Author
Deepak Kumar
Bio: Deepak Kumar is an academic researcher from Indian Institute of Technology Madras. The author has contributed to research in topics: Airfoil & Camber (aerodynamics). The author has an hindex of 4, co-authored 9 publications receiving 37 citations.
Papers
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TL;DR: The results show that the double corrugated variable camber morphing configuration can take more structural load without harmful deformation and the aerodynamic efficiency is higher compared to other configurations.
22 citations
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TL;DR: In silico screening showed that one of the molecules, VCD-004, exhibits improved mode of binding to bacterial DNA gyrase, suggesting that it impedes the development of resistance better than clindamycin.
8 citations
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04 Nov 2013
TL;DR: In this paper, a system that manages online advertising is presented, which identifies a user segment for targeting using an online advertisement slot and obtains a distribution associated with winning bids for online advertisements shown to the user segment.
Abstract: The disclosed embodiments provide a system that manages online advertising. During operation, the system identifies a user segment for targeting using an online advertisement slot. Next, the system obtains a distribution associated with winning bids for online advertisements shown to the user segment in the online advertisement slot. Finally, the system uses one or more points from the distribution as bid suggestions for advertising campaigns associated with the user segment.
7 citations
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TL;DR: In this article, an iterative scheme for geometrically large deflection analysis of corrugated structures using the nonlinear shooting method is proposed, which is extended to various boundary conditions (fixed-fixed and fixed-hinged) and loading conditions (point loads and uniformly distributed load).
Abstract: This manuscript proposes an iterative scheme for geometrically large deflection analysis of corrugated structures using the nonlinear shooting method. The corrugated structure is modeled by discretizing it in several corrugated units. The solution of each unit is obtained assuming it to be consistering of several beam elements. Finally, the deflection of a corrugated structure is calculated assembling the deflection of each of the corrugated units. The formulation has been extended to various boundary conditions (fixed–fixed and fixed–hinged) and loading conditions (point loads and uniformly distributed load). This shows the versatility of the methods in solving various problems. Furthermore, two prototypes of the corrugated structure are fabricated using aluminum and carbon fiber reinforced polymer (CFRP) laminate, and a moment actuation test is performed. The deflections of these prototypes obtained using the proposed iterative scheme are compared with the numerical model and validated with experiments, and results are found to be in good agreement.
6 citations
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19 May 2020TL;DR: In this article, a conceptual design of a morphing wing is proposed based on the insights gained from the numerical analysis that uses two hybrid bistable symmetric laminates as skin with a corrugated core.
Abstract: In the recent past, bistable laminates have been widely studied for their potential in wing morphing applications. The existence of multiple stable states makes them extremely viable as structural elements. However, for successful deployment, these laminates must be integrated into a larger mechanism. For integration, the bistable laminates are required to be clamped to a larger structure without the loss of bistability. In this work, an attempt has been made to understand the effect of integration (i.e., using different structural constraints and clamping) on the bistability and the snapthrough performance of a special class of hybrid bistable symmetric laminates (HBSLs). The structural analysis has been carried out using FEA software ABAQUS. Subsequently, a conceptual design of a morphing wing is proposed based on the insights gained from the numerical analysis that uses two HBSLs as skin with a corrugated core. Finally, using the analysis guidelines, two HBSL skins and a circular corrugated core are manufactured and integrated to show the possibility of using such bistable laminates as skin.
5 citations
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TL;DR: This paper presents a review of SMAs applications in the aerospace field with particular emphasis on morphing wings, tailoring of the orientation and inlet geometry of many propulsion system, variable geometry chevron for thrust and noise optimization, and more in general reduction of power consumption.
Abstract: Shape memory alloys (SMAs) show a particular behavior that is the ability to recuperate the original shape while heating above specific critical temperatures (shape memory effect) or to withstand high deformations recoverable while unloading (pseudoelasticity). In many cases the SMAs play the actuator's role. Starting from the origin of the shape memory effect, the mechanical properties of these alloys are illustrated. This paper presents a review of SMAs applications in the aerospace field with particular emphasis on morphing wings (experimental and modeling), tailoring of the orientation and inlet geometry of many propulsion system, variable geometry chevron for thrust and noise optimization, and more in general reduction of power consumption. Space applications are described too: to isolate the micro-vibrations, for low-shock release devices and self-deployable solar sails. Novel configurations and devices are highlighted too.
88 citations
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TL;DR: Flight-test experiments demonstrate that the total AVCW carrying the developed adaptive control system (ACS) can enhance UAV flight efficiency by 14.1% comparing to a traditional fixed-wing of Talon UAV and indicates that employing the whole AVCW structure can sustain a larger flight load, without increasing the weight of entire wing structure except for the actuator device and adhesives.
24 citations
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TL;DR: In this paper, the effects of the angle of attack and deflection rate on aerodynamic characteristics of the morphing wing were examined, and a method was developed to delay stall by using the flexible periodic trailing-edge deflection.
22 citations
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TL;DR: Performance comparison between the polymorphing wing and the baseline wing (non-Morphing) shows that chord morphing improves aerodynamic efficiency at low angles of attack while camber morphhing improves efficiency at high angles ofAttack.
20 citations
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TL;DR: In this paper, the authors investigated the snap-through characteristics of a special class of hybrid bistable symmetric laminate (HBSL) subjected to different loading constraints and imperfections.
19 citations