Energy characteristics of the composite modified double-base (CMDB) propellant, hydroxy terminated polybutadiene(HTPB)propellant, nitrate ester plasticized polyether (NEPE) propellant and glycidyl azide polymer (GAP) propellant containing dihydroxylammonium 5, 5′-bistetrazole-1, 1′-diolate(TKX-50) were calculated by CAD system software according to military standard GJB/Z84-1996 under the standard condition(p_c/p₀=70:1). Results show that theoretical specific impulse of the TKX-50 monopropellant is 2623.7 N·s·kg^-1and 6.5 N·s·kg^-1higher than that of the RDX monopropellant. TKX-50 is a better replacement of RDX in CMDB propellant. When the substitution of TKX-50 for AP in HTPB propellant and AP and HMX in GAP propellant, theoretical specific impulses for TKX-50-based HTPB propellant and TKX-50-based GAP propellant exist a optimal value of energy. When the substitution of TKX-50 for AP and HMX in NEPE propellant, theoretical specific impulse of TKX-50-based NEPE propellant increases at first, then decreases, and then increases, and the maximum increase can reach 20.4 N·s·kg^-1.