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Purpose: While more and more organizations commit to transformation projects with the aim of redesigning simultaneously their workspaces, work organization, and technologies, the design process supporting such projects remains largely understudied. This paper examines the political tensions that occur when such processes unfold as well as their implications for project management. By doing so, the paper counterbalances the prescriptive and normative literature on "New Ways of Working" which largely overlooks the political complexity of such projects. Design/methodology/approach: The paper is based on a qualitative study of a triple design process in a media company. Data collection mainly consists of a nine-month process of non-participant observation of weekly meetings held by the strategic group in charge of the project. Semi-structured interviews with members of the executive committee have also been conducted. Findings: The analysis illustrates how space, organization and technology are gradually designed and structured. Four interconnected and often concealed mechanisms that support triple design processes are identified: political tensions, unexpected twists, conflicting temporalities and arbitration measures. Originality/value: The originality of the paper lies in breaking down the concept of design in three separate objects – organization, space and technology – and examining how these objects were conjointly problematized by an organization in transformation, whereas existing studies often investigate organization design, space design or technology design in isolation. [ABSTRACT FROM AUTHOR]

In this paper, a brief history of the links between the Wright brothers and the Aeronautical Society has been discussed. [ABSTRACT FROM AUTHOR]

Purpose: The purpose of this paper is to identify the main features of smart work centers (SWCs) and show how these innovative offices would support the implementation of smart working and related changes in workspaces ("bricks"), technologies ("bytes") and organizational practices ("behaviors"). Design/methodology/approach: In this study, scientific literature is combined with white papers and business reports and visits to 14 workplaces, including offices designed as SWCs, co-working spaces, one telecenter, one accelerator and one fab lab. Primary data were collected through interviews with managers and users and non-participant observation, whereas secondary data included web-sites, brochures, presentations, press releases and official documents. Findings: The authors developed research propositions about how the design of spaces and the availability of technology within SWCs would support the "bricks" and "bytes" levers of smart working. More importantly, the authors assumed that this new type of workplace would sustain changes in employees' behaviors and managers' practices, thus helping to overcome several challenges traditionally associated with remote working. Research limitations/implications: The exploratory nature of the research only provides preliminary information about the role of SWCs within smart working programs. Additional qualitative and quantitative empirical investigation is required. Practical implications: This study provides valuable knowledge about how the design of corporate offices can be leveraged to sustain the implementation of smart working. Originality/value: This study advances knowledge on workplaces by focusing on an innovative design of traditional offices (SWC). It also lays the foundations for future investigation aimed at testing the developed propositions. [ABSTRACT FROM AUTHOR]

Purpose – The purpose of this paper is to present a solution space searching method to study the initial design of interplanetary low thrust gravity assist trajectory. Design/methodology/approach – For reducing the complexity and nonlinearity of the initial design problem, a sixth degree inverse polynomial shape based approach is brought. Then some improvements are provided for solving the parameters in the shape function and a quasi-lambert solver is brought through the shape based method, the thrust profile can be generated under the given time of flight, boundary states including positions and velocities for low thrust phase. Combining gravity assist model, the problem is summarized and an improved pruning technique is used for searching the feasible solution space for low thrust gravity assist trajectory. Findings – Using the solution space searching method, the feasible solution region would be generated under the given mission condition. The treatment about gravity assist demonstrates more accurate than previous method. Also another advantage is that the searching method can be used to design different types of mission trajectory, including flyby and rendezvous trajectories. Practical implications – The method can be used as an efficient approach to search the feasible region for the complex low thrust gravity assist trajectory, and it can provide appropriate initial guesses for the low thrust gravity assist trajectory in mission design phase. Originality/value – Feasible solution space would be obtained through the searching method. The quasi-Lambert solver in the paper is found under the shape-based method and relative improvement, and it shows its availability during the searching process. Through mission trajectory design, the effectiveness of the method is shown. [ABSTRACT FROM AUTHOR]

Purpose – The purpose of this paper is to propose an attitude control algorithm for spacecraft with geometric constraints. Design/methodology/approach – The geometric constraint is reformulated as a quadratic form when quaternion is used as attitude parameter, then the constraint is proved to be nonconvex and is further transformed to a convex one. By designing a new constraint formulation to satisfy the real constraint in the predictive horizon, the attitude control problem is reshaped to a convex planning problem which is based on receding horizon control. Findings – The proposed algorithm is more effective in handling geometric constraints than previous research which used single step planning control. Practical implications – With novel improvements to current methods for steering spacecraft from one attitude to another with geometric constraints, great attitude maneuver path can be achieved to protect instruments and meanwhile satisfy mission requirements. Originality/value – The attitude control algorithm in this paper is designed especially for the satisfaction of geometric constraints in the process of attitude maneuver of spacecraft. By the application of this algorithm, the security of certain optical instruments, which is critical in an autonomous system, can be further assured. [ABSTRACT FROM AUTHOR]

