“HoneycombAirbusMoS” criterion

X.D.1.1 “HoneycombAirbusMoS” criterion

This criterion is used to calculate honeycomb core margin of safety according to the so-called “Airbus” core failure criterion than combines the two components of out-of-plane stress tensor. The margin of safety is calculated according to the following expression:

MoS = \frac{1}{FoS \sqrt{{(\frac{τ_{L}}{σ_{L}})}^{2} + {(\frac{τ_{W}}{σ_{W}})}^{2}}} - 1,

in which $τ_{L}$ and $τ_{L}$ are the honeycomb longitudinal and transversal shear components of Cauchy stress tensor and $σ_{L}$ and $σ_{W}$ the corresponding allowables.

The arguments of the criterion are given in Table X.D.1. The method returns an Array of 8 elements according to Table X.D.2:

The four first elements correspond to the Result key on which the minimum margin of safety is calculated.
Then, the two components of the out-of-plane shear stress at critical location is given.
Then, one gives the critical (minimum) margin of safety.
The last element of the Array is a Result object that contains the margins of safety element-per-element, node-per-node...

Table X.D.1: Arguments of the “HoneycombAirbusMoS” predefined criterion


Pos.	Name	Type	meaning	can be modified?


1	dB	DataBase	DataBase (or derived)	NO

2	fos	Real	factor of safety	NO

3	allL	Real	shear allowable in L-direction	NO

4	allW	Real	shear allowable in L-direction	NO

5	stressRes	Result	Cauchy Stress Tensor	NO

Table X.D.2: Outputs of the “HoneycombAirbusMoS” predefined criterion


Pos.	Name	Type	meaning


1	ElemId	Integer	Critical Element ID

2	NodeId	Integer	Critical Node ID

3	LayerId	Integer	Critical Layer ID

4	SubLayerId	Integer	Critical Sub-Layer ID

5	sigLmax	Real	L OOP shear component of stress tensor at critical location

6	sigWmax	Real	W OOP shear component of stress tensor at critical location

7	mosMin	Real	Critical margin of safety

8	mosRes	Result	All the margins of safety that have been calculated

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