General Information

Reference Information

Redirect & Explore Select

Image Develop Capabilities

NASA Asteroid

Redirect Mission Identify

General Information - Asteroid Strategy and Mission Concept

Map of Cis-Lunar Space

38,200 miles 38,200 miles

248,500 miles

22,400 miles

DRO

Credit: NASA

Strategy In April 2010, President Barack Obama announced a human mission to an asteroid. The

budget leverages NASA’s human and robotic activities for the mission and also accelerates

efforts to address potentially hazardous asteroids:

To protect our planet.

To advance exploration capabilities and technologies for human space flight.

To learn how to best utilize space resources.

- The FY14 budget aligns relevant portions of NASA’s science, space technology, and human

exploration capabilities to plan for the mission.

Concept Capture and redirect a 16.4-32.8 ft (with

45.9 ft maximum dimension) up to

2.2 million lbs (1000 metric ton) near Earth

asteroid in a DRO in trans-lunar space.

Enable astronaut missions to the

asteroid as early as 2021.

Map Legend LEO - Low Earth orbit

MEO - Medium Earth orbit

HEO - High Earth orbit

GEO - Geosynchronous Earth orbit

LLO - Lunar low orbit

DRO - Distant Retrograde Orbit

L1 & L2 - Lagrange point 1 & 2

Asteroid Mission Overview

Legend:

LGA - Lunar Gravity Assist

SLS - Space Launch System S/A - Solar Array

SEP - Solar Electric Propulsion

DRO - Distant Retrograde Orbit

Credit: NASA

2) Separation & S/A Deployment

2) Separation & S/A Deployment

Credit: NASA

Asteroid Mission Preliminary Schedule Credit: NASA

Legend:

SST - Space Surveillance Telescope

PS-2 - Panoramic Survey Telescope

and Response System

SLS - Space Launch System

GEO - Geostationary Earth Orbit

EM-1 & EM-2 - Exploration Mission 1 and 2

Capabilities Required for First Steps to Destinations

The capabilities required for the first steps to Mars and other destinations as well as

the International Space Station (ISS) and Asteroid Redirect Mission are shown.

Credit: NASA

2013 Mission Formulation Review (MFR)

The MFR results were based on or enabled by:

The Asteroid Redirect Mission Feasibility Study, April 2, 2013, which was in turn

based on previous studies (e.g., Keck Institute for Space Studies, April 2, 2012, KISS);

NASA investments in asteroid observation, low thrust mission tools/design, solar

electric propulsion technology and experience from various Science Mission

Directorate and Human Exploration and Operations Mission Directorate missions.

The MFR reviewed the results of the three reference mission concept studies:

1) Identifying candidate asteroid targets for the reference mission;

2) Conducting a feasibility assessment of robotic redirection of a small near Earth

asteroid (NEA);

3) Conducting an assessment of the astronaut exploration and sampling of the asteroid

using the Orion.

The MFR also reviewed three high-level trade studies to examine alternatives (e.g.

shorter studies than the reference mission):

1) Alternative approach to the robotic mission;

2) Demonstrate planetary defense and retrieve boulder(s) from a large NEA (potentially

hazardous size);

3) Alternative Robotic Mission System trade studies included:  

-- Capture System;

-- Solar Electric Propulsion (SEP).

The MFR determined the Asteroid Redirect Mission is technically and

programmatically feasible within the constrained budget environment during the

mission years.

Identify - NASA Selects an Asteroid

Credit: NASA NASA must first identify a suitable

asteroid target. The ideal space rock is

one that is small, 16.4-32.8 ft with a

45.9 ft maximum dimension, and close

to Earth. The size of the asteroid is

important. If something were to go

wrong, this asteroid would be small

enough to burn up before it enters

Earth's atmosphere.

