Composite Boom Research Articles

Thermo-structural analysis of deployable composite booms with slotted hinges for space applications

The constraints on size and geometry of launch vehicle payload volume and the necessity of large antennas, solar cells, instruments for field of view, and isolation lead to the research and production of deployable structures. They accomplish compact packing volume on the launch and a large deployable length in space once the satellite is ejected into orbit. Booms are cantilever arms that are deployable which project out of the satellite or any spacecraft main body to perform various tasks. Static and dynamic analysis of deployable composite boom with integral slotted hinges is carried out in the present work. A deployable composite boom prototype is manufactured using glass epoxy composite and experiments are carried out. A similar structure is modeled and analyzed in the software also. The results for deflection, stress, strain, natural frequency, etc. for such a structure are presented initially. The effect of stacking sequence and number of layers in the composite boom structure is also studied. Finally, the thermal effect on the static and dynamic behavior of deployable composite boom prototypes is also discussed.

Analysis of Buckling Characteristics and Parameter Influence of Composite Thin-walled Lenticular Boom Structures

The stretchable composite thin-walled lenticular boom can be used in the unfolding process of a large spacecraft structure, and its buckling characteristic is one of the focuses of structural design. In this paper, firstly, the critical buckling load formula is derived based on Euler’s formula and laminated theory for the axial compression buckling problem of the lenticular boom, and verified by the finite element method. Secondly, the influence law of the lenticular boom section and layer parameters on the critical buckling load is quantitatively analyzed. The results show that the lenticular boom generally undergoes first-order buckling in the outer direction of the symmetrical bonding surface. The critical buckling load is most significantly affected by the radius of the convex arc, followed by the center ordinate of the convex arc, the thickness of the layer, and the angle of the layer. And these parameters are positively related to the critical buckling load. The radius of the concave arc and the length of the straight section have little effect on the critical buckling load. The research methods and conclusions of this paper can provide reference for the engineering design of the lenticular boom structure.

Efficient Storage and Deployment of Tubular Composite Boom Using Spring Root Hinges

This paper proposes a metallic spring root hinge to effectively stow and deploy a collapsible and rollable tubular carbon fiber reinforced polymer (CFRP) boom. The proposed hinge consists of two half-cylindrical parts with narrowed regions and a hole. One of the ends of the hinge is fixed to a hub with the circular cross section, and the other end that is connected to the boom is flattened with the boom to roll the boom around the hub with a small diameter. First, the hinge concept was designed, and a numerical analysis of the stowing of the hinge was conducted. Subsequently, the tests of compression, expansion, bending, stowage, and vibration of the hinge and the boom were conducted to show the effectiveness of the hinge, especially in the stowage radius and the bending stiffness. Finite element simulations of the compression test and vibration mode analysis were also conducted. Finally, deployment tests of the boom with and without the hinge were performed to compare the deployment behaviors. The tubular CFRP booms with the hinges are expected to be used for developing an efficient lightweight large membrane structure.

Blossoming analysis of composite deployable booms

Deployable coilable booms are extendible structures that have been used in a number of space and terrestrial applications. Fiber reinforced polymer (FRP) composite variants of these deployable booms have advantages over the metallic versions in the form of higher specific stiffness and greater design flexibility. A deployment failure mode called ‘blossoming’, in which the boom unwinds and extends within the deployment mechanism, can occur if an excessive load is applied to the boom tip. Blossoming can be mitigated by using compression rollers which radially constrain the coiled boom. An energy method is used to model the composite boom during deployment, and to predict the tip force a boom can withstand before blossoming occurs. The analytical results are compared with experimental results. The effects of the boom material properties and geometric parameters are investigated to provide more guidance in the design of deployable coilable boom systems.

필라멘트 와인딩 공법에 의한 30m급 굴절형 고소작업차용 유리섬유/에폭시 복합재 붐 개발에 관한 연구

Since electric energy is used in industry, mass production and various conveniences are provided. To provide convenience for the construction and operation of such electric energy transmission and distribution facilities, it is increasing that the demand for special purpose vehicles, that is, telescopic aerial work platform vehicles. When working active electric work using the telescopic aerial work platform vehicles, due to active electric work is inevitable, it is essential to ensure insulation performance for the safety of the operator. In this paper, we study the design and development of mechanical properties for filament winding process of glassfiber/epoxy composite, it is required to boom of telescopic aerial work platform vehicles. The glass fiber/epoxy composite filament winding process and its mechanical properties were evaluated to replace the existing ATOS80 boom. By filament winding process it was obtained the mechanical properties required for the design analysis of the glass fiber/epoxy composite boom. Using this, the insulated boom for the 30m class aerial work vehicle was designed and was manufactured by applying the filament winding process. The fabricated composite boom was evaluated by the static strength test to meet the required strength. The maximum displacement was 84mm and the crack occurred at the maximum load of 8981N. It satisfied the maximum lifting load of 4900N and 210mm the maximum displacement required for the boom.

