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An optimal steering law for sails that exploit both solar and infrared planetary radiation pressure is presented in this paper. The optimal steering law maximises the orbit raise over one revolution of the sail around the planet. An indirect analytical approach, that uses Pontryagin Minimum Principle, is used to develop specialised steering laws for the sunlit and eclipse cases in a planar motion scenario. The law for the sunlit case uses both the solar and infrared radiation emitted from the planet, while the law for the eclipse case finds the optimal sail attitude that maximises the raise of the orbit using only the planetary radiation. Numerical results show that these laws lead to better performance in terms of orbit raising against other sub-optimal and optimal strategies exploiting the solar radiation pressure only. A numerical study is also carried out to show the effects of the reflectivity coefficient in the infrared band on the orbital motion of the sail.
Anaïs Barles; Matteo Ceriotti; Francesco Ciampa; Leonard Felicetti. An optimal steering law for sailing with solar and planetary radiation pressure. Aerospace Science and Technology 2021, 107051 .
AMA StyleAnaïs Barles, Matteo Ceriotti, Francesco Ciampa, Leonard Felicetti. An optimal steering law for sailing with solar and planetary radiation pressure. Aerospace Science and Technology. 2021; ():107051.
Chicago/Turabian StyleAnaïs Barles; Matteo Ceriotti; Francesco Ciampa; Leonard Felicetti. 2021. "An optimal steering law for sailing with solar and planetary radiation pressure." Aerospace Science and Technology , no. : 107051.
Autonomous operations in the proximity of Near Earth Objects (NEO) are perhaps the most challenging and demanding type of mission operation currently being considered. The exceptional variability of geometric and illumination conditions, the scarcity of large scale surface features and the strong perturbations in their proximity require incredibly robust systems to be handled. Robustness is usually introduced by either increasing the number and/or the complexity of on-board sensors, or by employing algorithms capable of handling uncertainties, often computationally heavy. While for a large satellite this would be predominantly an economic issue, for small satellites these constraints might push the ability to accomplish challenging missions beyond the realm of technical possibility. The scope of this paper is to present an active approach that allows small satellites deployed by a mothership to perform robust navigation using only a monocular visible camera. In particular, the introduction of Non-cooperative Artificial Visual landmarks (NAV-Landmarks) on the surface of the target object is proposed to augment the capabilities of small satellites. These external elements can be effectively regarded as an infrastructure forming an extension of the landing system. The quantitative efficiency estimation of this approach will be performed by comparing the outputs of a visual odometry algorithm, which operates on sequences of images representing ballistic descents around a small non-rotating asteroid. These sequences of virtual images will be obtained through the integration of two simulated models, both based on the Apollo asteroid 101955 Bennu. The first is a dynamical model, describing the landing trajectory, realized by integrating over time the gravitational potential around a three-axis ellipsoid. The second model is visual, generated by introducing in Unreal Engine 4 a CAD model of the asteroid (with a resolution of 75 cm) and scattering on its surface a number N of cubes with side length L. The effect of both N and L on the navigation accuracy will be reported. While defining an optimal shape for the NAV-Landmarks is out of the scope of this paper, prescriptions about the beacons geometry will be provided. In particular, in this work the objects will be represented as high-visibility cubes. This shape satisfies, albeit in a non-optimal way, most of the design goals.
Marco Zaccaria Di Fraia; Lounis Chermak; Joan-Pau Cuartielles; Leonard Felicetti; Antonio Fulvio Scannapieco. NAV-Landmarks: Deployable 3D Infrastructures to Enable CubeSats Navigation Near Asteroids. 2020 IEEE Aerospace Conference 2020, 1 -14.
AMA StyleMarco Zaccaria Di Fraia, Lounis Chermak, Joan-Pau Cuartielles, Leonard Felicetti, Antonio Fulvio Scannapieco. NAV-Landmarks: Deployable 3D Infrastructures to Enable CubeSats Navigation Near Asteroids. 2020 IEEE Aerospace Conference. 2020; ():1-14.
