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1. 发明申请

US20180354658A1 PROPULSION SYSTEM FOR SMALL ARTIFICIAL SATELLITES 审中-公开
公开(公告)号：US20180354658A1
公开(公告)日：2018-12-13
申请号：US15748951
申请日：2016-07-25
申请人： D-Orbit SRL
发明人： Luca ROSSETTINI , Goncalo Daniel ALBANO LOPES
IPC分类号： B64G1/24 , B64G1/10 , B64G1/26 , B64G1/28 , B64G1/40
CPC分类号： B64G1/242 , B64G1/1085 , B64G1/26 , B64G1/285 , B64G1/40 , B64G1/403 , B64G1/404
摘要： A propulsion system for small artificial satellites comprises a plurality of engines (2) fixable to a frame (101) of a satellite (100); a control unit (3) connected functionally to the engines (2) for sending at least one activation signal (AS) for activating at least one engine (2); the system is selectively configurable at least between a first configuration in which at least one of the engines (2) is activated for correcting the orbit of the satellite (100) and a second configuration in which at least one of the engines (2) is activated for dispersing said satellite (100) relative to another adjacent satellite.

2. 发明申请

US20180273193A1 ELECTRICALLY OPERATED PROPELLANT THRUST ASSIST FOR SUPPLEMENTING AIRPLANE TAKEOFF, LANDING OR IN-FLIGHT MANEUVERABILITY 审中-公开
公开(公告)号：US20180273193A1
公开(公告)日：2018-09-27
申请号：US15469026
申请日：2017-03-24
申请人： Raytheon Company
发明人： Matt H. Summers , Frederick B. Koehler , James K. Villarreal , Mark T. Langhenry
IPC分类号： B64D27/02 , B64D31/02 , F02K9/97 , F02K9/08 , C06B33/06
CPC分类号： B64D27/023 , B64C2201/046 , B64C2201/167 , B64D31/02 , B64G1/403 , B64G1/404 , C06B33/06 , C06D5/06 , F02K9/08 , F02K9/94 , F02K9/95 , F02K9/97 , F05D2220/80 , F05D2240/35
摘要： Electrically operated propellant thrust assist supplements an airplane's takeoff, landing or inflight maneuvers. Unlike conventional SRM propellants, the burn rate of the electrically operated propellant can be varied via an electrical input and even extinguished by interrupting the electrical to control a secondary thrust profile (e.g., amplitude, transition rates) to fulfill the needs of a given takeoff, inflight or landing maneuver and provide a smooth transition in and out of the maneuver. Multiple pairs of fixed thrusters (opposite sides of the fuselage), a single pair of gimbaled thrusters or a hybrid of fixed and gimbaled thrusters may be configured to provide all such maneuvers. Flight control inputs are passed back and forth through an interface to enable the thrust assist.

3. 发明申请

US20170015444A1 DEBRIS REMOVAL DEVICE AND DEBRIS REMOVAL SYSTEM 审中-公开
标题翻译： DEBRIS拆除装置和拆卸系统
公开(公告)号：US20170015444A1
公开(公告)日：2017-01-19
申请号：US15124311
申请日：2015-04-02
申请人： ASTROSCALE JAPAN INC.
发明人： Mitsunobu OKADA
IPC分类号： B64G1/64 , B64G1/24 , B64G1/40 , B64G1/36
CPC分类号： B64G1/646 , B64G1/242 , B64G1/26 , B64G1/36 , B64G1/361 , B64G1/403 , B64G1/62 , B64G1/64
摘要： A debris removal device includes: a body part; an adhesion part to let the space debris adhere to the body part; a braking part to generate braking force in a specific direction, to act on the space debris adhering to the body part via the adhesion part during circling of the body part around the orbit together with the space debris; and a timing control part to control generation timing of the braking force. The timing control part generates the braking force, during circling of the body part together with the space debris around the orbit, when the body part is located at a specific region on the orbit where a direction of the braking force is substantially parallel to an orbit plane including the orbit and substantially parallel to a tangential line of the orbit, and in substantially an opposite direction of a circling direction of the space debris.
摘要翻译：碎片去除装置包括：主体部分; 粘附部分使空间碎片粘附到身体部位; 用于在特定方向上产生制动力的制动部件，在与所述空间碎片一起围绕所述轨道围绕所述主体部分的过程中，通过所述粘附部分作用于附着于所述主体部分的所述空间碎片; 以及用于控制制动力的产生定时的定时控制部。定时控制部分在主体部分位于轨道上的特定区域时，在身体部分与轨道周围的空间碎片环绕时产生制动力，其中制动力的方向基本上平行于轨道包括轨道并且基本上平行于轨道的切线并且与空间碎片的盘旋方向基本上相反的方向。

