公开(公告)号：US09102421B2

公开(公告)日：2015-08-11

申请号：US13783301

申请日：2013-03-03

Applicant: Fukashi Andoh

Inventor： Fukashi Andoh

IPC: B64G1/26

CPC classification number: B64G1/26 ,  B64G1/12

Abstract: An attitude control device for space station with system parameter uncertainties and on-orbit dynamic disturbances. A plurality of state sensors measure a plurality of states of the space station. An identification frequency selecting device selects an identification frequency. A moment of inertia identification operator calculation unit calculates a moment of inertia identification operator. A moment of inertia identification device calculates moment of inertia of the space station. A disturbance torque identification device calculates disturbance torque. A control torque calculation unit calculates a control signal. A plurality of thrusters generate a control torque based on the control signal.

Abstract translation: 一种具有系统参数不确定性和轨道动态扰动的空间站姿态控制装置。 多个状态传感器测量空间电台的多个状态。 识别频率选择装置选择识别频率。 惯性矩识别算子计算单元计算惯性矩识别算子。 惯性矩识别装置计算空间站的惯性矩。 扰动转矩识别装置计算扰动转矩。 控制扭矩计算单元计算控制信号。 多个推进器基于控制信号产生控制转矩。

公开(公告)号：US08886371B2

公开(公告)日：2014-11-11

申请号：US12987434

申请日：2011-01-10

Applicant: William C. Peters

Inventor： William C. Peters

IPC: B64G1/36 ,  G05D1/08 ,  B64G1/26 ,  B64G1/24

CPC classification number: G05D1/0858 ,  B64C15/02 ,  G05D1/0883

Abstract: A vehicle having a plurality of thruster components, wherein each of the thruster components includes a plurality of sub-thrusters, each sub-thruster being grouped into one of a plurality of control groups. The vehicle including a control system receiving information related to the vehicle, wherein the control system selects one of the control groups and activates the sub-thrusters of the selected control group.

Abstract translation: 一种具有多个推进器部件的车辆，其中每个推进器部件包括多个次推进器，每个副推进器被分组成多个控制组中的一个。 所述车辆包括接收与所述车辆相关的信息的控制系统，其中所述控制系统选择所述控制组中的一个并激活所选择的控制组的所述次推进器。

公开(公告)号：US08702041B2

公开(公告)日：2014-04-22

申请号：US12443359

申请日：2007-10-17

Applicant: Christophe Chavagnac ,  Jérôme Bertrand ,  Hugues Laporte-Weywada ,  Olivier Poulain ,  Philippe Matharan ,  Robert Laine

Inventor： Christophe Chavagnac ,  Jérôme Bertrand ,  Hugues Laporte-Weywada ,  Olivier Poulain ,  Philippe Matharan ,  Robert Laine

IPC: B64G1/14 ,  B64G1/26 ,  B64G1/40 ,  B64D27/02 ,  B64C39/12

CPC classification number: B64G1/005 ,  B64D27/023 ,  B64D2027/026 ,  B64G1/002 ,  B64G1/14 ,  B64G1/401 ,  Y02T50/44

Abstract: An aircraft having propulsion units for both conventional aircraft flight in the atmosphere and for high-altitude operation as a rocket. The aircraft is divided into a payload compartment and a compartment containing rocket propulsion unit propellant or fuel, and includes a long transverse wing with a small back-sweep to favor lift in the dense layers of the atmosphere and to thus make it possible to climb to high altitudes at a subsonic speed before using the rocket propulsion units. The return flight portion is performed by gliding or controlled as for a conventional aircraft.

Abstract translation: 一架飞机具有用于常规飞机在大气中飞行和作为火箭进行高空作战的推进装置。 飞机分为有效载荷舱和包含火箭推进装置推进剂或燃料的舱室，并且包括具有小的反向扫掠的长横翼，以有利于在大气层的致密层中的升力，从而使其可以爬上 在使用火箭推进装置之前，亚音速的高海拔高度。 返回飞行部分通过滑翔或受控于常规飞机执行。

公开(公告)号：US20120187250A1

公开(公告)日：2012-07-26

申请号：US12931005

申请日：2011-01-21

Applicant: Vaclav Majer

Inventor： Vaclav Majer

IPC: B64G1/26

CPC classification number: B64G1/26 ,  B64G1/242 ,  B64G1/405

Abstract: A satellite longitude and drift control method is provided that includes providing a satellite that has a continuously or a quasi-continuously firing thruster, where the thruster is disposed to apply accelerations which counter a tri-axiality displacement in an orbit of the satellite, and the satellite thruster is disposed to achieve optimal ΔV performance in the presence of orbit determination and orbit propagation errors. The method further includes targeting an optimal two-phase continuous acceleration target cycle using the continuously or the quasi-continuously firing thruster, providing a closed loop and a hybrid loop implementation of the thruster firing, where the hybrid loop implementation includes an open and closed loop implementation, and where the closed loop and the hybrid loop implementations are disposed to provide quasi-continuous implementations of an optimal continuous control program.

