专

一种单管蓝光半导体激光器外腔装置

KR203171B1

发明人

TANG XIAHUI, FANG XING, CHANG YUNWEI, DING ZEYU, CHEN GUONING, HAN JINLONG, NIU ZENGQIANG

受让人

UNITED WINNERS LASER CO. LTD.

申请人

中兴通讯股份有限公司

申请号

017075

申请日

2010-02-15

公开(公告)号

KR203171B1

公开(公告)日

2003-11-05

IPC分类号

C02F1/50

CPC分类号

优先权号

2009117640

优先权日

2009-05-13

摘要

Communicating information from a service robot on a ring spinning frame to service personnel, and that any spin unit which the robot is unable to service properly is notified visually by means of suitable appts.

Pref. the robot travels around the frame on the track and when a defect, such as lack of roving, faulty traveller, etc., is encountered, which cannot be rectified mechanically, the robot signals via the line to the visual display details of the unit position and number. The visual indicator is placed at one end of the frame, and may also be equipped with a printer to record details. The connections may be from one or several frames to a central visual indicator.

ADVANTAGE -Service personnel are made aware of faults which could not be rectified mechanically, and it is proposed that a series of robots and frames may be supervised by one operator from a central point. @(2pp Dwg.No 0/4)

权利要求

a power generator device to provide power for the movement of the ordnance transfer assembly.

2. The apparatus according to claim 1 , further comprises an extendible arm assembly attached to the first airborne aerial vehicle, the arm first end is attached to the body of the first airborne aerial vehicle, the arm second end provided with freedom of movement.

3. The apparatus of claim 2 further comprising an ordnance transfer control assembly providing for the control of the arm and the ordnance transfer assembly to enable controlling the movement of the extended arm in a bi-directional, multi-axis movement.

4. The apparatus of claim 1 , wherein the ordnance carriage cradle is mounted outside the ordnance transfer assembly, hence the at least one ordnance unit held by said ordnance carriage cradle is not limited in size by the size of the ordnance transfer assembly.

5. The apparatus of claim 1 wherein the at least one ordnance unit is an aerial bomb device intended to be released, dropped or ejected from the second aerial vehicle toward a target.

6. The apparatus of claim 1 wherein the at least one ordnance unit is a missile device to be launched from the second aerial vehicle toward a target.

7. The apparatus of claim 3 wherein the ordnance transfer control assembly comprises: a computer device having a memory device to hold software programs associated with the control of the movement of the extendible arm; a communication device to transfer bi-direction control data, command data and positional information between the first aerial vehicle and the extendible arm; thereby enabling control for an air-to-air transfer of the at least one ordnance unit from the first aerial vehicle to the second aerial vehicle.

8. The apparatus of claim 1 wherein the ordnance transfer assembly further comprises a foldable aerodynamic control surface assembly to provide for aerodynamic lift and control to the extendible arm.

9. The apparatus of claim 3 wherein the ordnance transfer assembly further comprises an at least one image acquiring device to provide the arm position-specific images to the ordnance transfer control assembly.

10. The apparatus of claim 9 further comprising an at least one lighting device to enhance the quality of the arm position-specific images provided to the ordnance transfer control assembly during ordnance transfer occurring under reduced quality lighting conditions.

11. The apparatus of claim 9 further comprising an at least one night vision device to provide enhanced quality mechanical arm position-specific images during day and nighttime ordnance transfer.

12. The apparatus of claim 1 wherein the extendible arm assembly further comprises: bi-directional movement providing means to drive the arm assembly from or to the first aerial vehicle; and multi-axis movement providing means to control the arm assembly unit along several axes; thereby enabling bi-directional and multi axis movement and control of the extendible arm within a trajectory between the first airborne aerial vehicle and the second airborne aerial vehicle.

13. The apparatus of claim 2 wherein the ordnance transfer assembly comprises at least two interlinked arm sections coupled together by at least one motorized joint to provide for the movement of the interlinked arm sections in respect to each other.

