Mechanical behaviour of tape springs used in the deployment of reflectors around a solar panel

Dewalque, Florence; Collette, Jean-Paul; Brüls, Olivier

doi:10.1016/j.actaastro.2016.03.029

Cited by 31 publications

(18 citation statements)

References 22 publications

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“…The allowable shear stress [τ] = 17 MPa. Based on the size of the hinges given in Delimont et al (2015), Dewalque et al (2016), and Naves et al (2017), the parameter values of the hinge are set. The radii of the inner cylinder and outer ring are r = 6 mm, R = 30 mm.…”

Section: Finite Element Simulationsmentioning

confidence: 99%

Design and Analysis of Flexible Hinge Used for Unfolding Spacecraft Solar Panels

Zhang

Yan

Kou

2019

J.Aerosp. Technol. Manag.

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Two stiffness models for a flexible hinge with large rotation angle are established based on the pseudo-rigid body method and the series or parallel relationship of flexible units. Finite element simulation of the flexible hinge is conducted in ANSYS to verify the two stiffness models of the flexible hinge. A multi-objective optimization method is used to optimize the design parameters of the hinge. The stiffness models of the flexible hinge are used to establish the optimized objective function of an optimization model to improve the rotation angle of the hinge under a certain radial stiffness. After optimization, the rotation angle can reach 70 deg when the rotational and radial stiffnesses are 1.29 N·mm/rad and 1.37 N/mm.

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Section: Finite Element Simulationsmentioning

confidence: 99%

Design and Analysis of Flexible Hinge Used for Unfolding Spacecraft Solar Panels

Zhang

Yan

Kou

2019

J.Aerosp. Technol. Manag.

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“…The obvious merits of membrane antennas are their large sizes and light weights, since they can be folded into a small stowage volume and deployed on orbit. Typical deploying methods include inflation [4], elastic ribs-driven method [5,6], Shape Memory Polymerinflation [7,8], and electrostatic forming [9,10], and the antenna shapes after deployment are either parabolic or planar. Despite extensive studies in the United States [11], Europe [12], China [13], Japan [14] etc., practical applications in a spaceborne environment are still very rare.…”

Section: Introductionmentioning

confidence: 99%

Theoretical and numerical studies on multi‐physical issues of space parabolic membrane antennas

Liu

et al. 2021

IET Microwaves Antenna & Prop

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Front-fed parabolic reflectors are among the most commonly used antennas in the industry. While in spaceborne applications, membrane reflectors are very promising due to their lightweight and foldable features. However, considering the large size, small thickness and low stiffness, solar radiation and microwave radiation will have considerable influences on the antennas' shape accuracy as well as the radiation characteristics. In this article, a theoretical approach is presented to solve the multi-physical effects of the parabolic antenna. The deformation of the reflector is derived by the shallow shell theory, taking into account the solar pressure, the microwave pressure and the thermal effects due to solar and microwave heating. The far-field electromagnetic radiation pattern is then obtained by considering the deformation of the reflector. On the other hand, a numerical approach combining the finite element method, the multi-level fast multipole method, and the large element physical optics is also presented. Numerical examples suggest good agreement between the theoretical and numerical results. The methods have been applied into the analysis of design models in the Space Solar Power Station project. Also, these approaches can be directly extended into other space membrane reflector antennas.This is an open access article under the terms of the Creative Commons Attribution-NonCommercial-NoDerivs License, which permits use and distribution in any medium, provided the original work is properly cited, the use is non-commercial and no modifications or adaptations are made.

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“…These are narrow metallic strips with a curved cross-section, that works under the simple torsion spring principle. 18,19 Furthermore, these elements have been proved to be useful to incorporate reflectors of solar light. 20 Nevertheless, their complexity is related to their (uncontrollable) non-linear mechanical behaviour.…”

Section: Introductionmentioning

confidence: 99%

“…20 Nevertheless, their complexity is related to their (uncontrollable) non-linear mechanical behaviour. 21 They also must be specifically configured for their final goal for a specific space mission, 19 which hinders the manufacture process. Thus, although they are passive mechanism with a final locking, they represent design complexities.…”

Section: Introductionmentioning

confidence: 99%

Conceptual design and finite element method validation of a new type of self-locking hinge for deployable CubeSat solar panels

Solís-Santomé

Urriolagoitia-Sosa

Romero-Ángeles

et al. 2019

Advances in Mechanical Engineering

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Deployable mechanisms in CubeSat satellites have many problems with the system that provides the anchor position. The main defect of the traditional deployment mechanisms for solar panels in CubeSats is the lack of position system to block the back-driving of the panel when it reaches the final phase of the deployment. This generates spurious oscillations in the panel, affecting the photovoltaic process as well as generating fatigue in the mechanical elements of the mechanism (hinge or pin). In this work, the design, analysis and manufacture of a deployment mechanism for CubeSat solar panels is shown. A finite element method analysis was carried out in a hinge with an integrated blocking system as well as a double torsion spring, which can be used on CubeSats. The outcome shows the layout of the described anchor hinge and the used double-torsion spring, which provides a positive direction torque transfer. Likewise, the performed numerical analyses on the designed system, reduce the weight and optimise the geometry of the mechanism, showing its feasibility as well as the potential applications and further research in the area.

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Mechanical behaviour of tape springs used in the deployment of reflectors around a solar panel

Cited by 31 publications

References 22 publications

Design and Analysis of Flexible Hinge Used for Unfolding Spacecraft Solar Panels

Design and Analysis of Flexible Hinge Used for Unfolding Spacecraft Solar Panels

Theoretical and numerical studies on multi‐physical issues of space parabolic membrane antennas

Conceptual design and finite element method validation of a new type of self-locking hinge for deployable CubeSat solar panels

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