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FY98SPACE AND MISSILES
TECHNOLOGY AREA PLAN
HEADQUARTERS AIR FORCE MATERIEL COMMANDDIRECTORATE OF SCIENCE & TECHNOLOGY
WRIGHT PATTERSON AFB, OH
DISTRIBUTION A. Approved for Public Release; distribution unlimited.
“Note: This Technology Area Plan (TAP) is a planning document for the FY98-03 S&T programand is based on the President’s FY98 Budget Request. It does not reflect the impact of the FY98Congressional appropriations and FY98-03 budget actions. You should consult PL/XP, DSN 246-4962 or Commercial (505) 846-4962 for specific impacts that the FY98 appropriation may have hadwith regard to the contents of this particular TAP. This document is current as of 1 June 1997.”
About the cover:
Pictured on the cover is an artist’s concept of the MightySat II spacecraft. Orderly and routine dem-onstrations provide flight heritage of emerging space and missile technologies prior to their transitionto the operational user. MightySat II is a three-axis stabilized spacecraft generating 325 watts ofpower for satellite and payload operations. The first of a series of five spacecraft will fly in FY00,flying nine experiments developed under the Space and Missiles and Directed Energy TAPs. Amongthe Space and Missile technologies aboard MightySat II are multifunctional structures, the isogridsolar array, composite structures, shape memory alloys and Microsystem and Packaging for LowPower Electronics (MAPLE). MightySat is tailored to fly technologies developed within the AirForce laboratories and supports the test of payloads as well as experimental bus components.
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VISIONS & OPPORTUNITIESSpace & Missiles
Rapid and cost effective research, development andtransition of advanced space technologies enables afford-able and decisive military capabilities for US forces. TheSpace and Missiles Technology Area Plan is developingtechnologies that provide options for the warfighter thattake maximum advantage of space as an operating envi-ronment. In the face of declining budgets and manninglevels, constraints are placed on the S&T programs. Weconstantly strive tomake technologyinvestments in thehigh payoff areas.Our investmentstrategy empha-sizes improvedproductivity atreduced cost. Theneed for afforda-bility is a perva-sive requirementthat is emphasizedthroughout allaspects of theSpace and MissilesTechnology AreaPlan.
The breadth oftechnologies pur-sued in the Spaceand Missile Tech-nology Area Planis driven by spe-cific military operational needs described in the FutureJoint Warfighting Capabilities. These are:1. To maintain near perfect knowledge of the
enemy and communicate that to all forces innear-real time.
2. To engage regional forces promptly in deci-sive combat, on a global basis.
3. To employ a range of capabilities which allowachievement of military objectives with mini-mum casualties and collateral damage.
4. To control the use of space.5. To counter the threat to the CONUS and de-
ployed forces of future ballistic cruise mis-siles and other weapons of mass destruction.
We respond to these warfighter needs through the AirForce mission area planning process. The Air Force op-erational needs are described in terms of deficiencies,operational concepts, and technology needs to meet userrequirements.
Our technology investments in support of the war-fighter will be focused into Global Engagement andGlobal Presence, or what we call Global Virtual Pres-ence. Global Virtual Presence is the ability to know andunderstand what is happening anywhere, anytime in thebattlespace environment, and to be able to engage mili-tarily, in real or near real time, with graduated levels ofresponse, to meet national objectives. Global Engage-
ment, Global Pres-ence -- instant aware-ness, global domi-nance in air andspace, and omnipres-ence with space basedsensors and weapons -- will allow proactivereactions with a widerange of graduatedlevels of response to awide variety of levelsof tension in the bat-tlefield of the 21stCentury.
We implement theover arching vision ofGlobal Virtual Pres-ence by formulatingfour major technologyEnterprises that pro-vide focus and direc-tion to our technologyinvestment plans.