Chicago/Turabian StyleMarco Zaccaria Di Fraia; Lounis Chermak; Joan-Pau Cuartielles; Leonard Felicetti; Antonio Fulvio Scannapieco. 2020. "NAV-Landmarks: Deployable 3D Infrastructures to Enable CubeSats Navigation Near Asteroids." 2020 IEEE Aerospace Conference , no. : 1-14.
This paper proposes an image-based visual-servoing algorithm that allows for optimal formation control. The proposed distributed controller utilizes visual features of other team members, retrieved from images captured by onboard cameras, to autonomously plan and perform formation acquisition, keeping or reconfiguration maneuvers. The problems of minimization of the control effort is analyzed and the paper proposes an optimal framework for developing controllers that address the issue. The viability of such a technique is explored through numerical simulations.
Leonard Felicetti; Jorge Pomares. Image-Based Visual Servoing Control for Spacecraft Formation Flying. 2020 IEEE Aerospace Conference 2020, 1 -10.
AMA StyleLeonard Felicetti, Jorge Pomares. Image-Based Visual Servoing Control for Spacecraft Formation Flying. 2020 IEEE Aerospace Conference. 2020; ():1-10.
Chicago/Turabian StyleLeonard Felicetti; Jorge Pomares. 2020. "Image-Based Visual Servoing Control for Spacecraft Formation Flying." 2020 IEEE Aerospace Conference , no. : 1-10.
Literature on solar sailing has thus far mostly considered solar radiation pressure (SRP) as the only contribution to sail force. However, considering a sail in a planetary mission scenario, a new contribution can be added. Since the planet itself emits radiation, this generates a radial planetary radiation pressure (PRP) that is also exerted on the sail. Hence, this work studies the combined effects of both SRP and PRP on a sail for two case studies, i.e. Earth and Venus. In proximity of the Earth, the effect of PRP can be significant under specific conditions. Around Venus, instead, PRP is by far the dominating contribution. These combined effects have been studied for single- and double-sided reflective coating and including eclipse. Results show potential increase in the net acceleration and a change in the optimal attitude to maximise the acceleration in a given direction. Moreover, an increasing semi-major axis manoeuvre is shown with and without PRP, to quantify the difference on a real-case scenario.
Alessia De Iuliis; Francesco Ciampa; Leonard Felicetti; Matteo Ceriotti. Sailing with solar and planetary radiation pressure. Advances in Space Research 2019, 1 .
AMA StyleAlessia De Iuliis, Francesco Ciampa, Leonard Felicetti, Matteo Ceriotti. Sailing with solar and planetary radiation pressure. Advances in Space Research. 2019; ():1.
Chicago/Turabian StyleAlessia De Iuliis; Francesco Ciampa; Leonard Felicetti; Matteo Ceriotti. 2019. "Sailing with solar and planetary radiation pressure." Advances in Space Research , no. : 1.
We propose a non-linear model predictive scheme for planning fuel efficient maneuvers of small spacecrafts that shall rendezvous space debris. The paper addresses the specific issues of potential limited on-board computational capabilities and low-thrust actuators in the chasing spacecraft, and solves them by using a novel MatLab-based toolbox for real-time non-linear model predictive control (MPC) called MATMPC. This tool computes the MPC rendezvous maneuvering solution in a numerically efficient way, and this allows to greatly extend the prediction horizon length. This implies that the overall MPC scheme can compute solutions that account for the long time-scales that usually characterize the low-thrust rendezvous maneuvers. The so-developed controller is then tested in a realistic scenario that includes all the near-Earth environmental disturbances. We thus show, through numerical simulations, that this MPC method can successfully be used to perform a fuel-efficient rendezvous maneuver with an uncontrolled object, plus evaluate performance indexes such as mission duration, fuel consumption, and robustness against sensor and process noises.
