On-orbit thermal deformation prediction for a high-resolution satellite camera

Zhang, Heng; Zhao, Xinbing; Mei, Qiang; Wang, Yue; Song, Shaoyun; Feng, Yilin

doi:10.1016/j.applthermaleng.2021.117152

Cited by 20 publications

(9 citation statements)

References 19 publications

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“…The thermal environment for a satellite in GEO can be calculated with the same methodologies that are presented by González-Bárcena et al 42 for LEO. Another approach followed by Zhang et al 53 is to neglect both the albedo and OLR heat flows considering only the prevalent direct solar radiation at these altitudes.…”

Section: Thermal Loadsmentioning

confidence: 99%

“…79 The heat transfer problem can be computed through any of the methods while the thermo-elastic problem is usually solved by FEA. 53,[80][81][82] To compute surface deformations induced by in-orbit vibration loads, the surface deformations are computed with FEA and statistical energy analysis (SEA). The first is used to obtain the response to low-excitation frequencies, which enable a more deterministic analysis of the system.…”

Section: Surface Deformations Of Optical Componentsmentioning

confidence: 99%

See 1 more Smart Citation

Opto-thermo-mechanical phenomena in satellite free-space optical communications: survey and challenges

Badás,

Piron,

Bouwmeester

et al. 2023

Opt. Eng.

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Growing interest in free-space optical communication, due to the high bandwidth and security provided by these links, has generated the necessity of designing high-performance satellite terminals. In order to develop these terminals, the optothermo-mechanical phenomena that appear in the space environment and their effect on optical communication links have to be understood in detail. A review of the opto-thermo-mechanical phenomena occurring in spaceborne terminals is presented, describing the relevance of each of them. The methods found to compute the impact on the communication performance due to opto-thermo-mechanical phenomena are collected by building the bridge between the optical and communication performance parameters. Finally, techniques available to mitigate the detrimental effects of these phenomena are classified, and the relevant research challenges are identified.

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Section: Thermal Loadsmentioning

confidence: 99%

Section: Surface Deformations Of Optical Componentsmentioning

confidence: 99%

Opto-thermo-mechanical phenomena in satellite free-space optical communications: survey and challenges

Badás,

Piron,

Bouwmeester

et al. 2023

Opt. Eng.

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“…At present, the thermal design of most space camera focal plane components abroad adopts the direct way of heat conduction aluminium strip or heat pipe and radiation heat dissipation plate to dissipate heat, or is directly exposed to the space environment, the outer surface is wrapped with multi-layer heat insulation components, and the refrigerator is used for active refrigeration under high temperature conditions, and the closed-loop active heating loop is used under low temperature conditions to maintain the focal plane temperature at a certain level. NASA's Earth Observation Satellite-1 (EO-1) carries an Advanced Land Imager (ALI), whose thermal control of the focal surface uses a thermally conductive aluminium strip to connect the focal surface and the heat dissipation surface, and a compensation heating device is set on the aluminium strip [4] . In China, for example, Tao Yang and Shilei Zhao of Beijing Institute of Space Mechatronics have designed a new type of loop heat pipe for simultaneous precision temperature control of multiple CCDs [5] .…”

Section: Introductionmentioning

confidence: 99%

Thermal design of focal plane assembly of wavefront camera for exoplanet imaging corona module

Wen,

Jiang,

et al. 2024

J. Phys.: Conf. Ser.

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The focal plane assembly of wavefront camera is the key imaging device of wavefront detection camera and the key load of the exoplanet imaging coronagraph module. In order to ensure the imaging quality and reduce the dark current and thermal noise, it is necessary to effectively dissipate the heat of the focal plane CCD and other high-power electronic devices to ensure the working performance and reliability of the focal plane assembly. Based on the limited space and cooling resources, this paper adopts the flexible graphene heat conducting cable and grooved heat pipes, and carries out detailed thermal design and thermal analysis of its cooling path. The finite element model is established by thermal analysis software and thermal simulation is carried out. in that steady state, the work temperature range of the CCD chip is -12.8∼-10.9°C, which meets the temperature control index, and the work temperatures of other components are also within the design requirements, which indicate that the thermal design scheme is reasonable and feasible, and meets the task requirements.

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“…With the development of aerospace optical remote sensing technology, data images with high resolution have been widely used in many national economic fields such as meteorological observation, resource investigation and national defense construction. [1][2][3] With the improvement of resolution and precision, it brings more severe challenges to the optical platform structure. In order to enhance the payload and reduce cost, it is urgent to improve the lightweight level and compressive performance of the opto-mechanical structure.…”

Section: Introductionmentioning

confidence: 99%

Fabrication and compressive performance of novel lightweight C/SiC honeycomb for ultrahigh stability structures

Zhang

Yang

et al. 2023

Jnl of Sandwich Structures & Materials

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As for high resolution satellite application field, novel C/SiC honeycomb sandwich structure is the first to propose and develop on account of such many attractive properties as excellent ultrahigh dimensional stability in thermal and moisture coupling environment, lightweight and high load-bearing. Three types of C/SiC honeycomb sandwich structures were fabricated for the first time as opto-mechanical structure in satellite. The innovative interlayer-crosslinking method to weave the continuous carbon fiber fabric of honeycomb core was proposed. The compressive properties of novel C/SiC honeycomb sandwich structures were investigated. Meanwhile, the damage mechanism for sandwich structures were analyzed by non-destructive testing. The results showed that the innovative fabrication processing possessed the capability to prepare high quality C/SiC honeycomb, which was shown from the volume and distribution of pores in the X-ray tomography. The compression modulus and strength of the C/SiC honeycomb reached 927 MPa and 10.76 MPa, and showed better rigidity and higher strength compared with classical honeycombs. Two main types of cracks wall were found in the C/SiC honeycomb, i.e., the horizontal ones in the wall with t thickness and the inclined ones in the wall with 2 t thickness. The outstanding compressive performance was attributed to the high mechanical property of ceramic-matrix composite with fiber pull-out mechanism. The exceptional lightweight capacity was inherited from the low bulk density of honeycomb structure ranged from 0.08 g/cm3 to 0.15 g/cm3. This study can help for the development of lightweight materials for opto-mechanical structure in aerospace optical remote sensing technology.

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On-orbit thermal deformation prediction for a high-resolution satellite camera

Cited by 20 publications

References 19 publications

Opto-thermo-mechanical phenomena in satellite free-space optical communications: survey and challenges

Opto-thermo-mechanical phenomena in satellite free-space optical communications: survey and challenges

Thermal design of focal plane assembly of wavefront camera for exoplanet imaging corona module

Fabrication and compressive performance of novel lightweight C/SiC honeycomb for ultrahigh stability structures

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