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Showing results for tags 'aerospace'.
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Hi all I have just discovered aerospace certification stress tool. It uses python scripts to do analytical methods . However i can not get the correct ms vaules. can someone help me to find a way to implement my own method to this tool? regards
Hi guys, I'm currently developing a complex composite structure und simulated it already with optistruct with shell elements (Mat8, PCOMPP). In order to distuguish different failure mechanisms I need analyse the stress in thickness direction of the structre. For that I used the "shell-to-solid conversion" within the aerospace menu. Now that I have a solid mesh, I'm not sure how to proceed. What property do I assign to the solid mesh ? What material card do I use for it ? Do I need to assign the material orientation to the new mesh again and if yes, how do I do that ? Thanks in advance
Hello, I am a new user to hyperworks, I am a student and currently doing a project on topology optimization on an engine fan blade, I have gone through the tutorials and built up my model, but I have some problems to create the results of topology optmization, basicly my model has two structures, one external structure (Non-design) and one internal structure(design) and they are meshed seperately, I am trying to optimize the internal strucure while under centrifugal load and aerodynamic load, therefore I set the external structure as the constraint, and applied aerodynamic load and centrifugal load on the structure, I received an error message when I was creating the result, can anyone help me check what is the problem? The message is :" Invalid design problem. All the sensitivities of response 1 (objective) are zero." I have attached my model file, please help me take a look which part is incorrect to get the result. Thanks a lot. fan-blade-project.hm
I'm trying to apply pressure loads on an aircraft wing. I've created a .csv file for the same . the first column of the file represents the wing chord, second column represents the wing span and the third represents the pressure magnitude(figure attached). When I apply this load on the wing, the pressure is not applied normal to the elements (figure attached). I've checked the element normals and they all point outward. I'm not able to figure out why the pressure is not being applied in the normal direction. Please suggest solutions. Thanks.