International Journal of Aerospace Engineering / 2012 / Article / Tab 1

Research Article

Multisized Inert Particle Loading for Solid Rocket Axial Combustion Instability Suppression

Table 1

Reference motor characteristics.


Propellant grain length, 52 cm
Initial port diameter, 3.6 cm
Nozzle throat diameter, 1.6 cm
Grain/nozzle-conv. length ratio, 16 : 1
Propellant specific heat, 1500 J/kg-K
Propellant density, 1730 kg/m3
Propellant thermal conductivity, 0.4 W/m-K
Propellant thermal diffusivity, 1.54 × 10-7 m2/s
Propellant flame temperature, 3000 K
Propellant surface temperature, 1000 K
Propellant initial temperature, 294 K
Gas specific heat, 1920 J/kg-K
Specific gas constant, 320 J/kg-K
Gas thermal conductivity, 0.2 W/m-K
Gas absolute viscosity, μ8.07 × 10-5 kg/m-s
Gas specific heat ratio, γ1.2
De St. Robert exponent, 0.35
De St. Robert coefficient, 0.05 cm/s-(kPa)n
Particle solid density, 2700 kg/m3
Particle specific heat, J/kg-K900 J/kg-K
Particle mass fraction, 0%
Propellant elastic modulus, 45 MPa
Propellant Poisson’s ratio, 0.497
Casing inner wall radius, 3.24 cm
Casing wall thickness, 0.127 cm
Casing material density, 2700 kg/m3
Casing elastic modulus, 80 GPa
Casing material Poisson’s ratio, 0.33
Sleeve wall thickness, 0.47 cm
Sleeve material density, 7850 kg/m3
Sleeve elastic modulus, 200 GPa
Sleeve material Poisson’s ratio, 0.30
Casing/prop. rad. damping ratio, 0.35
Casing/prop. long. damping ratio, 0.10

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