14. The apparatus of claim 1 wherein the ordnance transfer assembly comprises: at least two ordnance gripping arms; at least one stabilizing surface to be used for stabilizing the pylon adapter to the pylon; and a multi-fuzing unit to enable fuzing of the at least one transferred ordnance unit.

15. The apparatus of claim 1 wherein the ordnance transfer assembly is an extendible telescopic probe assembly comprising at least two telescopic tubes with the base of the ordnance transfer assembly attached to the first aerial vehicle and the innermost telescopic tube is linked to the second aerial vehicle.

16. The apparatus of claim 15 wherein the ordnance transfer assembly comprises at least two interlinked mechanized arm sections joined by motorized links and providing movement of the mechanized arm sections in respect of each other.

17. The apparatus of claim 13 wherein the ordnance transfer assembly comprises a ordnance transfer assembly connected to the second end of the arm assembly, the ordnance transfer assembly comprising an ordnance carrier cradle equipped with gripping arms to secure at least one ordnance unit to the ordnance carriage cradle.

18. The apparatus of claim 1 wherein the extendible arm is an extendible boom assembly attached at one end to the first airborne aerial vehicle, the boom assembly comprising: an internally mounted ordnance conveyor mechanism enclosed in a rigid or semi-rigid tube for the feeding of the at least one ordnance unit from the first airborne aerial vehicle to the second airborne aerial vehicle; at least one foldable aerodynamic lifting and control surface to provide for the controlling of the boom assembly; and an ordnance carriage cradle installed at the second end of the boom assembly.

19. The apparatus of claim 1 wherein the extendible arm comprises at least two interlinked arm sections having at least one motorized joints to provide for the movement of the interlinked arm sections in respect to each other, the arm comprising: an externally mounted ordnance conveyor mechanism enclosed in a rigid or semi-rigid tube connected to the at least two interlinked mechanized arm section to provide for the feeding of an at least one ordnance unit from the first airborne aerial vehicle to the second airborne aerial vehicle; an at least one aerodynamic lifting and control surface to control maneuvering of the extended arm; and an ordnance carriage cradle installed at the second end of the arm to receive an at least one ordnance unit fed by the ordnance conveyor mechanism and attach the at least one ordnance unit to a pylon attached to a weapon station on the second airborne aerial vehicle.

an externally mounted ordnance conveyor mechanism to provide for the transfer of the at least one ordnance unit from the first airborne aerial vehicle to the second airborne aerial vehicle, the ordnance conveyor mechanism comprising: a moveable ordnance carriage cradle device to carry the at least one ordnance unit along the extended mechanical arm from the first arm section of the mechanical arm via the intermediate arm sections of the mechanical arm to the second arm section of the mechanical arm in order to transfer the at least one ordnance unit between the first airborne aerial vehicle and the second airborne aerial vehicle; and at least two movement direction bars extended along, the mechanized arm sections in order to provide support and direction to the moveable ordnance carriage cradle device; and a power generator to provide power for the movement of the ordnance carriage cradle device along the at least two interlinked arm sections of the arm.

21. The apparatus of claim 20 wherein the moveable ordnance carriage cradle device coupled to the ordnance conveyor mechanism associated with the arm, the ordnance carriage cradle device comprising: a cradle body to support operational elements of the ordnance carriage cradle device; at least two ordnance unit positioning bars to provide upward movement to the at least one ordnance unit where the ordnance unit is positioned in relation to the pylon; at least two ordnance unit gripping arms to hold the at least one ordnance unit on the ordnance carriage cradle during the transfer of the at least one ordnance unit between the first airborne aerial vehicle and the second airborne aerial vehicle; and a guidance boom device attached to the cradle body to provide in the final phase of the ordnance transfer the establishment of contact with an engagement rod installed on the pylon.