These four Enterprises are:• Protection Enterprise• Space Force Projection Enterprise• Remote Sensing and Surveillance Enterprise• Space Operations Enterprise
The underlying technology base conducted in the Spaceand Missiles Technology Area Plan cuts across, and tosome degree is interwoven between, these four Enter-prises.
The Protection Enterprise provides focus and directionto technology investments that assure the survival of ourspace systems, whether the threat is natural or man-made. This Enterprise is broadly defined to address eve-rything from radiation hardened electronics and sensorsto threat warning and attack reporting. It will includeboth passive and active techniques for self protection aswell as the development of protocols for debris manage-ment and mitigation. In addition, a major objective inthis enterprise is to advance the understanding of the
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effects of interactions between the environment andmilitary systems and provide guidance to designers ofadvanced systems to ensure increased survivability andreduced weight and cost. Our space assets and capabili-ties must have assured survivability at any level of adver-sarial hostility.
The Space Force Projection Enterprise provides focusand direction to technology investments that address theapplication of force from and through space to points inspace, in the air and on the ground. The scope of thisEnterprise is wide and includes leading technology ini-tiatives in areas such as the Military Space Plane, SpaceBased Lasers and ballistic missile systems. Though cur-rent treaty implications limit the actual fielding of weap-ons in space, low end capabilities providing entry levelsof graduated deterrence are needed now. The technologybase required to met future space weapon needs must bedeveloped and matured today if it is to be available forfuture warfighter needs.
The Remote Sensing and Surveillance Enterprise pro-vides focus and direction to active and passive technologyinvestments that assure innovative and revolutionarytechniques for detecting and determining adversarialthreats. This investment will form the foundation of thetactical situation awareness for the 21st Century. Classi-cal, wide area surveillance will continue to be a criticalAir Force mission area, but this Enterprise will specifi-cally address advanced technologies for tactical theaterarea interrogation and high value targeting that will beused for cueing other sensor and weapon systems. Acritical part of theater information will be the knowledgeof the battlespace environment, and this Enterprise willprovide the capability to observe, model, and predict en-vironmental conditions encountered by the warfighter atany time, anywhere on the globe. These revolutionaryremote sensing tools will allow a level of situationalawareness on the ground, in the air and in space that hasnever before been available to the warfighter.
The Space Operations Enterprise provides focus anddirection to technology investments critical to the in-creasingly important operation of the Air Force in space.Satellite autonomous operation will usher in a new era of“information on demand” satellite systems, with inter-connected constellations of satellites precisely providingthe information that the warfighter needs, when it’s
needed, where it’s needed. Mobility in space coupledwith less expensive and easier access to space is a key toAir Force dominance of the space arena. Decision aidsmust be developed for mission planning and operationsthat specify the expected performance of military systemsbased on anticipated conditions in the environment. TheAir Force of the 21st Century will have to move in andthrough space with the same ease that it now moves inand through the atmosphere. Orbit transfer propulsionsystems will be key to this essential capability. Spacesystems will cost less, last longer, and perform betterthrough improved capabilities in payload thermal man-agement; payload stabilization; power generation, storageand management; on-board processing capability, dataprocessing and communication. Deploying these capa-bilities in the space environment will be made more af-fordable through investments in lighter and higher per-formance lift systems, improvements in design, integra-tion, and operation processes, component weight reduc-tion, and operation and control technologies.
To meet these aggressive goals for the Air Force’s rolein Space, we will leverage our efforts with industry andother government agencies to mutually exploit technol-ogy innovation as part of our vision for future technologydevelopment and transition. An emphasis is placed ondirect commercial exploitation, assessment of commer-cial off-the-shelf technology for military application, andcooperative research and development with industry,academia and other space focused government organiza-tions.