Alexander Korsfeldt Larsén; Yutao Chen; Mattia Bruschetta; Ruggero Carli; Angelo Cenedese; Damiano Varagnolo; Leonard Felicetti. A computationally efficient model predictive control scheme for space debris rendezvous. IFAC-PapersOnLine 2019, 52, 103 -110.
AMA StyleAlexander Korsfeldt Larsén, Yutao Chen, Mattia Bruschetta, Ruggero Carli, Angelo Cenedese, Damiano Varagnolo, Leonard Felicetti. A computationally efficient model predictive control scheme for space debris rendezvous. IFAC-PapersOnLine. 2019; 52 (12):103-110.
Chicago/Turabian StyleAlexander Korsfeldt Larsén; Yutao Chen; Mattia Bruschetta; Ruggero Carli; Angelo Cenedese; Damiano Varagnolo; Leonard Felicetti. 2019. "A computationally efficient model predictive control scheme for space debris rendezvous." IFAC-PapersOnLine 52, no. 12: 103-110.
This paper proposes an image-based control scheme for tracking space debris using onboard optical sensors. The proposed strategy uses an onboard camera for detecting space debris. The camera is rigidly attached to the satellite; therefore specific attitude maneuvers need to be performed during different phases of the mission. First, the spacecraft orients its attitude to point the camera toward a fixed direction in space, and then when debris traces streak across the field of view of the camera, the spacecraft follows and tracks the motion of the debris. Finally, a disengagement maneuver is executed to stop the spacecraft rotation when the debris disappears from the camera field of view. The model and the developed control scheme take into account the typical characteristics of space-qualified cameras, and a Kalman filter is developed to reduce the effects of the camera noise, detect and predict the path of the debris in the image plane, and estimate the angular velocity of the spacecraft. The entire estimation/control scheme is then validated through numerical simulations, using a model of reaction wheels as the main attitude actuation system. The results demonstrate the viability of such maneuvers in a typical space debris surveillance mission scenario.
Leonard Felicetti; M. Reza Emami. Image-based attitude maneuvers for space debris tracking. Aerospace Science and Technology 2018, 76, 58 -71.
AMA StyleLeonard Felicetti, M. Reza Emami. Image-based attitude maneuvers for space debris tracking. Aerospace Science and Technology. 2018; 76 ():58-71.
Chicago/Turabian StyleLeonard Felicetti; M. Reza Emami. 2018. "Image-based attitude maneuvers for space debris tracking." Aerospace Science and Technology 76, no. : 58-71.
The utilization of zooming cameras during a non-cooperative rendezvous in space is investigated in this paper. An image-based controller, utilizing visual servoing techniques usually applied to ground-based robotic systems, is designed for the particular problem of far-to-close approach of a spacecraft to a non-cooperative object. The controller directly utilizes the visual features from image frames of the noncooperative target for computing both attitude and orbital maneuvers concurrently. The additional feature derived from the utilization of the zooming camera gives a greater versatility to the maneuvers if compared with the classic fixed optics approaches. The stability of the proposed controller is proven analytically in the invariant space, and its viability is explored through the application to a realistic space debris removal scenario.
Jorge Pomares; Leonard Felicetti; Javier Perez; M. Reza Emami. Spacecraft visual servoing with adaptive zooming for non-cooperative rendezvous. 2018 IEEE Aerospace Conference 2018, 1 -8.
AMA StyleJorge Pomares, Leonard Felicetti, Javier Perez, M. Reza Emami. Spacecraft visual servoing with adaptive zooming for non-cooperative rendezvous. 2018 IEEE Aerospace Conference. 2018; ():1-8.
Chicago/Turabian StyleJorge Pomares; Leonard Felicetti; Javier Perez; M. Reza Emami. 2018. "Spacecraft visual servoing with adaptive zooming for non-cooperative rendezvous." 2018 IEEE Aerospace Conference , no. : 1-8.
