AVIOAR: Avionics for Miura (PLD) Launchers. Project manager responsible for the development, integration and validation of the overall avionics system for Miura-1 micro launcher, integrated and operated by PLD space.
Space-Rider: Responsible for the phase A/B1 of the GMV activities related with RendezVous GNC, Re-Entry Navigation and the supporting Mission Analysis.
NGTATB: Next Generation Transportation Avionics Test bed This pro-ject (under ESA/ESTEC contract) aims at instantiating at ESTEC avionics lab two scenarios: Micro Launcher Ascent phase and Active Debris Removal. The project envisages the fully chain for Flight Software Verification and Validation starting with the Functional Engineering Simulator (FES) up to Hard-ware in the Loop (HWIL) validation.
MSRN: Multispectral Sensor for Relative Navigation. This project (under ESA/ESTEC contract) is fully devoted to analysis the performance of a Multispectral sensor for relative navigation. This sensor shall be able to detect and process several spectra signals: Visible Thermal Infrared and Near Infrared.
MVFLAU: Feasibility Study of In-Flight Model Validation and Performance Analysis of Launchers GNC. This project (under ESA/ESTEC con-tract) aims at developing a post flight analysis tool to determine several VEGA uncertainty parameters related to different launcher subsystems: Propulsion, Structural Flexible modes, Aerodynamics load, GNC parameters.
VEMIPRO: Missionization Process for Multi-mission Vehicles. This project (under ESA/ESTEC contract) is dedicated to define the missionization process of a launcher to avoid complex qualification activities at each launch. Guidelines for Flight Software Architecture and Mission Repository database prototyping are the main objectives of this contract
SPARTAN-FP7. Space Exploration Research For Throatable Advanced Engine. Responsible for the GMV’s team working on GNC subsystem design, HW procurement, breadboarding and testing. Responsible for the navigation algorithms design and mechanization. Support to the G&C algorithms definition and mechanization.
VEGA Program: FPSA. Flight Program Software For Vega Launcher (2nd Source Development). Responsible for the whole GMV collocated team at ELV premises. Also responsible of several technical activities mainly related with Guidance and Navigation, FDIR, and Flight Manager.
AIE4T: Autonomous Inertia Estimation For Transportation. This pro-ject transfers to the automotive sector the space technology related with Mass, Inertia and CoG identification based on inertial sensor.
ROBEDL. Robust Entry, Descent and Landing Guidance and Control Techniques. This project aims at designing and implementing a whole GNC system for Entry Descent and Landing. Two different scenarios are considered for precise landing: Moon (Lunar Lander) and Mars (Mars Sample Return mission). GMV is responsible for the design implementation and validation of the navigation function.
VVAF. Worst Case and Safety Analysis Tools for Autonomous Rendezvous System. Four different verification and validation frameworks are designed and implemented within this project. They make use of several advanced concept in robust control (mu-analysis and LFT) and hybrid optimisation techniques for the identification of a worst case scenario
HIGHLIFT. Prototyping and validation of Guidance and Control re-entry algorithms for an high Lift-Over-Drag vehicle. The analysis of re-entry from lunar return trajectories (supercircular re-entry) represents a key feature
HARVD. Support for the GNC validation for an integrated multirange rendezvous system.
GNCDERIS3. Responsible for the identification and definition of the guidance algorithms for RendezVous into elliptical orbit. Algorithms have been implemented into the Guidance Analysis TOol (GATO)
MOONLIB: Analysis of Lagrangian Trajectories in the Earth-Moon System. Responsible for the analysis and definition of transfer strategy to the Earth Moon lagrangian points orbits (Lissajous and Halo).
GNCO: Development of GNC algorithms for Rendezvous and Formation Flying in Non-Circular orbits. In charge of the scenario definition and guidance algorithms development for Rendezvous in Mars elliptical orbit and Formation Flying in Earth high elliptical orbit (Proba-3 mission).
AASTR: Analysis of Transportation Architecture for European Space Exploration. Responsible for the Mission Analysis concerning transfer trajectories from LEO to Lagrangian Orbit in the Earth-Moon (EML) system and back and EML to Lunar Low Orbit and back
HARVD: Integrated Multi-Range RendezVous Control System. In charge of the definition, design and implementation of the “Guidance Expert” within the vehicle GNC system
MOONTWINS: Vision Based Hazard Avoidance Experiment, within MSR Additional Pre-Cursor Mission Pre-Phase A. Providing support to the prime contractor for the Hazard Avoidance function definition for the Moon landing scenario.
FLPP: Future Launcher Preparatory Programme. In charge of developing a tool for the generation of guess values for the Hopper vehicle ascent trajectory optimization.
VBRNAV: Visual Based Navigation Techniques Framework. Responsible for the guidance algorithms trade-off, testing and implementation for the Rendezvous and Hazard Avoidance mission scenarios. Responsible for the whole integration of the Rendezvous Tool (RVDT)
ATV Evolution. Responsible for the assessment of the ascent trajectory of a composite vehicle based on Ariane5 and a CTV (Crew Transportation Vehicle) derived by the ATV (Automated Transfer Vehicle). In charge of both technical and management aspects.
WALES Mission Analysis and Operations. Responsible for the mission analy-sis and operations assessment for WALES earth observation mission. Managerial and technical issues have been covered.
GNCDERIS-2 GNC Development Environment and Rendezvous with Incapacitated Spacecraft. Responsible for the design, development and testing of a Guidance Analysis Tool (GATO)
SMART-II Mission Definition Study. Responsible for the overall orbital/transfer analysis. In charge of developing dedicated software programs for the transfer trajectories computation to both Lissajous-Halo orbits and Heliocentric Earth Trailing orbits.
GNCDERIS-1 GNC Development Environment and Rendezvous with Incapacitated Spacecraft In charge of the mission definition related to the launchers ascent scenario. Software requirements/specifications were also derived from the previous activity.
ARIESC-B: Ariane5 System Study: 3DoF Trajectory and Eclipse Study. Responsible for the ascent trajectory optimization of the new Ariane5-ESCB version. SARATO, a dedicated trajectory optimization tool, was developed during this study
SOGAGE: Study on GPS at GTO Experiment. Responsible for the visibility analysis of the GPS constellation from a spacecraft into a GTO orbit