The situational awareness afforded throughout the bat-tlespace -- on the surface of the earth, in the air and inspace -- provides the means for aerospace supremacy,enabling the full range of options for other weapons sys-tems employed in the theater. These investments providethe nation not only a precision, global strike capabilitywith minimum casualties and collateral damage, but alsothe possibility of strategic deterrence, flexible responses,and the ability to influence events in real time, therebyproviding the warfighter with a continuous range of re-sponse options, varying from lethal to non-lethal. This isGlobal Virtual Presence and this is the vision of theSpace and Missiles Technology Area Plan. We have theopportunity to lead the Air Force into the Space Force ofthe 21st Century.
“This plan has been reviewed by all Air Force laboratory commanders/directors and reflects integrated AirForce technology planning. I request Air Force Acquisition Executive approval of the plan.”
RICHARD R. PAULMajor General, USAFTechnology Executive Officer
MICHAEL L. HEIL, Colonel, USAF CommanderPhillips Laboratory
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CONTENTSPage
Visions and Opportunities i
Introduction 1
Program Descriptions
Thrust 1: Boost and Orbit Transfer Propulsion Technology 6
Thrust 2: Spacecraft and Tactical Propulsion Technology 8
Thrust 3: Space Vehicle Technologies 10
Thrust 4: Advanced Space Technology Integration and Demonstration 14
Thrust 5: Space Mission Technologies 17
Thrust 6: Space System Technologies 22
Thrust 7: Battlespace Communications and Operations 24
Thrust 8: Optical Surveillance Effects and Battlespace Operations 27
Glossary 30
Index 32
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INTRODUCTIONSpace & Missiles
BACKGROUNDThe Space and Missiles Technology Area, highlighted
in Figure 1, is that part of the Air Force Science andTechnology (S&T) Program charged with developingevolutionary and revolutionary technology for space andballistic missile systems. It also includes the formerGeophysics Technology Area, which advances Air Forcewarfighting capabilities by providing technology to de-fine, understand, and control interactions between all AirForce systems and their battlespace environment.
The programming reflected in this Technology AreaPlan (TAP) is coordinated and aligned with variousTechnical Planning Integrated Product Teams (TPIPT) toaddress user requirements and provide visionary oppor-tunities for technology push. The TPIPTs, in turn, re-ceive far- and near-term requirements of the space andmissile community both through the validated MAJCOMrequirements in the Mission Need Statements, Opera-tional Requirements Documents, and Mission Area Plan(MAP) Deficiencies. Technology requirements to sup-port advanced systems are generated by the Product Divi-sions with laboratory support. Both technology push and
pull enable substantial payoffs for AF systems.
Figure 2: S&M S&T $ vs AF S&T $
This document details the implementation of the SpaceForce Enhancement TPIPTs’ technology developmentplans and includes needs, goals, major accomplishments,and changes from last year.
The program de-scribed in this TAP issubject to change basedon possible congres-sional action.
The President’sFY98 Budget Requestincludes an AF S&Tfunding total to PhillipsLaboratory (PL) ap-proaching $136M toperform exploratoryand advanced technol-ogy development forthe Space and MissilesTechnology Area (ref.Figure 2). Additionally,Ballistic Missile De-fense Organization(BMDO), DefenseAdvanced ResearchProjects Agency(DARPA), NASA, andothers also provide sig-nificant funding to PLfor Space and MissileS&T (ref. Figure 3).The total budget is dis-
AEROPROPULSION& POWER
AIR VEHICLES
AVIONICS
HUMAN SYSTEMS C3I
SPACE &MISSILES
MATERIALS &PROCESSES
DIRECTEDENERGY
RESEARCH
WRIGHTLAB
ARMSTRONGLAB
AFOSR ROMELAB
PHILLIPSLAB
PE 62601FPE 63302F
PE 63410FPE 63707F
AFAE
TEO
CONVENTIONALARMAMENT PE 63311F
PE 63401F
Figure 1: Air Force Science and Technology Program Structure
Estimated AF S&T Budget for FY98: 1.203 B
AF S&T Balance
S&M ($136 M)
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tributed across a range of both in-house and contractualprograms.
