Abstract: A pump system is disclosed including a first pump having a first inlet and a first outlet, and a second pump having a second inlet and a second outlet. The second pump is arranged in parallel with the first pump, and the first inlet and the second inlet are for fluidically coupling to one or more fluid reservoirs. A control system is coupled to the first pump and the second pump for controlling the operation of the first pump and the second pump simultaneously. The control system is configured to measure a value of a first pressure head at the first outlet, measure a value of a second pressure head at the second outlet, control the first pump to achieve a required output and control the second pump by providing a demand for the second pump to achieve a measured value of the second pressure head which equals the measured value of the first pressure head.

Abstract: A fuel system includes a chamber for storing a fuel, an optical differential pressure sensor, and one or more processors in communication with the optical differential pressure sensor. The optical differential pressure sensor is fluidically connected to the chamber and is configured to, when the fuel is stored in the chamber, output a signal indicative of a pressure difference in the optical differential pressure sensor to the one or more processors.

Abstract: An aircraft fuel tank monitoring system is disclosure including at least one first sensor for sensing a pressure of fuel within a fuel tank; at least one second sensor for sensing a pressure of an ullage space above the fuel within the fuel tank; a processor for monitoring the change in the pressure of the fuel within the fuel tank over a time period and for monitoring the change in the pressure of the ullage space within the fuel tank over the time period, and to determine a fault if the monitored pressure changes exceed normal operating conditions.

Abstract: A system for monitoring an aircraft fluid storage tank assembly is disclosed including a pressure sensor configured to receive an acoustic signal emitted from a location within the aircraft fluid storage tank assembly in use and a controller. The controller is configured to receive information indicative of the acoustic signal from the pressure sensor and perform a determination process to determine, on the basis of the received acoustic signal, whether to output an indicator of a fault condition of the aircraft fluid storage tank assembly.

Abstract: An aircraft including a wing, a first pressure sensor and a second pressure sensor, wherein each pressure sensor is configured to measure pressure of a liquid within the wing and has a known position within the wing. The aircraft includes a processing system configured to receive first pressure data from the first pressure sensor, receive second pressure data from the second pressure sensor, and determine a bending state of the wing based on the first pressure data, the second pressure data, and the known positions of the first and second pressure sensors within the wing.