CN110884689A - Optical imaging satellite bottom light shield unfolding system - Google Patents
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Abstract
Description
技术领域technical field
本发明属于卫星技术领域,具体涉及一种光学成像卫星底部遮光罩展开系统。The invention belongs to the technical field of satellites, and in particular relates to an optical imaging satellite bottom hood deployment system.
背景技术Background technique
部署于地球静止轨道(GEO)的光学成像卫星可以实现对适合于对地进行长期的连续监视和快速的访问成像,卫星在GEO轨道运行工作时,会受到太阳光等杂散光的影响,轴外杂散光通过辐射进入到卫星的光学系统中来,经由主、次反射镜最终到达相机焦平面位置,就会导致卫星的光学系统目标信噪比、像面对比度下降,目标成像模糊,进而影响卫星的探测能力以及成像性能,对此,为了消除太阳光等杂光对卫星光学系统的影响,需要在卫星上加装遮光罩结构。光学主镜底部的遮光罩结构通常为圆形固定结构,遮盖于卫星主反射镜底部。Optical imaging satellites deployed in the Geostationary Orbit (GEO) can realize long-term continuous monitoring and fast access imaging suitable for the ground. When the satellite operates in the GEO orbit, it will be affected by stray light such as sunlight, and the off-axis will be affected. The stray light enters the optical system of the satellite through radiation, and finally reaches the focal plane position of the camera through the primary and secondary mirrors, which will cause the target signal-to-noise ratio and image plane contrast of the satellite's optical system to decrease, and the target image is blurred, thereby affecting the satellite. In this regard, in order to eliminate the influence of stray light such as sunlight on the satellite optical system, it is necessary to install a hood structure on the satellite. The hood structure at the bottom of the optical primary mirror is usually a circular fixed structure, covering the bottom of the satellite primary mirror.
传统卫星光学镜头底部遮光罩结构通常固定结构,而GEO高分辨率光学成像卫星,为了实现其高分辨率,其卫星主反射镜需要很大的口径,需要在发射之初进行主反射镜的分块或者折叠,并具备在轨展开能力,传统固定式遮光罩不能满足随着卫星主反射镜的折叠展开而折叠展开。The bottom hood structure of the traditional satellite optical lens is usually fixed, while the GEO high-resolution optical imaging satellite, in order to achieve its high resolution, requires a large aperture for its satellite main mirror, which needs to be divided at the beginning of the launch. Block or foldable, and have the ability to deploy on-orbit, the traditional fixed hood cannot be folded and unfolded with the folding and unfolding of the satellite main reflector.
发明内容SUMMARY OF THE INVENTION
本发明提供一种光学成像卫星底部遮光罩展开系统,利用折叠伸展机构进行在轨展开,使卫星结构尺寸满足整流罩的要求。The invention provides an optical imaging satellite bottom hood unfolding system, which utilizes a folding and stretching mechanism for on-orbit unfolding, so that the satellite structure size meets the requirements of the fairing.
本发明的技术方案,包括:The technical scheme of the present invention includes:
一种光学成像卫星,包括主次镜伸缩系统、底部遮光罩展开系统、侧面遮光罩展开系统、共形结构、光学相机和各卫星分系统,其中:An optical imaging satellite, comprising a primary and secondary mirror telescopic system, a bottom hood unfolding system, a side hood unfolding system, a conformal structure, an optical camera and each satellite subsystem, wherein:
主次镜伸缩系统,包括能够向圆周方向伸展打开的主反射镜、能够向长度方向伸长的次镜伸展臂以及安装在次镜伸展臂端部的次反射镜,次镜伸展臂与主反射镜的中心连接,并且主反射镜打开后形成内凹的球面;The primary and secondary mirror telescopic system includes a primary mirror that can be stretched and opened in the circumferential direction, a secondary mirror stretch arm that can be stretched in the length direction, and a secondary mirror installed at the end of the secondary mirror stretch arm. The secondary mirror stretch arm and the main reflector The center of the mirror is connected, and the main mirror is opened to form a concave spherical surface;
底部遮光罩展开系统,设置在主次镜伸缩系统的主反射镜的外侧,包括底部遮光罩伸展机构和安装在其上的底部遮光罩,底部遮光罩伸展机构采用折叠的方式能够向圆周方向将底部遮光罩打开,以遮蔽主反射镜;The bottom hood unfolding system is arranged on the outer side of the main reflector of the primary and secondary mirror telescopic system, and includes a bottom hood stretching mechanism and a bottom hood installed on it. The bottom hood opens to shield the main reflector;
侧面遮光罩展开系统,包括设置在次镜伸展臂的顶端的顶部伸缩套环支撑杆结构和设置在主反射镜和底部遮光罩伸展机构之间的底部折叠杆和连接在二者之间的侧面遮光罩,顶部伸缩套环支撑杆结构和底部折叠杆能够随着次镜伸展臂的伸长而向圆周方向打开,同时将侧面遮光罩拉伸并罩设在次镜伸展臂的外部;The side hood deployment system includes a top telescopic collar support rod structure arranged at the top end of the secondary mirror extension arm, a bottom folding rod arranged between the primary mirror and the bottom shade extension mechanism, and a side surface connected between the two The hood, the top telescopic collar support rod structure and the bottom folding rod can be opened in the circumferential direction with the extension of the secondary mirror extension arm, and the side visor is stretched and covered outside the secondary mirror extension arm;
共形结构,设置在次镜伸展臂的端部,将次反射镜、通信天线共心对接,其中通信天线位于次反射镜的外侧;The conformal structure is arranged at the end of the extension arm of the secondary mirror, and concentrically connects the secondary mirror and the communication antenna, wherein the communication antenna is located outside the secondary mirror;
光学相机安装在主次镜伸缩系统的次镜伸展臂内。The optical camera is installed in the secondary mirror extension arm of the primary and secondary mirror extension system.
所述卫星分系统,包括姿态控制系统、轨道控制系统、供配电系统、热控系统、数据管理系统、摄像与图像处理系统、通信系统;The satellite subsystem includes an attitude control system, an orbit control system, a power supply and distribution system, a thermal control system, a data management system, a camera and image processing system, and a communication system;
光学相机、推进系统推进剂储箱以及其他分系统通过固定结构固定在次镜伸展臂的构架单元内;The optical camera, the propellant storage tank of the propulsion system and other subsystems are fixed in the frame unit of the extension arm of the secondary mirror through the fixed structure;
卫星推进分系统的喷口安装于卫星的底部,通过六根连接于主镜底座的固定支架固定一个六边环,六边环固定于卫星推进分系统的喷口外围从而起到对喷口的固定作用;The nozzle of the satellite propulsion subsystem is installed at the bottom of the satellite, and a hexagonal ring is fixed by six fixed brackets connected to the base of the main mirror, and the hexagonal ring is fixed on the periphery of the nozzle of the satellite propulsion subsystem to fix the nozzle;
推进分系统推进剂储箱通过管路与喷口连接。The propellant storage tank of the propulsion subsystem is connected to the nozzle through a pipeline.
其中的主次镜伸缩系统:Among them, the primary and secondary mirror telescopic system:
主反射镜包括主镜底座、通过电机驱动的可自锁关节均匀铰接在主镜底座圆周上的若干个间隔布置的主镜支撑骨架和镜面薄膜牵引骨架、连接在主镜支撑骨架和镜面薄膜牵引骨架上的光学主反射镜薄膜、以及控制主镜支撑骨架和/或镜面薄膜牵引骨架运动的电机。The main reflector includes a main mirror base, a number of spaced-arranged main mirror support frames and mirror film traction frames that are evenly articulated on the circumference of the main mirror base by self-locking joints driven by motors, and connected to the main mirror support frame and mirror film traction frame. The optical main mirror film on the frame, and the motor for controlling the movement of the main mirror support frame and/or the mirror film traction frame.
