| 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 | 无接触板状发射体电磁推进系统 | CN03132493.2 | 2003-07-09 | CN1477029A | 2004-02-25 | 李立毅; 李小鹏; 程树康; 寇宝泉 |
| 无接触板状发射体电磁推进系统，它涉及一种高脉冲大电流放电技术的直线电磁推进器。它包含运载器、对称固定在运载器两侧的机翼、以运载器的中心线为对称轴对称设置在运载器左右侧的两组电磁推进器；电磁推进器的中心处设有与运载器所在空间相贯通的并呈直线形的机翼运行通道，运载器两侧的机翼分别设置在两组电磁推进器中的机翼运行通道内；每组电磁推进器包含分别设置在机翼运行通道上下方的双列线圈，通入的电流幅值、方向和交变频率均相同的双列线圈的上线圈和下线圈以机翼运行通道的水平中心面为对称面相互上下对称设置。本发明具有成本低、可控性良好、单位载荷运输费用低、可重复使用的优点。 | ||||||
| 22 | 空间游戏的方法及实现该方法的装置 | CN99803105.4 | 1999-04-29 | CN1120028C | 2003-09-03 | 谢尔盖·米哈伊洛维奇·萨夫罗诺夫; 叶夫根尼·亚历山德罗维奇·扎伊采夫; 阿列克谢·尤列维奇·梅利尼科夫; 尤里·费多罗维奇·康斯坦丁诺夫; 亚历山大·叶夫根涅夫维奇·列兹尼科夫; 斯坦尼斯拉夫·瓦西列维奇·斯塔罗斯京 |
| 本发明涉及一种游戏方法，该方法包括将筹码下在一项游戏项目记录上，此项游戏项目由能空间运动的游戏部件(1)进行。游戏项目的特性应用技术系统(2)并根据可运动游戏部件(1)相对于至少一个系统(3)的空间分布进行记录，系统(3)用于评定游戏项目并位于同一空间中。游戏部件(1)和系统(3)不是位于地球上而是在外部空间中，同时，由技术系统(2)进行的游戏项目特性的记录是在地球上进行的。在装置的第一实施例中，游戏由比赛组成。游戏部件(1)由飞船构成，而系统(3)是自然产生的物体，技术系统不是在地球上而是在外部空间设定游戏过程，并确保其在地球上的重现。根据此装置的第二实施例，游戏部件(1)由飞船构成，而系统(3)由所述飞船之一或空间碎片之一构成。根据所述装置的另一实施例，游戏部件(1)由在外部空间中随机运动的可运动物体构成，而系统(3)由飞船的外表面构成，技术系统(2)布置在飞船的外表面上。 | ||||||
| 23 | 空间游戏的方法及实现该方法的装置 | CN99803105.4 | 1999-04-29 | CN1291111A | 2001-04-11 | 谢尔盖·米哈伊洛维奇·萨夫罗诺夫; 叶夫根尼·亚历山德罗维奇·扎伊采夫; 阿列克谢·尤列维奇·梅利尼科夫; 尤里·费多罗维奇·康斯坦丁诺夫; 亚历山大·叶夫根涅夫维奇·列兹尼科夫; 斯坦尼斯拉夫·瓦西列维奇·斯塔罗斯京 |
| 本发明涉及一种游戏方法,该方法包括将筹码下在一项游戏项目记录上,此项游戏项目由能空间运动的游戏部件(1)进行。游戏项目的特性应用技术系统(2)并根据可运动游戏部件(1)相对于至少一个系统(3)的空间分布进行记录,系统(3)用于评定游戏项目并位于同一空间中。游戏部件(1)和系统(3)不是位于地球上而是在外部空间中,同时,由技术系统(2)进行的游戏项目特性的记录是在地球上进行的。在装置的第一实施例中,游戏由比赛组成。游戏部件(1)由飞船构成,而系统(3)是自然产生的物体,技术系统不是在地球上而是在外部空间设定游戏过程,并确保其在地球上的重现。根据此装置的第二实施例,游戏部件(1)由飞船构成,而系统(3)由所述飞船之一或空间碎片之一构成。根据所述装置的另一实施例,游戏部件(1)由在外部空间中随机运动的可运动物体构成,而系统(3)由飞船的外表面构成,技术系统(2)布置在飞船的外表面上。 | ||||||
| 24 | 碟型超高速太空飞行器 | CN200620137623.4 | 2006-10-09 | CN200971171Y | 2007-11-07 | 尚铁钢 |
| 一种碟型超高速太空飞行器，其特征在于整体外壳由钛锰合金板成型，内层复合铝合金蜂窝网格填充物复合板，仓内全封闭蜂窝结构，使用液压螺旋惯能立式磁浮交流发电机提供电力能源，单边环型环包壳片状转子直线感应电动机、自激冲击推进器双层逆向对接式冲击锤片状转子直线感应电机组成动力装置。可完成地球大气压环境和宇宙太空真空环境的三维空间定位飞行并可达到光电磁波速度运行。 | ||||||
| 25 | 星箭解锁分离包带加载装置 | CN200620113382.X | 2006-04-30 | CN2897825Y | 2007-05-09 | 张益丹; 李景俊; 高峰; 王国山; 李庆辉; 任春玲 |
| 星箭解锁分离包带加载装置包括手动液压泵、分配器、单向载荷阀、油缸，手动液压泵通过管路接至分配器，分配器将管路分成若干个支路，在每个支路中均接有单向载荷阀，单向载荷阀的输出接至油缸的紧固弹簧，在所述手动液压泵与分配器之间接有压力表，用于，每个支路中还接有调节阀，用于调节支路的压力。本实用新型实现了半自动化操作，保证了均匀、同步加载预紧力的要求，降低了劳动强度，提高了工作效率，保证了装配质量。 | ||||||
| 26 | METHOD OF FORMING A SPACE-BORNE BODY | PCT/US2018/040986 | 2018-07-06 | WO2019018139A1 | 2019-01-24 | BROWN, Trevor |
Artificially directing a plurality of space-borne natural bodies to a target accretion region, such that gravitational forces amongst the plurality of space-borne natural bodies within the target accretion region produces an agglomerated space-borne body comprised of at least portions of the plurality of space-borne natural bodies. These teachings will accommodate use of a variety of space-borne natural bodies including asteroids, comets, and moons. |
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| 27 | Elimination of lifetime limiting mechanism of hall thrusters | US11044471 | 2005-01-28 | US07500350B1 | 2009-03-10 | David T. Jacobson; David H. Manzella |
| A Hall thruster includes inner and outer electromagnets, with the outer electromagnet circumferentially surrounding the inner electromagnet along a centerline axis and separated therefrom, inner and outer poles, in physical connection with their respective inner and outer electromagnets, with the inner pole having a mostly circular shape and the outer pole having a mostly annular shape, a discharge chamber separating the inner and outer poles, a combined anode electrode/gaseous propellant distributor, located at an upstream portion of the discharge chamber and supplying propellant gas and an actuator, in contact with a sleeve portion of the discharge chamber. The actuator is configured to extend the sleeve portion or portions of the discharge chamber along the centerline axis with respect to the inner and outer poles. | ||||||
