Ultralight deployable booms for solar sails and other large gossamer structures in space

Block, Joern; Straubel, Marco; Wiedemann, Martin

doi:10.1016/j.actaastro.2010.09.005

Cited by 150 publications

(59 citation statements)

References 1 publication

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“…Thin-walled deployable composite boom (DCB) structures of hinge and lenticular boom varieties are of considerable interest in the aerospace field, with typical examples shown in Figure 1 [1][2][3][4][5][6] .…”

Section: Introductionmentioning

confidence: 99%

Thermal analysis of thin-walled deployable composite boom in simulated space environment

Bai

Shenoi

Xiong

2017

Composite Structures

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This paper seeks to investigate thermal behaviour of a thin-walled deployable composite boom (DCB) in a space environment using ground thermal-vacuum test and FEA methods. Thermal tests simulating a space environment include three key conditions, namely ultra-high level of vacuum (lower than 10 -5 Pa), heat sink (-180℃) that is realized using black panels with the liquid-nitrogen cooling system and thermal loading that is achieved through infrared lamps. The thermal tests of the DCB under seven typical heat fluxes were conducted to characterize heat transfer mechanisms and to obtain temperature fields. The basic heat transfer methods for the DCB in a space environment were surface radiation, cavity radiation and heat conduction. These led to significant temperature difference and gradient occurring on the irradiated and shadowed parts of the DCB at nighttime and daytime. FE models were established to predict temperature fields and thermally induced deformation. Good correlation was achieved between experimental and numerical results.

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Section: Introductionmentioning

confidence: 99%

Thermal analysis of thin-walled deployable composite boom in simulated space environment

Bai

Shenoi

Xiong

2017

Composite Structures

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“…Chinese Journal of Mechanical Engineering *Correspondence: guohw@hit.edu.cn 2 China State Key Laboratory of Robotics and System, Harbin Institute of Technology, Harbin 150001, China Full list of author information is available at the end of the article small size. Silver et al [15] proposed an integral folding hinge to deploy camera and investigated axial loading, bending induced buckling response.…”

Section: Open Accessmentioning

confidence: 99%

“…But those structures have some disadvantages, such as large weight, high friction and energy-wasting features. Tape-spring hyperelastic (TSH) hinges, which are folded elastically can self-deploy by releasing stored strain energy, which consist of a fewer component parts, can be manufactured conveniently [1,2]. Flexible hinges have several advantages for space applications, including a low mass-to-deployedstiffness ratio, cost, and self-latch [3].…”

Section: Introductionmentioning

confidence: 99%

Design and Experiment of Triangular Prism Mast with Tape-Spring Hyperelastic Hinges

Yang

Guo

Wang

et al. 2018

Chin. J. Mech. Eng.

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Because of the limited space of the launch rockets, deployable mechanisms are always used to solve the phenomenon. One dimensional deployable mast can deploy and support antenna, solar sail and space optical camera. Tape-spring hyperelastic hinges can be folded and extended into a rod like configuration. It utilizes the strain energy to realize self-deploying and drive the other structures. One kind of triangular prism mast with tape-spring hyperelastic hinges is proposed and developed. Stretching and compression stiffness theoretical model are established with considering the tape-spring hyperelastic hinges based on static theory. The finite element model of ten-module triangular prism mast is set up by ABAQUS with the tape-spring hyperelastic hinge and parameter study is performed to investigate the influence of thickness, section angle and radius. Two-module TPM is processed and tested the compression stiffness by the laser displacement sensor, deploying repeat accuracy by the high speed camera, modal shape and fundamental frequency at cantilever position by LMS multi-channel vibration test and analysis system, which are used to verify precision of the theoretical and finite element models of ten-module triangular prism mast with the tape-spring hyperelastic hinges. This research proposes an innovative one dimensional triangular prism with tape-spring hyperelastic hinge which has great application value to the space deployable mechanisms.

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“…If the spacecraft is close to Mercury the light pressure can be an order of magnitude higher. Then two parameters are decisive: the size of the sail must be as large as possible so that the pressure of photons would result in nonnegligible driving force; the overall mass must be as small as possible to efficiently convert the driving force into a nonnegligible acceleration [4]. Solar sail performance is significantly affected by four main factors: sail surface/mass ratio; optical properties of the sail film; mechanical properties of the sail film; and sail geometry.…”

Section: Introductionmentioning

confidence: 99%

Design and Characterization of a Small-Scale Solar Sail Prototype by Integrating NiTi SMA and Carbon Fibre Composite

Costanza

Leoncini

Quadrini

et al. 2017

Advances in Materials Science and Engineering

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Solar sails are propellantless systems where the propulsive force is given by the momentum exchange of reflecting photons. In this study, a self-deploying system based on NiTi shape memory wires and sheets has been designed and manufactured. A small-scale prototype of solar sail with carbon fibre loom has been developed. Different configurations have been tested to optimize material and structure design of the small-scale solar sail. In particular the attention has been focused on the surface/weight ratio and the deployment of the solar sail. By reducing weight and enlarging the surface, it is possible to obtain high values of characteristic acceleration that is one of the main parameters for a successful use of the solar sail as propulsion system. Thanks to the use of shape memory alloys for self-actuation of the system, complexity of the structure itself decreases. Moreover, sail deployment is simpler.

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Ultralight deployable booms for solar sails and other large gossamer structures in space

Cited by 150 publications

References 1 publication

Thermal analysis of thin-walled deployable composite boom in simulated space environment

Thermal analysis of thin-walled deployable composite boom in simulated space environment

Design and Experiment of Triangular Prism Mast with Tape-Spring Hyperelastic Hinges

Design and Characterization of a Small-Scale Solar Sail Prototype by Integrating NiTi SMA and Carbon Fibre Composite

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