Discuss necessity of maximum_structrual_payload_mass

Discussion

Summary

Lets discuss the necessity of maximum_structrual_payload_mass in the aircraft exchange file. Following situation: The user can set the number of passenger, its weight (body and luggage) and extra cargo mass. Also it is required to define a maximum_structrual_payload_mass. If number of passenger * weight + cargo > maximum_structrual_payload_mass the program thouws an error. So that means if the payload exceeds a limit (I guess from the naming a structural limit of the aircrafts body)

I currently do not understand the role of the maximum_structrual_payload_mass. Is that really a TLAR and does the user really knows this value? In conceptual aircraft design, we dont have a fixed structure - so how should we know this limit?

So my question is how uses that value (I checked in the code and saw it in create_mission_xml, mission_analysis, performance_assessment and weight_and_balance).

Could the responsible explain for what they use this node and why they are not using the actual payload+cargo?

Looking forward to a fruitful discussion ✈️