Professor Guglielmo S Aglietti

Research Interests

Currently I carry out research in the area of microvibrations on board spacecraft, multifunctional spacecraft structures, correlation between FEM and testing, response of electronic packaging subjected to harsh vibration environment. My top priority will be to strengthen the collaboration between the Surrey Space Centre and SSTL to create new synergies and ensure a seamless relation between the research carried out in the Centre and the practical applications pursued by SSTL.

Further information on my activities is available on the Spacecraft Structures, Materials and Mechanisms page.

Affiliations

I am a Chartered Engineer and a Fellow of the Royal Aeronautical Society. I have active partnerships with industry and I have collaborated with all the most important UK companies operating in the space sector.

Contact Me

E-mail:
Phone: 01483 68 3417

Find me on campus
Room: BA U

Publications

Journal articles

  • Remedia M, Aglietti GS, Richardson G. 'Modelling the effect of electrical harness on microvibration response of structures'. Acta Astronautica, 109, pp. 88-102.

    Abstract

    © 2015 IAA. Published by Elsevier Ltd. All rights reserved.The term "microvibrations" generally refers to accelerations in the region of micro-g, occurring over a wide frequency range, up to say 500-1000 Hz. The main issues related to microvibrations are their control and minimisation, which requires their modelling and analysis. A particular challenge is posed in the mid-frequency range, where many of the micro-vibration sources on board a spacecraft tend to act. In this case, in addition to the typical issues related to predicting responses in the mid-frequency, the low amplitude of the inputs can produce further non-linear behaviour which can manifest as uncertainties. A typical example is the behaviour of cables secured onto panels; when very low forces are applied, the presence of harness can influence the characteristics of the panel in terms of stiffness and damping values. In these circumstances, the cables themselves couple with the panel, hence become paths for vibration transmission. The common practise is to model such cables as Non-Structural Mass; however, this paper illustrates that this method does not yield accurate results. In order to demonstrate this, an experimental campaign was conducted investigating a honeycomb panel, which was tested bare and with different configurations of harness secured to it. The results of this experimental campaign showed significantly different behaviour of the structure depending on the amplitude of the loads and the frequency. In particular, it was found that the effects the addition of the cables had on the panel were different depending on the frequency range considered. Based on this observation, a general methodology to deal with the whole frequency range is presented here and the basis to extend it to the case of more complex structures is also proposed.

  • Addari D, Aglietti GS, Remedia M. (2017) 'Experimental and numerical investigation of coupled microvibration dynamics for satellite reaction wheels'. Elsevier Journal of Sound and Vibration, 386, pp. 225-241.
  • Mercer JF, Aglietti GS, Kiley AM. (2016) 'Model Reduction and Sensor Placement Methods for Finite Element Model Correlation'. AIAA Journal: devoted to aerospace research and development, 54 (12), pp. 3941-3955.

    Abstract

    The issue of model reduction is one that must often be overcome in order to perform the necessary checks as part of the spacecraft Finite Element Model (FEM) validation process. This work compares different reduction methods; specifically the popular and long-standing Guyan method, and the potentially more accurate System Equivalent Reduction Expansion Process (SEREP). The influence of sensor set location on the quality of the reduced model has also been considered, and the commonly applied methods to maximize kinetic energy and effective independence have been applied. These investigations have taken the form of studies involving two large, unique, scientific spacecraft. The computational results are compared with experimental results that are also detailed in the paper. The findings highlight the potential issues with the accuracy of a Guyan reduced model in replicating the full system dynamics, even with a reasonably large sensor set. It is shown that this can be improved slightly in some circumstances through implementation of sensor set placement optimization techniques. The SEREP method is shown to have the benefit of being more accurate at replicating the full system behavior than the more traditional Guyan method, while also producing higher diagonal values in cross-orthogonality comparisons between FEM and test.

  • Stabile A, Aglietti GS, Richardson G, Smet G. (2016) 'Design and verification of a negative resistance electromagnetic shunt damper for spacecraft micro-vibration'. Elsevier Journal of Sound and Vibration, 386, pp. 38-49.

    Abstract

    Active control techniques are often required to mitigate the micro-vibration environment existing on board spacecraft. However, reliability issues and high power consumption are major drawbacks of active isolation systems that have limited their use for space applications. In the present study, an electromagnetic shunt damper (EMSD) connected to a negative-resistance circuit is designed, modelled and analysed. The negative resistance produces an overall reduction of the circuit resistance that results in an increase of the induced current in the closed circuit and thus the damping performance. This damper can be classified as a semi-active damper since the shunt does not require any control algorithm to operate. Additionally, the proposed EMSD is characterised by low required power, simplified electronics and small device mass, allowing it to be comfortably integrated on a satellite. This work demonstrates, both analytically and experimentally, that this technology is capable of effectively isolating typical satellite micro-vibration sources over the whole temperature range of interest

  • Forshaw JL, Aglietti GS, Navarathinam N, Kadhem H, Salmon T, Pisseloup A, Joffre E, Chabot T, Retat I, Axthelm R, Barraclough S, Ratcliffe A, Bernal C, Chaumette F, Pollini A, Steyn WH. (2016) 'RemoveDEBRIS: An in-orbit active debris removal demonstration mission'. PERGAMON-ELSEVIER SCIENCE LTD ACTA ASTRONAUTICA, 127, pp. 448-463.
  • Addari D, Aglietti GS, Remedia M. (2016) 'Dynamic Mass of a Reaction Wheel Including Gyroscopic Effects: an Experimental Approach'. AIAA Journal,
  • Sairajan KK, Aglietti GS, Mani KM. (2015) 'A review of multifunctional structure technology for aerospace applications'. Elsevier Acta Astronautica, 120, pp. 30-42.

    Abstract

    The emerging field of multifunctional structure (MFS) technologies enables the design of systems with reduced mass and volume, thereby improving their overall efficiency. It requires developments in different engineering disciplines and their integration into a single system without degrading their individual performances. MFS is particularly suitable for aerospace applications where mass and volume are critical to the cost of the mission. This article reviews the current state of the art of multifunctional structure technologies relevant to aerospace applications.

  • Wu C, Viquerat AD, Aglietti G. (2015) 'Improving the Natural Frequency of Bistable Carbon Fibre Reinforced Plastic Tubes for Space Applications'. International Association for Shell and Spatial Structures Journal of the International Association for Shell and Spatial Structures, 56 (4), pp. 259-267.

