CN100364857C - An Earth Simulator Suitable for Ground Detection of Dual Cone Scanning Infrared Horizon - Google Patents

An Earth Simulator Suitable for Ground Detection of Dual Cone Scanning Infrared Horizon Download PDF

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CN100364857C
CN100364857C CNB2005100303787A CN200510030378A CN100364857C CN 100364857 C CN100364857 C CN 100364857C CN B2005100303787 A CNB2005100303787 A CN B2005100303787A CN 200510030378 A CN200510030378 A CN 200510030378A CN 100364857 C CN100364857 C CN 100364857C
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cold
basin
earth
hot plate
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崔维鑫
童广辉
周士兵
吕银环
刘石神
刘学明
杨晓宇
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Shanghai Institute of Technical Physics of CAS
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Abstract

一种适合双圆锥扫描式红外地平仪地面检测用的地球模拟器,包括冷热板组件、热盆组件、冷热板支架、热盆支架、基座、温控系统和二维精密转台。热盆和热板构成地球模拟面,冷板及系统背景用来模拟太空冷背景,温控系统对热板和热盆温控加热,等效模拟红外地平仪所获取的相对于太空冷背景的14-16μm地球红外辐射强度及梯度,实现冷热板边界和热盆外边界模拟红外地平圆目标。各组件中的多维调节机构以光学校准精确调整冷热板边界及热盆外边界的位置,实现特定轨道高度卫星与地球红外地平圆的几何位置关系。红外地平仪安装在二维精密转台上,以二维转动模拟卫星在轨时的滚动和俯仰姿态角偏差,实现对姿态角的测量和双圆锥扫描红外地平仪的地面性能检测。

Figure 200510030378

An earth simulator suitable for ground detection of a double-cone scanning infrared horizon, comprising a cold and hot plate assembly, a hot basin assembly, a cold and hot plate support, a hot basin support, a base, a temperature control system and a two-dimensional precision turntable. The hot basin and the hot plate constitute the earth simulation surface, the cold plate and the system background are used to simulate the cold background of space, and the temperature control system controls and heats the hot plate and the hot basin, which is equivalent to simulating the temperature obtained by the infrared horizon relative to the cold background of space. 14-16μm earth infrared radiation intensity and gradient, to realize the simulation of infrared horizon circle target on the boundary of cold and hot plates and the outer boundary of hot basin. The multi-dimensional adjustment mechanism in each component precisely adjusts the position of the boundary of the cold and hot plates and the outer boundary of the hot basin through optical calibration, so as to realize the geometric positional relationship between the satellite at a specific orbital height and the earth's infrared horizon circle. The infrared horizon is installed on a two-dimensional precision turntable, and the two-dimensional rotation simulates the roll and pitch attitude angle deviation of the satellite when it is in orbit, and realizes the measurement of the attitude angle and the ground performance detection of the double-cone scanning infrared horizon.

Figure 200510030378

Description

适合双圆锥扫描式红外地平仪地面检测用的地球模拟器 An Earth Simulator Suitable for Ground Detection of Dual Cone Scanning Infrared Horizon

技术领域:Technical field:

本发明涉及一种空间科学仪器地面检测设备,特别是一种适合卫星平台应用的姿态敏感器红外地平仪的地面检测设备。The invention relates to a ground detection device for a space science instrument, in particular to a ground detection device for an attitude sensor infrared horizon suitable for satellite platforms.

背景技术:Background technique:

利用地球红外辐射作为基准目标的红外地平仪,具有高精度、可靠性好等优点,因此被普遍采用。早期红外地平仪应用于控制导弹的发动机点火和载入试验。自1959年2月开始在卫星上使用,成功地测量了卫星绕地球飞行的姿态,由于红外地平仪与其它姿态敏感技术相比具有简单可靠且有较高的姿态测量精度(一般在0.1°-0.5°),所以发展迅速,在以后的载人宇宙飞船,特别是对地定向侦探、气象、通讯、地资等人造卫星上广泛使用,目前发射的空间飞行器大都是采用红外地平仪来实现姿态控制,因此,红外地平仪的研制也成为卫星姿态测量中的一个独立分支科学。The infrared horizon using the earth's infrared radiation as a reference target has the advantages of high precision and good reliability, so it is widely used. Early infrared horizons were used to control missile engine ignition and loading tests. It has been used on satellites since February 1959 and has successfully measured the attitude of satellites flying around the earth. Compared with other attitude-sensitive technologies, the infrared horizon is simple, reliable and has high attitude measurement accuracy (generally within 0.1°- 0.5°), so it develops rapidly. It will be widely used in future manned spaceships, especially on man-made satellites such as ground-directed reconnaissance, meteorology, communication, and ground information. At present, most space vehicles launched use infrared horizons to achieve attitude Therefore, the development of infrared horizon has also become an independent branch of science in satellite attitude measurement.

由于地球的平均亮温度为247K,而太空的平均亮温度约为4.2K,所以卫星在轨时看到的地球红外图像为深冷的太空背景下一个“灼热”的圆盘,其边界就是通常所说的红外地平圆。红外地平仪作为卫星姿态控制系统的姿态敏感器,正是基于对地球红外辐射的敏感,在轨实现卫星相对于局地垂线的滚动、俯仰姿态信号测量,为卫星初始入射时对地球的捕获及稳态运行时卫星的姿态控制提供测量基准。红外地平仪测量精度和可靠性直接关系到卫星飞行姿态是否准确和稳定。Since the average brightness temperature of the earth is 247K, and the average brightness temperature of space is about 4.2K, the infrared image of the earth seen by the satellite when it is in orbit is a "hot" disk in the background of deep and cold space, and its boundary is usually The so-called infrared horizon is flat and circular. As the attitude sensor of the satellite attitude control system, the infrared horizon is based on the sensitivity to the earth's infrared radiation, and realizes the measurement of the satellite's rolling and pitching attitude signals relative to the local vertical line in orbit, which is the capture of the earth when the satellite is initially incident. And the attitude control of the satellite during steady-state operation provides a measurement reference. The measurement accuracy and reliability of the infrared horizon are directly related to the accuracy and stability of the satellite flight attitude.

