技术领域technical field
本发明涉及空间碎片利用技术领域。The invention relates to the technical field of space debris utilization.
背景技术Background technique
空间碎片长期以来作为有害的存在对航天活动产生了制约与危害,而空间碎片的日益增多，已经严重影响了空间安全。空间维护的传统方式是将空间碎片清除离轨，这样固然能保护空间飞行器的运行环境，但也造成了这些空间碎片物质的直接浪费，因此探索一种将空间碎片有效的利用起来为空间飞行器服务的新途径极具应用价值。As a harmful existence, space debris has restricted and harmed space activities for a long time, and the increasing number of space debris has seriously affected space security. The traditional way of space maintenance is to remove space debris from orbit, which can protect the operating environment of space vehicles, but it also causes direct waste of these space debris materials. Therefore, it is necessary to explore a way to effectively use space debris to serve space vehicles The new approach has great application value.
发明内容Contents of the invention
(一)要解决的技术问题(1) Technical problems to be solved
本发明的目的是提供一种基于激光推进的空间碎片能量转化装置及方法，解决传统空间维护方式存在的空间碎片物质无法有效利用的问题。The purpose of the present invention is to provide a space debris energy conversion device and method based on laser propulsion to solve the problem that space debris materials in traditional space maintenance methods cannot be effectively utilized.
(二)技术方案(2) Technical solution
为了解决上述技术问题，本发明提供了一种基于激光推进的空间碎片能量转化装置，包括装置本体以及分别设置在所述装置本体上的光学准直机构、光学分光机构、至少一个光学工质耦合机构和至少一个工质供给机构，其中所述光学分光机构设置在所述光学准直机构的底部，各所述光学工质耦合机构分别对应设置在所述光学分光机构的光束输出方向上，各所述光学工质耦合机构分别与各所述工质供给机构一一对应连接；In order to solve the above technical problems, the present invention provides a space debris energy conversion device based on laser propulsion, which includes a device body and an optical collimation mechanism, an optical beam splitting mechanism, and at least one optical working fluid coupling mechanism and at least one working fluid supply mechanism, wherein the optical beam splitting mechanism is arranged at the bottom of the optical collimation mechanism, each of the optical working fluid coupling mechanisms is respectively arranged in the beam output direction of the optical beam splitting mechanism, each The optical working fluid coupling mechanism is respectively connected to each of the working fluid supply mechanisms in a one-to-one correspondence;
所述光学准直机构用于将入射激光束进行准直，并将准直后的准直激光束传输至所述光学分光机构；The optical collimation mechanism is used to collimate the incident laser beam, and transmit the collimated collimated laser beam to the optical beam splitting mechanism;
所述光学分光机构用于将所述准直激光束分成至少一个方向的分体激光束，并将所述分体激光束传输至所述工质耦合机构；The optical splitting mechanism is used to split the collimated laser beam into split laser beams in at least one direction, and transmit the split laser beams to the working fluid coupling mechanism;
所述工质供给机构用于向所述工质耦合机构输送固态工质；The working medium supply mechanism is used to deliver solid working medium to the working medium coupling mechanism;
所述工质耦合机构利用所述分体激光束与所述固态工质发生烧蚀耦合，形成等离子体反喷产生推力。The working fluid coupling mechanism utilizes the split laser beam to ablate and couple with the solid working fluid to form plasma blowback to generate thrust.
进一步地，所述光学准直机构包括菲涅耳透镜和聚集透镜，所述菲涅耳透镜用于将所述入射激光束聚焦在所述菲涅耳透镜的焦点上，形成点光源，所述聚集透镜的焦点与所述菲涅耳透镜的焦点相同，位于焦点的点光源经过所述聚集透镜形成平行光束。Further, the optical collimation mechanism includes a Fresnel lens and a focusing lens, the Fresnel lens is used to focus the incident laser beam on the focal point of the Fresnel lens to form a point light source, the The focal point of the focusing lens is the same as that of the Fresnel lens, and the point light source at the focal point passes through the focusing lens to form a parallel light beam.
