Alberto Fedele

University of Florida | UF

In this work, the formation flight of the CubeSat cluster RODiO (Radar for Earth Observation by synthetic aperture DIstributed on a cluster of CubeSats equipped with high-technology micro-propellers for new Operative services) with respect to a small satellite in LEO (Low Earth Orbit) has been analyzed. RODiO is an innovative mission concept funded...

In this work, the formation flight of the CubeSat cluster RODiO (Radar for Earth Observation by synthetic aperture DIstributed on a cluster of cubesats equipped with high-technology micro-propellers for new Operative services [1]) with respect to a small satellite in LEO (Low Earth Orbit) has been analyzed. RODiO is an innovative mission concept fu...

FUTURE is a Low Earth Orbit (LEO) nanosatellite mission that has recently concluded phase A, whose aim is to demonstrate the capability of autonomously determining its orbit exploiting only visual observations, without relying on ranging measurements or on the GNSS (Global Navigation Satellite System) positioning systems. Such approach represents a...

Spacecraft returning scientific samples or humans from space must be capable of surviving re-entry and landing in a desired location. Traditionally, this has been accomplished via a propulsive de-orbit burn. However, it is not always possible to mount a propulsion system on board a satellite or a capsule. In the case of small satellites deployed fr...

In this paper, relative orbit and attitude adaptive controllers are integrated to perform roto-translational maneuvers for CubeSats equipped with a Drag Maneuvering Device (DMD). The DMD enables the host CubeSat with modulation of aerodynamic forces/torques and gravity gradient torque. Adaptive controllers for independent orbital and attitude maneu...

Aerocapture technology provides a far-reaching capability for missions at destinations across the solar system, from SmallSat to Flagship class. It will enable a new class of SmallSat orbiters, allow high priority missions to carry more science payload to their destination, and open a new rapid transportation pathway to the outer solar system. Sign...

Payloads left in space at the end of life create debris. A high number of space debris surround our planet and within a few years, experts argue, it will no longer be possible to send payloads safely into space. Our study strives to demonstrate the ability to bring a payload back to Earth without the use of active propulsion system in close proximi...

This paper presents results of a study conducted for the project IPERDRONE that aims at the design and development of a small re-entry system, able to perform in-orbit operations near the International Space Station (ISS), to reenter the atmosphere, and to land safely on Earth bringing back scientific payloads/experiments intact from the ISS. The r...

The European Union H2020 EFESTO project is coordinated by DEIMOS Space with the end goals of improving the European TRL of Inflatable Heat Shields for re-entry vehicles (from 3 to 4/5) and paving the way towards further improvements (TRL 6 with a future In-Orbit Demonstrator, IOD). This paper presents the project objectives and the initial results...

WHITE PAPER FOR THE PLANETARY SCIENCE AND ASTROBIOLOGY DECADAL SURVEY, 2023 - 2032 http://surveygizmoresponseuploads.s3.amazonaws.com/fileuploads/623127/5489366/58-2db114bc7ca4334fc80b9da65549fe36_AustinAlex.pdf

White Paper for the Planetary Science Decadal Survey, 2023 -2032

Deployable aerobrakes for Earth re-entry capsules may offer many advantages in the near future, including the opportunity to recover on Earth payloads and samples from Space with reduced risks and costs with respect to conventional systems. Such capsules can be accommodated in the selected launcher in folded configuration, optimizing the available...

Deployable aerobrakes for Earth re-entry capsules may offer many advantages in the near future, including the opportunity to recover on Earth payloads and samples from Space with reduced risks and costs with respect to conventional systems. Such capsules can be accommodated in the selected launcher in folded configuration (optimizing the available...

The article deals with the aerothermodynamic and thermal analysis of two technological demonstrators suitable for research activities on deployable heatshield entry capsules. Variable geometry bodies represent a formidable way to build low ballistic coefficient entry platforms able to limit convective heat fluxes, mechanical loads, and final descen...

The European Union H2020 EFESTO project is coordinated by DEIMOS Space with the end goals of improving the TRL of Inflatable Heat Shields for re-entry vehicles (from 3 to 4/5) and paving the way towards further improvements (TRL 6 with a future In-Orbit Demonstrator). This paper presents the project objectives and provides with a general overview o...

The Space Rider Programme, previously named Pride, is an ESA programme whose objective is to define and develop an affordable reusable European space transportation system to be launched by VEGA-C, to be used as a platform for several types of payload applications. Payloads and related applications strongly drive the definition of Space Rider missi...

MINI-IRENE is the Flight Demonstrator of IRENE, a new-concept capsule with a variable geometry, originally conceived by ASI to widen the range of available platforms to retrieve payloads and/or data from low Earth orbit. The main characteristics of IRENE is the “umbrella-like“ deployable front structure that reduces the capsule ballistic coefficien...

MINI Irene is the Flight Demonstrator of IRENE, a new-concept capsule with a variable geometry, originally conceived by ASI to widen the range of available platforms to retrieve payloads and/or data from low Earth orbit. This paper, after a short introduction of the patented IRENE deployable heat shield concept and benefits, shows the ongoing activ...

The present work was carried out in the framework of the Unmanned Space Vehicles (USV) program, executed by the Italian Aerospace Research Centre (CIRA), with the aim of developing innovative GN&C technologies focused on a complete autonomous atmospheric reentry, including hypersonic flight and landing. In particular the investigation of advanced c...

This paper presents the results obtained by system identification from flight data of an experimental ultra-light aircraft called FLARE (Flying Laboratory for Aeronautical Research). After a brief introduction, the description of the experimental ultra-light aircraft subjected to the identification process is provided. Then the simulation model, id...

This paper presents the results obtained by system identification from flight data of an experimental ultra-light aircraft called FLARE (Flying Laboratory for Aeronautical Research). After a brief introduction, the description of the experimental ultra-light aircraft subjected to the identification process is provided. Then the simulation model, id...