目前,中国卫星平台上所使用的红外地平仪主要是圆锥扫描式红外地平仪,双圆锥扫描式红外地平仪工作原理是基于对地球和太空冷背景之间的红外辐射差敏感,,利用光学扫描电机和特殊设计的光学系统(由固定反射镜、旋转反射镜和红外热敏探测器组成)基于红外热敏探测器瞬时视场对地球进行双圆锥光学扫描,光学系统的等效双圆锥扫描光路及对地球和太空的扫描轨迹如图1所示,地平辐射信号成像在热敏元件上,经过电子学系统的处理,在一个扫描周期内可得到相对敏感器基准信号0的4个红外地平圆穿越点:太空/地球穿越点(S/E)1、3,地球/太空穿越点(E/S)2、4,通过信息处理电路实现卫星姿态角的测量。At present, the infrared horizons used on Chinese satellite platforms are mainly conical scanning infrared horizons. The working principle of the double-cone scanning infrared horizons is based on being sensitive to the difference in infrared radiation between the earth and the cold background of space. Using optical scanning The motor and the specially designed optical system (composed of fixed mirrors, rotating mirrors and infrared thermal detectors) perform biconical optical scanning of the earth based on the instantaneous field of view of the infrared thermal detectors, and the equivalent biconical scanning optical path of the optical system And the scanning trajectory of the earth and space is shown in Figure 1. The horizon radiation signal is imaged on the thermal element, and after being processed by the electronic system, four infrared horizons relative to the sensor reference signal 0 can be obtained in one scan cycle. Circle crossing points: space/earth crossing points (S/E) 1, 3, earth/space crossing points (E/S) 2, 4, the measurement of the satellite attitude angle is realized through the information processing circuit.

地球模拟器作为红外地平仪产品的专用地面性能测试设备,是实现红外地平仪性能指标地面检测、标定及全物理仿真的必要手段。As a special ground performance testing equipment for infrared horizon products, the earth simulator is a necessary means to realize ground detection, calibration and full physical simulation of infrared horizon performance indicators.

发明内容:Invention content:

本发明的目的在于考虑到产品双圆锥光学扫描特点,提供一种适合双圆锥扫描式红外地平仪地面性能检测、标定及全物理仿真用的地球模拟器。为双圆锥扫描式红外地平仪性能指标评估提供地面测试设备,进而使得双圆锥扫描式红外地平仪能够提供更高精度的卫星姿态测量。The purpose of the present invention is to provide an earth simulator suitable for ground performance detection, calibration and full physical simulation of a bicone scanning infrared horizon in consideration of the characteristics of bicone optical scanning products. Provide ground test equipment for the evaluation of the performance index of the dual-cone scanning infrared horizon, so that the dual-cone scanning infrared horizon can provide higher-precision satellite attitude measurement.

本发明的目的是这样实现的:本发明的一种在地面对双圆锥扫描式红外地平仪进行检测等用的地球模拟器,至少包含以下七个部分:四个冷热板组件、一个热盆组件、一个冷热板支架、一个热盆支架、一个基座、一个温控系统和一个二维精密转台。The object of the present invention is achieved like this: a kind of earth simulator of the present invention carries out detection etc. to bicone scanning type infrared horizon instrument on the ground, comprises following seven parts at least: four cold and hot plate assemblies, a thermal Basin assembly, a hot and cold plate support, a hot basin support, a base, a temperature control system and a two-dimensional precision turntable.

所述的地球模拟器是利用热盆和冷热板组件共同组成地球模拟面,静态地模拟地球/太空冷热穿越边界,通过光学校正结构调整系统准确调整并定位地球模拟器冷热边界的位置,达到理想边界位置附近,将位置精度控制在一定范围内;地模热盆和4个冷热板组件的热板涂有机黑漆(比辐射率0.9),并将其加热升温模拟地球的热辐射;把冷热板组件的冷板热模拟表面喷沙阳极化处理,以模拟太空冷背景;加热器设计成加热薄片,并把它粘贴在被加温体的内侧,同时在加热薄片和模拟太空之间用绝热材料进行隔离,防止进行热交换而导致的模拟太空体温度升高。The earth simulator uses the hot basin and the hot and cold plate components to form the earth simulation surface, statically simulates the earth/space cold and hot crossing the boundary, and accurately adjusts and locates the position of the hot and cold boundary of the earth simulator through the optical correction structure adjustment system , to reach the ideal boundary position, and control the position accuracy within a certain range; the heat basin of the ground model and the hot plate of the four cold and hot plate components are coated with organic black paint (the specific emissivity is 0.9), and they are heated to simulate the heat of the earth. Radiation; sandblasting and anodizing the thermal simulation surface of the cold plate assembly to simulate the space cooling background; the heater is designed to heat the sheet and paste it on the inside of the heated body, while heating the sheet and the simulation Spaces are isolated with insulating materials to prevent the temperature rise of the simulated space body caused by heat exchange.

所述的温控系统,即地平仪温控系统,其主要由5路相互独立的温差控制单元、温差显示仪表和多路温度循检单元组成,配置在专用控制柜中。每路控制单元由数字式温度调节器、可控硅交流电力控制器和测温热电偶构成,形成闭环温度控制回路;温控系统的工作原理是利用5路相互独立的温差控制单元通过数字式温度调节器实现PID温度调节,分别控制4块热板及热盆相对于冷板的温差,显示仪表和多路温度环循检测单元可显示热板和热盆的当前温差。The temperature control system, that is, the temperature control system of the horizon instrument, is mainly composed of 5 independent temperature difference control units, a temperature difference display instrument and a multi-channel temperature inspection unit, which are arranged in a special control cabinet. Each control unit is composed of a digital temperature regulator, a thyristor AC power controller and a temperature measuring thermocouple, forming a closed-loop temperature control loop; the working principle of the temperature control system is to use 5 independent temperature difference control units through digital The temperature regulator realizes PID temperature regulation, controls the temperature difference between the 4 hot plates and the hot basin relative to the cold plate respectively, and the display instrument and the multi-channel temperature cycle detection unit can display the current temperature difference between the hot plate and the hot basin.