进一步地，所述光学分光机构包括至少一个分光镜以及与所述分光镜相配合的多个反射镜，各所述分光镜分别用于将所述准直激光束分成沿指定方向的分体激光束，所述反射镜用于将所述分体激光束反射至指定位置。Further, the optical beam splitting mechanism includes at least one beam splitter and a plurality of mirrors matched with the beam splitter, each of the beam splitters is used to split the collimated laser beam into split laser beams along a specified direction beam, and the reflector is used to reflect the split laser beam to a designated position.
进一步地，所述工质供给机构包括行程控制器、与所述行程控制器连接的工质推送板、以及工质支撑板，其中所述行程控制器用于控制所述工质推送板的运动位置，所述工质推送板用于带动固态工质运动，所述工质支撑板用于支撑所述固态工质。Further, the working medium supply mechanism includes a stroke controller, a working medium pushing plate connected to the stroke controller, and a working medium supporting plate, wherein the stroke controller is used to control the movement position of the working medium pushing plate , the working medium pushing plate is used to drive the solid working medium to move, and the working medium supporting plate is used to support the solid working medium.
进一步地，所述工质耦合机构包括耦合腔体，所述耦合腔体设有分体激光束输入通道、固态工质输入通道和离子体反喷输出通道。Further, the working medium coupling mechanism includes a coupling cavity, and the coupling cavity is provided with a split laser beam input channel, a solid working medium input channel, and an ion plasma back-spray output channel.
进一步地，还包括设置在所述装置本体上的激光器，所述激光器用于向所述光学准直机构发出入射激光束。Further, a laser arranged on the device body is also included, and the laser is used to emit an incident laser beam to the optical collimation mechanism.
具体地，所述光学分光机构与所述光学准直机构通过第一卡扣结构连接，所述光学工质耦合机构与所述工质供给机构通过第二卡扣机构连接。Specifically, the optical beam splitting mechanism is connected to the optical collimation mechanism through a first buckle structure, and the optical working medium coupling mechanism is connected to the working medium supply mechanism through a second buckling mechanism.
本发明还提供了一种基于激光推进的空间碎片能量转化方法，将上述的基于激光推进的空间碎片能量转化装置安装到飞行器上；The present invention also provides a method for energy conversion of space debris based on laser propulsion, wherein the above-mentioned energy conversion device for space debris based on laser propulsion is installed on an aircraft;
该方法具体包括如下步骤：The method specifically includes the following steps:
第一步，将收集到的空间碎片制作为圆柱状固态工质，并将所述圆柱状固态工质加载到所述的空间碎片能量转化装置中；In the first step, the collected space debris is made into a cylindrical solid working medium, and the cylindrical solid working medium is loaded into the space debris energy conversion device;
第二步，通过激光器发射入射激光束至光学准直机构，经过所述光学准直机构完成入射激光束的准直，并将准直后的准直激光束传输到光学分光机构；In the second step, the incident laser beam is emitted to the optical collimation mechanism through the laser, the collimation of the incident laser beam is completed through the optical collimation mechanism, and the collimated collimated laser beam is transmitted to the optical beam splitting mechanism;
第三步，所述光学分光机构按需要将所述准直激光束分成至少一个方向的分体激光束，并将所述分体激光束输出至工质耦合机构；In the third step, the optical splitting mechanism divides the collimated laser beam into at least one split laser beam in one direction as required, and outputs the split laser beam to the working medium coupling mechanism;
第四步，通过工质供给机构将所述圆柱状固态工质推送至所述工质耦合机构，使所述圆柱状固态工质与所述分体激光束相互作用形成等离子体反喷产生推力；The fourth step is to push the cylindrical solid working medium to the working medium coupling mechanism through the working medium supply mechanism, so that the cylindrical solid working medium interacts with the split laser beam to form a plasma blowback to generate thrust ;
第五步，通过所述推力直接为飞行器提供在轨动力，实现空间碎片能量的直接转化利用。The fifth step is to directly provide on-orbit power for the aircraft through the thrust, so as to realize the direct conversion and utilization of space debris energy.
