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A Dihedral Optimization Method for Improving the Horizontal Flight Quality of Flying Wing Layout Aircraft

A flying quality and flying wing technology, applied in the field of dihedral angle optimization, can solve problems such as deterioration of aircraft flight quality and difficulty in ensuring flight safety, and achieve the effects of improving flight quality, increasing damping ratio, and improving safety

Active Publication Date: 2015-11-18
BEIHANG UNIV
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

Although this method can improve the stability of the aircraft, when the flight control system fails, the flight quality of the aircraft will seriously deteriorate, making it difficult to guarantee flight safety.

Method used

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  • A Dihedral Optimization Method for Improving the Horizontal Flight Quality of Flying Wing Layout Aircraft
  • A Dihedral Optimization Method for Improving the Horizontal Flight Quality of Flying Wing Layout Aircraft
  • A Dihedral Optimization Method for Improving the Horizontal Flight Quality of Flying Wing Layout Aircraft

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Embodiment

[0037] Take a small flying wing aircraft as an example, such as figure 2 shown. The aircraft has a wingspan of 7m and a leading edge sweep of 35°. The maximum chord length is 2.5m, the half-wing span of the inner section is 1.25m, the chord length of the middle wing section is 0.77m, the span length of the middle section is 1.7m, and the span length of the wing tip section is 0.55m.

[0038] In the original state without the application of the invention, the aircraft is analyzed for lateral flight dynamics, and the root locus of the root of the Dutch roll characteristic changing with the angle of attack is drawn at a typical speed (60m / s), namely Figure 4 . The drawing plane is a complex number plane, the origin is at the lower right corner, the X-axis is the real axis, and the positive direction is to the right; the Y-axis is the imaginary axis, and the positive direction is upward. Each data point is an eigenvalue root of a Dutch roll mode of the aircraft at an angle of...

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Abstract

The invention discloses a dihedral angel optimization method capable of improving the wing layout aircraft transverse course flight quality. The method comprises the following steps that step 1, the worst state is obtained; step 2, the modal damping rate of a Dutch roll is adjusted; step 3, the modal frequency of the Dutch roll is adjusted; step 4, whether the spiral characteristic root of the aircraft is diffused or not is judged; step 5, through the four steps, the structure of each wing is changed and according to the new structure of each wing, the step 1 is repeated and the worst state of each wing is obtained again. The modal frequency and the modal damping rate of the Dutch roll of the wing layout aircraft are obviously improved, so that the transverse course flight quality of the aircraft is improved. The requirements for a flight control system of the wing layout aircraft are reduced and the safety of the aircraft is improved; according to the aircraft with the requirement for invisibility, serious influence on the RCS of the aircraft is not caused and the invisibility performance of the aircraft is guaranteed.

Description

technical field [0001] The invention relates to a dihedral angle optimization method for improving the horizontal flight quality of a flying-wing layout aircraft, and belongs to the technical field of aviation aerodynamics. Background technique [0002] The stability of the aircraft is very important in flight. In order to make the aircraft have sufficient lateral stability in flight, the aircraft generally has a vertical tail. The vertical tail can increase the lateral aerodynamic force of the aircraft, so that the lateral aerodynamic derivative of the aircraft (the derivative of the lateral force to the sideslip angle C Yβ , Derivative C of yaw moment to sideslip angle nβ , The derivative C of the lateral force to the yaw rate Yr and the derivative of yaw moment to yaw rate C nr ) has a suitable value. Generally, for an aircraft whose lateral stability meets the requirements, there are three motion modes in the lateral direction, which are roll convergence mode, Dutch ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/00
Inventor 解静峰黄俊宋磊杨华颜旭峰刘成
Owner BEIHANG UNIV
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