PERSPECTIVES ON SPACE FUTURE BRIG GEN S. PETE WORDEN Director for Development and Transformation , Space and Missile Systems Center November 2003 LAUNCH VEHICLES, MICROSATELLITES AND CISLUNAR SPACE

• WHAT’S NEW IN DoD? • ACCESS TO SPACE – U.S. Dilemma – cost too much and takes too long – Shuttle Problems, EELV Limitations – Short Term – Small Launch Vehicles – Long Term, Reusable • Hypersonics/Airbreathers vs Rockets • Horizontal vs Vertical • MICROSATELLITES – U.S. has largely ignored – “Responsive” potential • CISLUNAR/TRANSLUNAR OPPORTUNITIES –NEOS – Large Telescopes, Lunar Resources Organization and Money

• 2002 – Implementation of “Rumsfeld” Commission • 2002 – Reorganization of Air Force and NRO – Under Secretary of the AF – Joint with DNRO • DARPA – “Virtual Space Office” – $100s M per year – Transformational Charter STRATEGIC COMMAND -- 1 OCT 2002

Our Mission Establish and provide full-spectrum global strike, coordinated space and information operations capabilities to meet both deterrent and decisive national security objectives. Provide operational space support, integrated missile defense, global C4ISR and specialized planning expertise to the joint warfighter. ACCESS TO SPACE ?

1998 1986 Challenger Titan IV

2003 Columbia Spacelift Needs Annual Peacetime Launch Needs 100+Klb Class 45Klb Class 15 Klb Class 1Klb Class Payloads to Cargo/Crew to Station Beyond GEO/Large Sats LEO/Polar/GTO Payloads to GEO •SBL Payloads to Payload Servicing •Civil ISS •Multi-Mission space LEO/Polar platforms •Responsive Sats & •National •MicroSats •Small Commercial Sats •Full LRS

5-10 launches / year 15-30 launches / year 10-15 launches / year 5 launches / year +++ + Annual War-time Launch Needs 10 launches 35 launches 2 launches No addit’l launches

(Additional launches required for prewar augmentation and reconstitution given a near-peer competitor) Spacelift Options

• Reference – Existing LV systems •RLV -TSTO Payload – Optimized LH-LH Classes – Optimized RP-RP –Microsat – Optimized RP-LH • ELV –5 klb –BimeseLH-LH – Liquid two stage –15 klb –25 klb –BimeseRP-RP – Solid three stage –45 klb – Hypersonic-Rocket –100 klb ImagineAdvanced the Possibilities Space Transportation ♦ Current Space Transportation is paced on a shallow slope WHEN? ♦ Dramatic Change requires investment in Current new technologies

CAPABILITY Space Transportation ♦ Imagine the Possibilities …

TIME A National Initiative Why RLVs? A Glance at Production Costs B-2 ($8150/lb) 4500 F-22 Note 4000 Production is the largest component of ELV flight costs. 3500 Military Aircraft (70% for Delta II) 3000

s su 2500 ga Pe 2000 JSF II Launch Vehicles las B-1 At S II A s V tla n I 1500 us A ta S Commercial ur Ti U a I N Aircraft T F16 a I IV elt an 1000 D Tit T 747Series Production Cost Floor o 7 7 7 7 7 m 7 3 5 6 7 7 Vehicle Cost/Inert Wt (FY'02$/Lb) Vehicle Cost/Inert S 7 7 7 500 1 e 7 S 7 - - - for flight vehicles a 7 r e 4 2 3 h -2 i ri 0 0 0 a 0 e e 0 0 0 w 0 s s E L E k R R R 0 0 100 200 300 400 500 Vehicle Inert Wt (Klb) ISABE SAPIndia 01|McClinton.ppt #10 Configuration Summary HTHL Technology Level Moderate Aggressive