Maximum leverage of these R&D investments is ac-complished through the broad base of the Space and Mis-siles Technology Area supporting many AF mission ar-eas. Towards meeting these AF, and DoD, mission areaneeds, technology efforts in the Space and Missiles TAPare managed along eight technology thrusts, as listed inTable 1 and funding among these thrusts as shown inFigure 4:
Table 1: S&M Technology Thrusts
1. Boost and Orbit Transfer Propulsion Technology2. Spacecraft and Tactical Propulsion Technol-
ogy3. Space Vehicle Technologies
4. Advanced Space Technology Integration andDemonstration
5. Space Mission Technologies6. Space System Technologies7. Battlespace Communications and Operations8. Optical Surveillance Effects and Battlespace
OperationsThe majority of the S&T programs in these technology
thrusts proceed from basic research, to exploratory devel-opment, to advanced technology development, and in-deed to technology transfer/transition. (Exception: Geo-physics programs differ from other technology areas inthat the advanced technology program delivers manyS&T products directly to customers for operational de-velopment, such as the 55th Space Weather Squadron,rather than to an intermediary SPO.)
Recent accomplishments in the Technology Thrustsfollow:• A small Solid Oxygen (SOX) Engine was developed
and fired. This project demonstrated that cryogenicsolids can be burned in a hybrid rocket geometry. So-lidifying the oxygen increases the oxidizer density andprovides a means of storing other energetic oxidizers,such as ozone. Adding 50% ozone in solid oxygen in-creases the specific impulse of a hydrogen-oxygen/ozone system by 20 sec.
• In the composite space vehicles area, two significantevents occurred. The first was a successful flight dem-onstration of a composite shroud on the BMDO Com-bined Experiments Program (CEP). This flight dem-onstrated a 61% mass savings and 88% savings inmanufacturing time over conventional shrouds. Thesecond accomplishment was the delivery of the Ad-vanced Composite Experimental Spacecraft Structure(ACESS), which will be used on STRV-2. This pay-load module demonstrates a low-weight, low cost uni-body construction for satellites.
Estimated S&M S&T Funding for FY98 $136 M
Thrust 8
Thrust 2
Thrust 1Thrust 7
Thrust 6
Thrust 5
Thrust 3Thrust 4
Figure 4: Major S&M Technology ThrustFunding
Figure 3: FY97 and FY98 Total Space & Missiles Funding
1997BMDO16%
AF S&T56%
CONG ADD20%
SPOS3%
OTHER5%
DARPA0.2%
1998
BMDO22%
AF S&T74%
OTHER2%
DARPA0.2%
SPOS2%
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• The multi-junction ManTech Solar Cell program dem-onstrated a photovoltaic array with a lot average con-version efficiency of 24.2% for the first time. This rep-resents a 33% improvement over conventional GaAssolar cells and paves the way for meeting the higherpower requirements of future communications satel-lites.
• The thermal management technology area had a suc-cessful flight demonstration of the liquid metal heatpipe on STS-77. This demonstrated the highest everoperating temperature for a heat pipe, approximately900°C.
• A flight of the Missile Technology Demonstration 2(MTD 2) was conducted on 29 January 1997. MTD 2tested range safety, missile electronics, and penetratortechnologies for ballistic missiles. MTD 2 utilized anactive on-board differential GPS/IMU for flight navi-gation in addition to the range safety metrics demon-strated on the flight’s predecessor, MTD 1. ThreeGPS/INS packages were independently demonstratedon the flight.
• By reconfiguring the design of the Advanced Technol-ogy Insertion Module Single Board Computer and us-ing an advanced Aluminum Nitride substrate, a dou-ble-sided 32-Bit Multichip Module (MCM) was suc-cessfully designed and prototyped. This design re-duced the weight by 10X, size by 15X and provided thesame functionality as the larger version.
• Through innovative design and advanced packagingapplications, a credit-card-size, 70V bus, >90% effi-cient distributed payload power converter (EHF Pay-load Power Converter) was developed. The new designeliminates virtually 80 pounds per converter, and re-duces the volume from ~ 3 cu-ft to ~0.001 cu-ft.
