公开(公告)号：US20130154170A1

公开(公告)日：2013-06-20

申请号：US13331512

申请日：2011-12-20

申请人： Porter Davis ,  Steven Hadden ,  Pablo Bandera

发明人： Porter Davis ,  Steven Hadden ,  Pablo Bandera

IPC分类号： F16F15/04 ,  F16F3/00

CPC分类号： B64G1/641 ,  B64G2001/228

摘要： Embodiments of a low frequency isolation device are provided, as are embodiments of a spacecraft isolation system including a plurality of low frequency isolation devices. In one embodiment, the low frequency isolation device includes a three parameter isolator and a break frequency-reducing series spring mechanically coupled in series with the three parameter isolator and having a predetermined axial stiffness (KS AXIAL) and a predetermined lateral stiffness (KS LATERAL). The predetermined axial stiffness (KS AXIAL) of the break frequency-reducing series spring is less than the predetermined lateral stiffness (KS LATERAL) thereof.

摘要翻译： 提供低频隔离装置的实施例，如包括多个低频隔离装置的航天器隔离系统的实施例。 在一个实施例中，低频隔离装置包括三参数隔离器和与三参数隔离器串联的具有预定轴向刚度（KS AXIAL）和预定侧向刚度（KS LATERAL）的机械耦合的断路减频串联弹簧， 。 断裂减频串联弹簧的预定轴向刚度（KS AXIAL）小于其预定的横向刚度（KS LATERAL）。

公开(公告)号：US20060145026A1

公开(公告)日：2006-07-06

申请号：US10536929

申请日：2002-12-04

申请人： Miguel Lancho Doncel

发明人： Miguel Lancho Doncel

IPC分类号： B64G1/00

CPC分类号： F16F1/32 ,  B64G1/641 ,  B64G2001/228 ,  F16F1/366 ,  F16F1/371 ,  F16F1/3732 ,  F16F1/393 ,  F16F3/12 ,  F16F7/00 ,  F16F9/30 ,  F16F15/08 ,  F16F15/085

摘要： The attenuation device of the present invention comprises a surface of revolution (11) of circular cross section, such that a set of slots (14) is distributed between the sides of the surface of revolution (11) and adapted to confine an elastic material (15) within the limits defined by the slots (14), generating a structural labyrinth for load passage from a lower interface of the surface of revolution (11) to an upper interface.

摘要翻译： 本发明的衰减装置包括圆形横截面的旋转表面（11），使得一组槽（14）分布在旋转表面（11）的侧面之间并且适于限制弹性材料（ 15），在由槽（14）限定的限度内，产生用于从旋转表面（11）的下界面到上界面的负载通道的结构迷宫。

公开(公告)号：US06722614B2

公开(公告)日：2004-04-20

申请号：US10218461

申请日：2002-08-15

申请人： Takuo Ozawa ,  Tsuyoshi Ozaki

发明人： Takuo Ozawa ,  Tsuyoshi Ozaki

IPC分类号： B64G122

CPC分类号： B64G1/222 ,  B64G1/641 ,  B64G2001/228 ,  Y10S136/292

摘要： In a solar array paddle having panels which are connected to a main body of a satellite and rotatably connected to one another, elastic insertion members for prevention of vibration are disposed in a clearance between each of the panels and between the main body and the panel adjacent to the main body when the panels are housed, folded, and layered. Each of the insertion members for prevention of vibration is inserted into the clearances and between the main body of the satellite and the panels adjacent to the main body such that one surface contacts a first panel and the other surface is adhered to a second panel.

摘要翻译： 在具有连接到卫星的主体并彼此可旋转地连接的面板的太阳能阵列桨叶中，用于防止振动的弹性插入构件设置在每个面板之间以及主体与相邻的面板之间的间隙中 当面板被容纳，折叠和分层时，到主体。 用于防止振动的每个插入构件插入到卫星的主体和邻近主体的面板之间的间隙中，使得一个表面接触第一面板，另一个表面粘附到第二面板。

