The burning rate characteristics of ammonium perchlorate (AP) based composite propellants is studied as a function of the chemical nature of the polymers used as binders. The following five types of polymers are used: (1) hydroxy-terminated polybutadiene (HTPB) (2) polypropyleneglycol (PPG) (3) polysulfide (PS) (4) polyesterpolyol (PO) (5) azidomethylmethyloxetane (AMMO) Experiments are conducted using differential thermal analysis (DTA), thermogravimetric analysis (TG), and burning rate analysis. The AP/PS propellant shows the highest burning rate and the AP/PO propellant shows the lowest burning rate within the propellants rested. Though the burning rate appears to be very dependent on the type of binder used, the characteristics of burning rate versus pressure cannot be correlated with the thermochemical data obtained by DTA and TG. The results of the photographic observation of the burning surface indicate that the formation of a melting layer of the binder reduces the burning rate due to the reduced reaction rate between the binder and the AP particles.