Antares Test Launch “A-ONE Mission” Overview Briefing

Home , Alexander (satellite), Bell (satellite), Graham (satellite)

April 17, 2013

A-ONE Mission Overview

 Primary Objective  Conduct a Test Launch of the Antares Launch Vehicle to Reduce Risk and Improve the Probability of Success for the COTS Demonstration Mission and Cargo Delivery to the ISS

 Secondary Objectives  Perform Payload Pathfinders where Practical  Collect Payload Environments and Vehicle Data During Flight  Fly Secondary Payloads

 Mission Approach  Define and Implement the Test Launch (A-ONE) to be Representative of the COTS Demonstration Mission (Orb D1) − Launch Vehicle Configuration − Cygnus Simulator Mass Properties, Volume and Mechanical Interfaces − Orbital Parameters − Integration and Launch Operations

JFS-3/25/13 © 2013 Orbital Sciences Corporation. All Rights Reserved. 2 A-ONE Mission Summary  Launch Vehicle – Antares 110 Configuration  Booster with Dual AJ-26 Engines  CASTOR 30 Solid Motor Second Stage  No Third Stage

 Space Vehicle - Cygnus Mass Simulator

 Launch Site – MARS Spaceport Pad 0A, Wallops Island, Va.

 Launch Range – NASA Wallops Flight Facility

 Launch Window – 1700hrs-2000hrs EDT

 Target Orbit – Altitude 250 km x 303 km, Inclination 51.64O

 Payload Separation Time – T+ 603 Seconds

 End of Mission (EOM) – T+1124 Sec

Designed to Provide Versatile, Cost-effective PAYLOAD FAIRING • 3.9 meter diameter by 9.9 meter envelope Access to Space for • Composite Construction • Non-contaminating Separation Systems Medium-Class Payloads STAGE 2 • ATK CASTOR® 30/30B/30XL Solid Motor with Currently Under Contract Active Thrust Vectoring • Orbital MACH avionics module to Support 10 NASA • Cold-gas 3-axis Attitude Control System International Space Station (ISS) Re-supply Missions

STAGE 1 On-Ramped to NASA • Liquid Oxygen/RP-1 fueled NLS-II Contract • Two AJ26 engines with independent thrust vectoring • 3.9 meter booster derived from On-Ramped to USAF heritage Zenit design

OSP-3 Contract VEHICLE PARAMETERS • Gross Liftoff Mass: 290,000 kg EELV New Entrant • Vehicle Length: 40 m • Vehicle Diameter: 3.9 m Statement of Intent Accepted • Mass to ISS Orbit: 5000 kg Baseline by USAF 6265 kg Enhanced

Medium-Lift Composite Structures Performance Payload Separation Utilizing Largely System Proven Elements From Heritage, World-Class ® Suppliers Avionics CASTOR 30 Solid Motor

Thrust Vector Control Systems Frangible Separation Systems

Booster Structures and Systems

AJ-26 Main Engines

Booster Second Stage Payload Accommodations

Booster Production and Assembly in Yuzhmash Factory CASTOR 30 Motor Qualification Test Payload Fairing Second Stage Integration

AJ-26 Engine Avionics Main Engine Section & TVC And System Payload Adapter RUAG 2624VS Separation System

Test Stand Stennis

Test Test 100% Complete 100% Complete

Test Engine Flight Engine Facilities

Demo ATRR Comp. Engine Test Delivery Delivery & Inst.

- AJ 100% Complete 100% Complete 100% Complete 100% Complete 100% Complete Dwg Release Inter-Stage Bay Test Article Qual Tests 5K / 7K Test Core First Flight Unit & Fab

Liquid Oxygen Tank

Core Systems

Inter- Tank Bay

Kerosene

Tank

Stage

Main Aft Bay Engine

System st

1 100% Complete 100% Complete 100% Complete 100% Complete 100% Complete ILV Assy &

HIF Pad Site Activation 5000/7000 Tests Roll-out

site

Launch 100% Complete 100% Complete 100% Complete 2/22/2013 w/o 4/8/13

Static Fire US Qual Tests Fairing Qual First flight units

11 12 Cygnus Mass Simulator

 Physical Properties  Height = 199.25”  Diameter = 114”  Mass = 8377.6 lbs (3800 kg)

 Instrumentation  22 Accelerometers  2 Microphones  12 Digital Thermometers  24 Thermocouples  12 Strain Gages

 Secondary Payload provider for the Antares Test mission is Spaceflight Services  http://www.spaceflightservices.com/Services

 Payloads manifested are:  3U ISIPOD – NASA Ames Research Center − Three 1U Phone Sat Spacecraft ◦ “Alexander, Graham, Bell” − 1.124 kg each, Lithium battery  3U ISIPOD – Commercial Customer − Dove 1 (One 3U Spacecraft)  Neither payload contains a propulsive system  Anticipated time in orbit 2 weeks to 1 month

 Purpose – Demonstrate the Use of Smart Phones as Avionics in Cube Sats

 Established in 1945 by the National Advisory Committee for Aeronautics, as a Center for Aeronautic Research.