Abstract translation: 提供了一种卫星经度和漂移控制方法，其包括提供具有连续或准连续点火推进器的卫星，其中推进器被设置为施加相对于卫星轨道中的三轴位移的加速度，并且 设置卫星推进器以在存在轨道确定和轨道传播误差的情况下实现最佳的Dgr。V性能。 该方法还包括使用连续或准连续点火推进器来瞄准最佳两相连续加速度目标循环，提供闭环和推进器点火的混合回路实现，其中混合回路实现包括开闭闭环 实现，以及闭环和混合环路实现被设置在何处以提供最佳连续控制程序的准连续实现。

公开(公告)号：US20110248120A1

公开(公告)日：2011-10-13

申请号：US13165655

申请日：2011-06-21

Applicant: Moonish R. PATEL ,  Neil E. GOODZEIT

Inventor： Moonish R. PATEL ,  Neil E. GOODZEIT

IPC: B64G1/28 ,  B64G1/26

CPC classification number: B64G1/283 ,  B64G1/007 ,  B64G1/26 ,  B64G2001/245

Abstract: A system for providing attitude control with respect to a spacecraft is provided. The system includes a reaction wheel control module configured to control a number of reaction wheel assemblies associated with the spacecraft in order to control attitude, and a maneuver control module configured to use a number of gimbaled Hall Current thrusters (HCTs) to control the total momentum associated with the spacecraft. The total momentum includes the momentum associated with the reaction wheel assemblies and the angular momentum of the spacecraft. Using the gimbaled HCTs to control the momentum associated with the reaction wheel assemblies results in minimal HCT gimbal stepping.

Abstract translation: 提供了一种用于提供关于航天器的姿态控制的系统。 该系统包括反作用轮控制模块，其配置成控制与航天器相关联的多个反作用轮组件以控制姿态;以及机动控制模块，其被配置为使用多个万向霍尔电流推进器（HCT）来控制总动量 与航天器有关。 总动量包括与反作用轮组件相关联的动量和航天器的角动量。 使用万向HCT来控制与反作用轮组件相关的动量导致最小的HCT万向节步进。

公开(公告)号：US07988097B2

公开(公告)日：2011-08-02

申请号：US12639937

申请日：2009-12-16

Applicant: Moonish R. Patel ,  Neil E. Goodzeit

Inventor： Moonish R. Patel ,  Neil E. Goodzeit

IPC: B64G1/26 ,  B64G1/28

CPC classification number: B64G1/283 ,  B64G1/007 ,  B64G1/26 ,  B64G2001/245

Abstract: A system for providing attitude control with respect to a spacecraft is provided. The system includes a reaction wheel control module configured to control a number of reaction wheel assemblies associated with the spacecraft in order to control attitude, and a maneuver control module configured to use a number of gimbaled Hall Current thrusters (HCTs) to control the total momentum associated with the spacecraft during an orbit transfer. The total momentum includes the momentum associated with the reaction wheel assemblies and the angular momentum of the spacecraft. Using the gimbaled HCTs to control the momentum associated with the reaction wheel assemblies during the orbit transfer results in minimal HCT gimbal stepping.

Abstract translation: 提供了一种用于提供关于航天器的姿态控制的系统。 该系统包括反作用轮控制模块，其配置成控制与航天器相关联的多个反作用轮组件以控制姿态;以及机动控制模块，其被配置为使用多个万向霍尔电流推进器（HCT）来控制总动量 在轨道转移期间与航天器相关联。 总动量包括与反作用轮组件相关的动量和航天器的角动量。 在轨道转移期间使用万向HCT来控制与反作用轮组件相关的动量导致最小的HCT万向节步进。

公开(公告)号：US07922124B2

公开(公告)日：2011-04-12

申请号：US11608229

申请日：2006-12-07

Applicant: James D. Soldi ,  Andrew I. Mactavish

Inventor： James D. Soldi ,  Andrew I. Mactavish

IPC: B64G1/10 ,  B64G1/26 ,  B64G1/44

CPC classification number: B64G1/242 ,  B64G1/405 ,  B64G1/428

Abstract: Systems and methods are disclosed employing electric propulsion stationkeeping in a cyclical manner to better match the cyclical pattern of power generated by the solar array system. For a typical orbit design, e.g. a geostationary orbit, North-South stationkeeping can be intermittently suspended, tolerating some additional drift but yielding in a very significant reduction in the required solar power system. If necessary, stationkeeping can be supplemented with a chemical thrusters during off periods for the electric propulsion. Because of this, the overall electrical power margin for the solar array system design can be reduced without compromising the mission performance.