主镜支撑骨架和镜面薄膜牵引骨架分别设有个。The main mirror support frame and the mirror film traction frame are respectively provided with two.
光学主反射镜薄膜可以是整体环形的薄膜,主镜支撑骨架和镜面薄膜牵引骨架粘接在光学主反射镜薄膜的表面;也可以是扇形结构设计,光学主反射镜薄膜的两侧边分别与相邻的主镜支撑骨架和镜面薄膜牵引骨架连接。The optical main mirror film can be an integral annular film, and the main mirror support frame and the mirror film traction frame are bonded to the surface of the optical main mirror film; it can also be a fan-shaped structure design, and the two sides of the optical main mirror film are respectively The adjacent main mirror support frame and the mirror film traction frame are connected.
光学主反射镜薄膜材料为聚偏氟乙烯制成的压电材料镜片。The optical primary mirror film material is a piezoelectric material lens made of polyvinylidene fluoride.
主反射镜收缩的状态下,光学主反射镜薄膜呈锯齿形折叠收纳。When the main mirror is retracted, the optical main mirror film is folded and stored in a zigzag shape.
次镜伸展臂由多个构架单元组成,每个构架单元的两端为三角形框架构造,中间为可向内侧折叠收纳的横向杆件,横向杆件的中间位置设置有能够折弯的弯曲套筒,在两端的三角形框架之间通过斜拉的弹簧连接。The secondary mirror extension arm is composed of a plurality of frame units. Both ends of each frame unit are triangular frame structures. The middle is a transverse rod that can be folded and stored inward. The middle position of the transverse rod is provided with a bending sleeve that can be bent. , connected by inclined springs between the triangular frames at both ends.
可自锁关节利用伺服电机驱动蜗杆转动,蜗杆转动驱动与蜗杆啮合的涡轮转动。The self-locking joint uses a servo motor to drive the worm to rotate, and the worm rotates to drive the turbine meshed with the worm to rotate.
次镜伸展臂发射前呈折叠状态安装于整流罩中,整流罩内的安装结构给次镜伸展臂以约束力。The extension arm of the secondary mirror is installed in the fairing in a folded state before launching, and the installation structure in the fairing provides a binding force to the extension arm of the secondary mirror.
光学系统次反射镜是有一定厚度的抛物曲面形薄壁结构件。The sub-reflector of the optical system is a parabolic thin-walled structure with a certain thickness.
其中的共形结构:Among the conformal structures:
次反射镜、通信天线对接连接后,通信天线的曲率半径小于次反射镜的曲率半径,在二者的非连接位置之间形成的空隙内均匀设置有六个固定支撑架,固定支撑架呈梯形结构,且其两侧边具有与对应的连接面配合的弧度。After the sub-reflector and the communication antenna are butt-connected, the radius of curvature of the communication antenna is smaller than that of the sub-reflector, and six fixed supports are evenly arranged in the gap formed between the non-connected positions of the two, and the fixed supports are trapezoidal structure, and its two sides have radians matched with the corresponding connecting surfaces.
固定支撑架上与通信天线馈源支撑结构连接,通信天线馈源支撑结构通过三角支撑的方式与通信天线馈源固定连接,使通信天线馈源位于通信天线的焦点处。The fixed support frame is connected with the communication antenna feed support structure, and the communication antenna feed support structure is fixedly connected with the communication antenna feed by means of triangular support, so that the communication antenna feed is located at the focus of the communication antenna.
次反射镜的外侧表面中心设有光学系统次反射镜固定结构,用于与次镜伸展臂连接。The center of the outer surface of the secondary mirror is provided with a secondary mirror fixing structure of the optical system, which is used for connecting with the extension arm of the secondary mirror.
光学系统次反射镜固定结构为环状或者多边形形状的凸台。The fixing structure of the sub-reflector of the optical system is a ring-shaped or polygonal boss.
光学系统次反射镜、通信天线采用碳纤维复合材料,同时光学系统次反射镜的薄壁底面镀上一层铝膜。The sub-reflector of the optical system and the communication antenna are made of carbon fiber composite materials, and the thin-walled bottom surface of the sub-reflector of the optical system is coated with a layer of aluminum film.
次反射镜与通信天线采用相同的口径大小。The secondary reflector adopts the same aperture size as the communication antenna.
其中的侧面遮光罩展开系统:Among them the side hood deployment system:
底部折叠杆主要包括折叠杆上段和折叠杆下段与折叠杆固定段,以及电机驱动的可自锁关节,折叠杆下段的非铰接端与侧面遮光罩固定连接,折叠杆上段和折叠杆下段折叠收纳在一起之后向折叠杆固定段内侧垂直折叠。The bottom folding rod mainly includes the upper section of the folding rod, the lower section of the folding rod and the fixed section of the folding rod, and the self-locking joint driven by the motor. After they are together, fold them vertically to the inside of the fixed section of the folding rod.
顶部伸缩套环支撑杆结构包括固定套环、伸缩套环、丝杠导轨、滚珠套筒、支撑杆、支撑臂、铰、支撑杆固定端、导轨固定三角,固定套环固定连接在次镜伸展臂的端部,丝杠导轨纵向与固定套环连接,伸缩套环能够滑动的连接在丝杠导轨上以使其能够沿着丝杠导轨滑动,铰凸伸设置在固定讨还上,每个铰与一个支撑杆连接,支撑杆与侧面遮光罩连接,每个支撑杆的中部与一个支撑臂的一端铰接,支撑臂的另一端与伸缩套环铰接,并且支撑臂的长度大于支撑杆的交接位置到铰之间的长度但小于支撑杆的长度。The top telescopic collar support rod structure includes a fixed collar, a telescopic collar, a lead screw guide, a ball sleeve, a support rod, a support arm, a hinge, a support rod fixed end, and a guide rail fixed triangle. The fixed collar is fixedly connected to the secondary mirror extension. At the end of the arm, the lead screw guide is longitudinally connected to the fixed collar, the telescopic collar can be slidably connected to the lead screw guide so that it can slide along the lead screw guide, and the hinge protrusion is arranged on the fixed return. It is connected with a support rod, the support rod is connected with the side hood, the middle part of each support rod is hinged with one end of a support arm, the other end of the support arm is hinged with the telescopic collar, and the length of the support arm is greater than the connecting position of the support rod The length to the hinge but less than the length of the support rod.
丝杠导轨的底端与三角形的导轨固定三角连接。The bottom end of the screw guide is connected with the triangular guide fixed triangle.
丝杠导轨由丝杠、丝杠安装座、步进电机组成,丝杆安装座顶端与固定套环固连,底部与导轨固定三角固连,步进电机安装于丝杆安装座内并驱动丝杠在丝杠安装座内转动。The screw guide is composed of a screw, a screw mounting seat, and a stepping motor. The top of the screw mounting seat is fixedly connected with the fixing collar, and the bottom is fixed with the guide rail fixing triangle. The stepping motor is installed in the screw mounting seat and drives the screw. The screw rotates in the lead screw mount.
支撑杆的端部设置有度弯折,用于与侧面遮光罩连接。The end of the support rod is provided with a degree of bending for connecting with the side visor.
所述侧面遮光罩采用柔性太阳能电池片,太阳能电池片用于为卫星的供电系统供电。The side sunshade adopts flexible solar cells, and the solar cells are used to supply power to the power supply system of the satellite.
