-
公开(公告)号：US20190202582A1
公开(公告)日：2019-07-04
申请号：US16329012
申请日：2017-09-05
发明人： Kenji KITAMURA , Takeya SHIMA , Katsuhiko YAMADA
摘要： When calculating a gimbal angle trajectory that satisfies boundary conditions set by an attitude boundary condition setter 2131 of the ground station 21, a gimbal angle trajectory calculator 2132 calculates the gimbal angle trajectory that minimizes a period of an acceleration interval within a range that satisfies driving restrictions of a gimbal, based on a gimbal angle θ0i of a start time and a gimbal angle θci of a fixed interval of an attitude change. Also, the gimbal angle trajectory is calculated that minimizes a period of a deceleration interval within a range that satisfies the driving restrictions of the gimbal, based on the gimbal angle θci of the fixed interval and a gimbal angle θfi of a completion time of the attitude change. The obtained θ0i, θci, θfi and an attitude change period τ are transmitted to the artificial satellite as gimbal angle trajectory parameters, and the control moment gyros are controlled based on the gimbal angle trajectory parameters.
-
公开(公告)号：US09963248B2
公开(公告)日：2018-05-08
申请号：US15016204
申请日：2016-02-04
申请人： The Boeing Company
发明人： Qinghong W. Wang , Alexander Jacob Sobel , Gary Lemke , Timothy Lui , Kangsik Lee , Glenn N. Caplin , Troy Allen Fontana
CPC分类号： B64G1/24 , B64G1/007 , B64G1/26 , B64G1/281 , B64G1/283 , B64G1/285 , B64G1/286 , B64G1/36 , B64G1/405 , B64G2001/245
摘要： Apparatus and methods for controlling a spacecraft for a transfer orbit. The spacecraft includes a momentum subsystem that stores angular momentum relative to a center of mass of the spacecraft, and a propulsion subsystem that includes electric thrusters. A controller identifies a target spin axis for the spacecraft, determines gimbal angles for electric thruster(s) that so that thrust forces from the electric thrusters are parallel to the target spin axis, and initiates a burn of the electric thruster(s) at the gimbal angles. The controller controls the momentum subsystem to compensate for a thruster torque produced by the burn of the electric thrusters. The momentum subsystem is able to produce a target angular momentum about the center of mass, where a coupling between the target angular momentum and an angular velocity of the spacecraft creates an offset torque to counteract the thruster torque.
-
公开(公告)号：US20170336807A1
公开(公告)日：2017-11-23
申请号：US15156507
申请日：2016-05-17
申请人： Raytheon Company
发明人： Eero H. Ala , Christopher P. Owan
CPC分类号： G05D1/0808 , B64C19/00 , B64G1/244 , B64G1/286 , B64G2001/245 , F42B10/025 , G01C19/04
摘要： An attitude control system includes one or more control moment gyro pairs, with gyros of individual of the pairs being counter-rotated to rotate the rotation axes of flywheels of the gyros of a gyro pair in opposite direction. The flywheels of a gyro pair may be in paddle configuration, with the rotation axes of the flywheels rotating in the counter-rotation through separate planes as the gyros are rotated. The rotation of the gyros of a gyro pair may be accomplished by coupling both of the gyros to a servo motor with suitable coupling gears, or by using independent servos for each gyro. The counter-rotation of gyros of an individual pair produces a resultant torque about a fixed global axis, such as the axis of a flight vehicle of which the attitude control system is a part. Further control may be accomplished for example by varying rotation speeds of the flywheels.
-
公开(公告)号：US09745082B2
公开(公告)日：2017-08-29
申请号：US15140065
申请日：2016-04-27
发明人： Sungyung Lim , Seamus Tuohy , Daniel Dionne , Laurent Duchesne , Louis Breger
CPC分类号： B64G1/286 , B64G1/242 , B64G1/283 , B64G2001/245 , G05D1/0883
摘要： A new approach for rapid slew and settle of small satellites is based on four single degree-of-freedom control moment gyroscopes with variable speed flywheels (or reaction wheels) in a pyramid configuration, combined with path and endpoint constraint time-optimal control. The path and endpoint constrained time-optimal control can be augmented with momentum management without the use of additional actuators.
