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

2017 ◽  
Vol 2017 ◽  
pp. 1-6 ◽  
Author(s):  
Girolamo Costanza ◽  
Gabriele Leoncini ◽  
Fabrizio Quadrini ◽  
Maria Elisa Tata
Keyword(s):  
Carbon Fibre ◽  
Shape Memory ◽  
Fibre Composite ◽  
Weight Ratio ◽  
Solar Sail ◽  
Structure Design ◽  
Small Scale ◽  
Momentum Exchange ◽  
Carbon Fibre Composite ◽  
Solar Sails

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.

scholarly journals Shape Memory Activated Self-Deployable Solar Sails: Small-Scale Prototypes Manufacturing and Planarity Analysis by 3D Laser Scanner

Actuators ◽  
2019 ◽  
Vol 8 (2) ◽  
pp. 38 ◽  
Author(s):  
Alberto Boschetto ◽  
Luana Bottini ◽  
Girolamo Costanza ◽  
Maria Elisa Tata
Keyword(s):  
Shape Memory ◽  
Laser Scanner ◽  
Solar Sail ◽  
Small Scale ◽  
Propulsive Force ◽  
Momentum Exchange ◽  
Solar Sails ◽  
Level Curves ◽  
Wolfram Mathematica ◽  
Critical Zones

Solar sails are propellantless systems where the propulsive force is given by the momentum exchange of reflecting photons. Thanks to the use of shape memory alloys for the self-actuation of the system, complexity of the structure itself has decreased and so has the weight of the whole structure. Four self-deploying systems based on the NiTi shape memory wires have been designed and manufactured in different configurations (wires disposal and folding number). The deployed solar sails surfaces have been acquired by a Nextengine 3D Laser Scanner based on the Multistripe Triangulation. 3D maps have been pre-processed through Geomagic Studio and then elaborated in the Wolfram Mathematica environment. The planarity degree has been evaluated as level curves from the regression plane highlighting marked differences between the four configurations and locating the vertices as the most critical zones. These results are useful in the optimization of the best folding solution both in the weight/surface reduction and in the planarity degree of the solar sail.

Incremental Damage Development in a 3D Woven Carbon Fibre Composite

2007 ◽  
Vol 15 (7) ◽  
pp. 521-533
Author(s):  
S. King ◽  
G. Stewart ◽  
A.T. McIlhagger ◽  
J.P. Quinn
Keyword(s):  
Carbon Fibre ◽  
Fibre Composite ◽  
Weight Ratio ◽  
Matrix Cracking ◽  
Limiting Factors ◽  
Damage Development ◽  
Carbon Fibre Composite ◽  
Damage Initiation ◽  
Fibre Composites ◽  
Carbon Fibre Composites

Interest in 3D woven carbon fibre composites has increased within industries such as aerospace, automotive and marine, due to their high strength to weight ratio, their increased tailorability and their capacity to be manufactured into near net shape preforms, thereby reducing parts count, assembly time, labour intensity and costs. It is vital that critical areas of concern such as damage (and in particular damage initiation and development) are studied and understood, thereby reducing the limiting factors to their acceptance. The damage initiation and subsequent intervals of development for ILSS (Interlaminar Shear Strength) were determined experimentally. Particular focus is paid to the significance of binder edge and binder middle testing and the influence of through-the-thickness (T-T-T) reinforcement in relation to damage types and development. Control samples for binder edge and binder middle loading locations were tested to failure as a means of determining an average point of failure, allowing the generation of testing intervals. The performance and architecture of samples from each incremental interval were characterised using a combination of graphical analysis and optical microscopy with the aid of dye-penetrant to highlight fibre damage and matrix cracking. Samples displayed specific damage initiation points, thus allowing the generation of a damage guide relating to applied force. In addition, the results imply that a relationship exists between the location of applied load and subsequent damage, thus showing the significant influence played by the T-T-T binder loading location on damage development within 3D woven carbon fibre composites. Some of the preliminary data shown in this paper was presented at IMC23 at the University of Ulster, UK in August 2006 and at Texcomp 8 in Nottingham, UK October 2006.

scholarly journals A Novel Self-Deployable Solar Sail System Activated by Shape Memory Alloys

Aerospace ◽  
2019 ◽  
Vol 6 (7) ◽  
pp. 78 ◽  
Author(s):  
Gianluigi Bovesecchi ◽  
Sandra Corasaniti ◽  
Girolamo Costanza ◽  
Maria Elisa Tata
Keyword(s):  
Shape Memory Alloys ◽  
Shape Memory ◽  
Environmental Conditions ◽  
Solar Sail ◽  
Operating Conditions ◽  
Small Scale ◽  
Space Vehicles ◽  
Solar Sails ◽  
Suitable Material ◽  
Transfer Mechanisms