其中的底部遮光罩展开系统:One of the bottom hood deployment systems:
底部遮光罩伸展机构,设置在主镜底座的外侧,包括带齿圈环形导轨、设置在带齿圈环形导轨上的导轨滑块、电机驱动的可自锁关节、连接在导轨滑块上的底部遮光罩伸展臂。The bottom hood extension mechanism is arranged on the outer side of the main mirror base, and includes a ring-shaped guide rail with a gear ring, a guide rail slider set on the ring gear ring guide rail, a motor-driven self-locking joint, and a bottom part connected to the guide rail slider. Hood extension arm.
底部遮光罩伸展臂中是空槽结构,槽内堆叠有镀铝聚酰亚胺薄膜。The extending arm of the bottom light shield has an empty groove structure, and aluminized polyimide films are stacked in the groove.
底部遮光罩采用镀铝聚酰亚胺薄膜或者柔性太阳能电池片。The bottom hood is made of aluminized polyimide film or flexible solar cells.
所述底部遮光罩被收纳在底部遮光罩伸展臂侧面的槽中。The bottom shade is received in a slot on the side of the extension arm of the bottom shade.
主镜底座内部设置有固定式遮光罩。A fixed hood is arranged inside the base of the main mirror.
主镜底座内设置有指向中心的多个固定支架,固定支架均与推进系统推进剂箱的喷口固定连接。The base of the main mirror is provided with a plurality of fixing brackets pointing to the center, and the fixing brackets are all fixedly connected with the spout of the propellant tank of the propulsion system.
可自锁关节利用伺服电机驱动蜗杆转动,蜗杆转动驱动与蜗杆啮合的涡轮转动。The self-locking joint uses a servo motor to drive the worm to rotate, and the worm rotates to drive the turbine meshed with the worm to rotate.
本发明的其它特征和优点将在随后的说明书中阐述,并且,部分地从说明书中变得显而易见,或者通过实施本发明而了解。Other features and advantages of the present invention will be set forth in the description which follows, and in part will be apparent from the description, or may be learned by practice of the invention.
下面通过附图和实施例,对本发明的技术方案做进一步的详细描述。The technical solutions of the present invention will be further described in detail below through the accompanying drawings and embodiments.
附图说明Description of drawings
图1为GEO高分辨率反射式光学成像卫星的使用状态示意图。Figure 1 is a schematic diagram of the use state of the GEO high-resolution reflective optical imaging satellite.
图2为省略遮光罩的GEO高分辨率反射式光学成像卫星的使用状态示意图。FIG. 2 is a schematic diagram of the use state of the GEO high-resolution reflective optical imaging satellite without the light shield.
图3为GEO高分辨率反射式光学成像卫星的收缩状态示意图。Figure 3 is a schematic diagram of the retracted state of the GEO high-resolution reflective optical imaging satellite.
图4为主反射镜的折叠状态示意图。FIG. 4 is a schematic diagram of the folded state of the main mirror.
图5为主反射镜的打开状态示意图。FIG. 5 is a schematic diagram of an open state of the main mirror.
图6为次反射镜与通信天线的共形结构的结构图。FIG. 6 is a structural diagram of the conformal structure of the sub-reflector and the communication antenna.
图7为次反射镜与通信天线的共形结构的剖视结构图。FIG. 7 is a cross-sectional structural view of the conformal structure of the sub-reflector and the communication antenna.
图8为次反射镜与通信天线的共形结构的底视结构图。FIG. 8 is a bottom view structural diagram of the conformal structure of the sub-reflector and the communication antenna.
图9为次镜伸展臂的结构单元示意图。FIG. 9 is a schematic diagram of the structural unit of the extension arm of the secondary mirror.
图10为次镜伸展臂的结构单元示意图。FIG. 10 is a schematic diagram of the structural unit of the extension arm of the secondary mirror.
图11为次镜伸展臂的结构单元示意图。FIG. 11 is a schematic diagram of the structural unit of the extension arm of the secondary mirror.
图12为卫星各分系统组装示意图。Figure 12 is a schematic diagram of the assembly of each sub-system of the satellite.
图13为卫星推进剂储箱与主镜底座的连接示意图。Figure 13 is a schematic diagram of the connection between the satellite propellant storage tank and the base of the primary mirror.
图14为遮光罩伸展机构的收缩状态示意图。FIG. 14 is a schematic diagram of the retracted state of the extension mechanism of the light shield.
图15为遮光罩伸展机构的伸展状态示意图。FIG. 15 is a schematic diagram of the extended state of the hood extending mechanism.
图16为顶部伸缩套环支撑杆的收缩状态示意图。Figure 16 is a schematic diagram of the retracted state of the top telescopic collar support rod.
图17为顶部伸缩套环支撑杆的打开状态示意图。FIG. 17 is a schematic diagram of the open state of the top telescopic collar support rod.
图18为丝杠导轨结构示意图。FIG. 18 is a schematic diagram of the structure of the screw guide rail.
图19为底部遮光罩伸展机构的收缩状态示意图。FIG. 19 is a schematic diagram of the retracted state of the bottom light shield extension mechanism.
图20为底部遮光罩伸展机构的打开状态示意图。FIG. 20 is a schematic view of the open state of the bottom light shield extension mechanism.
图21为主镜底座的结构示意图。Figure 21 is a schematic diagram of the structure of the main mirror base.
图22为光学系统次反射镜的结构示意图。FIG. 22 is a schematic structural diagram of a secondary mirror of an optical system.
图中:In the picture:
1、主反射镜;2、共形结构;3、光学相机;4、次镜伸展臂;5、侧面遮光罩;6、底部折叠杆;7、顶部伸缩套环支撑杆结构;8、底部遮光罩;9、底部遮光罩伸展机构;10、卫星分系统;11、光学主反射镜薄膜;12、主镜支撑骨架;13、镜面薄膜牵引骨架;14、主镜底座;15、可自锁关节;14A、外接圆环;14B、主梁;1. Main reflector; 2. Conformal structure; 3. Optical camera; 4. Extending arm of secondary mirror; 5. Side hood; 6. Bottom folding rod; 7. Top telescopic collar support rod structure; 8. Bottom shading Cover; 9. Bottom hood stretching mechanism; 10. Satellite subsystem; 11. Optical main mirror film; 12. Main mirror support frame; 13. Mirror film traction frame; 14. Main mirror base; 15. Self-locking joint ; 14A, circumscribed ring; 14B, main beam;
21、光学系统次反射镜;22、通信天线;23、通信天线馈源;24、通信天线馈源支撑结构;25、固定支撑架;26、光学系统次反射镜固定结构;21. Optical system sub-reflector; 22. Communication antenna; 23. Communication antenna feed; 24. Communication antenna feed support structure; 25. Fixed support frame; 26. Optical system sub-reflector fixed structure;
41、构架单元;41A、纵向杆件;41B、横向杆件;41C、扭簧;41D、球铰;41E、弹簧;41. Frame unit; 41A, longitudinal rod; 41B, transverse rod; 41C, torsion spring; 41D, ball hinge; 41E, spring;
61、折叠杆上段;62、折叠杆下段;63、折叠杆固定段;64、可自锁关节;65、可自锁关节;61. Upper section of folding rod; 62. Lower section of folding rod; 63. Fixed section of folding rod; 64. Self-locking joint; 65. Self-locking joint;
71、固定套环;72、伸缩套环;73、丝杠导轨;731、丝杠;732、导轨安装座;733、步进电机;74、滚珠套筒;75、支撑杆;76、支撑臂;77、铰;78、支撑杆固定端;79、导轨固定三角;71, fixed collar; 72, telescopic collar; 73, lead screw guide; 731, lead screw; 732, guide rail mounting seat; 733, stepper motor; 74, ball sleeve; 75, support rod; 76, support arm ;77, hinge; 78, fixed end of support rod; 79, fixed triangle of guide rail;
81、主镜底座外围的遮光罩;81. The hood on the periphery of the main mirror base;
91、带齿圈环形导轨;92、导轨滑块;93、可自锁关节;94、底部遮光罩伸展臂;91. Ring-shaped guide rail with gear ring; 92. Guide rail slider; 93. Self-locking joint; 94. Bottom hood extension arm;
101、喷口;102、推进系统推进剂箱;103、其他分系统;104、固定支架;105、六边环;106、固定结构。101, the nozzle; 102, the propellant tank of the propulsion system; 103, other sub-systems; 104, the fixed bracket; 105, the hexagonal ring; 106, the fixed structure.