Structural design and analysis of CFRP boom for concrete pump truck

This research presents structural design and analysis results of applying a composite boom structure on a Concrete Pump Truck (CPT). Carbon Fiber Reinforced Plastic (CFRP) is used to complete the structural design of the end boom to reduce the weight of the CPT. The weight of the newly designed end boom is reduced by 32% compared to the original steel component. Structural analysis is accomplished by applying static load combinations of self-weight of the boom and the weights of the pipes, the concrete and the drain hose. The results show that the tip deflection is reduced by 30% compared to the conventional end boom. Also, equivalent stress is considerably lower than the conventional design. Composite failure evaluation of the CFRP end boom is conducted by post-processing the stress results using Puck’s failure criteria. The evaluation results show that the design criteria are met on the static load of the pump truck. Specifically, it is expected that fiber failure and inter fiber failure of the boom do not occur under loading conditions according to the design evaluation results.

Characterization of deployable ultrathin composite boom for microsatellites excited by attitude maneuvers

Composite booms are often adopted onboard spacecraft to modify inertia properties and/or to move instrument as far as possible from the influence of the platform bus. In the frame of the current trend towards smaller spacecraft, also microsatellites are increasingly equipped with these deployable appendages. Due to limited volume and mass available on these platforms, the design of the boom is more challenging and a validation of the proposed system is crucial. The paper details, from the structural dynamics point of view, the numerical and experimental validation campaign for a 1-meter boom purposely designed and built in composite material for a microsatellite platform. The experimental validation was carried out by using a free-floating platform and while simulating the loads experienced during an in-orbit attitude re-orientation maneuver. The complete architecture of the platform, including solar panels’ appendages with related flexibility issues as well as the thrusters for actuation, provides for the credibility and the interest of the validation outcome.

ANSYS와 ADAMS을 이용한 30m급 굴절형 절연붐의 동적 내구성 분석

In this paper, the boom of a 30m class refracted insulation with outrigger on aerial elevating work platform is modeled as 3D CAD program of CATIA. The static and dynamic analyses are performed by using ANSYS and ADAMS programs, respectively. The refracted insulation boom uses acetal and the composite boom for insulation. And the composite insulation boom is modeled by using ACP (Ansys Composite Prepost) of ANSYS program. In order to analyze the durability of refracted insulation boom, the static analysis is performed and each analyzed part is stored as =MNF-type flexible body model. The dynamic analysis is performed with ADAMS by using the flexible model. As the result, these analyzes clarify the structural stability and dynamic durability (hot spot) of the refracted insulation boom.

Folding analysis for thin-walled deployable composite boom

Thin-walled deployable composite structures with high strain ability are of considerable interest and increasingly used in aerospace field due to their superior mechanical behaviour and folding function. This paper seeks to investigate large folding deformation behaviour of a thin-walled deployable composite boom (DCB) made of high strain carbon-fibre-reinforced-plastics fabricated by vacuum-bag and co-bonding technologies. Large deformation function tests are conducted to determine tensile, compression and folding behaviours of the DCB. Geometrically nonlinear, explicit and standard, finite element models and an analytical model are implemented to characterize the tensile and compression behaviours of the DCB, and the deviations of predictions from experiments are in an acceptable scatter. Furthermore, a geometrically nonlinear and explicit finite element model is also generated for folding analysis of the DCB, and a good correlation between predictions and experiments has been achieved.