    Abstract

    This paper describes the scalability analysis of bistable Carbon Fibre Reinforced Plastic (CFRP) tubes for space applications, with the aim of attaining a better understanding of the scaling laws of Bistable Reeled Composite (BRC) tubes. BRCs with substantially higher natural frequency are designed. The application for this work is a deployable solar array, which uses two BRC tubes to support a membrane containing flexible photovoltaic cells. Novel types of bistable tubes with stepped thickness changes, tapered diameter and reduced included angle are proposed to improve the natural frequency. Finite Element (FE) modelling and experimental verification have been used to study the vibration characteristics of the proposed BRC tubes. An FE model is combined with an optimization loop to improve the natural frequency with respect to the fibre angles within the laminate of the bistable tubes. The results demonstrate that the introduction of step changes in laminate thickness at certain locations, and careful selection of fibre angles can significantly improve the natural frequency.

  • Remedia M, Aglietti GS, Richardson G. (2015) 'A stochastic methodology for predictions of the environment created by multiple microvibration sources'. Journal of Sound and Vibration, 344, pp. 138-157.

    Abstract

    © 2015 Elsevier Ltd. All rights reserved. It is well documented that at frequencies beyond the first few modes of a system, the Finite Element Method is unsuitable to obtain efficient predictions. In this article, it is proposed to merge the efficiency of the Craig-Bampton reduction technique with the simplicity and reliability of Monte Carlo Simulations to produce an overall analysis methodology to evaluate the dynamic response of large structural assemblies in the mid-frequency range. The method (Craig-Bampton Stochastic Method) will be described in this article with a benchmark example shown and implemented in the theory of the dynamic coupling extended to the case when multiple sources of microvibrations act simultaneously on the same structure. The methodology will then be applied to a real practical application involving the modern satellite SSTL 300 S1.

  • Remedia M, Aglietti GS, Richardson G, Sweeting M. (2015) 'Integrated semiempirical methodology for microvibration prediction'. American Institute of Aeronautics and Astronautics AIAA Journal, 53 (5), pp. 1236-1250.
  • Fernandez JM, Visagie L, Schenk M, Stohlman OR, Aglietti GS, Lappas VJ, Erb S. (2014) 'Design and development of a gossamer sail system for deorbiting in low earth orbit'. Acta Astronautica, 103, pp. 204-225.
  • Sairajan KK, Aglietti GS, walker JI. (2014) 'Correlation of finite element models of multi-physics systems'. Rlsevier Journal of Sound and Vibration, 333 (17), pp. 4051-4070.

    Abstract

    The modal assurance criterion (MAC) and normalized cross-orthogonality (NCO) check are widely used to assess the correlation between the experimentally determined modes and the finite element model (FEM) predictions of mechanical systems. Here, their effectiveness in the correlation of FEM of two types of multi-physics systems, namely, viscoelastic damped systems and a shunted piezoelectric system are investigated using the dynamic characteristics obtained from a nominal FEM, that are considered as the ‘true’ or experimental characteristics and those obtained from the inaccurate FEMs. The usefulness of the MAC and NCO check in the prediction of the overall loss factor of the viscoelastic damped system, which is an important design tool for such systems, is assessed and it is observed that these correlation methods fail to properly predict the damping characteristics, along with the responses under base excitation. Hence, base force assurance criterion (BFAC) is applied by comparing the ‘true’ dynamic force at the base and inaccurate FEM predicted force such that the criterion can indicate the possible error in the acceleration and loss factor. The effect of temperature as an uncertainty on the MAC and NCO check is also studied using two viscoelastic systems. The usefulness of MAC for the correlation of a second multi-physics FEM that consists of a shunted piezoelectric damped system is also analyzed under harmonic excitation. It has been observed that MAC has limited use in the correlation and hence, a new correlation method – current assurance criterion – based on the electric current is introduced and it is demonstrated that this criterion correlates the dynamic characteristics of the piezoelectric system better than the MAC.

  • zhamg Z, Aglietti GS, Ren W, Addari D. (2014) 'Microvibration analysis of a cantilever configured reaction wheel assembly'. Techno-Press Advances in Aircraft and Spacecraft Science, Vol 1 (N 4), pp. 379-398.

    Abstract

    This article discusses the microvibration analysis of a cantilever configured reaction wheel assembly. Disturbances induced by the reaction wheel assembly were measured using a previously designed platform. Modelling strategies for the effect of damping are presented. Sine-sweep tests are performed and a method is developed to model harmonic excitations based on the corresponding test results. The often ignored broadband noise is modelled by removing spikes identified in the raw signal including a method of identifying spikes from energy variation and band-stop filter design. The validation of the reaction wheel disturbance model with full excitations (harmonics and broadband noise) is presented and flaws due to missing broadband noise in conventional reaction wheel assembly microvibration analysis are discussed.

  • Sairajan KK, Aglietti GS. (2014) 'Study of correlation criteria for base excitation of spacecraft structures'. Journal of Spacecraft and Rockets, 51 (1), pp. 106-116.
  • Zhang Z, Aglietti GS, Ren W. (2013) 'Coupled microvibration analysis of a reaction wheel assembly including gyroscopic effects in its accelerance'. Journal of Sound and Vibration, 332 (22), pp. 5748-5765.

    Abstract

    This article discusses the coupled microvibration analysis of a cantilever configured Reaction Wheel Assembly with soft-suspension system. A RWA-seismic mass coupled microvibration measurement system is presented and its model validated against test results. The importance of the RWA driving point accelerances in coupled microvibration analysis is thoroughly discussed. A RWA accelerance measurement system has been designed to measure the driving point accelerances in both static (flywheel not spinning) and dynamic (flywheel spinning) conditions. Analytically, RWA static accelerance is obtained by frequency response analysis of a finite element model. The traditionally ignored gyroscopic effects in the accelerances are included in the model and their effects with respect to traditional models are shown both theoretically and experimentally. Although at high angular speed, when nonlinearities in the microvibrations prevent an accurate simulation, it is shown that the predicted microvibrations match more closely with the test results when considering gyroscopic effects in RWA accelerances than those predicted using the traditional method. The presented coupled microvibration analysis method is also very efficient in practice and is applicable in an industrial environment. © 2013 Elsevier Ltd. All rights reserved.

  • Edeson RL, Aglietti GS, Tatnall ARL. (2013) 'Dimensional stability of materials subject to random vibration'. Precision Engineering, 37 (2), pp. 323-335.
  • Zhang Z, Aglietti GS, Ren WJ. (2012) 'Microvibration Model Development and Validation of a Cantilevered Reaction Wheel Assembly'. Applied Mechanics and Materials, 226, pp. 133-137.
  • Sairajan KK, Aglietti GS. (2012) 'Robustness of System Equivalent Reduction Expansion Process on Spacecraft Structure Model Validation'. American Institute of Aeronautics and Astronautics AIAA Journal: devoted to aerospace research and development, 50 (11), pp. 2376-2388.

