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(seated) Jim Tweel on left, Bill Tweel on far right
No full textfront row, (seated) left to right: Jim Tweel, owner of Jim\u27s Steak & Spaghetti House in Huntington, far right, Bill Tweel b&w. Plack on wall is for the Palmerian Society, and lists the honor roll of their member in the armed forces.https://mds.marshall.edu/bliss_enslow_add/1151/thumbnail.jp
Pat Nixon (right) and Mrs. William Rogers at the Greenbrier, ca. 1950\u27s
No full textPat Nixon, wife of Richard Nixon on right, with Mrs. William Rogers, at the Greenbrier, b&w. Nixon was the 37th President of the United States from 1969–1974 and was also the 36th Vice President of the United States (1953–1961) Attached typed note states Mrs. Nixon and mrs. Rogers were at Greenbrier with their husbands on a Memorial Day Weekend.https://mds.marshall.edu/bliss_enslow_add/1166/thumbnail.jp
A. L. Lynn, Vice pres. of Island Creek Coal Co.
No full textA. L. Lynn, Vice Pres. of Island Creek Coal Co., b&w. Sticker on back reads: A. L. Lynn, Vice President, Island Creek Coal company Barta Studios stamp.https://mds.marshall.edu/bliss_enslow_add/1177/thumbnail.jp
Mrs. Paul Stevenson
No full textMrs. Paul Stevenson, b&w.https://mds.marshall.edu/bliss_enslow_add/1178/thumbnail.jp
Broadcaster and commentator Lowell Thomas
No full textBroadcaster and commentator Lowell Thomas, b&w.https://mds.marshall.edu/bliss_enslow_add/1193/thumbnail.jp
Margaret Truman
No full textMargaret Truman, daughter of Pres. Harry Truman, b&w. Mary Margaret Truman Daniel (February 17, 1924 — January 29, 2008), widely known throughout her life as Margaret Truman, was an American singer who later became a successful writer. She was the only child of Harry S. Truman, 33rd President of the United States, and Bess Truman.https://mds.marshall.edu/bliss_enslow_add/1194/thumbnail.jp
Autographed photo of Viven Leigh as Scarlett O\u27hara
No full textAutographed photo of Vivien Leigh as Scarlett O\u27Hara, b&w. Gone With the Wind was filmed in 1939 and released in Jan. of 1940. This is a mate to the Clark Gable photo: 1979/01.0255.26.06.01.https://mds.marshall.edu/bliss_enslow_add/1180/thumbnail.jp
Levi User Guide
No full textThe User Guide for the Library of Appalachian Preaching is a Google Sheet that can be searched, sorted, and downloaded for offline use.
At the moment, Levi has only one sermon in the Library; it has a Guide of its own so the records will be complete. It includes the title, sermon text, date and place the sermon was preached, and so on. This information is available in the master list of sermons as well.https://mds.marshall.edu/levi_harry/1001/thumbnail.jp
McConnell User Guide
No full textThe User Guide for the Library of Appalachian Preaching is a Google Sheet that can be searched, sorted, and downloaded for offline use.
At the moment, McConnell has only one sermon in the Library; it has a Guide of its own so the records will be complete. It includes the title, sermon text, date and place the sermon was preached, and so on. This information is available in the master list of sermons as well.https://mds.marshall.edu/mcconnell_francisjohn/1001/thumbnail.jp
Multidisciplinary and Multi-Objective Optimal Design of a Cascade Control System for a Flexible Wing with Embedded Control Surfaces Having Actuator Dynamics
Get PDFA multidisciplinary and multi-objective optimization approach that integrates the design of the control surfaces’ sizes, active control systems, and estimator for an aircraft’s wing with three control surfaces is developed. Due to its attractive stability robustness properties, a control system based on the LQR (Linear Quadratic Regulator) is built for each control surface. The geometrical parameters of the control surfaces such as the span wise and chord lengths, the design details of the LQR penalty matrices, and the locations of the estimator poles are tuned by a widely used multi-objective optimization algorithm called NSGA-II (Non-dominated Sorting Genetic Algorithm). Four objectives are considered: minimizing impacts of external gust loads, maximizing stability robustness and extending flutter boundaries, reducing control energy consumption, and minimizing the Frobenius norm of the estimator gains. The solution of the multi-objective optimization problem is a set called Pareto set and the set of the corresponding function evaluation is called Pareto front. The solution set contains various geometrical configurations of the control surfaces with different feedback gains, which represent different degrees of optimal compromises among the design objectives. The optimization results demonstrate the competing relationship between the design objectives and necessity of handling the design problem in a multidisciplinary and multi-objective context. Three major results are obtained from inspecting the profiles of the closed-loop eigenvalues at various airspeeds 1) a unique control gain can be designed for the entire flight envelope, 2) the flutter boundaries can be infinitely extended, and 3) a unique observer gain can be designed for the entire flight envelope. The third chapter of this thesis presents a multi-objective and multidisciplinary optimal design of a cascade control system for an aircraft wing with four aerodynamic ailerons actuated by four identical brushless DC motors. The design of the control system is broken into a secondary and primary control algorithm. The primary control algorithm is designed based on the concept of LQR and then applied to mathematical model of the wing and its control surfaces to calculate their required deflections. The output of the primary controller serves as set-point for the secondary control loop which consists of the dynamic of the DC motor and Proportional Velocity (PV) based controller. Then, an optimal design of the control algorithms is carried out in multi-objective and multidisciplinary settings. Three objectives are considered: 1) the speed of response of the secondary controlled system must be faster than that of the primary one, 2) the controlled system must be robust against external disturbances affecting both control layers, and 3) optimal energy consumption. The decision variables of the primary as well as secondary control algorithms and the sizing elements of the control surfaces form the design parameter space of the optimization problem. Both geometrical and dynamic constraints are applied on the setup parameters. The multi-objective optimization problem (MOP) is solved by NSGA-II, which is one of the popular algorithms in solving MOPs. The solution of the MOP is a set of optimal control algorithms that represent the conflicts among the design objectives. Numerical simulations show that the design goals are achieved, the secondary control is always fast enough to prevent the propagation of disturbances to the primary loop, the inner and outer control algorithms are robust against disturbance inputs, and the primary control loop stays stable when the air stream velocity varies from 80 to 1000 (⁄) even at its worst relative stability value. The presented study may become the basis for multi-objective and multidisciplinary optimal design for aeroelastic structure having actuator dynamics