1st: Turbojet 2nd: RBCC B2 C2 Mach 4

1st: TBCC 2nd: Rocket B1 C1 Mach 8+

Technology Moderate Aggressive

1st: Turbojet 1st: Turbojet 2nd: RBCC B2 C2 Mach 4

2nd: Rocket 1st: TBCC E 2nd: Rocket Mach 6.5 Mach 8+ B1 C1 1st: Turbojet 2nd: Rocket Mach 6.5 E PAYLOAD NEEDS

Data from 9 May 2003 Partnership Council Briefing Peace-time rate (Civ, Gov, Mil) War-time rate Desired “End Point” Payload Mission Needs, Per Year

80

60

40

15 Klbs 40 Klbs 50 Klbs 20 GEO Polar ISS

0 10 20 30 40 50 60 70 80 90 100+ Payload to 100NM East LEO (Klbs) TSTO HTHL PAYLOAD CAPABILITY Airbreathing Design Space

Data from 9 May 2003 Partnership Council Briefing Peace-time rate (Civ, Gov, Mil) War-time rate 2.5 Desired “End Point” Payload

2.0

)

s Assumed Runway Bound

b

l

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1.5

W TOGW Margin

G 1.2

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T HTHL TSTO Limit 1.0 Aggressive Technology Bound Moderate Technology Bound 0.5

0 10 20 30 40 50 60 70 80 90 100+ Payload to 100NM East LEO (Klbs) Sprite Small Launch Vehicle Example

• 3-Stage Vehicle

– LOX/Kerosene Ablative Engines

– Hi Performance Pressure Fed Pressurization

System

– Composite Tanks

– Modular Vehicle, Common Stage

• 6 for stage 1

• 1 for stage 2 (vac nozzle)

– 2.5klb thrust 3rd stage

• 600 lb payload to easterly LEO GLOW: 78,500 lbs Height: 50 ft • ~$5M estimated launch cost Diameter: 11.2 ft Minuteman III Launch Vehicle

Minute-Man III Baseline Model

Payload Fairing 270 lb Jettison fairing with stage #: TBD 2070 lb CAVs 1800 lb

Guidance System 0lb

4th Stage NAME PSRE Dry 346 lb Propellant 260 lb Total 606 lb Thrust (vac) 332 lbf Isp (vac) 295.5 sec Ae 0.3 sq ft

3rd stage Adapter 0 lb 3rd Stage neglected SR 73 3rd Stage NAME SR73 Dry 905 lb Sref 14.75 sq ft Propellant 7292 lb Total 8197 lb Thrust (vac) 34500 lbf Isp (vac) 286.4 sec

e Ae 5.62 sq ft

al 2nd stage/ 3rd stage c inner stage adapter (fixed) 0 lb S neglected to

n 2nd Stage

w SR 19 a r 2nd Stage NAME SR19 t D

o Dry 2359 lb N Sref 14.75 sq ft Propellant 13680 lb Total 16039 lb Thrust (vac) 60700 lbf Isp (vac) 287.4 sec Ae 12.6 sq ft

1st stage/ 2nd stage 0 lb inner stage adapter neglected

1st Stage M55 1st Stage NAME M55 Dry 5560 lb Propellant 45670 lb Total 51230 lb Thrust (vac) 200400 lbf Isp (vac) 250.35 sec Ae 11.4 sq ft Sref 23.54 sq ft

TO TAL VEHICLE W EIG HT 78142.0 lbs Falcon Summary (SpaceX)

• Payload capability: Approx 1100 lbs to LEO (28.5 deg) • Launch from both Eastern and Western Ranges • Multiple manifest, secondary, and piggyback capabilities • Benign payload environment • $6M per vehicle through 2004 • First launch possible by late 2003

• Diameter 5.5’ tapering to 5’ • Length 68’ •1st Stage Parachute/Water Recovery •1st Stage Lox/RP1 •2nd Stage Lox/RP1 DARPA RASCAL LV

