Transcript Operationally Responsive Spacelift (ORS) Affordable

This Briefing Is Classified
UNCLASSIFIED
Operationally Responsive
Space (ORS)
Hybrid Launch Vehicle (HLV)
Subscale-Demonstration (SD)
Initiative
Lt Col Gus Hernandez
Chief, Space Vehicles Branch
HQ AFSPC/DRFV DSN: 692-3938
Outline
• Purpose of Brief
• Emerging Relationships
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Capability Need
AFSPC Missions
Operational View
ORS Analysis of Alternatives (AoA)
• Why a Hybrid Vehicle
• ORS Roadmap
• HLV Sub-scale Demo (SD)
• Goals
• Acquisition Schedule
• Flight Test Plan
• S&T
• Summary
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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Emerging Relationships
National Security Space (NSS)
Theater (JWS)
Global
• Core and enduring capabilities
• Global/multiple theater effects
• Various controlling authorities
• Single theater effects
• JFC dedicated
• Expeditionary Units
Operationally Responsive Space
• Tailored to JFC needs
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War Reserve Material
On-demand launch and capabilities
Affordable Lift
Rapid satellite initialization
Seamless integration
Responsive Ranges
Near Space
Joint Warfighter Space (JWS): Concept of Joint Force Commander-dedicated, rapid launch capabilities
that are tailored and integrated seamlessly with theater and global Nation Security Systems
Operationally Responsive Space (ORS): The ability to promptly, accurately, decisively deliver, position,
and operate national and military assets in and through space.
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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Operationally Responsive Spacelift (ORS)
Need
• Key capabilities
• On-demand payload deployment (CAV and satellites)
• Launch to sustain constellations for peacetime ops
• Rapid responsive space transport
• Integrated space operations mission planning
• Key characteristics
• Responsive, maneuverable, economical, survivable,
flexible, interoperable
• Speed consistent with Air Tasking Order (ATO) cycle
• Ready for launch within hours of call-up
• Operational payloads within hours of reaching orbit
• High launch tempos over extended periods
From ORS MNS JROCC Validated– 2002
Flexibility for sustained US Space Superiority
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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Operationally Responsive Spacelift
- AFSPC Missions • Rapid reconstitution
of space capabilities
lost due to enemy
action
• Augmentation of
critical ISR
capabilities
Force Enhancement
• Cost Effective Lift
• Responsive launch
• Routine launch
• Surge Capability
• Recover Space Assets
• On-Orbit Servicing
• Support ACTDs &
Testing
Space Support
HLV Brief to HQ AFSPC/CC – 24 Jan 05
• Global Precision Strike
• Centers of Gravity
• HDBT & WMD Defeat
• Anti-Access
• Common Aero Vehicle
(CAV)
• Response from CONUS
• < 120 min
Force Application
• Defensive
Counterspace
• Satellite Protection
• Offensive
Counterspace
• Space Surveillance
• Small (300-lb) PLs to
high-energy orbits
Counterspace
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ORS Operational View-1
Servicing
Space
Superiority
Satellite
Deployment
Orbit Transfer
Retrieve/
return
Orbit
insertion
Tactical ISR
Orbital Profile
Pop - up Profile
Force Applications
CONUS
Based
Force Applications
Responsive Space will provide a broad range of capabilities directly
supporting warfighter needs
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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ORS AoA Findings
• Significant Military Utility
• Hybrid Vehicle (reusable booster, expendable upper stages)
Based Architectures
• Lowest LCC generally
• AoA suggested evolutionary approach
• Starting Point: Hybrid (RLV-ELV) Demonstrator to reduce
risk and uncertainties
• Spacelift ground processing validation
• Production cost validation
AOA Highlighted Need For Affordable flexibility to achieve
High-Tempo Military Ops ~10K Payload
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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AFROCC Decision (15 July 2004)
DECISION: The AFROCC has reviewed the ORS AoA, and approves
it to proceed to USAF/CV as a pre-MS A (KDP A) AoA-A based on the
following recommendations:
 Leverage lessons learned from AF-DARPA FALCON demo
 Conduct Architecture Studies
o Responsive spacecraft: size and functions study
o Integration and technology needs
 Pursue a Hybrid launch vehicle: spiral development approach
o Step one: Small scale hybrid integration demonstrator
o Step two: Full scale operational hybrid demonstrator
o Step three: Vehicle production /operations
Additionally, the AFROCC requires an update of the costing section of
the AoA prior to MS B.
