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Publications (10 of 28) Show all publications
Pomares, J., Felicetti, L., Pérez, J. & Emami, R. (2018). Concurrent Image-based Visual Servoing with Adaptive Zooming for Non-cooperative Rendezvous Maneuvers. Advances in Space Research, 61(3), 862-878
Open this publication in new window or tab >>Concurrent Image-based Visual Servoing with Adaptive Zooming for Non-cooperative Rendezvous Maneuvers
2018 (English)In: Advances in Space Research, ISSN 0273-1177, E-ISSN 1879-1948, Vol. 61, no 3, p. 862-878Article in journal (Refereed) Published
Abstract [en]

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.

Place, publisher, year, edition, pages
Elsevier, 2018
National Category
Other Electrical Engineering, Electronic Engineering, Information Engineering
Research subject
Onboard space systems
Identifiers
urn:nbn:se:ltu:diva-66538 (URN)10.1016/j.asr.2017.10.054 (DOI)000424179100008 ()
Note

Validerad;2018;Nivå 2;2018-02-09 (andbra)

Available from: 2017-11-10 Created: 2017-11-10 Last updated: 2018-02-22Bibliographically approved
Felicetti, L. & Emami, R. (2018). Image-based attitude maneuvers for space debris tracking. Aerospace Science and Technology, 76, 58-71
Open this publication in new window or tab >>Image-based attitude maneuvers for space debris tracking
2018 (English)In: Aerospace Science and Technology, ISSN 1270-9638, E-ISSN 1626-3219, Vol. 76, p. 58-71Article in journal (Refereed) Published
Abstract [en]

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.

Place, publisher, year, edition, pages
Elsevier, 2018
National Category
Other Electrical Engineering, Electronic Engineering, Information Engineering
Research subject
Onboard space systems
Identifiers
urn:nbn:se:ltu:diva-67554 (URN)10.1016/j.ast.2018.02.002 (DOI)000432510200006 ()2-s2.0-85042010623 (Scopus ID)
Note

Validerad;2018;Nivå 2;2018-03-05 (svasva)

Available from: 2018-02-07 Created: 2018-02-07 Last updated: 2019-03-26Bibliographically approved
Felicetti, L., Harkness, P. & Ceriotti, M. (2017). Attitude and Orbital Dynamics of a Variable-Geometry, Spinning Solar Sail in Earth Orbit. In: : . Paper presented at 4th International Symposium on Solar Sailing (ISSS2017), Kyoto, Japan, 17-20 Jan. 2017.
Open this publication in new window or tab >>Attitude and Orbital Dynamics of a Variable-Geometry, Spinning Solar Sail in Earth Orbit
2017 (English)Conference paper, Published paper (Refereed)
Abstract [en]

At the ISSS 2013, a novel concept of variable-geometry solar sail was introduced: deployed in the shape of a three-dimensional quasi-rhombic pyramid (QRP), the sail exploited its shape and shift between center of mass and center of pressure to naturally achieve heliostability (stable sun-pointing) throughout the mission. In addition, mechanisms allowed to vary the flare angle of the four booms in opposite pairs, thus allowing to control the area exposed to the sun without the need of slew maneuvers. Using these adjustments in favorable orbital positions, it is possible to build a regular pattern of acceleration to achieve orbit raising or lowering without the need of propulsion system or attitude control. Subsequent more detailed investigations revealed that eclipses, even if lasting only a fraction of the orbit, have a substantial (and negative) impact on the heliostability effect: and even a small residual angular velocity, or disturbance torque, are enough to cause the spacecraft to tumble. In this work, we present a novel and improved concept which allows the sail to preserve its attitude not only with eclipses, but also in presence of disturbance torques such as the gravity gradient. The solution we propose is to add a moderate spin to the solar sail, combined with ring dampers. The gyroscopic stiffness due to the spin guarantees stability during the transient periods of the eclipses, while the heliostability effect, combined with the dampers, cancels any residual unwanted oscillation during the parts of the orbit exposed to the sun, and at the same time guarantees continuous sun-pointing as the apparent direction of the sun rotates throughout the year. Both theoretical and numerical analyses are performed. First, stability bounds on the sail design are calculated, obtaining conditions on the flare angles of the sail, in the different orbital regimes, to test the robustness of the concept. Then, a numerical analysis is performed to validate the study in a simulated scenario where all perturbations are considered, over extended amount of time. The concept targets equatorial orbits above approximately 5,000 km. Results show that an increase of 2,200 km per year for a small device at GEO can be achieved with a CubeSat-sized sail.