Development and testing of a pyro-driven launcher for harpoon-based comet sample acquisition

The CORSAIR (COmet Rendezvous, Sample Acquisition, Investigation, and Return) mission was a proposal for the NASA New Frontiers program. It belongs to the Comet Surface Sample Return mission theme which focuses on acquiring and returning to Earth a macroscopic sample from the surface of a comet nucleus. CORSAIR uses a harpoon-based Sample Acquisition System (SAS) with the spacecraft hovering several meters above the comet surface. This stand-off strategy overcomes disadvantages of other systems such as drills. Since comets are low gravity objects, those techniques would require anchoring before sampling, which is not necessary here. Moreover, the harpoon-based system allows for acquiring several samples from different locations on the comet maximizing the scientific output of the mission.Each SAS assembly consists of a pyro-driven launcher, a Sample Acquisition and Retrieval Projectile (SARP) and a retraction system using a deployable composite boom structure. In order to collect enough cometary material, the launcher has to provide the required kinetic energy to the SARP. Due to high energy densities, pyrotechnically actuated devices ultimately reduce the overall system mass and dimensions. First, the scientific and technological background of the CORSAIR mission is explained. Then, an overview of the development, design and testing of the launcher is given. Finally, the launcher theory is introduced explaining the entire reaction chain: initiation → gas dynamics → SARP motion.

A Study on the Composite Insulation Boom Development of the Aerial Work Platform for Electric Work

A Study on the Composite Insulation Boom Development of the Aerial Work Platform for Electric Work

Experiments and Simulations of the Deployment of a Bistable Composite Boom

The rapidly growing use of small satellites for space missions requires deployable systems to be highly storable yet large and with adequate mechanical properties when deployed. This paper focuses on the modeling and simulation of a meter-class passively deployable boom, based on the self-contained linear meter-class deployable boom, exploiting the bistable nature of composite shells. Experimental tests were performed on a boom prototype suspended in a gravity offloading system. The strain energy level, deployment time, and spacecraft displacements calculated from the finite element method agree well with analytical analyses, confirming the theoretical accuracy of the finite element method. Because friction and strain energy relaxation were not included in the model, the finite element simulations predicted deployment times up to five times shorter than those of the gravity offloaded boom experiments. The quick deployment and violent end-of-deployment shock created boom deployment dynamics that were not seen in the experiments. The observed differences between the finite element model and the tests were mainly due to inaccurate material and friction models.

Robotic magnetic mapping with the Kapvik planetary micro-rover

AbstractGeomagnetic data gathering by micro-rovers is gaining momentum both for future planetary exploration missions and for terrestrial applications in extreme environments. This paper presents research into the integration of a planetary micro-rover with a potassium total-field magnetometer. The 40 kg Kapvik micro-rover is an ideal platform due to an aluminium construction and a rocker-bogie mobility system, which provides good manoeuvrability and terrainability. A light-weight GSMP 35U (uninhabited aerial vehicle) magnetometer, comprised of a 0.65 kg sensor and 0.63 kg electronics module, was mounted to the chassis via a custom 1.21 m composite boom. The boom dimensions were optimized to be an effective compromise between noise mitigation and mechanical practicality. An analysis using the fourth difference method was performed estimating the magnetic noise envelope at ±0.03 nT at 10 Hz sampling frequency from the integrated systems during robotic operations. A robotic magnetic survey captured the total magnetic intensity along three parallel 40 m long lines and a perpendicular 15 m long tie line over the course of 3.75 h. The total magnetic intensity data were corrected for diurnal variations, levelled by linear interpolation of tie-line intersection points, corrected for a regional gradient, and then interpolated using Delaunay triangulation to lead a residual magnetic intensity map. This map exhibited an anomalous linear feature corresponding to a magnetic dipole 650 nT in amplitude. This feature coincides with a storm sewer buried approximately 2 m in the subsurface. This work provides benchmark methodologies and data to guide future integration of magnetometers on board planetary micro-rovers.

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

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 10−5Pa), heat sink (−180°C) 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.

Softenable composite boom for reconfigurable and self-deployable structures

ABSTRACTThis article investigates (experimentally and numerically) the time and temperature-dependent folding and unfolding behavior, including the structural nonlinearity, of thin-walled softenable composite structures. The composites are fabricated with woven fabric fibers and a heat softenable material of the shape memory polymer (SMP) resin. A numerical model is developed. The model is based on the elastic properties of the woven fabric fibers, their fabric geometry, and the thermo-viscoelastic properties of the SMP resin. A thin-walled cylindrical boom, which can be flexibly folded into an arbitrary configuration and be self-deployed, is fabricated using the heat softenable composite. The viscoelasticity and the shape memory behaviors are investigated during the folding and unfolding of the boom at elevated temperatures.

