IRL max target maneuvering G is also greatly influenced by warhead size and proximity fuze radius.
A bigger missile like Phoenix or R-37 can target an 8G manuevering target while doing less than 30Gs while smaller missiles with smaller warhead would require greater maneuverability to achieve 8G.
48g at mach 6 wont be as much as it sounds, + what direct support said
Should really only be 35G multiplane, 25G single plane. Post cold war UK materials from Germany place it at 25G single plane.
The guidance unit listed by the manufacturer has a G rating of 35 in any direction. This means it cannot be 35G single plane and could only be 25G single plane.
If it was 35G single then the multi plane figure would be greatwr than 35G which would kill the guidance unit.
Nothing I’ve seen from Russian docs talk about dual/single plane maneuverability. Also would this mean it would be only on par with r-24 with maneuverability? I think that is impossible.
yea i would assume its between 20-30Gs irl.
yeah the longer fuse distance would require less Gs to be pulled for a target
According to the manufacturer of the GCS on R-27 it can only hand a maximum of 35G for 6 seconds, this is the peak combined plane overload as if this was 35G single plane than the combined plane overload would be 50G ( 35G² + 35G² = 50G² ) which is well outside the operating specifications of the GCS which can only briefly handle 35G.
If the missile was 25G single plane, then the maximum combined plane overload would be 35G which it would briefly achieve before impact which lines up with the 6 second limit within the GCS.
Блок управления БУ-72 сер. 2 совместно с блоком электрических рулевых машин ПК-47 в составе системы управления 9В-1023 предназначен для стабили зации и управления самонаводящихся ракет К-27 и К-27Э класса «воздух-воздух» во всех условиях боевого применения с использованием сигналов от головок са монаведения (ГСН) различных типов.
Технические условия блока управления БУ-72 сер. 2:
- Тип блока: микроэлектронный (на элементах микроэлектроники)
- Масса: не более 4,8 кг
- Габариты: Ø 200х185
- Потребление тока в совместном и автономном полете:
* по цепи трехфазного напряжения переменного тока 36В±5, 1000Гц±5% в каждой фазе не более 0,5А;
* по цепи напряжения постоянного тока ±22В± 15% не более 0,7А;
* по цепи напряжения постоянного тока ±9В±15% не более 0,1 А;
* по цепи напряжения постоянного тока 27В±10% не более 1,7А.- Время готовности:
* по гиромоторам не более 30с;
* по электронной части не более 0,2с.- Высотность: до 27000м
- Допустимые линейные нагрузки:
* по оси х в направлении полета nx=35g в течении 6с, в направлении против полета nx=15g в течение 54с;
* по осям у и z: nу = 35g, nу = 35g в течение 15с.- Интервал температур: от минус 60°С до + 65°С
- Относительная влажность окружающего воздуха: до 98% при температуре +40°С
- Нулевые ошибки:
* а) I и II каналов, приведенные к перегрузке - 0±0,3 ед.п.
But not only do I have that Russia manufacturer source I have this NATO source which includes Germany from 1992 who operated R-27;
but why are you assuming that it must have used combined plane? each plane can pull 35 gs separately, there’s no need for combined plane
Because if its 35G in X and 35G in Y its just 35G in any direction. If the single plane value of R-27 was 35G then in a combined plane turn the missile could pull up to 50G which would break the GCS which can only handle 35G for 6 seconds.
Just so happens 35G MP is 25G SP (25G² + 25G² = 35G²) which lines up with the manufacturer limits on the GCS.
Nx = 35g for 6s is axis of forward flight course…
Ny and Nz are 15s and Y and Z axis are aligned with wings the fact you could got if you read the image by me which @kizvy posted as well as overload sensors being aligned the same
Which contradicts primary source in numerous numbers of launch altitudes as well R-73 having 45G tho we know it’s 60G single or dual plane (doesn’t matter, you don’t get 45 from 60)
Is the 35 G limit applied to any axis? If the missile can pull 35 G in a single-plane turn, a multi-plane maneuver could reach ~50 G. The GCS is rated for 35 G in any direction, so a multi-plane turn could exceed that limit. Conversely, if 35 G is the maximum for multi-plane maneuvers, the equivalent single-plane limit would be about 25 G, so the missile could never exceed 35 G and would remain within the GCS spec.
Literally here is written 35G for Z and Y axis for 15s
Right so 35G in any axis for up to 15seconds right? Thats literally combined plane.
The missile’s aerodynamic capabilities =/= the GCS operating limit, its a hardware endurance spec. If the GCS is rated “35 G" which you would express in x and y comparisons must use the resultant acceleration , not a per-axis value. Thus, two simultaneous control surfaces yield ~50 G resultant, exceeding a 35G GCS limit even though no single axis is above 35G.
Remember it’s not describing the missiles capabilities as whole it’s only describing what this small unit is capable of enduring.
