The separation and detemination of the extrctable organic components (HMX, C2 and NG+BTTN) in NEPE propellent are investigated. NEPE propellant samples were soaked in the purified THF for 24h; then, heat and stir the solution in 50℃ for 5 h.
It is discovered that rare earth compounds added into silicone substrate can certainly increase bonding strength between RTV Silicone rubber and HMX-CMDB propellant or Al-RDX-CMDB propellent coated with the primer, and the failure mode of shear samples is cohesive failure of silicone rubber itself.
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 operating process of liquid apogee engine (N2O4/MMH) thrust chamber is studied. By applying the SIMPLE algorithm with staggered grid, the numerical model is established. The atomization mechanism and decomposition combustion of hypergolic rocket propellant are considered in the model.
Analysis and operational results show that the control system can meet all technical requirements for high energy composite solid propellant manufacturing.
Comprehensive Substantiation of the Structure and Parameters of a Power-Propellant System for a Spacecraft
The conceptual and methodological principles, as well as some results of the comprehensive substantiation of a technical approach at early stages of design of power-propellant systems (PPS), are presented.
The time of turn is minimized, as well as the functional having a meaning of the propellant consumption.
The estimations of the propellant consumption for a realization of the programmed turn are made.
An experimental method for determination of critical conditions of condensation of metal propellants of electric jet engines (EJEs) on the surfaces of materials of spacecraft thermoregulating covers is presented.
Mechanism of combustion of fire-extinguishing propellants based on potassium nitrate
A study is made of one-dimensional nonstationary problems of the combustion and detonation of aerosuspensions of unitary fuels or propellants, which contain the oxidant as well as the combustible material (gunpowder, high explosives).
The temperature of attainable superheating of rocket propellants is also calculated by the theory of homogeneous nucleation.
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.
It is verified that the constitutive model with damage proposed can more accurately estimate the stress response of a class of viscoelastic particle-reinforced composite, such as solid propellent, than the constitutive model without damage.
The rheological behaviour of plastic propellent in rocket motor situations is simulated in an experimental technique.
In this a differential gas pressure is applied across a plug of propellent in a rigid tube so as to deform it in an approximately telescopic shear fashion.
The rheological properties of plastic propellent have been examined by means of a technique in which gas pressures are used to stress a plug of propellent pressed into a rigid tube.
The application of these superposed results to predict propellent behaviour is discussed.
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.