Ground and space based Near Earth

Asteroid target detection,

characterization and selection will be

used. The majority of asteroids fall into three categories:

C-type (carbonaceous) includes more than 75 percent of known asteroids. Very dark with an

albedo of 0.03-0.09. Composition is thought to be similar to the Sun, depleted in hydrogen,

helium, and other volatiles. C-types inhabit the main asteroid belt's outer regions. The main

asteroid belt is the region of the Solar System located roughly between the orbits of Mars and

Jupiter.

S-type (silicaceous) accounts for about 17 percent of known asteroids. Relatively bright with

an albedo of 0.10-0.22. Composition is metallic iron mixed with iron- and magnesium-silicates.

S-types dominate the inner main asteroid belt.

M-type (metallic) includes many of the rest of the known asteroids. Relatively bright with an

albedo of 0.10-0.18. Composition is apparently dominated by metallic iron. M-types inhabit the

main asteroid belt's middle region.

C-Type Asteroid Desired as the Target A small carbonaceous C-Type

asteroid with hydrated minerals is

desired, but not required, because:

Asteroids of this type and size are

known to be too weak to survive

entry through the Earth’s

atmosphere, even if it did approach

the Earth it would break up and

volatilize in the atmosphere.

- The chemical and physical

properties of these asteroids are well

understood and benign.

-- They have a very low crushing

strength and high content of

desirable volatiles.

Carbonaceous asteroids are the

most compositionally diverse

asteroids.

A carbonaceous C-type asteroid may contain volatiles (water carbon-rich compounds), metals

(iron, nickel, and cobalt), and silicate residue (similar to the average lunar surface material).

The above chart shows what may be the composition in tons (T) of a 500 ton (one million

pound) C-type asteroid.

Other Materials

~2% (~10 T)

Water

~20 %

(~10 T)

Carbon-Rich

Compounds

~20 %

(~10 T) Iron

16.6 %

(83 T)

Silicate

Residue

40 %

(200 T)

Cobalt

0.2% (1 T)

Nickel

1.2% (6 T)

Credit: Keck Institute for

Space Studies

NEO Target Detection and Characterization Need to identify Near Earth Object (NEO) targets that meet:

Trajectory

Size

Spin rate

Composition

NEO search programs:

Currently, most NEO discoveries are made by:

- Catalina Sky Survey (60%)

-- Catalina Sky Survey searches for potentially hazardous NEOs.

- Panoramic Survey Telescope and Rapid Response System-1 (30%)

-- Pan-STARRS-1 surveys celestial objects including NEOs.

- Lincoln Near-Earth Asteroid Research (3%)

-- LINEAR conducts systematic discovery and tracking of NEOs.

NEO radar observation:

Radar provides size/shape, high precision range/orbit data, spin

rate, surface density and roughness.

Sites include Goldstone Observatory, CA and Arecibo Observatory,

Puerto Rico.

NEO infrared characterization includes:

Spitzer Space Telescope - An infrared space-based observatory

launched in 2003, formerly the Space Infrared Telescope Facility

- Orbits the Sun about 109 million miles from Earth

- Provides NEO thermal signatures and albedo/sizes

Enhancements and new surveys can be online in the next two years.

Some enhancements will require additional funding.

Spitzer Telescope

Pan-STARRS-1

Catalina Sky Survey Credit: U of Arizona

Credit: U of Hawaii

Credit: NASA

2013 MFR Reference Mission Asteroid Selected

The table provides the status of the 2013 Mission Formulation Review (MFR) candidate

asteroid targets with detailed mission design analysis:

2011 MD and 2008 HU4 need further characterization;

2009 BD and 2013 EC20 are well enough understood to be valid candidate targets:

- 2013 EC20 launch is too early and likely too small to be certified;

- 2009 BD is a “valid candidate target” with an estimated size of 13.1-26.2 ft, maximum

returnable mass of 1,300,727 lbs, and a velocity of 3,937 ft/sec.

-- This candidate target is low risk for capture and detumble/despin;

-- Possible certification for selection pending Spitzer observations in January 2014.

Choosing a mission target early will reduce concerns about mission readiness and reduce

overall mission risk and cost.

