Coupling High Fidelity Body Modeling with Non- Keplerian Dynamics to Design AIM-MASCOT-2 Landing Trajectories on Didymos Binary Asteroid
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1 6 th Internatinal Cnference n Astrdynamics Tls and Techniques (ICATT) Darmstadt March 2016 Cupling High Fidelity Bdy Mdeling with Nn- Keplerian Dynamics t Design AIM-MASCOT-2 Landing Trajectries n Didyms Binary Asterid Fabi Ferrari*, Michèle Lavagna*, Ian Carnelli * Plitecnic di Milan, Department f Aerspace Science and Technlgy Eurpean Space Agency, General Study Prgram Office, ESA HQ
2 Cntent 2 Intrductin: AIM and MASCOT-2 landing Dynamical envirnment arund Didyms system Gravity mdel Estimate f dynamical perturbatins Design f MASCOT-2 ballistic descent Requirements Assumptins Escape velcities in the three-bdy system Sensitivity analyses Successful landing prbability Landing dispersin at rest Fabi Ferrari
3 Asterid Impact Missin (AIM) Didyms will transit near Earth (less than 0.1 AU) in late 2022 [ Didyms = Didymain + Didymn ] Credits: ESA AIDA - Asterid Impact & Deflectin Assessment AIM - Asterid Impact Missin (ESA) Gals: Study f binary system Deplyment f a lander (MASCOT-2) Deplyment f cubesats (COPINS) DART - Duble Asterid Redirectin Test (NASA) Gals: High velcity kinetic impact Fabi Ferrari
4 MASCOT-2 landing highlights 4 MASCOT-2 shall land n the smaller asterid (Didymn) MASCOT-2 is a passive prbe N actuatrs fr trajectry cntrl N actuatrs r devices fr anchring t the surface Extremely lw gravity field n Didymn s surface MASCOT-2 can bunce but it shall stay n the surface MASCOT-2 release pint shall be safe frm AIM spacecraft pint f view Fabi Ferrari
5 Didyms system km Credits: ESA Diameter [m] Mass [kg] Didymain e11 Didymn e9 Tw rders f magnitude lwer than 67/P C-G (Rsetta/Philae) Fabi Ferrari
6 Didyms system km Credits: ESA Diameter [m] Mass [kg] Didymain e11 Didymn e9 Fur rders f magnitude lwer than 67/P C-G (Rsetta/Philae) + Didymain s perturbatin Fabi Ferrari
7 Didyms system Gravity mdel km MASCOT-2 dynamics Three-bdy system L* 1.18 km µ 9.2 e-3 Credits: ESA T h Diameter [m] Mass [kg] Didymain e11 Didymn e9 CR3BP t mdel the mtin f the asterids center f mass Fabi Ferrari
8 Didyms system Gravity mdel 8 CR3BP t mdel the mtin f the asterids center f mass Gravity surce Didymain (sphere) + Didymn (sphere) Didymain (sphere) + Didymn (ellipsid) Didymain (plyhedrn) + Didymn (ellipsid) Dynamical mdel S1+S2 (CR3BP) S1+E2 P1+E2 S1+E2 P1+E2 Fabi Ferrari
9 Didyms system Dynamical perturbatins 9 Relevant effects at 1 km [m/s 2 ] Acceleratin due t Didyms system s gravity e-5 Acceleratin due t SRP n MASCOT-2 lander e-8 Perturbatin due t Sun s gravity (third bdy) e-11 Perturbatin due t Earth s gravity (third bdy) e-13 Nt relevant fr MASCOT-2 scenari Irregularities in Didyms gravity field are the mst relevant perturbatins N relevant differences fund between S1+E2 and P1+E2 mdeling Fabi Ferrari
10 MASCOT-2 landing design Requirements 10 MASCOT-2 shall land n the smaller asterid (Didymn) MASCOT-2 is a passive prbe N actuatrs fr trajectry cntrl N actuatrs r devices fr anchring t the surface Extremely lw gravity field n Didymn s surface MASCOT-2 can bunce but it shall stay n the surface MASCOT-2 release pint shall be safe frm AIM spacecraft pint f view Ballistic descent with n escape after buncing v aftertd < v esc Fabi Ferrari
11 Escape velcity frm Didymn s surface Theretical limits 11 Dynamical mdel v esc [cm/s] S S1+S S1+E P1+E Values t escape Didymn s SOI (r neighbrhd) It depends n latitude they depend n latitude and lngitude The escape velcity is the tuch dwn velcity fr a pure ballistic landing frm the SOI v TD v esc Minimum energy t land / escape: thrugh L1 pint Fabi Ferrari
12 Tuch-dwn velcity Mnte Carl backwards integratin 12 Energy v TD < v L1 v L1 < v TD < v L2 v TD > v L2 Minimum v td [cm/s] Thrugh L1 neck (v L1 ) Thrugh L2 neck (v L2 ) S1+S S1+E P1+E Fabi Ferrari
