CN116674770A - Telescope thermal control method suitable for Lagrange point L2 aircraft - Google Patents
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Abstract
本发明提供了一种适应日地拉格朗日点L2飞行器的望远镜热控方法，其特征在于，包括如下步骤：S1、采用卫星帆板遮挡L2轨道的太阳直接照射，在空间望远镜遮光罩和主体外表面包覆多层隔热组件；S2、为空间望远镜设计载荷控温舱，望远镜主体安装于载荷控温舱内；S3、对望远镜底部舱板采用基于脉冲宽度调制的PID高精度控温算法进行主动温控；S4、通过粗控和精控两种类型的加热器补偿主、次镜通过入光口与冷黑背景的辐射漏热；S5、对望远镜次镜支撑桁架采用变热流密度加热器解决温度均匀性问题。
The invention provides a kind of telescope thermal control method adapting to the L2 aircraft of the Sun-Earth Lagrangian point, it is characterized in that, comprises the following steps: S1, adopts satellite sail plate to block the direct sunlight of L2 orbit, in the space telescope shading cover and The outer surface of the main body is covered with multi-layer heat insulation components; S2, design a load temperature control cabin for the space telescope, and the main body of the telescope is installed in the load temperature control cabin; S3, adopt PID high-precision temperature control based on pulse width modulation for the bottom cabin of the telescope Algorithm for active temperature control; S4, through two types of heaters, coarse control and fine control, to compensate the radiation heat leakage of the primary and secondary mirrors through the light entrance and the cool black background; S5, adopt variable heat flux density for the supporting truss of the secondary mirror of the telescope The heater solves the temperature uniformity problem.
Description
技术领域technical field
本发明涉及飞行器有效载荷热控技术领域，具体涉及一种适应日地拉格朗日点L2飞行器(简称日地L2飞行器)的光学望远镜高稳定度热控方法。The invention relates to the technical field of aircraft payload thermal control, in particular to a high-stability thermal control method for an optical telescope adapted to a Sun-Earth Lagrangian point L2 aircraft (abbreviated as a Sun-Earth L2 aircraft).
背景技术Background technique
在日地拉格朗日点，卫星受太阳、地球两大天体引力总用能够保持相对静止。满足该条件的点有五个，L1点轨道位于太阳、地球之间，观测背离太阳天区易受到地球遮挡；L3点轨道位于日地连线上，与地球通信易受到太阳高能粒子的影响；L4、L5点轨道与日心地球拖尾轨道类似，距离地球约1.5亿公里，消耗燃料较多并且通信成本高。L2点轨道位于日地连线的延长线上，没有地球重力梯度影响，也可以实现全天时观测，轨道的热辐射环境比较稳定，是观测宇宙、天文研究的理想场所。国外已发射多颗运行于日地L2的科学卫星，如欧洲航天局ESA发射的天文卫星“普朗克”和“赫歇尔”，美国国家航空航天局NASA的“詹姆斯韦伯”空间望远镜。At the Sun-Earth Lagrangian point, the satellite can remain relatively stationary under the gravitational force of the two celestial bodies, the sun and the earth. There are five points that meet this condition. The L1 point orbit is located between the sun and the earth, and the observation of the sky area away from the sun is easily blocked by the earth; the L3 point orbit is located on the line connecting the sun and the earth, and the communication with the earth is easily affected by the sun's high-energy particles; L4 and L5 point orbits are similar to the trailing orbits of the heliocentric Earth, about 150 million kilometers away from the earth, consume more fuel and have high communication costs. The L2 point orbit is located on the extension line of the connection between the sun and the earth. Without the influence of the earth's gravity gradient, it can also achieve all-day observation. The thermal radiation environment of the orbit is relatively stable, and it is an ideal place for observing the universe and astronomical research. Foreign countries have launched many scientific satellites operating at the L2 of the sun and the earth, such as the astronomical satellites "Planck" and "Herschel" launched by the European Space Agency ESA, and the "James Webb" space telescope of the National Aeronautics and Space Administration NASA.
