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1.发明授权Commande d'actionneur réduisant le niveau de vibrations d'une structure flexible associée 有权控制致动器以减少相关联的柔性结构的振动水平
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2.发明公开Rotation stabilizing device in a microgravitational rotating apparatus 审中-公开德米尼克斯·德雷肯德德·阿巴拉特（Drehungsstabilisierungsvorrichtung in einem）
公开(公告)号：EP1239353A3
公开(公告)日：2004-12-15
申请号：EP02005441.7
申请日：2002-03-08
发明人： Kawasaki, Shuichi
摘要： A rotation stabilizing device in a microgravitational rotating apparatus is provided by which vibration is suppressed and rotation is stabilized. Recess portions 10a, 10b are provided on a casing 10 so that bearings 14, 15 are arranged therein for supporting a rotary shaft 30. Experimental boxes 17a to 17h fixed to arms 16a to 16b rotate together with the rotary shaft 30. A fin 33 is fixed to outer circumferential surfaces of the experimental boxes 17a to 17b projecting outwardly therefrom. Pairs of electromagnetic coils 31a, 31b, in which the fin 33 is interposed with a predetermined gap maintained therebetween, and gap sensors 32 close thereto are fitted on the casing 10 side. Displacement of the fin 33 is detected by the gap sensors 32 to be inputted into a control unit to thereby control exciting current of the electromagnetic coils 31a, 31b. The gap is brought into the position within a demand value and rotation is stabilized.
摘要翻译： 提供了一种微重力旋转装置中的旋转稳定装置，通过该旋转稳定装置抑制振动并使旋转稳定。 凹部10a，10b设置在壳体10上，使得轴承14,15布置在其中用于支撑旋转轴30.固定到臂16a至16b的实验盒17a至17h与旋转轴30一起旋转。翅片33是 固定在从其向外突出的实验箱17a至17b的外圆周表面上。 一对电磁线圈31a，31b，其中翅片33以其间保持预定间隙插入，并且靠近其的间隙传感器32安装在壳体10侧。 翅片33的位移由间隙传感器32检测到输入到控制单元中，从而控制电磁线圈31a，31b的励磁电流。 间隙进入需求值的位置，并且旋转稳定。
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公开(公告)号：EP1249395A1
公开(公告)日：2002-10-16
申请号：EP01981093.6
申请日：2001-11-13
摘要： A substance mass measuring system is applied to a microgravitational rotating apparatus vibration control system to easily measure a mass of an object placed in an experimental box. Recess portions (10a, 10b) are provided in a casing (10). Both ends of a rotary shaft (30) are supported by bearings (11, 12) in the recess portions (10a, 10b). A lower end of the rotary shaft (30) is connected to a motor(13). Four arms (24 to 27), arranged horizontally in the direction of X and Y axes, are at their one ends fixed to the rotary shaft (30) and at the other ends fitted with experimental boxes (20 to 23). Experimental objects, such as plants or animals, are placed in the boxes (20 to 23) and rotated for experiments in the space. Vibration of the rotary shaft (30) and the boxes (20 to 23) is absorbed by the bearings (11, 12). Side plates (1a to 1d), acceleration sensors (2a to 2d) and distance sensors (3a to 3d) are arranged in the boxes (20 to 23). By collision of the object with the side plate, mass of the object is computed based on signals from the sensors (2, 3).
摘要翻译： 旋转轴（30）在壳体（10）的相对侧的凹部（10a，10b）中由轴承（11,12）支撑。 轴（30）的下端与电动机连接，四个臂（24-27）固定在X和Y轴上的水平方向上，诸如箱子的容器被固定在该水平方向上。 植物，动物等放在随后转动的箱子中。 来自轴和箱体的振动通过轴承吸收。 侧板（1a-1D），加速度传感器（2a-2d）和距离传感器（3a-3d）布置在盒子中，并确定盒子中的物体在与侧板碰撞时的质量。
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公开(公告)号：EP0788045B1
公开(公告)日：1999-12-15
申请号：EP97300676.0
申请日：1997-02-04
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公开(公告)号：EP0675825B1
公开(公告)日：1997-11-26
申请号：EP94905452.2
申请日：1993-12-20
CPC分类号： F41G7/222 , B64G1/28 , B64G1/281 , B64G1/366 , B64G1/38 , F16F15/02 , F41G7/2213 , Y10T74/1257
摘要： A nutational motion damper includes a damping body (30) positioned and constrained by springs (40) to slide on a guide plate (34) having a surface oriented substantially perpendicular to the axis of rotation of a gyroscopic body (22) by opposed spring members. The guide plate (34) is attached to a relatively non-rotating body coupled to the rotating gyroscopic body (22) to follow nutational motion. The springs (40) define a rest position for the damping mass on the axis of rotation and also urge the damping body against the guide plate.