22. The apparatus of claim 1 wherein the first airborne aerial vehicle is a manned cargo aircraft.

23. The apparatus of claim 22 wherein the first airborne aerial vehicle is a Lockheed Martin C-130 Hercules.

24. The apparatus of claim 1 wherein the first airborne aerial vehicle is an unmanned or an uninhabited aircraft.

25. The apparatus of claim 1 wherein the second airborne aerial vehicle is a manned aircraft.

26. The apparatus of claim 1 wherein the second airborne aerial vehicle is an unmanned or uninhabited aerial vehicle.

27. The apparatus of claim 1 wherein the first aerial vehicle and the second aerial vehicle are space platforms.

the ordnance carriage cradle comprising a pylon adapter to verify connection of the at least one ordnance unit during an air-to-air ordnance transfer, the pylon adapter comprising: a mechanical connector to the pylon; manipulating the extendible arm to provide for the bi-directional, movement of the arm between the first airborne aerial vehicle and the second airborne aerial vehicle.

29. The method of claim 28 further comprising: establishing contact between the at least one ordnance unit or the at least one ordnance assembly and the second airborne aerial vehicle; and attaching the at least one ordnance unit or the at least one ordnance assembly to a pylon of the second airborne aerial vehicle.

30. The method of claim 28 further comprising establishing contact between the second end of the arm and the second airborne aerial vehicle via the manipulation of the arm.

31. The method of claim 28 further comprising uploading the ordnance unit on an external or internal weapon station on the second airborne aerial vehicle.

32. The method of claim 28 further comprises: disconnecting the second end of the arm from the at least one ordnance unit or from the at least one ordnance assembly; stabilizing the at least one ordnance unit or the at least one ordnance assembly to a pylon; and fuzing the at least one ordnance unit or the at least one ordnance unit attached to the at least one ordnance assembly.

33. The method of claim 28 further comprises retracting the manipulable, extendible arm at the completion of the ordnance transfer procedure into the internal cargo space of the first airborne aerial vehicle.

34. The method of claim 28 further comprises feeding the at least one ordnance unit via an internally installed conveyor mechanism associated with the arm from the first airborne aerial vehicle to the second airborne aerial vehicle.

35. The method of claim 28 further comprises feeding the at last one ordnance unit via an externally installed ordnance conveyor mechanism associated with the extendible, manipulable arm from the first airborne aerial vehicle to the second airborne aerial vehicle.

36. The method of claim 28 further comprises controllably moving the ordnance carriage cradle carrying the at least one ordnance unit or the at least one ordnance assembly from the first airborne aerial vehicle to the second airborne aerial vehicle along the extended arm assembly where the second end of the arm assembly.

37. The method of claim 28 further comprises a step of aborting the ordnance transfer comprises a retrieval of the extendible arm.

38. The method of claim 37 wherein the step of aborting the ordnance transfer comprises jettisoning of the arm or the ordnance, or the ordnance carriage cradle or at least one part of the arm.

说明书

[0001]低斜率色散控制波导

[0002]发明领域

[0003]本发明一般涉及为长的转发器间隔、高数据速率的电信系统而设计的单模光学波导纤维。具体地，单模波导综合了优良的抗弯曲、低衰减、低色散和低色散斜率、以及长距离传输应用中所需的特性。

[0004]技术背景

[0005]电信工业对无需电子信号再发生，在长距离上更大信息容量的要求已经导致单模光纤折射率分布设计的再次革命。

[0006]掺铒光纤放大器(EDFA)和波分复用技术的近期发展已经能够产生大容量的光波系统。为了实现大容量，能够增大信道比特率和信号波长范围。当比特率增大到超过2.5Gb/s时，光纤色散成为长距离的一个主要退化因素。另一方面，如果色散太低，多信道的相互作用会引起四波混合和退化系统性能。为了降低色散和FWM退化，已经提议并实验演示了色散控制。色散控制可以通过电缆控制和光纤控制来实现，前者交替地拼接+D和-D光纤，后者将具有+D和-D特性的芯茎组合起来，拉制成一根光纤。

