公开(公告)号：US06804986B2

公开(公告)日：2004-10-19

申请号：US09847268

申请日：2001-05-02

申请人： Christian Patouraux

发明人： Christian Patouraux

IPC分类号： G01C1738

CPC分类号： G01C21/24 ,  B64G1/24 ,  B64G1/285 ,  B64G1/288 ,  B64G1/365 ,  B64G2001/245

摘要： The method according to the invention allows to determine the yaw angle of a satellite from the reading of two different sensors measuring the roll and/or pitch angles, provided that the reference point of the two sensors are not identical. A description is given basically for geostationary satellites but the method can be applied directly to satellites which are stationary with respect to any star. The method can be employed for circular and non-circular orbits.

摘要翻译： 根据本发明的方法允许从测量辊和/或俯仰角的两个不同传感器的读数来确定卫星的偏航角，只要两个传感器的参考点不相同即可。 基本上给出了对地静止卫星的描述，但该方法可以直接应用于相对于任何恒星静止的卫星。 该方法可用于圆形和非圆形轨道。

公开(公告)号：US06561462B1

公开(公告)日：2003-05-13

申请号：US10081468

申请日：2002-02-21

申请人： Hanching G. Wang ,  Umesh Ketkar ,  Albert A. Munoz ,  Sadek Mansour

发明人： Hanching G. Wang ,  Umesh Ketkar ,  Albert A. Munoz ,  Sadek Mansour

IPC分类号： B64G136

CPC分类号： B64G1/363 ,  B64G2001/245

摘要： A spacecraft power/sun acquisition method includes a pitch search phase in which the spacecraft is rotated about a pitch axis, stopped, quaternions reset to remember position, and yaw search phase is entered when a first TOA occurs from a first slit sun sensor, and a keyhole slew is performed when the first TOA does not occur. The method also includes yaw search phase in which a keyhole slew is performed by rotating the spacecraft about a yaw axis, stopping the spacecraft, and entering pitch search phase when the first TOA does not occur, and in which the spacecraft is rotated about a yaw axis, stopped, quaternions reset, and sun hold phase is entered when a second TOA occurs from a second slit sun sensor. Lastly, the method includes a sun hold phase in which the spacecraft is oriented to the sun and placed in spin at power safe attitude.

摘要翻译： 航天器功率/太阳采集方法包括：俯仰搜索阶段，其中航天器围绕俯仰轴线旋转，停止，四元数复位为记忆位置，并且当第一狭缝太阳传感器发生第一TOA时进入偏航搜索阶段，以及 当不发生第一个TOA时执行锁孔旋转。 该方法还包括偏航搜索阶段，其中通过围绕偏转轴旋转航天器，停止航天器并且当第一TOA不发生时进入俯仰搜索阶段执行锁孔，并且其中航天器围绕偏航旋转 轴，停止，四元数复位，并且当从第二狭缝太阳传感器发生第二TOA时进入太阳保持相位。 最后，该方法包括太阳保持阶段，其中航天器被定向到太阳并以功率安全的姿态旋转。

公开(公告)号：US20020116993A1

公开(公告)日：2002-08-29

申请号：US09847268

申请日：2001-05-02

发明人： Christian Patouraux

IPC分类号： G01C021/00

CPC分类号： G01C21/24 ,  B64G1/24 ,  B64G1/285 ,  B64G1/288 ,  B64G1/365 ,  B64G2001/245

摘要： The method according to the invention allows to determine the yaw angle of a satellite from the reading of two different sensors measuring the roll and/or pitch angles, provided that the reference point of the two sensors are not identical. A description is given basically for geostationary satellites but the method can be applied directly to satellites which are stationary with respect to any star. The method can be employed for circular and non-circular orbits.

