Title: Highly Operable Propulsion System Approaches and Propulsion Technologies for Operationally Responsive Space Systems
1Highly Operable Propulsion System Approaches and
Propulsion Technologies for Operationally
Responsive Space Systems
April 22, 2004
Russell Joyner Discipline Chief - Space Systems
and Mission Analysis Performance Systems Analysis
Integration
2Presentation Outline
- Introduction
- Responsive Space, Historically Speaking
- Spirally Develop with A Focus
- Ground Rules for Study Responsive Small Launch
Vehicle - Analysis Process
- Results TSTO RSLV Spiral 0-1
- TSTO RSLV Spiral 0-1 Geometry Comparison
- Spiral Development from TSTO RSLV to HTO-RSLV
- Horizontal Take-Off (HTO) RSLV Concept Trades
- HTO RSLV Concept Comparison to Legacy Systems
- Boil Off Issues for Cryogenics - Impact of
Integrated Thermal Management Unit (ITMU) - Summary Of Observations
3Introduction
- AFSPC 001-01/02 Operationally Responsive
Spacelift (ORS) and Prompt Global Strike Mission
Needs Statement Decomposition - .. capability to rapidly put spacecraft into
orbit - .. maneuver spacecraft to any point in
earth-centered space - .. logistically support them on orbit or return
them to earth - .. strike globally and rapidly high value
difficult to defeat targets in a single or
multi-theater environment - Operationally Responsive Spacelift Needs
Architectures that Support an Over-arching Vision
That Can Evolve - Spiral Development, Merging of Technical
Capability and Budget Realities - A Spiral Development Approach for ORS Needs A
Roadmap that Includes the Present and the
Possible..Technologies on the Shelf or at High
Readiness - An Approach for Creating the Roadmap from an
Operationally Responsive Propulsion and
Propellants Point of View - Evolve to Higher Responsiveness By Spiraling
in Upgrades to Propulsion, Propellants,
Propellant Management, and Dispersed Launch
Capability
4Responsive Space, Historically SpeakingUse of
Cryogenics for Propellants Was Successful Because
of Focused Process and Mission
Jupiter
- Time to Launch lt20-minutes
- Total Propellant Loading in 15-minutes After
Launch Commit Was Issued
110,000 lbs.
Titan I
Thor
220,000 lbs.
105,000 lbs.
Images Courtesy Strategic Missile Website
5Spirally Develop With A FocusVisionary (But
Focused) Approach Needed Early to Meet Full
Operational Responsiveness Needs
- Original F-16 was designed for an important, but
limited role as only an air-to-air fighter
aircraft - But Evolved to Be More Multi-Mission Capable
- Data ONE Team Payload Sensors Presentation Jan
2002
- A Responsive Small Launch Vehicle Could
Spirally Evolve Into a Highly Responsive Launch
Architecture - A Total Systems Architecture Vision Is Needed
A Horizontal Take-off Type RSLV Carrier?
?
Images Courtesy Space Exploration Technologies
Inc., aviation-history.com,Boeing WEBSITES,
6Ground Rules for Study Responsive Small Launch
Vehicle (RSLV)
- Notional Two Stage To Orbit (TSTO) RSLV As
Baseline Concept (e.g. Similar to Current TSTO
Approaches Coming On-line) - Orbit Notional Mission 1,700 pounds to 100/28.5
- LOX/Kerosene Propulsion and Propellant as
Baseline - Boost and Upper Stage Performance Per Optimum ISP
Nozzle Area Ratio and Max Diameter Per Stage
Diameter, O/F, and 2 Combustion Chamber Designs - Low Pressure, lt 500 Psia Higher Pressure,
750-900 Psia - Pressure Fed for lt 500, Gas Generator and
Expander Cycles for 750-900 - Start With LOX/Methane and 98 Hydrogen
Peroxide(HTP)/Solid Fuel Hybrid Evaluated for
Upper Stages and Booster Propulsion - Take LOX Operability As workable Per Historical
Systems and Current Experience - Look at Methane (Tboil (K) 112) ... versus (Tboil
(K) 90 for LOX) - 15 Seconds ISP increase over Kerosene, O/F 3.5
versus 2.7 Gives Average Bulk Density Difference
20 Which Trades With Lower Required Propellant
Fraction - Look at HTP/Solid Hybrid To See How The
Performance Differences Vary So System Cost
Attributes Could be Investigated - Look At General Thermal Storage Impact for
Sized Vehicle Propellant Loads - Evaluate Carriage of Sized Systems for Higher
Responsiveness Level 2 Spiral
7Analysis Process
DEFINE ALTERNATIVES FOR HIGHER RESPONSIVENESS
- Start With Concepts Based on Available
Hardware, Investigate Spiral Development
Elements - Define Notional TSTO (2-stage) Responsive Small
Launch Vehicles LOX/Kerosene Propellants - Fly-off with POST (Trajectory Code) to
100nm/28.5 Nominal Mission, Re-size to Meet
1,700 pound Payload (Performance for Systems
Flying 1,000 to Higher, Polar Orbits - Evaluate Alternative Engines/Propellants As
Spiral Evolutions to Base Notional Concept
SUMMARIZE RESULTS AND VALIDATE WITH DATA BASE