Design and Analysis of Oscillation-Decreasing Mechanism on the Deployable Composite Boom

Self-deployable booms are designed to fold elastically and to spontaneously deploy using structurally stored energy. Dealing with redundant vibration and oscillation produced after complete deployment is the main problem about using these structures. Also, the booms stiffness decreases after deployment so as it may returns due to a moment that applied on it. Therefore, it is necessary to design a mechanism by which the boom joint’s redundant oscillations are decreased and the boom’s stiffness, as well as stability, is increased. In this study, a composite deployable boom is first simulated via multibody dynamic analysis software, and then a mechanism is designed for decreasing the boom’s redundant oscillations and vibrations, as well as increasing the boom’s stability and stiffness. The results show that, by use of the designed mechanism for decreasing oscillation of the joints of the boom, the extra vibration of the deployed boom has been damped in much less time. Also, using this mechanism balances and decreases the applied influence and vibration on the satellite due to the boom’s deployment, and consequently facilitates the quick stability of the satellite.

Nonlinear buckling and folding analysis of a storable tubular ultrathin boom for nanosatellites

In this work we investigated the stability behavior and the folding capability of an ultrathin tubular composite boom with C-cross section to be used in nanosatellites applications. A nonlinear buckling analysis was performed using the Riks method, adopting a perturbed finite element model to study the influence of the unavoidable geometrical variations of the boom thickness, arising from the composite manufacturing processes, on the stability behavior of the tubular structure. The effect of several levels of geometrical imperfection on the buckling behavior was analyzed. The minimum coil radius that can be used for a safe storage the boom was determined by quasi-static explicit analysis. The boom folding process was considered as formed by two sequential steps, the flattening and the coiling. The stress fields associated with both steps were investigated.

Shape memory polymer composites with woven fabric reinforcement for self-deployable booms

To characterize the nonlinear relationship between load and displacement and its dependency on temperature and time variations, the rate form of thermomechanical constitutive equations for shape memory polymers is newly derived. Experimental tests of the shape memory polymers are analyzed to acquire the parameters needed for the model. In order to generate a fast recovery rate and a higher recovery ratio, an asymmetric shape memory polymer composite reinforced with woven fabrics is developed and fabricated. Moreover, the efficiency of the asymmetric shape memory polymer composite is evaluated through shape recovery tests after bending. A numerical model of the shape memory polymer composite is newly established. In addition, the structural nonlinear behavior of the asymmetric shape memory polymer composite is analyzed with time and temperature dependence. A “[Formula: see text]”-shaped cross-sectional shape memory polymer composite boom is fabricated, and its deployment procedures are demonstrated for the application of self-deployable booms in gossamer space structures.

Coiling dynamic analysis of thin-walled composite deployable boom

Thin-walled composite deployable structures are an attractive solution for many aerospace missions, especially when large configurations are required. This paper investigates the feasibility of coiling an ultra-thin composite boom into a small deployment system. Detailed simulation of the coiling process of a C-section boom made from a two-ply laminate of carbon fiber reinforced plastic was performed using non-linear explicit dynamic analysis. A complete description of the analysis parameters that control the numerical stability of the simulation, and of the boundary conditions and loads adopted to perform the folding process are reported within this paper. The simulation is divided into two consecutive stages: the flattening of the boom, and the coiling inside the deployment device. The accuracy of the results is verified using energy balance assessments, and the structural strength of the boom is evaluated via three specific failure criteria. A parametric analysis of geometrical parameters was carried out in order to find out the slot configuration allowing the boom to fold without reaching its failure.

Completely stripped solar sail concept using bi-stable reeled composite booms

The Surrey Space Centre is currently working on CubeSail, a 5×5 m 2 nano-solar sail spacecraft to be fitted inside a 3U Cubesat platform. The CubeSail mission has a two-fold aim: first, to demonstrate the concept of solar sailing using a 3-axis stabilized sail and second, to demonstrate the potential use of its large membrane as a drag augmentation device for de-orbiting satellites and launch vehicles' upper stages in low Earth orbit (LEO). The novel solar sail concept presented here is a result of the highly restrictive area-to-mass ratio and volume constraints imposed by the mission requirements. Therefore, this concept can be readily scaled up to produce future very high performance sailcrafts. Research on ultra-lightweight deployable structures leads to the invention of a new bi-stable composite boom that entails a light and simple deployment subsystem. This simplicity is the key feature that enables the sail to be attached along the length of the booms, thus reducing the structural mass requirement of these support structures. In the completely stripped sail concept the previously considered square or quadrant membrane is split into a set of parallel strips, in order to achieve a uniaxial tension state in the film. Also, a test-bed created for the successful deployment under gravity conditions of the 5 m 2 prototype sail is presented.