Credit: NASA

period

Redirect - Asteroid Capture and Return Spacecraft Launch

The asteroid redirect and explore sequence

is based on the Asteroid Redirect Initiative

animation and the April 2, 2012 Asteroid

Retrieval Feasibility Study, Keck Institute for

Space Studies.

Initial plans will launch the Asteroid Capture

and Return (ACR) spacecraft to low Earth

orbit on an Atlas V 551-class rocket as early

as 2017.

The Atlas V 551-class rocket is shown

launching the Juno spacecraft August 5,

2011 toward Jupiter from Space Launch

Complex-41 at the Cape Canaveral Air

Force Station, FL. The 8,000 lbs Juno

spacecraft will take five years to reach

Jupiter on a mission to understand the its

origin and evolution.

The Juno 16 ft diameter payload fairing was

shorter in length than the medium fairing

required by the ACR spacecraft.

Credit: NASA and United Launch Alliance

Select Image

for Animation

ACR Spacecraft Cruises to Asteroid using Solar Electric Propulsion

Solar Array

Panels (2) Spacecraft Bus

Capture Bag

Cover

Communications

Antenna

The Asteroid Capture and Return (ACR) spacecraft cruise configuration concept is dominated

by two 35 ft diameter foldable solar array panels.

The panels generate at least 40 kilowatt electrical of power for the electric propulsion system

consisting of five Hall thrusters with 2-axis gimbals.

- The Hall thrusters are located on the aft end of the spacecraft bus. The Hall thrusters’ xenon

propellant is located in tanks inside the spacecraft bus.

The asteroid capture bag is stowed inside the cover on the front of the spacecraft bus.

A suite of instruments is used to track and characterize the asteroid.

- The instruments are located on the forward end of the spacecraft bus.

- A hole in the capture bag cover provides a field-of-view for the instruments.

A communications antenna is mounted to the spacecraft bus.

Credit: NASA

Spacecraft Capture Bag Begins Deployment Credit: NASA

Since the asteroid is only 23-32 ft wide, the spacecraft would likely need to implement a search

to encounter the target.

The asteroid should be visible from a distance of 62,000 to 124,000 miles.

During the months prior to rendezvous, images and range measurements would determine the

asteroid’s position.

- Preliminary information for further approach and close-up characterization would also be

collected.

After the stowed capture bag’s protective cover is jettisoned, the bag would start to deploy.

The capture bag conceptual mechanisms includes inflatable deployable arms, a high-strength

bag assembly, and cinching cables.

Spacecraft with Capture Bag Fully Deployed Approaches Asteroid

Credit: NASA

When the capture bag is inflated and rigidized, four or more arms connected by two or more

inflated circumferential hoops provide the compressive strength to hold the bag open.

The bag would be roughly 50 ft in diameter by 33 ft long.

- The capture mechanism concept could accommodate a wide range of uncertainty in the

shape and strength of the asteroid.

The capture process must consider a tumbling, non-cooperative object.

Spacecraft Rendezvous with Asteroid

Credit: NASA

In the far-approach phase, the spacecraft would approach and loiter in the vicinity of the

asteroid.

The range to the target may be a mile at this point.

In the middle-approach phase, the spacecraft would be brought to within about 600 ft of the

target and parked there for an extended period of time.

A radar altimeter should be able to be used during this phase to maintain station-keeping.

Full characterization of the asteroid would be done at distances from 0.6 mile to 300 ft using

a suite of instruments including:

- A spectrometer would be considered for measuring the surface composition.

- A 1-2 Hertz frame rate camera could be used for resolving the spin state.

Spacecraft Matches Asteroid Rotation

Credit: NASA

Sometime after the spin state has been identified, the spacecraft would approach the asteroid

by following a series of closure steps consisting of several descent-station keeping cycles. The

view above is looking at the asteroid from within the capture bag.

The guidance subsystem would use radar-altimeter aided relative position estimates to plan

and execute these trajectories.