• A GPS Anti-Jam Filter was developed that removes theeffects of five jamming frequencies of various narrow-band formats and reconstructs the GPS signal withgreater than a 95% accuracy. The design was imple-mented after first pass successes for an adaptive trans-fer filter and a 12-bit analog-to-digital converter. Themodule can be used in a real sampling-double channelmode of a complex sampling-single channel mode; iftwo modules are used, complex sampling-double chan-nel mode can be implemented.
• A prototype Scintillation Network Decision Aid(SCINDA) was installed at 55SWS to provide the war-fighter with SATCOM outage regions and help planfor such outages and/or degradation of navigation.This aid also helps identify the source of the outage:equipment failure, jamming or ionospheric effect.
RELATIONSHIP TO OTHERTECHNOLOGY PROGRAMS
The Air Force Office of Scientific Research (AFOSR)supports numerous PL basic research efforts including:
• Research in energetic materials flows directly into theApplied Research In Energy Storage (ARIES) programinvestigating High Energy Density Matter (HEDM)
• Aerospace science research feeds investigations of com-bustion mechanisms, plume phenomena, and plasmadiagnostics
• Space vehicle efforts benefit from basic research inspacecraft dynamics and control phenomena
• Theoretical chemistry research in reactions of atmos-pheric species contribute to models of atmospheric ra-diance used by BMDO
• Atmospheric sciences research improves atmosphericprediction capabilities to understand atmospheric dy-namics and impacts on communications and surveil-lance systems
• Space science research is critical to the development offuture Air Weather Service space weather predictionmodels and future Air Force space surveillance systems.Wright Laboratory (WL) provides manufacturing and
materials technology development for several thrusts:• Manufacturing Technology (MANTECH) provides
methodologies for scaling research materials into pro-duction quantities. Selected propulsion technologycomponents have been carried from exploratorythrough advanced development and become candidatesfor MANTECH demonstrations. The Materials Tech-nology Area (WL/ML) develops materials and proc-esses for lightweight structural applications, high-efficiency multi-junction solar cells, high temperaturerocket engines, thermal protection, sensors and com-munication, and survivability from laser threats. In apartnership with PL, WL/ML transitions materialstechnologies to support PL satellite, launch, and pro-pulsion technologies.
• Other examples of cooperative programs with WL in-clude obtaining infrared (IR) signatures and predictivemodels of aircraft for Air Vehicles. Geophysics pro-grams lead in working with the Avionics TA in usingLidar to measure winds aloft as well as aiding in de-fining trajectories of bombs. Avionics leads in usingLidar to correct the trajectories of cargo, pallets, andprojectiles originating from aircraft.Rome Laboratory conducts joint ionospheric radio fre-
quency (RF) propagation experiments; and ArmstrongLaboratories is provided with space radiation humanhazard data.
Rome Laboratory (RL) and WL conduct 6.1 and 6.2technology programs in the areas of antennas, componentreliability, software, photonics, communications, andsignal processing, which have been transitioned to PL6.2 and 6.3 technology efforts.
PL is an active member on joint government and in-dustry teams working to develop space power technolo-gies for primary and secondary spacecraft systems:
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• Lithium ion battery technology is being developed inclose coordination with WL and other AF agencies.
• NASA supports the development of both nickel hydro-gen IPV and CPV designs.
• The primary battery program is strongly supported byindustry for insertion into commercial launch vehicles.
