We can determine the thrust based on the impulse. The motor is produced by the same company as the AIM-7F’s motor and from the same facility. If the impulse is the same it should be around 260s.
The sounding rocket using the M112 rocket motor was ~400kg and had a peak acceleration of 21G.
400 kg accelerating at 21G (9.80665 x 21) = 205.93965 m/s2 would require 82375.86 newtons of thrust.
So using this spreadsheet as a basis for finding the correct values we work towards a realistic in-game missile test model.
With 82,375.86 newtons of thrust and a burn time of 5 seconds we only need to adjust the weight of the burned propellant to find the correct impulse. This should give us a realistic look at what the propellant burn during boost phase is.
I came up with an initial weight of 637.3 kg, a weight at the end of the boost-phase of 475kg. With a thrust of 82375.87kg and 5 seconds burn time we get an ISP of 258.69s.
For the sustainer we must use a different approach. We know the propellant mass, so subtracting the total mass from the propellant burned we find an end weight of 342.465kg. We know the burn time is 21 seconds. From here we only need to adjust the thrust until we get a realistic impulse similar to the AIM-7F’s sustainer.
Deriving the impulse from the standard missile characteristics.
1976
1977
The sustainer should be approximately ~215s it seems. I think the propellant weights are switched incidentally on the SMC sheet and Gaijin thinks so as well as they also have them flipped.
Anyhow, to get the sustainer to 215s impulse we find a realistic thrust rating of ~13350 newtons.
This is the resulting missile data, please note that the thrust values are PEAK and so the deltaV will NOT be correct.
Gaijin can either adjust this further by reducing burn time or reducing it from peak thrust to average thrust.
To get an idea of what that would look like I can adjust the values until the total deltaV is approximately 40% higher than the Phoenix rather than the current 80% value.