4. 发明申请

US20160380486A1 Large-Scale Space-Based Solar Power Station: Power Transmission Using Steerable Beams 审中-公开
标题翻译：大型太空太阳能发电站：使用导向梁的动力传输
公开(公告)号：US20160380486A1
公开(公告)日：2016-12-29
申请号：US14712856
申请日：2015-05-14
申请人： California Institute of Technology
发明人： Seyed Ali Hajimiri , Harry A. Atwater , Sergio Pellegrino , Behrooz Abiri , Florian Bohn
IPC分类号： H02J50/80 , H02J50/90 , H02J50/40 , H02J50/23 , B64G1/66 , H02S20/30 , B64G1/44 , B64G1/42 , B64G1/10 , H02J3/38 , H02J3/46
CPC分类号： H02J50/80 , B64G1/1085 , B64G1/222 , B64G1/283 , B64G1/286 , B64G1/288 , B64G1/36 , B64G1/401 , B64G1/403 , B64G1/405 , B64G1/406 , B64G1/407 , B64G1/428 , B64G1/44 , B64G1/443 , B64G1/66 , B64G2001/1092 , H01L31/041 , H01L31/042 , H02J3/383 , H02J3/46 , H02J50/23 , H02J50/40 , H02J50/90 , H02S20/30 , H02S30/20 , H02S40/00 , H02S40/30 , H04B7/18515 , Y02E10/52
摘要： A space-based solar power station, a power generating satellite module and/or a method for collecting solar radiation and transmitting power generated using electrical current produced therefrom is provided. Power transmitters can be coordinated as a phased array and the power generated by the phased array is transmitted to one or more power receivers to achieve remote wireless power generation and delivery. In many embodiments, a reference signal is distributed within the space-based solar power station to coordinate the phased array. In several embodiments, determinations of the relative locations of the antennas in the array are utilized to evaluate the phase shift and/or amplitude modulation to apply the reference signal at each power transmitter.
摘要翻译：提供了一种太空太阳能发电站，发电卫星模块和/或收集太阳辐射并发射使用其产生的电流产生的电力的方法。功率发射器可以作为相控阵进行协调，由相控阵产生的功率被发送到一个或多个功率接收器以实现远程无线发电和发射。在许多实施例中，参考信号分布在空基太阳能发电站内以协调相控阵列。在几个实施例中，使用阵列中的天线的相对位置的确定来评估相移和/或幅度调制以在每个功率发射器处施加参考信号。

5. 发明申请

US20150375875A1 Space Launch Apparatus 审中-公开
标题翻译：太空发射装置
公开(公告)号：US20150375875A1
公开(公告)日：2015-12-31
申请号：US14547543
申请日：2014-11-19
申请人： Arthur McKee Dula
发明人： Arthur McKee Dula
IPC分类号： B64G1/00 , B64G1/40
CPC分类号： B64G1/002 , B64G1/40 , B64G1/401 , B64G1/402 , B64G1/403 , B64G1/404 , B64G1/58 , B64G1/62 , B64G1/641 , B64G1/645 , B64G2005/005
摘要： A space launch apparatus comprising a solid triangular space frame constructed of a plurality of connected truss members that are attached to each other at nodes and are also attached to at least one rocket motor and to at least one payload whereby the force produced by the operation of the rocket motor is transferred to the payload and aerodynamic and vibration loads are distributed through the truss members and their nodes.
摘要翻译：一种空间发射装置，包括由多个连接的桁架构件构成的实心三角形空间框架，所述多个连接的桁架构件在节点处彼此连接并且还附接到至少一个火箭发动机和至少一个有效载荷，由此由操作产生的力火箭发动机转移到有效载荷，空气动力学和振动载荷通过桁架构件及其节点分布。