所述地球模拟器通过二维转台控制器控制精密二维转台实现地平仪姿态角偏差,即俯仰角和滚动角,安装在精密二维转台上的地平仪通过对地球模拟器进行光学扫描,从而实现不同姿态角的测量。衡量红外地平仪单机测量精度的关键性技术指标是随机噪声等效角:该地面测试系统在正常工作模式下,所测得红外地平仪的随机噪声等效角(3σ)小于0.07*The earth simulator controls the precision two-dimensional turntable through the two-dimensional turntable controller to realize the attitude angle deviation of the horizon, that is, the pitch angle and the roll angle, and the horizon installed on the precision two-dimensional turntable optically scans the earth simulator, thereby Realize the measurement of different attitude angles. The key technical index to measure the measurement accuracy of the infrared horizon is the random noise equivalent angle: under the normal working mode of the ground test system, the measured random noise equivalent angle (3σ) of the infrared horizon is less than 0.07 * .

本发明的优点是:The advantages of the present invention are:

1、基于双圆锥扫描式红外地平圆光学扫描工作原理,相对于二维精密转台零位时正交的外框转轴和U型框转轴所构成的铅垂面,将地球模拟器设计成为复式结构:热盆组件通过热盆支架、四个冷热板组件通过冷热板支架前后平行地安装在基座上,由四个冷热板组件的冷板和热板及热盆组件的热盆外边界相对于环境背景构成的模拟红外地平圆。这样的结构除了对红外地平仪产品来说提供了一个完全等价的地球红外辐射观测目标外,相比于模拟红外地平圆的单一平面结构而言,使地球红外辐射热模拟面大幅度减小,一方面降低了地球模拟器加热功率,另一方面易于保证热模拟面尤其是热板的温度均匀度要求。1. Based on the working principle of dual-cone scanning infrared horizontal circular optical scanning, the earth simulator is designed as a compound structure relative to the vertical plane formed by the outer frame shaft and the U-shaped frame shaft that are orthogonal to the zero position of the two-dimensional precision turntable. : The hot tub assembly is installed on the base parallel to the front and rear through the hot tub bracket, and the four cold and hot plate assemblies are front and rear parallel. A simulated infrared horizon circle formed by the boundary relative to the ambient background. In addition to providing a completely equivalent earth infrared radiation observation target for infrared horizon products, this structure greatly reduces the earth infrared radiation heat simulation surface compared to the single plane structure that simulates the infrared horizon circle On the one hand, the heating power of the earth simulator is reduced, and on the other hand, it is easy to ensure the temperature uniformity requirements of the thermal simulation surface, especially the hot plate.

2、鉴于地球模拟器外形尺寸较大,装配组合零件多,加工精度和装配精度难于满足零件相互之间的位置精度要求,本发明采用结构简单、易于拆卸的各组件设计的用于光学校准的多维调节机构,利用二维矩形导轨移动副、圆柱形移动副、可调节垫块和螺纹调节等机构,使冷热板组件和热盆组件具备多自由度调节功能,保证光学装调时系统的可调性和精度要求。此外,由于多维调节机构的选用,通过调整冷热板组件和热盆组件相对于二维精密转台的位置关系,使地球模拟器在一定卫星轨道范围内模拟不同轨道高度卫星的姿态检测。2. In view of the large size of the earth simulator and the large number of assembly parts, the machining accuracy and assembly accuracy are difficult to meet the positional accuracy requirements of the parts. Multi-dimensional adjustment mechanism, using two-dimensional rectangular guide rail moving pair, cylindrical moving pair, adjustable pads and thread adjustment, etc., to make the cold and hot plate assembly and hot basin assembly have multi-degree-of-freedom adjustment functions, ensuring the system’s stability during optical assembly and adjustment. Adjustability and precision requirements. In addition, due to the selection of the multi-dimensional adjustment mechanism, by adjusting the positional relationship between the cold and hot plate assembly and the hot basin assembly relative to the two-dimensional precision turntable, the earth simulator can simulate the attitude detection of satellites at different orbital heights within a certain range of satellite orbits.

3、地球模拟器的热板及热盆的加热选用了薄膜加热器,配置在热板及热盆辐射表面的背面,具有加热面热流密度均匀、热效率高和加热器寿命长等特点。热板及热盆采用了隔热及绝热设计,采用了其中包括热板与冷板、支撑结构件之间,热盆与支撑结构件、外壳之间。因此,地球模拟器的加热功率小、温升速度快、温升幅度大、冷热边界温差控制范围宽、控温精度高。3. The heating of the hot plate and hot basin of the earth simulator uses a thin-film heater, which is arranged on the back of the radiating surface of the hot plate and hot basin. It has the characteristics of uniform heat flux density on the heating surface, high thermal efficiency and long heater life. The heat insulation and heat insulation design is adopted for the hot plate and the hot basin, including between the hot plate and the cold plate, the supporting structure, and between the hot basin and the supporting structure and the shell. Therefore, the heating power of the earth simulator is small, the temperature rise speed is fast, the temperature rise range is large, the control range of the temperature difference between the cold and the hot boundary is wide, and the temperature control accuracy is high.