[0007]迄今，已经提出了利用具有正色散斜率的+D和-D光纤控制的色散，其中，最终的光纤色散具有类似于色散漂移光纤的色散和斜率，换句话说，净的零色散在1550nm窗口中，总的色散斜率是正的。然而，仍然需要色散控制波导的其它设计。

[0008]定义

[0009]以下定义按照本领域的常规用法。折射率分布是以相似折射率的段的半径定义的。特定的段具有第一和最后折射率点。从波导中心线到这个第一折射率点的位置的半径是芯区或段的内径。同样，从波导中心线到这个最后折射率点的位置的半径是芯段的外径。

[0010]段的半径可以由许多方法方便地限定，正如以下对图1的描述中将看出的。在图1-3中，表1和2由此导出，折射率分布段的半径定义如下，这里参考是指Δ％与波长半径的图表：

[0011]*中心主折射率分布的外径r1是从波导的轴向中心线测量到外推中心折射率分布与x轴的相交点，即Δ％=0的点；

[0012]*第一环形段的外径r2是从波导的轴向中心线测量到外推或实际中心折射率分布与x轴的相交点，即Δ％=0的点；

[0013]*第二环形段的外径r3是从波导的轴向中心线测量到外推中心折射率分布与x轴的相交点，即Δ％=0的点；

[0014]*任何附加的环形段的外径是模拟第一和第二环形段的外径测量的；

[0015]*最后环形段的半径是中波导中心线测量到该段的中点。

[0016]段的宽度w取为段的内径与外径之间的距离。应当明白，段的外径对应于下一个段的内径。

[0017]-折射率Δ由以下方程式定义

[0018]Δ％=100×(n12-n22)/2n12，这里n1是折射率分布段1的最大折射率，n2是参考折射率，在本申请中它取为包层的折射率。

[0019]-术语折射率分布是指在芯的所选部分上Δ％或折射率与半径之间的关系。

[0020]-术语α分布是指以Δ(b)％项表示的折射率分布，这里b是半径，它遵循以下方程式

[0021]Δ(b)％=Δ(b0)(1-[︳b-b0｜/(b1-b0)]α)，这里b0是折射率为最大的半径点，b1是Δ(b)％为零的点，b是范围，bi≤b≤bf，这里，Δ定义如上，bi是α分布的起点，bf是α分布的终点，α是实数指数。

[0022]其它折射率分布包括台阶折射率、三角、不规则四边形和圆形台阶折射率，其中圆形的通常是由快速折射率变化的区域中杂质扩散造成的。

[0023]-总色散定义为波导色散和材料色散的代数和。在本领域中，总色散有时称为色散。总色散的单位是ps/nm-km。

[0024]-波导纤维的抗弯曲表示为在规定测试条件下的感应衰减。标准测试条件包括绕75mm直径心轴100圈的波导纤维和绕32mm直径心轴1圈的波导纤维。在每个测试条件下，测量弯曲感应衰减，通常以db/(单位长度)为单位。在本申请中，采用的弯曲测量是绕20mm直径心轴5圈的波导纤维，对于本波导纤维的更苛刻的工作环境，需要更高要求的测试。

[0025]发明内容

[0026]本发明的一个方面涉及一种单模光学波导，包括具有正色散和正色散斜率的第一光纤元件段和负色散和负色散斜率的第二光纤元件段，其中，波导沿其长度在第一光纤元件与第二光纤元件之间交替变换，其中，第一光纤元件段的长度至少是第二光纤元件段长度的两倍。关于1550nm较低衰减的工作波长窗口，即约1520nm至1625nm之间的窗口中，使波导实现最优化。

[0027]根据本发明的波导可以由其中具有各个第一和第二段的幺正光纤组成，例如，正的和负的色散和色散斜率的段交替组成。另一方面，波导可以由光缆组成，其中各个光纤元件段沿光缆长度连接起来。

