Accession Number : ADA118071

Title :   Lateral Flying Qualities of Highly Augmented Fighter Aircraft. Volume II.

Descriptive Note : Final rept. Mar 80-May 82,


Personal Author(s) : Monagan,Stephen J ; Smith,Rogers E ; Bailey,Randall E

PDF Url : ADA118071

Report Date : Mar 1982

Pagination or Media Count : 282

Abstract : This in-flight simulation experiment, using the USAF NT-33 vairable stability aircraft operated by Calspan, was undertaken to generate lateral-directional flying qualities data applicable to highly augmented fighter aircraft. In particular, the effects of time delay and prefilter lag in the lateral flight control system were studied for representative Flight Phase Category A and C tasks. The combined effects of these elements as well as the effects of nonlinear command gain and high Dutch roll damping were also evaluated. Tasks included were actual target tracking, air refueling and precision landing as well as special Head-Up Display (HUD) tracking tasks. Results indicated a properly designed HUD bank angle tracking task is a valid flying qualities evaluation task. Data show that lateral flying qualities are very sensitive to control system time delay and very short values of roll mode time constant typically result in poor lateral flying qualities. Excellent separation of the data into flying qualities levels is achieved for the Category A task data using time domain equivalent systems parameters. An optimum equivalent time constant value of 0.5 sec is indicated by the data; sensitivity to equivalent time delay is a minimum at this value. Volume I contains the body of the report, while Volume II consists of the Appendices.

Descriptors :   *Fighter aircraft, *Flight control systems, *Flight simulation, *Variable stability aircraft, Experimental data, Augmentation, Jet lag, Roll, Damping, Optimization, Test and evaluation, Comparison, Configurations, Parameters

Subject Categories : Attack and Fighter Aircraft
      Test Facilities, Equipment and Methods

Distribution Statement : APPROVED FOR PUBLIC RELEASE