Calculation of Airloads for a Flexible Wing via NASTRAN.

Abstract

This thesis describes the use of the NASTRAN program (Level 17.0) in the calculation of flexible wing airloads and stresses. The problems of interfacing aerodynamic and structural models are discussed with assumptions needed to solve them. Two different methods of transferring the aerodynamic forces into a structural load vector are presented. A Direct Matrix Abstraction Program was developed for use in these calculations. This sequence is limited to the use of one doublet-lattice panel for the aerodynamic model and requires several new data blocks for execution. Although these data blocks were input with the bulk data deck to test the sequence, a new preliminary module has been constructed to build them internally. The results of this investigation show that NASTRAN can be used in calculating the airloads and stresses for a flexible wing. This new sequence has extended the capability of NASTRAN to allow for the application of internally generated steady airloads to the structural model. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1980
Accession Number
ADA094770

Entities

People

  • Lance Eliot Chrisinger

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Forces
  • Aerodynamic Loading
  • Air Force
  • Aircrafts
  • Camber
  • Coefficients
  • Computer Programs
  • Dynamic Pressure
  • Engineering
  • Grids
  • Lifting Bodies
  • Lifting Surfaces
  • Planform
  • Pressure Distribution
  • Shape
  • Structural Loads

Readers

  • Aerodynamics/Aeronautics.
  • Computer Science/Computer Engineering/Data Science/Digital Signal Processing.
  • Structural Health Monitoring of Composite Structures.