Patent Number: 
Section: claims

1. A solar thermal rocket, comprising: a. a thermal energy storage section for initial heating of a propellant to a first temperature exceeding approximately 1570xc2x0 K;  b. a direct gain section for continued heating of said propellant to a second temperature at which said propellant may be effectively used as a rocket fuel, said direct gain section being in fluid communication with said thermal energy storage section;  c. a propulsion nozzle in fluid communication with said direct gain section;  d. a solar concentrator that focuses solar energy toward said thermal energy storage section and said direct gain section;  e. means for selectively directing solar energy from said solar concentrator to either said thermal energy storage section or said direct gain section;  f. a propellant storage container, said container being in fluid communication with said thermal energy storage section; and  g. a propulsion nozzle in fluid communication with said direct gain section. 2. The rocket of  claim 1 , wherein said means for selectively directing solar energy comprises insulation between said thermal energy storage section and said direct gain section, said insulation being movable between a first open position where solar energy is directed to said thermal energy storage section and a second closed position where solar energy remains in said direct gain section. claim 1 3. The rocket of  claim 1 , wherein said means for selectively directing solar energy comprises means for causing relative rotation of said solar concentrator between said thermal energy storage and direct gain sections. claim 1 4. The rocket of  claim 1 , wherein said direct gain section comprises refractory metal tubes. claim 1 5. The rocket of  claim 4 , wherein said refractory tubes are constructed from rhenium. claim 4 6. The rocket of  claim 1 , wherein said thermal energy storage section is constructed from at least one material selected from the group consisting of: rhenium coated graphite and tungsten encapsulated boron nitride. claim 1 7. The rocket of  claim 1 , wherein said temperature of said propellant exceeds 2400xc2x0 K. claim 1