 NASA's Principal Facility for Management and Implementation of Suborbital Research Programs.

 WFF is Ideal for Providing Equatorial Access for Low Earth Orbit Insertion.

 WFF Offers a Wide Array of Launch Vehicle Trajectory Options. The Coastline of Wallops Island is Oriented Such that a Launch Azimuth of 135° is Perpendicular to the Shoreline.

 Launch Azimuths Between 90° and 160° can be Accommodated Depending on Impact Ranges.  For Most Orbital Vehicles, this Translates into Orbital Inclinations Between 38° and Approximately 60°  Trajectory Options Outside of these Launch Azimuths, Including Polar and Sun-Synchronous Orbits, may be Achieved by In-Flight Azimuth Maneuvers

H-100 Mainland Cargo Processing

V-55 Payload Fueling Facility H-100 Cargo Processing Facility

Horizontal Integration Facility (HIF)

8.53 Miles Pad 0A

V-55 2.46 Miles Payload Fueling

HIF 1.1 Miles Pad 0A Liquid Fueling Facility

 L-08H 00M: Call to stations  L-07H 30M: Voice checks  L-07H 00M: Range and facility set up  L-06H 30M: Pad clear  L-06H 00M: OCCS sequencer initiation/warm helium charging  L-05H 50M: Vehicle power up and systems checks  L-03H 40M: 15 minute hold  L-03H 00M: Start of LOLS chilldown  L-01H 45M: 15 minute hold  T-01H 30M: Start of propellant loading  T-00H 25M: Start of engine low flow chilldown  T-00H 10M: Start of engine medium flow chilldown  T-00H 03M 30S: Initiate autosequencer transition (terminal count)  T-00H 03M 00S: Autosequencer control  T-00H 00M 00.5S: Initiation launch ordnance train  T-00H 00M 00S: Launch (1700 EDT)  T+1.5 seconds: Engine health checks complete  T+2 seconds: Liftoff  L+6 seconds: TEL clear

20 A-ONE Launch Ascent Profile and Mark Events

Launch Site Wallops Flight Facility Va. Longitude -75.5o E Latitude 37.4o N Altitude 0.028 km Azimuth 107.8o

No. Event Time(s) Altitude Latitude Longitude Velocity (Km) (Deg) (Deg) (m/s) 1 Stage 1 Ignition 0.0 0.0 37.8 -75.5 0 2 Lift Off 2.0 0.0 37.8 -75.5 0 3 MECO 230.0 107 36.6 -73.1 4402 4 Stage 1 Separation 235.0 113 36.5 -72.9 4403 5 Fairing Separation 319.0 184 34.7 -69.8 4251 6 Interstage Separation 324.0 186.8 34.6 -69.6 4244 7 Stage 2 Ignition 328.0 189 34.5 -69.5 4240 8 Stage 2 Burn-out / 483.0 256 29.4 -62.9 7468 Orbit Insertion 9 Payload Separation 603.0 255 23.5 -57.1 7475

Payload Separation Stage 2 Burnout Fairing Separation/ Interstage Separation/ Stage 2 Ignition MECO/Stage 1 Separation

L-0 sec L+231 sec L+236 sec L+319 sec L+328 sec L+483 sec L+603 sec L+606 sec L+1123 sec Stage 1 Stage 1 Fairing Stage 2 Stage 2 Payload Begin C/CAM Ignition MECO Separation Separation Ignition Burnout Separation EOM

TELEMETRY (RocketCam) (Stage 2 Avionics) (P/L Instrumentation) (LV Instrumentation) (Stage 1 Avionics)

Wallops Coquina Bermuda Antigua

FLIGHT TERMINATION Wallops (FTS Receiver) Coquina Bermuda L+440 sec No FTS Req’t

RADAR Wallops (Transponder) Coquina Bermuda

 COTS Mission Pressurized Cargo Element Loaded with Cargo at Wallop Flight Facility Payload Integration Center  Additional Cargo To Be Loaded Prior to Launch

 COTS Service Module, Along with Two Others, Assembled in Orbital Dulles Factory

 Orbital is Moving Into Antares Test Launch with High Confidence

 Successful Test Launch Will Validate Antares System Performance

 Successful Test Launch Will be Followed By COTS Demonstration Launch After Data Review and Vehicle Preparations