对于行星探测的天体测量技术，利用目标星和参考星之间相对的位置变化实现行星测量，通常要求测量精度达到微角秒级别。对于望远镜光学系统技术来讲，光学系统的稳定性是最重要的。由于望远镜光学和结构材料差异、温度差别、外界振动等因素的影响，将造成望远镜内方位元素的变化，进而造成光学系统稳定性误差。因此需根据L2飞行器空间环境的特点，结合高精度、高稳定性的热控需求，设计一套能适应日地L2轨道、能够实现空间光学望远镜高稳定度温度控制的热控方法。For the astrometric technology of planetary detection, the relative position change between the target star and the reference star is used to realize the planetary measurement, and the measurement accuracy is usually required to reach the micro-arcsecond level. For telescope optical system technology, the stability of the optical system is the most important. Due to the influence of factors such as telescope optics and structural material differences, temperature differences, and external vibrations, the azimuth elements in the telescope will change, which in turn will cause stability errors in the optical system. Therefore, according to the characteristics of the space environment of the L2 aircraft, combined with the high-precision and high-stability thermal control requirements, it is necessary to design a thermal control method that can adapt to the Sun-Earth L2 orbit and can achieve high-stability temperature control of the space optical telescope.
发明内容Contents of the invention
解决的技术问题Technical issues resolved
针对空间望远镜高精度、高稳定性热控的天体测量需求，本发明提供了一种适应日地拉格朗日点L2飞行器的空间光学望远镜热控方法，该方法能够实现对日地L2飞行器空间望远镜各个器件精准温度控制。Aiming at the astrometric requirements for high-precision and high-stability thermal control of space telescopes, the present invention provides a thermal control method for space optical telescopes adapted to the L2 aircraft at the Sun-Earth Lagrangian point. Precise temperature control of each component of the telescope.
技术方案Technical solutions
为实现以上目的，本发明通过以下技术方案予以实现：To achieve the above object, the present invention is achieved through the following technical solutions:
本发明提供一种适应日地拉格朗日点L2飞行器的空间望远镜热控方法，包括如下步骤：The invention provides a thermal control method of a space telescope adapted to the L2 aircraft of the Sun-Earth Lagrangian point, comprising the following steps:
S1、采用卫星帆板遮挡L2轨道的太阳直接照射，在空间望远镜遮光罩和主体外表面包覆多层隔热组件；S1. Use satellite sails to block the direct sunlight of the L2 orbit, and cover the space telescope hood and the outer surface of the main body with multi-layer heat insulation components;
S2、为空间望远镜设计载荷控温舱，望远镜主体安装于载荷控温舱内；S2. Design a load temperature control cabin for the space telescope, and the main body of the telescope is installed in the load temperature control cabin;
S3、对望远镜底部舱板采用基于脉冲宽度调制的PID高精度控温算法进行主动温控；S3. The PID high-precision temperature control algorithm based on pulse width modulation is used to actively control the temperature of the bottom deck of the telescope;
S4、通过粗控和精控两种类型的加热器补偿主、次镜通过入光口与冷黑背景的辐射漏热；S4. Compensate the radiation heat leakage of the primary and secondary mirrors through the light entrance and the cool black background through two types of heaters, coarse control and fine control;
S5、对望远镜次镜支撑桁架采用变热流密度加热器解决温度均匀性问题；S5. The variable heat flux density heater is used for the supporting truss of the secondary mirror of the telescope to solve the problem of temperature uniformity;
进一步地，步骤S1具体包括：空间望远镜遮光罩和主体均包覆15单元低温多层隔热组件，并且最外层采用导电型聚酰亚胺镀银二次表面镜。Further, step S1 specifically includes: the shading cover and the main body of the space telescope are both covered with 15 units of low-temperature multi-layer heat insulation components, and the outermost layer is a conductive polyimide silver-plated secondary surface mirror.
进一步地，步骤S2具体包括：载荷控温舱为卫星平台的一个单独舱体，材料为铝合金，与卫星平台隔热，在控温舱板上粘贴主动加热器进行控温，控温目标20℃。控温舱外表面包覆15单元多层隔热组件，内表面不做特殊处理。Further, step S2 specifically includes: the load temperature control cabin is a separate cabin of the satellite platform, the material is aluminum alloy, and is insulated from the satellite platform, and an active heater is pasted on the temperature control cabin to control the temperature. The temperature control target is 20 ℃. The outer surface of the temperature control cabin is covered with 15 units of multi-layer insulation components, and the inner surface is not specially treated.
