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公开(公告)号：US20220055773A1
公开(公告)日：2022-02-24
申请号：US17482182
申请日：2021-09-22
发明人： Tal KIANI , Edgar Moody
摘要： A system for vibration control of a cryocooler that cools an imager. The system includes a vibration sensor that is physically affixed to the cryocooler. The vibration sensor senses a physical vibration of the cryocooler and to generates a vibration signal therefrom. The system also includes cryocooler drive electronics operatively coupled to the vibration sensor and the cryocooler. The cryocooler drive electronics output a drive waveform that drives the cryocooler so as to reduce the vibration impact of the cryocooler. The harmonic content of the cryocooler drive waveform is controlled by the cryocooler drive electronics based on the vibration signal.
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公开(公告)号：US10913550B2
公开(公告)日：2021-02-09
申请号：US15934066
申请日：2018-03-23
申请人： THE BOEING COMPANY
IPC分类号： H02P21/05 , B64G1/28 , G01C19/30 , B64G1/36 , B64G1/24 , G01C21/18 , B64G1/38 , G01C19/06 , H02P27/08
摘要： Feedback control circuitry includes rate limiter circuitry configured to generate a rate limited position command based on a position command for a controlled component and based on a speed command for the controlled component. The feedback control circuitry also includes error adjustment circuitry configured to apply a control gain to an error signal to generate an adjusted error signal. The error signal is based on position feedback and the rate limited position command, and the position feedback indicates a position of the controlled component. The feedback control circuitry further includes an output terminal configured to output a current command generated based on the adjusted error signal.
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公开(公告)号：US20200002029A1
公开(公告)日：2020-01-02
申请号：US16570277
申请日：2019-09-13
发明人： Luc-Olivier GONIDOU
摘要： A method for determining, by reanalysis, a vibratory environment of a coupled vehicle/passenger system. A vehicle is subjected to external forces Fext and is coupled to a new passenger including multiple payloads (e.g., x=I, . . . N payload(s)). At the level of vehicle/passenger interfaces Ix, the method comprising a step DET1) for determining, based on reference interfacial acceleration γx_ref of a reference passenger, the interfacial acceleration γx′ relative to the new passenger.
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公开(公告)号：US09234561B2
公开(公告)日：2016-01-12
申请号：US13988844
申请日：2011-11-22
申请人： Philippe Laurens
发明人： Philippe Laurens
CPC分类号： F16F15/08 , B64G1/38 , B64G1/641 , B64G1/66 , B64G2001/228
摘要： A vibration isolation device designed to be positioned between a structure (10) and an equipment anchor plate (11), includes a lattice made of bars, with each bar including at least one axial actuator (25), the lattice being an active hexapod including six identical isolation bars (12) positioned according to a regular geometry, the six bars (12) being arranged such that the control of the tension-compression forces in each of the six bars (12) makes possible the force and torque control of six separate degrees of freedom at the interface between the structure and the equipment, so as to produce effective isolation along all the system's degrees of freedom. At least one end-fitting of each bar consists of an element (16) made of elastomeric material (called “elastomeric element”).
摘要翻译： 设计成定位在结构（10）和设备锚板（11）之间的隔振装置包括由杆构成的格子，每个杆包括至少一个轴向致动器（25），该格子是活动六足体，包括 根据规则几何形状定位的六个相同的隔离杆（12），六个杆（12）被布置成使得六个杆（12）中的每一个中的张力 - 压缩力的控制使得六个 在结构和设备之间的界面上分开的自由度，以便在所有系统的自由度上产生有效的隔离。 每个杆的至少一个端部配件由弹性体材料（称为“弹性体元件”）制成的元件（16）组成。
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公开(公告)号：US08620496B2
公开(公告)日：2013-12-31
申请号：US12178440
申请日：2008-07-23
申请人： Dan Y. Liu , Qinghong W. Wang , Richard Y. Chiang
发明人： Dan Y. Liu , Qinghong W. Wang , Richard Y. Chiang
CPC分类号： B64G1/281 , B64G1/283 , B64G1/285 , B64G1/286 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/366 , B64G1/38 , G05D1/0883
摘要： A system for damping nutation and removing wobble of a spacecraft spinning about a given axis is provided. The system includes a sensor configured to determine three dimensional attitude measurements of the spacecraft, a processor operatively coupled to the sensor and configured to execute a process that facilitates aligning the spin axis with a spacecraft momentum vector. The processor, when executing the process, is programmed to receive spacecraft attitude data from the sensor, determine a torque command using the received attitude data, and control a momentum storage actuator on the spacecraft using the determined torque command such that an angular deviation about the given axis is reduced.
