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Answer
With the time history monitor, you can view all results over time. In this case, it is also possible to select several parts of the structure and then export the results directly to Excel. 
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With the equivalent loads and forced vibrations addon modules, you can create result combinations that contain the governing combinations of seismic loads. To perform a design with them, they have to be combined further on the basis of the unusual combination. This combination is, for example, in the EN 1990 clause 6.4.3.4:${\mathrm E}_{\mathrm d}\;=\;\underset{}{\sum_{}^{}\;{\mathrm G}_{\mathrm k,\mathrm j}\;+\;\mathrm P\;+\;{\mathrm A}_{\mathrm{Ed}}\;+\;}\overset{}{\underset{}{\sum{\mathrm\psi}_{2,\mathrm i}\;{\mathrm Q}_{\mathrm k,\mathrm i}}}$This unusual combination has to be defined manually in RFEM. Make sure that (for a direction combination with the 100/30% rule), both created result combinations from RF / DYNAM Pro have to be added with the "Or" condition. Such a combination can be seen in Figure 02.This unusual combination can then be used for further design. It is possible to evaluate the governing internal forces as well as to import and calculate this combination in the design modules. 
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No, this option does not necessarily have to be activated to consider the selfweight. If the masses are imported from a load case that already contains the selfweight, this option must not be activated. Otherwise, the selfweight of structure is doubled. 
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In the results tables of the RFDYNAM Pro module, the stresses for solids are not displayed. To be able to display the stresses and internal forces, it is necessary to export the results to a load case or to a result combination. Then, you can look at the results in a load case or a result combination as usual.

Answer
The two solution methods 'Linear Modal Analysis' and 'Linear Implicit Newmark Analysis' are available.
Linear Modal Analysis
This solution method uses a decoupled structure that is based on the eigenvalues and mode shapes of the structure. It is essential to assign a defined natural vibration case.
This method should only be used if a sufficient number of eigenvalues of the structure have been calculated in the natural vibration case. This means that care should be taken to achieve an effective modal mass factor of the total structure of approximately 1 in all governing directions. If this is not possible, this method will lead to inaccurate results.
Linear Implicit Newmark Analysis
This is a direct time stepping method that does not require a natural vibration case and requires enough small time steps to achieve exact results.
This method is recommended for complex structures, which would require a very large number of mode shapes in order to achieve an effective modal mass factor of around 1.
If a sufficient number of eigenvalues can be guaranteed by means of the linear modal analysis, both solution methods lead to approximately the same results. For more information about both methods see the RFDYNAM Pro manual.

Answer
For some solution methods, the Rayleigh coefficients are absolutely necessary. Since only the Lehr's damping values are given in the literature, they have to be converted.
The following formula is used for converting Lehr's damping values into Rayleigh coefficients:${\mathrm D}_{\mathrm r}\:=\:\frac12\;\left(\frac{\mathrm\alpha}{{\mathrm\omega}_{\mathrm r}}\;+\;\mathrm\beta\;{\mathrm\omega}_{\mathrm r}\right)$Where α and β are the Rayleigh coefficients. It is necessary to set up a system of equations always containing the natural angular frequencies of the two most dominant mode shapes. In the case of these two mode shapes, the structure will then be damped with the specified damping value. All other mode shapes of the structure will have different damping values. These result from the curve displayed in Figure 01. The curve shows an example of the two natural angular frequencies of 10 and 20 rad/s and Lehr's damping of 0.015.It is also possible to use the 'Calculate from Lehr's Damping ...' button to activate corresponding conversion tool. 
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The results of the RF/DYNAM Pro addon modules Forced Vibrations , Nonlinear Time History and Equivalent Loads are not listed directly in the printout report. This is generally due to the fact that a lot of data and results are required for dynamic calculations.In each of the mentioned modules, it is possible to create a result combination with the envelope results. In this generated result combination, you can find the same results as in the main programs and display them in the printout report as usual.Additionally, you can print pictures in the printout report as usual. There is also an option to display the time history graphically in the printout report. 
Answer
The RF/DYNAM Pro  Equivalent Loads addon module only contains a linear analysis of structures. If you now apply a nonlinear model for the calculation, RF/DYNAM Pro — Equivalent Loads will modify it internally and treat it as a linear model. The nonlinearity in your model presents the masonry, which cannot absorb any tensile forces.
The problem is as follows: RF/DYNAM Pro — Equivalent Loads linearly calculates the equivalent loads and exports the load cases from them. However, the load cases are subsequently calculated nonlinearly on the basis of the material model, which is not entirely correct. In addition, the results are superimposed according to the SRSS or CQC method, which results in tensile and compressive forces being present in the model.
In this case, you could change e.g. the masonry to isotropic linear and work with linear properties of the material model. Additionally, it is possible to introduce line hinges at this place, which could be used to avoid moment restraint, for example.