Purpose – In today's competitive market, organizations are increasingly aware of the need to exchange the technologies, experience and knowledge they have developed in order to access new markets and revenue streams. They also recognize the need to acquire new technologies and knowledge from the external environment in order to exploit their ideas and create new products. Technology transfer (TT) is defined as the process for the passing and subsequent use of technology, expertise, know-how or facilities for a purpose not originally intended by the developing organization. Above all, the transfer of space technology is recognized as complex, even though it is increasingly adopted: space technologies can, for example, be adopted for healthcare products, improved waste management and water recovery, as well as by manufacturers. Notwithstanding, few studies have focused on the TT process inside the space sector. The purpose of this paper is to verify which process and what determinants result in the transfer of space technologies to other industrial sectors. Design/methodology/approach – This study has the final aim of developing the model of a transfer path suitable for the space industry. Specifically, the authors investigated two cases of TT, which have been promoted by an Italian systems integration company and supported by the National Research Council (CNR) and the Italian Space Agency (ASI). Findings – From an organizational viewpoint, some main differences related to the TT path emerge. Regarding the determinants, the study confirms other studies, i.e. that the most important determinants are the integrability, flexibility and high reliability of the technology, the availability of financial resources, followed by the technological versatility, and the level of R&D competences and knowledge of the receiver organization. Originality/value – The technological innovation literature has, as yet, paid little attention to the TT process into non-space areas from the space sector. In order to fill this gap, the paper contributes to broadening the knowledge base on the determinants for TT success in the space sector. [ABSTRACT FROM AUTHOR]

Purpose – The purpose of this paper is to study a finite-thrust orbital transfer optimization problem via a new optimal control method-Gauss pseudospectral method. Design/methodology/approach – Based on the dynamic equations with the pseudo-equinoctial elements as state variable, optimality condition is derived and the optimization problem is converted into nonlinear programming problem. Gauss pseudospectral method is used to avoid the two-point boundary value problem. The dynamic equations are converted into static parameter optimization problem. The state variables and control variables are selected as optimal parameters at all collocation nodes. Two numerical examples of orbital transfer with coplanar and different planes are analyzed, respectively. Findings – The simulation results demonstrate that Gauss pseudospectral method is not sensitive to the initial conditions of orbital transfer. They also show good robustness and control facility. Originality/value – The precision and efficiency of this trajectory optimization method are demonstrated by applying it to space vehicle orbital transfer with finite thrust optimization problem. [ABSTRACT FROM AUTHOR]

Purpose - This paper seeks to provide an insight into the design and development of the thermal test model (TTM) of X-Sat, a 120?kg class micro-satellite, being developed at the Centre. This model was specifically constructed for carrying out a thermal balance test (TBT) in a 4?m diameter vertical thermal vacuum chamber. Design/methodology/approach - The construction of the thermal model followed a structural mock-up model which was modified thermally to suit the purpose. Specific and careful consideration was given to the geometry and, more importantly, thermal characteristics such as thermal mass, surface properties, etc. to mimic the actual satellite configuration as closely as possible. Test plans were devised to qualify the fabricated components to meet the out-gassing and other thermal requirements for the model. Design and qualification of supporting frame and linkages for TBT are also covered. Findings - It is possible to simulate the thermal characteristics of a micro-satellite in orbit under a different mission scenario through proper scaling and using alternative material options while developing TTM. Originality/value - The paper discusses in detail the simplified cost-effective approach of constructing TTM and also outlines the various issues to be considered for a TBT. It provides valuable information needed for micro-satellite designers. [ABSTRACT FROM AUTHOR]

Spacecraft formation flying is a key technology for future astronautics. The relative dynamics of formation flying in eccentric orbits is studied, and the relative motion between spacecrafts is analyzed in this paper. Based on the two-body problem, the extension of Hill equations is achieved and used in relative dynamics of eccentric orbits. Moreover, the transformation of differential variables is applied, and the algebraic solution of the relative motion is obtained, which can be generally used for spacecraft formation flying in eccentric orbits. In addition, the analysis and numerical simulations are given for the relative motion of spacecraft formation flying. The results demonstrate that each spacecraft in eccentric orbits can run in a periodic motion surrounding the master spacecraft under some conditions. And multiple spacecraft can also set up some special formations according to missions. [ABSTRACT FROM AUTHOR]

