The absolute peak structural integrity is no more than 25.7G. The wing was not intended for 20G, rather only ~14G in pitch and yaw planes with a vector resultant of 19.8G. What this is discussing is the pitch vector.
The original missile was designed with an X plane maneuvering load limit of ~20G. The single plane maneuverability is usually quoted as 15G, the actual load limit of the design is 12G +/- 2 as stated (14G). 14 squared is 196. 196 + 196 = 392. The square root of 392 is 19.79 G @Flame2512
The combined plane overload is intended to be 20G. @David_Bowie They should either reduce the Sedjil to single plane of 14-15G or model the combined plane maneuvering limit of 20G. If they use combined plane - they should do so for the Phoenix as well which should be approximately 17G per axis and 24G combined with a similar overshoot of +/-2G that would be ~26.8G. To round that out we can use your source and simply put it at 25G.
To put simply the changes that were made to make the missile more reliable;
The maximum fin deflection is 22 degrees. The missile sometimes had a tendency to maximum pitch (22 degrees) with 20G overload towards targets and would then need to roll to keep up with target’s defensive maneuver.
Since 22 degrees is already the maximum deflection, roll was not possible while maintaining target intercept and the missile would lose control / breakup.
The solution was to allow 20G maximum pitch but limit fin deflection to 15 degrees in final intercept, this likely led to inferior over-leading characteristics that drained the missile of energy if the target chose to crank sooner… but the missile could actually reach the target. 15 degrees allowed a further 7 degrees for rapid roll response without causing too much pitch-roll-yaw type coupling and oscillations.
my issue is how can the in game Fakour sits at ~600kg, while the dimensions are smaller than the AIM-54…
Something doesn’t add up
There is likely a lot of empty space inside the AIM-54, including inside the motor.
Also, the density of the propellants might be different (e.g. M112’s propellant might have higher aluminum content).
A cylinder with a length of 3.96m and a diameter of 356mm has a volume of 394 liters (And obviously most parts that are used in a missile, including the body, warhead, and propellant, have a density quite a bit higher than 1).
Just look at this chart. The M112 motor itself, which has a diameter of 356mm and a length of just 2.678m (with “tail can and 3 fins”), already weighs almost as much as a full blown AIM-54A.
The missile can reach 20G in single plane per the document, that is the commanded limit due to structural concerns.
Though I think it highlights how important it is Gaijin fix the Phoenix so they can begin balancing the Tomcat.
I was only highlighting how most missiles mounted in “X” configuration actually can, and do, maneuver in combined plane as needed.
This will be a separate suggestion, currently we only implement single plane maneuverability, so there will be a bug report to revert this and a suggestion to implement dual plane maneuverability.
Literally says originally the wings were 14G’s single plane, and then extended to 20G’s single plane creating “loads that were significantly than those originally designed for”
From what I understand from this, originally I-Hawk’s wings were designed for the same G limit as basic Hawk, but then during development, they changed the “threat g level” from 3 g to 6 g and consequently, changed the missile guidance and increased the missile G and AoA limits to meet the new requirements:
From what I understand from this, the autopilot uses single plane maneuvering as long as there is no need to use max pull, and switches to dual plane when it needs max pull.
Though, another interpretation for this could be that the missile autopilot actually is not capable of dual plane maneuvering @MiG_23M@David_Bowie :
Because the autopilot is not capable of dual plane maneuvering, it cannot equally distribute the load on both pairs of wings. So:
1- “When pitch and yaw are limited” (e.g. The autopilot is trying to pull 5G in one axis and 10G in another axis), the forces are not “being distributed equally on both sets of wings”.
1- Only when the autopilot is trying to pull max G in both axes (i.e. “When pitch and yaw are not limited”, i.e. When the autopilot is trying to pull 20G in pitch and 20G in yaw), the forces are “being distributed equally on both sets of wings”
This is also more consistent with the rest of the document, highlighted here and here.
You are not understanding what is being said. The missile achieves 20G in single or dual plane. It does not need to use dual plane to achieve 20G. My point is that in real life, it maneuvers most of the time in dual plane so as to maintain roll control at higher angles of attack. The proof is just further evidence that tail control missiles launched in “X” configuration primarily use dual plane.
They said a 30% load factor was applied to that, which is ~18.2G
Yet, still it states quite clearly that the autopilot will pull in single plane up to 20G.
As shown. @sudo_su1 Settle down on this one, I got it.
