Aerion Corporation

Aerion Intellectual Property Management Corporation

James D Chase

Richard R Tracy

Michael Lorenzo Henderson

German Andres Garzon

Peter Sturdza

Ilan Kroo

Sturdza Peter

The present disclosure relates to a method of operating a supersonic aircraft comprising the steps of: at takeoff, positioning a slidable plug-cowl assembly disposed within a nozzle and behind an engine in an aft position such that a front surface of a plug is aft of an exit plane of a cowl, to thereby reduce noise during takeoff and maintain engine efficiency; and after takeoff, re-positioning the slidable plug-cowl assembly to a forward position such that the front surface of the plug is not disposed aft the exit plane of the cowl.

High flow plug nozzle apparatus and method of using the same

Improved supersonic laminar flow wing structure, on a supersonic aircraft, having strake extending forwardly of the wing inboard extent, and reversed fillet at strake junction with the wing leading edge. Plain and split flap structures may also be provided at each laminar flow wing.

Highly efficient supersonic laminar flow wing structure

Improved supersonic laminar flow wing structure, on a supersonic aircraft, having strake extending forwardly of the wing inboard extent, and reversed fillet at strake junction with the wing leading edge.

Highly efficient transonic laminar flow wing

In combination, an aircraft and a rotatively combined electrical power/generator and hydraulic motor/pump configured to provide either hydraulic power from electrical power, or electrical power from hydraulic power, installed in said aircraft.

Aircraft emergency and backup secondary power apparatus

Aircraft configured to operate at Mach numbers from above 0.80 and up to 1.2 with wing sweep angles defined by the wing outboard leading edge of less than 35 degrees, and incorporating calculated values of the ratio of outboard wing panel aspect ratio raised to an exponent of 0.78, divided by the ratio of maximum thickness divided by chord (t/c), greater than about 45, characterized by one of the following: a) where maximum thickness divided by chord (t/c) is at a location approximately 70% of the distance outboard from the attaching aircraft body to the wing tip, or b) where maximum thickness divided by chord (t/c) is the average value of (t/c)'s located between approximately 50% of the distance outboard from the attaching aircraft body to the wing tip.

Laminar flow wing optimized for transonic cruise aircraft

In a jet engine having a plug nozzle and a plug extending rearwardly from the nozzle exit, the improvement comprising a plug having successive cross sections spaced apart rearwardly of the nozzle exit, the cross sections transitioning from circular or near circular at the exit plane defined at the nozzle exit, to progressively non-circular, rearwardly.

Jet nozzle plug with varying, non-circular cross sections

On an aircraft designed for maximum efficient cruise speed in the range from about Mach 0.8 to about Mach 1.2, and having fuselage and wings with: (a) less than about 25 degrees of leading edge sweep, in combination with airfoil thickness to chord ratios between about 3% and about 8%, as an average along the wing semi-span outboard from the zone of substantial fuselage influence, and (b) wing leading edge sweep between about 20 degrees and about 35 degrees, in combination with airfoil thickness to chord ratios equal to or below about 3% as an average along the semi-span outboard from the zone of substantial fuselage influence to the wing tip.

A method of providing an aircraft having a fuselage and a wing configured for extensive laminar flow at design cruise conditions, the method characterized by a) providing wing biconvex-type airfoils having values of thickness, chord and shape along the wing span which provide substantially optimal aircraft range at design cruise conditions, considering the influences of wing drag and wing weight; b) providing wing leading edges, which are configured to effect laminar flow; c) providing fuselage and wing contours which, in combination, produce reduced total wave drag and produce extensive areas of laminar boundary layer flow on the wing; and d) providing wing sweep angularity that facilitates provision of a), b) and c).

Laminar flow wing optimized for supersonic cruise aircraft

Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided.

Supersonic aircraft jet engine installation

An improved supersonic laminar flow wing structure, on a supersonic aircraft, having one or more of the following: a strake extending forwardly of the wing inboard extent, a raked wing tip, a reversed fillet at the strake or fuselage junction, an inboard leading edge flap extending over less than about 15% of the inboard wing panel span, and a hybrid plain-split flap having a lower surface portion deflectable downwardly relative to plain flap extent.

Highly efficient supersonic laminar flow wing

Supersonic aircraft jet engine

An aircraft includes a fuselage, thin supersonic wings on the fuselage, there being trailing edge flaps carried by the wings, the flaps configured to provide flap deflection to simultaneously control wing twist and to reduce drag, when the aircraft is operated at subsonic flight conditions.

Lift and twist control using trailing edge control surfaces on supersonic laminar flow wings

In combination, an aircraft wing and fuselage, comprising the wing having camber at or near the wing leading edge which has blunted sharpness and low sweep angle, and the fuselage having indentation along the wing side thereof, and lengthwise of the fuselage.

Laminar flow wing for transonic cruise

An aircraft, comprising a fuselage having an elongated, narrow forward portion, a main wing carried by a rear portion of the fuselage, a canard wing carried by said fuselage forward portion and having swept back leading and trailing edges tapering toward a tip or tips, the canard wing having less lifting surface than the main wing.

Growing community of inventors

Reno, NV, United States of America

James D Chase