(三)有益效果(3) Beneficial effects
本发明的上述技术方案具有如下优点：The technical scheme of the present invention has the following advantages:
1、本发明所述的基于激光推进的空间碎片能量转化装置及方法，采用激光与空间碎片直接作用产生离子体喷射形成推力的方式，实现了空间碎片离子化与能量利用的紧耦合，简化了空间碎片利用的过程。1. The space debris energy conversion device and method based on laser propulsion according to the present invention adopts the method of direct interaction between laser and space debris to generate plasma ejection to form thrust, which realizes the tight coupling of space debris ionization and energy utilization, and simplifies The process of space debris utilization.
2、本发明所述的基于激光推进的空间碎片能量转化装置及方法，通过空间碎片与激光相互作用产生离子体后喷射，不会产生新的颗粒物质，不会对空间环境造成二次污染，在清洁利用空间碎片的同时也实现了空间碎片的有效清除。2. The space debris energy conversion device and method based on laser propulsion according to the present invention, through the interaction of space debris and laser to generate ions and then spray them, will not produce new particulate matter, and will not cause secondary pollution to the space environment, While cleanly utilizing space debris, it also realizes the effective removal of space debris.
3、本发明所述的基于激光推进的空间碎片能量转化装置，结构简单，转化利用效率高，可直接应用于空间飞行器的在轨控制。3. The space debris energy conversion device based on laser propulsion according to the present invention has a simple structure and high conversion and utilization efficiency, and can be directly applied to the on-orbit control of space vehicles.
附图说明Description of drawings
图1是本发明实施例一基于激光推进的空间碎片能量转化装置的结构示意图；Fig. 1 is a schematic structural diagram of a space debris energy conversion device based on laser propulsion according to an embodiment of the present invention;
图2是本发明实施例二基于激光推进的空间碎片能量转化装置的结构示意图；Fig. 2 is a schematic structural diagram of a space debris energy conversion device based on laser propulsion according to Embodiment 2 of the present invention;
图3是本发明基于激光推进的空间碎片能量转化装置的光学准直机构示意图；Fig. 3 is a schematic diagram of the optical collimation mechanism of the space debris energy conversion device based on laser propulsion in the present invention;
图4是本发明基于激光推进的空间碎片能量转化装置的光学分光机构示意图；Fig. 4 is a schematic diagram of the optical beam splitting mechanism of the space debris energy conversion device based on laser propulsion in the present invention;
图5是本发明基于激光推进的空间碎片能量转化装置的反射镜布置示意图；Fig. 5 is a schematic diagram of mirror layout of the space debris energy conversion device based on laser propulsion according to the present invention;
图6是本发明基于激光推进的空间碎片能量转化装置的工质供给机构示意图；Fig. 6 is a schematic diagram of the working fluid supply mechanism of the space debris energy conversion device based on laser propulsion in the present invention;
图7是本发明基于激光推进的空间碎片能量转化装置的工质耦合机构的工作原理图。Fig. 7 is a working principle diagram of the working fluid coupling mechanism of the space debris energy conversion device based on laser propulsion in the present invention.
图中：1：光学准直机构；101：菲涅耳透镜；102：聚集透镜；2：光学分光机构；201：第一分光镜；202：第二分光镜；203：第三分光镜；204：第四分光镜；205：反射镜；3：光学工质耦合机构；4：工质供给机构；401：行程控制器；402：工质推送板；403：工质支撑板；5：分体激光束；6：点光源；7：固态工质；8：冲量耦合面。In the figure: 1: optical collimation mechanism; 101: Fresnel lens; 102: converging lens; 2: optical beam splitting mechanism; 201: first beam splitter; 202: second beam splitter; 203: third beam splitter; 204 : fourth beam splitter; 205: reflector; 3: optical fluid coupling mechanism; 4: fluid supply mechanism; 401: stroke controller; 402: fluid pushing plate; 403: fluid support plate; 5: split Laser beam; 6: point light source; 7: solid working medium; 8: impulse coupling surface.