摘要翻译： 根据本发明的方法允许从测量辊和/或俯仰角的两个不同传感器的读数来确定卫星的偏航角，只要两个传感器的参考点不相同即可。 基本上给出了对地静止卫星的描述，但该方法可以直接应用于相对于任何恒星静止的卫星。 该方法可用于圆形和非圆形轨道。

公开(公告)号：US06441776B1

公开(公告)日：2002-08-27

申请号：US09479701

申请日：2000-01-07

申请人： Douglas H. Hein ,  Rongsheng Li

发明人： Douglas H. Hein ,  Rongsheng Li

IPC分类号： G01S502

CPC分类号： B64G1/242 ,  B64G1/24 ,  B64G1/26 ,  B64G1/288 ,  B64G1/36 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  B64G2001/245 ,  G01S19/53

摘要： A method, apparatus, and article of manufacture for directing a payload coupled to a spacecraft substantially at a target location is disclosed. The method comprises the steps of determining spacecraft orbital parameters and spacecraft payload attitude parameters; and directing the payload at the target location by applying a spacecraft bus steering law determined at least in part from the orbit and attitude parameters. The apparatus comprises a navigation system for determining spacecraft orbit parameters and spacecraft attitude parameters, and for applying a spacecraft bus steering law to direct the payload substantially at the target location. The spacecraft bus steering law is determined at least in part from the determined spacecraft orbital parameters, the determined spacecraft attitude, and determined payload attitude parameters. In one embodiment, the apparatus includes a payload attitude control system for directing the payload relative to the spacecraft bus. The article of manufacture comprises a program storage device tangibly embodying a series of instruction for performing the above method steps.

摘要翻译： 公开了一种用于引导耦合到航天器的有效载荷基本上在目标位置处的方法，装置和制品。 该方法包括确定航天器轨道参数和航天器有效载荷姿态参数的步骤; 以及通过应用至少部分地从轨道和姿态参数确定的航天器总线导向法，将有效载荷指向目标位置。 该装置包括用于确定航天器轨道参数和航天器姿态参数的导航系统，以及用于应用航天器总线指导规则以将有效载荷基本上引导到目标位置。 至少部分地根据确定的航天器轨道参数，确定的航天器姿态和确定的有效载荷姿态参数来确定航天器总线导向规律。 在一个实施例中，该装置包括用于将有效载荷相对于航天器总线引导的载荷姿态控制系统。 该制品包括有形地体现用于执行上述方法步骤的一系列指令的程序存储装置。

公开(公告)号：US20020047072A1

公开(公告)日：2002-04-25

申请号：US09990265

申请日：2001-11-23

发明人： Theodore Garver

IPC分类号： B64C023/02

CPC分类号： B64G1/26 ,  B63B1/248 ,  B63H9/0607 ,  B63H25/40 ,  B64C23/08 ,  B64G1/244 ,  B64G2001/245 ,  Y02T70/583

摘要： The invention utilizes a computer-controlled moving band, typically on an airplane, to increase the apparent speed and therefore the lift of any body moving through a fluid. The invention will allow greater precision of control. One benefit is that take-offs and landings can be carried at reduced speeds and with greater loads. This control will also adjust boundary layer to reduce drag due to turbulence thereby allowing more flexibility in wing design.

摘要翻译： 本发明利用计算机控制的移动带，通常在飞机上，以增加表观速度，并因此增加移动通过流体的任何物体的升力。 本发明将允许更高的控制精度。 一个好处是起飞和着陆可以以较低的速度和更大的载荷进行。 该控制还将调整边界层以减少由于湍流引起的阻力，从而允许机翼设计中的更大灵活性。

公开(公告)号：US6019320A

公开(公告)日：2000-02-01

申请号：US153123

申请日：1998-09-15

申请人： Piyush R. Shah ,  Douglas J. Bender

发明人： Piyush R. Shah ,  Douglas J. Bender

IPC分类号： B64G1/24 ,  B64G1/28 ,  B64G1/36 ,  G05D1/08

CPC分类号： G05D1/0883 ,  B64G1/24 ,  B64G1/283 ,  B64G1/288 ,  B64G1/36 ,  B64G1/363 ,  B64G1/365 ,  B64G1/285 ,  B64G2001/245

摘要： A system and method for acquiring Sun pointing in a three-axis stabilized spacecraft including slewing at least one solar wing until the Sun is detected, determining an initial Sun vector, performing one or more rotations of the spacecraft body so as to bring the instantaneous Sun vector coincident with a preferred final Sun vector, at least one rotation about an optimal axis, and slewing at least one solar wing to a preferred attitude relative to the Sun. In one embodiment, the optimal axis is chosen so as to minimize the time required to achieve an optimal thermal attitude. In another embodiment, the optimal axis is chosen so as to minimize the time required to align the instantaneous Sun vector with the final desired Sun vector. In a further embodiment, the optimal axis is chosen so as to maintain Earth lock.