附图说明Description of drawings

图1-1和图1-2为已知的双圆锥扫描式红外地平仪光学系统扫描光路和地球、太空扫描轨迹示意图;Figure 1-1 and Figure 1-2 are schematic diagrams of the scanning optical path and the earth and space scanning trajectories of the known dual-cone scanning infrared horizon optical system;

图2为本发明中的地球模拟器的组成框图;Fig. 2 is the composition block diagram of the earth simulator among the present invention;

图3为本发明中的地球模拟结构示意图;Fig. 3 is the earth simulation structure schematic diagram among the present invention;

图4为本发明中的冷热板组件结构安装图;Fig. 4 is the structural installation diagram of the cold and hot plate assembly in the present invention;

图5-1,5-2,5-3为本发明中的冷热板组件组装图;Figures 5-1, 5-2, and 5-3 are assembly diagrams of the cold and hot plate assembly in the present invention;

图6为本发明中的热盆组件结构安装图;Fig. 6 is the structural installation drawing of hot tub assembly among the present invention;

图7-1,7-2为本发明中的热盆组件组装图;Figures 7-1 and 7-2 are assembly diagrams of the hot tub assembly in the present invention;

图8为本发明中的二维精密转台结构图;Fig. 8 is a structural diagram of a two-dimensional precision turntable in the present invention;

图9为本发明中的温控系统原理框图。Fig. 9 is a functional block diagram of the temperature control system in the present invention.

具体实施方式Detailed ways

下面根据图2-图9给出本发明一个较好实施例,并予以详细描述,以使能更好地了解本发明的结构特征和功能特点,要指出的是,所给出的实施例是为了说明本发明,而不是用来限制本发明的范围。Provide a preferred embodiment of the present invention below according to Fig. 2-Fig. It is intended to illustrate the present invention, but not to limit the scope of the present invention.

图2给出了本发明的地球模拟器的系统组成及及其功能。冷热板组件1和热盆组件2构成地球模拟器的地球红外地平圆9;温控系统7通过加热器控制冷热组件1中的热板和热盆组件2中的热盆相对于冷热组件1中的冷板的温差,实现地球相对于太空冷背景的红外辐射强度的模拟;红外地平仪产品10安装在二维精密转台3上,通过转台控制系统8实现二维精密转台3的二维转动,以模拟卫星在轨时的滚动和俯仰姿态的偏差。Fig. 2 has provided the system composition and its function of the earth simulator of the present invention. The cold and hot plate assembly 1 and the hot basin assembly 2 constitute the earth's infrared horizon 9 of the earth simulator; The temperature difference of the cold plate in component 1 realizes the simulation of the infrared radiation intensity of the earth relative to the cold background of space; the infrared horizon product 10 is installed on the two-dimensional precision turntable 3, and the two-dimensional precision turntable 3 is realized through the turntable control system 8. The three-dimensional rotation is used to simulate the deviation of the roll and pitch attitude of the satellite when it is in orbit.

如图3所示,地球模拟器结构功能模块包括冷热板组件1、热盆组件2、二维精密转台3、冷热板组件支架4、基座5和热盆组件支架6。参照卫星在轨飞行时坐标系的定义,图中给出的正交坐标系OXYZ为:X轴为滚动轴,Y轴为俯仰轴,Z轴为偏航轴,其中X轴和Y轴分别为二维精密转台3的两个转轴。四个冷热板组件1和热盆组件2相对于坐标系OXYZ的位置关系取决于卫星特定的轨道高度。利用光学校准的方法将位置精度控制在±0.01mm范围内。As shown in FIG. 3 , the structural and functional modules of the earth simulator include a cold and hot plate assembly 1 , a hot basin assembly 2 , a two-dimensional precision turntable 3 , a cold and hot plate assembly support 4 , a base 5 and a hot basin assembly support 6 . Referring to the definition of the coordinate system when the satellite is in orbit, the orthogonal coordinate system OXYZ given in the figure is: the X axis is the roll axis, the Y axis is the pitch axis, and the Z axis is the yaw axis, where the X axis and the Y axis are respectively Two rotating shafts of the two-dimensional precision turntable 3. The positional relationship of the four cold and hot plate assemblies 1 and the hot basin assembly 2 with respect to the coordinate system OXYZ depends on the specific orbital altitude of the satellite. The position accuracy is controlled within ±0.01mm by optical calibration.

如图4所示,冷热板组件1包括四个独立的冷热板组件11、12、13、14,它们通过螺栓基于Z轴轴对称地安装在冷热板支架4上。冷热板组件11、13结构相同,冷热板组件12、14结构相同,且互为镜像结构。边界L1~L4设计用来模拟地球红外地平圆9,用于红外地平仪产品10的滚动姿态角R在-7°≤R≤+7°时性能的精确检测。冷热板组件支架4通过斜支撑杆41和支架安装底座42螺纹连接在基座5上,斜支撑杆41两端分别设计成左旋或右旋螺纹连接,可以用来调节冷热板组件支架4相对于水平面的垂直度,同时利用支架安装底座42相对于OXY面前后调节冷热板组件支架4。As shown in FIG. 4 , the cold and hot plate assembly 1 includes four independent cold and hot plate assemblies 11 , 12 , 13 , 14 , which are symmetrically installed on the cold and hot plate support 4 based on the Z axis through bolts. The hot and cold plate assemblies 11 and 13 have the same structure, and the hot and cold plate assemblies 12 and 14 have the same structure and are mirror images of each other. Boundaries L1-L4 are designed to simulate the earth's infrared horizon circle 9, and are used for accurate detection of the performance of the rolling attitude angle R of the infrared horizon product 10 when -7°≤R≤+7°. The hot and cold plate assembly bracket 4 is threadedly connected to the base 5 through the inclined support rod 41 and the bracket mounting base 42. Relative to the verticality of the horizontal plane, at the same time use the bracket installation base 42 to adjust the cold and hot plate assembly bracket 4 backwards and forwards relative to the front of the OXY.

