초록 ▼

A propulsion system is disclosed that uses microwaves originating from a ground-based or on-board source to provide energy for propulsion. The energy produces thrust by coupling into a propellant via a microwave absorbent heat exchanger, and by subsequent conversion of the propellant thermal energy

A propulsion system is disclosed that uses microwaves originating from a ground-based or on-board source to provide energy for propulsion. The energy produces thrust by coupling into a propellant via a microwave absorbent heat exchanger, and by subsequent conversion of the propellant thermal energy to kinetic energy through a thrust converter or nozzle.

대표청구항 ▼

We claim: 1. A thruster for a vehicle comprising: a source of propellant; a source of microwave energy at or above approximately 35 GHz; a heat exchanger for receiving energy from the source of microwave energy and coupled to the source of propellant to heat the propellant to create an expanding me

We claim: 1. A thruster for a vehicle comprising: a source of propellant; a source of microwave energy at or above approximately 35 GHz; a heat exchanger for receiving energy from the source of microwave energy and coupled to the source of propellant to heat the propellant to create an expanding medium; and a thrust converter coupled to the heat exchanger to generate thrust from the expanding medium. 2. The thruster of claim 1 where the source of propellant comprises a source of hydrogen gas under pressure. 3. The thruster of claim 1 where the source of propellant comprises ambient atmosphere. 4. The thruster of claim 1 where source of microwave energy is at or above approximately 140 GHz. 5. The thruster of claim 1 where the source of propellant comprises ambient atmosphere and a combustible material, which is combusted with the ambient atmosphere to release additional energy added to that from the source of microwave energy and delivered to the thrust converter. 6. The thruster of claim 1 where the heat exchanger comprises a microwave absorber thermally coupled with the propellant supplied from the source of propellant and electromagnetically coupled to the source of microwave energy. 7. The thruster of claim 6 where the microwave absorber comprises a lossy dielectric block having a plurality of propellant channels defined therethrough. 8. The thruster of claim 6 where the microwave absorber comprises a susceptor. 9. The thruster of claim 8 where the susceptor comprises a sheet having a layered structure in which a plurality of propellant channels are defined and in which a susceptor is embedded. 10. The thruster of claim 9 where the layered structure comprises a susceptor layer disposed about the plurality of propellant channels and in intimate heat exchanging relationship with propellant flowing through the plurality of propellant channels, a dielectric layer disposed on each side of the susceptor layer, and a reflector layer adjacent the dielectric layer on the side opposite the dielectric layer providing a microwave exposure surface, the dielectric, susceptor and reflector layers chosen in material properties and dimensions to maximize power absorption fraction of the susceptor layer. 11. The thruster of claim 11 further comprising an aeroshell for the vehicle and where the thruster forms part of the aeroshell. 12. The thruster of claim 11 where the microwave thruster acts as part of an atmospheric re-entry heat shield. 13. The thruster of claim 12 further comprising a source of cooling fluid coupled to the thruster and where a fluid is selectively passed through the heat exchanger to cool the overall structure. 14. The thruster of claim 8 where the susceptor is comprised of at least one layer having an electroplated surface. 15. The thruster of claim 14 where the susceptor is comprised of a plurality of susceptor layers, which are clad with one or more dielectric and reflecting layers, and where at least one of the susceptor, dielectric and reflecting layers are vapor deposited. 16. The thruster of claim 7 where the thrust converter comprises a Laval nozzle. 17. The thruster of claim 8 where the thrust converter comprises a Plug nozzle. 18. The thruster of claim 1 where the source of propellant is a source of hydrogen. 19. The thruster of claim 1 where the source of propellant is a source of ammonia.