公开(公告)号：US20230130658A1

公开(公告)日：2023-04-27

申请号：US17905311

申请日：2021-02-05

Applicant: JAPAN AEROSPACE EXPLORATION AGENCY

Inventor： Atsushi UENO

IPC: B64F5/00 ,  B64C30/00 ,  B64C23/04

Abstract: A method of designing an aircraft shape of a supersonic aircraft according to an embodiment of the present invention includes: obtaining an equivalent cross-sectional area distribution of an initial shape at an off-track position of an aircraft; setting a target equivalent cross-sectional area distribution at the off-track position of the aircraft for reducing sonic booms on the basis of the obtained equivalent cross-sectional area distribution; and converting, on the basis of a required additional cross-sectional area distribution that is a difference between the equivalent cross-sectional area distribution and the target equivalent cross-sectional area distribution, a required additional cross-sectional area of a cross-section of the aircraft on an off-track Mach plane that extends through an arbitrary position in an airflow direction into a required additional cross-sectional area of a cross-section of the aircraft on an on-track Mach plane of the aircraft that is located near the off-track Mach plane and adding the required additional cross-sectional area of the cross-section of the aircraft on the on-track Mach plane.

公开(公告)号：US20210031935A1

公开(公告)日：2021-02-04

申请号：US17044178

申请日：2019-03-25

Applicant: JAPAN AEROSPACE EXPLORATION AGENCY

Inventor： Atsushi UENO ,  Tatsunori YUHARA ,  Masashi KANAMORI

IPC: F02K1/34 ,  B64C30/00 ,  B64D29/04 ,  B64D27/20 ,  B64C5/02

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.