The catalysis of four TMOs (CuO,Fe 2O 3,Co 2O 3 and Cr 2O 3) and their six TMO mixtures (mass ratio:1∶1) on the combustion properties of AP/HTPB and AP/Al/HTPB composite solid propellants was investigated systematically.
Afterwards,oxidant prescription in solid propellants is designed adopted layout resolution inExcel based on energic demands of NEPE ( Nitrate Ester Plasticized Polyether )propellants(HMX:CL-20:AP:Al:FPM2602=60:10:19:8:3), specific impulse and the volumeof explosion of composite materials are validated at the same time.
Based on CT experimental results of HTPB composite solid rocket propellant and under the assumption of single type of microcrack,the concentration degree and area of internal defects are quantitatively analyzed,the mathematic model and measurement method of damage are established.
The basic concepts and main varieties of thermoplastic elastomers (TPEs) are outlined in the paper and advantages of TPEs over thermoset elastomers and the feasibility of TPEs as solid rocket propellant binders are analyzed in details. The basic requirements for TPEs used in solid propellants and applications of meet and enersetic TPFs to solld propellant formulations are reviewed.
This paper did some research on numerical simulation about the structure of solid rocket propellant, based on the mechanical problem during the designing process and stockpile process of solid rocket propellant .
A new type thermoplastic polyurethane elastomer for using as binder in solid propellent were prepared with melt prepolymerization method based on ethylene oxide tetrahydrofuran random copolyehter,isophorone diisocyanate and 1,4 butanediol.
Analysis and operational results show that the control system can meet all technical requirements for high energy composite solid propellant manufacturing.
Quasi-One-Dimensional Model of Combustion of Sandwich Heterogeneous Solid Propellant
This model includes the heat- and mass-transfer and kinetic-gasdynamic processes in the gas phase above the surface of burning solid propellant, as well as the heat-transfer processes in solid material.
The problem of the thermal stability of the base subsystem of components of a composite solid propellant with respect to the introduction of heat-absorbing agents, inhibitors, and burning rate catalysts was considered.
Numerical computations have been carried out in an inert simulator of solid propellant rocket motor with the aid of a standard k-ω turbulence model.
It is demonstrated that the employed kinetic model of thermochemical processes provides an adequate description of the available experimental data on the rate of combustion of AP- and PBR-based solid propellants.
The use of fractal for prediction of burning rate of composite solid propellants
By using the fractal geometry it is possible to calculate the actual AP (Ammonium Perchlorate) surface area and oxidizer-binder interface fractal dimension in the prediction of burning rate of composite solid propellants.
The starting characteristics of thermodynamic undersea vehicle systems are determined by the geometry, size and combustion area of solid propellants, which directly effect liquid propellant pipeline design.
It is necessary to establish accurate burning models for solid propellants.
The detection of defects and the characterization of solid rocket propellant were thus possible.
We have considered the electrodynamic effects on small Al2O3 spherules dumped into the Earth's magnetosphere in large quantities during solid rocket propellant burns.
TG studies of a composite solid rocket propellant based on HTPB-binder
The reasons for substantially nonstationary modes of operation of this system are considered, and a simplified model that approximates the phenomena of nonstationary combustion of a solid rocket propellant is proposed.
The paper presents estimates of the dynamic characteristics of unsteady combustion of a solid rocket propellant in a combustion chamber with in pressure is varied automatically by a specified program.