摘要翻译： 一种用于获取Sun指向三轴稳定的航天器的系统和方法，包括至少一个太阳翼的回转，直到检测到太阳，确定初始的太阳矢量，执行航天器主体的一个或多个旋转，以使瞬时的太阳 与优选的最后的Sun矢量重合的矢量，围绕最佳轴线至少一个旋转，并且将至少一个太阳翼旋转到相对于太阳的优选姿态。 在一个实施例中，选择最佳轴线以便最小化实现最佳热姿态所需的时间。 在另一个实施例中，选择最佳轴使得将瞬时的Sun矢量与最终期望的Sun矢量对准所需的时间最小化。 在另一个实施例中，选择最佳轴线以便保持接地锁定。

公开(公告)号：US5984237A

公开(公告)日：1999-11-16

申请号：US800720

申请日：1997-02-13

申请人： Neil Evan Goodzeit

发明人： Neil Evan Goodzeit

IPC分类号： B64G1/26 ,  G05D1/08 ,  B64G1/21

CPC分类号： G05D1/0883 ,  B64G1/26 ,  B64G2001/245

摘要： A three-axis stabilized spacecraft is subject to a velocity change in a desired direction by a thruster. Unavoidable alignment errors cause a body torque, which tends to slew the body away from the attitude which orients the thrust axis in the direction. The attitude control system eventually corrects the attitude, but the thrust during the attitude transient results in an error in the direction of the velocity change. This error in the direction accumulates during the attitude transient. When the attitude transient passes, no further pointing error occurs. A control system, operating without an accelerometer, determines the total error accumulated during the attitude transient, and processes the error signal to generate a supplemental torque demand signal, which is added to the torque demand signal produced by the attitude control system, to cause an oppositely-directed attitude transient to thereby cancel the original velocity change direction error.

摘要翻译： 三轴稳定的航天器通过推进器在所期望的方向上进行速度变化。 不可避免的对准错误导致体力矩，这倾向于使身体远离将推力轴朝向该方向的姿态。 姿态控制系统最终纠正姿态，但姿态瞬态中的推力会导致速度变化方向的误差。 在姿态瞬变期间，该方向的误差累积。 当姿态瞬变过去时，不会发生进一步的指示错误。 在没有加速度计的情况下操作的控制系统确定在姿态瞬变期间累积的总误差，并且处理误差信号以产生附加到由姿态控制系统产生的扭矩需求信号的补充扭矩需求信号， 反向导向的姿态瞬变，从而抵消原来的速度变化方向误差。

公开(公告)号：US5944761A

公开(公告)日：1999-08-31

申请号：US870743

申请日：1997-06-06

申请人： Christopher J. Heiberg

发明人： Christopher J. Heiberg

IPC分类号： B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/36 ,  G05D1/08 ,  G06F165/00

CPC分类号： G05D1/0883 ,  B64G1/24 ,  B64G1/28 ,  B64G1/36 ,  B64G1/26 ,  B64G1/283 ,  B64G1/286 ,  B64G1/288 ,  B64G2001/245

摘要： A filter for use in an attitude control system which may be subjected to vibrations from disturbances which have frequency contents that vary with time. Sensors on the system produce signals that contain the disturbance frequencies and a calculator connected to the source of disturbance produces a signal which varies as a function of the disturbance. The filter receives these signals and augments the control loop gain at the disturbance frequencies thereby enabling the attitude control devices to null the disturbance effects on the attitude of the system.

摘要翻译： 一种用于姿态控制系统中的过滤器，其可能受到具有频率内容随时间变化的干扰的振动。 系统上的传感器产生包含干扰频率的信号，连接到干扰源的计算器产生作为干扰的函数而变化的信号。 滤波器接收这些信号并增加扰动频率处的控制环路增益，从而使得姿态控制装置能够使对系统姿态的干扰影响失效。

