propellant grain

propellant grain

[prə′pel·ənt ‚grān]
(materials)
An elongated molding or extrusion, often of intricate shape, of solid propellant for a rocket, regardless of size.
References in periodicals archive ?
Tenders are invited for Design, manufacturing, supply, installation and commissioning of the special purpose machine for semi automatic arrangement of propellant grain and filling of 155 mm bi-modular charge system (bmcs) m92 modules at ofn
Regressive burning means there is constantly less surface area or gas produced as the propellant grain burns.
The effective mechanical properties of CSP are critical to study the deformation and fracture characteristics of propellant grain. Various experimental and numerical studies demonstrate that the mechanical properties of the CSP can be highly sensitive to the microstructural morphology such as the dimension, shape, distribution, and properties of the inclusion.
The MK 90 propellant grain is the propulsion component of the Hydra 70 family of rockets used by the US military and several allied nations to support overseas operations.
M2 EQUITYBITES-August 21, 2015-BAE Systems gets USD50m munitions contract for MK 90 propellant grain
Regardless of the composition, however, all propellants are processed into a similar basic geometric form, referred to as a propellant grain. Propellant grains are cylindrical in shape to fit neatly into a casing in order to maximise volumetric efficiency.
The oxidiser is generally a crystalline solid (such as Ammonium Perchlorate), the fuel and oxidiser are premixed into a propellant grain which is contained in a motor case.
Tenders are invited for Hiring of services for automated propellant grain arrangement for carrying out propellant grain arrangement and filling of bmcs m-92 (2,54,000 units) using special purpose machine (spm
Stewart, "Solid propellant grain design and burnback simulation using a minimum distance function," Journal of Propulsion and Power, vol.
Shen et al., the structural integrity of propellant grain was estimated by a numerical method that combines the Voronoi cell finite element method (VCFEM) and the homogenization method.
It was shown that there exists an optimal slope of the line z(X) providing maximum combustion efficiency for a given mass of metal in the propellant grain. The dependence of the coordinate of the point at which the metal particle leaves the grain surface on the initial size of the particle burning out at the channel outlet was given in the paper [7].
There are also effects expected in the area of propellant grain regression rate that plays a primary role in the performance of hybrid propulsion for instance.

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