A Computer Program for the Prediction of Solid Propellant Rocket Motor Performance. Volume 1

Coats, D.; Levine, J.; Cohen, N.; Nickerson, Gail B.; Tyson, T.J.

doi:10.21236/ada015140

Cited by 10 publications

(2 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Using empirical correlation, 18 sensitive study was carried out by employing MATLAB programming tool. This predicts two-phase energy losses behaviour as a function of condensed particle size.…”

Section: Specific Impulsementioning

confidence: 99%

Synergistic enhancement in mechanical and ballistic properties of HTPB based energetic polymer composites

Mehmood

Khan

2013

Plastics, Rubber and Composites

View full text Add to dashboard Cite

Influence of chain extender (CE) and bonding agent (BA) on the mechanical, interfacial and ballistic properties of AP/Al/HTPB composite is determined and compared. Results indicate a relationship between the two properties. The composite without the additives exhibited extremely poor mechanical properties whereas maximum tensile strength and ultimate elongation is achieved by introducing CE in the conventional composite. Better mechanical properties in this modified composite also contributed in improving the ballistic behaviour. SEM analysis of the condensed combustion residues obtained from the propellant burnt in open atmosphere reveals a considerable decrease in the agglomerate size in the modified composite. This effect is reflected as higher specific impulse in this composite, determined from thrust time profile obtained in static bed test. Pressure time profile for the modified composite manifests a stable and consistent burning at the tail end in tubular geometry as opposed to the conventional system that exhibits a susceptible and unstable tail-off.

show abstract

Section: Specific Impulsementioning

confidence: 99%

Synergistic enhancement in mechanical and ballistic properties of HTPB based energetic polymer composites

Mehmood

Khan

2013

Plastics, Rubber and Composites

View full text Add to dashboard Cite

show abstract

“…This can be a challenging and time-consuming process, especially for threedimensional or twisted geometries like the VISERION fuel grain. Therefore, more general methods were developed by Peterson et al [17] for the Solid Propellant Rocket Motor Performance Computer Program (SPP) [18][19][20]. A layering technique with predefined base geometries is used.…”

Section: Introductionmentioning

confidence: 99%

Hybrid Rocket Engine Burnback Simulations Using Implicit Geometry Descriptions

Zeriadtke,

Martin,

Wartemann

2024

Aerospace

View full text Add to dashboard Cite

The performance of hybrid rocket engines is significantly influenced by the fuel geometry. Burnback simulations, to determine the fuel surface and fluid volume, are therefore an important tool for preliminary design. This work presents a method for the simulation of spatially constant burn-ups on arbitrary geometries. An implicit surface definition by means of a signed distance function is used to represent the fluid volume and the fuel block on tetrahedral meshes. Two methods each are used to determine the fluid volume and the burning surface. The first method is based on a direct integration of the signed distance function with the Heaviside function or the Dirac delta distribution, respectively. The second method linearly interpolates the position of an isosurface and thus reconstructs the fuel surface. Both methods are compared and validated with analytical results of four example geometries. Both calculations of the fluid volume and the calculation of the surface content with the interpolation method are characterized as first-order methods. With practicable mesh resolutions of one million computational cells, errors below two percent can be achieved. With the interpolation method, numerical meshes can also be exported for any time points of the burn. Finally, the application of the program to the fuel geometry of the Viserion hybrid rocket engine is demonstrated.

show abstract

Modelling and Verification of Solid Propellant Rocket Motor Operation

Zygmunt

Surma

Leciejewski

et al. 2016

Cent. Eur. J. Energ. Mater.

View full text Add to dashboard Cite

This paper presents a mathematical-physical model of phenomena occurring in the combustion chamber of a new solid propellant rocket motor. Due to the fact that the geometrical shape of the propellant grain has already been elaborated, the proposal for the modelling of combustion gas generation is a novelty. To solve the system of equations associated with the mathematical model, a computer programme in Turbo Pascal 7.0 was developed. For the solution of ordinary first-order differential equations, the fourth-order Runge-Kutta numerical method was applied. The main results of the completed simulations, i.e. changes in gas pressure, p, in the combustion chamber, and the rocket motor thrust, R, as a function of time, t, of motor operation, are shown graphically. Experimental verification of the parameters of the designed motor shows good agreement with the numerically calculated parameters.

show abstract

A Computer Program for the Prediction of Solid Propellant Rocket Motor Performance. Volume 1

Cited by 10 publications

References 1 publication

Synergistic enhancement in mechanical and ballistic properties of HTPB based energetic polymer composites

Synergistic enhancement in mechanical and ballistic properties of HTPB based energetic polymer composites

Hybrid Rocket Engine Burnback Simulations Using Implicit Geometry Descriptions

Modelling and Verification of Solid Propellant Rocket Motor Operation

Contact Info

Product

Resources

About