to and from the aircraft refueling vehicle.

Abstract: A fuel delivery system of an aircraft refueling vehicle that is configured to distribute fuel from a hydrant pit valve at an airport. The fuel delivery system includes a first hose including a coupler that is configured to be fluidly connected to a hydrant pit valve at an airport to receive fuel from the hydrant pit valve. A fuel passageway is fluidly coupled to the first hose. An on-board fuel tank is fluidly coupled to the fuel passageway. A second hose is fluidly coupled to the fuel passageway. The second hose includes a nozzle that is configured to be coupled to a refueling point on an aircraft to distribute fuel into a fuel tank of an aircraft. A valve is coupled to the fuel passageway to control the flow of fuel to and from the aircraft refueling vehicle.

Abstract: A fueling control system for providing fuel from a vehicle to an aircraft, and a method of providing fuel from a fuel vehicle to an aircraft are disclosed herein. The fueling control system includes a pressure transducer for sensing back pressure in a fluid path to a fuel tank of an aircraft, and a digital controller coupled to the pressure transducer for receiving the back pressure in the fluid path and controlling fuel flow in the fluid path to the aircraft. The method includes the steps of sensing back pressure in a fluid path from the aircraft; receiving the sensed back pressure by a digital controller; and controlling fuel flow to the aircraft in the fluid path based on the sensed back pressure.

Abstract: In a mobile fuel delivery vehicle, providing bulk aircraft fuel from a pressurized fuel reservoir to an aircraft, a method of regulating electrical output of an electrical power source, includes the steps of: (a) receiving, in a fluid path, the bulk aircraft fuel from the pressurized reservoir; (b) controlling flow rate of the fuel along the fluid path; (c) fluidically rotating a shaft of the electrical power source in the fluid path, in response to step (b); (d) sensing rotation speed of the electrical power source by measuring number of revolutions per a time period; (e) setting a predetermined rotation speed for the electrical power source; (f) measuring a difference between the sensed rotation speed of step (d) and the set predetermined rotation speed of step (e); and (g) modifying the flow rate of the fuel along the fluid path based on step (f) and, in turn, the electrical output of the electrical power source.

Abstract: In a mobile fuel delivery vehicle, providing bulk aircraft fuel from a pressurized fuel reservoir to an aircraft, a method of regulating electrical output of an electrical power source, includes the steps of: (a) receiving, in a fluid path, the bulk aircraft fuel from the pressurized reservoir; (b) controlling flow rate of the fuel along the fluid path; (c) fluidically rotating a shaft of the electrical power source in the fluid path, in response to step (b); (d) sensing rotation speed of the electrical power source by measuring number of revolutions per a time period; (e) setting a predetermined rotation speed for the electrical power source; (f) measuring a difference between the sensed rotation speed of step (d) and the set predetermined rotation speed of step (e); and (g) modifying the flow rate of the fuel along the fluid path based on step (f) and, in turn, the electrical output of the electrical power source.

Abstract: A portable fueling control system is provided for delivering bulk fuel to a vehicle from a pressurized source. The portable system includes a fluid driven power source for operating auxiliary instrumentation of the system. An inlet receives the bulk fuel from the pressurized source. The inlet has a primary fluid path and a secondary fluid path. A first flow rate control is in fluidic communication with the primary fluid path for adjustably controlling the flow rate of bulk fuel from the pressurized source to a system outlet. A first monitor is operably linked to the secondary fluid path and the first flow rate control. The first monitor is responsive to the flow rate of the secondary fluid path for actuating the first flow rate control to vary the pressure difference across the first flow rate control.

Abstract: A fueling control system for providing fuel from a vehicle to an aircraft, and a method of providing fuel from a fuel vehicle to an aircraft are disclosed herein. The fueling control system includes a pressure transducer for sensing back pressure in a fluid path to a fuel tank of an aircraft, and a digital controller coupled to the pressure transducer for receiving the back pressure in the fluid path and controlling fuel flow in the fluid path to the aircraft. The method includes the steps of sensing back pressure in a fluid path from the aircraft; receiving the sensed back pressure by a digital controller; and controlling fuel flow to the aircraft in the fluid path based on the sensed back pressure.