| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | Efficient Electric Spacecraft Propulsion | US15826766 | 2017-11-30 | US20180080438A1 | 2018-03-22 | Wesley Gordon Faler; Donald Roy Smith |
| A propulsion system for spacecraft is based on an electric engine that expels propellant to achieve thrust. The propellant is first ionized to generate a plasma. Plasma particles are selectively accelerated via a pulsed laser that accelerates predominantly the electrons in the plasma. The electrons are expelled first, forming a space charge that acts as a virtual cathode to accelerate the positive ions. Interactions between the laser beam and plasma electrons are predominantly through the ponderomotive force. | ||||||
| 22 | USES OF HYDROCARBON NANORINGS | US14643577 | 2015-03-10 | US20150184643A1 | 2015-07-02 | Laurence H. COOKE |
| Hydro-carbon nanorings may be used, e.g., in power storage power transmission and transportation. Sufficiently cooled, an externally hydrogen doped carbon nanoring may be used to create a radial dipole containment field for electrons rotating in the nanoring. Such nanorings may transmit DC current with little or no loss. Similarly, an internally hydrogen doped carbon nanoring may be used to create a radial dipole containment field for positrons rotating in the nanoring. Virtually lossless transmission of AC current may be achieved by pairing such streams of electrons and positrons in their respective containment fields. Closed rotation of such streams may also be used to efficiently store large amounts of electrical energy. Finally, selectively accelerating and decelerating pairs of such paired electron and positron streams, which are moving at relativistic speeds, differential momentum may be created to cause physical movement. | ||||||
| 23 | Uses of hydrocarbon nanorings | US12946052 | 2010-11-15 | US09000660B2 | 2015-04-07 | Laurence H. Cooke |
| Hydro-carbon nanorings may be used, e.g., in power storage power transmission and transportation. Sufficiently cooled, an externally hydrogen doped carbon nanoring may be used to create a radial dipole containment field for electrons rotating in the nanoring. Such nanorings may transmit DC current with little or no loss. Similarly, an internally hydrogen doped carbon nanoring may be used to create a radial dipole containment field for positrons rotating in the nanoring. Virtually lossless transmission of AC current may be achieved by pairing such streams of electrons and positrons in their respective containment fields. Closed rotation of such streams may also be used to efficiently store large amounts of electrical energy. Finally, by selectively accelerating and decelerating pairs of such paired electron and positron streams, which are moving at relativistic speeds, differential momentum may be created to cause physical movement. | ||||||
| 24 | HYBRID ELECTRIC PROPULSION FOR SPACECRAFT | US14209249 | 2014-03-13 | US20140305096A1 | 2014-10-16 | Wesley Gordon Faler; Donald Roy Smith |
| A propulsion system for spacecraft is based on an electric engine that expels propellant to achieve thrust. The propellant is first ionized to generate a plasma. Plasma particles are selectively accelerated via a pulsed laser that accelerates predominantly the electrons in the plasma. The electrons are expelled first, forming a space charge that acts as a virtual cathode to accelerate the positive ions. Interactions between the laser beam and plasma electrons are predominantly through the ponderomotive force. | ||||||
| 25 | Method for propulsion | US11197697 | 2005-08-04 | US20070007393A1 | 2007-01-11 | Fabrizio Pinto |
| A method for propulsion that does not consume fuel. The method involves the modification of the dispersion force (i.e., van der Waals) that arises between particles, such as neutral atoms. The method comprises generating a lifting force by subjecting a plurality of confined particles to a trigger acceleration, exposing the particles to an amount of electromagnetic radiation that is sufficient to induce the lifting force to (1) exhibit relatively long-range interactions and (2) increase the momentum of the particles, and then transferring at least a portion of the increase in momentum to a vehicle. | ||||||
| 26 | Photoelectric propulsion drive | US10997657 | 2004-11-26 | US20060112673A1 | 2006-06-01 | Joseph Pellegrino |
| This invention is a device(s) that will utilize the power of photons to transfer their energy to electrons in turn transferring their energy to another object of mass that the casing(s) of the drive will be connected to by bombarding a wall of a negative electric field. This energy will then be transferred to the object this device(s) is connected to causing it to move in the same direction of the flow of the electrons. In theory the device(s) should cause movement up to ⅓ the speed of light. This will aid NASA any others that need or want to travel the solar system(s) in a more reasonable time frame. The fundamental principal behind the propulsion is the same as the solar sail. When high energy particles hit something, some of their energy is transferred to that object, and when the electrons are hit by photons of high energy, the photons energy is transferred to the electron and then in turn when the electron's energy is then transferred to the wall it hits and whatever it's connected to. I do suggest, though, that this drive be used in outer space and be lifted first from the earth via some other propulsion like a rocket. I do not feel currently it can produce enough “net force” to break away from earth's gravity on it's own. | ||||||
