Method for burning rate characterization of solid propellants
Patent 4554823 Issued on November 26, 1985. Estimated Expiration Date: 
June 25, 2004. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.
June 25, 2004. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.Patent References 3373564 Solid propellant measurement system Patent #: 4409821 InventorAssigneeApplicationNo. 06/624063 filed on 06/25/1984US Classes:73/116, MOTOR AND ENGINE TESTING73/35.15By time measurement (e.g., burning rate, detonation velocity)ExaminersPrimary: Myracle, Jerry W.Attorney, Agent or FirmInternational ClassesF02K 9/00 (20060101)F02K 9/96 (20060101) G01N 33/22 (20060101) AbstractA method for determining the burning rate of a propellant. The method involves the single firing of a subscale, propellant motor that has been modified so that the propellant motor has a tapered cylindrical port that produces a non-neutral pressure-time trace when burned. The pressure-time trace is initially progressive (pressure increases with time), and then regressive (pressure decreases with time). Unlike conventional motors, this motor operates over a range of burning rates; therefore, the burning rate behavior of the propellant can be characterized with a single motor firing. The burning rate of the propellant is extracted from the motor pressure-time history by a computer analysis package. The analysis package employs an optimization program which uses an internal ballistics model of the motor. The ballistics model is used to generate a theoretical pressure-time trace which can be compared with the digitized output signal from the actual motor. The optimization routine of the computer determines the propellant burning rate behavior by selecting the burning rate law which, when employed in the internal ballistics model of the motor, produces the best match between the computer generated and the actual motor pressure-time traces. Thus by using the tapered port motor and by reducing the data, the burning rate of a propellant can be characterized with a single motor firing.Other References
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