Abstract: A method and a system for providing in-flight reverse thrust for an aircraft are provided. The aircraft comprises an engine having a rotor, a compressor mechanically coupled to the rotor, and a variable geometry mechanism provided upstream of the compressor and configured to modulate an amount of compression work performed by the compressor. The method comprises operating the rotor with the variable geometry mechanism in a first position, receiving a request to increase reverse thrust for the rotor, in response to the request, adjusting the variable geometry mechanism from the first position towards a second position, the variable geometry mechanism having a greater opening angle in the second position than in the first position, and operating the rotor with the variable geometry mechanism in the second position for causing an increase in the amount of compression work performed by the compressor and an increase in reverse thrust for the rotor.

Abstract: A method and a system for providing in-flight reverse thrust for an aircraft are provided. The aircraft comprises an engine having a rotor, a compressor mechanically coupled to the rotor, and a variable geometry mechanism provided upstream of the compressor and configured to modulate an amount of compression work performed by the compressor. The method comprises operating the rotor with the variable geometry mechanism in a first position, receiving a request to increase reverse thrust for the rotor, in response to the request, adjusting the variable geometry mechanism from the first position towards a second position, the variable geometry mechanism having a greater opening angle in the second position than in the first position, and operating the rotor with the variable geometry mechanism in the second position for causing an increase in the amount of compression work performed by the compressor and an increase in reverse thrust for the rotor.

Abstract: An article and device are provided comprising a switchable microstructure or nanostructure array of non-parallel conducting plates, supported by a plurality of shaped prismatic oxide stages upon layered conductive and substrate-base materials, for directly generating a lateral or transverse Casimir force. Illustrative embodiments include a device for switchable generation of lateral or transverse Casimir force components that work in an orthogonal direction to normal Casimir forces which can be externally switched “on” or “off” electronically, mechanically or thermally by using a semiconductor PN-junction or superconductor to produce a thrust for guidance, maneuvering and propulsion of a manned or unmanned space vehicle, or in other novel applications requiring generation of precisely switched or continuous forces.

Abstract: An article and device are provided comprising a switchable microstructure or nanostructure array of non-parallel conducting plates, supported by a plurality of shaped prismatic oxide stages upon layered conductive and substrate-base materials, for directly generating a lateral or transverse Casimir force. Illustrative embodiments include a device for switchable generation of lateral or transverse Casimir force components that work in an orthogonal direction to normal Casimir forces which can be externally switched “on” or “off” electronically, mechanically or thermally by using a semiconductor PN-junction or superconductor to produce a thrust for guidance, maneuvering and propulsion of a manned or unmanned space vehicle, or in other novel applications requiring generation of precisely switched or continuous forces.

Abstract: Method and device for directly generating a transverse Casimir force comprising a technique for fabricating a microstructure array of non-parallel conducting plates held in place by an insulating material and affixed either to a conducting or insulating substrate are disclosed. As described by the illustrative embodiment, the lateral or transverse force component generated by the present invention works in an orthogonal direction to the normal Casimir force, thereby allowing its use as a means of vectored thrust for precise positioning, guidance, maneuvering and propulsion in a manned or unmanned space vehicle, or any application requiring precise forces.

Abstract: A non-invasive method and means for determining beat-by-beat assessments of a patient's cardiac performance by measuring the "pre-ejection phase" (PEP) and the "left ventricular ejection time" (LVET), the aforementioned phrases also being known as the "systolic time intervals" (STI) of the heart.