图5-1,5-2,5-3给出了冷热板组件1的详细结构。热板17利用隔热限位块内嵌在组合热板座18内,热模拟表面涂敷高比辐射率有机黑漆。薄膜加热器120粘贴在热板17的背面。在热板17与组合热板座18之间设计有有机泡沫绝热材料110。冷板16安装在圆柱形移动副130上,热模拟表面喷沙阳极化处理,通过螺纹调节可相对于热板17沿OZ轴方向前后移动,同时冷板16可以绕定位螺钉在平行和垂直于OXY平面内转动。利用矩形导轨移动副150和圆柱形移动副140在平行于OXY平面内实现冷热板16,17的上下平移和左右平移。Figures 5-1, 5-2, and 5-3 show the detailed structure of the hot and cold plate assembly 1 . The thermal plate 17 is embedded in the combined thermal plate seat 18 by means of a heat-insulating limit block, and the thermal simulation surface is coated with organic black paint with high specific emissivity. The thin film heater 120 is pasted on the back of the hot plate 17 . An organic foam heat insulating material 110 is designed between the heat plate 17 and the combined heat plate seat 18 . The cold plate 16 is installed on the cylindrical moving pair 130, and the thermal simulation surface is sandblasted and anodized. Through thread adjustment, it can move forward and backward relative to the hot plate 17 along the OZ axis. Rotate in the OXY plane. Utilize the rectangular guide rail moving pair 150 and the cylindrical moving pair 140 to realize the up-and-down translation and left-right translation of the hot and cold plates 16, 17 in parallel to the OXY plane.

热盆组件2、热盆组件支架6及基座5之间的装配关系如图6所示,热盆组件2通过安装法兰(图7中27)、芯轴及锁紧螺母固定在热盆组件支架6的支承座上,放松锁紧螺母可以绕热盆轴线转动热盆组件2,以满足光学校准的要求。热盆组件支架6通过安装底座64栓接在基座5上,热盆组件2的轴线与OZ轴同轴。边界L5~L10用来模拟地球红外地平圆9,用于红外地平仪产品10当滚动姿态角R在7°<|R|≤36°时姿态的测量。二维移动调节机构62和螺纹升降机构63实现了热盆组件2在OXZ平面内平移及沿OY轴的垂直升降。The assembly relationship between the hot tub assembly 2, the hot tub assembly bracket 6 and the base 5 is shown in Figure 6, and the hot tub assembly 2 is fixed on the hot tub assembly through the mounting flange (27 in Figure 7), the mandrel and the lock nut. On the support seat of the assembly bracket 6, loosen the lock nut to rotate the heat tub assembly 2 around the axis of the heat tub to meet the requirements of optical alignment. The hot tub assembly bracket 6 is bolted to the base 5 through the mounting base 64, and the axis of the hot tub assembly 2 is coaxial with the OZ axis. Boundaries L5-L10 are used to simulate the earth's infrared horizon circle 9, and are used to measure the attitude of the infrared horizon product 10 when the rolling attitude angle R is 7°<|R|≤36°. The two-dimensional movement adjustment mechanism 62 and the threaded lifting mechanism 63 realize the translation of the hot tub assembly 2 in the OXZ plane and the vertical lifting along the OY axis.

图7-1,7-2给出了热盆组件2的组装结构,热盆由边界模拟面21、圆台凹腔模拟面22和端盖模拟面23组成,热辐射模拟表面涂覆高比辐射率有机黑漆,薄膜加热器26、29、211、212和214分别配置在热盆的背面。罩壳24、210、215及安装法兰27与热盆之间采用了隔热螺栓连接及有机泡沫绝热材料用于填充25、28、210和213。Figures 7-1 and 7-2 show the assembly structure of the heat basin assembly 2. The heat basin consists of a boundary simulation surface 21, a circular platform concave cavity simulation surface 22 and an end cover simulation surface 23. The heat radiation simulation surface is coated with high specific radiation High rate organic black paint, film heaters 26, 29, 211, 212 and 214 are respectively configured on the back side of the hot basin. Between the shells 24, 210, 215 and the mounting flange 27 and the heat basin, heat insulating bolts are used to connect and organic foam heat insulating materials are used for filling 25, 28, 210 and 213.

如图8所示,二维精密转台3包括以机械联结的外框31、U型框32、底座33和螺纹调节支脚34。被检测红外地平仪产品10安装在U型框32的安装板上。外框31模拟滚动姿态角,U型框32模拟俯仰姿态角,转角定位精度优于5″。螺纹调节支脚34用于调节二维精密转台3的水平位置。As shown in FIG. 8 , the two-dimensional precision turntable 3 includes an outer frame 31 , a U-shaped frame 32 , a base 33 and a threaded adjustment leg 34 which are mechanically connected. The detected infrared horizon product 10 is installed on the mounting plate of the U-shaped frame 32 . The outer frame 31 simulates the rolling attitude angle, the U-shaped frame 32 simulates the pitching attitude angle, and the positioning accuracy of the rotation angle is better than 5″. The threaded adjustment leg 34 is used to adjust the horizontal position of the two-dimensional precision turntable 3 .

如前所述,本发明中的温控系统17由5路相互独立的温差控制单元、温差显示仪表和多路温度循检单元组成,配置在专用控制柜中。如图9所示,每路控制单元由数字式温度调节器74、可控硅交流电力控制器71、控温热电偶73和薄膜加热器120构成,控温热电偶73的测温端和参考端分别嵌入热板17(或热盆)和冷板16中,形成闭环温度控制回路,通过数字式温度调节器74实现PID温度调节,分别控制冷热板组件1中的4块热板17及热盆组件2中热盆相对于冷板16的温差。温差控制范围在20℃~40℃,温控精度优于±0.5℃。As mentioned above, the temperature control system 17 in the present invention is composed of 5 independent temperature difference control units, a temperature difference display instrument and a multi-channel temperature inspection unit, and is arranged in a dedicated control cabinet. As shown in Figure 9, each control unit is composed of a digital temperature regulator 74, a thyristor AC power controller 71, a temperature control thermocouple 73 and a thin film heater 120, and the temperature measurement terminal of the temperature control thermocouple 73 and the reference The ends are respectively embedded in the hot plate 17 (or hot basin) and the cold plate 16 to form a closed-loop temperature control loop. The PID temperature adjustment is realized through the digital temperature regulator 74, and the four hot plates 17 and the The temperature difference between the hot tub in the hot tub assembly 2 relative to the cold plate 16. The temperature difference control range is from 20°C to 40°C, and the temperature control accuracy is better than ±0.5°C.

