Design and optimization of the CFRP mirror components

Wei, Lei; Zhang, Lei; Gong, Xiaoxue

doi:10.1007/s13320-017-0388-2

Cited by 6 publications

(5 citation statements)

References 16 publications

(18 reference statements)

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“…Carbon-fiber-reinforced plastics (CFRPs) have excellent mechanical properties, such as high stiffness, high strength and low coefficient of thermal expansion (CTE), and are considered to be the next generation of aerospace application materials [10][11][12][13]. In recent years, structural thermal stability has increasingly been accomplished through the use of carbon-fiber-reinforced composites.…”

Section: Introductionmentioning

confidence: 99%

Thermal Stability Design of Asymmetric Support Structure for an Off-Axis Space Camera

et al. 2021

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With the development of space optical remote sensing technology, especially off-axis space cameras, the thermal dimensional stability of the support structure has become increasingly demanding. However, the asymmetry of the camera structure has not been fully considered in the past design of the thermal stability of off-axis cameras. In order to solve this problem, a support structure with very low thermal deformation in the asymmetric direction is presented in this paper for an off-axis TMA camera. By means of the negative axial thermal expansion coefficient of carbon-fiber-reinforced plastics (CFRP), a composite laminate with near zero-expansion was obtained by adjusting the direction of fiber laying, and the asymmetric feature of the off-axis remote sensing camera structure was fully considered, thus enabling the support structure to have good thermal dimensional stability. We carried out a thermal load analysis and an optical analysis of the whole camera in the case of a temperature rise of 5 °C. The results show that the zero-expansion support structure has good thermal stability, and the thermal deformation in the asymmetric direction of the camera is obviously smaller than that of the isotropic laminate support structure. Compared with the isotropic support structure, the influence of thermal deformation on MTF is reduced from 10.43% to 2.61%. This study innovatively incorporates the asymmetry of the structure into the thermal sta-bility design of an off-axis TMA camera and provides a reference for the thermal stability design of other off-axis space cameras.

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Section: Introductionmentioning

confidence: 99%

Thermal Stability Design of Asymmetric Support Structure for an Off-Axis Space Camera

et al. 2021

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“…The manufacturing of mirrors using composite materials has become a necessity for the next generation of optical elements of big size since it reduces weight, costs and time needed for production, while at the same time offering high stiffness and low thermal expansion coefficient (Wei et al, 2017). The method, called replication, consists of copying an optical quality mold surface with a series of layers of composite materials like carbon fiber impregnated with resin.…”

Section: Introductionmentioning

confidence: 99%

Mitigating print-through effects through an optimized method for CFRP mirror production in Chile

Castillo

Hamilton

Soto

et al. 2020

Preprint

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In the manufacturing process of Carbon Fiber Reinforced Polymer (CFRP) mirrors (replicated from a mandrel) the orientation of the unidirectional carbon fiber layers (layup) has a direct influence on different aspects of the final product, like its general (large scale) shape and local deformations. In particular, optical methods used to evaluate the surface's quality, can reveal the presence of print-through, a very common issue in CFPR manufacture. In practical terms, the surface's irregularities induced, among other artifacts, by print-through, produce unwanted scattering effects, which are usually mitigated applying extra layers of different materials to the surface. Since one of the main goals of CFPR mirrors is to decrease the final weight of the whole mirror system, adding more material goes in the opposite direction of that. For this reason a different layup method is being developed with the goal of decreasing print-through and improving sphericity while maintaining mechanical qualities and without the addition of extra material in the process.

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“…The most frequent design layout is a three-layered shell with the honeycomb reinforcement, less frequent is a thin shell with the reinforcing ribs over the convex surface [4,5]. The second form uses all carbon fiber not only as the top and bottom but also as the intermediate support [6]. The common features for all structures are, firstly, the requirements imposed for the shape and dimensional stability under thermal cycles resulting from orbiting and, secondly, low linear density (the mass in relation to the surface area) [4].…”

Section: Introductionmentioning

confidence: 99%

“…Addressing this manner, COMOTI decided to apply a thin 1µm gold coating over the reflective face, to create a smooth reflexive surface. A spherical mirror with Ø316 mm whose core cell reinforcement is an isogrid configuration was fabricated by Wei et al [6]. Compared with traditional ways of applying ultra-low-expansion glass (ULE) on the CFRP mirror surface, the method of nickel electroplating on the surface was found effective by the authors, and it reduces the processing cost and difficulty of the CFRP mirror.…”

Section: Introductionmentioning

confidence: 99%

On the Development of a Space Satellite Mirror with Intrinsic Self-Healing Properties

Vintilă

Condruz

Sandu

et al. 2019

MSF

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In the aerospace industry the demand for very strong and light components is a permanent objective and for this matter composite materials began to be used at large scales in construction of space structures. The presence of micrometeoroids and orbital debris in space, particularly in the lower earth orbit, presents a continuous hazard to orbiting satellites, spacecraft, and the International Space Station. Among the 8700 objects larger than 10 cm in Earth Orbits, only about 6% are operational satellites and the remainder is space debris. Likewise, a major challenge for space missions is the material selection due to the fact that in space materials present a higher degradation rate and they are subjected to wear and structural damage, especially when facing extreme environmental conditions. In this paper, a self-healing concept embedded into a Carbon Fiber Reinforced Polymer (CFRP) composite parabolic satellite mirror is under development at COMOTI Research & Development Institute for Gas Turbines. The goal of the research is to provide a material that increases the operational life of satellites in Low Earth Orbit (LEO). The work addresses two different but interconnected fields, material science for developing a multifunctional composite material having an embedded self-healing system and aerospace field for developing a new, lightweight structure. The self-healing system under study consists in a blend of microcapsules containing variations of dicyclopentadiene (DCPD) monomers, 5-Vinyl-2-norbornene (VNB), 5-Ethylidene-2-norbornene (5E2N or ENB) and ethylene glycol dicyclopentenyl ether methacrylate (EGDP).

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Design and optimization of the CFRP mirror components

Cited by 6 publications

References 16 publications

Thermal Stability Design of Asymmetric Support Structure for an Off-Axis Space Camera

Thermal Stability Design of Asymmetric Support Structure for an Off-Axis Space Camera

Mitigating print-through effects through an optimized method for CFRP mirror production in Chile

On the Development of a Space Satellite Mirror with Intrinsic Self-Healing Properties

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