    Abstract

    Test-analysis models are used in the validation of the nite element models of spacecraft structures. Here, a probabilistic approach is used to assess the robustness of a system equivalent reduction expansion process based testanalysis model when experimental and analytical modes contain different levels of inaccuracy. The approach is applied to three spacecraft models, and Monte Carlo simulations were used to determine the sensitivity of the normalized cross-orthogonality check to the system equivalent reduction expansion process reduced matrix. The effect of parameters used in this reduction and the amount of inaccuracies that can be tolerated in the modes before failing the normalized cross-orthogonality check were also determined. The results show that the probability to pass the normalized cross-orthogonality check is highly determined by the number of modes used in the reduction. The relation between capability of the nite element models to predict the frequency-response function and the quality of the model validation determined using normalized cross-orthogonality check is also investigated, and it is observed that the quantities are not always correlated. This study also shows that the sensor locations can be optimally chosen using the system equivalent reduction expansion process reduced mass matrix, and this can increase the probability to pass the normalized cross-orthogonality check.

  • Foster JA, Aglietti GS. (2012) 'Strategies for Thermal Control of a Multifunctional Power Structure Solar Array'. ASCE Edition. ASCE Journal of Aerospace Engineering, 25 (3)
  • Bianchi G, Aglietti GS, Richardson G. (2012) 'Static and fatigue behaviour of hexagonal honeycomb cores under in-plane shear loads'. Applied Composite Materials, 19 (2), pp. 97-115.

    Abstract

    Due to their high specific strength and high specific stiffness properties the use of honeycomb panels is particularly attractive in spacecraft structures. However, the harsh environment produced during the launch of a satellite can subject the honeycomb cores of these sandwich structures to severe quasi-static and dynamic loads, potentially leading to static or early fatigue failures. Knowledge of the static and fatigue behavior of these honeycomb cores is thus a key requirement when considering their use in spacecraft structural applications. This paper presents the findings of an experimental test campaign carried out to investigate the static and fatigue behaviors of aluminum hexagonal honeycomb cores subject to in-plane shear loads. The investigation involved carrying out both static and fatigue tests using the single block shear test method. These results are also discussed in relation to the observed damage and failure modes which have been reported for the statically tested specimens and for the fatigue tested specimens at various stages of fatigue life. As well as conducting tests for the more conventional principal cell orientations (L and W), results are also presented for tests carried out at intermediate orientations to investigate the variation of core shear strength with loading orientation. The results are further investigated using explicit non-linear finite element analysis to model the buckling failure mechanisms of the tested cores. © 2011 Springer Science+Business Media B.V.

  • Aglietti GS, Walker SJI, Kiley A. (2012) 'On the use of SEREP for satellite FEM validation'. Engineering Computations (Swansea, Wales), 29 (6), pp. 580-595.

    Abstract

    Purpose - The purpose of this paper is to assess the suitability of various methods for the reduction of a large finite element model (FEM) of satellites to produce models to be used for correlation of the FEM with test results. The robustness of the cross-orthogonality checks (COC) for the correlation process carried out utilizing the reduced model is investigated, showing its dependence on the number of mode shapes used in the reduction process. Finally the paper investigates the improvement in the robustness of the COC that can be achieved utilizing optimality criteria for the selection of the degrees of freedom (DOF) used for the correlation process. Design/methodology/approach - A Monte Carlo approach has been used to simulate inaccuracies in the mode shapes (analysis and experimental) of a satellite FEM that are compared during the COC. The sensitivity of the COC to the parameters utilized during the reduction process, i.e. mode shapes and DOFs, is then assessed for different levels of inaccuracy in the mode shapes. Findings - The System Equivalent Expansion Reduction Process (SEREP) has been identified as a particularly suitable method, with the advantage that a SEREP reduced model has the same eigenvalues and eigenvector of the whole system therefore automatically meeting the criteria on the quality of the reduced model. The inclusion of a high number of mode shapes in the reduction process makes the check very sensitive to minor experimental or modelling inaccuracies. Finally it was shown that utilizing optimality criteria in the selection of the DOFs to carry out the correlation can significantly improve the probability of meeting the COC criteria. Research limitations/implications - This work is based on the FEM of the satellite IT>Aeolus/IT>, and therefore the numerical values obtained in this study are specific for this application. However, this model represents a typical satellite FEM and therefore the trends identified in this work are expected to be generally valid for this type of structure. Practical implications - The correlation of satellite FEM with test results involves a substantial effort, and it is crucial to avoid failures of the COC due to numerical issues rather than real model inaccuracies. This work shows also how an inappropriate choice of reduction parameters can lead to failure of the COC in cases when there are only very minor differences (e.g. due to minor amount of noise in the results) between analytical and test resul

  • Zhou W-Y, Aglietti GS, Zhang Z. (2011) 'Modelling and testing of a soft suspension design for a reaction/momentum wheel assembly'. Journal of Sound and Vibration, 330 (18-19), pp. 4596-4610.
  • Zhang Z, Aglietti GS, Zhou W. (2011) 'Microvibrations induced by a cantilevered wheel assembly with a soft-suspension system'. AIAA Journal, 49 (5), pp. 1067-1079.

    Abstract

    Microvibration management onboard spacecraft with high stability requirements has drawn increasing interest from engineers and scientists, and this paper discusses a reaction wheel design that allows a significant reduction of mid- to high-frequency microvibrations and that has been practically implemented in industry. Disturbances typically induced by mechanical systems onboard a spacecraft (especially rotating devices such as reaction wheel assemblies and momentum wheel assemblies) can severely degrade the performance of sensitive instruments. Traditionally, wheel-induced high-frequency (over 100-200 Hz) vibrations, generated by a combination of phenomena from bearing noise to dynamic amplifications due to internal resonances, are especially difficult to control. In this paper, the dynamic behavior of a newly designed wheel assembly, with a cantilevered flywheel configuration supported by a soft-suspension system, is investigated. The wheel assembly's mathematical model is developed and later verified with vibration tests. Wheel-assembly-induced lateral and axial microvibrations are accurately measured using a seismic-mass microvibration measurement system, which represents an alternative to typical microvibration measurement setups. Finally, the performance of this wheel assembly in terms of microvibration emissions is compared with a traditional design (with a rigid suspension) through comparison of frequency spectra, and it is shown that this design produces significantly lower vibrations at high frequency. Copyright © 2010 by Zhe Zhang.