The final station-keeping location may be tens of yards from the asteroid center.

The spacecraft would then match the surface velocity and primary spin state of the asteroid

while maintaining position at the final station-keeping location.

Capture Bag Starts to Trap Asteroid

Credit: NASA

During capture, the asteroid would be positioned inside the capture bag and there would only

be a small residual relative velocity between the asteroid surface and the capture bag.

Cameras on the solar array supports would be used to verify proper capture bag deployment

and subsequently to aid in the asteroid capture.

A ring would be between the capture bag and the forward end of the spacecraft to impart

forces on the asteroid through the bag.

Capture Bag Starts to Secure Asteroid to Spacecraft

Credit: NASA

To capture the asteroid, multiple "draw strings" would cinch-close the opening of the bag and

also cinch-tight against the asteroid.

Due to the residual velocity between the asteroid and the spacecraft, some “impact” is

expected when the asteroid is captured.

- Since the asteroid would be much more massive than the spacecraft, it is perhaps better to

think of this as the asteroid capturing the spacecraft.

The tightly-cinched bag containing the asteroid would be drawn up against the ring that

constrains its position and attitude so that its center-of-mass is controlled, and forces and

torques could be applied by the spacecraft during transportation to the Moon.

Spacecraft Propels Secured Asteroid to Cis-Lunar Space

Credit: NASA

Reaction Control

Thrusters Pod (4)

Once the spacecraft and asteroid are tightly secured together, the spacecraft would de-tumble

the combination using four reaction control system thruster pods mounted to the spacecraft.

The four thruster pods would control the attitude when the electric propulsion system (EPS) is

not operating.

The EPS would then transport the spacecraft and asteroid combination to cis-lunar space

(between the Earth and Moon).

The image above shows the combination cruising toward cis-lunar space using the EPS.

- Thrusting with the EPS would be the normal operating mode during the mission.

- Attitude control during EPS thrusting would be provided by gimbaling the Hall thrusters.

Explore - Asteroid Mission Crew Launched

Credit: NASA

After the ACR spacecraft robotically captures the asteroid, and the combination parks in cis-

lunar space, NASA plans to send at least two astronauts to the asteroid to investigate and

collect samples as early as 2021. This would be the first crewed flight of the Orion Multi-

Purpose Crew Vehicle. Orion is shown being launched by the Space Launch System from

Kennedy Space Center, FL.

Orion Crew Begins Journey to Captured Asteroid Credit: NASA

Service

Module

Crew

Module

Following the separation of Orion from the Interim Cryogenic Propulsion Stage, the vehicle

starts to cruise to the ACR spacecraft/asteroid combination parked in cis-lunar space.

Orion will serve as the primary crew vehicle for missions beyond low Earth orbit (LEO).

- It is capable of conducting regular in-space operations (rendezvous, docking, extravehicular

activity) in conjunction with missions beyond LEO and Orion consists of:

-- Crew Module - the 16.5 ft diameter by 10.83 ft long transportation capsule provides a safe

habitat for the crew, storage for consumables and research instruments, and serves as the

docking port for crew transfer.

--- The crew module is the only part of Orion that returns to Earth.

-- Service Module - supports the crew module from launch through separation prior to re-entry

providing propulsion capability for orbital transfer, attitude control, and high altitude ascent

aborts as well as consumables needed to maintain a habitable environment.

Following the separation of Orion from the Interim Cryogenic Propulsion Stage, the vehicle

starts its cruise, moves around the Moon, and then begins its rendezvous maneuvers with the

ACR spacecraft/asteroid combination parked in high lunar orbit. Orion completes the

rendezvous with the combination where the path changes from red to green.

Orion Crew Starts Rendezvous with ACR Spacecraft/Asteroid

Orion

ACR Spacecraft/

Asteroid

Moon

Orion’s Cruise

Path from Earth

High Lunar

Orbit

Credit NASA

Orion’s Robotic Arm Grapples ACR Spacecraft

Credit: NASA

When Orion has approached within a few yards of the ACR spacecraft/asteroid combination,

the astronauts begin the docking operations.

