Hypersonic Airplane Space Tether Orbital Launch (HASTOL) Study NASA Institute for Advanced Concepts Second Annual Meeting Goddard Space Flight Center Greenbelt, Maryland June 7, 2000 John E.Grant The Boeing Company 5301 Bolsa Ave., Huntington Beach, CA 92647-2099 +1-714-372-5391 john.e.grant@boeing.com www.boeing.com
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Presentation Outline • Team Acknowledgments • HASTOL Concept of Operation • Phase I Results – Hypersonic Airplane – Tether Boost Facility – Tether – Payload Capture
• Phase II Plan • Follow-On Efforts
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HASTOL Phase II Study Team The Boeing Company John Grant, Reusable Space Systems, Huntington Beach, CA Jim Martin, Reusable Space Systems, Huntington Beach, CA Tom Bogar, Phantom Works, St. Louis, MO Don Johnson, Phantom Works, St. Louis, MO Joe Stemler, Phantom Works, St. Louis, MO Mike Bangham, Space and Communications, Huntsville, AL Ben Donahue, Space and Communications, Huntsville, AL Beth Fleming, Space and Communications, Huntsville, AL Brian Tillotson, Space and Communications, Seattle, WA Tethers Unlimited, Inc. Rob Hoyt, Seattle, WA Bob Forward, Seattle, WA
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The HASTOL System Concept of Operation Features a Reusable Launch Architecture • Hypersonic Airplane Carries Payload up to 100 km, Mach 12 • Rendezvous with Tip of Rotating Tether in Orbit • Tether Lifts and Tosses Payload into Orbit or Escape
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HASTOL Phase I Results Showed Concept Feasibility • Top -Level Requirements Developed; Top-Level Trades Conducted to Define Basic Design Approaches • Selected Hypersonic Aircraft Concept (DF-9) • Validated Overlap of Tether Tip and Hypersonic Aircraft Velocity and Geometry Envelopes for Capture – Defined Aircraft Apogee Altitude/Velocity Envelope – Tether Tip Can Withstand Thermal Loads as it Dips into the Atmosphere • Tether Boost Facility Concept Defined • Rotovator Tether Concept Selected • Simplified Grapple Concept Identified 5
HASTOL Baseline Hypersonic Aircraft Concept: Boeing-NASA/LaRC DF-9 Dual-Fuel Aerospaceplane
Takeoff Wt: Payload: Length: Apogee:
270 MT (590,000 lb) 14 MT (30,000 lb) 64 m (209 ft) 100 km
Speed at Apogee: 3.6 km/sec (approx. Mach 12) 4.1 km/sec (inertial) Turboramjets up to Mach 4.5 Ram-, Scramjets above Mach 4.5 Linear Rocket for Pop-Up Maneuver 6
Aircraft “Pop-Up” Mission Profile Analysis Shows Required Speed and Altitude are Attained
Launch Ascent
High Speed Climb Mach 4.5 - 10
Alternate Upper Stage to Tether Rendezvous Ballistic Trajectory to Tether Rendezvous
Subsonic Cruise
Pattern, Landing, Post Flight Operations
Initial Climb Mach 0.8 - 4.5
Descend Decel
Tanker Rendezvous Inflight Refueling
400,000 120
ft
❍
km
❍
❍
● Ac hie vable Po ints ❍ Unac hie vable Po ints
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Altitude
350,000 ❍
100
●
❍
●
300,000 90
80
●
●
250,000 8,000 2,500
9,000
10,000 3,000
●
●
11,000
12,000 3,500
ft/s m/s
Ve lo c ity
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Ongoing Hypersonic Aircraft Development Programs Will Benefit HASTOL Concept Maturity • DF-9 - Horizontal takeoff, horizontal land concept – Developed by Boeing for NASA LaRC – Derivative of DF-7 hypersonic cruise airplane concept
• Hyper-X (X-43) - Scramjet flight test vehicle from Pegasus booster – – – –
Microcraft prime contractor; Boeing subcontractor First flight test vehicle delivered; flight to Mach 7 in Sept 2000 Second flight test vehicle to be delivered to NASA in August 2000 Third flight test vehicle in design/fab; will fly to Mach 10 in Oct 2001
• X-34 - Rocket boosted hypersonic flight demo – Being developed by Orbital Sciences – Captive flight tests completed – Phase 1 flights to Mach 3.8; Phase 2 flights to Mach 8
• X-33 lifting body, aerospike engine – Being developed by Lockheed-Martin – Flight vehicle being assembled; testing to Mach 10+ envisioned
• X-37 (Future-X) Hypersonic research test bed vehicle – Boeing/NASA MSFC Cooperative Effort – First flight planned for 2003 (Shuttle payload); re-entry to powerless horizontal landing
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HEFT Tether Boost Facility is Adaptable to the HASTOL Mission Facility center of mass in slightly elliptical orbit: - 700 km apogee - 610 km perigee - 90 km from tether station - 7.6 km/sec perigee velocity Tether: - Length: 600 km - Tip velocity: 3.5 km/sec - When facility center of mass is at perigee, tether tip is at100 km altitude Station Mass: Tether Mass: Grapple Mass
1,650 MT 1,360 MT 650 MT
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HEFT Tether Boost Facility is Adaptable to the HASTOL Mission S o lar P an el A rra y