  • Walker SJI, McDonald AD, Niki T, Aglietti GS. (2011) 'Initial performance assessment of hybrid inflatable structures'. Acta Astronautica, 68 (7-8), pp. 1185-1192.
  • Redi S, Aglietti GS, Tatnall AR, Markvart T. (2011) 'Dynamic response to turbulence of tethered lighter-than-air platforms'. Journal of Aircraft, 48 (2), pp. 540-552.
  • Bianchi G, Aglietti GS, Richardson G. (2011) 'Static performance of hot bonded and cold bonded inserts in honeycomb panels'. Journal of Sandwich Structures and Materials, 13 (1), pp. 59-82.

    Abstract

    An investigation on the structural performance of inserts within honeycomb sandwich panels is presented. The investigation considers metallic inserts in all aluminum sandwich panels and emphasis is placed on the structural performance difference between hot bonded and cold bonded inserts. The former are introduced during panel manufacture while the latter are potted into existing panels. The investigation focuses on the static performance of the two insert systems subject to loads in the normal direction to the facing plane. The experimental part of the work presented involved carrying out pullout tests on hot bonded and cold bonded reference samples by loading them at a centrally located insert. The experimental results were compared with results from an analytical model and results from a finite element model. Contrary to what was expected it was found from the experiments that the cold bonded inserts outperformed the hot bonded inserts in terms of load carrying capability. From the finite element study it was found that this was mainly due to the difference in stiffness of the different filler materials used in the two insert systems. © The Author(s), 2011.

  • Amy RA, Aglietti GS, Richardson G. (2010) 'Board-Level Vibration Failure Criteria for Printed Circuit Assemblies: An Experimental Approach'. IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC IEEE TRANSACTIONS ON ELECTRONICS PACKAGING MANUFACTURING, 33 (4), pp. 303-311.
  • Roberts SC, Aglietti GS. (2010) 'Structural performance of a multifunctional spacecraft structure based on plastic lithium-ion batteries'. Acta Astronautica, 67 (3-4), pp. 424-439.
  • Foster JA, Aglietti GS. (2010) 'The thermal environment encountered in space by a multifunctional solar array'. Aerospace Science and Technology, 14 (3), pp. 213-219.
  • Redi S, Aglietti GS, Tatnall AR, Markvart T. (2010) 'An evaluation of a high altitude solar radiation platform'. Journal of Solar Energy Engineering, Transactions of the ASME, 132 (1), pp. 0110041-0110048.
  • Edeson R, Aglietti GS, Tatnall ARL. (2010) 'Conventional stable structures for space optics: The state of the art'. Acta Astronautica, 66 (1-2), pp. 13-32.
  • Amy RA, Aglietti GS, Richardson G. (2010) 'Accuracy of simplified printed circuit board finite element models'. PERGAMON-ELSEVIER SCIENCE LTD MICROELECTRONICS RELIABILITY, 50 (1), pp. 86-97.
  • Aglietti GS. (2009) 'Dynamic response of a high-altitude tethered balloon system'. Journal of Aircraft, 46 (6), pp. 2032-2040.
  • Walker SJI, Aglietti GS, Cunningham P. (2009) 'A study of joint damping in metal plates'. Acta Astronautica, 65 (1-2), pp. 184-191.
  • Amy RA, Aglietti GS, Richardson G. (2009) 'Simplified modelling of printed circuit boards for spacecraft applications'. PERGAMON-ELSEVIER SCIENCE LTD ACTA ASTRONAUTICA, 65 (1-2), pp. 192-201.
  • Amy RA, Aglietti GS, Richardson G. (2009) 'Sensitivity analysis of simplified Printed Circuit Board finite element models'. PERGAMON-ELSEVIER SCIENCE LTD MICROELECTRONICS RELIABILITY, 49 (7), pp. 791-799.
  • Aglietti GS, Redi S, Tatnall AR, Markvart T. (2009) 'Harnessing high-altitude solar power'. IEEE Transactions on Energy Conversion, 24 (2), pp. 442-451.
  • Amy RA, Aglietti GS, Richardson G. (2009) 'Reliability analysis of electronic equipment subjected to shock and vibration - A review'. IOS PRESS SHOCK AND VIBRATION, 16 (1), pp. 45-59.
  • Edeson R, Morris N, Tatnall A, Aglietti GS. (2009) 'Dimensional stability testing on a space optical bench structure'. AIAA Journal, 47 (1), pp. 219-228.
  • Aglietti GS, Redi S, Tatnall AR, Markvart T. (2008) 'High altitude electrical power generation'. WSEAS Transactions on Environment and Development, 4 (12), pp. 1067-1077.
  • Walker SJI, Aglietti GS, Cunningham P. (2008) 'Low-frequency damping of metal panels in ambient air'. Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science, 222 (8), pp. 1413-1420.
  • Walker SJI, Aglietti GS, Cunningham P. (2008) 'Study of damping linearity of jointed metal plates'. AIAA Journal, 46 (7), pp. 1738-1746.
  • Aglietti GS, Markvart T, Tatnall AR, Walker SJ. (2008) 'Solar power generation using high altitude platforms feasibility and viability'. Progress in Photovoltaics: Research and Applications, 16 (4), pp. 349-359.
  • Roberts SC, Aglietti GS. (2008) 'Satellite multi-functional power structure: Feasibility and mass savings'. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 222 (1), pp. 41-51.
  • Aglietti GS, Markvart T, Tatnall AR, Walker SJ. (2008) 'Aerostat for electrical power generation -concept feasibility'. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 222 (1), pp. 29-39.
  • Aglietti GS, Schwingshackl CW, Roberts SC. (2007) 'Multifunctional structure technologies for satellite applications'. Shock and Vibration Digest, 39 (5), pp. 381-391.
  • Schwingshackl CW, Aglietti GS, Cunningham PR. (2007) 'Experimental determination of the dynamic behavior of a multifunctional power structure'. AIAA Journal, 45 (2), pp. 491-496.
  • Walker SJI, Aglietti GS. (2007) 'A study of tape spring fold curvature for space deployable structures'. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 221 (3), pp. 313-325.
  • Walker SJI, Aglietti GS. (2007) 'Modeling the hinge moment of skew-mounted tape spring folds'. Journal of Aerospace Engineering, 20 (2), pp. 102-115.
  • Schwingshackl CW, Aglietti GS, Cunningham PR. (2006) 'Parameter optimization of the dynamic behavior of inhomogeneous multifunctional power structures'. AIAA Journal, 44 (10), pp. 2286-2294.
  • Schwingshackl CW, Aglietti GS, Cunningham PR. (2006) 'Determination of honeycomb material properties: Existing theories and an alternative dynamic approach'. Journal of Aerospace Engineering, 19 (3), pp. 177-183.
  • Walker SJI, Aglietti GS. (2006) 'Experimental investigation of tape springs folded in three dimensions'. AIAA Journal, 44 (1), pp. 151-159.
  • Walker SJI, Aglietti GS, Cunningham PR. (2006) 'Experimental analysis of damping across joints in metal plates'. Applied Mechanics and Materials, 5-6, pp. 391-398.