进一步地，步骤S3所述热控方法采用专用控温仪根据热敏电阻采集的温度数据直接进行控制，采样周期1s，控温周期5s，控温目标20.1℃。Further, the thermal control method described in step S3 uses a dedicated temperature controller to directly control the temperature data collected by the thermistor, the sampling period is 1s, the temperature control period is 5s, and the temperature control target is 20.1°C.
进一步地，步骤S4具体包括，将粗控和精控加热器布置于主、次镜支撑结构上，通过支撑结构的辐射作用对镜片进行温控。考虑到主、次镜单相偏离目标温度，加热器均采用开关闭环形式，粗控温加热器指标19～20℃，精控温加热器指标20.1～20.12℃。Further, step S4 specifically includes arranging the coarse control and fine control heaters on the supporting structures of the primary and secondary mirrors, and controlling the temperature of the lenses through the radiation effect of the supporting structures. Considering that the primary and secondary mirror single-phase deviates from the target temperature, the heaters are all in the form of switch and closed loop. The index of the coarse temperature control heater is 19-20°C, and the index of the fine-control temperature heater is 20.1-20.12°C.
进一步地，步骤S5具体包括，主、次镜之间的支撑桁架外部包覆多层隔热组件，考虑抑制杂散光的影响，多层组件外表面采用渗碳黑膜。沿着次镜支撑桁架粘贴主动加热器进行控温，为了防止出现两端高，中间低的温度分布，需要改变加热器的热流密度，根据仿真结果设置热流密度分布，解决支撑桁架的温度均匀性问题。加热器控温目标20.1～20.12℃。Further, step S5 specifically includes that the outer surface of the support truss between the primary and secondary mirrors is coated with a multi-layer heat insulation component, and the outer surface of the multi-layer component is made of a carburized black film in consideration of suppressing the influence of stray light. Paste the active heater along the supporting truss of the secondary mirror for temperature control. In order to prevent the temperature distribution with high ends and low temperature in the middle, it is necessary to change the heat flux density of the heater. Set the heat flux distribution according to the simulation results to solve the temperature uniformity of the support truss question. The temperature control target of the heater is 20.1-20.12°C.
进一步地，对所述望远镜的温度控制方法还包括：Further, the temperature control method for the telescope also includes:
在所述望远镜的支撑杆架上粘贴石墨导热条带增强材料导热作用并包覆多层隔热组件，其中，所述支撑杆架底部是整个望远镜载荷与所述卫星平台的安装接口。Graphite heat-conducting strips are pasted on the support rod frame of the telescope to enhance the heat conduction effect of the material and cover the multi-layer heat insulation assembly, wherein the bottom of the support rod frame is the installation interface of the entire telescope load and the satellite platform.
有益效果Beneficial effect
本发明提供了一种适应日地拉格朗日点L2飞行器的光学望远镜热控方法，通过采用主动热控方案，根据卫星轨道特点及空间探测需求，能够实现对日地L2飞行器中望远镜各个器件精准温度控制，并且能适应多种空间飞行状态下进行温度控制。The invention provides an optical telescope thermal control method adapted to the L2 aircraft of the Sun-Earth Lagrangian point. By adopting an active thermal control scheme, according to the characteristics of satellite orbits and space detection requirements, it is possible to realize the control of each device of the telescope in the L2 aircraft of the Sun-Earth. Accurate temperature control, and can adapt to temperature control in various space flight states.
附图说明Description of drawings
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍。显而易见地，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings that are required in the description of the embodiments or the prior art. Apparently, the drawings in the following description are only some embodiments of the present invention, and those skilled in the art can obtain other drawings according to these drawings without creative efforts.