具体实施方式Detailed ways
为使本发明的目的、技术方案和优点更加清楚,下面将结合本发明具体实施例及相应的附图对本发明技术方案进行清楚、完整地描述。显然,所描述的实施例仅是本发明一部分实施例,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 objectives, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the specific embodiments of the present invention and the corresponding drawings. Obviously, the described embodiments are only some, but not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.
本发明的GEO高分辨率反射式光学成像卫星,如图1和2所示,由卫星光学系统主反射镜1、光学系统次反射镜21与通信天线22的共形结构2、光学相机3、次镜伸展臂4、侧面遮光罩5、底部折叠杆6、顶部伸缩套环支撑杆结构7、底部遮光罩8、底部遮光罩伸展机构9以及卫星分系统10组成。The GEO high-resolution reflective optical imaging satellite of the present invention, as shown in Figures 1 and 2, consists of a satellite optical system
其中,主反射镜1、次镜伸展臂4和次反射镜21组成了主次镜伸缩系统,主反射镜1能够向圆周方向伸展打开,次镜伸展臂4能够向长度方向伸长,次反射镜21安装在次镜伸展臂4的端部,次镜伸展臂4与主反射镜1的中心连接,并且主反射镜1打开后形成内凹的球面。Among them, the
底部遮光罩8、底部遮光罩伸展机构9组成了底部遮光罩展开系统,设置在主次镜伸缩系统的主反射镜1的外侧。底部遮光罩伸展机构9采用折叠的方式能够向圆周方向将底部遮光罩8打开,以遮蔽主反射镜。The bottom hood 8 and the bottom
共形结构2设置在次镜伸展臂4的端部,将次反射镜21、通信天线22共心对接,其中通信天线22位于次反射镜21的外侧。The
光学相机3安装在主次镜伸缩系统的次镜伸展臂4内。The
如图3所示,为了减小卫星体积,GEO高分辨率反射式光学成像卫星在发射前是折叠压缩状态。所设计的GEO高分辨率反射式光学成像卫星能够实现对地2m超高分辨率所需的光学系统主反射镜1口径为12m、曲率半径144m;光学系统次反射镜口径4.2m、曲率半径143.9m;主镜与次镜间距离46.8m;焦点与主镜顶点间的距离8.02m,这些参数可以根据分辨率的选择而变化。As shown in Figure 3, in order to reduce the volume of the satellite, the GEO high-resolution reflective optical imaging satellite is in a folded and compressed state before launch. The designed GEO high-resolution reflective optical imaging satellite can realize the ultra-high resolution of 2m above the ground. The
关于主反射镜、次反射镜伸缩系统:About the main reflector and the secondary reflector telescopic system:
卫星在发射之前呈压缩状态,如图4所示,卫星光学系统主反射镜1折叠。卫星光学主反射镜1采用薄膜展开式设计,将24块扇形光学主反射镜薄膜11以12根主镜支撑骨架12和12根镜面薄膜牵引骨架13支撑,12根主镜支撑骨架12和12根镜面薄膜牵引骨架13均为有一定曲率的弯形肋板,并与主镜底座14利用24个电机驱动的可自锁关节15连接。可自锁关节利用伺服电机驱动蜗杆转动,蜗杆转动驱动与蜗杆啮合的涡轮转动,通过蜗杆的导程角小于啮合接触的摩擦角的设计实现关节自锁功能。卫星发射入轨后,通过主镜支撑骨架12底部安装的24个电机驱动12根主镜支撑骨架12和12根镜面薄膜牵引骨架13绕电机驱动的可自锁关节15运动,将光学主反射镜薄11展开,主反射镜薄11展开完全展开后电机停止工作,展开后光学主反射镜1结构如图5所示。The satellite is in a compressed state before launch, as shown in Figure 4, the
主镜底座14由等边12边环作为承力机构,为主镜的24根骨架向中间聚拢折叠留出预定空间。在主镜底座14的12边环的顶点处伸出12根主镜支撑骨架12,同时在12边环的每个边长中点处伸出12根镜面薄膜牵引骨架13。24根骨架及主镜底座14共同组成主镜1的主体结构,并通过电机驱动的可自锁关节15进行主镜1的折叠展开。此外,12根主镜支撑骨架12和12根镜面薄膜牵引骨架13交汇处设计一个圆孔,为轨控分系统的管道布置预留空间。主镜支撑骨架12与镜面薄膜牵引骨架13间与光学主反射镜薄膜11固定连接。光学主反射镜薄膜11材料为聚偏氟乙烯制成的压电材料镜片,在计算机控制的电子枪扫描之下快速改变形状。这种轻型的薄膜结构,经过折叠发射、在轨展开后,通过电子枪控制镜面成形误差不超过2.5×10-5mm,并且所使用的压电材料聚偏氟乙烯密度不超过1kg/m,很大程度上地满足了卫星主镜的设计要求。The
次反射镜结构由次反射镜21、光学系统次反射镜固定结构22组成,如图21所示。光学系统次反射镜21是有一定厚度的抛物曲面形薄壁结构件,根据次反射镜的设计参数可知曲面的曲率半径为143.9m。次反射镜21与光学系统次反射镜固定结构22固定连接。光学系统次反射镜固定结构22为12边环结构。同时光学系统次反射镜21的薄壁底面镀上一层铝膜以实现对光的反射。The sub-reflector structure consists of a sub-reflector 21 and a
GEO高分辨率光学卫星发射入轨后,光学系统主反射镜1与光学系统次反射镜21间距需要达到数十米才能满足卫星的光学系统2m分辨率的成像要求。而此高度的卫星无法利用火箭运载一次发射入轨,因此需要在光学系统主反射镜1与光学系统次反射镜21间加入可折叠展开式的次镜伸展臂4,以满足卫星的在轨工作要求。次镜伸展臂发射前呈折叠状态安装于整流罩中,整流罩内的安装结构给次镜伸展臂以约束力(例如:将折叠状态的次镜伸展臂的两端设置一个可打开的锁紧连杆,该锁紧连杆可通过电机控制打开),使其不展开,卫星飞离整流罩后,约束力解锁后消失,扭簧的弹性势能使次镜伸展臂在无重力状态下一节节展开。After the GEO high-resolution optical satellite is launched into orbit, the distance between the
如图9所示,次镜伸展臂4由多个构架单元41组成。构架单元由纵向杆件41A、横向杆件41B、弯曲套筒41C、球铰41D、弹簧41E等部件组成。3个薄壁条状纵向杆件41A首位固连形成刚性三角形平面,以达到良好的支撑稳定性,同时相比于四边形结构所用材料更少、结构更轻;3根横向杆件41A与刚性三角形平面利用球铰41D连接形成矩形,并在每个矩形对角点处固定有弹簧41E,在横向杆件中点处利用弯曲套筒41C连接。As shown in FIG. 9 , the secondary
如图10所示,卫星未发射入轨前,构架单元41呈压缩状态。向杆件41B通过中间高刚度扭簧41C向纵向杆件41A形成的刚性三角形平面质心对折,高刚度扭簧41C变形储藏弹性势能在上下两杆位于直线时无弹性势能,同时横向杆件41B与纵向杆件41A铰接形成的矩形平面对角处所安弹簧41E被压缩(设定弹簧41E在横向杆件41B位于直线时无弹性势能,即此时的弹簧41E不存在弹力作用);当卫星在轨运行时约束力消失,高刚度扭簧41C及压缩弹簧41E所储存的弹性势能转变为动能,使整个次镜伸展臂4张开,如图11所示。多个构架单元41共用刚性三角形形成次镜伸展臂4。As shown in FIG. 10 , before the satellite is launched into orbit, the frame unit 41 is in a compressed state. The
本发明具有以下特点:The present invention has the following characteristics:
1、双反光学成像系统的光路设计实现了主反射镜与次反射镜位于主反射镜焦点同侧,物、像分别位于次反射镜两侧,减少了光路的实际长度。1. The optical path design of the double-mirror optical imaging system realizes that the primary reflector and the secondary reflector are located on the same side of the focal point of the primary reflector, and the object and image are located on both sides of the secondary reflector, reducing the actual length of the optical path.
