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VV 16: The First VEGA Rideshare Mission Flight Session VIII: Space Access Wednesday, August 5 th 2020 AVIO Sp. A- All rights reserved – subject to the restrictions of last page. Nicola Romanelli Marketing & Business Development Elisa Nardi Flight Mechanics

€ 369 M Revenues 2019 1000 Mkt Cap 65% free float Employees Prime Contractor AVIO Sp. A- All rights reserved – subject to the restrictions of last page. € 407 M Partner Supplier

What we do - European Fleet Capacity Reference Orbit 10, 5 t 1, 2 t GTO SSO, 700 km Today Ariane 5 Vega AVIO Sp. A- All rights reserved – subject to the restrictions of last page. 2, 3 t SSO, 700 km 6 t 11 t GTO 2, 8 t SSO, 700 km 2020/21 2024 Vega C Ariane 62 Ariane 64 Vega E

SSMS - Introduction SSMS (Small Spacecraft Mission Service) program • new multi-launch concept for the VEGA & VEGA-C launchers • thanks to a new modular dispenser for the Small Satellites Market VV 16 POC (Proof Of Concept) of SSMS • on VEGA 16 th flight foreseen mid August 2020 • with a complex configuration of 43 satellites (43 separated by VEGA. One of the satellites will release 10 Cubesats. Totally 53 satellites) AVIO Sp. A- All rights reserved – subject to the restrictions of last page.

Plan Presentation focused on Mission Design process • SSMS keywords • Configuration • Trajectory & Mission Design • Separation Analysis • Conclusion AVIO Sp. A- All rights reserved – subject to the restrictions of last page.

SMMS Keywords Standardization of • • Dimensions and masses of the satellites Separation systems, Interfaces Operational constraints Modularity of the dispenser • to fit a wide set of possible aggregates HEX 1, HEX 2 PLAT 1, PLAT 2, PLAT 3 FLEX 3, FLEX 4, FLEX 5 AVIO Sp. A- All rights reserved – subject to the restrictions of last page.

CONFIGURATION: SATELLITES LOCATION Microsatellites on DECK structure Cubesats on HEX structure AVIO Sp. A- All rights reserved – subject to the restrictions of last page.

CONFIGURATION: SEPARATION DEVICES Microsatellites MLB = light bands AVIO Sp. A- All rights reserved – subject to the restrictions of last page. Cubesats Dedicated Deployer

Trajectory & Mission Design: MASSES & PERFO Orbits altitudes : about 530 km VEGA Performance Map • SSO type • Multi-PL type (2 orbits) Masses • Satellites : Total mass to be separated = 759 kg • SSMS dispenser: Total mass = 540 kg • (including PL Adapter 1194 of 81 kg) AVIO Sp. A- All rights reserved – subject to the restrictions of last page. Compatibility ? OK (including de-orbiting boost for safety purpose)

Trajectory & Mission Design: OPTIMIZATION For 7 microsatellites (ATHENA, NEMO-HD, UPMsat-2, GHGsat, ION, New. Sat, ESAIL) Requirements: 2 target orbits • P/L to be grouped into subsets • VEGA allows 5 main engine ignitions 2 circular orbits Constraints (standard for VEGA) • Safety • Visibility • System (aero, mechanical, thermal, control…) AVIO Sp. A- All rights reserved – subject to the restrictions of last page. For all Cubesats

Trajectory & Mission Design: MANEUVERS & TIMELINE In addition to AVUM boosts, other degrees of freedom: • • PL release times & separation DV (norm, direction) Boosts by the thrusters of the Roll & Attitude Control System (RACS) => Longitudinal boosts to distance the PL => to reach different, though close, orbits. AVUM 1 FC 14 AVUM 2 t=2425. 83 s NEMO-HD GHGSat ATHENA & UPMSat- release 2 release PL 1 Slew Maneuver AVUM 3 AVUM 4 ION release Slew Maneuver FC 19 t=6137. 03 s PL 2 Slew Maneuver AVIO Sp. A- All rights reserved – subject to the restrictions of last page. RACS boost New. Sat & ESAIL release 1 st Cubesat NAPA-1 HL 5 release 37 Cubesats released in 160 s Dist. boost Slew Maneuver AVUM 5 deorb

Trajectory & Mission Design: MANEUVERS & TIMELINE Separation logic for the 7 Microsatellites • • • FC 14 : ATHENA released FC 14 + 1. 5 s : NEMO-HD & UPMSAT-2 released FC 14 + 3. 5 s : GHGsat released in transversal direction (specific deployer as for Cubesat) FC 14 + 510 s : RACS boost of 2. 2 m/s FC 14 + 580 s : New. Sat & ESAIL released FC 14 + 580. 08 s : ION released Separation logic of 36 Cubesats • • • Commanded by SSMS sequencer: time step of 5 s starting from FC 19 event. Timeline in Avionics (2 sequencers) not in OBSW which only defines the FC 19 event. Last separation @ 160 s after FC 19. During 160 s, attitude control kept though RACS thrusters. To keep control allows a good spacing of the PL and guarantees non collision. Longitudinal axis of the launcher oriented towards out of orbital plan => separation of all the Cubesats in the orbital plan. Attitude control kept during 160 s => design robust to last minute change of mission: if a PL is removed or exchanged, unbalance of global center of mass may occur inducing possible disturbances at separations. AVIO Sp. A- All rights reserved – subject to the restrictions of last page.

SEPARATION ANALYSIS Two horizons • Very short term clearance analysis between bodies • Short and mid-term : over 1. 5 orbits, no collision between satellites (3 dof) Clearance • based on the 3 D-geometry of the different satellites. A set of critical points are defined a priori on these satellites. • Non-collision demonstrated by Monte-Carlo simulations. AVIO Sp. A- All rights reserved – subject to the restrictions of last page.

SEPARATION ANALYSIS Mid & long-term propagation • Risk of collision displayed in orbital frame and in relative wrt launch vehicle position. • Matrices of inter-distances (with the worst values computed over a set of Monte-Carlo runs) to demonstrate the compliance in terms of non-collision requirements. • Non-contamination by RACS thrusters as well as Main Engine plume during the boost also demonstrated. AVIO Sp. A- All rights reserved – subject to the restrictions of last page. Evolution of the different Microsats & Cubesats after their separation

CONCLUSION SSMS POC VEGA, a complex mission The FLEXI-3 dispenser allows the separation of 43 satellites grouped into: • 7 Microsats separated in two subsets on a quasi-circular orbit • and then 36 Cubesats separated in a short phase of 160 s on a 2 nd quasi-circular orbit. Mission design • compliant to requirements (propellant budget, injection accuracy, probability of non-collision and noncontamination, safety rules) • Several specific problems • solved while doing the Missionization • capitalized as design rules for future SSMS activities. • Tools updated and adapted to mission complexity (e. g. non-collision between dozens of PL). Next… • SSMS POC on VEGA launcher and current GNC algorithms • For VEGA-C, GNC algorithms made more flexible • (in particular, more AVUM boosts => more orbits) to be used for enlarge the range of SSMS missions AVIO Sp. A- All rights reserved – subject to the restrictions of last page.

Future scenarios and markets ENABLED DEBRIS SERVICES REMOVAL THANK YOU Sentinel Future LEO Mega Const. FUTURE SERVICES FOR YOUR ATTENTION Refueling Relocation Iridium Out of Service Satellites AVIO Sp. A- All rights reserved – subject to the restrictions of last page. Station keeping Salvage Repair Refurbishment Assembling