A METHOD TO DETERMINE THE ALLOWABLE ERROR OF A SENSOR USED TO DISPLAY ANGLE OF ATTACK.
Abstract
The pilot-vehicle systems analysis is applied to developing a method to determine the allowable error of a sensor used to indicate angle of attack. This investigation deals only with the control of the aircraft angle of attack by the pilot's use of elevators alone. The angle of attack perturbations are caused by random inputs in the form of atmospheric disturbances. An important consideration in the design of the sensor is the relative magnitude of the sensor and gust induced angle of attack errors. Therefore, the major portion of this thesis is devoted to determining the gust induced angle of attack error. Human response techniques and the airframe dynamics of the T-39A and KC-135 aircraft were used to obtain the predicted minimum gust induced angle of attack errors for the respective aircraft. The lead pilot model form resulted in predicted minimum gust induced angle of attack errors of .10494 degrees 2 and .015 degrees 2 for the T-39A and KC-135 aircraft respectively. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1968
- Accession Number
- AD0835462
Entities
People
- John T. Kensinger
Organizations
- Air Force Institute of Technology