2、地球静止轨道2m分辨率的光学系统主次反射镜参数设计。2. Parameter design of the primary and secondary mirrors of the optical system with a resolution of 2 m in the geostationary orbit.
3、地球静止轨道2m分辨率的光学系统的次反射镜伸展臂的折叠机构设计。3. The folding mechanism design of the extension arm of the secondary mirror of the optical system with a resolution of 2m in the geostationary orbit.
4、GEO光学成像卫星的可折叠展式开薄膜主反射镜由扇形光学主反射镜薄膜、主镜支撑骨架、镜面薄膜牵引骨架、主镜底座、电机驱动的可自锁关节组成。4. The foldable and unfoldable film main reflector of GEO optical imaging satellite is composed of a fan-shaped optical main reflector film, a main mirror support frame, a mirror film traction frame, a main mirror base, and a motor-driven self-locking joint.
5、主镜支撑骨架、镜面薄膜牵引骨架均为带有一定曲率的弯形肋板。5. The main mirror support frame and the mirror film traction frame are curved rib plates with a certain curvature.
6、GEO高分辨率光学的卫星的主反射镜在入轨之前是折叠状态、入轨之后展开。6. The main mirror of the GEO high-resolution optical satellite is folded before entering orbit, and unfolded after entering orbit.
7、利用电机驱动主镜支撑骨架、镜面薄膜牵引骨架通过电机驱动的可自锁关节的转动牵引薄膜式主镜折叠与展开。7. Use the motor to drive the main mirror support frame and the mirror film traction frame to fold and unfold the film-type main mirror through the rotation of the self-locking joint driven by the motor.
8、光学主反射镜薄膜材料为聚偏氟乙烯制成的压电材料镜片,利用电子枪控制镜面成形误差。8. The film material of the optical main reflector is a piezoelectric material lens made of polyvinylidene fluoride, and the mirror surface forming error is controlled by an electron gun.
9、主镜底座、主镜支撑骨架与镜面薄膜牵引骨架利用碳纤维材料。9. The main mirror base, main mirror support frame and mirror film traction frame are made of carbon fiber material.
本发明的效果Effects of the present invention
1、利用反射式光学成像系统实现了静止轨道2m高分辨成像,并且不存在色差;1. Using the reflective optical imaging system to achieve high-resolution imaging of 2m stationary orbit, and there is no chromatic aberration;
2、使主反射镜与次反射镜位于主反射镜焦点同侧减少了光路的实际长度;2. The actual length of the optical path is reduced by placing the primary reflector and the secondary reflector on the same side of the focal point of the primary reflector;
3、使物、像分别位于次反射镜两侧了降低制作工艺难度;3. The object and the image are located on both sides of the secondary mirror to reduce the difficulty of the manufacturing process;
5、设计了GEO光学成像卫星的可折叠展开式薄膜主反射镜,利用薄膜支撑骨架牵引薄膜,使其在卫星入轨之前呈折叠状态,大幅压缩了卫星的整体尺寸,折叠后可以直接放入卫星整流罩中;5. The foldable and unfoldable film main reflector of the GEO optical imaging satellite is designed. The film is used to support the skeleton to pull the film so that it is in a folded state before the satellite enters orbit, which greatly compresses the overall size of the satellite. After folding, it can be directly put into in the satellite fairing;
6、卫星采用的柔性薄膜材料作为主反射镜的材料,避免了刚性材料的使用,大幅降低了整个卫星的结构重量,使卫星在现有条件下可以实现一次入轨。6. The flexible film material used in the satellite is used as the material of the main reflector, which avoids the use of rigid materials, greatly reduces the structural weight of the entire satellite, and enables the satellite to enter orbit once under the existing conditions.
关于共形结构2:Regarding conformal structure 2:
卫星工作时,光学系统主反射镜1反射的光经光学系统次反射镜21进行二次反射。同时为保持卫星在GEO轨道与地面的有效通信,需要在卫星上加装通信天线。而为了最大程度的利用卫星现有结构,减少卫星零部件。如图6所示,卫星次反射镜与通信天线的共形结构由光学系统次反射镜21、通信天线22、通信天线馈源23、通信天线馈源支撑结构24、固定支撑架25以及光学系统次反射镜固定结构26组成。When the satellite is in operation, the light reflected by the
如图7为卫星次反射镜与通信天线的共形结构的剖视图,光学系统次反射镜21与通信天线22是两个口径相同、曲率不同的抛物曲面形薄壁结构件,两薄壁底部重合,并与光学系统次反射镜固定结构25固定连接。通常地,次反射镜21、通信天线22对接连接后,通信天线22的曲率半径小于次反射镜21的曲率半径,在二者的非连接位置之间形成的空隙内均匀设置有六个固定支撑架25,固定支撑架25呈梯形结构,且其两侧边具有与对应的连接面配合的弧度。如图8所示,光学系统次反射镜固定支撑架25为12边环结构,与光学系统次反射镜21固定连接,与光学系统次反射镜21连接的端面具有与光学系统次反射镜21相同的曲率,使其更好的支撑光学系统次反射镜21。光学系统次反射镜固定支撑架25与GEO光学卫星的次反射镜伸展臂4固定连接。FIG. 7 is a cross-sectional view of the conformal structure of the satellite sub-reflector and the communication antenna. The
光学系统次反射镜21与通信天线22利用固定支撑架25进行支撑,确保结构的稳定度和结构强度。固定支架25为由一定厚度的四边形支架,上下两边具有与两结构贴合的曲线并分别与光学系统次反射镜21、通信天线22焊接固定,左右两边为竖直的支撑梁结构。在光学系统次反射镜21于通信天线22之间均为分布六个固定支撑架25。The
每隔两个固定支撑架25上固定一根杆状通信天线馈源支撑结构24并向通信天线22的焦点处伸出,三根通信天线馈源支撑结构24连接通信天线馈源23,使通信天线馈源23位于通信天线22的焦点处,从而实现卫星与地面间的通信。光学系统次反射镜21、通信天线22采用碳纤维复合材料,同时光学系统次反射镜21的薄壁底面镀上一层铝膜以实现对光的反射。A rod-shaped communication antenna
光学系统次反射镜固定结构26为环状或者多边形形状的凸台。The optical system
本发明具有以下特点:The present invention has the following characteristics:
1.共形结构由光学系统次反射镜与通信天线的两个曲率不同的抛物曲面形薄壁结构件组成,承担反射光线和通信的双重功能。1. The conformal structure is composed of two parabolic thin-walled structural members with different curvatures of the sub-reflector of the optical system and the communication antenna, which undertakes the dual functions of reflecting light and communication.