• A new Flywheel Energy Storage and Attitude ControlProgram initiated in partnership with NASA/LeRCaims to increase the energy storage lifetime for LEOsatellites by a factor of three while significantly re-ducing the combined masses of conventional energystorage/attitude control systems.The Space and Missile TA also has joint activities with
other government organizations, including:• All of PL’s rocket propulsion programs support the In-
tegrated High Payoff Rocket Propulsion Technology(IHPRPT). IHPRPT is an Air Force, Army, Navy,NASA and industry effort to double rocket propulsionscapabilities by the year 2010
• Antenna and EHF component development efforts col-laboratively within Rome Laboratory’s C3I TAP
• Development of infrared sensors for the Air Force MauiOptical Site (AMOS) and Starfire Optical Range;characterization of atmospheric optical turbulence andits effects on laser systems; and remote sensing usingLidars are coordinated efforts with the Directed EnergyTA
• Development of technologies for Advanced MIL-SATCOM program office
• Integration of various databases being developed onradar clutter backgrounds for modeling signal proc-essing algorithms with Lincoln Labs, NASA (under theSIR-C and XSAR shuttle programs), and Georgia TechResearch Institute
• BMDO funded programs in support of kinetic energyweapons; plume phenomenology; small, modular sat-ellites; Advanced Liquid Axial Stage, and AdvancedSolid Axial Stage propulsion systems; adaptive struc-ture technology development; precision pointing ex-periments; and high reliability, low temperature cryo-coolers for cooling IR focal planes and optics
• Development of EHF antenna technology and GPSGuidance Package with DARPA
• Development of high-density memory modules withNASA Goddard Space Flight Center for two satelliteprograms, and production of space-qualified single-layer modules and multi-layer modules next year
• Joint data collection efforts with NASA/JPL SIR-C/X-SAR and TOPSAT critical to active sensor work in theAF
• Modeling and simulation (M&S) efforts supporting theArmy's obscurants modeling and transporter - erector -launcher live simulator development, and the NavalPostgraduate School's Unmanned Aerial Flight Simu-lator
• Passive sensor efforts to address deficiencies in theArmy's USASSDC sensor packaging program
• Coordination of programs with Rome Laboratory,NASA, Wright Laboratory and the other Services inCommunications, Sensors, and Processing and Elec-tronics
• A joint effort with the Army, Navy, and other Air Forceagencies to support the Hardened and Deeply BuriedTargets Defeat Capability (HDBTDC)ACC/STRATCOM Mission Needs Statement (PL inte-grates HDBTCD needs into its Ballistic Missile Tech-nology efforts through its Missile Technology Demon-stration flights.)
• System checkout of the Linear Aerospike SR-71 Ex-periment (LASRE) flight hardware prior to flight test-ing at NASA Dryden on an SR-71 aircraft (Technol-ogy, data, and lessons from this project will feed intoNASA’s X-33 program.)
Some international collaborative efforts include:• Detector technology developed used by the European
Space Agency (ESA) Infrared Space ObservatorySpectrometer
• Development of detector material technology in con-junction with international partners
• Collaboration on the Shuttle Potential and Return Elec-tron Experiment (SPREE) experiment on the ItalianTethered Satellite System (TSS) flown on the Shuttle(While the deployments of the TSS were unsuccessful,SPREE was an outstanding success since measure-ments agreed closely with predictive models on bothflights, very important to the development of futurelarge space systems.)
CHANGES FROM LAST YEARThe Space and Missiles TAP has undergone a major
restructuring this past year. Thrusts three through eighthave been realigned into four new thrusts. The previousStructures and Power thrusts have been combined intothe new Space Vehicle Technologies thrust. The oldElectronics thrust has been combined with Sensors andCommunications to create the Space Mission Technolo-gies thrust. Satellite Control and Astrodynamics havebeen combined into the Space Systems Technologiesthrust. Finally, Missile Dynamics has been incorporatedas a new subthrust of the Space Technology Integrationand Demonstration thrust.
The overall reduction in the number of thrusts has beenoffset by the incorporation of Geophysics technology intothe Space and Missiles TAP. Two new Geophysicsthrusts appear this year: Battlespace Communicationsand Operations and Optical Surveillance Effects andBattlespace Operations.
The mapping of previous thrusts and the GeophysicsTAP into the current Space and Missiles TAP is shownin Figure 5.
