I N THE last decade or so, advanced composites (and advanced metal alloys) are being increasingly used in flight-vehicle and hydrodynamic-vehicle primary and secondary structures and systems [1,2]. Nowadays, 40–50% of the structural systems of advancedfighter aircraft (such as the SuperHornet F/A-18) and other newest air-superiority fighter aircraft are made of various kinds of advanced composites [2]. Similarly, the so-called advanced composite (and/or advanced metal alloy) stiffened-plate or panel systems with various configurations and geometries have been extensively employed in lightweight, high-strength airand space-vehicle primary structural systems and subsystems [3–5]. A good example for their application in aircraft structures is the wing-cover plates or panels with multistiffeners [3–5]. Additionally, they can be used in bonded repair of metallic and nonmetallic (or composite) aircraft structures and systems [6,7]. These stiffened systems are also used in lightweight, high-speed, hydrodynamic, and marine vehicle structures. Another important application for the aforementioned bonded and stiffened systems is in some civil (and/or military) ground vehicle structures and substructures as well as in other areas of advanced engineering and technology. Generally speaking, the advanced composite (and/or advanced metal alloy) stiffened systemsmay easily be categorized (or grouped) in four main groups, as shown in Fig. 1. The group II systems can further be organized in terms of the subgroups of group II, which are also given in Fig. 1. Finally, subgroup II.1 systems are divided into several classes based on the number of the bonded stiffened-plate strips, as seen in Fig. 2. The subject matter of the present study is, therefore, the free flexural (or bending) vibrations of the subgroup II.1 and class 2 type of the bonded and stiffened system of Fig. 2 (see also Fig. 3). In spite of their general practical importance in advanced engineering and high-tech applications, there are a relatively small number of studies available in worldwide open scientific and engineering literature. For instance, in the case of the free vibrations of subgroup II.1 systems with bonded stiffened-plate strips, the number of published research studies is more or less limited. In this connection, one may mention some recent investigations by Baker et al. [6,7] aswell as byYuceoglu andOzerciyes [8–14]. In the case of the dynamics of the bonded joints, there exists a relatively large number of papers. Some important studies can be found in [15–23] and more recently in [10,24–31]. In passing, one can mention some investigations on group I and subgroup 1 systems given in Yuceoglu et al. [32–34]. As mentioned before, the subgroup II.1 and class 1 (of group II) case has been investigated in some detail by Yuceoglu and Ozerciyes [8–14]. However, to the best knowledge of the present authors, the subgroup II.1 and class 2 and the subgroup II.1 and class 3, etc., case studies (see also Fig. 2) are not available in the open scientific and engineering literature or related journals. Therefore, on the basis of the aforementioned brief review, the main objectives of the present investigations are the theoretical analysis of and the general method of solution and the numerical results (consistent with the theoretical analysis) of the free-bending vibrations response of composite Mindlin plates or panels stiffened by two adhesively bonded plate strips. This means that the Presented as Paper 2009-2375 at the 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit, PalmSprings, CA, 4–7May 2009; received1October 2011; revision received 13 November 2011; accepted for publication 14 November 2011. Copyright © 2011 by Jaber Javanshir, Touraj Farsadi, andUmurYuceoglu. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code 0021-8669/12 and $10.00 in correspondence with the CCC. ∗Graduate Student, Department of Aerospace Engineering. Professor, Department of Aerospace Engineering. JOURNAL OF AIRCRAFT Vol. 49, No. 4, July–August 2012