AIDA: Asteroid Impact & Deflection Assessment – A Joint ESA-NASA Mission

Chelyabinsk Meteor on 15 February 2013

Joint ESA – NASA AIDA Team

1

AIDA Asteroid Deflection Test

Telescopes

Didymos Binary

Radar

SBAG January, 2015

• AIDA international cooperation – First test of asteroid deflection by kinetic impact

• DART kinetic impactor (NASA) • AIM rendezvous and impact monitoring (ESA)

DART

AIM

2

AIDA = AIM + DART • ESA AIM rendezvous spacecraft

– Orbiter payload to characterize Didymos dynamical system and study impact results characterisation

– Asteroid proximity operations, lander release on secondary asteroid, deep-interior analysis

– Deep-space optical communication demonstration

• NASA DART interceptor and Earth-based observing – Measure asteroid deflection to within 10% – Return high resolution images of target prior to

impact – Autonomous guidance with proportional

navigation to hit center of 150 meter target body – Leverage space-based missile technology

SBAG January, 2015

3

AIDA Relevance

• Science – Conduct a visit to a binary near-Earth asteroid – Detect possible mass transfer between primary & secondary bodies – Measure crater formation and redistribution of material – Estimate internal structure and composition

• Planetary Defense – Understand kinetic impact effects for future deflection technologies – Estimate momentum transfer by impact and by enhancement of

ejecta • Exploration

– Coordinate international deep space mission operations – Develop flight techniques and experience for small body missions

• Optical navigation and acquisition • Rendezvous • Proximity Operations

– Plan and perform detailed characterization – Resources investigation

SBAG January, 2015

4

2022 Didymos Intercept

DART trajectory remains near 1 AU from Sun, Earth distance < 0.11 AU.

DART launch energy 3.74 km2/s2

Impact velocity 6.27 km/s

Impact event in Oct, 2022 occurs under excellent Earth-based viewing conditions including radar

Co-manifest launch under study

SBAG January, 2015

DART launches Dec 20, 2021 and intercepts Didymos on Oct 1, 2022

5

AIDA Target Properties • The target is the Near-Earth Asteroid 65803

(1996 GT) Didymos: a YORP spin-up binary with an equatorial ridge on the primary

Radar image of Didymos From L. Benner, Arecibo, Nov. 2003

Binary 1999 KW4 radar model Ostro et al. 2005

2008EV5 Busch et al. 2011

Bennu NASA/NSF/Cornell/Nolan

SBAG January, 2015

6

• DART payload is an imager based on New Horizons LORRI – 20 cm telescope, 1 arc sec/px, CCD camera

• Support autonomous guiding to impact target body through center

• Determine impact point within 1% of target diameter

• Characterize pre-impact surface morphology and geology of target (goal <20 cm/px) and companion body

5/29/2012

6

DART Payload Objectives

AIM mission objectives

Secondary objectives ④ to determine the momentum transfer resulting from the impact of the DART,

by measuring the variation of the asteroid´s period, its rotation state and by imaging of the resulting impact crater. An optional extension of this primary objective is the imaging the asteroid ejecta resulting from the impact.

⑤ to characterise the asteroid deep interior structure.

Primary objectives ① Determine the binary asteroid orbital and rotation dynamics, as well

as the mass, geolophysical properties, and surface and subsurface structure;

② to carry out a Telecommunication Engineering eXperiment (TEX), a Moonlet Engineering eXperiment (MEX) deploying the MASCOT-2 asteroid lander;

③ to test inter-satellite network link with COPINS (Cubesat Opportunity Payload Intersatellite Network Sensors) and the MASCOT-2 lander.

SBAG January, 2015

AIM main elements

Technology Payload Mass

OPTEL-D (Optical terminal) 39.3 MASCOT-2 (incl. low-frequency

radar) 13

COPINS 13.2

Asteroid Research Payload Mass

Thermal Infrared Imager 3.6

Monostatic High Frequency Radar 1.7 Bistatic Low Frequency Radar

(Orbiter) 1.2

Visual Imaging Camera 2.4

AIM mission scenario

1

2

4 6

Launch 1

Departure burn 2

Deep space manoeuvre 3

Rendezvous burn

4

Co-flying / Characterisation

5

6

5

Lander deployment

7 DART impact observation

8

Post-impact characterisation 9

Launch by Soyuz from Kourou: ~22/10/2020

Arrival 29/5/2022

DART impact 6/10/2022

7

DSM: 03/01/2021

Co-flying / Characterisation

8

~35 km

~100 km

3

SBAG January, 2015

P2 Early characterization: - High-resolution images - Optical comm experiment

Close proximity Asteroid Operations: 29 May 2022 – 25 December 2022

P4 Lander phase: Deploy MASCOT2 lander

P1 Rendezvous with Didymos Transition to 35 km “P2” co-flying position.