This work deals with the feasibility and reliability about the use of shape memory alloys (SMAs) as mechanical actuators for solar sail self-deployment instead of heavy and bulky mechanical booms. Solar sails exploit radiation pressure a as propulsion system for the exploration of the solar system. Sunlight is used to propel space vehicles by reflecting solar photons from a large and light-weight material, so that no propellant is required for primary propulsion. In this work, different small-scale solar sail prototypes (SSP) were studied, manufactured, and tested for bending and in three different environmental conditions to simulate as much as possible the real operating conditions where the solar sails work. Kapton is the most suitable material for sail production and, in the space missions till now, activated booms as deployment systems have always been used. In the present work for the activation of the SMA elements some visible lamps have been employed to simulate the solar radiation and time-temperature diagrams have been acquired for different sail geometries and environmental conditions. Heat transfer mechanisms have been discussed and the minimum distance from the sun allowing the full self-deployment of the sail have also been calculated.

Static Behaviours of Carbon Fibre Composite Strip with Bifurcated Type Shape Memory Alloy Pins

2007 ◽  
Vol 334-335 ◽  
pp. 1153-1156
Author(s):  
Kuen Cheong Chan ◽  
Li Min Zhou
Keyword(s):  
Shape Memory Alloy ◽  
Carbon Fibre ◽  
Shape Memory ◽  
Numerical Study ◽  
Fibre Composite ◽  
Axial Stress ◽  
Three Dimensional ◽  
Woven Fabric ◽  
Carbon Fibre Composite ◽  
Fabric Composite

A numerical study of the static behaviours of composite strip with bifurcated type shape memory alloy pins has been conducted. The case of bifurcated type shape memory alloy pins inserted inside the composite strip around the hole to reinforce the laminate, which was subjected to the axial stress was simulated. The models for stress analysis were established by using ANSYS finite element programme. Two types of shape memory alloy pins were proposed to insert along the through thickness direction of the carbon fibre woven fabric composite strip to induce the clamping force. The pre-tensioned load was applied to the shape memory alloy pins in order to reduce occurrence of delamination in the laminate. Three-dimensional elements and contact elements were used to simulate the contact between the composite laminate and shape memory alloy pin to investigate the stress distribution around the hole in the composite strip. The effect of pre-strain of shape memory alloy on the stresses inside composite was studied. The results show that the stress characteristics of the button-shaped and bifurcated shape memory alloy pin models are similar; however, the stresses for the button-shaped pin model are lower. The tensile and compressive stresses, both in button-shaped and bifurcated pin models, are strongly dependent on the percentage of pre-strain of the shape memory alloy. It is therefore concluded that the shape memory alloy pin method was significantly reduced the stress concentration of the composite strip laminate.

Composite Failure Modes at High Cyclic Fatigue Life Evaluation

2020 ◽  
Vol 17 (3) ◽  
pp. 8096-8103
Author(s):  
Haider F. Al-Qrimli ◽  
Mustafa J. Al-Dulaimi ◽  
Kayser A. Ameen
Keyword(s):  
Tensile Strength ◽  
Fatigue Life ◽  
Ultimate Tensile Strength ◽  
Carbon Fibre ◽  
Failure Modes ◽  
Fibre Composite ◽  
Weight Ratio ◽  
Carbon Fibre Composite ◽  
Composite Failure ◽  
Power Curves

Fibre reinforced polymer composite have been utilised in applications that require high strength-to-weight ratio and durability like automotive and spacecraft components. The literatures has indicated that there is a gap of knowledge in fatigue failure mechanism, and reliable prediction of fatigue life for glass and carbon fibre laminates. This study is to address experimentally the stress level dominated the composite failure mode and how to avoid stress concentration in fatigue design. In addition, it contributes to the scientific knowledge and to further increase the understanding the fatigue behaviour of composite materials structures. To accomplish this investigation goals, three types of materials were fabricated and tested; glass/epoxy, carbon/epoxy, and chopped glass/epoxy. Traditional hand layup technique for composite processing was used to fabricate the composite specimens. It involves manually positioning the reinforcement woven roving in an open mould and pouring, brushing, the resin onto the composites. This study details the experimental results of the ultimate tensile strength and high cycle fatigue, with a stress ratio of 0.1, using ASTM. Results showed that carbon fibre composite had the highest ultimate tensile strength. The power curves conducted from this paper were used to estimate the number of cycles which the material can endure.

Carbon fibre composite development for in-ground UAV’s with NACA0012 aerofoil wing

2021 ◽  
Author(s):  
Ajanas Saludheen ◽  
Firaz Muhammed Zakariya ◽  
M Ankith ◽  
Nirmal Nandakumar ◽  
Jais George ◽  
...  
Keyword(s):  
Carbon Fibre ◽  
Fibre Composite ◽  
Carbon Fibre Composite
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