| 28 | Split shroud exhaust nozzle | US10898035 | 2004-07-23 | US07174704B2 | 2007-02-13 | Bernard James Renggli |
| A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a throat section of increased diameter. An inner shroud surrounds the centerbody and cooperates with the centerbody to define the throat of the nozzle. An outer shroud surrounds the inner shroud and cooperates with the centerbody to define the exit area of the nozzle. Both shrouds are independently translatable to provide independent control of the nozzle throat area and the nozzle expansion ratio. | ||||||
| 29 | Jet exhaust noise reduction system and method | US10794968 | 2004-03-05 | US07114323B2 | 2006-10-03 | Robert Schlinker; Satish Narayanan; Wesley K. Lord; Gregory A. Kohlenberg; Ramons Reba; John Simonich; Marios C. Soteriou; Thierry Maeder |
| A system for reducing jet noise emission from an internally mixed gas turbine engine exhaust, comprising a fan/core flow mixer having a plurality of mixer lobes and a common flow nozzle having an equal number of tabs located along a circumferential edge of an aft end of the nozzle. There is a predetermined clocking relationship between the plurality of mixer lobes and the plurality of nozzle tabs that results in reduced exhaust noise emission, most evident in the lower frequency range. A method for reducing jet noise emission from an internally mixed gas turbine engine exhaust comprises selectively aligning a circumferential distribution of a mixed flow vorticity field produced by a fan/core mixer with a circumferentially distributed exhaust flow vorticity field produced by a modified common flow nozzle at an exit plane of the engine exhaust. | ||||||
| 30 | System and method for space elevator | US10942007 | 2004-09-16 | US06981674B1 | 2006-01-03 | James G. Dempsey |
| A system and method for a Space Elevator using a transport tether shaped into double catenary with one catenary below synchronous orbit altitude and the second catenary above synchronous orbit altitude and while also forming a harmonic oscillator using a combination of gravitational and centripetal forces with the zero crossing of the harmonic oscillator at an altitude of approximately one half synchronous orbit altitude of attached elevator. | ||||||
| 31 | Constellation of spacecraft, and broadcasting method using said constellation | US10176936 | 2002-06-21 | US06851651B2 | 2005-02-08 | Neil Evan Goodzeit |
| In general, a constellation of spacecraft is used to broadcast to a particular region with high angles of view in order to reduce blockage or shadowing. A constellation of a plurality of spacecraft is placed in 24-hour orbits having inclination of about 55°, eccentricity of about 0.32, semi-major axis of about 42,000 km, longitude of the ascending node of about 43° East, argument of perigee of about 270°, and longitude of the ground track at maximum latitude of about 7° East. The preferred number of spacecraft ranges from three to six. In a particular application of Digital Audio Broadcast to Europe in some embodiments, the most populous cities are provided with service from no more than about 10° from vertical, and broadcast takes place when the spacecraft are above at least 35° North latitude. The broadcast power is reduced during those portions of the orbit in which the ground track lies in the Southern hemisphere. | ||||||
| 32 | Method and apparatus for mapping planets | US3624650D | 1969-09-09 | US3624650A | 1971-11-30 | HORTTOR RICHARD L; GOLDSTEIN RICHARD M |