Leonard Felicetti; M. Reza Emami. Vision-Aided Attitude Control for Space Debris Detection. Journal of Guidance, Control, and Dynamics 2018, 41, 573 -575.
AMA StyleLeonard Felicetti, M. Reza Emami. Vision-Aided Attitude Control for Space Debris Detection. Journal of Guidance, Control, and Dynamics. 2018; 41 (2):573-575.
Chicago/Turabian StyleLeonard Felicetti; M. Reza Emami. 2018. "Vision-Aided Attitude Control for Space Debris Detection." Journal of Guidance, Control, and Dynamics 41, no. 2: 573-575.
An image-based servo controller for the guidance of a spacecraft during non-cooperative rendezvous is presented in this paper. The controller directly utilizes the visual features from image frames of a target spacecraft for computing both attitude and orbital maneuvers concurrently. The utilization of adaptive optics, such as zooming cameras, is also addressed through developing an invariant-image servo controller. The controller allows for performing rendezvous maneuvers independently from the adjustments of the camera focal length, improving the performance and versatility of maneuvers. The stability of the proposed control scheme is proven analytically in the invariant space, and its viability is explored through numerical simulations
Jorge Pomares; Leonard Felicetti; Javier Pérez; M. Reza Emami. Concurrent image-based visual servoing with adaptive zooming for non-cooperative rendezvous maneuvers. Advances in Space Research 2018, 61, 862 -878.
AMA StyleJorge Pomares, Leonard Felicetti, Javier Pérez, M. Reza Emami. Concurrent image-based visual servoing with adaptive zooming for non-cooperative rendezvous maneuvers. Advances in Space Research. 2018; 61 (3):862-878.
Chicago/Turabian StyleJorge Pomares; Leonard Felicetti; Javier Pérez; M. Reza Emami. 2018. "Concurrent image-based visual servoing with adaptive zooming for non-cooperative rendezvous maneuvers." Advances in Space Research 61, no. 3: 862-878.
This paper explores the viability and performance of a new algorithm for in-orbit space debris surveillance, which utilizes a network of distributed optical sensors carried onboard multiple spacecraft flying in formation. The resulting network of spacecraft is able to autonomously detect unknown debris, as well as track the existing ones, estimate their trajectories, and send the estimation results directly to the mission control centers for planning the required collision avoidance maneuvers. The proposed concept includes (a) an estimation algorithm that allows for sharing observations of common debris objects among spacecraft; (b) a coordination algorithm for the re-orientation of an ad hoc team of spacecraft to align their onboard optical sensors towards common targets; and (c) a control algorithm for the detection and tracking of the debris which uses vision-based attitude maneuvers.
Leonard Felicetti; M. Reza Emami. Spacecraft formation for debris surveillance. 2017 IEEE Aerospace Conference 2017, 1 -12.
AMA StyleLeonard Felicetti, M. Reza Emami. Spacecraft formation for debris surveillance. 2017 IEEE Aerospace Conference. 2017; ():1-12.
Chicago/Turabian StyleLeonard Felicetti; M. Reza Emami. 2017. "Spacecraft formation for debris surveillance." 2017 IEEE Aerospace Conference , no. : 1-12.
Leonard Felicetti; M. Reza Emami. Attitude coordination of multiple spacecraft for space debris surveillance. Advances in Space Research 2017, 59, 1270 -1288.
AMA StyleLeonard Felicetti, M. Reza Emami. Attitude coordination of multiple spacecraft for space debris surveillance. Advances in Space Research. 2017; 59 (5):1270-1288.
Chicago/Turabian StyleLeonard Felicetti; M. Reza Emami. 2017. "Attitude coordination of multiple spacecraft for space debris surveillance." Advances in Space Research 59, no. 5: 1270-1288.