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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Notional HLV Hybrid Concept
* Mach ~7 Separation for
Minimal Thermal Loading
* Separation Altitude: ~ 200,000 ft
REUSABLE
BOOSTER
EXPENDABLE
UPPER STAGES
* Goals
~ 1-2 Day Turn Time
~ Factor of 3 to 6 cost reduction
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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Why Hybrids Cost Less
RLV
Expended Hardware (Klb)
Hybrid*
ELV
0
33
12
36% of ELV
Reused Hardware (Klb)
196
0
61
31% of RLV
Fully-Reusable RLVs
Fully-Expendable ELVs
Hybrid ELV-RLVs
• Are big because orbiter must
go to/from orbit
• Expend large amounts of
hardware
• Drives higher development and
production costs
• Drives higher recurring
costs
• Balance ELV-RLV Production and
Development costs, resulting in
lower LCC for most cases
Hybrids offer cost-effective combination of RLV & ELV characteristics
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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Hybrid Vehicle Responsiveness
based on Shuttle Ops Data
Industrial
Base
Infrastructure
Integration
Launch
Launch Vehicle
Launch
Vehicle
Vehicle
Payloads
Spaceport
Post Ops
1st Stage Hybrid RLV Subsystems
• Modern
• Benign Environment • Batteries only • No TPS • No OMS
Engines
• No Fuel Cells Maint.
• Non-toxic
• Fewer Engines • Modern Self•
No
APUs
Contained Actuation
Required RCS
• High Margins
ORS
439
Propulsion
42
34
0
7
Mechanical
Electrical
Therma
l
OMS/RCS
STS
• Canisterized • No Crew or long
duration missions
Payloads
2
0
P/L Integration Crew Support
5,771
7,764
8,205
10,434
12,482
18,914
15,893
Hybrid turnaround time ~26 Serial Hrs
*HLVResult
AoA & AFRL/Industry (RAST & SOV Studies)
Brief to HQSupported
AFSPC/CC – 24By
Jan ORS
05
11
Experience in the HLV Mach 7 Flight Environment
199 FLIGHTS:
The X-15: 1959 -1968
DEMONSTRATED:
High Speed: Mach 6.33, with Inconel hot
structure
Low Cost: < ~$1.6M / flight (inflated to FY04)
Fast Turn: < 48 hours
Robust Rocket Engine (XLR-99): Throttleable, restartable, 24 MFBO
Demonstrated operable rocket powered flight above Mach 6
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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Why HLV will succeed where others failed
Mach 7 reusable booster
• Reduces expendable hardware by factor of three
• Is a more easily-managed low-risk development
PRIOR ATTEMPTS
Reusable Hardware Development
Energy requirement for reusable H/W
Weight allocations for robust hardware
Integration & Operability
Shuttle NASP
Mach
25
Mach
25
HLV
X-33
SD
Y*
Mach
15
Mach
7
Mach
7
Minimal
Robust Robust
Moderate
Moderate Small
Relevant demo of H/W responsiveness
NO
NO
NO
Yes
Yes
Relevant demo of H/W recurring costs
NO
NO
NO
Yes
Yes
Complexity (number & types of systems)
HI
HI
HI
Low
Mod-Low
Low-Mod
Low
Low
Moderate
Technology Maturity at program start
HI
* - Depends on successful completion of sub-scale demonstrator and Vector 1 technologies
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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Why HLV Demonstrations?
• Demonstrates the Hybrid RLV/ELV Concept
• Demonstrator Recommended by AFSPC ORS AoA
• Dovetails with AFSPC POM wedge for ORS Hybrid RLV/ELV
• Builds integration experience for the operational vehicle
• Test bed for technologies
• Adaptive Guidance
• Integrated Airframe/Tank/TPS ~ durable, operable, reliable
• Propulsion
• Leads to affordable acquisition and operations
• Rapid turnaround
• Low development and operations cost
Huge operational pay-off at low developmental cost & risk.
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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HLV Initiative Timeline
Subscale Demonstrator & Y-Vehicle
2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020 2021 2022
Responsive Space Architecture Completion
$6M
HLV Phase 1 Competition & Down-Select
HLV Concept Preference Established
~$200 M
HLV Subscale Demo Design & Production
HLV Subscale Demo 1st Flight
HLV Subscale Flight Test Program
Full-Scale Y-Veh
Design/Production
Full Scale Y-Veh Flight
Full Scale Production & Ops
Technology Insertion
Opportunities
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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Synergy of HLV Y-Vehicle with FALCON
• Expendable stages of FALCON can be used as the upper
stages of the HLV vehicle
HLV
Operational
System
HLV Brief to HQ AFSPC/CC – 24 Jan 05
HLV-FALCON
FALCON
(Generic Depiction)
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Subscale Demonstration Goals
1
2
3
Reduce launch cost by factor of
• 3 (threshold)
• 6 (objective)
Reduce turn time to
• 2 days (threshold)
• 1 day (objective)
Start now
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•
Demonstrate the application
and integration of modern