The Responsive Access, Small Cargo, Affordable Launch (RASCAL) program will design and develop a low cost orbital insertion capability for dedicated micro-size satellite payloads. The concept is to develop a responsive, routine, small payload delivery system capable of providing flexible access to space using a combination of reusable and low cost expendable vehicle elements. Specifically, the RASCAL system will be comprised of a reusable airplane-like first stage vehicle called the reusable launch vehicle and a second stage expendable rocket vehicle. The RASCAL demonstration objectives are to place satellites and commodity payloads, between 50 and 130 kilograms in weight, into low earth orbit at any time, any inclination with launch efficiency of $20,000 per kilogram or less. X-42 PROPOSED PROGRAM

Pop-Up Demonstrator TSTO System

Bi-mese ity abil or ap Weight + C ity Optimized labil Sca Î Size ger Lar

X-42 Baseline ~50% Scale Demonstrator NOTIONAL U.S. APPROACH Air Force Heavy • Launch System Design and Very Heavy Integration (40-60klb) (80 klb) • Launch Facility • Landing System • Flyback Engines Medium VTHL • Wiring RLV •TPS •GN&C (15-25klb) • Expendable upperstages • Operational Baseline • Validated Systems Analysis • Validated, Credible, Super Heavy Cost Estimates Lift (200 klb) Light RLV • Validated Technologies Ops Demo Common to Larger (10 Klb) Systems Common • Validated vehicle upgradeable as Booster medium 2nd stage w/ ELV Core • Low cost light payload capability

NASA Medium HTHL RLV Very Heavy Lift HTHL •Next Gen H2 Rocket (15-25klb) (200 klb) •Metallic cryo-tank and/or •Power •Actuation •Space-based Range •IVHM/Avionics

Medium HTHL Hypersonic (15-25klb) Light RLV

Flight Cost* ~ $7 M Hypersonic Turnaround ~ 24-72 hrs Technology Testbed Reliable ~ 0.995+

SmallSat Reusable Launcher

Jet Engines allow incremental expansion of Experimental CAV flight envelop with large Thrower number of flights

Cost includes: fixed & variable costs at a flight rate of 30/year, with no upperstage Notional Spiral Development Plan [25klb Spiral 2, without Crossfeed]

Same

Heritage

Same Heritage

Same

Same

FALCON Spiral 1 Spiral 2 Spiral 3 Spiral 4 Stage 1 Engine New RP 2 SSME New LH Engine (4) Same as Spiral 2 Same as Spiral 2 Stage 2 Engine New RP FALCON Stage 2 Spiral 1 Stage 1 Same as Stage 1 EELV Core Stage 3 Engine New RP FALCON Stage 3 -- -- EELV US Payload to LEO 1,500 lb 12,800 lb 25,000 lb 87,700 lb ~ 160,000 lb Staging Delta-V 12,700 fps 12,800 fps 10,600 fps 14,400 fps RLV Height 101 ft 112 ft 166 ft 166 ft 166 ft RLV Dry Weight 90.0 klb 367.9 klb 763.8 klb 493.3 klb GLOW 132.9 klb 580.7 klb 1,943.0 klb 4,389.5 klb 3,623.3 klb RESPONSIVE SPACE

• Microsatellites • Responsive Space Satellite Size vs. Capability

10,000

Large, MilStar, IntelSat6 Operational National Assets “Operational” 6.4x3.6x11.8m Commercial Communication Satellite 4600kg, Hubble,etc. Satellites 1,000 WindSat -Wind Speed Small Demo/Experiment Missions Sat - Map (“Low” Cost Class of DoD & NASA) Iridium GlobalStar Also Commercial LEO Comms. 100 ORBCOMM Tactical Satellites Micro TiPS (Historically University Sats CHIPSat MOST & Experiment Class) 10

Satellite Weight (kg) Satellite PC Sat University & Nano STARSHINE Experiment Class Sats CUBESATs 1 Satellite Class & Mission Capabilities 0.1 MicroSats in the <100 kg Class can Now Perform Valuable Niche Missions GLOBAL MICROSATS 2002 HISTORY

