Dual propellant launch for solid rockets

Claim 1

APPARATUS FOR LAUNCHING A ROCKET FROM AN ENCLOSED SILO COMPRISING A ROCKET POSITIONED WITHIN AN ENCLOSED SILO, SAID SILO BEING CYLINDRICALLY SHAPED WITH AN OPEN END AND A CLOSED END AND HAVING A CLOSED OUTER WALL OF SUBSTANTIALLY CONSTANT CIRCULAR CROSS SECTION ALONG THE LENGTH OF THE OUTER WALL, SAID OUTER WALL BEING POSITIONED IN CLOSE PROXIMITY TO THE OUTSIDE OF SAID ROCKET, SAID ROCKET HAVING A NOZZLE AT ONE END THEREOF, SAID NOZZLE BEING SITUATED AT THE CLOSED END OF SAID SILO, A PRIMARY PROPELLANT ENCASED WITHIN SAID ROCKET FOR PROVIDING THRUST THERETO, A RING-SHAPED SABOT MOUNTED WITHIN THE CLOSED END OF SAID SILO AND ADAPTED TO SUPPORT SAID ROCKET, SAID SABOT BEING POSITIONED AT A DISTANCE FROM THE CLOSED END OF SAID SILO WHEREBY A CHAMBER IS FORMED AT THE CLOSED END OF SAID SILO, SEALING MEANS CONNECTED ABOUT THE PERIPHERY OF SAID SABOT EXTENDING LATERALLY FROM SAID SABOT AND TERMINATING ADJACENT THE OUTER WALL OF SAID SILO TO SUBSTANTIALLY SEAL SAID CHAMBER, SAID SEALING MEANS COMPRISING A LABYRINTH TYPE SEAL FORMING AT LEAST TWO SUCCESSIVE THROATS WHICH CREATE PRESSURE DROPS ACROSS SAID SEAL WHEREBY CHOKED FLOW IS PRODUCED, A SECONDARY PROPELLANT HAVING A LOWER BURNING TEMPERATURE THAN SAID PRIMARY PROPELLANT ENCASED WITHIN SAID ROCKET, MEANS FOR IGNITING SAID SECONDARY PROPELLANT, AND MEANS FOR DIRECTING THE LOW TEMPERATURE GASES PRODUCED BY THE BURNING OF SAID SECONDARY PROPELLANT INTO SAID CHAMBER, SAID SEALING MEANS CONTROLLING THE EXPANSION OF SAID GASES WHEREBY SAID SABOT AND SAID ROCKET ARE FORCED TOWARD THE OPEN END OF SAID SILO.