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6.发明公开Vibration detection and reduction system and vibration sensors for use in micro-gravity environment 失效用于微型环境的振动检测和还原系统和振动传感器
公开(公告)号：EP0569994A3
公开(公告)日：1993-12-29
申请号：EP93107839.8
申请日：1993-05-13
CPC分类号： G01H9/00 , B64G1/22 , B64G1/36 , B64G1/38 , G01P15/093 , G01P15/18 , G05D19/02 , G10K11/178 , G10K2210/129 , G10K2210/3025 , G10K2210/3029 , G10K2210/3038 , G10K2210/3212 , G10K2210/501
摘要： The object of the invention is to make it possible to detect vibrations which would destroy a micro-gravity environment, to grasp factors of the vibrations, to detect and grasp a position and a scale of meteoroid/debris collisions, and to establish a counter-measure. Vibration sensors 2 are disposed in a matrix array on a vibrating body 1 placed in a micro-gravity environment, and the vibration data are collected and fed to a computer 5. The computer 5 analyzes a spectrum of the vibration, in a neural network section a vibration source is specified on the basis of the analyzed spectra, in a fuzzy control section, actuators 6 are driven so as to reduce harmful vibrations in response to the vibration energy and the energy source specified by the neural network section, and if necessary, a vibration factor is eliminated. The computer 5 takes in the result of driving for the actuators 6, the results are learnt in the neural network section and in the fuzzy control section to be ready for generation of vibrations at the next time. The vibration sensor 2 comprises a reflector or a transparent refractor disposed as floating in a micro-gravity space, output means fixed to the vibrating body for emitting energy towards the reflector or transparent refractor, and a receiver fixed to the vibrating body for receiving energy sent from the reflector or transparent refractor and measuring the nature of vibrations of the vibrating body on the basis of movement of the reflected or permeated energy.
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7.发明公开Vibration detection and reduction system and vibration sensors for use in micro-gravity environment 失效Schwingungsfeststellungs- und Verringerungssystem und Schwingungssensoren zum Gebrauch in einem Mikrogravitationsbereich。
公开(公告)号：EP0569994A2
公开(公告)日：1993-11-18
申请号：EP93107839.8
申请日：1993-05-13
CPC分类号： G01H9/00 , B64G1/22 , B64G1/36 , B64G1/38 , G01P15/093 , G01P15/18 , G05D19/02 , G10K11/178 , G10K2210/129 , G10K2210/3025 , G10K2210/3029 , G10K2210/3038 , G10K2210/3212 , G10K2210/501
摘要： The object of the invention is to make it possible to detect vibrations which would destroy a micro-gravity environment, to grasp factors of the vibrations, to detect and grasp a position and a scale of meteoroid/debris collisions, and to establish a counter-measure.
Vibration sensors 2 are disposed in a matrix array on a vibrating body 1 placed in a micro-gravity environment, and the vibration data are collected and fed to a computer 5. The computer 5 analyzes a spectrum of the vibration, in a neural network section a vibration source is specified on the basis of the analyzed spectra, in a fuzzy control section, actuators 6 are driven so as to reduce harmful vibrations in response to the vibration energy and the energy source specified by the neural network section, and if necessary, a vibration factor is eliminated. The computer 5 takes in the result of driving for the actuators 6, the results are learnt in the neural network section and in the fuzzy control section to be ready for generation of vibrations at the next time. The vibration sensor 2 comprises a reflector or a transparent refractor disposed as floating in a micro-gravity space, output means fixed to the vibrating body for emitting energy towards the reflector or transparent refractor, and a receiver fixed to the vibrating body for receiving energy sent from the reflector or transparent refractor and measuring the nature of vibrations of the vibrating body on the basis of movement of the reflected or permeated energy.摘要翻译： 本发明的目的是使得可以检测将破坏微重力环境的振动，掌握振动的因素，检测和掌握流星体/碎片碰撞的位置和规模，并建立反 - 测量。 振动传感器2以放置在微重力环境中的振动体1为矩阵阵列配置，振动数据被收集并送入计算机5.计算机5在神经网络部分中分析振动频谱 基于分析的光谱来指定振动源，在模糊控制部中，致动器6被驱动以响应于由神经网络部分指定的振动能量和能量源来减少有害振动，并且如果需要， 消除振动因子。 计算机5获取致动器6的驱动结果，结果在神经网络部分和模糊控制部分中被学习以准备在下一次产生振动。 振动传感器2包括设置为浮动在微重力空间中的反射器或透明折射器，固定到振动体的输出装置，用于向反射器或透明折射器发射能量，以及固定到振动体的接收器，用于接收能量发送 从反射器或透明折射器，并基于反射或渗透能量的运动来测量振动体的振动性质。
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8.发明公开Essentially passive method for inverting the orientation of a dual spin spacecraft 失效用于反转双纺丝航天器的取向方向实质上是被动的方法。
公开(公告)号：EP0441205A1
公开(公告)日：1991-08-14
申请号：EP91101002.3
申请日：1991-01-25
发明人： Fong, Herbert S.