Orion maneuvers until its forward end faces the aft end of the ACR spacecraft and the

centers of the two vehicles coincide.

Orion’s robotic arm is released from stowage and it’s end effector secures the ACR

spacecraft’s grapple fixture completing docking.

- The above shows a view from Orion looking at the aft end of the ACR spacecraft prior to the

robotic arm end effector attaching to the ACR spacecraft’s grapple fixture.

-- The green text indicates navigation (left) and robotic arm status to the crew.

-- Three of the ACR spacecraft’s Hall thruster/gimbals are shown centered on the aft end.

-- The capture bag/asteroid can be seen to the right and upper left of the spacecraft’s aft end.

-- One of the four reaction control thrusters pods can be seen below the grapple fixture.

Orion Crew Prepare to Explore Asteroid

After docking Orion to the ACR spacecraft/asteroid combination, the astronauts prepare to

spacewalk from the Crew Module to the aft end of the capture bag to investigate the asteroid.

The NASA Extreme Environment Mission Operations (NEEMO) missions in 2011 and 2012

simulated several challenges the crew will face when visiting an asteroid including how to move

around its surface and how to collect samples.

NASA has also simulated an asteroid mission as part of its 2012 Research and Technology

Studies ground test at Johnson Space Center, TX.

- During the simulation, a team evaluated how astronauts might do a spacewalk on an asteroid

and accomplish other goals.

Credit: NASA

Two Astronauts Spacewalk from Orion to ACR Spacecraft

After exiting Orion’s side hatch and installing a telescoping mobility aid, an astronaut is shown

moving to the ACR spacecraft using the aid as a handrail. Another astronaut, inside Orion, is

observing and will also use the aid to move to the spacecraft. A sample container is tethered to

Orion.

The first extravehicular activity (EVA) is initially planned for the day after Orion docks to the

ACR spacecraft/asteroid combination and a second EVA is planned for the third day after

docking.

Credit: NASA

Sample

Container

Asteroid Target Exploration and Characterization

Credit: NASA

After reaching the aft end of the capture bag, installing a foot restraint, and opening the bag,

the astronauts start to explore the asteroid.

The astronaut, restrained by the foot restraint (left), is photographing the asteroid.

The other astronaut is handling a sample container.

The immediate science goals of the mission are to understand the physical and chemical

history of the asteroid.

- Certain classical analytical procedures, such as assays for the content of a wide variety of

organic constituents, could easily be done on small samples (about one pound would qualify as

a “huge” sample).

Astronauts Stow Asteroid Samples in Orion

Credit: NASA

Upon completion of the asteroid exploration, the astronauts return to Orion with the sample

containers and other equipment used on the EVA. After passing the containers and equipment

through the side hatch, they would be stowed for the trip back to Earth.

Orion Releases ACR Spacecraft with Asteroid

Credit: NASA

Orion’s robotic arm releases the ACR spacecraft/asteroid combination after 5 days of

exploration.

- The astronauts performed two spacewalks on two separate days investigating the asteroid.

- Orion will now begin the journey back by first looping around the Moon and then returning to

Earth in 6 days after leaving the combination.

The combination will continue to orbit the Moon to enable further exploration of the asteroid.

- The electric propulsion system xenon propellant resupply or an additional propulsion module

may be necessary to maintain station-keeping of the combination in lunar orbit.

Orion Crew Separates from Service Module for Re-Entry

Credit: NASA

After the Orion service module (SM) separates from the crew module (CM), the CM enters the

atmosphere at a speed over 20,000 miles per hour. The SM will enter the atmosphere and burn

up.

Orion Crew Returns

Credit: NASA

The Orion crew module (CM) approaches splashdown in the Pacific Ocean prior to the end of

the 22 day asteroid retrieval and utilization mission. After returning to Earth, the CM will be

tethered and pulled into the well deck of a Navy ship for its trip back to dry land in Long Beach,

CA.

