Computer Simulation of an Aircraft Seat and Occupants(s) in a Crash Environment - Program SOM-LA/SOM-TA User Manual

Details

• Creators:
  Laananen, David H.
• Corporate Creators:
  Arizona State University. Dept. of Mechanical and Aerospace Engineering
• Corporate Contributors:
  United States. Department of Transportation. Federal Aviation Administration. Technical Center
• Subject/TRT Terms:
  • Computer program documentation
  • Crashworthiness
  • Finite element method
  • Mathematical models
  • Restraint systems
  • Seats
  • Simulation
  • Small aircraft
  • Vehicle occupants
• Publication/ Report Number:
  OOT/FANCf-90/4
• Resource Type:
  Tech Report
• Geographical Coverage:
  United States
• Edition:
  Final Report
• Contracting Officer:
  DeFiore, Thomas
• Corporate Publisher:
  United States. Department of Transportation. Federal Aviation Administration. William J. Hughes Technical Center
• Abstract:
  A three-dimensional mathematical model of a seat, occupant(s), and restraint system has been developed for use in aircraft crashworthiness analysis. Programs SOM-LA (Seat/Occupant Model-Light Aircraft) and SOM-T A (Seat/ Aircraft Model -Transport Aircraft) combine a lumped parameter model of aircraft occupants with a finite element model of the seat structure. SOM-LA models a single occupant, whereas SOM-TA has the capability to model up to three passengers. The intent of these programs is to aid in evaluation of the performance of aircraft seat and restraint systems in crash environments. Because the programs have been written for use primarily by engineers concerned with the design and analysis of seats and restraint systems, an effort has been made to minimize the input that is required to describe the occupants. Characteristics of two standard occupants, one dummy and one human, are included within the program, and an option is provided to simulate other occupants by providing additional input data. The structural model includes beam elements and has a maximum capacity of approximately 450 degrees of freedom, as determined by array dimensions within the programs. The beam elements can accommodate large plastic deformations and include the capability for cross section reduction due to local instabilities. Four different cases are described, and a listing of input data is presented for each. Examples of material properties to be used as program input are included in an appendix. Details of the mathematical models and solution algorithms for the SOM-LA program were reported in DOT/FANCT82/33-1 (March 1983) and for the SOM-TA program, in DOT/FANCT-86/25-1 (August 1986). The program documentation, including instructions for operation, was originally presented for each program in a User Manual that was published as a second volume of each of the above reports (DOT/FANCT82/33-11 and DOT/FANCT-86/25-11). Due to program modifications, those separate manuals are now superseded by this single document.
• Format:
  PDF
• Funding:
  DTFA03-89-A-00004
• Download URL:
  https://rosap.ntl.bts.gov/view/dot/93163/dot_93163_DS1.pdf
• File Type:
  [PDF - 4.85 MB]
• Collection(s):
  FAA William J. Hughes Technical Center for Advanced Aerospace
• Main Document Checksum:
  urn:sha-512:9f98f1f29d59af813097a1558cde1d0e5faf8617b715218e324d325e0f11e320df374216bdd9d10c7992549ae5b089271a929ec80ed471e2a3efaf98063c1462