Determining energetic characteristics and selecting environmentally friendly components for solid rocket propellants at the early stages of design

This paper has investigated the possibility to theoretically calculate a value of the specific impulse for highly energetic compositions using only two parameters – the heat of the reaction and the number of moles of gaseous decomposition reaction products. Specific impulse is one of the most important energetic characteristics of rocket propellant. It demonstrates the level of achieving the value of engine thrust and propellant utilization efficiency. Determining the specific impulse experimentally is a complex task that requires meeting special conditions. For the stage of synthesis of new promising components, the comparative analysis of energetic characteristics, forecasting the value of specific impulse, especially relevant are calculation methods. Most of these methods were first developed to determine the energetic characteristics of explosives. Since explosives and rocket propellants in many cases have similar energy content and similar chemical composition, some estimation methods can be used to assess the specific impulse of solid rocket propellant. The specific impulse has been calculated for 45 compositions based on environmentally friendly oxidizers (ammonium dinitramide, hydrazinium nitroformate, hexanitrohexaazaisowurtzitane) and polymer binders polybutadiene with terminal hydroxyl groups, glycidylazide polymer, poly-3-nitratomethyl-3-methyloxetane). It was established that the estimation data obtained correlate well with literary data. Deviation of the derived values of the specific impulse from those reported in the literature is from 0.4 % to 1.8 %. The calculation results could be used for preliminary forecasting of energetic characteristics for highly energetic compositions, selecting the most promising components, as well as their ratios.

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Test Method for Solid Rocket Propellant Specific Impulse Measurements

10.1520/d2508-93r02 ◽

2003 ◽

Author(s):

Keyword(s):

Specific Impulse ◽

Test Method ◽

Solid Rocket Propellant ◽

Rocket Propellant ◽

Solid Rocket

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Test Method for Solid Rocket Propellant Specific Impulse Measurements

10.1520/d2508-93 ◽

1993 ◽

Author(s):

Keyword(s):

Specific Impulse ◽

Test Method ◽

Solid Rocket Propellant ◽

Rocket Propellant ◽

Solid Rocket

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STUDIES OF THE INFLUENCE OF ENERGETIC ADDITIVES ON SELECTED PROPERTIES OF HETEROGENEOUS SOLID ROCKET PROPELLANT WITH LOW CONTENT OF HCL IN COMBUSTION PRODUCTS

PROBLEMY TECHNIKI UZBROJENIA ◽

10.5604/01.3001.0011.5821 ◽

2018 ◽

Vol 144 (4) ◽

pp. 15-30

Author(s):

Paulina MAGNUSZEWSKA ◽

Rafał Bogusz ◽

Bogdan Florczak

Keyword(s):

Sodium Nitrate ◽

Specific Impulse ◽

Combustion Products ◽

Heat Of Combustion ◽

Mechanical Stimuli ◽

Rocket Propellants ◽

Ballistic Properties ◽

Solid Rocket ◽

Solid Rocket Propellants ◽

Heterogeneous Solid

The paper presents influence of additives like aluminium, magnesium, AMD (aluminium-magnesium dust) and boron on selected properties of heterogeneous solid rocket propellants (HSRP) based on HTPB in which ammonium chlorate was partly replaced by sodium nitrate. The presence of sodium nitrate reduces the content of hydrogen chloride (HCl) in combustion products. Theoretical values of thermochemical and thermodynamical properties like isochoric heat of combustion (Q), specific impulse (Isp) and combustion products in motor chamber and nozzle were identified by ICT-Code program. A laboratory rocket motor (LRM) was used to examine ballistic properties for prepared samples of propellants. Their temperature of decomposition, heat of combustion and hardness were tested both with sensitivity to mechanical stimuli (impact, friction) and rheological properties at curing.

