Slow-Burn Ammonium Perchlorate Propellants with Oxamide: Burn Rate Model, Testing, and Applications

Vernacchia, Matthew T.; Mathesius, Kelly J.; Hansman, R. John

doi:10.2514/1.b38106

Journal of Propulsion and Power

2021

DOI: 10.2514/1.b38106

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Slow-Burn Ammonium Perchlorate Propellants with Oxamide: Burn Rate Model, Testing, and Applications

Matthew T. Vernacchia

Kelly J. Mathesius

R. John Hansman

Abstract: Low-thrust, long-burn-time solid rocket motors may be useful as propulsion for small, fast uncrewed aerial vehicles. These motors require a slow-burning propellant which can operate at unusually low chamber pressures (0.3-2 MPa). Slow-burn propellants were developed using ammonium perchlorate oxidizer and the burn rate suppressant oxamide. By varying the

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Cited by 7 publications

References 18 publications

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Analysis of thermal stability for slow burning propellant based on isothermal testing: Self‐accelerating decomposition temperature (SADT) calculation and validation

Luo,

Xia,

Wang

et al. 2024

Propellants Explo Pyrotec

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Burning rate suppressants (BRSs) refer to a series of additives that reduce the burning rate of propellants, crucial for achieving sustained and stable thrust. This research focuses on assessing the impact of ammonium sulfate and ammonium oxalate on thermal stability and their potential as BRSs. Due to the stronger inhibitory effect of ammonium sulfate on the AP proton transfer process, the activation energy of propellant's first decomposition can be increased from 94.71 kJ mol−1 to 129.69 kJ mol−1 at a 3 % addition level. Based on Semenov model, the self‐accelerated decomposition temperatures (TSADT) were calculated and validated through 7‐day isothermal test. Introducing ammonium sulfate and ammonium oxalate raised the TSADT from 197.31 °C to 220.90 °C and 215.06 °C, respectively, deviating less than 4 % from experimental results. Among the propellants tested, those with ammonium sulfate showed prolonged response delay times (44.43–33.60 h), lower superheating temperatures (222.8–445.5 °C), and reduced mass loss rates (33.0–71.4 %) after 7 days of isothermal storage at 220–240 °C. The consistency between thermal analysis and isothermal test underscores the significant impact of activation energy on thermal stability.

show abstract

Analysis of thermal stability for slow burning propellant based on isothermal testing: Self‐accelerating decomposition temperature (SADT) calculation and validation

Luo,

Xia,

Wang

et al. 2024

Propellants Explo Pyrotec

View full text Add to dashboard Cite

show abstract

Research Progress of Burning Rate Inhibitors in Solid Heterogeneous Propellants

Hu,

Chen,

et al. 2024

Propellants Explo Pyrotec

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The advancement of solid rocket technology has increased demand for high‐performing propellants, particularly in the aerospace industry. Solid propellants are an essential component of rocket engines, and their stable combustion and adjustable burning rate throughout a wide pressure range significantly affect the performance of motors. The burning rate modifiers include catalysts and inhibitors. Solid rocket motors for different purposes require propellants with different burning rates. Using propellants that burn at a slower rate is beneficial for the smooth release of propellant energy, reducing the loss of energy in the process of high burning rate release and improving the endurance time of missile engines. Therefore, it is necessary to decrease the burning rate of propellant. This article summarizes the development of burning rate inhibitors (BRIs) and analyzes the mechanisms and behaviors of different BRIs, including amide‐based compounds, metal salts, and cationic surfactants, that affect the combustion of propellants.

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Decomposition mechanism and kinetic investigation of novel urea burning rate suppressants in AP/HTPE propellants

Xu,

Pang,

Kong

2023

J Therm Anal Calorim

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Slow-Burn Ammonium Perchlorate Propellants with Oxamide: Burn Rate Model, Testing, and Applications

Cited by 7 publications

References 18 publications

Analysis of thermal stability for slow burning propellant based on isothermal testing: Self‐accelerating decomposition temperature (SADT) calculation and validation

Analysis of thermal stability for slow burning propellant based on isothermal testing: Self‐accelerating decomposition temperature (SADT) calculation and validation

Research Progress of Burning Rate Inhibitors in Solid Heterogeneous Propellants

Decomposition mechanism and kinetic investigation of novel urea burning rate suppressants in AP/HTPE propellants

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