6. 发明申请

US20150021439A1 SPACE VEHICLE WITH ELECTRIC PROPULSION AND SOLID PROPELLANT CHEMICAL PROPULSION 审中-公开
标题翻译：具有电动推进和固体推进剂的空间车辆化学推进
公开(公告)号：US20150021439A1
公开(公告)日：2015-01-22
申请号：US14375615
申请日：2013-01-31
申请人： HERAKLES
发明人： Olivier Duchemin , Pierre Marcel Yvart
IPC分类号： B64G1/40 , B64G1/42 , B64G1/24 , B64G1/10
CPC分类号： B64G1/403 , B64G1/10 , B64G1/24 , B64G1/405 , B64G1/406 , B64G1/42 , B64G1/428 , F02K9/22 , F03H1/0018
摘要： A space vehicle (1), in particular a satellite or a probe, capable of executing high-thrust maneuvers or high specific impulse maneuvers. According to the invention, the space vehicle (1) includes at least one solid-propellant chemical thruster (10-14) and at least one electric thruster (20-24).
摘要翻译：一种能够执行高推力机动或高比冲击动作的太空飞行器（1），特别是卫星或探头。根据本发明，空间车辆（1）包括至少一个固体推进剂化学推进器（10-14）和至少一个电推进器（20-24）。

7. 发明授权

US08800933B2 Space debris removal 有权
标题翻译：空间碎片清除
公开(公告)号：US08800933B2
公开(公告)日：2014-08-12
申请号：US13069028
申请日：2011-03-22
申请人： Michael J. Dunn
发明人： Michael J. Dunn
IPC分类号： B64G1/10 , B64G1/56 , B64G1/00 , B64G4/00 , B64G1/24 , B64G1/40
CPC分类号： B64G1/56 , B64G1/007 , B64G1/1078 , B64G1/242 , B64G1/401 , B64G1/403 , B64G4/00
摘要： A method comprises removing space debris having a relatively low ballistic coefficient by hastening orbital decay of the debris. A transient gaseous cloud is created at an altitude of at least 100 km above Earth. The cloud has a density sufficient to slow the debris so the debris falls into Earth's atmosphere.
摘要翻译：一种方法包括通过加速碎片的轨道衰减来去除具有相对低的弹道系数的空间碎片。在地球至少100公里的高度产生瞬态气体云。云具有足以减缓碎片的密度，使碎片落入地球大气层。

8. 发明授权

US08659422B2 Condition, health, and usage monitoring system 有权
标题翻译：条件，健康和使用监测系统
公开(公告)号：US08659422B2
公开(公告)日：2014-02-25
申请号：US12508433
申请日：2009-07-23
申请人： Terry A. Tracy , Behzad Moslehi , Gregory A. Ruderman
发明人： Terry A. Tracy , Behzad Moslehi , Gregory A. Ruderman
IPC分类号： G08B1/08
CPC分类号： B64G1/403 , F02K9/32 , F02K9/96
摘要： A sensor module includes a number of environment sensors and condition sensor interfaces. Each condition sensor interface is configured to couple with a condition sensor capable of sensing an attribute of a component exposed to the environment. The sensor module may be embedded within a structure associated with the component. For example, in the context of a solid rocket motor, the sensor module may be embedded within the exhaust plug.
摘要翻译：传感器模块包括许多环境传感器和条件传感器接口。每个条件传感器接口被配置为与能够感测暴露于环境的部件的属性的条件传感器耦合。传感器模块可以嵌入与组件相关联的结构中。例如，在固体火箭发动机的上下文中，传感器模块可以嵌入在排气塞内。