-
公开(公告)号：US09671789B1
公开(公告)日：2017-06-06
申请号：US15371506
申请日：2016-12-07
申请人： Beihang University
发明人： Lei Guo , Jianwei Xu , Jianzhong Qiao , Peixi Zhang
CPC分类号： G05D1/0883 , B64G1/24 , B64G2001/245
摘要： A method and system for anti-interference compound on-line guidance in the atmosphere-entering stage of a Mars lander is provided in the present invention. The method comprises steps of a) building a dynamics model for the atmosphere-entering phase of a Mars lander to incorporating the disturbance brought by the Mars atmosphere density uncertainty into the dynamics model for the atmosphere-entering stage of the Mars lander; b) constructing a disturbance observer to estimate the disturbance brought by the Mars atmosphere density uncertainty in the dynamics model for the atmosphere-entering phase of the Mars lander; c) building a prediction-correction guidance law, and guiding the heeling angle amplitude of the prediction-correction guidance law by continuously updating undetermined parameters; d) constructing an anti-disturbance composite guidance law to compensate the Mars atmosphere density uncertainty; and e) adjusting the deviation of the landing point of the Mars lander by compensating the Mars atmosphere uncertainty disturbance.
-
公开(公告)号：US09296494B1
公开(公告)日：2016-03-29
申请号：US13572586
申请日：2012-08-10
CPC分类号： B64G1/242 , B64G1/26 , B64G1/405 , B64G2001/245
摘要： Embodiments of the present invention provide an ion-thruster stationkeeping method and mounting configuration that reduces the propellant penalty when a single thruster fails, e.g., in the case where only three of a spacecraft's four ion thrusters are available. By improving firing efficiency for the single-thruster failure case, on-board propellant is reduced, thereby allowing increased payload mass. Also, the configuration supports both N/S and E/W stationkeeping using four ion thrusters (or three thrusters for the failure case) and therefore does not require a separate propulsion system or thrusters for E/W stationkeeping.
-
7.发明申请公开(公告)号：US20150369607A1
公开(公告)日：2015-12-24
申请号：US14309324
申请日：2014-06-19
申请人： The Boeing Company
CPC分类号： G01C21/025 , B64G1/361 , B64G2001/245 , G01C25/00 , G06F17/30241
摘要： A system and method for mitigating an occurrence of a dry spot, the method may include: (1) predicting the occurrence of the dry spot by at least one of determining a location of the occurrence of the dry spot, determining a date of the occurrence of the dry spot, and determining a duration of the occurrence of the dry spot; (2) generating a visualization of the occurrence of the dry spot, and (3) modifying a star catalog to reduce an impact of the dry spot by at least one of generating a set of modification to modify the star catalog, generating a modification schedule for modifying the star catalog, and uploading the set of modifications to the star catalog.
摘要翻译： 一种用于减轻干点发生的系统和方法，所述方法可以包括：（1）通过确定干点发生的位置，确定发生日期的至少一个来预测干斑的发生 的干点，并确定干点发生的持续时间; （2）产生干点发生的可视化，以及（3）通过生成一组修改以修改星号目录中的至少一个来修改星号目录以减少干点的影响，生成修改时间表 用于修改星号目录，并将修改集上传到星号目录。
-
8.发明授权Method and apparatus for spacecraft attitude control using polynomial interpolation 有权使用多项式插值的航天器姿态控制方法和装置公开(公告)号：US09061775B2
公开(公告)日：2015-06-23
申请号：US13924969
申请日：2013-06-24
申请人： Isaac M. Ross , Mark Karpenko
发明人： Isaac M. Ross , Mark Karpenko
IPC分类号： B64G1/24
CPC分类号： B64G1/24 , B64G1/1021 , B64G1/26 , B64G1/286 , B64G1/32 , B64G2001/245
摘要： A method, apparatus and system is provided for reducing an amount of information transmitted to a vehicle in order to implement attitude control of the vehicle. In accordance with the present invention, data corresponding to at least one time-varying attitude command trajectory defining an attitude of the vehicle is reduced, for example, into a vector of polynomial coefficients. The vector of polynomial coefficients then are transmitted to the vehicle, where they are used to reconstruct the at least one time-varying attitude command trajectory via a polynomial interpolation operation.