摘要： An essentially passive and "fuel-less" method for inverting the orientation of a preferably nutationally stable, dual spin spacecraft (10) disposed in an inclined orbit, includes the steps of increasing the rotational speed of (i.e., "spinning up") the spacecraft's despun platform (20) and decreasing the rotational speed of (i.e., "spinning down") the spacecraft's rotor (16), to thereby generate, via product of inertia coupling, a transverse torque of sufficient magnitude to temporarily destabilize the spacecraft and cause the spacecraft spin axis (12), which is the minimum moment of inertia axis of the spacecraft, to diverge and precess through a flat spin orientation and towards a final, inverted orientation, e.g., disposed at a precession angle of 180° relative to the initial orientation of the spacecraft spin axis. Normally, prior to the spacecraft spin axis reaching the final, inverted orientation, the spin axis encounters and is "stuck at" a barrier nutation angle beyond which further precession of the spacecraft spin axis is not possible without the implementation of a final acquisition procedure, which includes the steps of detecting the occurrence of the spin axis reaching the barrier nutation angle, and in response thereto, instituting limit cycle rotational motion of the platform, to thereby render non-secular the rotational motion of the platform, whereby the spacecraft damping system is brought into its pull-in or effective operating range for penetrating the barrier nutation angle, in order to achieve acquisition of the final inverted orientation of the spacecraft spin axis. Limit cycle rotation of the platform is preferably effectuated by means of applying a first and a second series of torquing pulses to the spacecraft despin motor suitable for reducing the rotational speed of the platform, the first series of pulses being of larger magnitude than that of the second series of pulses.
摘要翻译： 在倾斜轨道上，包括增加的旋转速度的步骤（即，“起转”），以从本质上被动和“燃料少”用于反相优选nutationally稳定，双自旋太空船（10）的取向的方法设置在所述 航天器的消旋平台（20），并通过惯性耦合的产物减少的（即，“停转”）的航天器的转子（16），以由此生成，转速，足够大小的横向转矩暂时破坏飞船和原因 太空船旋转轴（12），所有这些是航天器的惯性轴线的最小力矩，发散并通过扁平自旋方向并朝向最终，反向取向，例如，在相对于180°的旋进角处理完毕进动 飞船自旋轴的初始取向。 通常情况下，之前的航天器自旋轴达到最终，倒置取向中，自旋轴相遇并且“胶着”的阻挡章动角超过该航天器自旋轴的进一步旋进是不可能的，而不最终获取过程的执行情况， 其包括检测所述旋转轴到达屏障章动角的发生的步骤，并且响应于此，实行所述平台的极限周期旋转运动，从而使非世俗的平台，其中所述宇宙飞船阻尼系统的旋转运动 进入其拉入或有效操作范围为穿透屏障章动角，以达到获取飞船自旋轴的最终反向取向的。 所述平台的极限周期旋转优选通过将一个第一和一个第二系列将扭矩脉冲到航天器Despin马达适于减小所述平台的旋转速度，所述第一系列的脉冲是比的较大幅值的手段effectuated 脉冲secondSeries。
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9.发明授权
公开(公告)号：EP0057138B1
公开(公告)日：1986-07-30
申请号：EP82400111.9
申请日：1982-01-21
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公开(公告)号：EP3983297A1
公开(公告)日：2022-04-20
申请号：EP20827109.8
申请日：2020-01-31
发明人： VEDANT , ALLISON, James, T.
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