公开(公告)号：US06708928B2

公开(公告)日：2004-03-23

申请号：US10060439

申请日：2002-01-30

申请人： Kenneth N. Telford

发明人： Kenneth N. Telford

IPC分类号： B64G122

CPC分类号： B64G1/645 ,  B64G1/641 ,  B64G2001/228

摘要： A variable spacer includes a plate having a first surface and a second surface. At least one hole is integrally formed within the plate, extending from the first surface to the second surface. The hole receives a shaft of a separation bolt used for attaching a spacecraft to a launch vehicle. The plate increases a first load within the separation bolt to a second load during a turbulent stage. The second load reduces a gapping that occurs between the launch vehicle and the spacecraft. Thereafter, the plate reduces the second load within the separation bolt to a third load during a separation stage. The third load decreases a shock level experienced by the spacecraft and the launch vehicle.

摘要翻译： 可变间隔件包括具有第一表面和第二表面的板。 至少一个孔一体地形成在板内，从第一表面延伸到第二表面。 该孔容纳用于将航天器附接到运载火箭的分离螺栓的轴。 在湍流阶段，板将分离螺栓内的第一负载增加到第二负载。 第二个负载减少了在运载火箭和航天器之间发生的间隙。 此后，在分离阶段期间，板将分离螺栓内的第二负载减小到第三负载。 第三负载降低了航天器和运载火箭所经历的冲击水平。

公开(公告)号：US20040004161A1

公开(公告)日：2004-01-08

申请号：US10189860

申请日：2002-07-03

发明人： David A. Osterberg

IPC分类号： B64G001/28

CPC分类号： F16F15/022 ,  B64G1/641 ,  B64G1/645 ,  B64G2001/228 ,  F16C32/044 ,  F16C2326/47

摘要： A method and system for calculating a control function for a structural system (10) that can be used to determine an appropriate control force to apply to an active member (18) within a stationary member (12) on the structural system (10). An active member (18) and a stationary member (12) are defined as a two-mass system in which the active member (18) and the stationary member (12) move in opposite directions. The stationary member (12) is mounted to an isolation subsystem (14) that is composed of six isolators (28) at multiple degrees of freedom. The isolation subsystem (14) is softer than the stationary member (12), active member (18) and a spacecraft surface (16) due to a damping element (32) of the isolation subsystem (16). The isolation subsystem (16) is mounted to the spacecraft (16) and decouples the spacecraft (16) from the stationary member (12) and thus the active member (18). An accurate control force for the active member (18) can be determined based upon the above structure (10).

公开(公告)号：US06554228B2

公开(公告)日：2003-04-29

申请号：US09795221

申请日：2001-02-28

申请人： Michael J. Schoonmaker ,  George Sowers

发明人： Michael J. Schoonmaker ,  George Sowers

IPC分类号： B64G100

CPC分类号： B64G1/002 ,  B64G2001/228

摘要： An aerodynamic fairing which is mountable on a strap on solid rocket motor (SRM) is configured such that in flight aero-acoustic effects are significantly reduced with regard to the launch vehicle to which the SRM is mounted and other external apparatus. The aerodynamic fairing is configured to include a leading edge which is substantially flat and provides the forward intersection between the inboard and outboard sides of the fairing. On mounting the fairing and SRM to a launch vehicle, the inboard surface is closest to the launch vehicle while the outboard surface is further away. With regard to the aerodynamic fairing, the transition rearward from the leading edge to a base end, the inboard surface is initially flat and transitions to the cylindrical shape of the SRM. The outboard surface of the fairing is configured such that it has a profile of a canted ogive which extends from the leading edge and smoothly transitions to the cylindrical shape of the SRM at the base end.

公开(公告)号：US20030006341A1

公开(公告)日：2003-01-09

申请号：US09899600

申请日：2001-07-05

发明人： Daniel A. Buder

IPC分类号： B64C001/22

CPC分类号： F16F15/08 ,  B64G1/641 ,  B64G2001/228

摘要： A vibration isolator is provided that includes a plurality of elastomeric members. The vibration isolator includes a first support, a second support and at least one third support. The second support is spaced from the first support such that the first and second supports define at least one recess. The at least one third support is spaced from the first support such that the third support and the first support define at least one recess. The recesses between the first and second supports and the first and third supports are structured to at least partially receive at least one of the elastomeric members. The vibration isolator includes at least one fastener that is structured to mount the corresponding elastomeric members between the first and third supports and between the first and second supports such that elastomeric members damp vibration transmitted between the first and second supports.

