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Solid fuel ducted rocket with gel-oxidizer augmentation propulsion

  • US 5,152,136 A
  • Filed: 08/05/1991
  • Issued: 10/06/1992
  • Est. Priority Date: 08/05/1991
  • Status: Expired due to Fees
First Claim
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1. A solid fuel ducted rocket augmented with gel-oxidizer comprising:

  • (i) a rocket motor case having a head-end and an aft end;

    (ii) an exhaust nozzle secured to said rocket motor case at the aft-end thereof;

    (iii) a combustion zone of a combustion chamber within said rocket motor case and in communication with said exhaust nozzle, said combustion zone being a zone in the combustion chamber wherein fuel and oxidizer are brought together for hypergolic reaction;

    (iv) a glycidyl azide polymer solid fuel gas generator installed within said rocket motor case at the head-end thereof, said glycidyl azide polymer after being ignited performing the function of supplying fuel-rich hot gases for further combustion within said rocket motor case in a combustion zone of a combustion chamber;

    (v) an igniter for igniting said glycidyl azide polymer;

    (vi) a ducted member extending outwardly from said rocket motor case between said aft-end and said head-end thereof and forming an air scoop having an air inlet for directing air scooped from the atmosphere during a low pressure airbreathing sustain stage of a flight into the interior of said rocket motor case for combustion of said fuel-rich hot gases in a combustion zone of a combustion chamber;

    (vii) a moveable intake closure mounted within said combustion chamber, said intake closure capable of being opened during a sustain stage of flight to allow air to be scooped into said combustion chamber and said intake closure capable of being closed during a boost or dash stage of flight to minimize drag and to retain higher combustion pressure within said combustion chamber, as compared with said sustain stage of flight, employing said gel-oxidizer for hypergolic reaction with said fuel-rich hot gases;

    (viii) a housing structure in a spaced apart relationship from said glycidyl azide polymer within said rocket motor case and extending toward the aft-end of said rocket motor case, said housing structure in said spaced apart relationship defining a combustion zone and one or more conduits for conducting fuel-rich hot gases into said combustion zone for hypergolic reaction with air scooped in during a lower pressure airbreathing sustain stage of propulsion and said housing structure having a storage capability for storing a gel-oxidizer and means for expelling said gel-oxidizer for hypergolic reaction with said fuel-rich hot gases at a much higher pressure during a boost or dash stage of a flight as compared with said sustain stage of a flight;

    (ix) a combustion zone of a combustion chamber within said rocket motor case defined by an outer surface of housing structure extending toward said aft-end of said rocket motor case, said combustion zone being a zone of a combustion chamber for hypergolic reaction during said sustain, boost, and dash stages of flight with said fuel-rich hot gases, to produce combustion gases for exhausting through said exhaust nozzle to produce thrust; and

    ,(x) a fuel insulation layer installed on an internal surface of said rocket motor case, said fuel insulating layer performing a dual function of insulating said rocket motor case and supplying gaseous combustible products for combustion within said combustion zone of said combustion chamber.

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