Abstract: A system for neutralizing exhaust gases from an aircraft at altitude includes a turbofan jet engine. The turbofan jet engine creates exhaust gases. An exhaust is located within the turbofan jet engine. The exhaust has an interior volume. At least one corona discharge unit is located within the interior volume of the exhaust. The at least one corona discharge unit creates electrical discharges comprising high-speed relativistic electrons and gamma rays within the exhaust. The exhaust gases and the electrical discharges are directed to interact with one another in the interior volume of the exhaust. The interaction generates positively charged plasma ions within the exhaust gases. The exhaust gases are neutralized before leaving the turbofan jet engine.

Abstract: An electrical switch cover that restricts access to the enclosed switch actuator is placed over the existing electrical switch and is held in place against the existing electrical switch using the existing hardware. Actuation of the existing switch is provided through a removable cap located on the cover. When the cap of the present invention is removed restricted access is further achieved by dimensioning the opening that is revealed when the cap is removed such that the depth into which one must reach into the cover to affect the switch actuator exceeds the physical ability of a typical small child yet is within the abilities of a typical adult.

Abstract: The present invention is a childproof electrical switch cover that prevents children from operating the enclosed toggle or rocker electrical switch but allows adults to do so. The childproof cover is placed over the existing electrical switch to be protected and is held firmly in place against the existing electrical switch using the same hardware previously used to hold the existing electrical switch firmly against its support structure: the childproof electric switch cover and the wall switch that it is placed upon forming a protected volume that is not accessible to children attempting to actuate the electrical switch. Access by adults to the existing switch is provided thru removable childproof caps located on the childproof cover. When the childproof cap of the present invention is removed by an adult, the cover remains childproof.

Abstract: Apparatus and a method are described for prospecting for water ice on heavenly bodies with the apparatus consisting of site preparation tools and a water ice detector unit. The apparatus is attached at the end of any robotic arm equipped lander or rover spacecraft; for instance, lander designs such as Mars Phoenix or rover designs such as Mars Spirit and Opportunity. Supported on an internal, moveable carriage, the apparatus is also incorporated into smaller, dedicated water ice detection rover spacecraft. The water ice detection unit inserts electrodes into or against a potential water ice deposit and confirms the presence of water ice by making combination impedance and thermal conductivity measurements.

Abstract: An aircraft Ice Detection pitot-static tube is described which uses sensors integrated into the pitot-static tube to determine when and where the pitot-static tube is icing up. Temperature, thermal conductivity and impedance sensor measurements are combined with a mathematical transfer of the impedance sensor output into the complex dielectric plane to identify that the material accreating on the exterior and interior of the pitot-static tube is ice and only ice. Identification of ice realized when the trace in complex dielectric space has a distinctive semi-circular form, which only ice exhibits, with measured values in agreement with reference laboratory data stored in the onboard computer system.

Abstract: An Extra Electric Energy System that supplies electrical power to an aircraft of the continuous flight duration day/night cycle solar powered type is described where the extra electric energy is generated as static charge by collisions of the aircraft with particles existing in the earth's atmosphere. The manner in which the static charge is collected, stored and used immediately to meet present or future aircraft power needs is considered. An example of the application of the system to a high altitude solar powered Helios type aircraft is offered along with a discussion of how its structure is modified to store static charge.

Abstract: A means for harvesting local energy and using it to generate local electric power is disclosed which uses as its energy source P-Static charge generated on the external surfaces of aircraft flying through the earths atmosphere or generated on the external surfaces of electrically ungrounded objects immersed in the wind and subjected to the impact of charge generating ingredients contained in the atmosphere or wind. The P-Static charge is collected and stored in a high voltage rechargeable capacitor storage unit at several thousand volts with energy removed from the storage unit as needed and converted to low voltage DC or AC power which, in turn, is used to power local, low power consumption electronic chips and devices. Data measured by the chips or devices is relayed wirelessly back to a receiver located within the aircraft or object with the wireless transmitter also powered by the P-Static Electrical Power System.

Abstract: An ice detection system that detects the onset of ice accreation on an aircraft's external surfaces, continuously measures its thickness and growth time history and provides the type of ice, glaze or rime, is disclosed along with an independent way to confirm that the contaminant is known to be ice and only ice. Total impedance data, thermal conductivity value and complex dielectric properties are used to discriminate between ice, water, deicing fluid and snow with measurements made by low cost, low power consumption, low profile, miniature electronic chips, components and devices collocated together on the external surface in a thin pliant patch that does not effect the airflow about the aircraft. The ice detection system provides ice accreation data and warning signals to displays and aural signaling devices in the cockpit for the pilot and to the control console of a ground controller flying the aircraft if it is unmanned.