A solid propellant rocket motor which utilizes a propellant casing enclosing one or more propellant segments in an end-burning configuration wherein each propellant segment comprises a substantially homogeneous mixture of fuel particles distributed throughout a matrix of solid oxidizer. Such propellant segments provide sufficiently high burn rates to provide the desired thrust profiles for a variety of applications. Such a solid propellant rocket motor in the end-burning configuration permits larger payloads due to the weight savings realized by the reduced binder and propellant casing requirements, with less complicated manufacturing procedures than conventional CP rocket motor configurations. In addition, the end-burning configuration permits easier segmentation of the propellant grain to tailor the thrust profile during the burn, with the added flexibility of dynamically chosen thrusts, triggered by either guidance circuitry or human intervention.
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