Microsat Name Owner/Nation Date Launched Mass/Purpose Dash ISAS/Japan 4 Feb 2002 70kg/Technology Kolibri-2000 Academy of Unk 20kg/Education Sci/Russia/Australia Unk Tsinghua/China Sep 2002 (failed) Unk/Technology Alsat 1 Algeria/Surrey(UK) 28 Nov 2002 92kg/Disaster Monitor Mozhaets Russia 28 Nov 2002 64kg/Science/Education FedSat Australia 14 Dec 2002 50kg/Science WEOS Chiba Inst/Japan 14 Dec 2002 68kg/Science µ-lab Sat NASDA/Japan 14 Dec 2002 68kg/Technology Latin-Sat A,B Argentina 20 Dec 2002 11.35kg @/Technology UniSAT-2 Univ of Rome/Italy 20 Dec 2002 11.8kg/Science SaudiSat-1c Saudi Arabia 20 Dec 2002 Unk/Unk U.S. AFRL XSS-10 MICROSAT PROGRAM, FEB 2003

COST: APPROX $60M TIME: 6 YEARS OTHER EFFORTS: JUNE 2000

Figure 6 SNAP-1 Nanosatellite

Figure 7 Figure 8 Russian COST: APPROX $1M Tsinghua-1 COSPAS-SARSAT TIME: 1 YEAR Microsatellite Satellite Image Taken by SNAP-1

CONOPS: Launch Decision and Processing RESPONSIVE SPACE - TACSAT 1 2004

Automatic Orbit Maneuvers for Constellation Building

Launch Direct Downlink

United CINC: OPLAN Use Authorized 3-5 Days Launch Team Request Mission • Precise Orbit Calcs. Call-up • Range Safety Clearance • SC/Payload Integration Joint JTF Commander Decides: – Battery Charge Task Force 1. Payload Capability Needed – Fueling Commander 2. Area of Interest • Final LV Integration 3. Area for Direct Downlink 4. When to Call-up Asset Schedule of Downlink Times & Locations TacSat-1: Spacecraft & Mission Highlights

• Size: – 41 inches Diameter, 18 inches High • Mass: – Bus: ~60 kg – Copperfield-2S: 20 kg – Imager: 10 kg – Total: ~90 kg •Power: – Available: 186W – Bus: 55W OAP, 75W Peak – Payload: ~70W Peak • Orbit: – Altitude: 400-450km – Inclination: ~63 Degrees • Mission Life: – Approximately 1 Year Cis-Lunar Space

Cis-Lunar Space (Near Earth Deep Space)

L2 • Earth-Moon System Moon 24,000 km L1 • Lagrangian (Libration) L5 Points L4 o – L1, L2, L3 – Unstable 60 – L4, L5 – Stable GEO • Minimal Propellant 42,100 km GPS R = 384 ,000 km Requirements for 26,500 km

“Station- Keeping” L3 • “Clean environment” for 1023 m /sec science experiments • Region of Interest for MiDSTEP in Blue TRANSLUNAR SPACE Cis-Lunar Mission Concepts

= High Thrust (∆V m/sec) LOI-WSB (700) = Low Thrust WSB Optimization using LT Arc = Trajectory Correction (HT/LT) Altitude Control

Lunar GEO

GTO Libration PMF Orbit Insertion/ TTI Earth AMF Point (1,100) (700) (1,900) Station Keeping

Altitude Control

Repositioning/ LOI-Direct Station Keeping (800) TTI = Transfer Trajectory Insertion AMF = Apogee Motor Fire PMF = Perigee Motor Fire LOI = Lunar Orbit Insertion WSB = Weak Stability Boundary Navigation

1. Navigation in Cis-Lunar Space

•Tasks – Station-Keeping and L2 Repositioning – Maneuvering L1 L5 – On-Orbit Storage L4 • “Wandering” in Cis-Lunar Space (e.g., Near L1/L2) • Transferring Into Moon- Circling Orbit – Autonomy • Propulsion – Solar Sailing – Electric Propulsion

