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**Sandwich Panels**

An aircraft quality sandwich panel has the characteristics listed in the table.

**(a)** Use the data and equations 12.30, 12.31, and 12.32 from the text to calculate the equivalent density, flexural modulus, and strength.

**(b)** Plot these on a copy of a Modulus-Density chart, a Strength-Density chart, and a Modulus-Strength chart (Figures 3.3, 3.4, and 3.5). Do the flexural properties of the panel lie in a region of property space not filled by monolithic materials?

**Data for Glass Fiber / Aluminum Honeycomb Sandwich Panel:**

- **Face Material:** 0.38 mm glass fiber/epoxy
- **Core Material:** 3.2 mm cell, 97.8 kg/m³, 5052 Aluminum honeycomb
- **Panel Weight per Unit Area (\(m_e\)):** 2.65 kg/m²
- **Panel Length (\(L\)):** 510 mm
- **Panel Width (\(b\)):** 51 mm
- **Panel Thickness (\(d\)):** 10.0 mm
- **Flexural Stiffness (\(E_I\)):** 67 N.m
- **Failure Moment (\(M_f\)):** 160 Nm

Answer :

Sandwich panels are composites made of a lightweight, thick core structure (like honeycomb) and two thin laminate outer skins.

What does an aircraft sandwich panel do?

  • A sandwich panel typically consists of two stiff outer skins around a low stiffness, low density inner core, both of which are held together by a structural glue.
  • Usually, aerospace-grade aluminum or strong carbon fiber is used to create the outer skins.
  • The superior insulation of polyurethane sandwich panels is one of their most significant characteristics.
  • Because of the poor thermal conductivity of the plates' core, they provide better insulation.
  • A lightweight core material is sandwiched between two delicate yet rigid facesheets to create a sandwich panel.
  • The sandwich panel behaves as a composite material that is stronger than the sum of its parts if the whole thing deforms.

To learn more about aircraft sandwich panel refer to:

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