Purpose: The present work aims to analyze the performance of a newly designed graphene-based patch antenna by varying the chemical potential in graphene sheet, using the CST Microwave Studio ® software. This study mainly seeks to discuss and assess the advantage of using graphene, instead of copper, as the radiating patch. It should be noted that graphene is a new material that possesses unique properties. Its parameters are optimized for the purpose of introducing it in satellite technology. Design/methodology/approach: The use of graphene as a radiating patch of space technology applications, where a polygonal graphene patch antenna element is designed by the CST Microwave Studio ® software with Taconic RF-41 substrate to resonate in the satellite bands. Findings: Analysis of a graphene patch sheet by a variation in the chemical potential to ensure operation in a space environment. Originality/value: The increase in the chemical potential for a graphene patch antenna has shown a prominent increase in the values of the gain. A new contribution, by the combination of the antenna performance improvement techniques and the use of graphene as a radiating patch of space technology applications. [ABSTRACT FROM AUTHOR]

Purpose - As the installation of the vibration isolation device to the spacecraft for the whole spacecraft vibration isolation, the interface structure is typically modeled as a rigid structure during the design phase. However, the flexibility of the interface structure does exist for a large-sized adaptor. This is a source of uncertainty and could reduce the reliability of the system. It is necessary to investigate the influence of this type of flexibility on the vibration isolation performance in an engineering practice. This paper aims to address this situation. Design/methodology/approach - The vibratory transmissibility from the bottom of the isolator is generally used to evaluate the performance of the vibration isolation. By introducing the interface flexibility from both the adaptor and the vibration isolation device, a planar model which includes a flexible beam representing the interface structure is established to study the influence of this type of flexibility on the vibratory transmissibility. Findings - It is found that, when this type of flexibility is included, an extra low-frequency mode dominated locally by the interface structure is induced, and then a significant resonance appears in the vibratory transmissibility of the vibration isolation device at a low frequency. Originality/value - The vibration isolation performance may be over-estimated in the design by taking the interface as rigid. The inherent flexibility of the interface structure, on the other hand, may degrade the performance of the vibration isolation device and degrade the function of the rotation constraint device added into the vibration isolation device. [ABSTRACT FROM AUTHOR]

Purpose The purpose of this study is to increase maximum lift/drag ratio (Emax) of tactical unmanned aerial vehicles (TUAVs) via applying novel small aerodynamic modifications.Design methodology/approach A TUAV is manufactured in Erciyes University, Faculty of Aeronautics and Astronautics, Model Aircraft Laboratory. It has both passive and active morphing capabilities. Its nosecone and tailcone shapes are redesigned to improve Emax. Moreover, active flow control is also built on its wing for improving Emax.Findings Using these novel small aerodynamic modifications, considerable improvement on Emax is obtained.Research limitations/implications Permission of Directorate General of Civil Aviation in Turkey is required for testing TUAVs in real-time applications.Practical implications Small aerodynamic modifications such as nosecone-tailcone shape modifications and building active flow control on wing are very beneficial for improving Emax of TUAVs.Social implications Small aerodynamic modifications satisfy confidence, high performance and easy utility demands of TUAV users.Originality/value The study will enable the creation of novel approaches to improve Emax value and therefore aerodynamic performance of TUAVs. [ABSTRACT FROM AUTHOR]

Purpose A novel vision-based relative navigation system (VBRNS) plays an important role in aeronautics and astronautics fields, and the filter is the core of VBRNS. However, most of the existing filtering algorithms used in VBRNS are derived based on Gaussian assumption and disregard the non-Gaussianity of VBRNS. Therefore, a novel robust filtering named as cubature Huber-based filtering (CHF) is proposed and applied to VBRNS to improve the navigation accuracy in non-Gaussian noise case.Design/methodology/approach Under the Bayesian filter framework, the third-degree cubature rule is used to compute the cubature points which are propagated through state equation, and then the predicted mean and the associated covariance are taken. A combined minimum l1 and l2-norm estimation method referred as Huber’s criterion is used to design the measurement update. After that, the vision-based relative navigation model is presented and the CHF is used to integrate the line-of-sight measurements from vision camera with inertial measurement of the follower to estimate the precise relative position, velocity and attitude between two unmanned aerial vehicles. During the design of relative navigation filter, the quaternions are used to represent the attitude and the generalized Rodrigues parameters are used to represent the attitude error. The simulation is conducted to demonstrate the effectiveness of the algorithm.Findings By this means, the VBRNS could perform better than traditional VBRNS whose filter is designed by Gaussian filtering algorithms. And the simulation results demonstrate that the CHF could exhibit robustness when the system is non-Gaussian. Moreover, the CHF has more accurate estimation and faster rate of convergence than extended Kalman Filtering (EKF) in face of inaccurate initial conditions.Originality/value A novel robust nonlinear filtering algorithm named as CHF is proposed and applied to VBRNS based on cubature Kalman filtering (CKF) and Huber’s technique. The CHF could adapt to the non-Gaussian system effectively and perform better than traditional Gaussian filtering such as EKF. [ABSTRACT FROM AUTHOR]