13 MASCOT-2 landing design Trajectry selectin 13 Requirements Ballistic descent with n escape after buncing v aftertd < v esc Safety: release far frm Didymn cnstraints the dynamics t v TD v esc Design strategy Keep v TD as lw as pssible Trajectries with lw v TD are thse passing thrugh the L1 r L2 neck with lw energy (L2 neck is cnsidered fr safer release) Maniflds assciated t L2 pint Fabi Ferrari
14 MASCOT-2 landing design Example f landing slutin 14 Release frm 200 m altitude Manifld High time f flight Nt rbust after release dispersin Fabi Ferrari
15 MASCOT-2 landing design Example f landing slutin 15 Release frm 200 m altitude Near the manifld Lw time f flight Rbust after release dispersin Fabi Ferrari
16 MASCOT-2 landing design Assumptins 16 BALLISTIC DESCENT: MASCOT-2 dispersin at release Navigatin errr Release mechanism errr 5 deg (1σ) half cne angle arund nminal release directin 0.5 cm/s (1σ) uncertainty in release velcity BOUNCING DYNAMICS: velcity after tuch dwn Directin accrding t sil inclinatin Unifrm distributin in azimuth Gaussian distributin in elevatin: 90 ± 70 deg (µ ± 3σ) Nrm f velcity dumped accrding t the restitutin cefficient η = v aftertd v befretd = = 0.54 asterid s sil lander s structure Fabi Ferrari
17 MASCOT-2 landing design Escape prbability 17 Frm release up t escape r stay n Didymn s surface Mnte Carl simulatin ( cases fr each release pint) S1+E2 mdel used (equivalent t P1+E2) Release frm 200 m altitude Release frm 250 m altitude Fabi Ferrari
18 MASCOT-2 landing design Escape prbability 18 Frm release up t escape r stay n Didymn s surface Mnte Carl simulatin ( cases fr each release pint) S1+E2 mdel used (equivalent t P1+E2) Release altitude [m] Escaped trajectries [%] After release After tuch dwn TOT Fabi Ferrari
19 MASCOT-2 landing design Landing dispersin at rest 19 Frm release up t rest n Didymn s surface: utging vertical velcity lwer than 0.5 cm/s Mnte Carl simulatin ( cases fr each release pint) S1+E2 mdel used (equivalent t P1+E2) Release altitude [m] Dispersin at rest (µ ± 3σ) Latitude [deg] Lngitude [deg] Tf [h] ± ± ± ± ± ± ± ± ± ± ± ± ± ± ± 1.35 Fabi Ferrari
![at rest (µ ± 3σ) Latitude [deg] Lngitude [deg] Tf](/docs-images/93/117970865/images/20-2.jpg "[h] 200 0.1 ± 32.9 19.7 ± 60.5 2.50 ± 1.")
20 MASCOT-2 landing design Landing dispersin at rest: release frm 200 m 20 Release altitude [m] Dispersin at rest (µ ± 3σ) Latitude [deg] Lngitude [deg] Tf [h] ± ± ± 1.21 Fabi Ferrari
![MASCOT-2 landing design Landing dispersin at rest: release frm 200 m 21 Release altitude [m] Dispersin](/docs-images/93/117970865/images/21-2.jpg "at rest (µ ± 3σ) Latitude [deg] Lngitude [deg] Tf [h] 200 0.1 ± 32.9 19.7 ± 60.5 2.50 ± 1.")
21 MASCOT-2 landing design Landing dispersin at rest: release frm 200 m 21 Release altitude [m] Dispersin at rest (µ ± 3σ) Latitude [deg] Lngitude [deg] Tf [h] ± ± ± 1.21 Fabi Ferrari
22 MASCOT-2 landing design Cnclusin 22 Summary The main perturbing actin is due t the uncertainty n Didyms/Didymn gravity field Higher successful landing prbability fr lwer release pints Landing dispersin at rest is cnfined within a certain latitude-lngitude band Gd results with current assumptins n release dispersin, sil uncertainty and restitutin cefficient Release altitude [m] Successful prbability [%] Fabi Ferrari
23 6 th Internatinal Cnference n Astrdynamics Tls and Techniques (ICATT) Darmstadt March 2016 Cupling High Fidelity Bdy Mdeling with Nn- Keplerian Dynamics t Design AIM-MASCOT-2 Landing Trajectries n Didyms Binary Asterid Fabi Ferrari*, Michèle Lavagna*, Ian Carnelli * Plitecnic di Milan, Department f Aerspace Science and Technlgy Eurpean Space Agency, General Study Prgram Office, ESA HQ
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