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SM1: Boost and Orbit TransferPropulsion Technology
SM4: Advanced TechnologyIntegration and Demonstration
SM5: Space Power andThermal Management
SM6: Space Sensors andSatellite Communications
SM7: Space VehicleElectronics and Software
SM8: Space Vehicle andMissile Dynamics Technology
GP2: Geophysics for Airand Combat Operations
GP1: Geophysics for SpaceOperations and Communications
SM2: Spacecraft and TacticalPropulsion Technology
SM3: Space VehicleStructures and Controls
FY 97 Thrusts
SM1: Boost and Orbit TransferPropulsion Technology
SM4: Advanced Space TechnologyIntegration and Demonstration
SM5: Space MissionTechnologies
SM6: Space SystemTechnologies
SM7: BattlespaceCommunications andOperations
SM8: Optical SurveillanceEffects and BattlespaceOperations
SM2: Spacecraft and TacticalPropulsion Technology
SM3: Space VehicleTechnologies
FY 98 Thrusts
Figure 5: FY97 vs FY98 Thrust Numbering
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THRUST 1: BOOST AND ORBIT TRANSFER PROPULSION TECHNOLOGY
USER NEEDSThe Air Force Policy of “Global Presence” cites
Situational Awareness and Strategic Agility as ten-ants needing “technological innovations” to “en-hance US ability to exert presence.” The followingSMC Development Plans and NASA requirementsalso demand propulsion improvements to fulfillcritical deficiencies:Spacelift: High Performance, Advanced, Cryogenicand Liquid Rocket Propellants and Engines, LowCost Solid and Hybrid Motors, Low Cost Manufac-turing, High Performance Low Cost ExpendableEngines, Solar Thermal Propulsion (for OrbitTransfer), Advanced Orbit Transfer Concepts, andManufacturing TechnologiesStrategic Sustainment: Motor Aging and Surveil-lanceConventional Deterrence: Missile Propulsion Ma-terial Applications, Global Range and Survivability,Missile Propulsion Technology, Missile PropellantNon-Destructive Test Technology, Solid RocketMotor Manufacturing, ReliabilityReconnaisance/Surveillance: Large PayloadSpacelift SystemsNASA: Advanced Reusable Spacelift, Low CostReliable Access to Space.
GOALSThe propulsion needs identified above will be ful-
filled by achieving the goals set forth in the Inte-grated High Payoff Rocket Propulsion Technology(IHPRPT) initiative. IHPRPT’s vision is to doublespacelift propulsion capability by 2010 through thedevelopment of advanced, innovative rocket propul-sion technology.By 2000, the IHPRPT spacelift goals will:• increase expendable payload to orbit capability
by 9% or reusable payload to orbit capability by71% (over the life of the reusable system) and
• reduce payload launch costs by 19%.By 2010, the IHPRPT spacelift goals will:• increase expendable payload to orbit capability
by 22% or reusable payload to orbit capability by206% (over the life of the reusable system) and
• reduce payload launch costs by 42%.By 2000, the IHPRPT orbit transfer goals will:• double repositioning capabilities (double number
of repositioning maneuvers) or• increase allowable satellite mass by 10%.By 2010, the IHPRPT orbit transfer goals will:• increase repositioning capability by 5 times or
• increase allowable satellite mass by 30%.To meet the spacelift and orbit transfer propulsion
goals, chemical (liquid, solid, and hybrid), solarthermal, and electrical propulsion technology devel-opment is crucial. In response to the aboveneeds, PL develops spacelift and orbit transfer pro-pulsion technology for:• high performance, low cost expendable propul-
sion• advanced liquid and cryogenic reusable and ex-
pendable propulsion• low cost, rapid prototype thrust cell and compo-
nent manufacturing technology• high energy materials for potential use as pro-
pellants• improved ballistic missile motor service life in
both existing and new systems• dramatically reduced manufacturing and support
costs.• developing motor manufacturing processes that
eliminate harmful chemicals used in motormanufacturing
• developing long life, high performance, envi-ronmentally acceptable solid propellants whilemaintaining properties/integrity equal to currentsolid propellants
• chemical and solar thermal orbit transfer appli-cations.
