Design Solutions For Modular Satellite Architectures

The cost-effective access to space envisaged by ESA would open a wide range of new opportunities and markets, but is still many years ahead. There is still a lack of devices, circuits, systems which make possible to develop satellites, ground stations and related services at costs compatible with the budget of academic institutions and small and medium enterprises (SMEs). As soon as the development time and cost of small satellites will fall below a certain threshold (e.g. 100,000 to 500,000 €), appropriate business models will likely develop to ensure a cost-effective and pervasive access to space, and related infrastructures and services. These considerations spurred the activity described in this paper, which is aimed at: - proving the feasibility of low-cost satellites using COTS (Commercial Off The Shelf) devices. This is a new trend in the space industry, which is not yet fully exploited due to the belief that COTS devices are not reliable enough for this kind of applications; - developing a flight model of a flexible and reliable nano-satellite with less than 25,000€; - training students in the field of avionics space systems: the design here described is developed by a team including undergraduate students working towards their graduation work. The educational aspects include the development of specific new university courses; - developing expertise in the field of low-cost avionic systems, both internally (university staff) and externally (graduated students will bring their expertise in their future work activity); - gather and cluster expertise and resources available inside the university around a common high-tech project; - creating a working group composed of both University and SMEs devoted to the application of commercially available technology to space environment. The first step in this direction was the development of a small low cost nano-satellite, started in the year 2004: the name of this project was PiCPoT (Piccolo Cubo del Politecnico di Torino, Small Cube of Politecnico di Torino). The project was carried out by some departments of the Politecnico, in particular Electronics and Aerospace. The main goal of the project was to evaluate the feasibility of using COTS components in a space project in order to greatly reduce costs; the design exploited internal subsystems modularity to allow reuse and further cost reduction for future missions. Starting from the PiCPoT experience, in 2006 we began a new project called ARaMiS (Speretta et al., 2007) which is the Italian acronym for Modular Architecture for Satellites. This work describes how the architecture of the ARaMiS satellite has been obtained from the lesson learned from our former experience. Moreover we describe satellite operations, giving some details of the major subsystems. This work is composed of two parts. The first one describes the design methodology, solutions and techniques that we used to develop the PiCPoT satellite; it gives an overview of its operations, with some details of the major subsystems. Details on the specifications can also be found in (Del Corso et al., 2007; Passerone et al, 2008). The second part, indeed exploits the experience achieved during the PiCPoT development and describes a proposal for a low-cost modular architecture for satellite

Effect of late-season nitrogen fertilization on grain yield and on flour rheological quality and stability in common wheat, under different production situations

The increasing demand for a high and homogeneous technological quality of common wheat (Triticum aestivum L.) points out the necessity of improving wheat with by a higher protein (GPC) and gluten content, strength of dough (W) and dough stability. Among the current crop practices, late-season nitrogen (N) fertilization, from heading to flowering, is generally considered the practice that has the most effects on the storage proteins and technological quality of the grain. In order to explore the influence late-season N application can have on the dough properties and on the formation of homogeneous lots in more detail, a research was set up between 2007 and 2013, over 6 growing seasons at different sites in North West Italy using the Bologna cultivar in each of the trials. Three different late-season N fertilization strategies were compared: T1, control without a late distribution of N; T2, foliar N fertilization at flowering; T3, top-dress granular soil fertilization at the beginning of heading. A randomized complete block experimental design with four replicates was adopted. The grain yield, GPC, W and P/L indexes were analyzed. Moreover, the rheological and enzymatic properties of the samples were studied using a Mixolab® analyser (Chòpin Technologies, Paris, France). Grain yield was found to be unaffected by the fertilization treatments, while the late N application (T2, T3) significantly increased GPC. Only the granular N fertilization (T3) increased the W index compared to T1, while the P/L index was not affected by any of the fertilization strategies. Furthermore, the T3 strategy was always more effective in reducing the variability of the W index than the T2 and the T1 strategies. Water absorption and dough development time were higher in T3, than in T1, while intermediate results were reached for T2. The effect of late-season N fertilization was also significant on the starch behaviour of the dough, as an increase in starch gelatinization and retrogradation was observed. In short, the top-dress granular N fertilizer applied at the beginning of heading (T3) led to a more constant increase in GPC and flour rheological quality than the foliar application. Moreover, the adoption of this fertilization strategy resulted in a reduction in qualitative variability under different environmental and soil conditions

Communication and Mutual Physical Position Estimation System for CubeSat

In recent years, constellations of CubeSats organized as a swarm are redefining the classical concept of space missions. The biggest challenge for the realization of an efficient swarm is to provide to the CubeSats the ability to interact and communicate each other. In this paper we present a system able to provide to the CubeSats belonging to a swarm the ability to establish an inter-satellite communication crosslink and to determine the mutual physical positioning. The basic idea is to provide every CubeSat with a system involving a smart-antenna array. By exploiting the array, CubeSats can transmit or receive signals to / from every element of the swarm so as to perform the inter-satellite communication. The smart-antenna is managed by a beamforming control strategy: during the transmission, the beamforming algorithm controls the smart-antenna in order to shape the beam and establish a reliable and directive communication link with other spacecraft and/or with the ground station. Hence, the beam shaping avoid to perform attitude maneuvers to optimize the transmission. Every CubeSat acquires signals transmitted from other elements of the swarm and estimate the Direction-of-Arrival (DOA) and the distance (Range) in order to calculate the mutual physical positioning. By an appropriate distribution of the antennas on the structure of the CubeSat it is possible to obtain a working range of 4π steradians. Every element of the smart-antenna is connected to a signal conditioning chain able to modify the phase and the amplitude of the signal transmitted / received. The beamforming algorithm manages this signal conditioning chain dynamically to maximize the performance of the system. Thanks to his small footprint, the system can be mounted on every CubeSat geometry and it is completely integrated with the bus so as not to occupy space dedicated for the payload as shown in figure [1]. Through the use of a deployable structure fully developed at Politecnico di Torino, we increase the external surface of CubeSats: this surface allows to gain the interspace between elements of the smart-antenna (figure [2]). As a consequence, the directivity and detection performance of the DOA system in terms of directivity and accuracy are improved. Moreover, the deployable structure offers a greater usable surface, so a larger number of solar panels can be used, e.g.: up to 40x30 cm2 for a 1U CubeSat. Hence, the communication distance increase because a power up to 6W is available for the transmit mode. This paper describes the physical implementation of the antenna array system on a 1U CubeSat using the deployable structure developed. In section I we describe how the subsystem has been designed, we analyze how the hardware works and we focus on the main blocks that realize the positioning measurement / network communication. In the section II we describe how the swarm subsystem can be hosted on every CubeSat structure (even 1U) by exploiting a deployable structure able to increase the useful surface of the CubeSat and the antenna baseline. This structure allows to gain the available power supply for the transmission (also for the other on board systems) and improves the precision of the mutual positioning estimator. In section III we describe how the subsystem establishes the communication between the CubeSats and how it measures the direction of arrival (DOA) and the distance (Range) of the received signals in order to establish the mutual physical position of every CubeSat composing the swarm