P5 DART impact observation

35 km

~100 km

10 km P3 First detailed characterization: Thermal Infrared imaging High-frequency radar sounding of surface and shallow-subsurface

P6 Second detailed characterization: - High-frequency radar - Low-frequency radar - Crater imaging

~1 km

10 km

SBAG January, 2015

CubeSats Opportunity Payloads (COPINS)

ESA AIM ¨mothercraft¨

Intersatellite link demonstration in deep space

AO in 1st quarter 2015 SBAG January, 2015

AIM schedule ‘14 – ‘16

KO • End of February ‘15

Preliminary requirements

review •Dec ‘15

Intermediate system

requirements review

•June ‘16

Phase-A (9 months)

Phase-B1 (6 months)

2015

2016

2014

Pre-phase A (ESA CDF)

• May - Sept ‘14

AIM AO • Oct ’14 – Jan ‘15

13

DART Baseline Schedule

SBAG January, 2015

May 2015 MCR Feb 2016 SRR/CoDR Apr 2016 Instrument Phase B starts Jul 2016 Bus/ground Phase B starts

Feb 2017 PDR Jan 2018 CDR Sep 2018 SIR Apr 2019 PER Aug 2019 PSR/ORR Jan 2020 Launch

14

AIDA

Since we last met….

SBAG January, 2015

• DART Pre-phase A study efforts continue • Focus on modeling and simulation, algorithm development, AutoNav

development, and primary sensor detector trades • Continue to mature the integrated mission design: multiple launch

opportunities available to support an October 2022 intercept of the Didymos binary system

• AIM Advisory Group report on Environmental and Instrumentation

Requirements, issued April, 2014 • Participated in the ESA AIM mission engineering (CDF) study (past summer) at

ESTEC

• Multiple community interactions both in the US and Europe, including the.. • 1st International Community Workshop was held at APL October 15-17

• Formalizing the NASA-ESA partnership

• Telecon, and official NASA visit (November 17, 18) of Franco Ongaro, Head of ESA/ESTEC and Director of Technology

• Formalizing Letter of Intent to pursue Phase A/B1 in parallel

15

AIDA Next 6 months….

SBAG January, 2015

• DART will complete Pre-phase A study and transition to Phase A late Spring/early summer

• Next iteration design run in mid-March • Co-manifest launch study continues • MCR tentatively scheduled for late May 2015 • Exploring teaming with other NASA directorates (stakeholders) • Expand on community involvement and how to leverage other relevant

efforts funded by both US and European “NEO” Programs • Align joint milestone dates between DART and AIM (best effort)

• Our next AIDA international community forum will be during the Planetary

Defense Conference in April 2015

• ESA will down-select up to 3 industry system studies in late January 2015

• European payload studies and early development will start in early 2015

• ESA COPINS AO to be released Jan 2015

• Joint US payload contributions to an ESA surface package will be studied

16 SBAG January, 2015

17

• Parameter β defined as orbital momentum change divided by momentum input – Perfectly inelastic collision: β = 1 – Ejecta enhances momentum transfer, β > 1

• Assuming β = 1, the ∆v is ~0.3 mm/s for Didymos’ satellite after DART impact; period change of ~200 s (out of ~12 hours)

• Period change detectable from Earth

DART Impact Results

SBAG January, 2015

Imparted Δv, mm/s 0.3 0.4 0.5 1.52 Δ semi-major axis, m 3.75 5.00 6.25 19.01 Δ period, sec 204.72 272.9 341.37 1040.57 Δ period, % 0.48% 0.64% 0.80% 2.43% Δ eccentricity 0.00014 0.00019 0.00024 0.00072 Δ inclination, deg ≤ 0.037 ≤ 0.049 ≤ 0.062 ≤ 0.188 Δ longitude of pericenter, ῶ = Ω+ω, deg ≤ 2.01 ≤ 2.68 ≤ 3.35 ≤ 10.185