H oy te th er D es ig n C u t P rim ary L ine First Le ve l of S e co nd ary Lin es Tran sfers Lo ad A ro un d D a m ag ed S e ction
P rim a ry L in es
S econ da ry L ine s (Initially U nstre ssed)
1,00 0- to 2,0 00 -to nne Te th er C o ntro l S tatio n
Te ns of M e ters 600 -km S pe ctra 200 0 Teth er
E ffe cts o f D a m a ge L oca lize d S e co nd L evel of S e co nda ry Lin es R e distribu tes Lo ad B ack o n U n da m ag ed P o rtion of P rim ary L ine
2 0-m d ia m e ter
S pa ce T e the r F ac ility G ra p p le A s se m bly
G ra pp le W in ch Z ylon (P B O ) G rap ple T eth er G ra pp le
ylo ad co m m o dation se m bly
G ra pple T ethe r
T ethe r D ep lo ym en t a nd R etrieval M echan ism
G ra pp le A ssem b ly H ousing fo r T ethe r R ee l, A vion ics, R C S F ue l, B atteries, a nd B attery R ech argin g C ircu its
G ra pp le
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The Hoytether™ Design will survive meteorite strike cuts or material failure of primary lines
Primary Lines
First Level of Secondary Lines Redistributes Load to Adjacent Nodes
Secondary Lines (initially unstressed)
Effects of Damage Localized Second Level of Secondary Lines Redistributes Load Back to Undamaged Portion of Primary Line
Severed Primary Line
0.2 to 10's of meters
0.1- 1 meter
a.
b.
c. 11
Rotovator™ Tether and Hypersonic Airplane Rendezvous occurs at 100 km, 4.1 km/sec
Center-of-Mass Velocity
TETH-1017 200
100 80
150 Tether Tip Altitude (km)
Tether 60 Tip Temperature 40 (C)
100 50
0
20
675
700
725
750
775 Time (s)
800
825
850
0
675
700
725
750
775 Time (s)
800
825
850
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Phase I Results Show Feasibility of Payload Capture
• Tether-Payload Rendezvous Capability is a Key Enabling Technology • TUI Has Developed Methods for Extending Rendezvous Window – Works in Simulation – Validation Experiments Needed
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Simplified Grapple Approach Selected for Phase I
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Other Grapple Concepts Have Been Investigated; Baseline Approach Will Be Revisited in Phase II 1. Cable with tip grapnel flies by tether Tether
v
Tether
2. Tether tip lifts upward, grapnel snags cable.
Barbed Grapnel
v GRAPPLE TO PAYLOAD ATTACHMENT OPTION Grapple / End mass comes down on Payload
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Radially moving Levers move to ring and secure P/L
Grapple stops on Payload, levers on payload are in "in-close" position
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Payload Surface
3
Attach Levers then move radially outward toward ring; sliding on rails. Once contact with ring is made, they latch to the ring securing the payload to the grapple.
Grapple Ring
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HASTOL Phase II Study Tasks • Mission Requirements and Mission Opportunity Definition • System Requirements • System Concept Definition • System Analysis • Technology Development Roadmap (near term demos)
• Contract Schedule/Key Milestones: • First 12 of 18 month program funded • Concept Definition and System Analyses will be nearly complete by end of 12th month 16
HASTOL Phase II Study Schedule Task Names
2001 2000 Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec
1. Mission Opportunities Definition (SOW 1.0) 2. System Requirements Definition (SOW 2.0) 3. Conceptual Design (SOW 3.0) 4. System Analysis (SOW 4.0) 5. Technology Development Planning (SOW 5.0) Program Management Program Management and Reporting Reports Monthly Reports Midterm Report Final Report Program Reviews
Program Kick-off
NIAC Annual Meeting
NIAC Fellows’ Conference
Final Program Review
TETH-1010
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HASTOL Phase II Study Approach P h a se I R es ults
• R o to va to r co nce pt • T echno lo g y R ea dine ss Le ve l 2 syste m s (h yp e rson ic a irplane , te ther co n tro l station, te ther, grapp le a ssem b ly, pa yload accom m o da tion a ssem b ly) • T ra de stud y re su lts: d isco ve ry tha t re n de zvou s p oin t ca n be a ch ieved by e xistin g airp la ne (X -4 3) w itho u t o ve rhe a tin g te th e r tip • S e lected con cep ts - D F -9 h yp e rson ic ve h icle - R e nd ezvous p o in t a t M a ch 10 , 10 0-km altitude - H o yte therTM w ith S p e ctra2 00 0T M m a te ria l a nd PB O tip m a te ria l H yp e rs on ic A irp lan e S pa ce T ethe r O rb ita l L aun ch (H A ST O L ) S tud y P rog ra m , P hase II
T a s k 1 M iss io n O pp o rtu nitie s D e fin itio n • D eve lo p con ta ct p la n • C on du ct kick-o ff w ith p o ten tia l cu sto m ers a nd N IA C • M ee t w ith cu stom e rs to a sse ss p ote n tia l m issio ns a nd nea r-te rm ap p lications • Id en tify o p po rtunities to in tegra te into N A S A p rog ram s