technologies to validate
feasibility, ops, and cost
estimates
• Collect cost and operability information to
update cost and operations predictive
models
Specific goals
•
•
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HLV Brief to HQ AFSPC/CC – 24 Jan 05
Notional
Concept
5 launches in 10 days with 15 workers
Mach 4-7 stage separation
Booster return to launch site
Fast turn flight planning and range support
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HLV Sub-Scale Demonstrator
Suborbital
Mach 2
F-15
(Ref)
¼ - Scale
HLV Demo
~$200-250 million
Full Scale
60 Klb (Booster dry)
~10 Klb to LEO
~15 Klb (Booster dry)
Mach 7 separation
Fly by FY10
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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HLV SD Near-Term Acquisition Schedule
2005
Q1
Q2
2006
Q3
Q4
Q1
Q2
Q3
Q4
Phase 1: PRDA release
Industry proposal preparation / submission
Phase 1 source selection
Phase 1 contract awards
Phase 1
Phase 1 final reports
Kick-off
Heading checks
Mid-term reviews
Final reviews
Phase 2,3: RFP preparation
Phase 2,3: RFP release
Industry proposal prep
Phase 2,3 proposal submissions
Source selection
Phase 2,3 award
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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HLV SD Management Structure
General Officer
Steering Group
Project Manager
(SMC/TD)
Requirements
(AFSPC/DRF)
Deputy PM
(AFRL/VA)
Sys. Engineering
IPT
HLV Brief to HQ AFSPC/CC – 24 Jan 05
Technology
IPT
Operations,
Infrastructure,
& Test IPT
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HLV Progressive Phased Demonstration Program
Integrated
Ground Tests
1
Hypersonic Flight w/
Powered Return to Base
Lift-Off & Slow-Speed
Controllability Tests
2
3
Return to
Base
Maneuver
Controllability
Tests
Glide-Back
to Base
4
5
High-Speed
Upper Stage
Separation
Lift-Off in
Integrated
Configuration
Integrated Separation & Operability
Demos
HLV Brief to HQ AFSPC/CC – 24 Jan 05
•
•
•
•
A-G&C
ISHM
Subsystems
And more...
S&T High-Speed Test Bed Ops
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Vector 1 Pathway to Success
Revolutionary capabilities are within reach with Hybrid vehicle by 2020
MidTerm
NearTerm
FY 04
FY 06
FY 08
FY 10
SLV
FY 12
FY 14
FY 16
FY 18
FY 20
FY 22
FY24
FY26
1K lbs payload limit
SLV Flt HTV Flts
Hybrid
TRL 6 Engine
Hybrid Subscale Demo First Flight
TRL 4 Engine
TRL 6 Vehicle
Y-Vehicle First Flight
1st Stage (TBCC) Spiral
And / Or
X-Vehicle(s)
Far-Term
TRL 6 Engine
Y-Vehicle
TRL 6 Vehicle
2nd Stage (RBCC) Spiral
Beamed Energy (1K lb payload)
TRL 6 System
Accelerators (1 K lb payload)
Nuclear (TSTO Upper Stage)
Nuclear (SSTO)
50-90K lbs payload
Ops
TRL __ Engine
HLV Brief to HQ AFSPC/CC – 24 Jan 05
Range and Operations (Ground and Flight)
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HLV Technology Readiness
Analytical
Tools &
Manufacturing
Techniques
Tanks
Propulsion
Hot Structures &
Composites
Avionics &
IVHM
Interferometric Fiber
Optic Gyro
Ground
Systems
Four decades of R&D provide much better technology than was available
for the X-15. Could reduce costs well below factor of 3 estimates.
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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Responsive Space
Advanced Technology Study
RSATS conducted to assess state of technologies supporting ORS Concepts
• Built integrated roadmaps for all technologies--near, mid, & far term
• Assessed impact operability on multiple concepts relative to state-of-art
• Recommended prioritization of technologies & investments
Hybrid Rocket:
Assessment:
• Near Term--ELV technology very mature
TSTO Rockets:
• Mid Term--RLV technology maturing fast
• Critical Tech Gap: Vehicle Integration & Flight Vehicle Data
• Far Term--Exciting Far Term spacelift technology
prospects, including hypersonics
TSTO
Air-Breathers:
Recommendations:
SSTO Rocket:
• Continue or increase AFRL investments to support Hybrids & RLVs
• Need demo vehicle: Models alone don’t prove operability goals;
SSTO
require suitable vehicle to flight test technologies
Air-Breathers
• ORS is the optimal next step forward in launch systems
RSATS Selected Vision Vehicles
to Drive Out Technologies
HLV Brief to HQ AFSPC/CC – 24 Jan 05
24
:
Summary
• ORS HLV OBJECTIVES
• Demonstrate Low cost, responsive ops
• Demo Aircraft-Like Ops
• Risk reduction to full ORS capability
• Traceability to Operational System
• ORS HLV Enables
• Factor of 3 to 6 launch cost reduction
• ORS Responsiveness ~ 2 hr call-up, <24 hr turn
• Evolutionary development initiative using spirals
• ORS HLV fits well within ORS evolution roadmap
• Way Ahead– HQ AFSPC/CC approved recommendation to
proceed w/HLV SD Initiative
HQ AFSPC/CC approved – 24 Jan 05
HLV Brief to HQ AFSPC/CC – 24 Jan 05
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