MFR Asteroid Redirect Robotic Vehicle (ARRV) Concepts

The Mission Formulation Review (MFR) developed two ARRV configuration concepts:

1) Roll Out Solar Array (ROSA) Configuration - features an ARRV with a flexible blanket solar

array (SA) developed by Deployable Space Systems.

2) MegaFlex Configuration - has an ARRV with an accordion fanfold flexible blanket SA built

by ATK Space Systems.

1) ROSA

(Stowed)

2) MegaFlex

(Stowed)

1) ROSA

(Deployed)

2) MegaFlex

(Deployed)

Credit: NASA

ARRV configuration concepts based

on Space Technology Mission

Directorate (STMD) SA development.

MFR ARRV Baseline Concept

Credit: NASA

The MFR ARRV baseline concept is

comprised of:

Capture Mechanism - captures a

wide range of spinning/tumbling

asteroids.

Mission Module - flight heritage deep

space avionics packaged in modules.

Solar Electric Propulsion (SEP)

Module includes:

- Ion Propulsion - 4 Hall thrusters with

gimbals fueled by 22,046 lbs of xenon

in 8 seamless tanks, 50 kilowatt solar

arrays with solar array drives, and

power management and distribution

system;

- Mechanical & Structure -

conventional construction;

- Thermal Control - conventional cold

plates with heat-pipe radiators;

- Reaction Control - conventional

hydrazine monopropellant system.

Launch Adapter - transition structure

mounting the ARRV to the launch

vehicle (Atlas V, SLS or Falcon H).

MFR ARRV Capture Mechanism Concept

Credit: NASA

The 49 ft diameter fabric capture bag

consists of a cylindrical barrel section

and conical section attached to the

spacecraft, and includes:

An inflatable exoskeleton that deploys

the bag after arrival at the asteroid;

Inflatable "stack of torroids" at the

base of the cone forms a passive

cushion between the asteroid and the

spacecraft;

Circumferential cinch winches close

the diaphragm at the top of the

cylindrical section confining the asteroid

after the capture bag deflates;

Air bags quickly immobilize the

capture bag and asteroid at a very low

contact pressure;

Axial cinch winches control motion, re-

track bag, and position asteroid center-

of-mass.

The capture mechanism limits the

forces on the ARRV solar arrays from

the spacecraft/asteroid combination

rotational motions.

Air Bags

ARRV

Spacecraft

MFR Capture Sequence and Capture Testbed

The asteroid capture sequence is initiated when the spacecraft

approaches and matches the asteroid spin rate and continues:

The top diaphragm is closed after the asteroid is centered in the

capture bag;

At the moment the asteroid spin rate is matched, the air bags

inside the capture bag inflate limiting the loads on the asteroid

surface and achieving a controlled capture;

The asteroid is cinched tightly to the spacecraft while the capture

bag is venting.

The initial one-eighth scale capture testbed (right) has an inflatable

exoskeleton with winches suspended from a gantry over the

asteroid.

- A robot arm, attached to the asteroid, can spin and tumble it.

Credit: NASA

Asteroid Redirect Crewed Mission MFR Summary

The crewed mission is technically feasible.

The design accommodates predicted Orion Exploration Mission-2 (EM-2) performance with

the inclusion of mission kits for: rendezvous and docking, extravehicular activity (EVA), and

asteroid sample curation.

There are no significant changes to the Orion and Space Launch System requirements.

The crewed mission cost and schedule are feasible.

Mission risks are mitigated with the appropriate flight testing including:

- Employing EM-1 and 2 flight test strategy;

- Leveraging the International Space Station as an exploration test bed;

- Using the prior space shuttle flight test STORRM (Sensor Test for Orion Relative Navigation

Risk Mitigation) rendezvous and docking sensors.

-- STORRM successfully demonstrated new technology to make rendezvous and docking

easier and safer.