Abstract translation: 公开了以循环方式使用电力推进维护以更好地匹配由太阳能阵列系统产生的功率的循环模式的系统和方法。 对于典型的轨道设计，例如 一个地球静止轨道，南北驻守可以间歇地暂停，容忍一些额外的漂移，但是在所需的太阳能发电系统中显着减少。 如有必要，在电力推进的关闭期间，可以用化学推进器补充维护保养。 因此，可以减少太阳能电池阵列系统设计的整体电力余量，而不损害任务性能。

公开(公告)号：US20100168938A1

公开(公告)日：2010-07-01

申请号：US12576203

申请日：2009-10-08

Applicant: Hyun Ho Seo ,  Ki Lyuk Yong ,  Shi Hwan Oh ,  Hong Taek Choi ,  Seon Ho Lee ,  Jo Ryeong Yim ,  Yong Bok Kim ,  Hye Jin Lee

Inventor： Hyun Ho Seo ,  Ki Lyuk Yong ,  Shi Hwan Oh ,  Hong Taek Choi ,  Seon Ho Lee ,  Jo Ryeong Yim ,  Yong Bok Kim ,  Hye Jin Lee

IPC: G05D1/00 ,  B64G1/28 ,  B64G1/26

CPC classification number: B64G1/26 ,  B64G1/283 ,  B64G2001/245 ,  G05D1/0883

Abstract: Provided are an attitude control system and method of a spacecraft of an artificial satellite that may enhance a maneuverability and a controllability by simultaneously applying a reaction wheel and a thruster among drive units used to maneuver an attitude of the spacecraft of the artificial satellite. The attitude control system may include: a thruster-based attitude controller which control firing time of thrusters mounted on the spacecraft; and a reaction wheel-based attitude controller controlling driving of a reaction wheel mounted on the spacecraft. The spacecraft may include a plurality of reaction wheels. When a defect occurs in the spacecraft due to a partial malfunction of the reaction wheels, an attitude maneuverability of the spacecraft may be corrected by simultaneously applying the thruster-based attitude controller and the reaction wheel-based attitude controller.

Abstract translation: 提供了一种人造卫星的航天器的姿态控制系统和方法，其可以通过在用于操纵人造卫星的航天器的姿态的驱动单元中同时施加反作用轮和推进器来增强机动性和可控性。 姿态控制系统可以包括：基于推进器的姿态控制器，其控制安装在航天器上的推进器的点火时间; 以及控制驱动安装在航天器上的反作用轮的反作用轮式姿态控制器。 航天器可以包括多个反作用轮。 当由于反射轮的部分故障而在航天器中发生缺陷时，可以通过同时施加基于推进器的姿态控制器和基于反作用轮的姿态控制器来校正航天器的姿态机动性。

公开(公告)号：US07654490B2

公开(公告)日：2010-02-02

申请号：US10522576

申请日：2004-10-14

Applicant: Moonish R. Patel ,  Neil E. Goodzeit

Inventor： Moonish R. Patel ,  Neil E. Goodzeit

IPC: B64G1/26 ,  B64G1/28

CPC classification number: B64G1/283 ,  B64G1/007 ,  B64G1/26 ,  B64G2001/245

Abstract: A system for providing attitude control with respect to a spacecraft is provided. The system includes a reaction wheel control module configured to control a number of reaction wheel assemblies associated with the spacecraft in order to control attitude, and a maneuver control module configured to use a number of gimbaled Hall Current thrusters (HCTs) to control the total momentum associated with the spacecraft during an orbit transfer. The total momentum includes the momentum associated with the reaction wheel assemblies and the angular momentum of the spacecraft. Using the gimbaled HCTs to control the momentum associated with the reaction wheel assemblies during the orbit transfer results in minimal HCT gimbal stepping.

Abstract translation: 提供了一种用于提供关于航天器的姿态控制的系统。 该系统包括反作用轮控制模块，其配置成控制与航天器相关联的多个反作用轮组件以控制姿态;以及机动控制模块，其被配置为使用多个万向霍尔电流推进器（HCT）来控制总动量 在轨道转移期间与航天器相关联。 总动量包括与反作用轮组件相关的动量和航天器的角动量。 在轨道转移期间使用万向HCT来控制与反作用轮组件相关的动量导致最小的HCT万向节步进。

公开(公告)号：US20090166476A1

公开(公告)日：2009-07-02

申请号：US12331183

申请日：2008-12-09

Applicant: James A Termini

Inventor： James A Termini

IPC: B64G1/26

CPC classification number: B64G1/1078 ,  B64G1/242 ,  B64G1/26 ,  B64G1/405 ,  B64G1/646

Abstract: Enhanced translational thrusting is provided by reaction engines configured to permit translational thrusting off or through the center of gravity of a spacecraft or other vehicle. Among other applications, this approach is useful for a Satellite Life Extension System (SLES) that provides maintenance services to orbiting satellites. By attaching to the satellite and conducting maneuvers to maintain its operational orbit and attitude, the SLES increases the working lifetime of the satellite. Since the engines of the SLES are redundant, the failure of a single engine will not jeopardize the overall success of the mission.

Abstract translation: 增强的平移推力由构造成允许平移推力或通过航天器或其他车辆的重心的反作用发动机提供。 在其他应用中，这种方法对于为轨道卫星提供维护服务的卫星生命延长系统（SLES）是有用的。 通过附加卫星和进行机动以维持其操作轨道和态度，SLES增加了卫星的工作寿命。 由于SLES的引擎是多余的，因此单个引擎的故障不会危及任务的整体成功。