National Category
Aerospace Engineering
Research subject
Atmospheric science
Identifiers
urn:nbn:se:ltu:diva-66737 (URN)
Conference
4th International Symposium on Solar Sailing (ISSS2017), Kyoto, Japan, 17-20 Jan. 2017
Available from: 2017-11-23 Created: 2017-11-23 Last updated: 2017-12-05Bibliographically approved
Felicetti, L. & Emami, R. (2017). Attitude Coordination of Multiple Spacecraft for Space Debris Surveillance. Advances in Space Research, 59(5), 1270-1288
Open this publication in new window or tab >>Attitude Coordination of Multiple Spacecraft for Space Debris Surveillance
2017 (English)In: Advances in Space Research, ISSN 0273-1177, E-ISSN 1879-1948, Vol. 59, no 5, p. 1270-1288Article in journal (Refereed) Published
Abstract [en]

This paper discusses the attitude coordination of a formation of multiple spacecraft for space debris surveillance. Off-the-shelf optical sensors and reaction wheels, with limited field of view and control torque, respectively, are considered to be used onboard the spacecraft for performing the required attitude maneuvers to detect and track space debris. The sequence of attitude commands are planned by a proposed algorithm, which allows for a dynamic team formation, as well as performing suitable maneuvers to eventually point towards the same debris. A control scheme based on the nonlinear state dependent Riccati equation is designed and applied to the space debris surveillance mission scenario, and its performance is compared with those of the classic linear quadratic regulator and quaternion feedback proportional derivative controllers. The viability and performance of the coordination algorithm and the controllers are validated through numerical simulations.

Place, publisher, year, edition, pages
Elsevier, 2017
National Category
Other Electrical Engineering, Electronic Engineering, Information Engineering
Research subject
Onboard space systems
Identifiers
urn:nbn:se:ltu:diva-61257 (URN)10.1016/j.asr.2016.12.012 (DOI)000394066000008 ()2-s2.0-85008485258 (Scopus ID)
Note

Validerad; 2017; Nivå 2; 2017-03-06 (rokbeg)

Available from: 2016-12-27 Created: 2016-12-27 Last updated: 2018-09-13Bibliographically approved
Felicetti, L. & Emami, R. (2017). Spacecraft formation for debris surveillance. In: IEEE Aerospace Conference Proceedings: . Paper presented at IEEE Aerospace Conference, 2017, Big Sky, MT, 4-11 March 2017. Piscataway, NJ: Institute of Electrical and Electronics Engineers (IEEE), Article ID 7943750.
Open this publication in new window or tab >>Spacecraft formation for debris surveillance
2017 (English)In: IEEE Aerospace Conference Proceedings, Piscataway, NJ: Institute of Electrical and Electronics Engineers (IEEE), 2017, article id 7943750Conference paper, Published paper (Refereed)
Abstract [en]

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.

Place, publisher, year, edition, pages
Piscataway, NJ: Institute of Electrical and Electronics Engineers (IEEE), 2017
Series
IEEE Aerospace Conference Proceedings, ISSN 1095-323X
National Category
Other Electrical Engineering, Electronic Engineering, Information Engineering
Research subject
Onboard space systems
Identifiers
urn:nbn:se:ltu:diva-64209 (URN)10.1109/AERO.2017.7943750 (DOI)000405199502036 ()2-s2.0-85021208572 (Scopus ID)978-1-5090-1613-6 (ISBN)
Conference
IEEE Aerospace Conference, 2017, Big Sky, MT, 4-11 March 2017
Available from: 2017-06-19 Created: 2017-06-19 Last updated: 2017-12-15Bibliographically approved
Felicetti, L. & Emami, R. (2016). A multi-spacecraft formation approach to space debris surveillance (ed.). Acta Astronautica, 127, 491-504
Open this publication in new window or tab >>A multi-spacecraft formation approach to space debris surveillance
2016 (English)In: Acta Astronautica, ISSN 0094-5765, E-ISSN 1879-2030, Vol. 127, p. 491-504Article in journal (Refereed) Published
Abstract [en]

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.

National Category
Other Electrical Engineering, Electronic Engineering, Information Engineering
Research subject
Onboard space systems
Identifiers
urn:nbn:se:ltu:diva-10336 (URN)10.1016/j.actaastro.2016.05.040 (DOI)000383525100046 ()2-s2.0-84977260760 (Scopus ID)921b16f9-bba2-4e3c-a6ed-edadc4d6a638 (Local ID)921b16f9-bba2-4e3c-a6ed-edadc4d6a638 (Archive number)921b16f9-bba2-4e3c-a6ed-edadc4d6a638 (OAI)
Note

Validerad; 2016; Nivå 2; 20160620 (andbra)

Available from: 2016-09-29 Created: 2016-09-29 Last updated: 2018-07-10Bibliographically approved
Felicetti, L. & Palmerini, G. B. (2016). Analytical and numerical investigations on spacecraft formation control by using electrostatic forces (ed.). Paper presented at International Workshop on Satellite Constellations and Formation Flying : 08/06/2015 - 10/06/2015. Acta Astronautica, 123, 455-469
Open this publication in new window or tab >>Analytical and numerical investigations on spacecraft formation control by using electrostatic forces
2016 (English)In: Acta Astronautica, ISSN 0094-5765, E-ISSN 1879-2030, Vol. 123, p. 455-469Article in journal (Refereed) Published
Abstract [en]

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.