| A radar system is disclosed for obtaining data to map planets employing and S-band ranging transponder (RT) that is widely separated from and in motion relative to a stationary transmitter-receiver station (STRS) on earth. The STRS transmits a ranging signal which is biphase modulated by a pseudonoise (PN) code, and the RT retransmits the PN-modulated signal on a different carrier frequency. The STRS receives the retransmitted signal as a reflected signal from an area of the planet (AP) being mapped. Three time-varying delay times (STRS to RT, RT to AP and AP to STRS) are involved in the round trip communication delay. That round trip delay and a doppler shift of the reflected signal are tracked by the STRS for mapping. That is done by recording the received signal in phase quadrature at baseband. The technique for obtaining mapping data then consists of multiplying the recorded signal by a locally generated PN code after synchronizing the PN code modulation of the signal to the local PN code, and separating the synchronized PN-code-modulated signal from the rest of the received signal by a low-pass filter. The separated PN-code-modulated signal corresponds to a narrow strip or contour line at constant range from the RT which is substantially orthogonal to virtually parallel contours of doppler shift caused by motion of the RT relative to the AP. A filter which matches the doppler shift can thus be employed to resolve individual mapping points for display.
|
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| 33 | Buoyant anti-slosh system | US3443584D | 1967-02-24 | US3443584A | 1969-05-13 | EVENSEN DAVID A; RANEY JOHN P |
| 34 | Manufacturing method and device for protection device | JP2003437028 | 2003-12-14 | JP2005170359A | 2005-06-30 | NAKAGAWA TAKEO |
| <P>PROBLEM TO BE SOLVED: To provide a protector capable of solve a problem that it is difficult to manufacture an extensive flat plate in the space having no gravitational force according to the conventional technique, also it is difficult to forming a base system group consisting of a great number of base systems each as an extensive flat plate manufactured in a great quantity at a high speed which are arranged in a very large plane form and the protector requires a manufacturing device to achieve an initial object and attain the estimated effect. <P>SOLUTION: The protector manufacturing device is equipped with a transport device to transport iron meteorite(s) of appropriate size existing dotted in a minor planet zone, a material supply device to melt and stir the meteorite and distribute, a processing device to process it into plates and/or frames, a wroughting device whereby both the side edges of each of many band steel plates are subjected to automatic welding and each base plate in a wide band shape obtained by automatically welding a vertical frame and horizontal frame is wroughted automatically and cut into approximately a rectangular shape, an assembly device to assemble automatically members on the base plate after being transferred to an assembly table, and a control device formed in a combination of a transport network consisting of a group of electronic computers to control respective bodies of the transport device, a fabrication network consisting of a group of electronic computers to control each unit of each device of the fabrication system, etc. <P>COPYRIGHT: (C)2005,JPO&NCIPI | ||||||
| 35 | Parts preparing device, satellite operation plan planning device and program | JP2003111892 | 2003-04-16 | JP2004314805A | 2004-11-11 | YAMAMOTO KENJI |
| PROBLEM TO BE SOLVED: To provide parts preparing device, satellite operation plan planning device and program allowing a non-specialist having little knowledge of a method for controlling an artificial satellite or a command to easily arrange an operation plan of the satellite and avoid a competition. SOLUTION: This device is provided with an operation procedure parts preparing part 11 for preparing operation procedure parts in which commands having approaching execution times of various kinds of commands for the satellite operation are collected as a group, and an operation parts preparing part 12 for preparing operation parts in which operation procedure parts for completing an operation work are collected as a group. An operation arranging part 13 sets absolute execution times of prescribed commands included in the operation parts and arranges the times on a time axis. COPYRIGHT: (C)2005,JPO&NCIPI | ||||||
