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**Topology Optimization**

It is quite possible to obtain the most feasible material distribution of a designed object which is optimum in terms of stress, heat or pressure distribution during the first phase of a design process, even before dimensioning takes place. Visualization of an optimized topological layout is accomplished by extracting redundant areas or volumes from the computational domain in accordance with load balance. EDA benefits from three different methods while executing topology optimization processes:

- Sensitivity analysis based
- Gradient-based
- Genetic based

Two examples related to this topic are given below:

* Example - 1 : (Figure 1.)Topology optimization of a constant spar wing under aerodynamic loads using a density distribution method*.

Figure 1.Interior structure of a n airplane wing under aerodynamic loads. The shape is resulted from topology optimization in which the upper and lower faces are subjected to aerodynamic loads. The optimization has been done in CAEeda^{TM}

**Example - 2 **: (Figure 2.) Topology optimization of a variable spar wing under aerodynamic loads using a density distribution method

* a. Surface view of original cantilever wing geometry b. Applied pressure loads on upper and lower faces *

*c. The first step of optimization d.Final step of optimization** *

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*e. Remove low-density areas (regions below 0.3 density are removed) **f. Vertical cross-section from a one-quarter span position*

**Figure 2. **Interior structure of an airplane wing under aerodynamic loads. The shape is a result of topology optimization in which the upper and lower faces are subjected to aerodynamic loads. The optimization has been done in CAEeda.

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