摘要翻译： 提供了一种方法，装置和系统，用于减少发送到车辆的信息量，以便实现车辆的姿态控制。 根据本发明，将与定义车辆姿态的至少一个时变姿态指令轨迹对应的数据例如减少为多项式系数的向量。 然后，多项式系数的向量被发送到车辆，在那里它们被用于通过多项式插值运算重构至少一个时变姿态指令轨迹。
-
公开(公告)号：US20150115107A1
公开(公告)日：2015-04-30
申请号：US14064226
申请日：2013-10-28
申请人： Fukashi Andoh
发明人： Fukashi Andoh
CPC分类号： B64G1/1078 , B64G1/242 , B64G1/26 , B64G1/361 , B64G1/645 , B64G1/646 , B64G1/66 , B64G2001/245
摘要： A space debris remover aiming to remove a space debris object in earth orbits. Angular thrust calculation unit calculates angular thrust. Radial thrust calculation unit calculates radial thrust based on the angular thrust, estimated angular momentum and estimated space debris mass. A foam bonding mechanism connects the space debris remover and the space debris object. A space debris removal controller calculates firing time, and sends a space debris removal control signal comprising the radial thrust, the angular thrust and the firing time. A plurality of first stage thrusters generate the radial thrust and the angular thrust after the firing time. After the stage separator separates a first stage and a second stage of the space debris remover, a plurality of second stage thrusters generate the radial thrust and the angular thrust, and propel the space debris object towards the sun.
摘要翻译： 旨在消除地球轨道上的空间碎片物体的空间碎片清除装置。 角推力计算单元计算角度推力。 径向推力计算单元基于角推力，估计角动量和估计的空间碎片质量来计算径向推力。 泡沫粘合机构连接空间碎片清除器和空间碎片物体。 空间碎片清除控制器计算点火时间，并发送包括径向推力，角度推力和燃烧时间的空间碎片去除控制信号。 多个第一级推进器在点火时间之后产生径向推力和角推力。 在舞台分离器分离空间碎片去除器的第一阶段和第二阶段之后，多个第二阶段推进器产生径向推力和角度推力，并将空间碎片物体推向太阳。
-
10.发明申请公开(公告)号：US20140032022A1
公开(公告)日：2014-01-30
申请号：US13945821
申请日：2013-07-18
申请人： Thales
IPC分类号： B64G1/28
CPC分类号： B64G1/288 , B64G1/007 , B64G1/24 , B64G1/26 , B64G1/283 , B64G1/285 , B64G1/286 , B64G1/36 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/405 , B64G2001/245 , G05D1/0883
摘要： A method for reducing the angular momentum of a spacecraft comprises a propulsion device able to generate a torque along a Z axis corresponding to an axis of maximum inertia or minimum inertia of the spacecraft, an X axis and a Y axis forming with Z an orthogonal frame; an angular momentum accumulating device, able to generate an angular momentum and a torque along the three axes; and a set of sensors able to measure the angular velocities and estimate the angular momentum of the spacecraft. The method comprises a first step of aligning the angular momentum of the spacecraft along the Z axis, consisting in slaving the angular momentum of the angular momentum accumulating device to the angular velocity of the spacecraft, and a second step of reducing the angular momentum of the spacecraft using a torque generated by the propulsion device.
摘要翻译： 用于减小航天器的角动量的方法包括能够产生沿着Z轴对应于航天器的最大惯量或最小惯性的轴的扭矩的推进装置，X轴和Y轴形成正交框架 ; 角动量积存装置，能够沿着三个轴产生角动量和扭矩; 以及能够测量角速度并估计航天器的角动量的一组传感器。 该方法包括使沿着Z轴的航天器的角动量对准的第一步骤，其包括将角动量积存装置的角动量沿着航空器的角速度降低，以及第二步骤， 航天器使用由推进装置产生的扭矩。
-
-
-
-
-
-
-
-
-
搜索结果
219 条记录 (耗时 0.026 秒)