2.光学系统次反射镜与通信天线的两薄壁结构底部重合,中间利用固定结构支撑保证结构强度与稳定性。2. The sub-reflector of the optical system is overlapped with the bottom of the two thin-walled structures of the communication antenna, and the middle is supported by a fixed structure to ensure the structural strength and stability.
3.通信天线薄壁结构边缘处均匀伸出三根杆状通信天线馈源支撑结构连接通信天线馈源,使通信天线馈源位于通信天线的焦点处。3. Three rod-shaped communication antenna feed support structures are evenly extended from the edge of the thin-walled structure of the communication antenna to connect the communication antenna feed, so that the communication antenna feed is located at the focus of the communication antenna.
4.光学系统次反射镜与通信天线采用相同的口径大小,并且采用堆叠安装的方式减小了卫星的体积。4. The sub-reflector of the optical system and the communication antenna use the same aperture size, and the volume of the satellite is reduced by stacking installation.
5.光学系统次反射镜的薄壁底面镀一层铝膜以实现对光的反射。5. The thin-walled bottom surface of the sub-reflector of the optical system is coated with an aluminum film to reflect light.
本实施例进行了光学系统次反射镜与通信天线的共形设计。通过卫星次反射镜行使双重功能,当GEO光学成像卫星对地进行光学成像时,卫星次反射镜凹面朝向地面作为抛物面天线与地面进行通信,同时次反射镜凸面作为卫星光学系统的次反射镜,汇聚主镜反射光线进行光学反射。最大程度的利用卫星现有结构,减少卫星零部件,压缩了光学卫星的体积。In this embodiment, the conformal design of the sub-reflector of the optical system and the communication antenna is carried out. The satellite sub-reflector performs dual functions. When the GEO optical imaging satellite performs optical imaging on the ground, the concave surface of the satellite sub-reflector faces the ground as a parabolic antenna to communicate with the ground, while the convex surface of the sub-reflector serves as the satellite optical system. The light reflected by the primary mirror is concentrated for optical reflection. The existing structure of the satellite is used to the greatest extent, the satellite parts are reduced, and the volume of the optical satellite is compressed.
如图12所示,卫星在分系统的设计上采用了分布式的设计思想,通过将卫星主体作为载荷平台,使卫星分系统10安插其中,卫星各分系统分别是:姿态控制系统、轨道控制系统、供配电系统、热控系统、数据管理系统、摄像与图像处理系统、通信系统,这些控制系统均可以采用目前卫星通用的系统进行配置。如图10所示,光学相机3、推进系统推进剂储箱102以及其他分系统103通过固定结构106固定在次镜伸展臂4的构架单元41内,这些构架单元41无弯曲套筒41C,在卫星入轨前不折叠。各分系统的结构形状与安装固定位置可以根据任务进行具体的设计和安装。卫星推进分系统的喷口101安装于卫星的底部,通过六根连接于主镜底座14的固定支架104固定一个六边环105,六边环105固定于卫星推进分系统的喷口101外围从而起到对喷口101的固定作用。推进分系统推进剂储箱102通过管路与喷口101连接。分系统的设计上采用的分布式的设计思想革新了传统卫星平台-载荷的设计思路,打破了传统卫星的平台限制,实现了分系统-主体骨架的柔性化设计,减小了卫星整体所需的空间与重量。As shown in Figure 12, the satellite adopts the distributed design idea in the design of the sub-system. By using the main body of the satellite as the load platform, the
如图13所示,为保证次镜伸展臂4同卫星光学系统主反射镜1间的连接满足承力要求,卫星推进分系统推进剂储箱102所在的构建单元的刚性三角形为基准,浇筑出外接圆环14A以连接伸卫星光学系统主反射镜1支架,圆环与主镜的24根骨架均接触固定连接,能实现均匀承力。同时在主镜底座14的12边环处伸出3根主梁14B同外接圆环14A上的刚性三角形顶点进行固定连接,完成整个次镜伸展臂4同卫星光学系统主反射镜1连接处的承力结构设计。As shown in FIG. 13 , in order to ensure that the connection between the secondary
关于侧面遮光罩展开系统:About the side hood deployment system:
如图1、2所示,为了为了消除太阳光等杂光对卫星光学系统的影响,需要在卫星上加装遮光罩结构。遮光罩系统包括侧面遮光罩5与底部遮光罩8。侧面遮光罩5利用底部折叠杆6、顶部伸缩套环支撑杆结构7支撑。底部折叠杆6的作用是固定侧面遮光罩5的下端,总共六根。当卫星进行在轨展开时,协同顶部伸缩套环支撑杆7将侧面遮光罩5伸展开,如图14所示,底部折叠杆6为分段式结构。As shown in Figures 1 and 2, in order to eliminate the influence of stray light such as sunlight on the satellite optical system, it is necessary to install a light hood structure on the satellite. The hood system includes a
如图15所示,底部折叠杆6主要包括折叠杆上段61和折叠杆下段62与折叠杆固定段63,以及折叠杆上段61和折叠杆下段62之间的电机驱动的可自锁关节64、折叠杆上段61和折叠杆固定段63之间的电机驱动的可自锁关节65,折叠杆上段61和折叠杆下段62折叠收纳在一起之后向折叠杆固定段63内侧垂直折叠。为保证在折叠时,底部折叠杆6不接触卫星光学系统主反射镜1,首先从主镜底座14上伸出一定距离折叠杆固定段63,折叠杆固定段63与折叠杆上段61利用电机驱动的可自锁关节64连接,采用反折结构,折叠杆固定段63向上垂直折叠,与折叠杆下段62之间以电机驱动的可自锁关节65连接;折叠杆下段62向下垂直折叠。折叠杆下段62的非铰接端与侧面遮光罩5固定连接。As shown in FIG. 15 , the
如图16所示。当卫星在轨展开时,则带动周部遮光布展开,形成完整折叠杆,从而在卫星底部形成牵引遮光布的支撑结构。As shown in Figure 16. When the satellite is deployed in orbit, the peripheral shading cloth is driven to expand to form a complete folding rod, thereby forming a support structure for pulling the shading cloth at the bottom of the satellite.