摘要翻译： 提供了一种用于阻尼章动和消除围绕给定轴线旋转的航天器摆动的系统。 该系统包括被配置为确定航天器的三维姿态测量的传感器，可操作地耦合到传感器并被配置为执行有利于使旋转轴与航天器动量向量对准的过程的处理器。 处理器在执行该过程时被编程为从传感器接收航天器姿态数据，使用接收的姿态数据确定扭矩指令，并且使用所确定的扭矩命令来控制航天器上的动量存储致动器，使得围绕 给定轴减少。
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公开(公告)号：US20130299669A1
公开(公告)日：2013-11-14
申请号：US13988844
申请日：2011-11-22
申请人： Philippe Laurens
发明人： Philippe Laurens
CPC分类号： F16F15/08 , B64G1/38 , B64G1/641 , B64G1/66 , B64G2001/228
摘要： A vibration isolation device designed to be positioned between a structure (10) and an equipment anchor plate (11), includes a lattice made of bars, with each bar including at least one axial actuator (25), the lattice being an active hexapod including six identical isolation bars (12) positioned according to a regular geometry, the six bars (12) being arranged such that the control of the tension-compression forces in each of the six bars (12) makes possible the force and torque control of six separate degrees of freedom at the interface between the structure and the equipment, so as to produce effective isolation along all the system's degrees of freedom. At least one end-fitting of each bar consists of an element (16) made of elastomeric material (called “elastomeric element”).
摘要翻译： 设计成定位在结构（10）和设备锚板（11）之间的隔振装置包括由杆构成的格子，每个杆包括至少一个轴向致动器（25），该格子是活性六足体，包括 根据规则几何形状定位的六个相同的隔离杆（12），六个杆（12）被布置成使得六个杆（12）中的每一个中的张力 - 压缩力的控制使得六个 在结构和设备之间的界面上分开的自由度，以便在所有系统的自由度上产生有效的隔离。 每个杆的至少一个端部配件由弹性体材料（称为“弹性体元件”）制成的元件（16）组成。
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7.发明申请公开(公告)号：US20090152402A1
公开(公告)日：2009-06-18
申请号：US11587007
申请日：2005-04-15
申请人： Didier Massonnet
发明人： Didier Massonnet
IPC分类号： B64G1/10 , B64G1/64 , B64G1/38 , H01L31/042 , H01L31/052
CPC分类号： B64G1/222 , B64G1/1021 , B64G1/1085 , B64G1/34
摘要： The invention concerns an observation satellite (1) which is intended to be placed in orbit around a celestial body (2), and which comprises a reflecting device (5), a receiving device (6), a linking mechanical system (19), the whole forming a capture system (3) which is suitable to be able to orient the capture system (3) by gravity gradient in an aiming position in which the electromagnetic radiation corresponding to the information to be captured is received.The invention extends to an observation method and a fleet of such satellites (1).
摘要翻译： 本发明涉及一种旨在围绕天体（2）放置在轨道上的观测卫星（1），其包括反射装置（5），接收装置（6），连接机械系统（19）， 整体形成捕获系统（3），其适于能够通过重力梯度在捕获对应于要捕获的信息的电磁辐射的瞄准位置中定向捕获系统（3）。 本发明延伸到这种卫星的观察方法和舰队（1）。
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8.发明申请Unified sensor-based attitude determination and control for spacecraft operations 审中-公开统一的基于传感器的姿态测定与控制公开(公告)号：US20050133670A1
公开(公告)日：2005-06-23
申请号：US10727764
申请日：2003-12-03
申请人： H. Wang , Rongsheng Li
发明人： H. Wang , Rongsheng Li
IPC分类号： B64G1/00 , B64G1/24 , B64G1/26 , B64G1/28 , B64G1/36 , B64G1/40 , B64G1/44 , G01C21/02 , G05D1/08 , B64G1/38
CPC分类号： G01C21/025 , B64G1/007 , B64G1/242 , B64G1/244 , B64G1/26 , B64G1/283 , B64G1/288 , B64G1/361 , B64G1/401 , B64G1/405 , B64G1/443
摘要： Systems and method of attitude determination and control for spacecraft include the use of a unified set of sensors for all phases of space flight. For example, the same set of sensors may be used for on-station operations and transfer orbit operations. The use of a unified set of sensors reduces complexity, spacecraft cost, and spacecraft weight.
