| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 一种微推力器 | CN201310626611.2 | 2013-11-28 | CN104675651A | 2015-06-03 | 麻树波 |
| 本发明公开了一种微推力器，包括L形壳体、电源以及电机，还包括烧蚀靶心、供料机构、激光器、调节光路组、聚焦透镜以及保护薄膜；所述L形壳体一侧依次固定安装有所述供料机构、制冷器、所述电源和所述激光器，所述供料机构、所述制冷器和所述激光器均与所述电源通过导线连接，所述L形壳体上位于所述激光器前端设置有所述调节光路组和扫描振镜，所述L形壳体一侧固定设置有所述聚焦透镜，所述聚焦透镜的入射一侧设置有所述保护薄膜，所述保护薄膜的一端固定设置在所述卷轴内，所述保护薄膜的另一端固定设置在所述电机的动力输出轴上。本发明具有以下特点：设计合理，结构简单，使用寿命长，保护薄膜可及时更换，维护费用低。 | ||||||
| 2 | Photo-turbine | JP15425584 | 1984-07-25 | JPS6131674A | 1986-02-14 | AOKI TAKASHI |
| PURPOSE:To simplify the structure of photo-turbine for converting the light energy into mechanical rotary energy in the air, by providing a spiral and/or radial reflector/straightner while arranging an impeller rotatably in the center. CONSTITUTION:Plural (eight in the drawing) reflector/straightner 1 are arranged in spiral on a circular bottom plate 4 then an impeller 2 is journaled rotatably to the rotary shaft 5 planted vertically from the center of the bottom plate 4 such that it will be positioned in the center of the spiral of said reflector/ straightner 1. While a tube having open ends 3 is arranged above the reflector/ straightner 1 coaxially with the impeller 2. An updraft is produced by the thermal energy produced from each vane of the impeller 2 through irradiation of light and the air flow sucked through the gap of said reflector/straightner 1 is straightened and taken in then collided against one face of impeller to rotate the impeller. | ||||||
| 3 | Uses of hydrocarbon nanorings | US14643577 | 2015-03-10 | US10072642B2 | 2018-09-11 | 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. | ||||||
| 4 | PROPULSIVE DEVICES THAT COMPRISE SELECTIVELY REFLECTIVE EPITAXIAL SURFACES | US15555548 | 2016-03-02 | US20180051680A1 | 2018-02-22 | David Hyland |
| A device for generating thrust using the dynamic Casimir effect comprising: an epitaxial stack of closely spaced parallel semiconductor laminae; and a voltage source; wherein each said semiconductor lamina is connected to said voltage source such that said voltage source can apply voltage to each semiconductor lamina. | ||||||
| 5 | Hybrid electric propulsion for spacecraft | US14209249 | 2014-03-13 | US09856862B2 | 2018-01-02 | 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. | ||||||
| 6 | System and method for propellantless photon tether formation flight | US11491830 | 2006-07-22 | US20070045474A1 | 2007-03-01 | Young Bae |
| 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. | ||||||
| 7 | Propulsion device and method of generating shock waves | US09827496 | 2001-04-06 | US06459205B1 | 2002-10-01 | Wolfgang Schall; Eberhard Zeyfang; Wolfgang Riede; Wilhelm Mayerhofer |
| For providing a propulsion device particularly for a spacecraft, comprising a plasma chamber in which a plasma can be produced in a propellant, and a focussing arrangement for focussing an electromagnetic radiation field into a focussing region in the plasma chamber in order to produce the plasma, the propulsion device being highly efficient and controllable, it is proposed to arrange in the plasma chamber a plasma ignition arrangement whereby a material which lowers the plasma breakdown threshold in the propellant can be brought into the focussing region. | ||||||
| 8 | Propulsion device and method of generating shock waves | US09827496 | 2001-04-06 | US20020047673A1 | 2002-04-25 | Wolfgang Schall; Eberhard Zeyfang; Wolfgang Riede; Wilhelm Mayerhofer |
| For providing a propulsion device particularly for a spacecraft, comprising a plasma chamber in which a plasma can be produced in a propellant, and a focussing arrangement for focussing an electromagnetic radiation field into a focussing region in the plasma chamber in order to produce the plasma, the propulsion device being highly efficient and controllable, it is proposed to arrange in the plasma chamber a plasma ignition arrangement whereby a material which lowers the plasma breakdown threshold in the propellant can be brought into the focussing region. | ||||||
| 9 | Nonlinear electromagnetic propulsion system and method | US691889 | 1991-04-26 | US5142861A | 1992-09-01 | Rex L. Schlicher; Steven M. Rinaldi; David J. Hall; Peter M. Ranon; Charles E. Davis |
| An electromagnetic propulsion system based on an extremely low frequency (elf) radiating antenna structure driven by a matched high current pulsed power supply is described. The elf antenna structure resembles a modified three dimensional multiple-turn loop antenna whose geometry is optimized for the production of reaction thrust rather than the radiation of electromagnetic energy into space. The antenna structure is current driven rather than voltage drive. Rigid three dimensional geometric asymmetry, made up of flat electrical conductors that form a partially closed volume in the loop antenna structure, trap magnetic flux thereby causing a magnetic field density gradient along a single axis. This magnetic field density gradient then causes an imbalance in the magneto- mechanical forces that normally result from the interactions of the loop antenna's internal magnetic field with the current in the conductors of the loop antenna structure, as described by the Lorentz Force Law. The pulsed power supply is designed to provide the proper waveform to the antenna structure at an impedance matching the load impedance of the antenna. The rise time and shape of the input current waveform is crucial to maximizing the production of reaction thrust. Input voltage is at a nominal value sufficient to allow the desired high input current. | ||||||
| 10 | CO.sub.2 Coupling material | US206206 | 1980-11-12 | US4426843A | 1984-01-24 | Michael C. Fowler; David C. Smith |
| An improved energy conversion device for converting the energy carried by a laser beam to kinetic energy of a working fluid transparent to the laser radiation incorporates a seed gas having a relatively low dissociation temperature. The beam is focused to a beam spot the maximum diameter of which depends on the total power of the beam. | ||||||