具体实施方式Detailed ways
为使本发明实施例的目的、技术方案和优点更加清楚，下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例是本发明的一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动的前提下所获得的所有其他实施例，都属于本发明保护的范围。In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.
实施例一Embodiment one
如图1所示，本实施例提供的基于激光推进的空间碎片能量转化装置，包括装置本体以及分别设置在所述装置本体上的光学准直机构1、光学分光机构2、一个光学工质耦合机构3和一个工质供给机构4，其中所述光学分光机构2设置在所述光学准直机构1的底部，所述学工质耦合机构3对应设置在所述光学分光机构2一个光束输出方向上，所述光学工质耦合机构3与所述工质供给机构4连接。As shown in Figure 1, the space debris energy conversion device based on laser propulsion provided by this embodiment includes a device body and an optical collimation mechanism 1, an optical beam splitting mechanism 2, and an optical working fluid coupling device respectively arranged on the device body. Mechanism 3 and a working fluid supply mechanism 4, wherein the optical beam splitting mechanism 2 is arranged at the bottom of the optical collimation mechanism 1, and the working fluid coupling mechanism 3 is correspondingly arranged in a beam output direction of the optical beam splitting mechanism 2 Above, the optical working medium coupling mechanism 3 is connected to the working medium supply mechanism 4 .
使用时，所述光学准直机构用于将入射激光束进行准直，并将准直后的准直激光束传输至所述光学分光机构。所述光学分光机构用于将所述准直激光束分成一个指定方向的分体激光束，并将所述分体激光束传输至所述工质耦合机构。所述工质供给机构用于向所述工质耦合机构输送固态工质。所述工质耦合机构利用所述分体激光束与所述固态工质发生烧蚀耦合，形成等离子体反喷产生推力。In use, the optical collimation mechanism is used to collimate the incident laser beam, and transmit the collimated laser beam to the optical beam splitting mechanism. The optical beam splitting mechanism is used to split the collimated laser beam into split laser beams in a specified direction, and transmit the split laser beams to the working medium coupling mechanism. The working medium supply mechanism is used to deliver solid working medium to the working medium coupling mechanism. The working fluid coupling mechanism utilizes the split laser beam to ablate and couple with the solid working fluid to form plasma blowback to generate thrust.
实施例二Embodiment two
如图2所示，本实施例提供的基于激光推进的空间碎片能量转化装置，包括装置本体以及分别设置在所述装置本体上的光学准直机构1、光学分光机构2、四个光学工质耦合机构3和四个工质供给机构4，其中所述光学分光机构2设置在所述光学准直机构1的底部，各所述光学工质耦合机构3分别对应设置在所述光学分光机构2的前、后、左、右四个光束输出方向上，各所述光学工质耦合机构3分别与各所述工质供给机构4一一对应连接。As shown in Figure 2, the space debris energy conversion device based on laser propulsion provided by this embodiment includes a device body and an optical collimation mechanism 1, an optical beam splitting mechanism 2, and four optical working fluids respectively arranged on the device body. A coupling mechanism 3 and four working fluid supply mechanisms 4, wherein the optical beam splitting mechanism 2 is arranged at the bottom of the optical collimation mechanism 1, and each of the optical working fluid coupling mechanisms 3 is respectively arranged on the optical beam splitting mechanism 2 In the four beam output directions of front, rear, left and right, each of the optical working fluid coupling mechanisms 3 is connected to each of the working fluid supply mechanisms 4 in a one-to-one correspondence.