    Abstract

    In the current world of engineering, structural vibration problems continue impact the design and construction of a wide range of products. Amid the parameters that determine the dynamic behaviour of a structure the one that takes into account the dissipation of energy resulting in the decay of the vibration is the least understood and the most difficult to quantify [1]. The estimation of damping factors is of interest in most branches of engineering sciences. In the field of aircraft structures the damping directly affects the fatigue life, a parameter which is applied conservatively due to the inherent complexity in modelling the damping of built up structures and the potentially catastrophic consequences of a fatigue failure. One of the most important problems is the limited knowledge of how joints affect the damping of the complete structure. This work therefore addresses this issue and focuses on the damping of joints in metal plates as part of a larger project to investigate the damping of built up structures. Various plate configurations are experimentally investigated using two different approaches. The results from the configurations are compared and discussed along with the advantages and disadvantages of each experimental approach. This enables a link to be identified between the damping magnitudes and the mode shapes and joint stiffnesses.

  • Xiao Y, White RG, Aglietti GS. (2005) 'Comparison of structural response and fatigue endurance of aircraft flap-like box structures subjected to acoustic loading.'. J Acoust Soc Am, United States: 117 (5), pp. 2820-2834.
  • Xiao Y, White RG, Aglietti GS. (2005) 'An experimental characterization of the acoustic fatigue endurance of GLARE and comparison with that of CFRP'. Composite Structures, 68 (4), pp. 455-470.
  • Tan ACH, Meurers T, Veres SM, Aglietti G, Rogers E. (2005) 'Robust control of microvibrations with experimental verification'. Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science, 219 (5), pp. 453-460.
  • Aglietti GS, Langley RS, Rogers E, Gabriel SB. (2004) 'Model building and verification for active control of microvibrations with probabilistic assessment of the effects of uncertainties'. Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science, 218 (4), pp. 389-400.
  • Walker SJI, Aglietti G. (2004) 'Study of the Dynamics of Three-Dimensional Tape Spring Folds'. AIAA Journal, 42 (4), pp. 850-856.
  • Aglietti GS, Rogers E. (2003) 'Experimental validation of Lagrange-Rayleigh-Ritz modeling technique for mass loaded actively controlled panels'. Journal of Aerospace Engineering, 16 (1), pp. 31-37.
  • Aglietti GS, Cunningham PR. (2002) 'Is a simple support really that simple?'. Journal of Sound and Vibration, 257 (2), pp. 321-335.
  • Aglietti GS, Cunningham PR, Langley RS. (2002) 'Verification of various modelling techniques for simply-supported piezoelectric actuated thin panels'. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 216 (3), pp. 155-164.
  • Aglietti GS. (2002) 'A lighter enclosure for electronics for space applications'. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 216 (3), pp. 131-142.
  • Aglietti GS, Langley RS, Rogers E, Gabriel SB. (2000) 'An efficient model of an equipment loaded panel for active control design studies.'. J Acoust Soc Am, UNITED STATES: 108 (4), pp. 1663-1673.
  • Cunningham PR, White RG, Aglietti GS. (2000) 'Effects of various design parameters on the free vibration of doubly curved composite sandwich panels'. Journal of Sound and Vibration, 230 (3), pp. 617-648.
  • Bardell NS, Langley RS, Dunsdon JM, Aglietti GS. (1999) 'An h-p finite element vibration analysis of open conical sandwich panels and conical sandwich frusta'. Journal of Sound and Vibration, 226 (2), pp. 345-377.
  • Aglietti GS, Wicks A, Barrington-Brown AJ. (1999) 'SIL SGS-2.4 S-band ground station'. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 213 (4), pp. 265-272.
  • Aglietti GS, Wicks A, Barrington-Brown AJ. (1999) 'Development of the MiniSIL™ structural design'. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 213 (4), pp. 255-263.
  • Aglietti GS, Gabriel SB, Langley RS, Rogers E. (1997) 'A modeling technique for active control design studies with application to spacecraft microvibrations.'. J Acoust Soc Am, UNITED STATES: 102 (4), pp. 2158-2166.
  • Aglietti G, Rogers E, Langley RS, Gabriel SB, Stoustrup J. (1997) 'Robust control of microvibrations'. IEE Colloquium (Digest), (385)

Conference papers

  • Remedia M, Aglietti GS, Appolloni M, Cozzani A, Kiley A. (2016) 'A Virtual Testing Approach for Spacecraft Structures Post-Correlation Purposes'. Toulouse, France: 14th European Conference on Spacecraft Structures, Materials and Environmental Testing (ECSSMET 2016)
    [ Status: Accepted ]
  • Yotov V, Aglietti GS, Remedia M, Richardson G. (2016) 'Stochastic FEM-BEM Method for Spacecraft Vibroacoustic Analysis'. Proceedings of the 14th European Conference on Spacecraft Structures, Materials and Environmental Testing (ECSSMET), Toulouse, France: 14th European Conference on Spacecraft Structures, Materials and Environmental Testing (ECSSMET)
    [ Status: Accepted ]
  • Stabile A, Aglietti GS, Richardson G, Smet G. (2016) 'Design and Analysis of a Novel 2-collinear-DoF Strut With Embedded Electromagnetic Shunt Dampers'. Proceedings of ECSSMET 2016, Toulouse, France: 14th European Conference on Spacecraft Structures, Materials & Environmental Testing (ECSSMET)
    [ Status: Accepted ]
  • Duke R, Bridges C, Stewart B, Taylor B, Massimiani C, Forshaw JL, Aglietti G. (2016) 'Integrated Flight & Ground Software Framework for Fast Mission Timelines'. Proceedings of 67th International Astronautical Congress 2016, Guadalajara, Mexico: 67th International Astronautical Congress