[0028]本发明的另一个方面涉及通过提供小的总色散和低的色散斜率而控制光纤色散的单模光学波导。根据本发明的较佳波导在1520至1625nm范围上呈现色散，其幅度总是小于2，较佳地小于1ps/nm2-km。波导光纤在1550nm处的总色散在约-2.0至+2.0ps/nm-km的范围内，更好地是在-1.0至+1.0，最好是-0.5至+0.5ps/nm-km。各个正的和负的色散段的ri、Δi％和折射率分布还可以选择为提供在1550nm处的总衰减不大于0.25dB/km。

[0029]所有这些特性是在维持高强度、良好抗疲劳性、和良好抗弯曲性的同时实现的，即诱发的弯曲损失，对于绕32mm心轴1圈不大于0.5dB，对于绕75nm心轴100圈不大于0.05dB。根据本发明的波导还可以与光学放大器兼容。此外，光缆形式的光纤的截止波长小于1520nm。附加的好处是偏振模式色散小于约.5ps/(km)1/2，小于.3ps/(km)1/2则更好，通常约为.1ps/(km)1/2。

[0030]在以下的详细描述中将给出本发明的附加特征和优点，对于本领域专业人员而言，从以上的描述一部分特征和优点是显然的或者通过实施这里所描述的本发明，包括以下的详细描述，权利要求书和附图可以看出。

[0031]应当明白，以上的一般描述和以下的详细描述仅仅是本发明的示例，希望提供一个概要或框架，以理解本发明的本质和特征。包含的附图可提供对本发明的进一步理解，并构成本说明书的一部分。附图示出本发明的各种实施例，与说明相结合可以解释本发明的原理和工作。

[0032]附图简述

[0033]图1示出供本发明实验的负色散光纤段分布。

[0034]图2示出根据本发明的另一种负色散光纤段折射率分布。

[0035]图3示出另一种较佳的负色散光纤段分布。

[0036]图4示出根据本发明的交替+D和-D段光纤的色散特性。

[0037]图5示出色散与根据本发明的色散平化和色散控制光纤的距离的关系。

[0038]图6示出色散与根据本发明的色散平化和色散控制的波长曲线的关系。

[0039]较佳实施例的详细描述

[0040]现在将详细描述本发明的较佳实施例，其中一些例子是借助于附图描述的。只要在可能的地方，在整个附图中将采用相同的参考标号表示相同或相似部件。

[0041]在本发明中，低的斜率和色散控制的光纤波导是通过将具有正色散和正色散斜率的第一光纤元件和具有负色散和负色散斜率的第二光纤元件合成为交替的段而实现的，其中第一光纤元件的长度至少是第二光纤元件长度的两倍，较佳地是三倍，最好是至少五倍。

[0042]本发明的波导可以为具有正负色散和色散斜率的交替段的幺正光纤的形式。例如，通过将具有所需折射率分布的交替芯小片组装在一个管子或其它支承器件中能够制造这种光纤。交替芯小片能产生所需的交替正负色散特性。然后内含这些交替元件小片的管子可以被硅石包层覆盖，产生的预型件被固结和拉制成连续光纤，它沿其长度呈现具有正负色散和色散斜率的交替部分。在1997年4月23日提交的美国专利申请08/844,997中进一步揭示了这种制造技术，该专利申请的说明书和附图在此全部引作参考。

[0043]在另一个实施例中，波导由光缆波导构成。例如，波导可以由具有正色散和正色散斜率的、其长度至少50km，至少75km则更好的第一光纤元件和具有负色散和负色散斜率的、其长度小于20km，小于15km则更好的第二光纤元件组成。这种光缆波导可以设置在光纤通信系统中的放大器之间。第二光纤元件可以交替地放置在放大器内的放大器旁或者放大器模块自身中。

