User's Guide for FAR23 Loads Program.
Abstract
The FAR23 Loads program provides a procedure for calculating the loads on an airplane according to the Code of Federal Regulations, Title l4-Aeronautics and Space, Chapter I-Federal Aviation Administration, Subchapter C-Aircraft, Part 23 Airworthiness Standards: Normal, Utility, Aerobatics, and Commuter Category Airplanes, Subpart C-Structures. Most of the detail flight loads are developed from the flight envelopes specified in FARs 23.333 and 23.345. At every point specified in the flight envelope, the airplane is balanced by a tail load reacting to the specified liner normal acceleration and the aerodynamic lift, drag, and moment about the center of gravity. The data needed to make these balancing calculations consists of: (1) weight and center of gravity, (2) aerodynamic surface geometry, (3) structural speeds, and (4) aerodynamic coefficients. After the balanced load data are developed, the critical structural loads are determined for each component. For the critical conditions, the air loads, inertial loads, and net loads are calculated. Aileron, flap, tab, engine mount, landing, and one engine out loads are also calculated. Landing loads are calculated from the landing gear geometry, landing load factor, weight, and center of gravity data. The FAR23 Loads program was developed by Aero Science Software to calculate the loads on an airplane using methods acceptable to the FAA. The program includes 20 modules that are each self contained programs designed for a specific application.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1997
- Accession Number
- ADA324952
Entities
People
- P. Miedlar
Organizations
- University of Dayton