Study On The Performance Of Solid Propellant With Hedc

By the addition of HEDC (High Energy Density Compound) in HTPB solid propellant, the energy characteristic can be improved. So The application of HEDC in solid propellant will be the definite direction in the 21st century.Based on the theory of least free energy, the characteristic of solid propellant with HEDC was computed by the RJS-A application, which was contrasted with the propellant of basal constitute have the weight proportion of AP/Al/HTPB is 68.5/16/15.5, then got the congruent constitute. By the result of appraising the consistent between HEDC and HTPB solidification system, the congruent parameter of solidification was chose and the solid propellant with RDX, with CL-20, with TAGZT, with DNOAF were manufactured; DNTF can't consist with HTPB solidification system.The thermal decomposition of HEDC was researched by DSC and Solid Reaction Cell/FTIR. By the research of HEDC selected, then the parameters of dynamics such as Tc, Ea, A were gained and the course of decomposition was conjectured; By the thermo analysis research of the mixture of HEDC and component of propellant, then the influence to the thermal decomposition of HEDC added to the propellant was groped.The results show that: AP can accelerate the decomposition of HEDC, the effect is RDX>TAGZT>CL-20>DNOAF; HTPB can accelerate the decomposition of CL-20 and DNOAF, restrain the decomposition of RDX and TAGZT; all HEDC will restrain the decomposition of AP, the effect is TAGZT>RDX>DNOAF>CL-20; the combustion characteristic of solid propellant with HEDC was effected by AP, HTPB, HEDC and the oxygen balance of system; and so on.The combustion characteristic of solid propellant with HEDC was measured by some morden technology. The burning rate data was gained and the burning rate bicatalysts on pressure exponent was computed; By the combustion wave structure of propellant measured, the range of temperature, the temperature of combustion surface and final flame, the flame structure of propellant in different testing pressure were gained; The flameout surface structure of propellant was analyzed and the influence to flameout surface structure by the change of the kind of HEDC and the testing pressure was realized; With the SEM/EDS and chemic means, the burning leavings of propellant were analyzed. The results show that: the order of burning rate data of solid propellant with HEDC in the same proportion is CL-20>DNOAF>RDX>TAGZT; the combustion area of solid propellant with HEDC can be distinguished to three parts; the central element of the flameout surface is C, O, Al and Cl; the combustion leavings are mostly made up of C and ball granule; and so on.By the above researches, the energy performance, the thermal decomposition and the combustion characteristic of solid propellant with HEDC was studied.