Since time and motion study was developed, the necessity for standard times tor motions has been recognized to be very useful in many industrial applications. Among many attempts to set up predetermined times for manual motions, the Methods Engineering Council has established certain workable standard data known as Methods-Time Measurement which is applicable throughout industry. With the purpose to appraise the value of this new work-measurement technique of MTM, this study was conducted and it was devoted to investigating their data on the Reach and Move motions involving body rotation movements. The findings of this investigation do indicate that the MTM method of determining the time of Reach motion has inconsistencies and thus is weak. As a result, a suggested method of measuring the length of motion is made and the time values obtained may serve as a guide for further study on industrial operations by which they can be conclusively verified. Also, it was found that time data can be derived for moves in the area above forty-two inches and that further study should be made to supplement this data for industrial use. / Master of Science

Research has been conducted in recent years to determine the dynamic behavior of aircraft in unusual flight attitudes, particularly at very high angle-of-attack or post-stall conditions. The possibility that future advanced fighter aircraft will have the ability to perform controlled maneuvers at such attitudes is indicated by the current military aircraft flying qualities specification, MIL-STD-1797. As it becomes more important to understand the dynamics of aircraft at such flight conditions, the need for a meaningful and useful assessment of aircraft departure resistance in varying attitudes will increase proportionally. This thesis surveys some of the measures of departure susceptibility currently in use and examines a candidate for a new departure resistance criterion which offers distinct advantages over the traditional metrics. The new departure resistance criterion, called DP_SSV is essentially a measure of how much uncertainty the nominally stable plant can tolerate before being driven unstable. DP_SSV is calculated using structured singular values. In this thesis, DP_SSV is calculated over various flight conditions for a typical high-performance fighter aircraft which is represented by a full six degree of freedom, nonlinear simulation. The results are compared with those obtained by using a traditional departure susceptibility metric and by examining the eigenvalues of linearized forms of the aircraft model. The new criterion DP_SSV is shown to provide more information about the departure susceptibility of an aircraft than C_{ηβ_DYN} traditional metric, and to produce results in good agreement with the eigenvalue analysis of the stability of the aircraft for the conditions studied. The interpretation of DP_SSV is discussed, and suggestions for future investigation are also presented. / Master of Science

The design of modern high-performance aircraft is toward increased aerodynamic efficiency, decreased structural weight, and higher flight speeds. Preliminary designs often exhibit a flutter instability within the desired operating envelope of the aircraft. Passive methods which have been used to solve the flutter problem include added structural stiffness, mass balancing, and speed restrictions. These methods may result in significant weight penalties. Studies by Boeing (ref. 1) show that weight penalties as high as 2 to 4% of the total structural weight may be required to solve the flutter problem passively by increasing the structural stiffness. Therefore, there is considerable interest in alternative methods of increasing the flutter speed beyond the original unaided value. / Master of Science