Studies on Comparative Performance of RDX, HMX and CL-20 in Hydroxyl Terminated Polybutadiene Based Composite Propellant Formulations

Nanochromates MCr2O4 (M = Co, Ni, Cu, Zn): Preparation, Characterization, and Catalytic Activity on the Thermal Decomposition of Fine AP and CL-20

“…As one of the most important propellants, the high burning rate solid rocket propellant has been extensively used in terms of operational rockets, missiles, satellites, and space shuttle launch vehicles. Many efforts have been devoted for developing novel propellants with high burning rate to fulfill the ever-growing and challenging requirements. − The burning rate can be tuned by the addition of high energetic materials, combustion catalysts, and even by adjusting the particle size of oxidizers in the solid rocket propellants. − In particular, chromate as a transition metal combustion catalyst is capable of increasing the burning rate of solid propellants. − Ammonium perchlorate (AP) with the particle size of about 1 μm, namely, fine AP (FAP), has been widely used as an oxidizer to promote the burning rate of composite propellants. , On the other hand, hexanitrohexaazaisowurtzitane (CL-20), a novel high explosive, has aroused great concerns to be used as a high energetic additive to improve the energy of composite propellants. , …”

“…15,16 On the other hand, hexanitrohexaazaisowurtzitane (CL-20), a novel high explosive, has aroused great concerns to be used as a high energetic additive to improve the energy of composite propellants. 17,18 It is well known that the combustion behavior of the composite propellant depends heavily on the thermal decomposition of both AP and CL-20. As thus, tuning the thermal decomposition of above two components by the addition of catalysts suggests great potential strategies to modify the combustion properties of composite propellants.…”

Study on Comparative Performance of CL‐20/RDX‐based CMDB Propellants

“…The effects of CL-20 and RDX on basic properties of CMDB propellants were investigated, the major findings could be summarized as follows: 1) The calculations on energetic properties for CL-20/RDX-CMDB propellants showed that energetic properties of propellant with CL-20 were superior to of propellant with RDX. 2) The data on burning rate revealed that with the increase of RDX/CL-20 mass fraction in the propellants, the burning rates at low pressure (2-8 MPa) remained almost the same but differ observably at high pressure (10)(11)(12)(13)(14)(15)(16)(17)(18)(19)(20)(21)(22). With the increase of CL-20 mass fraction in the propellants, the burning rates of propellants could be enhanced significantly, but the burning rates of propellants containing RDX decreased.…”

“…Ramesh Kurva et al [15] reported that a successful attempt had been made to incorporate RDX, HMX and CL-20 at 10 % level partly replacing ammonium perchlorate to enhance the performance of HTPB/AP/Al based composition having 86 % solid loading and studied in detail for viscosity build up, mechanical, thermal and ballistic properties. In another study, the thermal decomposition behavior of CL-20-NEPE propellant and the interaction among the compo-nents had been studied by Li Ding et al [16].…”

Experimental Approaches to Develop a High Thrust Ratio in a Single Chamber Dual Thrust Motor Using a Composite Propellant Formulation Based on HTPB/AP/Al

“…The pressure exponent (n) was determined using the SSBR data at different pressures by plotting a curve of log e (burning rate) vs. log e (pressure) and calculating n from the slope of the curve [20]. The data obtained are presented in Table 2.…”