NDLI: Integration of dynamic, aerodynamic and structural optimization of helicopter rotor blades

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Integration of dynamic, aerodynamic and structural optimization of helicopter rotor blades

Content Provider	NASA Technical Reports Server (NTRS)
Author	Peters, David A.
Copyright Year	1987
Description	The purpose of the research is to study the integration of structural, dynamic, and aerodynamic considerations in the design-optimization process for helicopter rotorblades. This is to be done in three phases. Task 1 is to bring on-line computer codes that could perform the finite-element frequency analyses of rotor blades. The major features of this program are summarized. The second task was to bring on-line an optimization code for the work. Several were tried and it was decided to use CONMIN. Explicit volume constraints on the thicknesses and lumped masses used in the optimization were added. The specific aeroelastic constraint that the center of mass must be forward of the quarter chord in order to prevent flutter was applied. The bending-torsion coupling due to cg-ea offset within the blade cross section was included. Also included were some very simple stress constraints. The first three constraints are completed, and the fourth constraint is being completed.
File Size	984916
Page Count	34
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19880000630
Archival Resource Key	ark:/13960/t4nk87v0s
Language	English
Publisher Date	1987-11-02
Access Restriction	Open
Subject Keyword	Aerodynamics Finite Element Method Thickness Structural Design Constraints Rotor Blades Turbomachinery Stiffness Applications Programs Computers Aeroelasticity Aerodynamic Characteristics Helicopter Design Optimization Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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