The flexible wearable chair is like a light weight mobile exoskeleton that allows people to sit anywhere in any working position. The traditional chair is difficult to move to different working locations due to its large size, heavy weight (~5 -7 kg) and rigid structure and thus, they are inappropriate for workplaces where enough space is not available. Flexible wearable chair has a gross weight of 3 kg as it utilizes light-weight aluminium alloy members. Unlike the traditional chair, it consists of kinematic pairs which enable taking halts between continuous movements at any working position and thus, it is capable of reducing the risk of the physical musculoskeletal disorder substantially among workers. The objective of this paper is to focus on the mechanical design and finite element analysis (FEA) of the mechanism using ANSYS ® software. In the present work, all the parts of the mechanism are designed under static load condition. The results of the analysis indicate that flexible wearable chair satisfies equilibrium and stability criterion and is capable of reducing fatigue during working in an assembly line/factory.
In this paper, whole work is done for hybrid laminated composite beam which is made of three composite materials boron-epoxy, aramid-epoxy, and s-glass-epoxy. A numerical study, using finite element method is carried out to analyse the free transverse vibration behaviour of composite beam. ANSYS APDL is used as a finite element solver to simulate the free transverse vibrations. A variety of parametric studies is performed to check the effects of various parameters associated with crack geometry and laminate property on the three least natural frequencies. Parameters for the investigation are included as fibre volume fraction, ply angle for (0°/Φ°/0°/Φ°/0°/90°/(90-Φ)°/0°/(90-Φ)°/0°) stacking sequence, location of crack geometry relative to the restricted end, depth of crack (a) and support conditions (C-C & C-F configuration) for hybrid laminated composite beam, trend of the least three transverse natural frequencies is also discussed in detail. It is noted that maximum value of natural frequency occur at Φ equals to 90° for both (CC) and (C-F) and for relative crack depth 0.5 to 0.6, there is sharp decrement in natural frequency for (C-F). Other factors of laminate and crack geometry are also discussed in present analysis, which shows a great scope of this hybrid composite with (0°/Φ°/0°/Φ°/0°/90°/(90-Φ)°/0°/(90-Φ)°/0°) stacking sequence in the field of aviation and prosthetics.
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