摘要翻译： 航天器姿态确定与控制的系统和方法包括在空间飞行的所有阶段使用一套统一的传感器。 例如，同一套传感器可用于车载操作和转移轨道操作。 使用统一的传感器可以降低复杂性，航天器成本和飞船重量。
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9.发明授权Wobble and nutation control, and spin stabilization for a spacecraft using momentum conserving devices 失效摇摆和章动控制，以及使用动量守恒装置的航天器的自旋稳定
公开(公告)号：US6062512A
公开(公告)日：2000-05-16
申请号：US921752
申请日：1997-08-27
摘要： A method of damping nutation and removing wobble of a spacecraft provided with first and second momentum sources having linearly independent momentum components in the plane transverse to the given axis. The method includes sensing angular velocities of the spacecraft along orthogonal first and second axes in the transverse plane, and generating velocity signals representative of the angular velocities. The velocity signals are processed to form control signals representative of desired torques for driving the momentum sources. The desired torques have a first additive component proportional to the angular velocities for removing the wobble and a second additive component proportional to the first derivatives of the angular velocities for damping the nutation.
摘要翻译： 一种阻尼章动和去除摆放在具有在垂直于给定轴线的平面中的具有线性独立的动量分量的第一和第二动量源的航天器的摆动的方法。 该方法包括：沿横向平面中的正交第一和第二轴检测航天器的角速度，以及产生代表角速度的速度信号。 处理速度信号以形成表示用于驱动动量源的期望转矩的控制信号。 期望的扭矩具有与用于移除摆动的角速度成比例的第一添加剂组分和与用于阻尼章动的角速度的一阶导数成比例的第二添加剂组分。
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10.发明授权Mechanism for mounting and actuating a momentum wheel with high vibration isolation 失效安装和启动具有高隔振性能的动量轮的机构
公开(公告)号：US5820079A
公开(公告)日：1998-10-13
申请号：US843115
申请日：1997-04-24
申请人： John P. Harrell
发明人： John P. Harrell
摘要： An apparatus for mounting a momentum wheel assembly (10) to a spacecraft (54). The momentum wheel assembly (10) includes a momentum wheel which has a primary spin axis coinciding with the primary spin axis of the spacecraft and spins in a direction opposite that of the spacecraft (54). Suspension isolation struts (20) attach the momentum wheel assembly (10) to the spacecraft (54) and provide substantial vibration isolation between the spacecraft (54) and the momentum wheel assembly (10). Voice coil actuators (40) attach to an adaptor ring (14) which in turn attaches to the spacecraft (54). The voice coil actuators (40) magnetically interact with a magnetically conductive element (42) attached to the momentum wheel assembly case (12). Interaction between the voice coil actuators (40) and the magnetic element (42) provides forces which displace the momentum wheel assembly case (12) in two axes orthogonal to the primary spin axis.
摘要翻译： 一种用于将动量轮组件（10）安装到航天器（54）的装置。 动量轮组件（10）包括动量轮，其具有与航天器的主旋转轴线重合的主旋转轴线，并沿与航天器（54）相反的方向旋转。 悬挂隔离支柱（20）将动量轮组件（10）附接到航天器（54）并且在航天器（54）和动量轮组件（10）之间提供实质性的隔振。 音圈致动器（40）附接到适配器环（14），转接环又附接到航天器（54）。 音圈致动器（40）与附接到动量轮组件壳体（12）的导磁元件（42）磁性地相互作用。 音圈致动器（40）和磁性元件（42）之间的相互作用提供了使力矩轮组件壳体（12）在与主旋转轴线正交的两个轴线上移动的力。
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