概括地说,本实施例提供的一种适合双圆锥扫描式红外地平仪地面性能检测标定及全物理仿真用的地球模拟器,属于为卫星平台姿态敏感器红外地平仪配套设计的专用地面测试系统,包括冷热板组件1、热盆组件2、冷热板支架4、热盆支架6、基座5、温控系统7和二维精密转台3,其特征在于,由热盆组件1的热盆和四个独立冷热板组件11、12、13、14的热板17构成地球红外辐射模拟面、由四个独立冷热板组件11、12、13、14的冷板16及系统环境背景模拟太空冷背景、以及由温控系统7对热板17和热盆的温控加热,等效模拟卫星在轨时红外地平仪所获取的相对于太空冷背景的14-16μm地球红外辐射强度及梯度,实现冷热板边界和热盆外边界模拟相对于卫星轨道高度的红外地平圆目标;利用各组件中具有多维调节机构,通过光学校准方法可精确调整冷热板边界及热盆外边界相对于二维精密转台3的位置,实现特定轨道高度卫星与地球红外地平圆的几何位置关系;二维精密转台3包括以机械联结的转台底座33、外框31、U型框32和控制系统(调节支脚)34,其中外框31和U型框32可独立绕正交轴线转动,被测红外地平仪产品10安装在二维精密转台3的U型框32安装板上,利用其二维转动来模拟卫星在轨时的滚动和俯仰姿态角偏差,来实现姿态角的测量,进而实现双圆锥扫描红外地平仪的地面性能检测。In a nutshell, this embodiment provides an earth simulator suitable for the ground performance detection and calibration of the double-cone scanning infrared horizon and the full physical simulation, which belongs to the special ground test system designed for the satellite platform attitude sensor infrared horizon. , including a hot and cold plate assembly 1, a hot basin assembly 2, a hot and cold plate support 4, a hot basin support 6, a base 5, a temperature control system 7, and a two-dimensional precision turntable 3, characterized in that the heat of the hot basin assembly 1 The basin and the hot plate 17 of the four independent cold and hot plate assemblies 11, 12, 13, 14 constitute the earth infrared radiation simulation surface, the cold plate 16 and the system environment background of the four independent cold and hot plate assemblies 11, 12, 13, 14 Simulate the cold background of space, and the temperature-controlled heating of the hot plate 17 and the hot basin by the temperature control system 7, which is equivalent to simulating the 14-16 μm earth infrared radiation intensity and Gradient, to realize the infrared horizon circle target of the simulation of the boundary of the cold and hot plate and the outer boundary of the hot basin relative to the height of the satellite orbit; using the multi-dimensional adjustment mechanism in each component, the relative relationship between the boundary of the cold and hot plate and the outer boundary of the hot basin can be precisely adjusted through the optical calibration method At the position of the two-dimensional precision turntable 3, the geometric positional relationship between the specific orbital height satellite and the earth's infrared horizon circle is realized; the two-dimensional precision turntable 3 includes a turntable base 33, an outer frame 31, a U-shaped frame 32 and a control system ( Adjusting feet) 34, wherein the outer frame 31 and the U-shaped frame 32 can independently rotate around the orthogonal axis, and the measured infrared horizon product 10 is installed on the U-shaped frame 32 mounting plate of the two-dimensional precision turntable 3, and the two-dimensional rotating To simulate the roll and pitch attitude angle deviation of the satellite when it is in orbit, to realize the measurement of the attitude angle, and then to realize the ground performance detection of the dual-cone scanning infrared horizon.

相对于二维精密转台3零位时正交的外框31转轴和U型框32转轴所构成的铅垂面,热盆组件通过热盆支架6、四个独立冷热板组件11、12、13、14通过冷热板支架4前后平行地安装在基座5上,构成复式结构,其中,由四个独立冷热板组件11、12、13、14的冷板16和热板17构成的模拟红外地平圆9,用于红外地平仪产品10当滚动姿态角R为-7°≤R≤+7°时性能的精确检测,如产品姿态角测量的精度、线性度和地面标定;而由热盆组件2的热盆外边界L5-L10相对于环境背景构成的模拟红外地平圆9,用于红外地平仪产品10当滚动姿态角R为R≤-7°和R≥+7°时姿态角的检测,用于产品10工作视域的测量;热盆设计成凹腔结构,保证了二维精密转台3在模拟姿态角偏差时的外框回转空间要求;With respect to the vertical plane formed by the rotating shaft of the outer frame 31 and the rotating shaft of the U-shaped frame 32 that are orthogonal to the zero position of the two-dimensional precision turntable 3, the hot tub assembly passes through the hot tub bracket 6, four independent cold and hot plate assemblies 11, 12, 13 and 14 are installed on the base 5 in parallel front and rear through the cold and hot plate bracket 4 to form a composite structure, wherein the cold plate 16 and the hot plate 17 composed of four independent cold and hot plate assemblies 11, 12, 13, 14 The simulated infrared horizon circle 9 is used for accurate detection of the performance of the infrared horizon product 10 when the rolling attitude angle R is -7°≤R≤+7°, such as the accuracy, linearity and ground calibration of the product attitude angle measurement; and by The simulated infrared horizon circle 9 formed by the heat basin outer boundary L5-L10 of the heat basin assembly 2 relative to the environmental background is used for the attitude of the infrared horizon product 10 when the rolling attitude angle R is R≤-7° and R≥+7° The detection of the angle is used for the measurement of the working field of view of the product 10; the heat basin is designed as a concave cavity structure, which ensures the space requirement for the outer frame of the two-dimensional precision turntable 3 when simulating the deviation of the attitude angle;

