Space Exploration Via Technology Demonstration and Small Satellite Missions Flown on Reusable Launch Vehicles SSC04-X-8.

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1 Space Exploration Via Technology Demonstration and Small Satellite Missions Flown on Reusable Launch Vehicles SSC04-X-8 Presented to: Utah State Small Satellite Conference Logan, Utah August 12, 2004 Debra Facktor Lepore Director of Marketing 1

New Space Exploration Vision Presents Opportunities Goals & Objectives Implement a sustained and affordable human and robotic program to explore the solar system and beyond Extend human presence

2 New Space Exploration Vision Presents Opportunities Goals & Objectives Implement a sustained and affordable human and robotic program to explore the solar system and beyond Extend human presence across the solar system Develop innovative technologies, knowledge, and infrastructures; and Promote international and commercial participation in exploration Exploration Mission Examples Space weather station Solar observatory Earth observatory Lunar and Mars resource mapping Lunar and Mars positioning satellites In-space communications relays Logistics support Technology Demonstration, Small Satellites and Robotic Missions will Play a Key Role Mosaic of the near side of the Moon 2

Small Satellites Have Contributed to Exploration Mission Name Launch Date Nation Mission Purpose Giotto 1985 ESA Study Comet P/Halley Pegsat 1990 US Chemical release experiment Ulysses 1990 US/ESA

1994 US Sensor technology demo; map lunar surface MSTI-2 1994 US Investigate spaceflight techniques and technologies Mars Pathfinder 1996 US Mars lander with surface rover MSTI-3 1996 US Sensor

Prospector 1998 US Determine origin, evolution, and state of lunar resources Mars Climate Orbiter 1998 US Mapping and weather studies of Mars TRACE 1998 US Ultraviolet imaging telescope for studies

recover and return cometary material Simplesat 2001 US Test methods for building cheap astronomical satellites TIMED 2001 US Study the thermosphere mesosphere and lower ionosphere Odin 2001 Sweden

3 Small Satellites Have Contributed to Exploration Mission Name Launch Date Nation Mission Purpose Giotto 1985 ESA Study Comet P/Halley Pegsat 1990 US Chemical release experiment Ulysses 1990 US/ESA Fly over the poles of the sun Hiten/Muses-A 1990 Japan Lunar swingby techniques, ejected lunar orbiter Solar 1991 Japan X-ray imaging of sun MSTI 1992 US Test Miniature Seeker Technology Clementine 1994 US Sensor technology demo; map lunar surface MSTI US Investigate spaceflight techniques and technologies Mars Pathfinder 1996 US Mars lander with surface rover MSTI US Sensor technology tests NEAR 1996 US Rendezvous with and orbit asteroid Eros ACE 1997 US Determine composition of interplanetary matter Deep Space US To flyby asteroid and cometary targets Lunar Prospector 1998 US Determine origin, evolution, and state of lunar resources Mars Climate Orbiter 1998 US Mapping and weather studies of Mars TRACE 1998 US Ultraviolet imaging telescope for studies of the sun Noxom/Planet-B 1998 Japan Test spacecraft technology, study Mars atmosphere Mars Polar Lander 1999 US Study Martian volatiles and climate history Stardust 1999 US Fly near comet and recover and return cometary material Simplesat 2001 US Test methods for building cheap astronomical satellites TIMED 2001 US Study the thermosphere mesosphere and lower ionosphere Odin 2001 Sweden Study galactic molecular clouds CONTOUR 2002 US Explore three comets HESSI 2002 US Imaging hard X-ray flares form the sun Galex 2003 US Observe galaxies ultraviolet wavelengths Mars Pathfinder Mars Polar Lander HESSI Satellite MER-A 2003 US Search, characterize rocks and soils on Mars MER-B 2003 US Search, characterize rocks and soils on Mars SIRTF 2003 US Observatory for infrared astronomy Hayabusa/MUSES-C 2003 Japan Technology demo, collect, return sample from asteroid Galex Satellite 3

Re-use hardware for repeat flights K-1 offers wide range of performance for dedicated or

