Three Point Bending Test
HITEC UNIVERSITY
Three Point Bending Test
By
Group#04
Members Name
Usman Rasheed (ME-131)
Sarnad Ali Shah (ME-108)
Farrukh Muhummad Aoun (ME-30)
Shahzaib bakht (ME-84)
Hafiz Abdul Hadi ()ME-32
A PROJECT SUBMITTED
IN PARTIAL FULFILLMENT OF THE
REQUIREMENTS FOR THE COURSE OF
MECHANICS OF MATERIALS
IN MECHACNICAL ENGINEERING
B.Sc. Mechanical Engineering
HITEC UNIVERSITY
January, 2011
Projector Supervisor’s: Mr. Sheharyar Malik
Taxila, Pakistan
January, 2011
ABSTRACT
In this report different mathematical models for a ballistic missile are derived and simulated for the complete guided control system. In this research work V-2 rocket is taken as an example. Equations of motion are used in SIMULINK to perform simulations. An optimum trajectory is in accordance with launch angle and different burnout parameters. The missile would follow this ideal trajectory in the absence of any disturbance. But in real flight there are various errors and perturbations that make the vehicle not to follow the designated path. To have a successful flight it is required to remove the effect of these disturbances through a properly designed control and guidance system. 6DOF program is simulated which is then incorporated with the pitch orientation controller and a roll stabilization controller and results are simulated in accordance. Inertial navigation mechanization model is constructed in Simulink to propose an ideal navigation model for the rocket system. The controller analysis is performed at various points in the trajectory and the measurements are made in frequency domain. A comprehensive roll control model is designed along with pitch controller using Simulink and various frequency domain plot; bode plots & root locus for analysis.
Aim
To calculate the modulus of elasticity in bending Ef, flexural stress σf, flexural strain εf and the flexural stress-strain response of the material by performing three point bending flexural test
Theory
This
Three Point Bending Test
By
Group#04
Members Name
Usman Rasheed (ME-131)
Sarnad Ali Shah (ME-108)
Farrukh Muhummad Aoun (ME-30)
Shahzaib bakht (ME-84)
Hafiz Abdul Hadi ()ME-32
A PROJECT SUBMITTED
IN PARTIAL FULFILLMENT OF THE
REQUIREMENTS FOR THE COURSE OF
MECHANICS OF MATERIALS
IN MECHACNICAL ENGINEERING
B.Sc. Mechanical Engineering
HITEC UNIVERSITY
January, 2011
Projector Supervisor’s: Mr. Sheharyar Malik
Taxila, Pakistan
January, 2011
ABSTRACT
In this report different mathematical models for a ballistic missile are derived and simulated for the complete guided control system. In this research work V-2 rocket is taken as an example. Equations of motion are used in SIMULINK to perform simulations. An optimum trajectory is in accordance with launch angle and different burnout parameters. The missile would follow this ideal trajectory in the absence of any disturbance. But in real flight there are various errors and perturbations that make the vehicle not to follow the designated path. To have a successful flight it is required to remove the effect of these disturbances through a properly designed control and guidance system. 6DOF program is simulated which is then incorporated with the pitch orientation controller and a roll stabilization controller and results are simulated in accordance. Inertial navigation mechanization model is constructed in Simulink to propose an ideal navigation model for the rocket system. The controller analysis is performed at various points in the trajectory and the measurements are made in frequency domain. A comprehensive roll control model is designed along with pitch controller using Simulink and various frequency domain plot; bode plots & root locus for analysis.
Aim
To calculate the modulus of elasticity in bending Ef, flexural stress σf, flexural strain εf and the flexural stress-strain response of the material by performing three point bending flexural test
Theory
This