Dual-fuselage multipurpose launch vehicle aerodynamic configuration with high aspect ratio support wings

A technology with large aspect ratio and aerodynamic layout, applied to aircraft, fuselage, motor vehicles, etc., can solve the problems of reducing aerodynamic efficiency and increasing lift-to-drag ratio, and achieve the effect of increasing aerodynamic efficiency and enhancing adaptability

Active Publication Date: 2019-01-25
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the support wing and the wing will form adverse aerodynamic interference between the wings and reduce the aerodynamic efficiency. If the adverse aerodynamic interference can be reduced, the lift-to-drag ratio can be further increased

Method used

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  • Dual-fuselage multipurpose launch vehicle aerodynamic configuration with high aspect ratio support wings
  • Dual-fuselage multipurpose launch vehicle aerodynamic configuration with high aspect ratio support wings
  • Dual-fuselage multipurpose launch vehicle aerodynamic configuration with high aspect ratio support wings

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0035] The airfoils of the main wing 2 and the supporting wing 5 are RAE2822, the incoming flow velocity is 100m / s, the incoming flow angle of attack is 2°, point A is located at the leftmost sextile point of the main wing 2, and the dihedral angle of the V-shaped tail is 30°~60°, the dihedral angle of the supporting wing is 10°~25°, and the forward / backward sweep angle of the supporting wing is 5°~10°. In the section along the span direction of the main wing 2, take different horizontal distances s (-0.1, 0.5, 0.9) between the leading edge of the support wing 5 and the leading edge of the main wing 2 in the horizontal direction, and take the vertical distance g as 0.3, and get The flow pressure contours of the supporting wing 5 and the main wing 2 are as follows Figure 7a , 7b , 7c shown. From Figure 7a It can be seen that when the supporting wing 5 is at the leading edge of the main wing, the acceleration of the airflow on the upper surface of the supporting wing 5 caus...

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Abstract

The invention discloses an aerodynamic configuration of a dual-fuselage multipurpose carrier aircraft with a high aspect ratio support wing, belonging to the technical field of aerodynamic configuration design of the aircraft. Includes engine, main wing, engine attachment, fuselage, support wing, payload, payload attachment, v-tail, tail support and support wing tip attachment. A support wing configuration is combine with a two-fuselage configuration, the aspect ratio of the main wing is greater than 35, the engine has two, each engine has a fuselage directly beneath it, each fuselage has a supporting wing symmetrically arranged on the left and right sides, when the fuselage is in the horizontal position, the leading edge of the supporting wing and the trailing edge of the main wing in thehorizontal direction coincide length in the chord length direction is 0% of the chord length of the main wing at the position 40%. A support wing is arrange below that trailing edge of the main wingto carry out the support layout, the structural rigidity of the main wing is increased, the adverse interference between the support wing and the main wing is reduce, and different payloads can be mounted.

Description

technical field [0001] The invention belongs to the technical field of aircraft aerodynamic layout design, and in particular relates to an aerodynamic layout of a large-aspect-ratio support-wing dual-fuselage multi-purpose carrier aircraft. Background technique [0002] The wings of an aircraft often bear the distributed load formed by the entire weight of the aircraft, so a certain amount of deformation will occur. The wings of the aircraft with large aspect ratio are larger, and the deformation of the wings is more serious. When encountering a gust of wind or making a pitch attitude control, the large-aspect-ratio wing with large deformation may produce elastic swings that affect flight safety. The aspect ratio of the wing should not be too large under the existing material technology level. However, it is known from technical common sense that the larger the aspect ratio of the wing, the higher the cruise lift-to-drag ratio of the aircraft, and increasing the aspect rat...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/26B64C3/00B64C39/04
CPCB64C1/26B64C3/00B64C39/04
Inventor 蒋崇文李志豪林宏渊何新高振勋李椿萱
Owner BEIHANG UNIV
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