4 K-1 Fully Reusable Vehicle Overview K-1 vehicle can accommodate Exploration Missions Deliver payloads to space Return payloads from space Test technology, instruments, and experiments Re-use hardware for repeat flights K-1 offers wide range of performance for dedicated or rideshare missions LEO satellites Technology demonstrations Interplanetary missions International Space Station 4

K-1 LEO Satellite Delivery 12,500 lbs to LEO (due east) Dedicated or rideshare of multiple small satellites Up to 3 minisatellites (< 500 kg each) Up to 8 microsatellites (< 125

0 in) 2930 mm (115.5 in) 3180 mm (125.2 in) 2820 mm (111.1 in) 2465 mm (97.1 in) 5335 mm (210.0 in) 4058 mm (160.0 in) 5610 mm (220.8 in) 4890 mm (192.5 in) 5245 mm (206.

5 K-1 LEO Satellite Delivery 12,500 lbs to LEO (due east) Dedicated or rideshare of multiple small satellites Up to 3 minisatellites (< 500 kg each) Up to 8 microsatellites (< 125 kg each) plus primary payload 3350 mm (132.0 in) 2930 mm (115.5 in) K-1 MPAS Modeled after Ariane 4 Adapter RADIUS RADIUS 4058 mm (160.0 in) 2910 mm (114.6 in) 3350 mm (132.0 in) 2930 mm (115.5 in) 3180 mm (125.2 in) 2820 mm (111.1 in) 2465 mm (97.1 in) 5335 mm (210.0 in) 4058 mm (160.0 in) 5610 mm (220.8 in) 4890 mm (192.5 in) 5245 mm (206.5 in) K-1 Can Fly ESPA Ring 2640 mm (104.0 in) STANDARD PAYLOAD MODULE (SPM) Two Payload Modules for LEO 2640 mm (104.0 in) EXTENDED PAYLOAD MODULE (EPM) 8 Microsatellites with Primary Payload 5

6 K-1 as Technology Testbed Test technology experiments in full flight environment Body Station 1000 Body Station Body Station Variety of experiment locations Standard experiment interfaces and integration approach Reusability enables experiment recovery and repeat flights Footprint 6 Footprint 4 Footprint 3 Footprint 5 Footprint 2 Footprint 1 Externally Mounted (Passive) for TPS and Advanced Materials Typical Experiment OV Aft Flare Mounting Location ECOBOX Tray Experiment Bolt-Down Holes (136) 1.000" Square Cut-Outs (119) ECOBOX Attachment Brackets and Bolts (8) Power Receptacle Connector Data Recording and Command Interface Receptacle Connector 1553B Data Receptacle Connector OV Mid Body Mounting Location OV Forward Mounting Location Experiment Containment Box (ECOBOX) Internally Mounted (Active) for Avionics and Microgravity 6

Use K-1 expendable active dispenser Preliminary design complete Space Exploration: Moon/Mars & Beyond Well suited for small Lunar and Mars missions 3,500 lbs to GTO 2,000 to 3,000 lbs to

7 Use K-1 expendable active dispenser Preliminary design complete Space Exploration: Moon/Mars & Beyond Well suited for small Lunar and Mars missions 3,500 lbs to GTO 2,000 to 3,000 lbs to interplanetary targets Extended Payload Module (EPM) Negator Spring Assemblies (4) Satellite EPM Forward Fairing Active Dispenser Deployment Guide Rails (4) EPM / OV Interface Ring Payload Module Interface Fittings EPM Aft Fairing Active Dispenser Shown Inside Payload Module Example is Mars Exploration Rover 7

Standard Payload Racks (ISPR) Avionics Pallet Star Trackers, Proximity Sensors, Batteries, Mechanism Controllers K-1 Second Stage

8 3200 kg cargo delivered 900 kg cargo recovered 30 m 3 of cargo volume Up to 40 km reboost Berth to U.S. node K-1 ISS Missions: Cargo Resupply and Return Dome Common Berthing Mechanism (CBM) Support Structure for Cargo and International Standard Payload Racks (ISPR) Avionics Pallet Star Trackers, Proximity Sensors, Batteries, Mechanism Controllers K-1 Second Stage Interface Ring Attitude Control System (ACS) 4 Places Flight Releaseable Grapple Fixture (FRGF) K-1 Inherent Reusability Gives the U.S. Another Capability to Recover Cargo 8