公开(公告)号：US06494406B1

公开(公告)日：2002-12-17

申请号：US09466868

申请日：1999-12-20

申请人： Yukio Fukushima ,  Ryuzo Shimizu ,  Hiroshi Matsunaga ,  Yoshifumi Yasunaga ,  Yutaka Matsuda

发明人： Yukio Fukushima ,  Ryuzo Shimizu ,  Hiroshi Matsunaga ,  Yoshifumi Yasunaga ,  Yutaka Matsuda

IPC分类号： B64G110

CPC分类号： B64G1/645 ,  B64G1/002 ,  B64G1/641 ,  B64G2001/228

摘要： A rocket fairing mounted on a forward section of a rocket body included in a rocket comprises a first structure formed on the fairing-base side, and including a first side wall defining a first storage space for storing a first payload; and a second structure formed on the fairing-forward side, and including a second side wall defining a second storage space for storing a second payload. The first side wall has a plurality of first side wall segments capable of being separated from each other along a plane including the longitudinal axis of the fairing and of being turned away from the first payload when releasing the first payload from the first storage space. The second side wall has a plurality of second side wall segments capable of being separated from each other along a plane including the longitudinal axis of the fairing and of being turned away from the second payload when releasing the second payload from the second storage space.

摘要翻译： 安装在包括在火箭中的火箭主体的前部的火箭整流罩包括形成在整流罩底侧上的第一结构，并且包括限定用于存储第一有效载荷的第一存储空间的第一侧壁; 以及形成在整流罩侧的第二结构，并且包括限定用于存储第二有效载荷的第二存储空间的第二侧壁。 第一侧壁具有多个第一侧壁段，其能够沿着包括整流罩的纵向轴线的平面彼此分离，并且在从第一存储空间释放第一有效载荷时被转向远离第一有效载荷。 第二侧壁具有多个第二侧壁段，其能够沿着包括整流罩的纵向轴线的平面彼此分离，并且在从第二存储空间释放第二有效载荷时将其从第二载荷转回。

公开(公告)号：US06371412B1

公开(公告)日：2002-04-16

申请号：US09438713

申请日：1999-11-11

申请人： David A. Osterberg

发明人： David A. Osterberg

IPC分类号： B64G110

CPC分类号： G10K11/16 ,  B64G1/002 ,  B64G1/641 ,  B64G2001/228

摘要： An acoustic vibration isolator for use in preventing damage to a payload connected to a launch vehicle by removing the air around the payload so that acoustic vibrations do not have a medium to travel through to reach the payload.

摘要翻译： 一种声学隔振器，用于通过去除有效载荷周围的空气来防止对连接到运载火箭的有效载荷造成的损坏，使得声振动不具有传播到达有效载荷的介质。

公开(公告)号：US06315247B1

公开(公告)日：2001-11-13

申请号：US09368978

申请日：1999-08-05

申请人： Michael J. Wehner ,  Keith V. Kroening ,  L. Dwight Gilger

发明人： Michael J. Wehner ,  Keith V. Kroening ,  L. Dwight Gilger

IPC分类号： B64G110

CPC分类号： B64G1/002 ,  B64G1/1085 ,  B64G1/641 ,  B64G2001/228

摘要： A spacecraft having a movable structure which is held in a preselected location by a holding mechanism substantially free of microdynamic noise. The holding mechanism comprises two mechanical members in physical contact with each other and movable with respect to each other. The unintentional movement of the two mechanical members with respect to each other generates microdynamic noise. The two mechanical members are secured together to provide joinder of the two mechanical members when the movable structure is located in the preselected position to prevent long-term unintentional movement between the two mechanical members.

摘要翻译： 具有可移动结构的航天器，其通过基本上没有微动噪声的保持机构保持在预选位置。 保持机构包括彼此物理接触并相对于彼此可移动的两个机械构件。 两个机械构件相对于彼此的无意的运动产生微动力噪声。 当可移动结构位于预选位置时，两个机械构件固定在一起以提供两个机械构件的联接，以防止两个机械构件之间的长期无意的移动。