This paper proposes a new mission concept devoted to the identification and tracking of space debris through observations made by multiple spacecraft. Specifically, a formation of spacecraft has been designed taking into account the characteristics and requirements of the utilized optical sensors as well as the constraints imposed by sun illumination and visibility conditions. The debris observations are then shared among the team of spacecraft, and processed onboard of a “hosting leader” to estimate the debris motion by means of Kalman filtering techniques. The primary contribution of this paper resides on the application of a distributed coordination architecture, which provides an autonomous and robust ability to dynamically form spacecraft teams once the target has been detected, and to dynamically build a processing network for the orbit determination of space debris. The team performance, in terms of accuracy, readiness and number of the detected objects, is discussed through numerical simulations.
Leonard Felicetti; M. Reza Emami. A multi-spacecraft formation approach to space debris surveillance. Acta Astronautica 2016, 127, 491 -504.
AMA StyleLeonard Felicetti, M. Reza Emami. A multi-spacecraft formation approach to space debris surveillance. Acta Astronautica. 2016; 127 ():491-504.
Chicago/Turabian StyleLeonard Felicetti; M. Reza Emami. 2016. "A multi-spacecraft formation approach to space debris surveillance." Acta Astronautica 127, no. : 491-504.
A variable-geometry solar sail for on-orbit altitude control is investigated. It is shown that, by adjusting the effective area of the sail at favorable times, it is possible to influence the length of the semimajor axis over an extended period of time. This solution can be implemented by adopting a spinning quasi-rhombic pyramidal solar sail that provides the heliostability needed to maintain a passive “sun-pointing” attitude and the freedom to modify the shape of the sail at any time. In particular, this paper investigates the variable-geometry concept through both theoretical and numerical analyses. Stability bounds on the sail design are calculated by means of a first-order analysis, producing conditions on the opening angles of the sail, while gravity gradient torques and solar eclipses are introduced to test the robustness of the concept. The concept targets equatorial orbits above approximately 5000 km. Numerical results characterize the expected performance, leading to (for example) an increase of 2200 km/yr for a small device at geostationary Earth orbit.
Leonard Felicetti; Matteo Ceriotti; Patrick Harkness. Attitude Stability and Altitude Control of a Variable-Geometry Earth-Orbiting Solar Sail. Journal of Guidance, Control, and Dynamics 2016, 39, 2112 -2126.
AMA StyleLeonard Felicetti, Matteo Ceriotti, Patrick Harkness. Attitude Stability and Altitude Control of a Variable-Geometry Earth-Orbiting Solar Sail. Journal of Guidance, Control, and Dynamics. 2016; 39 (9):2112-2126.
Chicago/Turabian StyleLeonard Felicetti; Matteo Ceriotti; Patrick Harkness. 2016. "Attitude Stability and Altitude Control of a Variable-Geometry Earth-Orbiting Solar Sail." Journal of Guidance, Control, and Dynamics 39, no. 9: 2112-2126.
The paper investigates some analytical and numerical aspects of the formation control exploited by means of inter-spacecraft electrostatic actions. The analysis is based on the evaluation and check of the stability issues by using a sequence of purposely defined Lyapunov functions. The same Lyapunov approach can also define a specific under-actuate control strategy for controlling selected “virtual links” of the formation. Two different selection criteria for these links are then discussed, showing the implications on the control chain. An optimal charge distribution strategy, which assigns univocally the charges to all the spacecraft starting from the charge products computed by the control, is also presented and discussed. Numerical simulations prove the suitability of the proposed approach to a formation of 4 satellites.
Leonard Felicetti; Giovanni B. Palmerini. Analytical and numerical investigations on spacecraft formation control by using electrostatic forces. Acta Astronautica 2016, 123, 455 -469.
AMA StyleLeonard Felicetti, Giovanni B. Palmerini. Analytical and numerical investigations on spacecraft formation control by using electrostatic forces. Acta Astronautica. 2016; 123 ():455-469.
Chicago/Turabian StyleLeonard Felicetti; Giovanni B. Palmerini. 2016. "Analytical and numerical investigations on spacecraft formation control by using electrostatic forces." Acta Astronautica 123, no. : 455-469.