Credit: NASA

Orion/Asteroid Redirect Robotic Vehicle

(ARRV) concept rendezvous and

docking system, and EVA tools revised.

Orion

ARRV with

Asteroid

MFR Crewed Mission Trajectory & Schedule

Legend:

TLI - Trans-Lunar Injection

DRO - Distant Retrograde Orbit

ARV - Asteroid Redirect Robotic Vehicle

MECO - Main Engine Cut Off

EI - Entry Interface

EVA - Extravehicular Activity

Credit: NASA

Mission duration and timing of specific events

will vary slightly based on the launch date.

I

MFR Crewed Mission ARRV Rendezvous and Docking

Legend:

ARRV - Asteroid Redirect Robotic Vehicle

IDSS - International Docking System Standard LED - Light Emitting Diode

LIDAR - Light Detection and Ranging

Credit: NASA

• The minimum ARRV hardware to accommodate Orion rendezvous and docking was identified

using the International Docking System Standard.

MFR Rendezvous and Docking Mission Kits

• is

• is

Credit: NASA

The Relative Navigation Sensor Kit, mounted to the Orion hatch, is the primary navigation

instrument used by the spacecraft during rendezvous, proximity operations, and docking.

MFR Crewed Mission ARRV EVA Accommodations

Legend:

ARRV & ARV - Asteroid Redirect Robotic Vehicle

EVA - Extravehicular Activity

Credit: NASA

EVA Translation Booms

• Translation booms for asteroid EVA

• Tool box stores 187 lbs tools

MFR Suit & EVA Mission Kits

Legend:

AES - Advanced Exploration Systems

EVA - Extravehicular Activity

ISS - International Space Station

NBL - Neutral Buoyancy Laboratory

PLSS - Portable Life Support System

Assumes Government Furnished Equipment for EVA support kits

Four kits were identified to enable Orion capsule-based EVA capability

Credit: NASA

MACES Capsule-Based EVA Development Plan

Legend:

AES - Advanced Exploration Systems

ISS - International Space Station

NBL - Neutral Buoyancy Laboratory

Credit: NASA

MACES - Modified Advanced Crew Escape Suit is an upgraded version of the Advanced Crew Escape Suit

that astronauts donned for the launch and entry phases of shuttle operations.

Leverages existing AES, Orion and ISS investments

NASA Future Activities 2014 Major Activities (as of April 10, 2013)

The Science Mission Directorate’s Planetary Science Program plans to:

- Implement the systematic focus on candidate targets using ground assets;

- Begin the study of a space-based observation platform.

The Space Technology Mission Directorate plans to:

- Accelerate the development of a demonstration of a high power solar electric propulsion

system including:

-- Begin the design and test of a large-scale solar electric array leveraging investment in the

ground demonstration of large arrays that was initiated in 2012;

-- Design and build engineering units of the high power electronics and ion thruster engines;

-- Design a large quantity xenon propellant tank.

- Engage academic and industry for ideas and concepts regarding asteroid capture,

characterization, sampling, and resource utilization.

Human Exploration and Operations Mission Directorate’s Advanced Exploration Systems

plans to:

- Begin the development of an asteroid capture mechanism;

- Investigate spacecraft control algorithms for capturing and redirecting an asteroid;

- Demonstrate concepts for astronaut extravehicular activity on the surface of an asteroid.

Credit: NASA

Reference Information

Text and Images:mages

http://www.nasa.gov/

http://www.youtube.com/

http://en.wikipedia.org/

http://www.kiss.caltech.edu/

http://nssdc.gsfc.nasa.gov/

http://www.lpl.arizona.edu/

http://pan-starrs.ifa.hawaii.edu/

http://astronomy2009.nasa.gov/

Project Orion Overview and Prime Contractor Announcement, Skip Hatfield, NASA Orion

Project Manager, August 31, 2006 - presentation includes crew module configuration

Asteroid Redirect Initiative Video: http://www.nasa.gov/mission_pages/asteroids/news/asteroid_initiative.html

End