Supersonic civil aircraft layout

By designing a special layout of the engine nacelle and flat tail tip in the ultrasonic civil aircraft, the shielding effect of the wing and flat tail avoids shock wave propagation, and providing additional vertical tail tail capacity through the foldable flat tail tip, the acoustic explosion, propulsion efficiency and vertical tail efficiency of the ultrasonic civil aircraft during ultrasonic cruise are solved, achieving lower sound explosion loudness and higher heading stability.

CN119659923AActive Publication Date: 2025-03-21XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Patent Information

Application Number
CN202411883614.9
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-12-19
Publication Date
2025-03-21
Estimated Expiration
2044-12-19

AI Technical Summary

Technical Problem

When supersonic civil aircraft is cruising, the shock waves generated by the engine inlet and exhaust system are merged with the shock waves generated by other components of the aircraft, resulting in high ground sound explosion noise; the engine's performance deteriorates under non-designed operating conditions and reduces propulsion efficiency; the tail capacity of the vertical tail decreases during supersonic cruise, and the heading stability decreases.

Method used

A supersonic civil aircraft layout is designed. The engine nacelle is installed on the rear fuselage between the wing and the flat tail. The air inlet is blocked by the rear edge of the wing, and the exhaust port is blocked by the front edge of the flat tail. The shielding effect of the wing and the flat tail avoids shock wave propagation; the engine mount can be pitched and deflected around the rotation axis at a small angle to adjust the engine installation angle; the flat tail tip can be folded upward to provide additional vertical tail capacity.

Benefits of technology

It effectively reduces the ground sound loudness, improves the engine's propulsion efficiency under non-designed point conditions, makes up for the efficiency loss of the vertical tail during ultrasonic cruising, and improves heading stability.

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Abstract

The invention belongs to the technical field of aviation, and particularly relates to a supersonic civil aircraft layout. According to the supersonic civil aircraft layout, the engine nacelle is installed above the rear fuselage between the wing and the horizontal tail, the lower portion of the air inlet is shielded by the rear edge of the wing, the lower portion of the air outlet is shielded by the front edge of the horizontal tail, shock waves generated by the engine are prevented from spreading to the ground through the shielding effect of the wing and the horizontal tail, and the ground sound explosion loudness of the aircraft is effectively reduced; the engine and the hanger can perform small-angle pitching deflection around the rotating shaft in the hanger, so that the mounting angle of the engine is adjusted, and the propulsive efficiency of the engine under the non-design-point working condition is improved; the horizontal tail tip can be folded upwards to provide additional vertical tail capacity during supersonic cruising, loss of vertical tail efficiency during supersonic cruising is made up, and expansion waves generated by an engine exhaust nozzle and a horizontal tail are prevented from spreading to the ground. And the wingtip is put down during low-speed take-off and landing, so that a larger horizontal tail area is ensured, and the trimming requirement of a take-off and landing structure is met.
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