| 27 | Electric dipole moment propulsion system | US10142239 | 2002-05-09 | US20030209635A1 | 2003-11-13 | John Quincy St. Clair |
| This invention relates to a spacecraft propulsion system utilizing a rotating octagon of trapezoidal electrically charged flat panels to create an electric dipole moment that generates lift on the hull. On the interior side of each panel are electrostatically charged rods which produce a planar electric field that emerges from holes in the panel to form an ellipsoidal potential energy bubble on the outside of the hull. The rotating hull dipole moment generates a magnetic moment which, together with the magnetic field gradient developed by the rotating electric field of the electrostatically charged panels, produces said lift force. The potential energy field is enhanced by using a double cladding of hull material with different ranges of permittivities. | ||||||
| 28 | PHOTONIC ENGINE | US09477631 | 2000-01-05 | US20020002821A1 | 2002-01-10 | CEZARY RAFAK GALINSKI |
| Both chemical and nuclear rocket engines waste huge amounts of energy. This waste can be decreased by application of light-conducting structures. In case of chemical engine transparent walls of combustion chamber can allow to intercept generated light into light-conducting components. They can deflect photons trajectory in the same direction as a stream of exhaust gases. This can generate additional thrust. In case of thermonuclear photonic engine typical nuclear engine may be used as a fuel pump. Thermonuclear reaction is initiated in stream of thermonuclear fuel exiting nuclear engine. Light-conducting components intercept photons generated during this reaction. They can deflect photons trajectory in the same direction as a stream of exhaust gases. This can generate additional thrust. In both cases light-conducting structure is used to decrease loses of energy in typical rocket engines. Light conducting structure may be used to create antimatter photonic engine as well. In this case the antimatter portions are released into the chamber where they hit the stream of matter what causes annihilation. Light-conducting components intercept photons generated during this reaction. They can deflect photons trajectory in the same direction. This can generate the thrust. Light-conducting components can be made of optic fibers, but light-conducting surfaces can be used as well. Light conducting surfaces have to meet the following conditions: Photons generated during reaction enter into the structure according to the rule of complete internal reflection, Once photons enter the structure they are reflected many times, but always according to the rule of complete internal reflection, Curvature should assure correct flow direction after photons exit the structure. Light-conducting surfaces can help to organize flow of the coolant around hot regions of the engine. Application of light-conducting components to generate thrust of the engine is disclosed, as well as the shape of light-conducting components useful in this application, and cooling system that allows to keep safe temperature inside light-conducting components and recover additional amount of energy. | ||||||
| 29 | SYSTEM AND METHOD FOR PROPELLANTLESS PHOTON TETHER FORMATION FLIGHT | PCT/US2006032266 | 2006-08-18 | WO2007024655A3 | 2007-11-01 | BAE YOUNG K |
| The invention is a system and method for propellantless, ultrahigh precision satellite formation flying based on ultrahigh precision intracavity laser thrusters and tethers with an intersatellite distance accuracy of nanometers at maximum estimated distances of tens of kilometers. The repelling force of the intracavity laser thruster and the attracting force of tether tension between satellites form the basic forces to stabilize matrix structures of satellites. Users of the present invention can also use the laser thruster for ultrahigh precision laser interferometric metrology, resulting in simplification and payload weight reduction in integrating the thruster system and the metrology system. | ||||||
| 30 | SYSTEM AND METHOD FOR PROPELLANTLESS PHOTON TETHER FORMATION FLIGHT | PCT/US2006032266 | 2006-08-18 | WO2007024655A8 | 2008-03-06 | BAE YOUNG K |
| The invention is a system and method for propellantless, ultrahigh precision satellite formation flying based on ultrahigh precision intracavity laser thrusters and tethers with an intersatellite distance accuracy of nanometers at maximum estimated distances of tens of kilometers. The repelling force of the intracavity laser thruster and the attracting force of tether tension between satellites form the basic forces to stabilize matrix structures of satellites. Users of the present invention can also use the laser thruster for ultrahigh precision laser interferometric metrology, resulting in simplification and payload weight reduction in integrating the thruster system and the metrology system. | ||||||
| 31 | METHODS AND APPARATUS FOR BEAMING POWER | PCT/US0151327 | 2001-10-23 | WO0247122A2 | 2002-06-13 | BERRIOS JESUS; COX ERIC L; PORTER TERRY J |
| Methods and apparatus for beaming power from one location to another are provided. Energy is used to power one or more lasers to provide a coherent, wide-aperture beam, which is directed to the receiving platform. Photovoltaic cells on the receiving platform convert energy of the laser beam into electrical energy. Receiving platforms are provided that take advantage of the higher energy density in the laser beam. | ||||||
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