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A tailless compound helicopter

A helicopter and composite technology, applied in the direction of the fuselage, rotorcraft, motor vehicles, etc., can solve the problems of lack of stable surface, insufficient orientation and longitudinal stability, and achieve the effect of eliminating tail shudder.

Active Publication Date: 2021-08-17
AIRBUS HELICOPTERS DEUT GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Furthermore, the proposed architecture is expected to have insufficient directional and longitudinal stability due to the lack of a stabilizing surface relative to the helicopter's center of gravity

Method used

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  • A tailless compound helicopter
  • A tailless compound helicopter
  • A tailless compound helicopter

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0071] figure 1 A schematic compound helicopter 1 is shown. The compound helicopter 1 is viewed from above and extends in a longitudinal direction 22 , a transverse direction 23 and a vertical direction 38 .

[0072] The longitudinal direction 22 corresponds to the intrinsic roll axis of the compound helicopter 1 . The transverse direction 23 is perpendicular to the roll axis and corresponds to the pitch axis of the compound helicopter 1 . The plane formed by the longitudinal direction 22 and the transverse direction 23 is considered "horizontal" and corresponds to figure 1 A top plan view of the compound helicopter 1 is shown. The plane formed by the longitudinal direction 22 and the transverse direction 23 is also sometimes referred to as the horizontal plane or the X-Y plane.

[0073] The vertical direction 38 corresponds to the yaw axis of the compound helicopter 1 and is oriented vertically with respect to the X-Y plane. The plane formed by the lateral direction 23 a...

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PUM

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Abstract

The present embodiments relate to a compound helicopter 1 with a fuselage 4, at least one main rotor 2, and a fixed wing arrangement 5. The at least one main rotor 2 may include at least two rotor blades 2a, 2b that form a main rotor disc 3 during rotation of the at least one main rotor 2, wherein the main rotor disc 3 defines a compound helicopter perimeter 3a. The fixed wing arrangement 5 is completely arranged laterally relative to the fuselage 4 within the compound helicopter perimeter 3a, and includes a rear horizontal plane structure 13, at least one vertical fin 17 that is arranged with a predetermined angle 17a at the rear horizontal plane structure 13, at least one upper wing, at least one lower wing, and an interconnection region 11, in which an upper wing 6 is connected to an associated lower wing 7.

Description

technical field [0001] The proposed embodiment relates to a compound helicopter having a fuselage, at least one main rotor at least adapted to generate lift in operation, and a fixed-wing configuration laterally attached to the fuselage. Background technique [0002] Conventional helicopters are generally characterized by the use of a main rotor and a tailboom with an auxiliary tail rotor adapted to counteract torque. In addition to the tail rotor, the tail boom usually has a vertical and a horizontal tail plane mounted with the tail rotor on the tail of the tail boom. [0003] The tailboom of a modern helicopter is basically a closed cylindrical structure that extends toward the rear of the fuselage. The tail boom is usually designed as a fish-shaped tail featuring a smooth transition from the fuselage to the tail boom structure, or as a beam-shaped tail projecting from the upper portion of the rear fuselage. [0004] The longitudinal extension of the tailboom relative to...

Claims

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Application Information

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IPC IPC(8): B64C27/22B64C27/26B64C27/28B64C1/06
CPCB64C27/22B64C27/26B64C27/28B64C1/068B64C39/068
Inventor 马丁·布拉查阿克塞尔·芬克
Owner AIRBUS HELICOPTERS DEUT GMBH