Gulfstream Aerospace Corporation

Jimmy Lee Hancock, Jr

Preston A Henne

Donald C Howe

Robert R Wolz

Jeffrey Hausmann

Robert O'Dell

Frank Manochio

Jason Meade

A system is provided that includes a detachable mounting apparatus. The detachable mounting apparatus is configured to be secured on an aircraft. The detachable mounting apparatus includes a detection system and a warning system. The detection system can detect objects in proximity to the aircraft and generate a detection signal when an object is detected in proximity to the aircraft. The warning system can generate at least one alarm signal that is perceptible outside the aircraft.

Detachable detection and warning system for an aircraft

Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when the vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region there between and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle.

Supersonic aircraft with spike for controlling and reducing sonic boom

Method for configuring and operating an aircraft for minimizing sonic boom effects at ground level during supersonic flight of the aircraft. The method includes configuring an aircraft and flying the aircraft at supersonic speed so that in the supersonic flight, a lower profile of the aircraft is presented and generally groundwardly directed; and generating multiple different magnitude pressure disturbances below the aircraft, and radiating therebelow, and controlling the different magnitude pressure disturbances generated below the aircraft so that differentials thereamong are sufficiently minimized that ground level sonic boom effects are minimized during the supersonic flight.

Supersonic aircraft for reducing sonic boom effects at ground level

An aircraft includes a spike projecting forward from the leading end of the fuselage and/or rearward from the trailing end of the fuselage. The spike can include a single section or two or more sections of varying cross-sectional area. Transition regions between sections of varying cross-sectional area are located and shaped to reduce coalescence of shock waves created thereby during supersonic flight. The spike can be collapsible and can be retracted into the fuselage. The spike can have a cross-sectional shape wherein the nose thereof lies on a line formed by the intersection of the bottom of the spike with a plane tangent to the bottom of the spike. A spike thus shaped causes an asymmetric pressure distribution during supersonic flight, wherein the ground-directed pressure contour is of lesser magnitude than the pressure contour propagating in other directions.

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Savannah, GA, United States of America

Jimmy Lee Hancock, Jr