K-1 Program Overview K-1 vehicle 1 is ready for integration and launch 75% hardware, 85% design, 100% Guidance Navigation & Control (GN&C) software complete System requirements tasks completed

9 K-1 Program Overview K-1 vehicle 1 is ready for integration and launch 75% hardware, 85% design, 100% Guidance Navigation & Control (GN&C) software complete System requirements tasks completed Numerous tests conducted Over $600 million in private capital invested In process of finalizing plan of reorganization Existing technologies, hardware on hand, testing status, and the experienced K-1 team assures the accomplishment of the K-1 mission 22.0 ft 14.0 ft 19.2 ft 60.2 ft 61.0 ft Extended Payload Module Launch Assist Platform (LAP) Orbital Vehicle (OV) 9

K-1 Vehicle Fabrication 75% Complete Systems Engineering Design Specifications Complete Design Data Books Complete - Aerodynamics, Loads, Thermal Design Reference Missions Complete Electrical

10 K-1 Vehicle Fabrication 75% Complete Systems Engineering Design Specifications Complete Design Data Books Complete - Aerodynamics, Loads, Thermal Design Reference Missions Complete Electrical Database Complete Vehicle Integrated Schematics Complete Wiring and Small Plumbing Line Drawings Complete Vehicle Exterior Structure 21 of 23 Major Panels Complete LAP LOX Tank 100% Complete Parachutes Engineering 90% Complete Mains Complete Drogue Complete Stabilization 95% Complete Mortar Complete Drop Tests - Complete OV RP Tank 100% Design Complete 35% Fabrication Complete OV LOX Tank 100% Complete Thermal Protection System (TPS) Overall Design Complete Detailed Design 30% Arc Jet Testing Planned Production at Restart LAP RP Tank 100% Design Completed 30% Fabrication Complete Payload Module 100% Structural Design Complete 25% Fabrication Complete LOX Retention Tank 100% Design Completed 75% Fabrication Complete OMS Engine 40 Igniter Tests Complete 29 Injector Tests Complete NK-43 Engine 9 Engines at Aerojet NK-33 Engines 37 Engines at Aerojet Verification Engine in Test Airbags OV Fabrication 50% Complete LAP Fabrication 50% Complete ¼ Scale Drop Tests Complete Airbag Inflation Tests Complete Avionics Hardware Vehicle Computer - Delivered GPS/INS Units - Delivered TDRSS Receiver - Off the Shelf FAA Transponder Delivered SMU - In Manufacturing PDU, MEC - In Test Avionics Software GN&C Complete Hardware in the Loop (HWIL) With Flight Hardware/Software Testing Final Assembly Commenced 5/98 1 st Stage LOX Tank Delivered 6/98 Australia Launch Site Contract Executed for Site Design and Construction Launch Site Design 100% Complete Environmental Approval Received Launch Operation Contract Signed Native Title Agreement Signed Site Ground Breaking Export License Approved September

11 Standard Planning Documents Guide the Customer Process K-1 VEHICLE PAYLOAD USER S GUIDE K-1 VEHICLE TA-10 FLIGHT EXPERIMENT DESIGN AND REQUIREMENTS DOCUMENT May 2001 December 2002 With Active Dispenser Addendum May 2002 Includes: Interface Definition & Requirements Document Preliminary Questionnaire Detailed Experiment Questionnaire Available at 11

Kistler is Available to Support Exploration Missions Contact: Debra Facktor Lepore Director of Marketing dflepore@kistleraero.

12 Kistler is Available to Support Exploration Missions Contact: Debra Facktor Lepore Director of Marketing 3760 Carillon Point, Kirkland, WA Telephone = / Facsimile = Website = Global mosaic of Mars 12

Space Exploration Via Technology Demonstration and Small Satellite Missions Flown on Reusable Launch Vehicles

SSC04-X-8 Abstract Space Exploration Via Technology Demonstration and Small Satellite Missions Flown on Reusable Launch Vehicles Debra Facktor Lepore Director of Marketing Kistler Aerospace Corporation