This paper deals with the main drivers for the design of a space manipulator aimed to the removal of the final stages which remain in Low Earth Orbit after releasing their payloads. At the scope, the different phases of a debris removal mission are considered, starting from the parking orbit where the servicing spacecraft equipped with the manipulator (chaser) waits for the call on duty, encompassing the approach to the target and its grasping and finally dealing with the dismissal of the captured object. The characteristics and requirements of each phase, in terms of torques to be applied to the joints of the manipulator(s) and to the forces to be generated via thrusters at the system level, are analysed. The number of robotic arms, the number of joints of each arm, and the torque level that each joint motor should supply are mainly defined by the grasping phase and the de-orbit phase. During the grasping, the tumbling target must be tracked with a large degree of robustness, and, to this aim, a redundant manipulator must be designed, so that its workspace can be as large as possible. On the other hand, increasing the degrees of freedom of a robotic arm means higher complexity and manufacturing costs. The number of arms depends also on the final de-orbit phase, in which the powerful apogee motor of the chaser satellite is ignited to change the composite system (chaser+target) orbit. The thrust, applied on the chaser, is transferred to the target by means of the manipulator(s): it is shown that a single robotic arm could not be sufficient to withstand the high stress acting during this phase. The torques at the joints required to maintain the arms in the desired configuration end up to be very high too, and the motors – as well as in general the structural elements of the arms – should be sized according to this phase of the mission.
Leonard Felicetti; Paolo Gasbarri; Andrea Pisculli; Marco Sabatini; Giovanni B. Palmerini. Design of robotic manipulators for orbit removal of spent launchers’ stages. Acta Astronautica 2016, 119, 118 -130.
AMA StyleLeonard Felicetti, Paolo Gasbarri, Andrea Pisculli, Marco Sabatini, Giovanni B. Palmerini. Design of robotic manipulators for orbit removal of spent launchers’ stages. Acta Astronautica. 2016; 119 ():118-130.
Chicago/Turabian StyleLeonard Felicetti; Paolo Gasbarri; Andrea Pisculli; Marco Sabatini; Giovanni B. Palmerini. 2016. "Design of robotic manipulators for orbit removal of spent launchers’ stages." Acta Astronautica 119, no. : 118-130.
This paper focuses on electrostatic orbital control in formation flying by using switching strategies for charge distribution. Natural and artificial charging effects are taken into account, and limits in charging technology and in power requirements are also considered. The case of three spacecraft formation, which is intrinsically different and more difficult than the two spacecraft problem often analyzed in literature, has been investigated. A Lyapunov based global control strategy is presented and applied to perform formation acquisition and maintenance maneuvers, producing as output the required overall charge. Then, a selective and optimized charge distribution process among the satellites is discussed for avoiding charge breakdowns to surrounding plasma, for reducing the power requirements and the number of charge switches. The results of numerical simulations show the advantages and drawbacks of the selected control technique.
Leonard Felicetti; Giovanni Battista Palmerini. Three spacecraft formation control by means of electrostatic forces. Aerospace Science and Technology 2016, 48, 261 -271.
AMA StyleLeonard Felicetti, Giovanni Battista Palmerini. Three spacecraft formation control by means of electrostatic forces. Aerospace Science and Technology. 2016; 48 ():261-271.
Chicago/Turabian StyleLeonard Felicetti; Giovanni Battista Palmerini. 2016. "Three spacecraft formation control by means of electrostatic forces." Aerospace Science and Technology 48, no. : 261-271.