National Category
Other Electrical Engineering, Electronic Engineering, Information Engineering
Research subject
Onboard space systems
Identifiers
urn:nbn:se:ltu:diva-35087 (URN)10.1016/j.actaastro.2015.12.056 (DOI)000384626700049 ()2-s2.0-84981361171 (Scopus ID)97a08b22-50f7-4099-b95f-aa44837409a5 (Local ID)97a08b22-50f7-4099-b95f-aa44837409a5 (Archive number)97a08b22-50f7-4099-b95f-aa44837409a5 (OAI)
Conference
International Workshop on Satellite Constellations and Formation Flying : 08/06/2015 - 10/06/2015
Note

Validerad; 2016; Nivå 1; 20160114 (andbra); Konferensartikel i tidskrift

Available from: 2016-09-30 Created: 2016-09-30 Last updated: 2018-07-10Bibliographically approved
Felicetti, L., Ceriotti, M. & Harkness, P. (2016). Attitude Stability and Altitude Control of a Variable-Geometry Earth-Orbiting Solar Sail. Journal of Guidance Control and Dynamics, 39(9), 2112-2126
Open this publication in new window or tab >>Attitude Stability and Altitude Control of a Variable-Geometry Earth-Orbiting Solar Sail
2016 (English)In: Journal of Guidance Control and Dynamics, ISSN 0731-5090, E-ISSN 1533-3884, Vol. 39, no 9, p. 2112-2126Article in journal (Refereed) Published
Abstract [en]

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 5000km. Numerical results characterize the expected performance, leading to (for example) an increase of 2200km/yr for a small device at geostationary Earth orbit

National Category
Aerospace Engineering
Research subject
Onboard space systems
Identifiers
urn:nbn:se:ltu:diva-59680 (URN)10.2514/1.G001833 (DOI)000383261500015 ()
Note

Validerad; 2016; Nivå 2; 2016-10-12 (andbra)

Available from: 2016-10-12 Created: 2016-10-12 Last updated: 2018-07-10Bibliographically approved
Felicetti, L., Gasbarri, P., Pisculli, A., Sabatini, M. & Palmerini, G. B. (2016). Design of robotic manipulators for orbit removal of spent launchers' stages (ed.). Paper presented at International Astronautical Congress : 20/09/2014 - 03/10/2014. Acta Astronautica, 119, 118-130
Open this publication in new window or tab >>Design of robotic manipulators for orbit removal of spent launchers' stages
Show others...
2016 (English)In: Acta Astronautica, ISSN 0094-5765, E-ISSN 1879-2030, Vol. 119, p. 118-130Article in journal (Refereed) Published
Abstract [en]

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

National Category
Other Electrical Engineering, Electronic Engineering, Information Engineering
Research subject
Onboard space systems
Identifiers
urn:nbn:se:ltu:diva-28732 (URN)10.1016/j.actaastro.2015.11.012 (DOI)2a023785-2861-4132-b3f4-a40e0593c8ff (Local ID)2a023785-2861-4132-b3f4-a40e0593c8ff (Archive number)2a023785-2861-4132-b3f4-a40e0593c8ff (OAI)
Conference
International Astronautical Congress : 20/09/2014 - 03/10/2014
Note

Konferensartikel i tidskrift

Available from: 2016-09-30 Created: 2016-09-30 Last updated: 2017-11-30Bibliographically approved
Felicetti, L. & Palmerini, G. B. (2016). Three spacecraft formation control by means of electrostatic forces (ed.). Paper presented at . Aerospace Science and Technology, 48, 261-271
Open this publication in new window or tab >>Three spacecraft formation control by means of electrostatic forces
2016 (English)In: Aerospace Science and Technology, ISSN 1270-9638, E-ISSN 1626-3219, Vol. 48, p. 261-271Article in journal (Refereed) Published
Abstract [en]

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

National Category
Other Electrical Engineering, Electronic Engineering, Information Engineering
Research subject
Onboard space systems
Identifiers
urn:nbn:se:ltu:diva-3559 (URN)10.1016/j.ast.2015.11.022 (DOI)000368971200027 ()2-s2.0-84948951825 (Scopus ID)163423f4-1228-495c-9720-983110b569ed (Local ID)163423f4-1228-495c-9720-983110b569ed (Archive number)163423f4-1228-495c-9720-983110b569ed (OAI)
Note
Validerad; 2016; Nivå 2; 20151215 (andbra)Available from: 2016-09-29 Created: 2016-09-29 Last updated: 2018-07-10Bibliographically approved
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Identifiers
ORCID iD: ORCID iD iconorcid.org/0000-0001-6830-4308

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