8Results TSTO RSLV Spiral 0-1
9TSTO RSLV Spiral 0-1 Geometry Comparison
- Objective Achieve Greater Responsiveness with
Core and Evolve Via Spiral Development to be
Fully Responsive With Technology Insertion via
Upgraded Stage Propulsion and ITMU Usage
Images Courtesy Strategic Missile Website
75 ft
58 ft
64 ft
58 ft
58 ft
Design the Spiral Development Elemental Steps
In At the Beginning To Avoid Encroachment On
Objective Responsiveness
Payload(lb) 1,700 1,700 1,700 2,300 1,700 GLOW(
lb) 64k 144k 52k 68k 72k Empty(lb) 3.7k 18k 4.7k 4
.2k 11k
10Spiral Development from TSTO RSLV to HTO-RSLV
High Pressure Hybrid Boost or S/O LOX/Methane U/S
Level 2 Spiral Options
High Pressure LOX/Kerosene Boost LOX/Methane U/S
Level 1 Spiral
High Pressure All LOX/Kerosene
Level 0 Spiral
Horizontal T/O Hybrid Boost or S/O LOX/Methane
U/S
11Horizontal Take-Off (HTO) RSLV Concept Trades
Other A/C TOGW(lb) For Comparison C-17 585,000 B-
1B 477,000
12HTO RSLV Concept Comparison to Legacy Systems
TOGW(lb) 160,000 Payload(lb) lt70,000(LEO
3,000) Empty(lb) 74,000 Mach max
3.5 Sref(ft2) 1,600 Length(ft) lt 100, b_span 65
ft Runway Field Length lt 5,500 ft, T/W 0.5
USAF/General Dynamics B-58 Hustler TOGW(lb) 163,
000 Payload(lb) lt 40,000 Empty(lb) 56,000 Mach
cruise 2.2 Sref (ft2) 1,550 Length(ft) 97,
b_span 56 ft Runway Field Length lt 7,900 ft, T/W
0.3
13Boil Off Issues for Cryogenics - Impact of
Integrated Thermal Management Unit (ITMU)
NASA/GRC Has TMS/ZBO Designs Evolving To Higher
Tech Readiness
Images Courtesy NASA GRC
14Summary of Observations
- Responsive Spacelift Must Be Approached With A
Careful Spiral Development Approach - A RSLV system must also keep trading off how the
system meets affordable cost criteria, obtains
high reliability and low maintenance, and has the
performance to deliver a wide range of payload
that could go as low as 100 pounds or as high as
12,000 pounds to LEO - Most likely not done by a single launch vehicle
design due to the affordability trade-offs but by
some combination of stages that builds off the
base design without compromising the
Demonstrated Responsiveness - To Meet Global Reach and Rapid Spacelift Mission
Needs, Systems Must Respond in Minutes Like
Current Military Aircraft - The Goal Should be Spirally Develop Systems
Using Evolved Propulsion Technologies With A
Strong Focus on Operability Within a Military
Mission Environment (e.g. F119, RL10) - Evolve them to formulate a reliable,
Operationally Responsive Spacelift and on-orbit
architecture - Evolve in innovative use of air-breathing
propulsion, employment of soft-cryogenic fuels
and oxidizers, low cost hybrid motors, and an
integrated vehicle-engine health management
system to create higher levels of operational
responsiveness - An Operationally Responsive Propulsion Roadmap
can be Created Using This Approach to Support
Evolving Responsive Spacelift And Systems Needs
for the Military Forces of the United States of
America
15BACKUPS
16Possible Sweet-spot Evolved HTO
17Process and Physics Driven Cost
1820Klb Methane Expander Engine Concept
CH4 In
O2 In
25
43
200
175
13.8
48.4
FIV
OIV
Main Turbine Inlet
Total Area Ratio
FSV
990
591
70 1
880
800
742
OFC
179
Regen Area Ratio
1549
13.0
13.0
48.4
216
10 1
13.8
Vacuum Thrust
Main Turbine Exit
591
22,000 lbf
742
500
Vacuum Isp
Regen section
13.0
6244
1010
353.2 sec
62.3
800
13.8
Turbine bypass0.8 lb/s
Radiation-cooled skirt
1920Klb Methane Expander Engine Concept Attributes
Indicates Previous Risk Reduction
Leverage current RL10 hardware - O2 turbo pump
and fuel turbo pump - Fuel and oxidizer inlet
valves - Main fuel and main oxidizer valves -
Thrust control valve - Cool down valves -
Pneumatic control approach
Alter Gear Ratio Between Fuel and Oxidizer Pumps
Regeneratively or radiativelycooled nozzle
20Klb ThrustCH4/O2Systems Integration
RL10 CH4 History
Minimum modifications to existing injector
Use existing 40Klb test chamber
Insert new TCA technology
Low Risk CH4 Expander Demo
20The Symbiotic Hybrid As Part Of an RLV
Key Features No Additional Turbomachinery Low
Risk Pressurization Flow Uses LOX tank
pressurant from vehicle main
engines Affordability Thrust Augmentation
Modular development Benign environments Low
complexity Low cost fuel canisters
21Notional HRC Characteristics For Hybrid Motor
Leverage HPDP Technology
Fixed Nozzle Baseline
Simplified HRC characteristics derived from HPDP
program (PW team member)
Low Cost Monolithic Graphite Case
22Firebolt/HAST Hybrid Propulsion System First
Production Hybrid with Flight Maturity--Demonstrat
ed Throttling Capability
Hybrids have gone to production and flight
status before..