The constant thrust hybrid rocket motor of this invention is capable of providing operation for at least 50 seconds over a wide temperature range and with minimal variation in chamber pressure. The constant thrust hybrid rocket motor of this invention includes a combustion chamber containing a Plexiglas grain having at least one longitudinal port, an ignition squib associated therewith to ignite the hybrid rocket motor, an oxidizer source, a squib valve, a pressure regulator, and a solenoid valve, all elements being of the type disclosed in U.S. Patent No. 3,156,092 referred to hereinabove. In addition thereto, and forming the inventive concept of the constant thrust hybrid rocket motor of this invention are means for creating a bypass around the solenoid valve. This may be accomplished by the utilization of an actual bypass line having a fixed sized orifice in conjunction with a conventional solenoid valve and feedback transducer, or by incorporating within the hybrid rocket motor a unique solenoid valve which contains therein a constant flow orifice in combination with a feedback transducer.


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    Relativistic Flight with a Constant Thrust Rocket

    G. M. Anderson / D. T. Greenwood | NTIS | 1970


    Thrust Reversal Unit for Rocket Motor

    R. G. Daudelin | NTIS | 1965



    Electromechanical System for Solid Rocket Motor Thrust Modulation

    Zamir, Yossi / Albagli, David / Gany, Alon et al. | British Library Conference Proceedings | 2019