    Abstract

    Flight and ground segment software in university missions is often developed only after hardware has matured sufficiently towards flight configuration and also as bespoke codebases to address key subsystems in power, communications, attitude, and payload control with little commonality. This bespoke software process is often hardware specific, highly sequential, and costly in staff/monitory resources and, ultimately, development time. Within Surrey Space Centre (SSC), there are a number of satellite missions under development with similar delivery timelines that have overlapping requirements for the common tasks and additional payload handling. To address the needs of multiple missions with limited staff resources in a given delivery schedule, computing commonality for both flight and ground segment software is exploited by implementing a common set of flight tasks (or modules) which can be automatically generated into ground segment databases to deliver advanced debugging support during system end-to-end test (SEET) and operations. This paper focuses on the development, implementation, and testing of SSC’s common software framework on the Stellenbosch ADCS stack and OBC emulators for numerous missions including Alsat-1N, RemoveDebris, SME-SAT, and InflateSail. The framework uses a combination of open-source embedded and enterprise tools such as the FreeRTOS operating system coupled with rapid development templates used to auto-generate C and Python scripts offline from ‘message databases’. In the flight software, a ‘core’ packet router thread forwards messages between threads for inter process communication (IPC). On the ground, this is complemented with an auto-generated PostgreSQL database and web interface to test, log, and display results in the SSC satellite operations centre. Profiling is performed using FreeRTOS primitives to manage module behaviour, context, time and memory – especially important during integration. This new framework has allowed for flight and ground software to be developed in parallel across SSC’s current and future missions more efficiently, with fewer propagated errors, and increased consistency between the flight software, ground station and project documentation.

  • Mercer JF, Aglietti GS, Kiley A. (2016) 'Study of Correlation Criteria for Spacecraft-Launch Vehicle Coupled Loads Analysis'. Orlando, Fl, USA: 34th Conference and Exposition on Structural Dynamics of Multiphysical Systems (IMAC XXXIV)
  • Forshaw J, Aglietti G. (2016) 'An Overview of Debris Removal Research Activities at Surrey: Surrey Space Centre (SSC) & Surrey Satellite Technology Limited (SSTL)'. Southampton, UK: 2nd Stardust Global Virtual Workshop
  • Wu C, Viquerat AD, Aglietti G. (2016) 'Optimization of the Natural Frequency and Buckling Analysis of Bistable Carbon Fiber Reinforced Plastic Booms for Space Applications'. American Institute of Aeronautics and Astronautics San Diego, CA: 3rd AIAA Spacecraft Structures Conference
  • Secheli G, Viquerat AD, Aglietti G. (2016) 'Mechanical Development of a Novel Inflatable and Rigidizable Structure'. American Institute of Aeronautics and Astronautics 3rd AIAA Spacecraft Structures Conference Proceedings, San Diego, CA: 3rd AIAA Spacecraft Structures Conference
  • Mercer J, Aglietti GS, Remedia M, Kiley A. (2016) 'Investigations concerning the effectiveness of the spacecraft finite element model correlation and update process'. Toulouse, France: 14th European Conference on Spacecraft Structures, Materials and Environmental Testing (ECSSMET)

    Abstract

    In order to examine the dynamic response of spacecraft during launch, Coupled Loads Analyses (CLAs), which couple a Finite Element Model (FEM) of the spacecraft with a model of the launch vehicle, are performed to simulate critical flight events. For the CLA results to be trusted, it is necessary to first develop a high level of confidence in the spacecraft FEM. This confidence is achieved by conducting appropriate test-FEM correlation and update activities making use of data gathered during vibration testing of the physical hardware. One major point of concern is the containment of the correlation and update effort in terms of mode count/modal domain. As such, this work is concerned with the assessment of the effectiveness of various target mode selection criteria. Findings are presented for initial investigations conducted using FEM data for a large, unique, scientific spacecraft developed by the European Space Agency (ESA). The work presented herein is the initial stage, and a larger study would be required to draw conclusions on the most effective means of containing the modal domain for correlation and update activities to those natural frequencies/modes which are most likely to contribute significantly in response to flight event level loading conditions.

  • Massimiani C, Forshaw J, Richter M, Viquerat A, Simons E, Duke R, Aglietti G. (2015) 'Review of Surrey Space Centre Debris Removal Research Missions'. Rome, Italy: 3rd IAA Conference on University Satellite Missions & CubeSat Workshop
  • Joffre E, Forshaw J, Secretin T, Reynaud S, Salmon T, Aurelien P, Aglietti G. (2015) 'RemoveDebris – Mission Analysis for a Low Cost Active Debris Removal Demonstration in 2016'. Deutsches Zentrum fuer Luft- und Raumfahrt e. V. (DLR) Munich, Germany: 25th International Symposium on Space Flight Dynamics (ISSFD)

    Abstract

    Contracted by the European Commission in the frame of the EU’s Seventh Framework Programme for Research (FP7), a wide European consortium has been working since 2013 towards the design of a low cost in-orbit demonstration called RemoveDEBRIS. With a targeted launch date in the second quarter of 2016, the RemoveDEBRIS mission aims at demonstrating key Active Debris Removal (ADR) technologies, including capture means (net and harpoon firing on a distant target), relative navigation techniques (vision-based navigation sensors and associated algorithms), and deorbiting technologies (drag sail deployment after the mission followed by an uncontrolled reentry). In order to achieve these objectives, a micro satellite testbed will be launched into a Low Earth Orbit, where it will deploy its own dedicated targets and CubeSats to complete each demonstration. As part of its System Engineering role, Airbus Defence and Space has been conducting the Mission Analysis studies for this unprecedented mission. This paper will present a description of the RemoveDEBRIS demonstration objectives and scenario and will present in detail some specific mission related analyses and trade-offs that have driven the mission design.