T a s k 2 S y s te m R e q uire m en ts D e fin itio n C an dida te list o f m ission nee ds
• D erive pre lim ina ry syste m re q uirem e nts fo r ea ch o f th e H A S T O L syste m s • D ete rm ine pa yloa d cha racte ristics, traffic rate, g uid an ce and co n tro l, g -fo rce lim itations, in itia l a nd life cycle co sts, a n d syste m in te rface re qu ire m en ts • Id en tify, de fin e, allo ca te , a nd tra de m a jo r syste m re qu ire m en ts
T a s k 3 C o n c e ptu al D e sig n • Integ rate in to system arch itectu re • C onduct tra de stud ie s • D e velop R O M co st e stim a te
T a s k 5 Tec h n o lo g y D e ve lo p m e n t P la n n ing • • -
Ide n tify te chn o lo gy ne ed s D e velop techno log y de velop m e nt roa dm ap F lig ht te st p lan L a bo ra tory tests
T a sk 4 S y s tem A n a lys is • C onduct m od e ling and sim ula tio n s • C onduct pre lim ina ry te chn ica l a sse ssm ent - Ide n tify h igh-risk are a s - D e velop m itiga tion p lan s
P h a s e II D elive ra b le s • •
•
F ina l P ha se II p rog ram review P ha se II fin a l repo rt – S ystem re quirem ents – A na lyze key tech n ica l issu es – C om p le te system de sig n con cep t to T R L 3 ✔ GN&C – A rea s o f d eve lop m e n t w ork n eed ed ✔ P ayloa d transfe r op era tion s – T e chnolog y ro ad m ap ✔ T e th er de sign an d d yn am ics – C o st m ode ls ✔ M aterial se le ction P ha se III cu sto m e r fun d ing co m m itm en t ✔ S im u la tion re su lts
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System Analysis Tasks Address Areas of Concern •
Detailed rendezvous and payload capture simulation will identify payload grapple requirements
•
Abort modes will be investigated -- what if payload is not captured?
•
Payload release orbits
•
Cost modeling -- compare HASTOL to other launch system architectures
•
Tether dynamics and associated interaction with grapple assembly
•
Tether material survivability in space environment
•
Electrodynamic thrust control for reboost and orbit transfer
•
Collision avoidance of known orbiting assets
Technology Development Roadmap will identify near term demonstrations needed for low risk flight demonstration. 19
Roadmap Identifies Stepwise Technology Demonstration and System Development, Production and Deployment Task Names
1994 1995 1996 1997 1998 1999 2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 94 95 96 97 98 99 00 01 02 03 04 05 06 07 08 09 10 11 12 13 14
Applicable Tether Experiments Plasma Motor Generator SEDS-2 TSS-1R TIPS ISS Tether Reboost ProSEDS Applicable Hypersonic Aircraft Contracts Dual Fuel Vehicle Study Hyper-X Flight Test Program Dual-Role Vehicle Study Airbreathing Launch Vehicle Study Boeing / TUI Contracts MMOSTT HASTOL Follow-on Technology Demonstrations Typical Technology Demo No. 1 Typical Technology Demo No. 2 Typical Technology Demo No. 3 Operational System
Phase 1 Phase 1
Phase 2 Phase 2
Operational System Production
Operational System Deployment
Prototype Demonstration Program TETH-1023
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Additional Near-Term Studies Can Assess Feasibility and Identify Key Flight Demos • Automated Rendezvous & Capture – Time Window for Capture < 10 Seconds – High Accuracy Requirements
• Electrodynamic Tether Operation – High Power & Voltage Issues – Control of Tether Dynamics
• Traffic Control/Collision Avoidance • Economic Analysis/Business Plan – Technology Risk Reduction – Incremental Commercial Development Path – Customer Acceptance
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Near-Term Flight Experiments will Validate Feasibility for Prototype System Development • Spinning Tether Orbital Transfer System - STOTS – – – – –
Deploy Small Payload on a Tether Demonstrate Spin-Up of Tether System Using Reeling Demonstrate Controlled Toss of Payload Build on SEDS Heritage Piggyback on Delta II Launch
• Tether Orbit Raising Qualification Experiment - TORQUE – – – – – –
Deploy Hanging Tether Below Small Facility Demonstrate Payload Rendezvous & Docking with Hanging Tether Demonstrate Electrodynamic Spin-up of Tether Demonstrate Controlled Toss of Payload Demonstrate Electrodynamic Reboost of Facility Perform Repeated Boosting of Commercial/Scientific Payloads 22
Tether Systems Have the Potential to Enable Low Cost Access to Space • Concept feasibility study already completed. • Key targets for technical risk reduction have been identified. • Tether experiments have already flown in space. • Planned near term experiments further reduce potential system risks. • Phase II analyses will reveal near term demonstrations and flight experiments required for full scale system development. • Modest near term government investment is encouraged to fund demos and experiments. 23