[0044]第一光纤元件，即具有正色散和色散斜率的光纤元件可以通过利用传统的单模光纤，如由康宁公司提供的SMF28来提供。SMF-28在1550nm处的总色散为17ps/nm.km，色散斜率为0.06ps/nm2·km。

[0045]可以采用各种光纤分布来提供具有负色散和负色散斜率的第二光纤元件。在本发明的较佳实施例中，负元件光纤段的分布具有三段或四段。

[0046]图1示出负色散、负色散斜率光纤段元件的这种较佳的三段分布的一个实施例。图1的分布由外径r1的第一中心主折射率分布10、被外径r2的第一环形段12环绕，被外径r3的第二环形段14环绕而组成。如图所示，可以采用各种分布形状，例如采用与图1中第一中心主折射率分布10的可能分布形状相关的虚线。

[0047]新颖的单模光学波导的特征在于其分段的芯设计，它提供这里所给出的特性的非寻常组合。这些特性的实现是通过选择每个段的适当折射率分布形状以及选择各个段的适当的相对折射率德尔塔，Δi％，半径范围，ri。分布参数已知是相互作用的。例如，α约为1的中心区α分布将具有不同于具有不规则四边形折射率的中心区的半径，提供具有基本一致的特性的光纤。

[0048]各个段的折射率分布实际上可以是任何特定形状，包括α分布、阶梯形分布、或不规则四边形分布。除非在过程中插入特别步骤，在折射率陡然变化的地方，折射率分布将是圆形的。圆形是由于用于改变基质玻璃折射率的掺杂物材料的扩散造成的。因此在特定点上可以使任何这些折射率分布是圆的。例如，具有正Δ％的阶梯折射率分布通常将具有圆的上角和下角。

[0049]下表1中给出的是可以用于形成本发明负色散、负色散斜率光纤段的3段分布的半径与德尔塔的较佳参数。正如从表中看出的，光纤可以包括或不包括中心凹陷折射率区，这通常是由锗掺杂物的迁移引起的。

[0050]表1

[0051]半径(微米)德尔塔(％)

[0052]r11.25-50.5-2

[0053]r21.25-10-0.5--0.1

[0054]r32.5-150.1-1.0

[0055]图1中所示的负色散光纤的芯段小片与具有正色散和正色散斜率的传统单模光纤(SMF28)相组合，拉制成光纤。由图1中实线所示的光纤在1550nm处呈现负色散，即约-35ps/nm·km和约0.15ps/nm2·km的色散斜率。因此，在这种情况中，(DSMF/SSMF)=17/0.06=280，而(Dn/Sn)=-35/0.15=-233。因此，(Dp/Sp)/(Dn/Sn)=0.83，它相当接近于1，正如所需。

[0056]图2示出四段光纤芯分布，它用作本发明的负色散斜率色散光纤段。图2中所示的分布加入两个折射率凹下区12和16。

[0057]下表2中给出的是可以用于形成本发明负色散、负色散斜率光纤段的这四段分布的半径与德尔塔的较佳参数。

[0058]表2半径(微米)德尔塔(％)r11.25-50.5-2r21.25-10-0.5--0.1r32.5-150.1-1.0r45-25-0.5-0

[0059]这里揭示的任何分布也可以包括中心线尖端部分，它是小于第一主芯段的峰值德尔塔的凹下的相对折射率区。这个中心线尖端通常是由所谓的掺杂物离子烧尽或迁移引起的，这有时出现在光纤波导的制造期间。

[0060]根据本发明的波导较佳地在1520至1625nm范围上呈现色散，其幅度总是小于2，小于1ps/nm2-km则更好。波导光纤在1550nm的总色散在约-2.0至+2.0，较好地在-1.0至+1.0，最好在-0.5至+0.5ps/nm-km。也可以选择各个正负色散段的ri、Δi％和折射率分布，提供在1550nm的总衰减不大于0.25dB/km。

