초록 ▼

A propellant depot (40, 150) includes a utility box (42, 42′) that has space flight equipment. A propellant cartridge adaptor (95) is coupled to the utility box (42, 42′) and to an exchangeable propellant cartridge system (41). The propellant depot (40, 150) also includes a docking adaptor (44) for

A propellant depot (40, 150) includes a utility box (42, 42′) that has space flight equipment. A propellant cartridge adaptor (95) is coupled to the utility box (42, 42′) and to an exchangeable propellant cartridge system (41). The propellant depot (40, 150) also includes a docking adaptor (44) for coupling to an approaching spacecraft (24). A controller (66) controls the transfer of propellant from within the exchangeable propellant cartridge system (41) to the spacecraft (24). A method of providing propellant to a spacecraft in space includes launching an orbital propellant depot (40, 150) into space. The spacecraft is docked to the orbital propellant depot (40, 150) in space. Propellant is transferred to the spacecraft. The spacecraft is separated from the orbital propellant depot (40, 150).

대표청구항 ▼

1. An exchangeable propellant cartridge system, comprising: a cylindrical main fuel tank having a docking end and an internal end;a conical docking adaptor coupled to said docking end of said main fuel tank;a first interstage having a plurality of cross-support members arranged in a cone shape and p

1. An exchangeable propellant cartridge system, comprising: a cylindrical main fuel tank having a docking end and an internal end;a conical docking adaptor coupled to said docking end of said main fuel tank;a first interstage having a plurality of cross-support members arranged in a cone shape and pressurant bottles, said first interstage coupled to said internal end of said main fuel tank;a cylindrical oxidizer tank having a main fuel tank end and an avionics shelf end, wherein said main fuel tank end is coupled to said first interstage;a second interstage having a plurality of cross-members arranged in a cylinder shape, said second interstage being coupled to said avionics shelf end of said oxidizer tank; andan avionics platform coupled to said second interstage, said avionics platform comprising an avionics support system;said main fuel tank having a diameter larger than the diameter of said oxidizer tank; andsaid main fuel tank being positioned coaxially with said oxidizer tank. 2. The exchangeable propellant cartridge system of claim 1, wherein: said pressurant bottles contain pressurized helium. 3. The exchangeable propellant cartridge system of claim 1, further comprising propellant lines coupled to the main fuel tank. 4. The exchangeable propellant cartridge system of claim 3, wherein: said conical docking adaptor has a conical section and a cylindrical section;said conical section has propellant line couplings attached to the propellant lines. 5. A cartridge system as in claim 1 wherein said avionic support system comprises disposal electronics. 6. A cartridge system as in claim 5 wherein said disposal electronics disposes of the cartridge system when propellant within any of the main fuel tank, or the oxidizer tank is below a predetermined level. 7. A cartridge system as in claim 6 wherein said disposal electronics in disposing of the cartridge system performs a task selected from at least one of crashing the cartridge system and de-orbiting the cartridge system from an orbit in which the orbital propellant depot exists. 8. A cartridge system as in claim 1 further comprising a communication system coupled to said avionics support system. 9. A cartridge system as in claim 8 wherein said communication system comprises orbital propellant depot communication capable electronics. 10. A cartridge system as in claim 8 wherein said communication system comprises ground communication capable electronics. 11. A cartridge system as in claim 1 further comprising: a cooling system coupled to either of said main fuel tank or said oxidizer tank;a temperature sensor generating a temperature signal indicative of the temperature of a propellant in either of said main fuel tank or said oxidizer tank; anda controller coupled to said cooling system and said temperature sensor and adjusting temperature of said propellant in response to said temperature signal.