顶部伸缩套环支撑杆7的作用是协同底部折叠杆6将侧面遮光罩5伸展开,如图17所示,顶部伸缩套环支撑杆7结构包括固定套环71、伸缩套环72、丝杠导轨73、滚珠套筒74、支撑杆75、支撑臂76、铰77、支撑杆固定端78,导轨固定三角79。固定套环71固定连接在次镜伸展臂4的端部,丝杠导轨73纵向与固定套环71连接,伸缩套环72能够滑动的连接在丝杠导轨73上以使其能够沿着丝杠导轨73滑动,铰77凸伸设置在固定讨还71上,每个铰77与一个支撑杆75连接,支撑杆75的自由端与侧面遮光罩连接,每个支撑杆75的中部与一个支撑臂76的一端铰接,支撑臂76的另一端与伸缩套环72铰接,并且支撑臂76的长度大于支撑杆75的交接位置到铰77之间的长度但小于支撑杆75的长度。固定套环71为圆环,与次镜伸展臂4最上端的构架单元41的上表面的刚性三角形固连。在固定套环71与的构架单元41的上表面的刚性三角形连接处垂直穿过三根丝杠导轨73,丝杠导轨73与固定套环71固连。3根丝杠导轨73的顶端距固定套环71一定距离,并与光学系统次反射镜固定结构25固连,起到对光学系统次反射镜2的支持作用。The function of the top telescopic
如图18所示,三根丝杠导轨73由丝杠731、丝杠安装座732、步进电机733组成,丝杆安装座732顶端与固定套环71固连,底部与导轨固定三角79固连,步进电机733安装于丝杆安装座内并驱动丝杠731在丝杠安装座内转动。固定套环71外圆周围均匀伸出6根一定长度的支撑杆固定端78,支撑杆固定端78通过球形铰链77连接支撑杆75。支撑杆75为两段细长杆连接组成,两杆之间成钝角。支撑杆75的顶端与遮光布连接。伸缩套环72与固定套环71都是圆环,伸缩套环72通过滚珠套筒74实现在丝杠导轨73上的移动。支撑臂76一端与支撑杆75铰接,一段与滑动套筒铰接。如图15,卫星入轨前顶部伸缩套环支撑杆7为折叠状态,此时伸缩套环72沿着丝杠导轨73向下移动,直至支撑臂76与导轨平行。卫星入轨后,与丝杠结构的导轨连接的步进电机转动,驱动内部安装滚珠的滚珠套筒74沿着丝杠导轨73向上运动,带动支撑臂76与支撑杆75展开,实现从顶部带动卫星遮光布的在轨伸展。As shown in FIG. 18 , the three
如图3所示,GEO高分辨率光学成像卫星的侧面遮光罩5在卫星发射前呈折叠状围绕在折叠光学系统主反射镜1周围,其折叠分为径向压缩折叠和轴向层状对折。径向折叠为锯齿状折叠,其顶部与底部分别与顶部伸缩套环支撑杆结构7和底部折叠杆6连接,当底部折叠杆6与顶部伸缩套环支撑杆结构7同时展开时,侧面遮光罩5沿圆周向外扩展,锯齿折叠角度随之变大,总周长变大,锯齿状折叠遮光罩完全展开呈六边形。当次镜伸展臂4展开,由于次镜伸展臂的最上端与顶部伸缩套环支撑杆的固定套环71固定连接,所以在次镜伸展臂4向上运动时,带动顶部伸缩套环支撑杆结构7向上运动,从而带动侧面遮光罩5沿径向的拉伸,经过在轨完全伸展后,如图1所示,会形成6面的巨型遮光结构。为充分利用该结构,卫星在设计时采用柔性太阳能电池片作为侧面遮光罩5,在为卫星光学系统遮光的同时,也作为卫星的能源系统为卫星进行供电。As shown in Figure 3, the
本发明具有以下特点:The present invention has the following characteristics:
1.GEO光学成像卫星周部的自展开太阳能电池遮光罩利用顶部伸缩套环支撑杆结构和部折叠杆结构支撑展开。1. The self-expanding solar cell hood at the periphery of the GEO optical imaging satellite is supported and expanded by the top telescopic collar support rod structure and the partial folding rod structure.
2.底部折叠杆为反折结构,与顶部伸缩套环支撑杆为卫星周部遮光布的牵引机构,随卫星主体骨架进行折叠收缩、在轨伸展,使卫星周部遮光结构尺寸满足了整流罩的要求。2. The bottom folding rod is a reflex structure, and the top telescopic collar support rod is the traction mechanism of the shading cloth around the satellite. It folds and shrinks with the main skeleton of the satellite and extends on-orbit, so that the size of the shading structure around the satellite meets the fairing. requirements.
3.采用柔性太阳能电池片作为卫星的周部遮光布,在为卫星光学系统遮光的同时,也作为卫星的能源系统为卫星进行供电,减少了卫星的结构,降低了卫星的整体重量。3. The flexible solar cells are used as the shading cloth around the satellite. While shading the satellite optical system, it also serves as the energy system of the satellite to supply power to the satellite, which reduces the structure of the satellite and reduces the overall weight of the satellite.
本发明的效果Effects of the present invention
本发明设计了一种GEO光学成像卫星周部的自展开太阳能电池遮光罩,遮光罩在卫星入轨前成折叠状态,可以利用顶部伸缩套环支撑杆结构7与底部折叠杆6进行遮光罩展开,并且采用可折叠太阳能电池片作为遮光罩的外层结构,可作为卫星的能源系统为卫星进行供电,折叠展开式遮光罩的设计,使一GEO光学成像卫星在现有条件下可以实现一次入轨。The present invention designs a self-expanding solar cell hood for the periphery of a GEO optical imaging satellite. The hood is in a folded state before the satellite enters orbit. The hood can be unfolded by using the top telescopic collar
关于底部遮光罩展开系统:About the bottom hood deployment system:
如图1、2所示,为了消除太阳光等杂光对卫星光学系统的影响,需要在卫星上加装遮光罩结构。GEO光学成像卫星遮光罩包括侧面遮光罩5与卫星底部可展开式遮光罩8。GEO光学成像卫星底部可展开式遮光罩8由两部分组成,分别是主镜底座内部固定式遮光罩和主镜底座外部可展开遮光罩。主镜底座外部可展开遮光罩由可折叠遮光布81与底部遮光罩伸展机构9组成。As shown in Figures 1 and 2, in order to eliminate the influence of stray light such as sunlight on the satellite optical system, it is necessary to install a hood structure on the satellite. The GEO optical imaging satellite hood includes a
除了卫星侧面需要遮光,卫星底部也需要遮光。主镜底座外围的遮光罩81由底部遮光罩伸展机构9展开,如图19所示,底部遮光罩伸展机构9由带齿圈环形导轨91,1个导轨滑块92、2个电机驱动的可自锁关节93、2个底部遮光罩伸展臂94构成。卫星入轨之前,2个环形导轨滑块92、2个电机驱动的可自锁关节93、2个底部遮光罩伸展臂94并列在一起,底部遮光罩伸展机构9呈压缩状态,底部遮光罩伸展臂94绕电机驱动的可自锁关节93转动成竖直状态。底部遮光罩伸展臂94中是空槽结构,槽内堆叠有镀铝聚酰亚胺薄膜,当卫星入轨后,如图20所示,底部遮光罩伸展臂94绕电机驱动的可自锁关节93转动成水平状态,带齿圈环形导轨91固定,导轨滑块92内安装齿轮且齿轮与环形导轨的齿圈啮合,由安装于导轨滑块上的电机驱动齿轮沿着带齿圈的环形导轨91圆周运动,底部遮光罩伸展臂94固定于环形导轨滑块92上随着环形导轨滑块92的运动而运动,使两根底部遮光罩伸展臂94分开,从而将折叠杆内堆叠的镀铝聚酰亚胺薄膜拉伸,镀铝聚酰亚胺薄膜内镶嵌蛛网状金属丝网,入轨之前人工将金属丝网与镀铝聚酰亚胺薄膜一同折叠于底部遮光罩伸展臂94的空槽结构内,入轨后金属丝网随着镀铝聚酰亚胺薄膜的展开而逐步展开,以支撑整个圆环形遮光罩结构,如图20所示,在卫星底部形成完整的圆环形遮光罩结构。In addition to the need for shading on the side of the satellite, the bottom of the satellite also needs shading. The
可自锁关节利用伺服电机驱动蜗杆转动,蜗杆转动驱动与蜗杆啮合的涡轮转动,通过蜗杆的导程角小于啮合接触的摩擦角的设计实现关节自锁功能。The self-locking joint uses the servo motor to drive the worm to rotate, and the worm rotates to drive the turbine that meshes with the worm to rotate. The self-locking function of the joint is realized by the design that the lead angle of the worm is smaller than the friction angle of the meshing contact.
