Abstract: A method of monitoring for the in-flight accretion of matter involves an electric field sensor applying a time-varying electric field to an engine surface of an aircraft while the aircraft is in flight. The electric field sensor is thermally-coupled and thermally-matched to the engine surface. A sensor monitor receives, in substantially real-time from the electric field sensor, at least one measurement set that includes a measurement of a phase and a magnitude of a current detected by the electric field sensor and resulting from the time-varying electric field. The sensor monitor generates an assessment, in substantially real-time, of an instantaneous accumulation of matter on the engine surface from the at least one measurement set. The sensor monitor activates an alarm upon the assessment indicating an accumulation of matter on the engine surface.

Abstract: A water and ice detection and quantitative assessment system (“WIDQAS”) for moisture detection and assessment of water accumulation on an aircraft having an airframe that has at least one enclosed space within the airframe is described. The WIDQAS may include a plurality of sensors and a data measurement device. The plurality of sensors may be arranged in the at least one enclosed space within the airframe and each sensor of the plurality of sensors may be configured to detect a presence of moisture in the at least one enclosed space and generate a data measurement that is responsive to the detection of moisture in the at least one enclosed space. The data measurement device is in signal communication with the plurality of sensors and may be configured to record the data measurement for each sensor and record identifying information about the measurement during a flight of the aircraft.

Abstract: A method for detecting ambient conditions conducive to ice formation. The method includes the steps of measuring at least one parameter selected from a group of parameters consisting of a static pressure, a total pressure, a total temperature, a dew point temperature, and a liquid water content, and determining whether ambient conditions are conducive to ice formation based on the measured parameter.

Abstract: A stabilizing in-flight parachute system for an airplane comprising a retractable canopy built into a top portion of a fuselage of the airplane. A parachute is under the canopy, while a framework is attached to the parachute. A device is for winding and unwinding the parachute on the framework. A facility is for retracting the canopy and exposing the parachute. A mechanism is for accelerating deployment of the parachute out from the fuselage of the airplane, when the canopy is retracted.

Abstract: A built-in control flap for a ram air, multi-cell, wing type canopy having a ram air inlet is located in each side of the canopy at the rear portion thereof. Each built-in control flap is separated from the adjacent center portion of the canopy between the control flaps. A seal and guide of a sheet of flexible material connects the top of each control flap to the bottom of the adjacent center portion of the canopy across the separation for directing air flow thereby when a control flap is down. Each control flap receives air flow from the ram air inlet.