Shape Recovery of Polymeric Matrix Composites by Irradiation

2016 ◽  
Vol 879 ◽  
pp. 1645-1650 ◽  
Author(s):  
Loredana Santo ◽  
Denise Bellisario ◽  
Fabrizio Quadrini
Keyword(s):  
Shape Memory ◽  
Fiber Composite ◽  
Shape Memory Polymer ◽  
Recovery Phase ◽  
Initial Configuration ◽  
Conventional Heating ◽  
Carbon Fiber Composite ◽  
Space Applications ◽  
Aerospace Applications ◽  
Air Gun

Shape memory composite (SMC) structures are of great interest for the aerospace applications. In previous works, the authors have studied SMC lab-scale deploying prototypes manufactured by using two carbon fiber composite layers with a shape memory polymer interlayer. The prototypes were produced in an initial configuration and subsequently it was changed in the memorizing step. The initial configuration was then recovered by heating. Memorization and recovery phases were performed by means of conventional heating (by hot air gun or heater plate). In this work, for the first time the authors evaluate the SMC heating by means of radiating lamps. A square plate was purposely produced and recovered after different memory steps. Time, temperature and recovery are measured during and after the tests. The radiating lamp power and type, and the distance of the SMC from the lamp are fundamental parameters for the heating phase. As result of the irradiation tests, the initial configuration can be successfully recovered without failures. This study is especially aimed to future space applications in which the deployment (recovery) phase will be initiated only by exposure to solar radiation.

Shape Memory Composite Hands for Space Applications

2015 ◽  
Author(s):  
Fabrizio Quadrini ◽  
Giovanni Matteo Tedde ◽  
Loredana Santo
Keyword(s):  
Shape Memory ◽  
Composite Structures ◽  
Polymer Matrix Composites ◽  
Fiber Composite ◽  
Shape Memory Polymer ◽  
Small Scale ◽  
Carbon Fiber Composite ◽  
Space Applications ◽  
First Case ◽  
Shape Memory Composite

Shape memory composites combine structural properties of continuous-fiber polymer-matrix composites with functional behavior of shape memory polymers. In this study, the production of shape memory composite structures for aerospace applications is described. Small-scale grabbing systems were prototyped as they could be used for space cleaning operations. Composite hands were manufactured by using two carbon fiber composite layers with a shape memory polymer interlayer. They were produced in the closed-hand configuration and subsequently opened in the memorizing step. Due to heating, composites tended to recover the initial closed configuration, allowing to grab small objects. Two different shapes (cylindrical and cubic) were considered for composite hands. In the first case, the shape memory behavior was given to the entire structure whereas, in the second case, shape memory properties were provided only to folding zones. As a result, a good shape recovery was observed in both cases but part weight was already not negligible also in these small-scale systems.

An Analytical Shape Memory Polymer Composite Beam Model for Space Applications

2016 ◽  
Vol 16 (02) ◽  
pp. 1450093 ◽  
Author(s):  
D. Bergman ◽  
B. Yang
Keyword(s):  
Shape Memory ◽  
Polymer Composite ◽  
Geometric Model ◽  
Shape Memory Polymer ◽  
Constitutive Law ◽  
Finite Difference Approximation ◽  
Dynamic Equations ◽  
Difference Approximation ◽  
Beam Model ◽  
Space Applications

Shape memory polymer composite (SMPC) structures, due to their ability to be formed into a small compact volume and then transform back to their original shape, are considered as a solution in the design of light-weight large deployable space structures. There is a wide array of constitutive and qualitative work being done on SMPC’s but little or no development of dynamic equations. This paper documents a macroscopic model for the shape fixation and shape recovery processes of a SMPC cantilever beam. In particular the focus is on the shape fixation process, whereby a quasi-static equilibrium model can be used instead of a full equation of motion. Numerical results are obtained in this regard by use of finite difference approximation with Newton’s method. This formulation combines a nonlinear geometric model with a temperature dependent constitutive law. Additionally, the dynamic equations of the SMPC cantilever are derived. Future work will include a dynamic numerical model, and a finite element model of the SMPC structure.

