Supersonic aircraft and method of reducing sonic booms

Patent metadata

Field	Value
Publication number	US-11420759-B2
Application number	US-201917044178-A
Country	US
Kind code	B2
Filing date	Mar 25, 2019
Priority date	Apr 6, 2018
Publication date	Aug 23, 2022
Grant date	Aug 23, 2022

Abstract

[Object] To provide a supersonic aircraft and a method of reducing sonic booms, by which sonic booms due to engine exhaust can be reduced.[Solving Means] A supersonic aircraft includes: a pair of engine nacelles 12R, 12L mounted on a fuselage 11 of an airframe 10; fins 13R, 13L as a pair of shielding plates that inhibits engine exhaust 15 discharged from jet engines (not shown) accommodated in the engine nacelles 12R, 12L from wrapping downward around the airframe 10; and a pair of horizontal tails 14R, 14L disposed behind the engine nacelles 12R, 12L. The fins 13R, 13L are disposed on the horizontal tails 14R, 14L so as to sandwich the engine exhaust 15, respectively.

First claim

The invention claimed is:

1. A method of reducing sonic booms of a supersonic aircraft with an engine nacelle mounted on a fuselage of an airframe, the method comprising:
disposing a pair of shielding plates on the airframe so as to sandwich engine exhaust discharged from a jet engine accommodated in the engine nacelle;
inhibiting the engine exhaust from wrapping downward around the airframe by the pair of shielding plates;
drawing inverted Mach cones from positions at which pressure is to be increased by disposing the pair of shielding plates and disposing the pair of shielding plates at positions based on the inverted Mach cones;
setting a first position on a plane of symmetry that crosses perpendicularly to a center of the airframe, the first position being the position at which the pressure is to be increased by disposing the pair of shielding plates and a second position and a third position shifted by a predetermined angle in first and second directions of a circumferential direction around the fuselage of the airframe from the first position, the second position and the third position being each the position at which the pressure is to be increased by disposing the pair of shielding plates;
drawing first to third inverted Mach cones from the first to third positions, respectively;
positioning a rear end of a shielding plate of the pair of shielding plates, which is located on a side of the second direction, at a point on a parabola at which the first inverted Mach cone and the second inverted Mach cone intersect; and
positioning a rear end of a shielding plate of shielding plates, which is located on a side of the first direction, at a point on the parabola at which the first inverted Mach cone and the third inverted Mach cone intersect.

2. A method of reducing sonic booms of a supersonic aircraft with an engine nacelle mounted on a fuselage of an airframe, the method comprising:
disposing a pair of shielding plates on the airframe so as to sandwich engine exhaust discharged from a jet engine accommodated in the engine nacelle; and
inhibiting the engine exhaust from wrapping downward around the airframe by the pair of shielding plates;
defining an angle at which each of the pair of shielding plates is inclined outward from the airframe by using the third-order pole in the multipole method as the index; and
defining an angle at which each of the pair of shielding plates is inclined outward from the airframe by using a difference between a correction amount of a pressure distribution according to the multipole method immediately below the airframe in a case where the pair of shielding plates is provided and a correction amount of a pressure distribution according to the multipole method immediately below the airframe in a case where the pair of shielding plates is not provided or a difference between a third-order pole distribution in a case where the pair of shielding plates is provided and a third-order pole distribution in a case where the pair of shielding plates is not provided as an index.

Assignees

• Japan Aerospace Exploration

Inventors

• Ueno Atsushi
• Yuhara Tatsunori
• Kanamori Masashi

Classifications

• B64D27/20

  within, or attached to, fuselages · CPC title

• B64D29/04

  associated with fuselages · CPC title

• B64C23/04

  by generating shock waves · CPC title

• B64D33/06 Primary

  Silencing exhaust or propulsion jets · CPC title

• B64C5/02 Primary

  Tailplanes · CPC title