Designing a TL 7 8 cm HE Solid Fuel Rocket
Hello all,
I thought I had asked sometime back in 2015 on how to design a solid fuel rocket. Unfortunately I cannot find the notes or the thread. My 8 cm HE rocket warhead calculations returned a weight of 4.8 kg, a Volume of 0.96 m^3, and a cost of Cr48. Unfortunately, I have not figured out how to calculate the solid fuel rockets per the directions on TNE FF&S Mk I Mod 1 (January 1994) p. 70. Can anyone please walk me through building a solid fuel rocket? 
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http://cgsc.contentdm.oclc.org/cdm/c...9/id/312/rec/1 Somewhere online is also the DA Pam covering ammunition used by the Viet Cong. I just need to remember where it is. I think that there is also the DA Pam covering weapons used in Vietnam. I have some stuff in my handbooks on artillery as well, but I need to get them out. 
More Stuff.
Equipment guides to weapons circa 2010. http://cgsc.contentdm.oclc.org/cdm/s.../2089/rec/1367 http://cgsc.contentdm.oclc.org/cdm/s.../2090/rec/1368 Viet Cong Ammunition Guide https://archive.org/details/PAM38112 Looks at the German Rocket Material. https://archive.org/details/CatalogO...teriel/page/n1 
Morning timerover51,
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Thank you very much for the link which has been added to my reference folder. 
Hello again timerover51,
First my apologies for the delay in getting back to you since I did notice that you had supplied more material to the original link. My guess is that I was typing my reply and missed the notification. That you for the additional material. Quote:

You might want to check to see if any nearby library has a copy of Jane's Weapons System, or see if you could pick one up fairly cheap online.

Morning timerover51,
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Thank you for the suggestions of checking my local library for or purchasing a copy of Jane's Weapons Systems. Seeing I've spent my book allowance already for the month of May, I'll have to stop by my library. Thank you again for sharing the links and your help. Tom Rux 
Hello again,
TNE FF&S Mk 1 Mod 0 (January 1994) Book II Subsystems Chapter 9 Sublight (Maneuver) Drives: Self Contained Thrusters p. 60 provides the following instructions for building a solid fuel rocket. Th: Thrust, in tonnes, per cubic meter of engine. *Note that solid fuel rockets have no engine volume perse; the fuel volume is the engine volume. Solid rocket fuel (SRF) mass in tonnes equals its volume in cubic meters. See FC note below to calculate solid rocket thrust. FC: Fuel consumption, in tonnes, per hour per tonne of thrust To determine volume in cubic meters, multiply by the volume of the fuel type. For solid rockets, simply pick a fuel mass. Divide the mass by the FC value. The result is thrust in tonnehours. Select either the thrust or the duration, and the other is determined from that. For example, 18 tonnes of TL6 SF rocket fuel could have 2 tonnes of thrust for one hour, 4 tonnes for 30 minutes, 1 tonne for two hours, or any other combination desired, as limited by the maximum allowed thrust (MaxT column). Size Efficiency: Solidfuel rockets with less than 500 kg of propellant (fuel) mass suffer from inefficient fuel combustion. To determine the fuel consumption inefficiency of a solidfuel rocket, divide 500 by the fuel mass (in kilograms). The result is the final fuel use multiplier. Multiply the calculated fuel consumption of the engine by this number. However, any multiplier less than 1 is treated as 1 and any multiplier greater than 10 is treated as 10. On the SelfContainer Thrusters Table a TL 7 SF Rocket MaxT = 1,500 tonnes of thrust for one engine, FC = 7.5 tonnes per hour per tonne of thrust, FT = SRF, and Airframe = Hypersonic. The Fuel Table shows that SRF has a Density (Volume?) of 1 and the price is Cr 2,000 per cubic meter. From Book III Chapter 9 Munitions a TL 7 8cm HE warhead mass is 4.8 kg and the volume is 0.96 cubic meters. Using CT Striker the warhead is 5 kg and the propellant needed to travel 1 km is 5 kg. Using the CT Striker fuel mass of 5 kg or .005 tonnes the thrust is .005/75 = 0.000667 tonnes of thrust per hour. The 5 kg is less than 500 kg which results in a fuel inefficiency value of 10 adjusting the thrust from 0.000667 x 10 to 0.00667 tonnes. Have I followed the directions correctly? 
You also need the section on Atmospheric Rockets and Missiles on page 146 of FF&S, where you'll select an average velocity and fuel mass, calculate average mass, and use velocity, average mass, and a tech modifier to figure how much thrust is required. The fuel consumption is then calculated, which gives the information needed to calculate endurance and range.

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For the sake of this calculation, I'm using the 700 m/s launch velocity of an 8cm Flz.Rakete Oerlikon as the average velocity. This is 503.6 km/h using the conversion formula in step 1. Propellant mass is 5 kg. For an unguided rocket, average mass is 7.3 kg (4.8 kg warhead plus half of the propellant mass; there is no guidance or engine mass). Required thrust is 503.6 * 503.6 * 7.3 * 0.0000009, which is 1.666 kilograms of thrust. Fuel burned per kilogram of thrust per second is the TL 7 Solid Rocket FC of 7.5 divided by 3600, or 0.00208; this is multiplied by 10 for fuel inefficiency to 0.0208. Fuel burned per second is 0.0208 * 1.666, or 0.0347 kilograms per second. Fuel endurance is 5 divided by 0.0347, which is 144 seconds. Range is the velocity of 503.6 km/h multiplied by 144 seconds and divided by 3600, which gives a range of 20.15 kilometers. Reducing the fuel to 1 kilogram (and keeping all other numbers the same) would give a range of 2.8 kilometers. 
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