9. 发明申请

US20120181373A1 PROJECTILE AND METHOD THAT INCLUDE SPEED ADJUSTING GUIDANCE AND PROPULSION SYSTEMS 有权
标题翻译：包括速度调节指导和推进系统的项目和方法
公开(公告)号：US20120181373A1
公开(公告)日：2012-07-19
申请号：US13020276
申请日：2011-02-03
申请人： Andrew B. Facciano , James A. Ebel , Michael Alkema , Robert D. Travis , Mike J. Saxton
发明人： Andrew B. Facciano , James A. Ebel , Michael Alkema , Robert D. Travis , Mike J. Saxton
IPC分类号： F42B15/01 , F42B10/32 , F42B12/02 , F41G7/00
CPC分类号： B64G1/002 , B64G1/401 , B64G1/403 , F42B10/32 , F42B15/01 , F42B15/10
摘要： Some embodiments pertain to a projectile and method that includes a flight vehicle and a propulsion system attached to the flight vehicle. The propulsion system includes a plurality of motors that propel the projectile. A guidance system is connected to the propulsion system. The guidance system ignites an appropriate number of the motors to adjust the speed of the projectile based on the location of the projectile relative to a desired destination for the flight vehicle. In some embodiments, the flight vehicle is a kinetic warhead. The projectile may be an interceptor that includes a first propulsion stage, a second propulsion stage and a third propulsion stage that includes the third propulsion system. The number of booster motors that will be ignited by the guidance system depends on the speed that the projectile needs to be adjusted to in order to maneuver the projectile to a desired location.
摘要翻译：一些实施例涉及包括飞行车辆和附接到飞行器车辆的推进系统的射弹和方法。推进系统包括推动射弹的多个马达。引导系统连接到推进系统。引导系统点燃适当数量的电机，以根据飞弹相对于飞行器的所需目的地的位置来调整射弹的速度。在一些实施例中，飞行器是动力弹头。抛射体可以是包括第一推进阶段，第二推进阶段和包括第三推进系统的第三推进阶段的拦截器。引导系统将引燃的助力马达的数量取决于弹丸需要调整的速度，以便将弹丸操纵到所需的位置。

10. 发明授权

US08033021B2 Method for fabricating structural propellants 有权
标题翻译：制造结构推进剂的方法
公开(公告)号：US08033021B2
公开(公告)日：2011-10-11
申请号：US12689562
申请日：2010-01-19
申请人： Prakash B. Joshi , Bernard L. Upschulte , Alan H. Gelb , B. David Green , Dean M. Lester , W. David Starrett , Ingvar A. Wallace
发明人： Prakash B. Joshi , Bernard L. Upschulte , Alan H. Gelb , B. David Green , Dean M. Lester , W. David Starrett , Ingvar A. Wallace
IPC分类号： B21D53/92
CPC分类号： B64G1/403 , B64G1/22 , B64G1/421 , C06B21/005 , C06B31/28 , C06B45/10 , C06D5/00 , F02K9/08 , F02K9/32 , F02K9/36 , F42B3/02 , F42B5/16 , Y10T29/49622
摘要： A vehicle includes at least one polyoxymethylene structural support member. The polyoxymethylene structural support member includes a polyoxymethylene component that is a propellant that provides thrust to the vehicle upon pyrolysis or combustion of the polyoxymethylene component of the product of pyrolysis of the polyoxymethylene component. The vehicle can be a satellite or other type of spacecraft.
摘要翻译：车辆包括至少一个聚甲醛结构支撑构件。聚甲醛结构支撑构件包括聚甲醛组分，其是推进剂，其在热分解或燃烧聚氧化亚甲基组分的热解产物的聚甲醛组分时向车辆提供推力。车辆可以是卫星或其他类型的航天器。

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