The coordination of the attitude among different spacecraft belonging to a multiple platform system (formation or constellation) is a basic requirement in several missions, mainly the ones involving sensors like radars or optical interferometers. It is also an open topic in research, above all as it matches the characteristics of the current trend towards interoperability and federated systems. Different approaches are possible to define and chase such a coordinated attitude. The classic control strategy is the so-called leader-follower architecture, where all spacecraft depend on ("follow") the behavior of a single master. Alternatively, the behavioral approach involves a continuous re-selection of the desired target configuration which is computed on the basis of the behavior of all the platforms. A third possibility is to define a "virtual" architecture, especially suitable with respect to the mission requirements, which is not dependent on the current kinematic state of the platforms. The paper proposes a unified treatment of these concepts by using some fundamental definitions of the consensus dynamics and cooperative control. The convergence to the targeted configuration is addressed both analytically, by using Lyapunov stability criteria, and numerically, by means of numerical simulations. The attitude requirements and constraints are highlighted and a solution for the control algorithm - involving continuous actuators on each platform - is developed. A comparative analysis of different optimal control strategies, the Linear Quadratic Regulation (LQR) and the State Dependent Riccati Equation (SDRE) - suitably modified to address the needs of coordination - is presented. The results show the general value of the proposed approach with respect to either linear or nonlinear models of the dynamics.
Leonard Felicetti; Giovanni B. Palmerini. Attitude coordination strategies in satellite constellations and formation flying. 2015 IEEE Aerospace Conference 2015, 1 -13.
AMA StyleLeonard Felicetti, Giovanni B. Palmerini. Attitude coordination strategies in satellite constellations and formation flying. 2015 IEEE Aerospace Conference. 2015; ():1-13.
Chicago/Turabian StyleLeonard Felicetti; Giovanni B. Palmerini. 2015. "Attitude coordination strategies in satellite constellations and formation flying." 2015 IEEE Aerospace Conference , no. : 1-13.
A. Pisculli; Leonard Felicetti; Paolo Gasbarri; G.B. Palmerini; Marco Sabatini. A reaction-null/Jacobian transpose control strategy with gravity gradient compensation for on-orbit space manipulators. Aerospace Science and Technology 2014, 38, 30 -40.
AMA StyleA. Pisculli, Leonard Felicetti, Paolo Gasbarri, G.B. Palmerini, Marco Sabatini. A reaction-null/Jacobian transpose control strategy with gravity gradient compensation for on-orbit space manipulators. Aerospace Science and Technology. 2014; 38 ():30-40.
Chicago/Turabian StyleA. Pisculli; Leonard Felicetti; Paolo Gasbarri; G.B. Palmerini; Marco Sabatini. 2014. "A reaction-null/Jacobian transpose control strategy with gravity gradient compensation for on-orbit space manipulators." Aerospace Science and Technology 38, no. : 30-40.
Leonard Felicetti; Fabrizio Piergentili; Fabio Santoni. Thermosphere density and wind measurements in the equatorial region using a constellation of drag balance nanospacecraft. Advances in Space Research 2014, 54, 546 -553.
AMA StyleLeonard Felicetti, Fabrizio Piergentili, Fabio Santoni. Thermosphere density and wind measurements in the equatorial region using a constellation of drag balance nanospacecraft. Advances in Space Research. 2014; 54 (3):546-553.
Chicago/Turabian StyleLeonard Felicetti; Fabrizio Piergentili; Fabio Santoni. 2014. "Thermosphere density and wind measurements in the equatorial region using a constellation of drag balance nanospacecraft." Advances in Space Research 54, no. 3: 546-553.
Leonard Felicetti; Fabio Santoni. Drag balance Cubesat attitude motion effects on in-situ thermosphere density measurements. Advances in Space Research 2014, 54, 489 -498.
AMA StyleLeonard Felicetti, Fabio Santoni. Drag balance Cubesat attitude motion effects on in-situ thermosphere density measurements. Advances in Space Research. 2014; 54 (3):489-498.
Chicago/Turabian StyleLeonard Felicetti; Fabio Santoni. 2014. "Drag balance Cubesat attitude motion effects on in-situ thermosphere density measurements." Advances in Space Research 54, no. 3: 489-498.