-
1.发明申请LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF 有权发射车辆及其经济有效发射的系统及方法公开(公告)号：US20140306065A1
公开(公告)日：2014-10-16
申请号：US14211779
申请日：2014-03-14
IPC分类号： B64G1/40
CPC分类号： B64G1/409 , B64G1/002 , B64G1/402 , B64G1/406 , F02K9/95 , F41A1/04 , F41B6/00 , F41B6/006 , F41F1/00 , F41F3/04 , F41F3/0406 , F42B6/006 , F42B15/10 , F42B15/12 , F42C11/00 , F42C11/04
摘要： The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.
摘要翻译： 本公开涉及一种发射系统，与发射系统一起使用的运载火箭，以及使用该运载火箭和/或发射系统发射有效载荷的方法。 本公开可以提供在地面位置，地球轨道位置或眶外位置处的有效载荷的传送。 运载火箭可以包括有效载荷，推进剂罐，电加热器，其中推进剂，例如轻质气体（例如氢气）被电加热至显着高的温度，以及排气喷嘴，加热的推进剂从该喷嘴膨胀以提供排气 例如7-16公里/秒的速度。 运载火箭可以与发射系统一起使用，其可以进一步包括由至少一个管形成的发射管，其可以是导电的并且可以与至少一个绝缘管组合。 可以提供诸如电池组和相关电感器的电能源。
-
公开(公告)号：US08025002B2
公开(公告)日：2011-09-27
申请号：US12381378
申请日：2009-03-11
IPC分类号： B64D1/04
摘要： A system for defending a planet having a satellite against impact from an incoming body includes an explosive system and a propulsion system. The explosive system is adapted for deployment on the satellite and detonation thereon with sufficient explosive force to produce at least one ejectum to which is imparted a velocity increment sufficient for the ejectum to exceed the satellite's escape velocity and enter orbit about the planet. The propulsion system is adapted to be secured to at least one ejectum and impart a velocity increment to the ejectum sufficient to leave orbit about the planet and enter an orbit intercepting the incoming body.The system is used in a planetary defense method in which the explosive system is deployed at a deployment site on the satellite and detonated to produce at least one ejectum having a velocity that exceeds the escape velocity of the satellite. The ejectum enters into orbit around the planet, at which time the propulsion system is secured to the ejectum to produce a projectile. The propulsion system is then activated to increase the velocity of the projectile, causing the projectile to enter into an intercept orbit targeting the incoming body and subsequently intercept and impact the incoming body. The impact prevents the incoming body from impacting the planet.
摘要翻译： 一种用于捍卫具有卫星的行星的系统，防止来自进入的身体的撞击包括爆炸系统和推进系统。 爆炸系统适用于在卫星上部署并以足够的爆炸力对其进行爆炸，以产生至少一个喷射，其中赋予足够的速度增量以使喷射超过卫星的逃逸速度并进入围绕行星的轨道。 推进系统适于固定在至少一个弹射片上，并赋予足够的速度增量以足以离开行星轨道并进入拦截入射体的轨道。 该系统用于行星防御方法，其中爆炸系统部署在卫星的部署地点并被引爆以产生具有超过卫星逃逸速度的速度的至少一个弹射。 弹头进入围绕行星的轨道，此时推进系统被固定到弹头以产生射弹。 然后启动推进系统以增加弹丸的速度，使射弹进入瞄准进入身体的拦截轨道，并随后拦截和撞击进入的身体。 这种冲击防止进入的身体撞击地球。
-
3.发明申请LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF 有权发射车辆及其经济有效发射的系统及方法公开(公告)号：US20160368623A1
公开(公告)日：2016-12-22
申请号：US15251408
申请日：2016-08-30
发明人： Miles R. Palmer
CPC分类号： B64G1/409 , B64G1/002 , B64G1/402 , B64G1/406 , F02K9/95 , F41A1/04 , F41B6/00 , F41B6/006 , F41F1/00 , F41F3/04 , F41F3/0406 , F42B6/006 , F42B15/10 , F42B15/12 , F42C11/00 , F42C11/04
摘要： The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.
摘要翻译： 本公开涉及一种发射系统，与发射系统一起使用的运载火箭，以及使用该运载火箭和/或发射系统发射有效载荷的方法。 本公开可以提供在地面位置，地球轨道位置或眶外位置处的有效载荷的传送。 运载火箭可以包括有效载荷，推进剂罐，电加热器，其中诸如轻质气体（例如氢气）的推进剂被电加热到显着高的温度，加热的推进剂从该喷嘴膨胀以提供排气速度 例如为7-16km / sec，以及与电加热器电连接的滑动电触头。 运载火箭可以与发射系统一起使用，其可以进一步包括由同心导电管形成的发射管，以及电能源，例如电池组和相关联的电感器。
-
4.发明申请LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF 有权发射车辆及其经济有效发射的系统及方法公开(公告)号：US20140306064A1
公开(公告)日：2014-10-16
申请号：US14211698
申请日：2014-03-14
申请人： Palmer Labs, LLC
发明人： Miles R. Palmer
IPC分类号： B64G1/40
CPC分类号： B64G1/409 , B64G1/002 , B64G1/402 , B64G1/406 , F02K9/95 , F41A1/04 , F41B6/00 , F41B6/006 , F41F1/00 , F41F3/04 , F41F3/0406 , F42B6/006 , F42B15/10 , F42B15/12 , F42C11/00 , F42C11/04
摘要： The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.