图1为本发明一实施例提供的适应日地拉格朗日点L2飞行器的光学望远镜热控方法步骤示意图；Fig. 1 is a schematic diagram of steps of an optical telescope thermal control method adapted to a sun-earth Lagrangian point L2 aircraft provided by an embodiment of the present invention;
图2为本发明一实施例提供的空间望远镜在卫星上的安装位置示意图；Fig. 2 is a schematic diagram of the installation position of the space telescope on the satellite provided by an embodiment of the present invention;
图3为本发明一实施例提供的空间望远镜总体热控方案示意图；Fig. 3 is a schematic diagram of the overall thermal control scheme of the space telescope provided by an embodiment of the present invention;
图4和图5为本发明一实施例提供的望远镜主次镜及桁架结构热控设计示意图；Figure 4 and Figure 5 are schematic diagrams of the thermal control design of the primary and secondary mirrors of the telescope and the truss structure provided by an embodiment of the present invention;
图6和图7为本发明一实施例提供的望远镜的折转镜1位置及热控设计示意图；Figure 6 and Figure 7 are schematic diagrams of the position and thermal control design of the folding mirror 1 of the telescope provided by an embodiment of the present invention;
图8为本发明一实施例提供的望远镜的三镜、折转镜2和折转镜3位置示意图；Fig. 8 is a schematic diagram of the positions of the three mirrors, the folding mirror 2 and the folding mirror 3 of the telescope provided by an embodiment of the present invention;
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作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 purpose, technical solutions and advantages of the embodiments of the present invention more clear, 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. Apparently, the described embodiments are some, but not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
参阅图1，本发明一实施例提供了一种适应日地拉格朗日点L2飞行器的热控方法，包括如下步骤：Referring to Fig. 1, an embodiment of the present invention provides a thermal control method for an L2 aircraft adapted to the Sun-Earth Lagrangian point, including the following steps:
S1、采用卫星帆板遮挡L2轨道的太阳直接照射，在空间望远镜遮光罩和主体外表面包覆多层隔热组件；S1. Use satellite sails to block the direct sunlight of the L2 orbit, and cover the space telescope hood and the outer surface of the main body with multi-layer heat insulation components;
S2、为空间望远镜设计载荷控温舱，望远镜主体安装于载荷控温舱内；S2. Design a load temperature control cabin for the space telescope, and the main body of the telescope is installed in the load temperature control cabin;
S3、对望远镜底部舱板采用基于脉冲宽度调制的PID高精度控温算法进行主动温控；S3. The PID high-precision temperature control algorithm based on pulse width modulation is used to actively control the temperature of the bottom deck of the telescope;
S4、通过粗控和精控两种类型的加热器补偿主、次镜通过入光口与冷黑背景的辐射漏热；S4. Compensate the radiation heat leakage of the primary and secondary mirrors through the light entrance and the cool black background through two types of heaters, coarse control and fine control;
S5、对望远镜次镜支撑桁架采用变热流密度加热器解决温度均匀性问题；S5. The variable heat flux density heater is used for the supporting truss of the secondary mirror of the telescope to solve the problem of temperature uniformity;
参阅图2，采用卫星帆板遮挡L2轨道的太阳直接照射，在空间望远镜遮光罩和主体外表面包覆多层隔热组件，望远镜主体安装于载荷控温舱内；Referring to Figure 2, the satellite sails are used to block the direct sunlight of the L2 orbit, and the space telescope hood and the outer surface of the main body are covered with multi-layer heat insulation components, and the main body of the telescope is installed in the load temperature control cabin;
在本实施例中，所述载荷控温舱的材料为铝合金，表面粘贴薄膜加热片，内外侧均包覆多层隔热组件。其中，所述载荷控温舱控温指标一般为20.1±0.5℃，用于隔离平台单机温度干扰，为有效载荷提供一个稳定的热环境。In this embodiment, the material of the load temperature control chamber is aluminum alloy, the surface is pasted with a film heating sheet, and the inner and outer sides are covered with multi-layer heat insulation components. Among them, the temperature control index of the load temperature control cabin is generally 20.1±0.5°C, which is used to isolate the temperature interference of the single machine of the platform and provide a stable thermal environment for the payload.
在本实施例中，所述望远镜采用反太阳指向设置，通过遮阳板及所述卫星平台舱挡住太阳辐射热流。其中，对于望远镜，长焦距、大口径、高分辨率的空间相机通常要求达到或接近衍射极限，细微扰动都将对相机成像质量产生显著影响，对温度变化非常敏感。空间望远镜为了保证成像质量，要求温度控制精度应该达到每次观测时间2小时内小于45mK。In this embodiment, the telescope adopts an anti-solar pointing arrangement, and the solar radiation heat flow is blocked by the sun visor and the satellite platform cabin. Among them, for telescopes, space cameras with long focal length, large aperture, and high resolution are usually required to reach or approach the diffraction limit, and slight disturbances will have a significant impact on the imaging quality of the camera, which is very sensitive to temperature changes. In order to ensure the imaging quality of the space telescope, the temperature control accuracy should be less than 45mK within 2 hours of each observation time.