公开(公告)号：US5806804A

公开(公告)日：1998-09-15

申请号：US748037

申请日：1996-11-12

申请人： Neil Evan Goodzeit ,  Santosh Ratan

发明人： Neil Evan Goodzeit ,  Santosh Ratan

IPC分类号： B64G1/26 ,  B64G1/36 ,  B64G1/38 ,  G05D1/08

CPC分类号： B64G1/38 ,  B64G1/26 ,  B64G1/36 ,  G05D1/0883 ,  B64G2001/245

摘要： A spacecraft (10) carries a solar panel (17) which rotates to follow the sun, and also carries various thrusters (20). Thruster plume impingement on the solar panel affects the torque applied to the spacecraft body (12) in a manner which depends upon solar panel angle. The errors in the thrust during stationkeeping tend to perturb attitude, especially early in the maneuver, because of the delay inherent in the attitude control loop. A torque bias is summed with the residual torque demand signal to correct for the errors in torque. The torque bias signal is generated by a Fourier model of the torques, updated by an adaptive tuning filter, so that successive stationkeeping maneuvers progressively adapt the amplitude and phase of the Fourier coefficients in a manner which tends to minimize the residual torque demand and attitude error. Thus, the torque bias signal automatically approaches the correct value.

摘要翻译： 航天器（10）携带太阳能电池板（17），其旋转以跟随太阳，并且还携带各种推进器（20）。 太阳能电池板上的推进器羽流撞击以取决于太阳能电池板角度的方式影响施加到航天器本体（12）的扭矩。 由于姿态控制回路固有的延迟，驻车期间的推力误差往往会扰乱姿态，特别是在机动的早期。 转矩偏差与剩余转矩需求信号相加，以纠正转矩误差。 转矩偏置信号由转矩的傅立叶模型产生，由自适应调谐滤波器更新，使得连续的驻停操作以倾向于最小化剩余转矩需求和姿态误差的方式逐渐适应傅里叶系数的幅度和相位 。 因此，转矩偏置信号自动接近正确的值。

公开(公告)号：US5799902A

公开(公告)日：1998-09-01

申请号：US900923

申请日：1997-07-28

申请人： Edward L. Keith ,  Thomas P. Bauer

发明人： Edward L. Keith ,  Thomas P. Bauer

IPC分类号： B64G1/00 ,  B64G1/24 ,  B64G1/26 ,  B64G1/40 ,  B64G1/64 ,  F02K9/76 ,  F02K9/80 ,  F42B15/36 ,  B64C15/02 ,  B64F1/10 ,  B64G1/42

CPC分类号： B64G1/26 ,  B64G1/002 ,  B64G1/242 ,  B64G1/401 ,  B64G1/641 ,  B64G1/645 ,  F02K9/766 ,  F02K9/80 ,  F42B15/36 ,  B64G2001/245

摘要： A low-cost, liquid-propellant rocket launch vehicle having a central pod that carries an optional final-stage rocket engine cluster, and having additional engine clusters arranged in diametrically opposed pairs of clusters. The pairs of clusters are burned and separated in a staging sequence until the final stage is reached. In the presently preferred embodiment, there are three pairs of engine clusters arranged in a hexagonal configuration about the central pod and each engine cluster contains seven identical engines. The engines are made from light-weight, low-cost materials, without gimbals or other moving parts. Steering of the vehicle is effected by differential control of the engine thrusts of selected engines, using duty-cycle modulation of a plurality of on/off propellant supply valves and, additionally, control of other on/off valves controlling the supply of an inert cryogenic fluid to secondary injection ports on the engine. An onboard gas generator provides inert gas for fluid pressurization and preferably uses as its principal reactant the same material used as the cryogenic fluid. Navigation is effected with inexpensive onboard systems and the entire vehicle provides a dramatic reduction in cost in comparison with conventional launch vehicles.

摘要翻译： 一种低成本的液体推进剂火箭运载火箭，其具有携带可选的最终级火箭发动机组的中央舱，并且具有排列成直径相对的一对群组的附加发动机集群。 这些群集在分段序列中燃烧和分离，直到达到最后阶段。 在目前优选的实施例中，有三对发动机组以六边形构型围绕中心舱排列，并且每个发动机组包含七个相同的发动机。 发动机由重量轻，成本低廉的材料制成，不需要万向节或其他运动部件。 车辆的转向是通过使用多个开/关推进剂供应阀的占空比调制来选择发动机的发动机推力的差速控制来实现的，另外控制另外的控制供应惰性低温的开关阀 流体到发动机上的二次注射口。 机载气体发生器提供用于流体加压的惰性气体，并且优选将其用作与低温流体相同的材料作为其主要反应物。 使用便宜的车载系统进行导航，与传统运载火箭相比，整个车辆显着降低了成本。