| 11 | Electromagnetic Energy Beam Angular Momentum Engine: Self-Propulsion of Energy Beam Source via Application of Conservation of Angular Momentum | US15869850 | 2018-01-12 | US20180195499A1 | 2018-07-12 | Stephen Kardos |
| The present application relates to optical-mechanical systems and methods for moving a solid object by applying conservation of angular momentum to a configuration of a laser light beam that emanates from the solid object. The system includes a rotatable housing and an axially movable laser light source coupled to the housing and configured to emit a first light beam along a first path. The system can include a first beam splitter disposed along the first path for splitting the first light beam into a second light beam and a third light beam. The system can cause the third light beam to travel in a closed path, as an approximation of a circular path of initial radius, and of decreasing radius. The system can further include a second beam splitter, axially movable first, second and third mirrors, and a third beam splitter disposed at one end of the housing. | ||||||
| 12 | Nanomotor Propulsion | US15370783 | 2016-12-06 | US20170175720A1 | 2017-06-22 | Jinyao Tang; Baohu Dai; Jizhuang Wang |
| Self-propelling, programmable nanoscopic motors capable of harvesting energy from absorbed photons and undergoing subsequent photoeletrochemical (PEC) reactions are provided. A nanomotor can have a three-dimensional Janus configuration and can sense the direction of a light source. By controlling the zeta potential of different parts of the nanomotor with chemical modifications, the nanomotor can be programmed to show either positive phototaxis or negative phototaxis. | ||||||
| 13 | USES OF HYDROCARBON NANORINGS | US12946052 | 2010-11-15 | US20120117937A1 | 2012-05-17 | 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. | ||||||
| 14 | PHOTONIC LASER-BASED PROPULSION HAVING AN ACTIVE INTRACAVITY THRUST AMPLIFICATION SYSTEM | US11943480 | 2007-11-20 | US20080197238A1 | 2008-08-21 | Young Kun Bae |
| The invention is a system and method for propelling and slowing down spacecraft and other space systems and objects using the thrust generated from the direct laser photon momentum transfer between two platforms to and from unprecedented high speeds approaching the speed of light. The thrust from the direct laser photon momentum is amplified in an intracavity arrangement, in which laser photons bounce between two high reflectance mirrors separately located in two platforms. The laser gain medium is typically located between two mirrors, and amplifies the intracavity photon power, thus creating amplified thrust. This intracavity medium location arrangement offers two critical advantages: 1) the ability to maintain the intracavity photon power constant when the distance between the mirrors rapidly changes; and 2) the ability to overcome the power loss mechanisms, such as scattering and absorption.Furthermore, the current invention can be used for controlling the position and attitude of multiple spacecraft or spacecrafts in high precision formation flying or fractionated spacecraft architecture. This is advantageous over other propulsion concepts, such as chemical propulsion and laser beamed energy plasma or ablation propulsion, because the invention provides the highest specific impulse and dose not require any propellant, thus, significantly increases the payload fraction (payload weight/the total rocket weight), significantly decreases the payload launching cost, and is able to propel the spacecraft to velocities approaching the speed of light. | ||||||
| 15 | System and method for propellantless photon tether formation flight | US11491830 | 2006-07-22 | US07413147B2 | 2008-08-19 | Young Kun Bae |
| 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. | ||||||
| 16 | Methods and apparatus for beaming power | US09912775 | 2001-07-24 | US06534705B2 | 2003-03-18 | Jesus Berrios; Eric L. Cox; Terry J. Porter |
| 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. | ||||||
| 17 | Methods and apparatus for beaming power | US09912775 | 2001-07-24 | US20020046763A1 | 2002-04-25 | Jesus Berrios; Eric L. Cox; Terry J. Porter |
| 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. | ||||||
| 18 | Ram jet powered by a laser beam | US29958972 | 1972-10-20 | US3818700A | 1974-06-25 | KANTROWITZ A; ROSA R |
| A ram jet vehicle is powered in flight by laser beam radiation which heats the ram jet gas in the vehicle combustion chamber or exhaust nozzle. The beam is incident upon the vehicle or a part thereof that directs the radiation to the ram jet gas in the combustion chamber or exhaust nozzle. The gas is sufficiently absorptive of the radiation either intrinsically or because of added material to absorb substantial power from the beam and thereby add to the gross thrust of the jet gas.
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| 19 | Method of ionic propulsion utilizing a laser-stimulated ionic emission | US54995466 | 1966-05-13 | US3392527A | 1968-07-16 | GILMOUR JR ALEXANDER S; GIORI FRANCIS A |
| 20 | FLUID DRIVEN MOTOR DEVICE | US15844620 | 2017-12-18 | US20190186475A1 | 2019-06-20 | SAMIR HANNA SAFAR |
| The fluid driven motor device, which does not use a magnet or an armature coil, includes a motor casing chamber containing a fluid mixture, a shaft disposed within the chamber, and a plurality of ray guns arranged on the periphery of the chamber. The shaft has a plurality of cell holders, onto which a corresponding plurality of membrane cells is attached. Each membrane cell holds a predetermined quantity of a liquid. The membrane cells expand and contract continuously based on the firing of the subatomic rays by the plurality of ray guns. This expansion and contraction cycle causes the shaft to rotate. The device has several advantages such as being very energy and heat efficient, having lesser weight as compared to conventional electromagnetic coil based motors. | ||||||
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