  • Bamber DC, Forshaw JL, Frame TE, Aglietti G, Geshnizjani R, Goerries S, Kornienko A, Levenhagen J, Gao Y, Chanik A. (2015) 'Absolute Attitude Determination System for a Spherical Air Bearing Testbed'. Jerusalem: 66th International Astronautical Congress
  • Forshaw JL, Aglietti G, Navarathinam N, Kadhem H, Salmon T, Joffre E, Chabot T, Retat I, Axthelm R, Barraclough S, Ratcliffe A, Bernal C, Chaumette F, Pollini A, Steyn WH. (2015) 'An In-Orbit Active Debris Removal Mission – RemoveDEBRIS: Pre-launch Update'. Jerusalem: 66th International Astronautical Congress
  • Forshaw JL, Massimiani C, Richter M, Viquerat A, Simons E, Duke R, Aglietti G. (2015) 'Surrey Space Centre: A Survey of Debris Removal Research Activities'. Jerusalem: 66th International Astronautical Congress
  • Mercer JF, Aglietti GS, Kiley A. (2015) 'Modal and Frequency base Techniques for Finite Element Model Correlation'. Crete Island, Greece: 5th International Conference on Computational Methods in Structural Dynamics and Earthquake Engineering. COMPDYN 2015
  • Stabile A, Aglietti GS, Richardson G. (2015) 'Electromagnetic damper design using a multiphysics approach'. SPIE-INT SOC OPTICAL ENGINEERING ACTIVE AND PASSIVE SMART STRUCTURES AND INTEGRATED SYSTEMS 2015, San Diego, CA: Conference on Active and Passive Smart Structures and Integrated Systems 9431
  • Remedia M, Aglietti GS, Richardson G, LePage B. (2014) 'Modelling Non-Structural Elements for Microvibration Analysis'. Conference on Noise and Vibration Engineering (ISMA) Proceedings, Leuven, Belgium: Conference on Noise and Vibration Engineering (ISMA)
  • Remedia M, Aglietti GS, Richardson G, LePage B, Seabrook T. (2014) 'Application of a Substructural Method for Modelling Satellite Microvibrations'. Braunschweig, Germany: European Conference on Spacecraft Structures, Materials & Environmental Testing (ECSSMET)
  • Mercer JF, Kiley AM, Aglietti GS. (2014) 'BepiColombo: Sine test FEM correlation experiences'. Proceedings of ISMA 2014 - International Conference on Noise and Vibration Engineering and USD 2014 - International Conference on Uncertainty in Structural Dynamics, , pp. 835-849.
  • Walker SJI, Cook A, Foster J, Aglietti G. (2014) 'Final development and testing of a multifunctional power structure for the ROV-E project'. Proceedings of ISMA 2014 - International Conference on Noise and Vibration Engineering and USD 2014 - International Conference on Uncertainty in Structural Dynamics, Leuven: ISMA2014 - USD2014 Conference, pp. 895-909.

    Abstract

    The ROV-E project is a three year European Union Framework 7 project, which began in January 2011, dedicated to the research and development of lightweight technologies for exploration rovers. As part of this the University of Southampton, along with other consortium members, have been looking into the development of a Multifunctional Power Structure (MFPS). This is a structure that combines aspects of the electrical power system into a single panel component, removing the unnecessary mass of additional structures and containers required to support distributed discrete components inside a rover. The specific components imbedded into the multifunctional panel include: power generation (photovoltaic cells), control electronics and power storage. The main focus of the research at the University of Southampton was the power storage function of the panel, which aimed at exploiting the cost benefits of using off the shelf components by using commercially available lithium polymer battery cells. Initial validation testing exposed these cells to structural, temperature and pressure environments which proved the robustness of the cells throughout the predicted lifecycle of the multifunctional panel. An initial representative honeycomb panel incorporating battery cells was constructed to validate the manufacturing process. This panel was then used experimentally to assess the failure methods of the cells, revealing that the cells are more likely to suffer performance loss due to bending than accelerations. Following on from the initial validation testing a full MFPS was designed and optimised before being subjected to mechanical and thermal environments. This paper focuses on the final design and testing of this complete MFPS. Although the testing encountered various unforeseen problems, the batteries were both mechanically and thermally validated as part of the complete MFPS.

