7112MECH: Structural Dynamics - Engineering Assignment Help

Assignment Task:

Problem Formulation:
A small-scale experimental structure is built in order to analyse the effect of structural modification of a helicopter tail. The structure is made of constant cross-section aluminium beams and it needs to be restrained at one end (Figure Q.1). The details about the restrain are given in the figure.

Aluminium properties (suggested):
E = 68..70 GPa
  = 2650..2800 kg/m3

Based on your study you need to find the exact values!

A sketch of the structure is shown in figure Q1. All the dimensions are given in mm.

Length of the edge AF is 600 mm, length of the edge FB is 300 mm. The angle between AF and FB is 40°. The opposite edges are parallel. On edge AF (and the opposite edge), you can create (if necessary) a partition at 120 mm distance from point A.
 
The cross-sectional area (see Figure Q2) is constant along the length of the structure. All the dimensions are given in mm.

The rotor tail and the gearbox are modelled as a point mass of approximately 0.35 kg and is attached at the top of the structure (point B in Figure Q1). The location of this point mass will be further referred to as “rotor”.

In order to simulate a cantilever connection, the structure is restrained as shown in figure Q3. How you decide to simulate the restraint is also your task.

Task 1
Using the sketch and data provided, create a model of the structure and compare it against the frequencies given in figures Q4, and Q5 Make sure you have at least the first five modes close to the values shown in the frequency responses.

Question 1.
Please fill in the table below. Insert the values of the frequencies of your model and the errors.

Comment on the type of constraint you have used and on how this can influence the results.

Insert your comments here (no more than 100 words):

Question 2.
Comment on the influence of the damping on the frequency plot (no more than 50 words):

Question 3
Provide the comparative plots for frequency response for your model and the model provided. The match between the two responses will be important for your mark. Your response needs not to be identical with the response provided but both the amplitudes and the frequencies should be close.

Insert the comparative plot of the frequency response function given and the one you obtained (Y-direction) here:

Task 2.
Use your numerical model and run a modal dynamic analysis for the shock profile shown in Figure Q6. Recommended time period: 0.04 s.

The shock is applied to the base in Y-direction. Use all modes you have extracted for the frequency extraction step.

Question 5
Insert a plot of the base motion displacement for the whole model, total displacement of the point F and total displacement of the rotor, all in Y-direction.

Question 6
Insert a plot of the base acceleration, relative acceleration of point F in Y-direction.

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