| 36 | Operation plan making system and method of artificial satellite | JP2000049307 | 2000-02-25 | JP2001233300A | 2001-08-28 | AOYAMA ISAO |
| PROBLEM TO BE SOLVED: To solve a problem of increasing the number of operation demands reserved when competition of the mutual operation demands is caused in large numbers in a cenventional plan making method. SOLUTION: This operation plan making system is provided with an operation plan making means 6 for making a new operation plan on the basis of operation plans obtained by plan making processing of the last time, an operation plan evaluating means 7 for determining an evaluation value of the new operation plan, an operation plan holding means 8 for holding plural operation plans, an operation plan selecting means 9 for renewing the operation plan holding means by selecting the operation plans by the decided number on the basis of evaluation values of the respective operation plans from the operation plan holding means and an operation plan selecting means 10 for selecting the operation plans being the basis in the next plan making processing from the operation plan holding means. The new operation plan is repeatedly made and selected, and when there is no change in the reserving number of operation demands, an evaluation reference of the operation plans is changed so as to reduce a difference between evaluation points imparted in respective orders of precedence such as an operation day to thus automatically make the operation plans for minimizing the number of reserving operation demands. COPYRIGHT: (C)2001,JPO | ||||||
| 37 | Contact method and apparatus of the solid particles and gas under the microgravity environment | JP17694192 | 1992-07-03 | JP2818076B2 | 1998-10-30 | 繁生 千葉; 香津雄 堤; 恭史 大山; 治 村岸; 康史 榊田; 洋 武内; 淳一 河端; 紘明 藤森 |
| 38 | Space station | JP29583196 | 1996-10-16 | JPH10119900A | 1998-05-12 | SHIBAGAKI MORIYUKI |
| PROBLEM TO BE SOLVED: To correct the displacement of an orbit of an artificial satellite, and to drastically improve the global atmosphere such as weather or the like, by installing a long material such as a wire or the like in a space circularity for surrounding the earth, rotating the long material in the longitudinal direction, and making a large amount of moisture attached to the long material. SOLUTION: A long material L such as a flexible metallic wire or the like, is loaded in a space craft, the space craft is put on an orbit rotating around the earth E, and the long material L is taken out on the orbit so that it is installed circularity for surrounding the earth E. The circular long material L is rotated in a longitudinal direction on the orbit, whereby the attractive force of the earth and the centrifugal force are balanced in the same way as an ordinary artificial satellite, and the long material is stabilized at a constant height from the earth E. Various kinds of artificial satellites A1, A2... are moored to the long material L installed as mentioned in the above. Further by making a large amount of moisture carried from the earth E, attached to the circular long material L, the global atmosphere can be improved. COPYRIGHT: (C)1998,JPO | ||||||
| 39 | Space for animal breeding device | JP9639389 | 1989-04-18 | JP2575872B2 | 1997-01-29 | TAKAOKI MUNEO; SHIOJI NORIO; OKAZAKI HIROSHI; IZUMISAWA SEIJI; NISHI ATSUKO |
| 40 | JPS54153800U - | JP5114478 | 1978-04-18 | JPS54153800U | 1979-10-25 | |
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