摘要翻译： 本公开涉及一种发射系统，与发射系统一起使用的运载火箭，以及使用该运载火箭和/或发射系统发射有效载荷的方法。 本公开可以提供在地面位置，地球轨道位置或眶外位置处的有效载荷的传送。 运载火箭可以包括有效载荷，推进剂罐，电加热器，其中诸如轻质气体（例如氢气）的推进剂被电加热到显着高的温度，加热的推进剂从该喷嘴膨胀以提供排气速度 例如为7-16km / sec，以及与电加热器电连接的滑动电触头。 运载火箭可以与发射系统一起使用，其可以进一步包括由同心导电管形成的发射管，以及电能源，例如电池组和相关联的电感器。
-
5.发明申请DISTRIBUTED ORDNANCE SYSTEM, MULTIPLE STAGE ORDNANCE SYSTEM, AND RELATED METHODS 有权分布式系统，多级阶段系统及相关方法公开(公告)号：US20140069289A1
公开(公告)日：2014-03-13
申请号：US13608824
申请日：2012-09-10
CPC分类号： F42B15/01 , F02K9/95 , F42B15/12 , F42B15/36 , Y10T29/49764
摘要： A distributed ordnance system comprises a plurality of ordnance controllers and a plurality of firing units. Each ordnance controller of the plurality of ordnance controllers may be operably coupled with at least one firing unit of the plurality of firing units. Each ordnance controller may be configured to provide power signals to the at least one firing unit coupled therewith, and communicate with the at least one firing unit for initiation of an ordnance event. A multiple-stage ordnance system may comprise a first stage and a second stage that each include an ordnance controller configured to control operation of an ordnance event, and at least one firing unit to initiate the ordnance event. Related methods for constructing a multiple-stage ordnance control system and controlling initiation of an energetic material are also disclosed.
摘要翻译： 分布式弹药系统包括多个弹药控制器和多个发射单元。 多个弹药控制器的每个弹药控制器可以与多个击发单元中的至少一个击发单元可操作地联接。 每个弹药控制器可以被配置为向与其耦合的至少一个击发单元提供功率信号，并且与至少一个击发单元通信以启动弹药事件。 多级武器系统可以包括第一级和第二级，每级包括被配置为控制弹药事件的操作的弹药控制器，以及至少一个起动单元以启动弹药事件。 还公开了用于构建多级弹道控制系统和控制高能材料的启动的相关方法。
-
公开(公告)号：US07687750B2
公开(公告)日：2010-03-30
申请号：US11766957
申请日：2007-06-22
申请人： Raoul D. Revord
发明人： Raoul D. Revord
摘要： A system under international control is in possession of the firing codes required to launch missiles owned by the parties to the system. Upon a request to the international authority for the release of its firing codes so that it may launch a first strike, the target party is advised of the request and given the opportunity to launch its own missiles first. The system deters first strikes.
摘要翻译： 国际管制的系统拥有发射系统各方拥有的导弹所需的射击守则。 应国际权力机关要求释放其射击守则，以便可以发起罢工，向目标方通知请求，并有机会首先发射自己的导弹。 该系统阻止了第一次罢工。
-
公开(公告)号：US20090241763A1
公开(公告)日：2009-10-01
申请号：US11766957
申请日：2007-06-22
申请人： Raoul D. Revord
发明人： Raoul D. Revord
摘要： A system under international control is in possession of the firing codes required to launch missiles owned by the parties to the system. Upon a request to the international authority for the release of its firing codes so that it may launch a first strike, the target party is advised of the request and given the opportunity to launch its own missiles first. The system deters first strikes.
摘要翻译： 国际管制的系统拥有发射系统各方拥有的导弹所需的射击守则。 应国际权力机关要求释放其射击守则，以便可以发起罢工，向目标方通知请求，并有机会首先发射自己的导弹。 该系统阻止了第一次罢工。
-
公开(公告)号：US3026772A
公开(公告)日：1962-03-27
申请号：US71305458
申请日：1958-02-03
发明人： MORELAND CARLTON A
CPC分类号： F02K9/20 , F02K9/18 , F42B15/12 , Y10S285/92
-
公开(公告)号：US20170264015A1
公开(公告)日：2017-09-14
申请号：US15068026
申请日：2016-03-11
申请人： Raytheon Company
发明人： Glafkos K. Stratis , Anton Vanderwyst , Wayne L. Sunne , David G. Derrick , James P. Edmiston , David G. Manzi , Howard C. Choe , Alphonso A. Samuel
CPC分类号： H01Q3/34 , B64C30/00 , B64G1/66 , F42B15/10 , F42B15/12 , F42B15/34 , G01B7/06 , G01N9/24 , H01Q1/281 , H01Q1/42 , H01Q21/20 , H01Q21/28 , H05H1/00 , H05H1/0062
摘要： A sensor system and method of reducing plasma-induced communication inhibition for a main antenna includes using auxiliary antennas for detecting a density of plasma that affects operation of the main antenna, and re-orienting an electromagnetic field around the main antenna in response to the density detected to reduce effect of the plasma on the main antenna. The auxiliary antennas are also operable for data link communication and switchable such if the density of the plasma inhibits receipt or sending of signals by one of the auxiliary antennas, another one of the auxiliary antennas may be used for data link communication.
-
公开(公告)号：US09617016B2
公开(公告)日：2017-04-11
申请号：US14211779
申请日：2014-03-14
CPC分类号： B64G1/409 , B64G1/002 , B64G1/402 , B64G1/406 , F02K9/95 , F41A1/04 , F41B6/00 , F41B6/006 , F41F1/00 , F41F3/04 , F41F3/0406 , F42B6/006 , F42B15/10 , F42B15/12 , F42C11/00 , F42C11/04
摘要： The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.
-
-
-
-
-
-
-
-
-
搜索结果
32 条记录 (耗时 0.018 秒)