使用时，所述光学准直机构用于将入射激光束进行准直，并将准直后的准直激光束传输至所述光学分光机构。所述光学分光机构用于将所述准直激光束分成前、后、左、右四个指定方向的分体激光束，并将所述分体激光束传输至对应的工质耦合机构。所述工质供给机构用于向所述工质耦合机构输送固态工质。所述工质耦合机构利用所述分体激光束与所述固态工质发生烧蚀耦合，形成等离子体反喷产生推力。In use, the optical collimation mechanism is used to collimate the incident laser beam, and transmit the collimated laser beam to the optical beam splitting mechanism. The optical beam splitting mechanism is used to split the collimated laser beam into split laser beams in four designated directions: front, back, left, and right, and transmit the split laser beams to the corresponding working medium coupling mechanism. The working medium supply mechanism is used to deliver solid working medium to the working medium coupling mechanism. The working fluid coupling mechanism utilizes the split laser beam to ablate and couple with the solid working fluid to form plasma blowback to generate thrust.
此外，根据实际需要，本发明所述的基于激光推进的空间碎片能量转化装置，还可以在所述光学分光机构指定的两个方向或三个方向上，对应设置两个或三个光学工质耦合机构，以及相对应的两个或三个工质供给机构。In addition, according to actual needs, the space debris energy conversion device based on laser propulsion according to the present invention can also be provided with two or three optical working fluids correspondingly in the two or three directions specified by the optical beam splitting mechanism Coupling mechanism, and corresponding two or three working fluid supply mechanisms.
如图3所示，所述光学准直机构1包括菲涅耳透镜101和聚集透镜102，所述菲涅耳透镜101用于将所述入射激光束聚焦在所述菲涅耳透镜101的焦点上，形成点光源6，所述聚集透镜102的焦点与所述菲涅耳透镜101的焦点相同，位于焦点的点光源6经过所述聚集透镜102形成平行的准直激光束。As shown in Figure 3, the optical collimation mechanism 1 includes a Fresnel lens 101 and a focusing lens 102, the Fresnel lens 101 is used to focus the incident laser beam on the focal point of the Fresnel lens 101 Above, a point light source 6 is formed, the focal point of the focusing lens 102 is the same as that of the Fresnel lens 101 , and the point light source 6 at the focal point passes through the focusing lens 102 to form a parallel collimated laser beam.
在实施例1的基础上，所述光学分光机构包括一个分光镜以及与之配合的多个反射镜，其中所述分光镜用于将所述准直激光束分成沿指定方向的分体激光束，所述反射镜用于将所述分体激光束反射至指定位置。同理，如图4所示，在实施例2的基础上，所述光学分光机构2包括四个分光镜以及多个反射镜，其中所述的四个分光镜分别为第一分光镜201、第二分光镜202、第三分光镜203和第四分光镜204，所述的第一分光镜201、第二分光镜202、第三分光镜203和第四分光镜204从上到下依次排列设置。其中所述的第一分光镜201、第二分光镜202、第三分光镜203和第四分光镜204用于将准直后的主体激光束分别分成右分体光束、左分体光束、前分体光束和后分体光束。On the basis of Embodiment 1, the optical beam splitting mechanism includes a beam splitter and a plurality of mirrors matched with it, wherein the beam splitter is used to split the collimated laser beam into split laser beams along a specified direction , the reflector is used to reflect the split laser beam to a designated position. Similarly, as shown in FIG. 4 , on the basis of Embodiment 2, the optical beam splitting mechanism 2 includes four beam splitters and a plurality of reflection mirrors, wherein the four beam splitters are respectively the first beam splitter 201, The second beam splitter 202, the third beam splitter 203 and the fourth beam splitter 204, the first beam splitter 201, the second beam splitter 202, the third beam splitter 203 and the fourth beam splitter 204 are arranged in order from top to bottom set up. The first beam splitter 201, the second beam splitter 202, the third beam splitter 203 and the fourth beam splitter 204 are used to divide the collimated main laser beam into right split beam, left split beam, front split beam, and Split beam and post-split beam.
根据需要将分体激光束反射到指定位置时，每个分光镜需要配合不同数量的反射镜，由于反射位置的不同，反射镜的布置方式也不相同。如图5所示为其中一种反射镜布置方式，通过所述反射镜205能够将所述分体激光束反射至指定位置。When reflecting the split laser beam to a designated position as required, each beam splitter needs to be matched with different numbers of mirrors, and the arrangement of the mirrors is also different due to the different reflection positions. As shown in FIG. 5 , one of the reflector arrangements is shown, and the split laser beam can be reflected to a designated position through the reflector 205 .