所述的各组件中的用于光学校准的多维调节机构,包括二维矩形导轨移动副50、圆柱形移动副130、140,可调节垫块和螺纹调节机构,以保证红外地平圆模拟边界的光学校正精度在±0.01mm范围内;The multi-dimensional adjustment mechanism used for optical calibration in each of the components includes a two-dimensional rectangular guide rail moving pair 50, a cylindrical moving pair 130, 140, an adjustable pad and a threaded adjustment mechanism, so as to ensure the accuracy of the infrared ground circle simulation boundary. The optical correction accuracy is in the range of ±0.01mm;

温控系统7主要由5路相互独立的温差控制单元、温差显示仪表和多路温度循检单元组成,配置在专用控制柜中,每路控制单元主要由数字式温度调节器74、可控硅交流电力控制器71和测温热电偶73构成,形成闭环温度控制回路,温控系统利7用5路相互独立的温差控制单元通过数字式温度调节器实现PID温度调节,分别控制4块热板17及热盆相对于冷板16的温差,显示仪表和多路温度循检单元可显示热板和热盆当前的温差;The temperature control system 7 is mainly composed of 5 independent temperature difference control units, a temperature difference display instrument and a multi-channel temperature inspection unit, which are arranged in a dedicated control cabinet. Each control unit is mainly composed of a digital temperature regulator 74, a thyristor The AC power controller 71 and the temperature measuring thermocouple 73 form a closed-loop temperature control loop. The temperature control system uses 7 independent temperature difference control units of 7 channels to realize PID temperature adjustment through a digital temperature regulator, and controls 4 hot plates respectively. 17 and the temperature difference between the hot plate and the cold plate 16, the display instrument and the multi-channel temperature inspection unit can display the current temperature difference between the hot plate and the hot plate;

冷热板组件1的热板17及热盆组件2的热盆的模拟地球红外辐射的表面涂覆有机黑漆,冷热板组件1的冷板16模拟太空冷背景的表面进行喷沙阳极化处理,以满足设计上对红外辐射表面辐射特性的要求,热板17及热盆的加热选用了薄膜加热器120,配置在热板17及热盆辐射表面的背面;热板17及热盆采用了隔热及绝热设计,其中包括热板17与冷板16、支撑结构件之间,热盆与支撑结构件、外壳之间;温控系统的最大加热功率小于2Kw,升温时间最慢为45min,温差控制范围在20~40℃,温控精度介于±0.5℃之间,温度不均匀度小于±1.5℃。The surface of the hot plate 17 of the cold and hot plate assembly 1 and the hot basin of the hot basin assembly 2 simulating the earth’s infrared radiation are coated with organic black paint, and the surface of the cold plate 16 of the cold and hot plate assembly 1 simulates the cold background of space for sandblasting and anodization In order to meet the design requirements for the radiation characteristics of the infrared radiation surface, the heating of the hot plate 17 and the hot basin adopts a thin film heater 120, which is arranged on the back of the hot plate 17 and the radiant surface of the hot basin; the hot plate 17 and the hot basin adopt Heat insulation and heat insulation design, including between the hot plate 17 and the cold plate 16, the supporting structure, between the hot basin and the supporting structure, and the shell; the maximum heating power of the temperature control system is less than 2Kw, and the slowest heating time is 45min , The temperature difference control range is 20-40°C, the temperature control accuracy is between ±0.5°C, and the temperature unevenness is less than ±1.5°C.

Claims (5)