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STUDIES OF HIGH EXPLOSIVES IMPACT ON REDUCTION OF HCL IN HETEROGENEOUS SOLID ROCKET PROPELLANTS

PROBLEMY TECHNIKI UZBROJENIA ◽

10.5604/01.3001.0010.6308 ◽

2017 ◽

pp. 29-45

Author(s):

Rafał Bogusz ◽

Paulina Magnuszewska ◽

Bogdan Florczak

Keyword(s):

Specific Impulse ◽

Calorific Value ◽

Combustion Products ◽

Decomposition Temperature ◽

Mechanical Stimuli ◽

High Explosives ◽

Combustion Heat ◽

Rocket Propellants ◽

Solid Rocket ◽

Heterogeneous Solid

The paper describes an influence of high explosives: hexogene (RDX), octogene (HMX), and dinitro-diaminoethene (FOX-7) on the properties of heterogeneous solid rocket propellant (HSRP) prepared on the base of Hydroxy Terminated Polybutadiene (HTPB) in which ammonium perchlorate (AP) was partially replaced by sodium nitrate (SN). It reduced the content of HCl in combustion products. Theoretical values of thermochemical and thermodynamic properties such as isochoric combustion heat (Q), specific impulse (Isp) and contents of combustion products in motor combustion chamber and nozzle have been identified by using the ICT-Code program. The rheological properties (virtual viscosity) of the propellant slurry during curing process, the sensitivity to mechanical stimuli (impact, friction), decomposition temperature, calorific value and hardness of propellants containing explosive materials were tested by instruments and ballistic properties were investigated by laboratory rocket motor (LRM).

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Performance Analysis of a Dual-Fuel Sugar Based Solid Rocket Propellant

European Journal of Engineering Research and Science ◽

10.24018/ejers.2021.6.2.2347 ◽

2021 ◽

Vol 6 (2) ◽

pp. 34-41

Author(s):

Gbadebo Omoniyi Adeniyi ◽

Inkechukwu Nkere ◽

Lanre Moshood Adetoro ◽

Olusegun Samuel Sholiyi

Keyword(s):

Cell Model ◽

Single Point ◽

Specific Impulse ◽

Potassium Nitrate ◽

Rocket Motor ◽

Chamber Pressure ◽

Dual Fuel ◽

Solid Rocket Propellant ◽

Rocket Propellant ◽

Solid Rocket

The effects of dual-fuel on improving the ballistic efficiency of a low energy sugar-based solid rocket propellant were investigated in this paper. This was achieved by establishing a threshold proportion of sucrose to sorbitol that provided the highest ballistic efficiency, using a beam load cell (model single-point 2,000 kg linearly defined by 0-20 kN force, with ±.005 percent precision). Seven different propellant formulations were prepared, loaded into the rocket motor and tested for performance. The major performance parameters of interest were the thrust, total impulse, burn time, delivered specific impulse, delivered characteristic velocity, and the chamber pressure. The formulations tested were potassium nitrate–sucrose propellant (65% KNO3 and 35% sucrose (C12H22O11)) (KNSU); potassium nitrate-sorbitol propellant (65% KNO3 and 35% sorbitol (C6H14O6)) (KNSB); modified potassium nitrate-sucrose propellant (65% KNO3, 32% sucrose (C12H22O11)), and 3% carbon (C) (MODKNSU); potassium nitrate-sucrose-sorbitol propellant (65% KNO3, 25% sucrose (C12H22O11)), and 10% sorbitol (C6H14O6) (KNERK); potassium nitrate-sucrose-sorbitol-carbon propellant (65% KNO3, 24% sucrose (C12H22O11), 10% sorbitol (C6H14O6), and 1% carbon (C)) (MODKNERK); and finally a propellant made from KNO3, sucrose (C12H22O11), sorbitol (C6H14O6), carbon (C) and iron II oxide(Fe2O3) combinations in 65, 30, 3, 1, 1% proportion respectively. The novel result obtained from these experiments was applied to boost the performance of a KNSB rocket propellant motor during a rocket launch experiment. Both static and dynamic rocket motor internal ballistic parameters were then compared. The measured delivered motor average thrust and the effective propellant burn times were recorded as: (164.15N, 3.97s); (102.95N, 6.53s); (65.66N, 9.38s); (79.09N, 3.77s); (243.98N, 3.77s) and (92.6N, 5.89s) respectively. The MODKNERK, was established to produce a most efficient motor and with the full delivery of its ballistic energy. It was also established, that the ballistic and rocket motor efficiency of a lower energy rocket motor can be improved by starting the ignition of such motor with fast burning dual-fuel rocket propellant (MODKNERK).

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