# Problem Description#

The goal is to design the composite structure of a rotor blade to match some desired beam properties.

## Scope of the study#

This example assumes a uniform design along the span of the blade. A specific topology which is a box spar design is considered for the structure, as shown in Fig. 2. More details about the parameterization of the structure can be found in Section: Cross-sectional Parameterization and Beam Properties.

## Specifications#

Airfoil, chord length and target beam properties are summarized in Table 3.

 Airfoil SC1095 Chord length $$20.76\ \mathrm{in}$$ Mass per unit length ($$\hat{m}$$) $$0.00149\ \mathrm{lbf\cdot s^2 / in^2}$$ Torsional stiffness ($$\hat{GJ}$$) $$24.31\times 10^6\ \mathrm{lbf\cdot in^2}$$ Flapwise bending stiffness ($$\hat{EI}_f$$) $$22.20\times 10^6\ \mathrm{lbf\cdot in^2}$$ Lead-lag bending stiffness ($$\hat{EI}_l$$) $$835.00\times 10^6\ \mathrm{lbf\cdot in^2}$$ Horizontal location of the shear center from the leading edge ($$\hat{SC}_2^{le}$$) $$-5.19\ \mathrm{in}$$ Horizontal location of the mass center from the leading edge ($$\hat{MC}_2^{le}$$) $$-6.01\ \mathrm{in}$$