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1.发明公开Nutation damper system comprising a control member for varying a natural frequency of a pendulum 失效包含控制构件的调整阻尼器系统改变一个PENDULUM的自然频率
公开(公告)号：EP0091811A3
公开(公告)日：1985-01-09
申请号：EP83302022
申请日：1983-04-11
申请人： NEC CORPORATION
CPC分类号： B64G1/24 , B64G1/32 , G05D1/0883
摘要： In a nutation damper system comprising a pendulum (30, 33, 34, 38) swingable at a natural fequency and a block element (35) operable in cooperation with the pendulum to damp nutation having a nutation frequency, a control member (40) is electromagnetically coupled to the pendulum to vary the natural frequency to a forced frequency substantially equal to the nutation frequency. The control member comprises an electromagnetic coil supplied as a control signal with an electric current produced by a control signal circuit and proportional to a square of the nutation frequency. The block element may comprise either a permanent magnet or an electromagnet when a pendulum weight of the pendulum is of an electrical conductor. The electromagnet may intermittently be energized by a power source circuit. Alternatively, the block element may be of an electrical conductor when the pendulum weight is of a permanent magnet.
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公开(公告)号：EP0090914A3
公开(公告)日：1985-01-09
申请号：EP83100699
申请日：1983-03-23
申请人： DORNIER SYSTEM GmbH
CPC分类号： G05D1/0883 , B64G1/24 , B64G1/281
摘要： Verfahren zur Lageänderung der Spinachse eines drall stabilisierten Satelliten mittels kurzer Pulse, wobei zwei Lagekorrekturdüsen (12, 14), die so am Satelliten (-Rotor) (10) befestigt sind, dass sie in einem körperfesten Koordina tensystem entgegengesetzte Drehmomente erzeugen, ein oder mehrere Pulspaare erzeugen, und jeweils der Puls aus der zweiten Düse (14) eine halbe Umdrehungszeit nach dem Puls aus der ersten Düse (12) gegeben wird.
摘要翻译： 用于通过短脉冲改变自旋稳定卫星的自旋轴的姿态的方法，两个姿态校正喷嘴（12,14），其以这样的方式附接到卫星（转子）（10），使得它们产生 扭矩与身体固定的坐标系相对，产生一个或多个脉冲对，并且在每种情况下，来自第二喷嘴（14）的脉冲在来自第一喷嘴（12）的脉冲之后被给予一个半转周期。
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公开(公告)号：EP0195553A3
公开(公告)日：1987-09-16
申请号：EP86301554
申请日：1986-03-05
摘要： A spacecraft (20) is adapted for orbital flight in two alternative modes, referred to as the earth-oriented and quasi sun-oriented modes. The spacecraft comprises a spacecraft body (21), at least one solar array (44, 46) extendible outwardly from the spacecraft body, passive attitude control means (58) utilizing gravity gradient stabilization means which is extendible and retractable relative to the spacecraft body (21), and active attitude control means (69, 71). The gravity gradient stabilization means (58) is effective when extended to stabilize the spacecraft in the earth-oriented mode, and the active attitude (69, 71) control means is effective to stabilize the spacecraft in the quasi sun-oriented mode.
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公开(公告)号：EP0101302A3
公开(公告)日：1985-07-31
申请号：EP83304644
申请日：1983-08-11
CPC分类号： B64G1/24 , B64G1/285 , B64G1/36 , G05D1/0883
摘要： A digital system for controlling the attitude of a spacecraft (14), e.g., a satellite, with respect to three orthogonal axes. The system can control satellites (14) in parking orbit, transfer orbit, or final operational orbit, whether or not the satellite (14) employs one or more momentum wheels. A processor (2) converts weighted data from spacecraft sensors (12), representing angular orientation and angular velocities about each of the three axes, into thruster pulsetrain signatures to command the firing of each of six thrusters positioned about spacecraft (14). A positive and a negative thruster being positioned to impart both directions of angular momentum about each of the three axes. Each thruster pulsetrain signature is created once every processed error cycle period T1, and contains a varying number of pulses of varying widths. A negative feedback PWPF loop (2, 16, 20, 22, 24) is actuated for each of the three axes, preferably several times each Tl inorder to achieve better thrust on/off resolution. The PWPF loops are preferably implemented by digital means. Serial-out shift registers (44, 46) load the thruster pulsetrain signatures into means (48, 50, 52, 54) for firing the thrusters, preferably after splitting the signature pulses into clone pulses in order to minimize the impact of errors due to asynchronization between the clock which loads the registers (44, 46) and the clock which shifts these registers. Data extenders (40, 42) eliminate possible gaps caused by asynchronization, and thus prevent unwanted on/off thruster switching.
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