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The differences between the two modules are explained in this FAQ .
In general, you should also calculate the same results for both addon modules if the settings are identical. However, this does not apply to existing nonlinearities. This is because no nonlinearities are considered in the RF/DYNAM Pro addon module. If the results are output via the Forced Vibrations addon module, all nonlinearities are ignored. In contrast to this, the equivalent loads are calculated on a linear system, but the exported load cases are then calculated on the real system, that is, with all nonlinearities in RFEM or RSTAB . This may lead to inconsistent results.
If you deactivate the nonlinearities for the exported load cases, they should have identical results.
The way of considering nonlinearities in the response spectrum analysis is described using the tension members in this FAQ.

Answer
The complete quadratic combination (CQC rule) must be applied if adjacent modal shapes whose periods differ by less than 10% are present when analyzing spatial models with mixed torsional / translational mode shapes. If this is not the case, the square root sum rule (SRSS rule) is applied. In all other cases, the CQC rule must be applied. The CQC rule is defined as follows:
${\mathrm E}_{\mathrm{CQC}}=\sqrt{\sum_{\mathrm i=1}^{\mathrm p}\sum_{\mathrm j=1}^{\mathrm p}{\mathrm E}_{\mathrm i}{\mathrm\varepsilon}_{\mathrm{ij}}{\mathrm E}_{\mathrm j}}$
with the correlation factor:
${\mathrm\varepsilon}_{\mathrm{ij}}=\frac{8\sqrt{{\mathrm D}_{\mathrm i}{\mathrm D}_{\mathrm j}}({\mathrm D}_{\mathrm i}+{\mathrm D}_{\mathrm j})\mathrm r^{\displaystyle\frac32}}{\left(1\mathrm r^2\right)^2+4{\mathrm D}_{\mathrm i}{\mathrm D}_{\mathrm j}\mathrm r(1+\mathrm r^2)+4(\mathrm D_{\mathrm i}^2+\mathrm D_{\mathrm j}^2)\mathrm r^2}$
with:
$\mathrm r=\frac{{\mathrm\omega}_{\mathrm j}}{{\mathrm\omega}_{\mathrm i}}$
The correlation coefficient is simplified if the viscous damping value D is selected to be the same for all mode shapes:
${\mathrm\varepsilon}_{\mathrm{ij}}=\frac{8\mathrm D^2(1+\mathrm r)\mathrm r^{\displaystyle\frac32}}{\left(1\mathrm r^2\right)^2+4\mathrm D^2\mathrm r(1+\mathrm r^2)}$
In analogy to the SRSS rule, the CQC rule can also be executed as an equivalent linear combination. The formula of the modified CQC rule is as follows:
${\mathrm E}_{\mathrm{CQC}}=\sum_{\mathrm i=1}^{\mathrm p}{\mathrm f}_{\mathrm i}{\mathrm E}_{\mathrm i}$
with:
${\mathrm f}_{\mathrm i}=\frac{{\displaystyle\sum_{\mathrm i=1}^{\mathrm p}}{\mathrm\varepsilon}_{\mathrm{ij}}{\mathrm E}_{\mathrm j}}{\sqrt{{\displaystyle\sum_{\mathrm i=1}^{\mathrm p}}{\displaystyle\sum_{\mathrm j=1}^{\mathrm p}}{\mathrm E}_{\mathrm i}{\mathrm\varepsilon}_{\mathrm{ij}}{\mathrm E}_{\mathrm j}}}$
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