[0061]所有这些特性可以在维持高强度、良好抗疲劳性和良好抗弯曲性的同时实现，即诱发弯曲损失对于绕32mm心轴1圈，不大于0.5dB，对于绕75mm心轴100圈，不大于0.05dB。根据本发明的波导还可以与光学放大器相兼容。此外，光缆形式的光纤的截止波长小于1520nm。附加的好处是偏振模式色散小于0.5ps/(km)1/2，更好地小于0.3ps/(km)1/2。

[0062]本发明的一个特定的较佳色散控制波导通过提供负的总色散以及低的色散斜率而控制光纤色散。在抑制潜在孤立子形成是重要的系统中，需要波导光纤的总色散是负的，从而使线性色散不能抵消非线性自相位调制(对大功率信号发生的)。为了均衡光纤色散，最好尽可能地满足以下关系：

[0063]DpLp+DnLn=0

[0064]这里D和L代表色散和光纤长度，脚标“p”和“n”代表正的和负的色散光纤元件。此外，为了均衡色散斜率，最好尽可能地满足以下关系：

[0065](Dp/Sp)/(Dn/Sn)=1，这里S是色散斜率。

[0066]这里所描述的波导适合于大功率和长距离传输应用，包括传统的RZ(归零)或NRZ(不归零)以及孤立子传输应用。大功率和长距离的定义仅仅是在特定的电信系统的范围内有意义，其中规定了比特率、比特差错率、复用方案、也许还有光学放大器。还有一些附加因素，对本领域专业技术人员而言是所熟知的，对大功率和长距离的含义产生作用。然而，广泛而言，大功率是指每个信道的光学功率大于约10mW。在一些应用中，1mW甚至更小的信号功率电平仍然对非线性效应敏感，以致于Aeff仍然是这种低功率系统中的一个重要考虑依据。

[0067]长距离是指两个电子再生器之间的距离可以超过100至120km的距离。再生器不同于利用光学放大器的转发器。转发器间隔，尤其是在高数据密度系统中，可以小于再生器间隔的一半。

[0068]通过以下的希望是本发明范例的例子将能进一步弄清本发明。

[0069]例子

[0070]图3示出一个较佳的用作负色散、负斜率光纤段的三段折射率分布。这个特定分布在1550nm处显示色散-35.47ps/nm.km、斜率-0.1018ps/nm2.km。在1550nm处，截止波长为1.18微米，管脚阵列弯曲损失1.3dB、MFD为4.8微米、Deff为4.68微米。

[0071]图4示出在SMF-28这一情况中，当正色散光纤元件与图3中揭示的各种负色散光纤元件相组合时所实现的色散特性，具有以下参数：

[0072]德尔塔(％)半径(μm)

[0073]芯22.2(r1)

[0074]第一槽沟-0.45.76(r2)

[0075]圆环0.66.72(r3)

[0076]下表3列出最终的色散和色散斜率特性，以及色散与色散斜率之比，这是通过交替的光纤段的这一组合而实现的。

[0077]表3

[0078]+D光纤-D光纤

[0079]D(ps/nm.km)17-35

[0080]S(ps/nm2.km)0.058-0.1018

[0081]D/S(nm)293350

[0082]图5示出最终的波导光纤的轴向设计，以最终色散平化、色散控制光纤的波导长度(nm.km)上的色散表示。

[0083]图6示出色散平化和控制光纤的最终总色散特性。在这个例子中Lp/Ln约为2∶1。周期Ln+Lp约为3km。正如从图6看出的，对于这个设计的例子，从1520到1620nn，总色散远小于1ps/nm.kmn，实际上，小于约0.5ps/nm.km。这与单模光纤的低损失窗口相一致。根据传统单模光纤的损失光谱，从1520到1620nm，衰减小于0.22dB/km。

[0084]本领域的专业技术人员显而易见，能够对本发明作出各种改进和变化，而不会偏离本发明的精神和范围。因此，希望本发明覆盖在所附权利要求书及其等效物的范围之内的对该发明的改进和变化。

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