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In this article microhexapod robot is introduced as a micromanipulator. First hexapod which is a parallel mechanism is investigated and also modifications that is needed for the improvement of positioning accuracy and eliminating factors such as clearance and friction in the conventional joints. Doing this, spherical and universal joints are replaced with flexural beam type joints after scaling down the hexapod. Then the degrees of freedom of flexure joints are achieved and after that the instantaneous center of rotation of flexure joints is derived for every finite twist of moving platform and it is shown that the kinematic chain of each pod of microhexapod consists of two spherical joints and a prismatic actuator; but it differs from hexapod in a way the location of the instantaneous center changes with the change of the finite twist of moving platform. Thereafter the velocity kinematics of microhexapod is solved using screw theory. In addition, using the analytical formula, the velocity of actuators was calculated for some case studies; linear motion of moving platform with constant velocity and also constant acceleration and also movement with constant velocity in a circular path. The results are verified with the finite element analysis and shown good agreement.

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The aerodynamic characteristics of nine configurations of supersonic continuous deflectable nose guided missiles have been investigated. Then the optimized geometry is achieved based on the maneuverability from aerodynamic and flight dynamic point of view. The studied configurations consists of a spherical nose tip, a tangent ogive, one set of stabilizing tail fins and a cylindrical body that its mid-section is flexible to form an arc of a circle. So the cylindrical body consists of a fix part in vicinity of nose, middle flexible part and main body with stabilizers. The effects of fix length and flexible length parameters on the aerodynamic and flight dynamics of guided missile have been studied. A code has been developed to solve full Navier-Stokes equations using finite volume and modified Baldwin-Lomax turbulence model. Multi-block technique is also used to solve main body and fin parts flow field. Further, a 3 degree of freedom code has been developed to compare planar flight dynamic of missiles. It is found that missiles with bigger lengths for fix and flexible parts show more aerodynamic maneuverability, but drag force grows concurrently. Flight dynamic analysis shows that drag effect is negligible and aerodynamic maneuverability analysis is compatible with flight maneuverability.

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The flight dynamics of nine configurations of supersonic continuous deflectable nose guided missiles have been investigated. The studied configurations consist of a spherical nose tip, a tangent ogive, a set of stabilizing tail fins and a cylindrical body that its mid-section is flexible to form an arc of a circle. So the cylindrical body consists of a fix part in vicinity of nose, middle flexible part and main body with stabilizers. The effects of fix length and flexible length parameters on the flight dynamics of surface to surface, antiaircraft and antimissile missiles have been studied. A code has been developed to solve full Navier-Stokes equations using finite volume and modified Baldwin-Lomax turbulence model. Further, a 3 degree of freedom code has been developed to compare planar flight dynamics of missiles. This code consists of a guidance subroutine based on pure persuit law. The results show that even increase of fixed and flexible lengths enhance the maneuverability of the missile, but in some scenarios this can lead to increased flight time and more errors in the target engagement. Deflected nose relocates mass center away from the axis and a thrust vector torque is created. Study of surface to surface scenario shows that this torque improves accuracy of targeting and the ability of target dislocation. In air defense missiles, increase of Fix and Flex variables, will extend the limits of allowable firing angle. However, a heavy nose increases the role of thrust torque and subsequently decreases the role of nose geometry.

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With the arrival of composite materials, because of their unique properties, the ideas were presented in order to strengthen and improve their performance. The ideas were causing building of Grid composite structures. These structures have most widely used in the aerospace, missile and Marine industry because have made ideal mechanical properties: special stiffness and high strength against impact and fatigue. Grid composite plates are made from thin composite shell connected by series composite ribs. Ribs network results in a significant increase in stiffness and strength of structure. In this research, experimental and numerical investigations of effect of Shape of ribs have been on flexural behavior of grid composite plates. For this purpose, three types of Grid plates were considered with triangle, square and rhombic ribs. For the building these plates, silicone mold was designed and built and also was used for making plates from hand lay-up and hand-wound layer technique. Samples were subjected to three-point bending test that for this purpose, the fixture was designed and built. From numerical solution of the problem and compared with experimental results was observed that there is very little difference between experimental and numerical results. Experimental results show that special flexural stiffness of plate with square rib is 1.92 and 1.88 plate with triangular and rhombic ribs, respectively. Also, the flexural strength of plate with square rib is 1.58 plate with triangular rib. Thus plate with square rib is the highest stiffness and bending strength Keywords