• Navigation Aid L3 – ”Leaking” GPS Signals Classes of Near-Earth Asteroid Orbits

Apollos IEOs Earth

Atens

Amors Earth HAZARD SUMMARY (2003 NASA REPORT) MOST: “Microvariability and Oscillations of STars”

• Status: – In Phase D; pre-ship review by end of 2001 – Launch scheduled for early 2003 (on Delta-2, with Radarsat 2). • Innovative Elements: • First CSA microsatellite. – Highly-accurate (~ 10 arc- • Space astronomy mission. seconds) attitude control. • Dynacon is Prime Contractor – Science-grade imaging telescope. MITIGATION MITIGATION

• Near-Term -- “Kiss it goodbye” • Best-Identify objects decades or centuries out – Explore Object – Divert using “conventional” means • Chemical or Electric Propulsion • “Impact” movement • “Yarkovsky” Effect -- use solar radiation pressure • Surprise Object -- especially a “Comet” – Diversion “Hard” – Disruption “Dangerous” - “Rubble Pile” Problem – “Kiss it Goodbye” • “GIGGLE FACTOR”!!! MITIGATION - COMMAND AND CONTROL

•The Real Issue on Planetary Defense is not “Weapons” -- its “COMMAND AND CONTROL” -- C-2

•Who identifies the Threat? •Who believes that its real and why? •Who tells whom about the Threat? •Who decides what to do? •Who builds and executes the operation? •Who pays? •Who coordinates with all the effected parties? •Who tests the mitigation method? •Who gets blamed when it goes wrong? C2 Environment for Today’s Missile Warning

SENSORS & FIXED AND ENDURING DECISION MAKERS WARFIGHTERS PROCESSING COMMAND CENTERS NCA/CINC Global Vigilance Command and Control Global Grid TRIAD BMEWS C&C PAVE PAWS PARCS Missile NMD C3 Missile Warning IO Space Air

CINC C2 Theater NODE PETE Coalition RAOC/SBCC CINCS Forces Air Control & Warn JTF/ AMWC CND JTF SPACEAF AOC SEWS Partners EGLIN Collateral/ MCCC Contributing AOC AEF GEODSS / Have Stare OC3F NORAD/USSPACECOM Warfighting Support System Space Surveillance & Warn

AlignAlign WithWith GlobalGlobal Warfighter/C2Warfighter/C2 GoalsGoals ASTEROID 2002 AA29 NEO Way Ahead

• USE MICROSATS TO IDENTIFY SUITABLE NEOS -- ESPECIALLY “HORSESHOE” ORBIT OBJECTS • MOUNT SURVEY AND SAMPLE RETURN MISSIONS WITH MICROSATS • CONDUCT “MANEUVER” EXPERIMENTS • IF SUITABLE OBJECT CAN BE FOUND “MOVE” INTO EARTH ORBIT LUNAR SOUTH POLE “PEAKS OF ETERNAL LIGHT” JAMES WEBB SPACE TELESCOPE 25 YEAR SPACE PROGRAM

• DEVELOP AFFORDABLE “RESPONSIVE” LAUNCHERS 2010- 2015 • USE MICROSATELLITES TO SURVEY CISLUNAR SPACE, SUITABLE NEOS AND LUNAR POLES 2008-2018 • EVOLVE FULLY REUSABLE HEAVY LIFT AND PARTIALLY REUSABLE VERY HEAVY LIFT VEHICLES 2015-2020 • CONSTRUCT VERY LARGE SPACE TELESCOPE (PLANET FINDER) 30 METERS IN DIAMETER AT L-2 - 2020-2025 • DEVELOP LUNAR/NEO RESOURCE USAGE 2020-2025 • MOVE NEO INTO EARTH ORBIT 2025-2030