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Method for structural design of coaxal helicopter composite material blade

A technology of coaxial helicopters and composite materials, applied in the field of helicopter rotor design, can solve the problems such as the lack of details

Inactive Publication Date: 2009-05-13
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In "Helicopter Technology" and "Journal of Nanjing University of Aeronautics and Astronautics", there are some articles on the design of helicopter composite blades, but they are all theoretical descriptions, and no specific details are introduced.

Method used

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  • Method for structural design of coaxal helicopter composite material blade
  • Method for structural design of coaxal helicopter composite material blade
  • Method for structural design of coaxal helicopter composite material blade

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Embodiment Construction

[0048] See figure 1 , figure 2 , image 3 Shown: a method for structural design of a coaxial helicopter composite material blade, the specific steps of the method are as follows (taking a helicopter with a total weight of 350 kg as an example):

[0049] Step 1: Quality Estimation

[0050] The radius of the blade is 2.5m, and the chord length is 0.17m. The mass of the blade can be estimated as:

[0051] m ly =60×2.5×0.172=4.335(kg)

[0052] Step 2: Centrifugal force at the blade root

[0053] The rotor speed is 600 rpm, and the centrifugal force at the blade root can be calculated as:

[0054] f li =0.005483×4.335×2.5×600 2 =21391(N)

[0055] Step 3: (same as above)

[0056] Step 4: Determine the cross-sectional area of ​​the C-beam of the blade

[0057] S c =1.5×21391 / 500=64(mm 2 )

[0058] Step five: (same as the previous section)

[0059] Step 6: (same as above)

[0060] Step 7: Determine the area of ​​the trailing edge of the blade

[0061] It can be prelimi...

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Abstract

The invention provides a method for designing a coaxial helicopter composite material blade structure. The method comprises ten steps as follows: step one, estimation of quality; step two, calculation of the centrifugal force of a blade root; step three, determination of the structural pattern of a composite material blade; step four, determination of the section area of a blade C-type beam; step five, determination of the chordwise position of a blade Z-type web plate; step six, determination of the outer panel of a blade; step seven, determination of the trailing-edge strip area of the blade; step eight, adjustment of the chordwise center of gravity of the blade; step nine, determination of the balance weight of the blade; and step ten, loop iteration. The method which grasps the key link of the helicopter blade design has the advantages of simple and convenient operation, and scientific and reasonable design. Practice proves that the composite material blade designed by the method can meet operating requirement for the helicopter. The method opens a new path for automatically designing the helicopter according to the Chinese situation, and can be served as a reference on the internal structure design of a wind generator blade and a screw propeller.

Description

(1) Technical field [0001] The invention relates to a method for structural design of blades, in particular to a method for structural design of composite material blades of coaxial helicopters, and belongs to the technical field of helicopter rotor design. (2) Background technology [0002] Helicopter blades are the most stressed parts in a helicopter. The structural design technology of helicopter blades has always been one of the most complex design technologies in helicopter design. The materials used in helicopter blades were originally wood, and then developed into metal materials. Since the 1980s, most helicopter blades have been made of advanced composite materials. The design technology of helicopter composite blades has been mastered by several foreign companies and has never been disclosed. Our country can only produce composite material blades according to the drawings given by foreign companies, and has not independently designed relatively successful helicop...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/46
Inventor 王吉东
Owner BEIHANG UNIV
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