Mono-dispersed, spherical and core/shell structure aluminum nanopowders (ANPs) were produced massively by high energy ion beam evaporation (HEIBE). And the number weighted average particle size of the ANPs is 98.9 nm, with an alumina shell (3-5 nm). Benefiting from the passivation treatment, the friction, impact and electrostatic spark sensitivity of the ANPs are almost equivalent to those of aluminum micro powders. The result of TG-DSC indicates the active aluminum content of ANPs is 87.14%, the enthalpy release value is 20.37 kJ/g, the specific heat release S 1 /Δm 1 * (392-611 °C) which determined the ability of energy release is 19.95 kJ/g. And the value of S 1 /Δm 1 * is the highest compared with ANPs produced by other physical methods. Besides, the ANPs perfectly compatible with hydroxylterminated polybutadiene (HTPB), 3 wt. % of ANPs were used in HTPB propellant replaced micron aluminum powders, and improved the burning rate in the 3-12 MPa pressure range and reduced the pressure exponential by more than 31% in the 3-16 MPa pressure range. The production technology of ANPs with excellent properties will greatly promote the application of ANPs in the field of energetic materials such as propellant, explosive and pyrotechnics.The large specific surface area, high density, low consumption of oxygen, high volumetric heat of combustion and high reactivity made ANPs can be broadly used in propellants 1, 2 . Great attentions had been paid to aluminum nanoparticles because of their superior performances in burning and energy release, which is expected to solve the problems of aluminum micro-particles, existed in propellants 3-5 . The burning rate of the solid rocket propellants is one of the most important factors that determine the performance of rocket 6 . The typical diameter of aluminum particles used in propellants is in the order of ~30 μm 7 . The burning rate of propellants can be increased by employing aluminum powders with higher specific surface area 8,9 . Replacement of micro-aluminum powders by ANPs will increase the propellant burning rate by ~100% and always show low pressure-exponents in 1-12 MPa pressure range 10 . Besides, the burning rate of the solid propellants increases depending on the percentage of high-energy matters, ANPs, in the propellant content 6 .ANPs have small size and surface effects, and their surface atoms are not matched, which leads to the particles are in highly active state 2 . The high reactivity of ANPs have also caused aging problems, particularly in an environment of high relative humidity 11 . Another problem of using ANPs as additives in propellants is the original agglomeration, leading to heterogeneity of the mixtures and to coalescence of agglomerates in the heat penetration zone during combustion 12 . The near-surface combustion of ANPs controls the propellant burning rate, the high agglomeration level of ANPs points to low exponent of burning rate 10 . In order for any energetic material to have application, it must be sensitive enough to various stimuli to combus...