scholarly journals Shape Memory Polymer Composite Actuator: Modeling Approach for Preliminary Design and Validation

Actuators ◽  
2019 ◽  
Vol 8 (3) ◽  
pp. 51 ◽  
Author(s):  
Salvatore Ameduri ◽  
Monica Ciminello ◽  
Antonio Concilio ◽  
Fabrizio Quadrini ◽  
Loredana Santo
Keyword(s):  
Shape Memory ◽  
Shape Memory Polymer ◽  
Critical Role ◽  
Solar Sails ◽  
Modeling Approach ◽  
Aerospace Applications ◽  
Actuation System ◽  
Smart Actuator ◽  
Definition Of ◽  
Specific Modeling

The work at hand focuses on the modeling, prototyping, and experimental functionality test of a smart actuator based on shape memory polymer technology. Particular attention is paid to the specific modeling approach, here conceived as an effective predictive scheme, quick and, at the same time, able to face those nonlinearity aspects, strictly related to the large displacements shape memory polymers usually undergo. Shape memory polymer composites (SMPCs) may play a critical role for many applications, ranging from self-repairing systems to deployable structures (e.g., solar sails, antennas) and functional subcomponents (e.g., pliers, transporters of small objects). For all these applications, it is very important to have an effective tool that may drive the designers during the preliminary definition of the main parameters of the actuation system. For the present work, a SMPC plate sample has been conceived and realized in view of aerospace applications. An external fibre optic sensor has been then fixed with special adhesive. The temperatures needed for the activation of the Shape Memory Polymer (SMP) and strain storing have been provided by a thermo-gun and complete load–unload cycles, including strain storing, have been performed. Experimental displacements and strains have been used to validate a dedicated predictive theoretical approach, suited for laminates integrated with SMP layers.

Deployment performance of shape memory polymer composite hinges at low temperature

2019 ◽  
Vol 30 (17) ◽  
pp. 2625-2638 ◽  
Author(s):  
Van Luong Le ◽  
Vinh Tung Le ◽  
Nam Seo Goo
Keyword(s):  
Low Temperature ◽  
Shape Memory ◽  
Polymer Composite ◽  
Room Temperature ◽  
Shape Memory Polymer ◽  
Heating Element ◽  
Heating Process ◽  
Space Applications ◽  
Design Modification ◽  
The Impact

Shape memory polymer composite hinges, adapted for possible space applications, were successfully designed and fabricated, and performance tests at room temperature confirmed their full recoverability in our previous studies. Since shape memory polymer composite hinges are intended for space applications, they should be able to operate at low temperature. Even though the deployment of the hinge at room temperature triggered by the stimulation of a heating element has been quite promising, a suitable design for a shape memory polymer composite hinge with a heating element is more important at low temperatures because shape memory polymer composite hinges lose much heat to the environment. The recoverability of shape memory polymer composite hinges and the impact of the heating element design on the deployment time at low temperature are brought to light in this article. A shape memory polymer composite hinge with an attached heating element was fabricated as in our previous studies. The necessary power and supply power for deployment of the shape memory polymer composite hinge at a low temperature of –10°C were calculated, and a finite element analysis for the heating process was performed with the supply power. A folding and deployment test of the shape memory polymer composite hinge at –10°C was performed to show its shape recoverability. However, the shape memory polymer composite hinge did not deploy to its original shape. To determine the reason, measurements of temperature distribution were done using an infrared camera and thermocouples. The results revealed that the low temperature along the two side edges of the shape memory polymer composite tape prevented full deployment of the shape memory polymer composite hinge, which also revealed the need for design modification. The folding and deployment test of our modified shape memory polymer composite hinge demonstrated a nearly full deployment.

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