  • Addari D, Aglietti GS, Remedia M, Richardson G, LePage B. (2014) 'Inspecting the characterisation of microvibration sources'. International Astronautical Federation Proceedings of the International Astronautical Congress, IAC, Toronto, Canada.: 65th International Astronautical Congress 2014 (IAC 2014): Our World Needs Space 8, pp. 5616-5621.
  • Remedia M, Aglietti GS. (2013) 'A Substructural Analytical Method for Micro-Vibration Related Analyses'. 64th International Astronautical Congress (IAC) Proceedings, Beijing, China: 64th International Astronautical Congress (IAC)
  • Remedia M, Aglietti GS, Richardson G, Le Page B. (2013) 'A general methodology for analysis of structure-borne micro-vibration'. 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference,
  • Foster JA, Aglietti GS, Walker SJI. (2013) 'ROV-E activities at Southampton University'. Proceedings of the International Astronautical Congress, IAC, 8, pp. 5995-6001.
  • Zhang Z, Aglietti GS. (2012) 'Coupled disturbance modelling and validation of a reaction wheel model'. European Space Agency, (Special Publication) ESA SP, 691 SP
  • Zhang Z, Aglietti GS, Ren W. (2012) 'Microvibration model development and validation of a cantilevered reaction wheel assembly'. Applied Mechanics and Materials, 226-228, pp. 133-137.
  • Remedia M, Aglietti GS, Zhang Z, LePage B, Richardson G. (2012) 'Modeling methodologies for microvibration-related analyses of spacecraft structures'. European Space Agency, (Special Publication) ESA SP, 691 SP
  • Sairajan KK, Aglietti GS. (2012) 'Validity of model correlation methods in FEM validation for forced vibration analysis'. European Space Agency, (Special Publication) ESA SP, 691 SP
  • Zhang Z, Aglietti GS, Le Page BH. (2012) 'Microvibration modelling and testing of a satellite reaction wheel assembly'. Institution of Mechanical Engineers - 10th International Conference on Vibrations in Rotating Machinery, , pp. 775-785.
  • Sairajan KK, Aglietti GS. (2012) 'Standard FEM validation checks and quality of response prediction'. Proceedings of the International Astronautical Congress, IAC, 8, pp. 6216-6222.
  • Edeson RL, Aglietti GS, Tatnall AR. (2012) 'The effects of random vibration on the dimensional stability of precision structures'. European Space Agency, (Special Publication) ESA SP, 691 SP
  • Remedia M, Aglietti G, Zhang Z, Page BL, Richardson G. (2012) 'A general methodology to study the transmission of micro-vibrations in satellites'. Proceedings of the International Astronautical Congress, IAC, 8, pp. 6386-6393.
  • Walker SJI, Kiley A, Aglietti GS, Cook A, McDonald AD. (2012) 'Modelling three dimensional, tape spring based, space deployable structures'. European Space Agency, (Special Publication) ESA SP, 691 SP
  • Remedia M, Aglietti GS. (2011) 'Modeling micro-vibrations transmission in spacecraft structures'. 62nd International Astronautical Congress 2011, IAC 2011, 7, pp. 5682-5690.
  • Edeson RL, Aglietti GS, Tatnall AR. (2011) 'Dimensional stability loss in structures subject to random vibration'. ECCOMAS Thematic Conference - COMPDYN 2011: 3rd International Conference on Computational Methods in Structural Dynamics and Earthquake Engineering: An IACM Special Interest Conference, Programme,
  • Walker SJI, Aglietti GS, Cook A, McDonald AD. (2011) 'Modelling built up, tape spring based, space deployable structures'. 62nd International Astronautical Congress 2011, IAC 2011, 7, pp. 5506-5515.
  • Aglietti GS, Zhang Z, Richardson G, Page BL, Haslehurstl A. (2011) 'Disturbance sources modeling for analysis of structure-borne micro-vibration'. ECCOMAS Thematic Conference - COMPDYN 2011: 3rd International Conference on Computational Methods in Structural Dynamics and Earthquake Engineering: An IACM Special Interest Conference, Programme,
  • Bianchi G, Aglietti GS, Richardson G. (2010) 'Development of efficient and cost-effective spacecraft structures based on honeycomb panel assemblies'. IEEE Aerospace Conference Proceedings,
  • Walker SJI, Santos S, McDonald A, Aglietti GS. (2010) 'Development of morphing deployables for space applications'. 61st International Astronautical Congress 2010, IAC 2010, 3, pp. 2007-2017.
  • Bianchi G, Aglietti GS, Richardson G. (2009) 'Experimental investigation of static and fatigue behaviour of honeycomb panels under in-plane shear loads'. Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference,
  • Foster JA, Aglietti GS. (2009) 'Thermal control of multifunctional power structures using phase change materials'. 60th International Astronautical Congress 2009, IAC 2009, 7, pp. 5688-5693.
  • Walker SJI, McDonald AD, Niki T, Aglietti GS. (2009) 'Development of inflatable structures at the University of Southampton'. 60th International Astronautical Congress 2009, IAC 2009, 7, pp. 5463-5472.
  • Redi S, Aglietti GS, Tatnall AR, Markvart T. (2009) 'Configuration study of high altitude solar collectors'. 2009 IEEE Electrical Power and Energy Conference, EPEC 2009,
  • Carrella A, Friswell MI, Pirrera A, Aglietti GS. (2008) 'Numerical and experimental analysis of a square bistable plate'. 23rd International Conference on Noise and Vibration Engineering 2008, ISMA 2008, 6, pp. 3433-3440.
  • Amy RA, Aglietti GS, Richardson G. (2008) 'Analysis of simplified FE models of PCBs exposed to random vibrations'. 23rd International Conference on Noise and Vibration Engineering 2008, ISMA 2008, 2, pp. 979-986.
  • Foster JA, Roberts SC, Aglietti GS. (2008) 'Multifunctional power structures and related thermal issues'. Proceedings of the ASME Conference on Smart Materials, Adaptive Structures and Intelligent Systems, SMASIS2008, 1, pp. 61-70.
  • Bianchi G, Aglietti GS, Richardson G. (2008) 'Static performance of hot bonded inserts in honeycomb panels'. Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference,
  • Roberts SC, Aglietti GS. (2008) 'Design of a multifunctional spacecraft structure using plastic lithium-ion batteries'. 12th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, MAO,
  • Schwingshackl CW, Aglietti GS, Cunningham PR. (2006) 'The dynamic behaviour of mulifunctional power strucutres'. AIAA 57th International Astronautical Congress, IAC 2006, 8, pp. 5266-5275.
  • Aglietti GS, Gomes L, Da Silva Curiel A. (2006) 'Hard disk drives for spacecraft application'. AIAA 57th International Astronautical Congress, IAC 2006, 5, pp. 3443-3451.
  • Amy RA, Aglietti GS, Richardson G. (2006) 'Simplified modelling of printed circuit boards for spacecraft applications'. AIAA 57th International Astronautical Congress, IAC 2006, 8, pp. 5022-5031.
  • Walker SJI, Aglietti GS, Cunningham P. (2006) 'A study of joint damping in metal plates'. AIAA 57th International Astronautical Congress, IAC 2006, 8, pp. 5181-5189.
  • Roberts SC, Aglietti GS. (2006) 'Multifunctional powerstructures structures for spacecraft'. AIAA 57th International Astronautical Congress, IAC 2006, 8, pp. 5258-5265.
  • Ward C, Curiel ADS, Sweeting M, Aglietti G, Schaffner J. (2005) 'Surrey small satellite transfer vehicle'. International Astronautical Federation - 56th International Astronautical Congress 2005, 4, pp. 2169-2178.
  • Schwingshackl CW, Cunningham PR, Aglietti GS. (2004) 'Honeycomb elastic material properties: A review of some existing theories and a new dynamic approach'. Proceedings of the 2004 International Conference on Noise and Vibration Engineering, ISMA, , pp. 1353-1363.
  • Tan ACH, Meurers T, Veres SM, Aglietti G, Rogers E. (2003) 'Satellite vibration control using frequency selective feedback'. Proceedings of the IEEE Conference on Decision and Control, 2, pp. 1693-1698.
  • Walker SJI, Aglietti G. (2003) 'A study into the dynamics of three dimensional tape spring folds'. Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 2, pp. 886-893.
  • Walker SJI, Aglietti G. (2003) 'A study into the dynamics of three dimensional tape spring folds'. 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference,
  • Meurers T, Veres SM, Aglietti G, Rogers E. (2003) 'Frequency selective microvibration control for a single plate'. Proceedings of the Tenth International Congress on Sound and Vibration, , pp. 179-186.
  • Aglietti GS, Cunningham PR, Langley RS. (2002) 'Development and verification of modelling techniques for piezoelectric actuated panels'. Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 2, pp. 1238-1246.
  • Aglietti GS, Langley RS, Rogers E, Gabriel SB. (2002) 'Model verification for active control of microvibrations'. IEEE Conference on Control Applications - Proceedings, 1, pp. 465-470.
  • Stoustrup J, Aglietti G, Rogers E, Langley RS, Gabriel SB. (1999) 'H-infinity controllers for the rejection of microvibration disturbances'. IEEE European Control Conference, ECC 1999 - Conference Proceedings, Karlsruhe, Germany: European Control Conference, ECC 1999, pp. 1294-1299.
  • Aglietti GS, Stoustrup J, Rogers E, Langley RS, Gabriel SB. (1998) 'LTR control methodologies for microvibrations'. IEEE Conference on Control Applications - Proceedings, 1, pp. 624-628.
  • Aglietti GS, Langley RS, Rogers E, Gabriel SB, Stoustrup J. (1998) 'Modelling of equipment loaded panels for robust control investigations'. Proceedings of the 23rd International Conference on Noise and Vibration Engineering, ISMA, , pp. 1333-1339.
  • Aglietti GS, Gabriel SB, Langley RS, Rogers E. (1996) 'Initial modelling and controller design for active control of spacecraft microvibrations'. European Space Agency, (Special Publication) ESA SP, (386 PART 2), pp. 633-640.

Book chapters

  • Aglietti GS. (2011) 'Spacecraft Mechanisms'. in (ed.) Spacecraft Systems Engineering, Fourth Edition , pp. 495-526.

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