1. a suitable double cone scanning type infrared horizon instrument ground performance detects the earth simulator for earth of usefulness, belong to and be the supporting design-calculated dedicated ground of satellite platform attitude sensor infrared horizon instrument test macro, comprise cold-hot plate component, hot basin component, cold-hot plate bracket, hot basin bracket, pedestal, temperature control system and two-dimensional precision rotating platform, it is characterized in that, constitute earth infrared radiation falseface by the hot basin of hot basin component and the hot plate of four cold-hot plate components, cold drawing and system environments background simulation space cold-scarce scape by cold-hot plate component, and by the temperature control heating of temperature control system to hot plate and hot basin, equivalent simulation satellite infrared horizon instrument is obtained when rail 14-16 μ m earth infrared intensity and gradient with respect to space cold-scarce scape realize the infrared horizon circle target of cold and hot edges of boards circle and hot basin exterior boundary simulation with respect to satellite orbital altitude; Have the multidimensional regulating mechanism in each assembly, accurately adjust cold and hot edges of boards circle and hot basin exterior boundary position, realize the geometry site of certain tracks height satellite and earth infrared horizon circle with respect to two-dimensional precision rotating platform by optical correction; Two-dimensional precision rotating platform comprises turret base, housing, U type frame and the control system with mechanical connection, wherein housing and U type frame can independently rotate around quadrature-axis, tested infrared horizon instrument is installed on the two-dimensional precision rotating platform U type frame adapter plate, utilize its two dimension to rotate rolling and the pitch attitude angular deviation of analog satellite when rail, thereby realize the measurement of attitude angle, and then realize that the ground performance of double cone scanned infrared horizon instrument detects.
2. suitable double cone scanning type infrared horizon instrument ground performance according to claim 1 detects the earth simulator for earth of usefulness, it is characterized in that, the vertical guide that the housing rotating shaft of quadrature and the rotating shaft of U type frame are constituted during with respect to the two-dimensional precision rotating platform zero-bit, hot basin component passes through hot basin bracket, four cold-hot plate components are installed on the pedestal by before and after the cold-hot plate bracket abreast, constitute duplex, wherein, by the simulation infrared horizon circle that the cold drawing and the hot plate of four cold-hot plate components constitutes, be used for the infrared horizon instrument product and accurately examine the precision of this product attitude angle during in-7 °≤R≤+ 7 ° as roll attitude angle R, the linearity and ground are demarcated; And by the hot basin exterior boundary of hot basin component with respect to the simulation infrared horizon circle that environmental background constitutes, be used for of the detection of infrared horizon instrument product when roll attitude angle R attitude angle in R≤-7 ° and during R 〉=+7 °, be used for the measurement of the product work ken; Hot basin is designed to curved cavity, guarantees the housing rotary space requirement of two-dimensional precision rotating platform when simulation attitude angle deviation.
3. the earth simulator for earth that suitable double cone scanning type infrared horizon instrument Performance Detection according to claim 1 is used, it is characterized in that, the multidimensional regulating mechanism that is used for optical correction in described each assembly, comprise two-dimensional rectangle guide rail moving sets, cylindrical moving sets, scalable cushion block and threaded adjusting mechanism, with the optical correction precision that guarantees infrared horizon circle simulating boundary in ± 0.01mm scope.
4. suitable double cone scanning type infrared horizon instrument ground performance according to claim 1 detects the earth simulator for earth of usefulness, it is characterized in that, temperature control system is mainly by 5 tunnel separate temperature difference control units, temperature difference display instrument and multi way temperature follow the inspection unit and form, be configured in the special-purpose control housing, every road control unit is mainly by the digital temperature regulating control, SCR AC electric power controller and temperature thermocouple constitute, form the closed loop thermal control loop, temperature control system utilizes 5 tunnel separate temperature difference control units to realize the PID adjustment by the digital temperature regulating control, control 4 blocks of hot plates and the hot basin temperature difference with respect to cold drawing respectively, display instrument and multi way temperature follow the inspection unit can show the hot plate and the current temperature difference of hot basin.
5. suitable double cone scanning type infrared horizon instrument ground performance according to claim 1 detects the earth simulator for earth of usefulness, it is characterized in that, the surface coating of the simulation earth infrared radiation of the hot plate of cold-hot plate component and the hot basin of hot basin component is organic pitch-dark, anodizing sandblasts on the surface of the cold drawing simulation space cold-scarce scape of cold-hot plate component, design the requirement of going up to satisfy to infrared radiation surface emissivity characteristic, thin film heater has been selected in the heating of hot plate and hot basin for use, is configured in the back side of hot plate and hot basin radiating surface; Hot plate and hot basin have adopted heat insulation and insulated design, between hot plate and cold drawing, supporting structure, between hot basin and supporting structure, the shell; The maximum heating power of temperature control system is less than 2Kw, and the temperature rise time is 45min the most slowly, and temperature difference range of control is at 20~40 ℃, and accuracy of temperature control is between ± 0.5 ℃, and the non-uniform temperature degree is less than ± 1.5 ℃.
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Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101462599B (en) * 2008-12-15 2011-04-27 中国科学院上海技术物理研究所 A New Earth Simulator for Ground Detection of Static Infrared Horizon
CN101607604B (en) * 2009-07-02 2012-05-23 哈尔滨工业大学 Integrated executive mechanism of satellite attitude control and thermal control and control method thereof
CN102310953B (en) * 2010-06-29 2013-08-28 长春理工大学 Portable earth simulator
CN102092488B (en) * 2010-12-31 2013-04-10 北京控制工程研究所 Dual-chord width earth simulator
CN102175247B (en) * 2011-01-14 2012-11-14 中国科学院上海技术物理研究所 Method for improving altitude measurement precision of linear array static infrared horizon sensor
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CN103983231B (en) * 2014-05-16 2016-02-03 上海微小卫星工程中心 A kind of base and use the infrared horizon of this base
CN105197262B (en) * 2015-09-17 2017-07-28 哈尔滨工业大学 Earth target simulator in spacecraft ground simulation
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CN106828988B (en) * 2016-11-30 2023-09-12 中国科学院上海技术物理研究所 Earth simulator for linear array infrared earth sensor variable orbit polarity measurements
CN106500730B (en) * 2016-11-30 2019-09-27 中国科学院上海技术物理研究所 Attitude Simulation Method Based on Linear Array Earth Sensor Variable Orbit Earth Simulator
CN106643795A (en) * 2016-11-30 2017-05-10 中国科学院上海技术物理研究所 Simulation method based on area array earth sensor semi-physical simulation earth simulator
CN119223266B (en) * 2024-09-11 2025-04-18 中国科学院上海技术物理研究所 A method, device and storage medium for measuring the attitude of a spacecraft

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5437030A (en) * 1990-10-31 1995-07-25 Grumman Aerospace Corporation Self-configuring test sytstem
US20050029405A1 (en) * 2003-07-25 2005-02-10 Anglin Patrick T. Predicting, bounding and mitigating satellite attitude disturbances arising from infrared earth sensors for satellites in inclined, elliptical orbits

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5437030A (en) * 1990-10-31 1995-07-25 Grumman Aerospace Corporation Self-configuring test sytstem
US20050029405A1 (en) * 2003-07-25 2005-02-10 Anglin Patrick T. Predicting, bounding and mitigating satellite attitude disturbances arising from infrared earth sensors for satellites in inclined, elliptical orbits

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
卫星控制系统多转台多模拟器半物理仿真方法. 刘慎钊.航天控制,第22卷第4期. 2004 *
圆锥扫描式红外地平仪原理. 董峰等.红外月刊,第12期. 2000 *
高精度大型地球模拟器及红外标定转台. 何柏年等.控制工程. 1985 *

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