如图6所示，所述工质供给机构4包括行程控制器401、与所述行程控制器401连接的工质推送板402、以及工质支撑板403，其中所述行程控制器401用于控制所述工质推送板402的运动位置，所述工质推送板402用于带动固态工质7运动，所述工质支撑板403用于支撑所述固态工质7。工作时，行程控制器401控制工质推送板402向外推出固体工质，为所述工质耦合机构输送固态工质7，其中固态工质7的外端面即为激光束与固态工质作用的冲量耦合面8。As shown in Figure 6, the working medium supply mechanism 4 includes a stroke controller 401, a working medium pushing plate 402 connected to the stroke controller 401, and a working medium supporting plate 403, wherein the stroke controller 401 is used for The moving position of the working medium pushing plate 402 is controlled, the working medium pushing plate 402 is used to drive the solid working medium 7 to move, and the working medium supporting plate 403 is used to support the solid working medium 7 . When working, the stroke controller 401 controls the working medium pushing plate 402 to push out the solid working medium to deliver the solid working medium 7 to the working medium coupling mechanism, wherein the outer end surface of the solid working medium 7 is the interaction between the laser beam and the solid working medium. The impulse coupling surface 8.
所述工质耦合机构包括耦合腔体，所述耦合腔体设有分体激光束输入通道、固态工质输入通道和离子体反喷输出通道。如图7所示为所述工质耦合机构的工作原理图，其中所述工质耦合机构采用发射式烧蚀工作模式，实现工质的烧蚀，产生冲量。射式是指激光直接烧蚀固态工质产生喷射，而喷射方向与激光束方向在固态工质的同一侧。工作时，所述工质供给机构输出的固态工质通过固态工质输入通道进入到耦合腔体中，从光学分光机构输出的分体激光束通过分体激光束输入通道进入到耦合腔体中，使分体激光束直接烧蚀固态工质，形成等离子体反喷产生推力。The working medium coupling mechanism includes a coupling cavity, and the coupling cavity is provided with a split laser beam input channel, a solid working medium input channel and an ion plasma back spray output channel. FIG. 7 is a schematic diagram of the working principle of the working medium coupling mechanism, wherein the working medium coupling mechanism adopts a radiation ablation working mode to realize the ablation of the working medium and generate impulse. Injection type means that the laser directly ablates the solid working medium to produce jetting, and the jetting direction and the direction of the laser beam are on the same side of the solid working medium. When working, the solid working medium output by the working medium supply mechanism enters the coupling cavity through the solid working medium input channel, and the split laser beam output from the optical beam splitting mechanism enters the coupling cavity through the split laser beam input channel , so that the split laser beam directly ablates the solid-state working fluid, forming a plasma backspray to generate thrust.
在上述各实施例中，所述的基于激光推进的空间碎片能量转化装置还包括激光器，所述激光器用于向所述光学准直机构1发出入射激光束。In each of the above embodiments, the laser propulsion-based energy conversion device for space debris further includes a laser, and the laser is used to emit an incident laser beam to the optical collimation mechanism 1 .
在上述各实施例中，所述光学分光机构2与所述光学准直机构1通过第一卡扣结构连接，所述光学工质耦合机构3与所述工质供给机构4通过第二卡扣机构连接，结构简单，便于安装，使用方便。In each of the above-mentioned embodiments, the optical beam splitting mechanism 2 and the optical collimation mechanism 1 are connected through a first buckle structure, and the optical working medium coupling mechanism 3 and the working medium supply mechanism 4 are connected through a second buckle Mechanism connection, simple structure, easy installation and use.
本发明针对空间碎片能量转化利用需求，还提供一种基于激光推进的空间碎片能量转化方法，该方法将上述的基于激光推进的空间碎片能量转化装置安装到飞行器上。The present invention also provides a space debris energy conversion method based on laser propulsion, which installs the above-mentioned space debris energy conversion device based on laser propulsion on an aircraft.