在本实施例中，参阅图3，根据望远镜所处外部环境的不同将其分为两个部分：In this embodiment, referring to Fig. 3, it is divided into two parts according to the difference of the external environment where the telescope is located:
1)辐射换热区：光学平台至入光口之间的部分，包括遮光罩，主镜、次镜及其支撑结构，称之为辐射换热区。辐射换热区各组件无热耗，透过入光口存在与外部冷黑背景的辐射作用；1) Radiation heat exchange area: The part between the optical platform and the light entrance, including the hood, primary mirror, secondary mirror and their supporting structures, is called the radiation heat exchange area. There is no heat loss for each component in the radiation heat exchange area, and there is radiation effect with the external cool black background through the light entrance;
2)干扰抑制区：载荷其余部分，包括三镜、五镜及支架，电子学，称之为干扰抑制区。这部分为接近封闭空间，但会受到卫星平台温度波动及望远镜电子学工作的影响。辐射换热区向宇宙深冷空间的散热需要通过加热器来补偿，考虑到外热流环境稳定，采用开关型加热器控制方法对光学系统部件进行控温，控温区间20.1～20.12℃。干扰抑制区的温控一般采用两级控温的方法。在卫星平台设计载荷控温舱，对舱内各个面板进行主动温控，与卫星平台隔热，作为二级控温对象，隔离平台温度的影响，控温目标20±0.5℃。望远镜干扰抑制区安装于载荷控温舱内，将望远镜底部舱板作为一级控温对象，采用基于脉冲宽度调制的PID高精度控温算法进行控温。焦面探测器与望远镜主体隔热连接，本体包覆多层隔热组件，通过环路热管将热量传导至外部独立散热面单独进行散热。同样基于两级控温的方法，将散热面作为二级控温对象，探测器机箱作为一级控温对象，实现高稳定度温控。2) Interference suppression area: The rest of the load, including three mirrors, five mirrors and brackets, electronics, is called interference suppression area. This part is a near-enclosed space, but is subject to fluctuations in the temperature of the satellite platform and the operation of the telescope's electronics. The heat dissipation from the radiative heat exchange area to the deep-cold space of the universe needs to be compensated by heaters. Considering the stability of the external heat flow environment, the temperature control method of the optical system components is controlled by a switch heater control method, and the temperature control range is 20.1-20.12°C. The temperature control in the interference suppression area generally adopts a two-stage temperature control method. The load temperature control cabin is designed on the satellite platform, and the active temperature control of each panel in the cabin is insulated from the satellite platform. It is used as a secondary temperature control object to isolate the influence of the platform temperature. The temperature control target is 20±0.5°C. The interference suppression area of the telescope is installed in the load temperature control cabin, and the bottom cabin of the telescope is used as the first-level temperature control object, and the temperature is controlled by the PID high-precision temperature control algorithm based on pulse width modulation. The focal plane detector is insulated from the main body of the telescope. The main body is covered with multi-layer heat insulation components, and the heat is conducted to the external independent heat dissipation surface through the loop heat pipe for independent heat dissipation. Also based on the two-level temperature control method, the heat dissipation surface is used as the second-level temperature control object, and the detector chassis is used as the first-level temperature control object to achieve high-stability temperature control.
在本实施例中，参阅图4和图5，对辐射换热区的温控方法包括：In this embodiment, referring to Fig. 4 and Fig. 5, the temperature control method for the radiation heat exchange area includes:
1)在所述望远镜的主、次镜支撑结构上分别布置粗控温加热器和精细控温加热器，所述粗控温加热器常开，所述精细控温加热器采用开关控温策略。其中，望远镜的主、次镜通过背面支撑结构进行辐射控温，补偿向空间的辐射漏热。主、次境正面为极低发射率0.05，背面为高发射率0.9。主、次境支撑结构喷涂黑漆，为高发射率表面，支撑结构与境面侧面之间包覆多层隔热组件，形成一个封闭腔体。1) A coarse temperature control heater and a fine temperature control heater are respectively arranged on the primary and secondary mirror support structures of the telescope, the coarse temperature control heater is always on, and the fine temperature control heater adopts a switch temperature control strategy . Among them, the primary and secondary mirrors of the telescope carry out radiation temperature control through the back support structure to compensate for the radiation heat leakage into space. The front of the main and secondary borders has an extremely low emissivity of 0.05, and the back has a high emissivity of 0.9. The main and secondary environment support structures are sprayed with black paint, which is a high-emissivity surface, and the support structure and the side surfaces of the environment are covered with multi-layer heat insulation components to form a closed cavity.