如图21所示,主镜底座14的12边环以内的结构在整个发射过程中不产生变化,因此在卫星的初始结构设计上,直接使用镀铝聚酰亚胺薄膜(PI)作为遮光布,包裹住主镜底座14边环以内的卫星结构,利用主镜底座14边环与喷管固定支架的6根固定支架104进行牵拉,将喷管布置在遮光罩外。As shown in Figure 21, the structure within the 12-sided ring of the
本发明具有以下特点:The present invention has the following characteristics:
1.GEO光学成像卫星底部可展开式遮光罩由主镜底座内部固定式遮光罩和主镜底座外部可展开遮光罩两部分组成。1. The expandable hood at the bottom of the GEO optical imaging satellite consists of two parts: the fixed hood inside the main mirror base and the expandable hood outside the main mirror base.
2.主镜底座外部可展开遮光罩由底部遮光罩伸展机构和可折叠遮光布组成,底部遮光罩伸展机构在卫星发射前是折叠状态,其内部中空槽内堆叠可折叠遮光布。2. The expandable hood outside the base of the main mirror is composed of a bottom hood stretching mechanism and a foldable shading cloth. The bottom hood stretching mechanism is in a folded state before the satellite is launched, and the foldable shading cloth is stacked in the inner hollow slot.
3.可折叠遮光布的材料是镀铝聚酰亚胺薄膜(PI)3. The material of the foldable shade cloth is aluminized polyimide film (PI)
4.底部遮光罩伸展机构利用电机驱动环形导轨滑块沿着环形导轨呈扇形打开可折叠遮光布。4. The bottom hood stretching mechanism uses the motor to drive the annular guide slider to open the foldable shading cloth in a fan shape along the annular guide.
5.主镜底座内部固定式遮光罩利用喷管固定支架进行遮光罩固定。5. The fixed hood inside the base of the main mirror is fixed by the nozzle fixing bracket.
本发明的效果Effects of the present invention
本发明设计了一种GEO光学成像卫星底部可展开式遮光罩,克服了传统遮光罩固定结构不能折叠的缺陷,适用于为GEO光学成像卫星的可折叠主镜的底部遮光,并且减少占用的整流罩空间,使GEO光学成像卫星在现有条件下可以实现一次发射入轨。The invention designs an expandable light hood at the bottom of the GEO optical imaging satellite, which overcomes the defect that the fixed structure of the traditional light hood cannot be folded, is suitable for shading the bottom of the foldable primary mirror of the GEO optical imaging satellite, and reduces the rectification occupied Cover the space, so that the GEO optical imaging satellite can be launched into orbit at one time under the existing conditions.
综上,本领域技术人员容易理解的是,在不冲突的前提下,上述各有利方式可以自由地组合、叠加。To sum up, those skilled in the art can easily understand that, on the premise that there is no conflict, the above advantageous manners can be freely combined and superimposed.
以上所述仅为本发明的实施例而已,并不用于限制本发明,对于本领域的技术人员来说,本发明可以有各种更改和变化。凡在本发明的精神和原则之内,所作的任何修改、等同替换、改进等,均应包含在本发明的权利要求范围之内。The above description is only an embodiment of the present invention, and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the scope of the claims of the present invention.
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112433358A (en) * | 2020-11-30 | 2021-03-02 | 中国科学院长春光学精密机械与物理研究所 | Space ultra-large-diameter lens hood |
CN113515002A (en) * | 2021-04-23 | 2021-10-19 | 上海卫星工程研究所 | External heat flow restrained satellite-borne shading system |
CN115320894A (en) * | 2022-08-12 | 2022-11-11 | 中国空间技术研究院 | Protection device of satellite-borne optical device |
CN117031862A (en) * | 2023-10-09 | 2023-11-10 | 天津航天机电设备研究所 | Assembling and adjusting system of connecting rod unfolding mechanism for folding and unfolding light shield and using method |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH10129599A (en) * | 1996-11-01 | 1998-05-19 | Nec Corp | Light shielding part developing mechanism |
US20110242663A1 (en) * | 2010-04-05 | 2011-10-06 | Dailey Dean R | Space-based occulter |
CN104765122A (en) * | 2015-04-29 | 2015-07-08 | 哈尔滨工业大学 | Telescopic truss type binary optical space camera and on-orbit work method thereof |
CN206155103U (en) * | 2016-11-07 | 2017-05-10 | 杨芝兵 | Car lens hood and car |
CN108773502A (en) * | 2018-06-09 | 2018-11-09 | 哈尔滨工业大学 | Based on cylindrical surface or circular conical surface helix can in-orbit expansion hood |
CN110376823A (en) * | 2019-06-25 | 2019-10-25 | 中国科学院长春光学精密机械与物理研究所 | A kind of camera secondary mirror end structure with telescopic lens cap |
-
2019
- 2019-11-30 CN CN201911209044.4A patent/CN110884689B/en not_active Expired - Fee Related
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH10129599A (en) * | 1996-11-01 | 1998-05-19 | Nec Corp | Light shielding part developing mechanism |
US20110242663A1 (en) * | 2010-04-05 | 2011-10-06 | Dailey Dean R | Space-based occulter |
CN104765122A (en) * | 2015-04-29 | 2015-07-08 | 哈尔滨工业大学 | Telescopic truss type binary optical space camera and on-orbit work method thereof |
CN206155103U (en) * | 2016-11-07 | 2017-05-10 | 杨芝兵 | Car lens hood and car |
CN108773502A (en) * | 2018-06-09 | 2018-11-09 | 哈尔滨工业大学 | Based on cylindrical surface or circular conical surface helix can in-orbit expansion hood |
CN110376823A (en) * | 2019-06-25 | 2019-10-25 | 中国科学院长春光学精密机械与物理研究所 | A kind of camera secondary mirror end structure with telescopic lens cap |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112433358A (en) * | 2020-11-30 | 2021-03-02 | 中国科学院长春光学精密机械与物理研究所 | Space ultra-large-diameter lens hood |
CN112433358B (en) * | 2020-11-30 | 2022-08-30 | 中国科学院长春光学精密机械与物理研究所 | A space super-large aperture hood |
CN113515002A (en) * | 2021-04-23 | 2021-10-19 | 上海卫星工程研究所 | External heat flow restrained satellite-borne shading system |
CN113515002B (en) * | 2021-04-23 | 2022-12-27 | 上海卫星工程研究所 | External heat flow restrained satellite-borne shading system |
CN115320894A (en) * | 2022-08-12 | 2022-11-11 | 中国空间技术研究院 | Protection device of satellite-borne optical device |
CN117031862A (en) * | 2023-10-09 | 2023-11-10 | 天津航天机电设备研究所 | Assembling and adjusting system of connecting rod unfolding mechanism for folding and unfolding light shield and using method |
CN117031862B (en) * | 2023-10-09 | 2023-12-19 | 天津航天机电设备研究所 | An assembly and adjustment system and use method of a connecting rod expansion mechanism for folding and unfolding sunshades |
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