该方法具体包括如下步骤：The method specifically includes the following steps:
第一步，将收集到的空间碎片制作为圆柱状固态工质，并将所述圆柱状固态工质加载到所述的空间碎片能量转化装置中。In the first step, the collected space debris is made into a cylindrical solid working medium, and the cylindrical solid working medium is loaded into the space debris energy conversion device.
第二步，通过激光器发射入射激光束至光学准直机构，经过所述光学准直机构完成入射激光束的准直，并将准直后的准直激光束传输到光学分光机构。In the second step, the incident laser beam is emitted to the optical collimation mechanism through the laser, the collimation of the incident laser beam is completed through the optical collimation mechanism, and the collimated collimated laser beam is transmitted to the optical beam splitting mechanism.
第三步，所述光学分光机构按需要将所述准直激光束分成至少一个方向的分体激光束，并将所述分体激光束输出至工质耦合机构。In the third step, the optical beam splitting mechanism splits the collimated laser beam into at least one split laser beam as required, and outputs the split laser beam to the working medium coupling mechanism.
若采用实施例1所述的空间碎片能量转化装置，则所述光学分光机构将所述准直激光束分成一个方向的分体激光束。If the space debris energy conversion device described in Embodiment 1 is used, the optical beam splitting mechanism splits the collimated laser beam into split laser beams in one direction.
若采用实施例2所述的空间碎片能量转化装置，则所述光学分光机构将所述准直激光束分成四个方向的分体激光束。If the space debris energy conversion device described in Embodiment 2 is used, the optical beam splitting mechanism splits the collimated laser beam into four-direction split laser beams.
第四步，通过工质供给机构将所述圆柱状固态工质推送至所述工质耦合机构，使所述圆柱状固态工质与所述分体激光束相互作用形成等离子体反喷产生推力。The fourth step is to push the cylindrical solid working medium to the working medium coupling mechanism through the working medium supply mechanism, so that the cylindrical solid working medium interacts with the split laser beam to form a plasma blowback to generate thrust .
第五步，通过所述推力直接为飞行器提供在轨动力，实现空间碎片能量的直接转化利用。The fifth step is to directly provide on-orbit power for the aircraft through the thrust, so as to realize the direct conversion and utilization of space debris energy.
综上所述，本发明实施例所述的基于激光推进的空间碎片能量转化装置及方法，基本原理是将空间碎片作为激光推进的固态工质，利用激光与收集到的空间碎片相互作用，引起空间碎片烧蚀和气化并电离形成等离子体，等离子体爆燃波压缩空间碎片表面产生推力，用于空间飞行器在轨控制，从而实现空间碎片的再利用，简化了空间碎片利用的过程，在清洁利用空间碎片的同时，实现了空间碎片的有效清除，具有结构简单，转化利用效率高，不会对空间环境造成二次污染的优点，可直接应用于空间飞行器的在轨控制。To sum up, the basic principle of the space debris energy conversion device and method based on laser propulsion described in the embodiments of the present invention is to use space debris as a solid-state working medium for laser propulsion, and use the laser to interact with the collected space debris to cause Space debris is ablated, gasified, and ionized to form plasma, and the plasma deflagration wave compresses the surface of space debris to generate thrust, which is used to control space vehicles in orbit, thereby realizing the reuse of space debris and simplifying the process of space debris utilization. At the same time, it realizes the effective removal of space debris. It has the advantages of simple structure, high conversion and utilization efficiency, and no secondary pollution to the space environment. It can be directly applied to the on-orbit control of space vehicles.
最后应说明的是：以上实施例仅用以说明本发明的技术方案，而非对其限制；尽管参照前述实施例对本发明进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本发明各实施例技术方案的精神和范围。Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: it can still be Modifications are made to the technical solutions described in the foregoing embodiments, or equivalent replacements are made to some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.
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| CN201610945812.2ACN106545478B (en) | 2016-11-02 | 2016-11-02 | A kind of space junk energy conversion device and method based on laser threat warner |
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