2)设计变热流密度薄膜加热器，沿着所述望远镜的次镜支撑桁架粘贴，对所述望远镜的主、次镜之间的支撑桁架进行主动控温。其中，主、次镜之间的支撑桁架包覆多层隔热组件，考虑抑制杂散光的影响，多层组件外表面采用渗碳黑膜。2) Design a thin-film heater with variable heat flux density, stick it along the supporting truss of the secondary mirror of the telescope, and actively control the temperature of the supporting truss between the primary and secondary mirrors of the telescope. Among them, the support truss between the primary and secondary mirrors is covered with multi-layer heat insulation components. Considering the suppression of stray light, the outer surface of the multi-layer components is made of carburized black film.
3)在折转镜1的支架外侧除入光口外均包覆多层隔热组件，内侧喷涂黑漆。其中，折转镜1位于主镜孔内部，通过安装于光学平台上的支架进行固定，如下图6和图7所示。3) The outer side of the bracket of the folding mirror 1 is covered with multi-layer heat insulation components except the light entrance, and the inner side is sprayed with black paint. Wherein, the folding mirror 1 is located inside the main mirror hole, and is fixed by a bracket installed on the optical table, as shown in Fig. 6 and Fig. 7 below.
在本实施例中，对干扰抑制区的温控方法包括：In this embodiment, the temperature control method for the interference suppression zone includes:
1)将所述望远镜底部舱体内部喷涂高发射率黑漆，舱体外部布置主动加热器，并包覆多层隔热组件。其中，如图8所示，三镜，折转镜2和折转镜3处于望远镜底部舱体内，相对较为封闭，热环境比较稳定。1) The inside of the cabin at the bottom of the telescope is sprayed with high-emissivity black paint, and the outside of the cabin is equipped with an active heater and covered with multi-layer heat insulation components. Among them, as shown in Figure 8, the three mirrors, the folding mirror 2 and the folding mirror 3 are located in the bottom cabin of the telescope, which is relatively closed and the thermal environment is relatively stable.
2)在所述望远镜的支撑杆架上粘贴石墨导热条带增强材料导热作用并包覆多层隔热组件，其中，所述支撑杆架底部是整个望远镜载荷与所述卫星平台的安装接口。其中，望远镜的支撑杆架底部是整个望远镜载荷与卫星平台的安装接口，位于载荷控温舱内，接口温度20±0.5℃。2) Paste a graphite heat-conducting strip on the support rod frame of the telescope to enhance the heat conduction effect of the material and cover the multi-layer heat insulation component, wherein the bottom of the support rod frame is the installation interface of the entire telescope load and the satellite platform. Among them, the bottom of the support rod of the telescope is the installation interface between the entire telescope payload and the satellite platform, which is located in the payload temperature control cabin, and the interface temperature is 20±0.5°C.
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，并不会使相应技术方案的本质脱离本发明各实施例技术方案的保护范围。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 described in the foregoing embodiments The recorded technical solutions are modified, or some of the technical features are replaced equivalently; and these modifications or replacements will not make the essence of the corresponding technical solutions deviate from the protection scope of the technical solutions of the various embodiments of the present invention.
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| CN116986020A (en) * | 2023-09-26 | 2023-11-03 | 长光卫星技术股份有限公司 | Small satellite active thermal control method based on thermal characteristics of controlled object |
| CN119036943A (en) * | 2024-10-30 | 2024-11-29 | 中国科学院西安光学精密机械研究所 | Precise temperature control large-caliber thin-wall carbon fiber bearing cylinder structure |
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| CN116986020A (en) * | 2023-09-26 | 2023-11-03 | 长光卫星技术股份有限公司 | Small satellite active thermal control method based on thermal characteristics of controlled object |
| CN116986020B (en) * | 2023-09-26 | 2023-12-01 | 长光卫星技术股份有限公司 | Small satellite active thermal control method based on thermal characteristics of controlled object |
| CN119036943A (en) * | 2024-10-30 | 2024-11-29 | 中国科学院西安光学精密机械研究所 | Precise temperature control large-caliber thin-wall carbon fiber bearing cylinder structure |
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