The thin-layer of composite solid propellant (TLCSP) is fabricated by coating the propellant slurry on a non-combustible tape and subsequently fast curing. This report presents a primary solution towards a high efficient instrument for measuring propellant burning rate based on TLCSP. It consist of combustion chamber,pressure/temperature control system,data acquisition and data processing system. The combustion chamber contains a 1650 mm length of TLCSP sample on which 1051 fuses with 1.50 mm apart each other are covered . There are three modes of pressure control including manual,stepped and linear type. Using manual mode,the pressure exponent of burning rate can be obtained only with one ignition,thus remarkably improving the measurement efficiency. Combining stepped and linear control modes,it is possible that the pressure function of burning rate can be determined. Furthermore,the applicability of pressure range can be checked when using current burning rate equations.