These technologies will provide the technical so-lutions to develop next generation space systems inaddition to upgrades for existing space vehicles. Themajor challenges to achieving the spacelift goals areaddressed by our IHPRPT programs, which coordi-nate our efforts closely with the Air Force, Navy,Army, NASA, and Industry to lower developmentcosts for everyone involved.
MAJOR ACCOMPLISHMENTSA series of U.S. Patents were issued pertaining to
an entirely new polymer technology that was pio-neered and developed at the Phillips Laboratory Pro-pulsion Directorate. The hybrid polymer technologyis being evaluated along with conventional (whollyorganic) high performance plastics as engine duct-ing, trusses, component substructures, cases, andthermal insulation applications in both rockets andspace vehicles.
A small Solid Oxygen (SOX) Engine was devel-oped and fired by the Phillips Laboratory. The ob-jective of this project was to demonstrate that cryo-genic solids can be burned in a hybrid rocket ge-ometry. Solidifying the oxygen increases the oxi-
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dizer density and provides a means of storing otherenergetic oxidizers, such as ozone. It has been cal-culated that adding 50% ozone in solid oxygen willincrease the Isp of a hydrogen-solid oxygen/ozonesystem by 20 sec.
Phillips Laboratory tested an advanced hybridrocket fuel demonstrating that high regression ratesare possible in a hybrid tactical rocket engine. Italso demonstrated that the fuel's regression rate isdependent on the mass flow of the oxidizer ratherthan pressure as is the case with solid rocket motors.PL also tested an oxidizer for hybrid tactical rockets.
This was the first firing using Hydroxyl AmmoniumNitrate (HAN) and demonstrated the application ofHAN as a potential hybrid tactical oxidizer.
CHANGES FROM LAST YEARStrategic sustainment was added to the Boost and
Orbit Transfer Propulsion Technology thrust thisyear. This effort will look at technologies to upgradeand maintain the U.S. strategic missile fleet as wellas transition the technologies into current and futurelaunch vehicles.
Milestones Year MetricsDemonstrate alternative oxidizers for advanced solid propellanttechnology
FY98 Demonstrate solid propellant with theoretical Isp greaterthan 267.5 sec
Demonstrate split line flexseal nozzle at sea level FY98 Show 2% increase in mass fraction and 2% increase in IspDemonstrate 1200psi expander cycle LOX/LH2 upper stageengine
FY99 Demonstrate IHPRPT Phase I goals for upper stage
Develop/test high performance solid motor case FY99 Show 10% reduction in component weight and 15% reduc-tion in component cost
Demo integrated powerhead (IPD) preburner/turbomachinery FY99 Test IPD engine conditions. Quantify performance, oper-ability, and reliability improvements
Develop/test altitude compensating nozzle design FY00 Show 5-10% increase in flight trajectory performance
1997 1998 1999 2000 2001 2002 2003 2004 2004+
Propellant Development
75% Reduction in StageFailure Rate
35% Improvement inMass Fraction (Solids)
26 SecondImprovement in ISP
35% Reduction inHardware Count
35% Reduction inSupport Costs
100% Improvement inThrust to Weight(Liquids)
Responsive, Less CostlySpacelift & SpaceOperations EnablingGlobal Presence
Reduce ELVLaunch/O&S Costs($/lb to Orbit) 33%and RLVLaunch/O&S Costs82%
Increase ELV PayloadCapability 22% andRLV PayloadCapability 95%
Solid PropellantEnvironmental
Issues
Low Cost, Non-Toxic Propellants
High Energy, HighDensity Propellants
Alternate CleanPropellants
High PerformanceOxidizers
Hydrocarbon FuelAdditives
High PerformanceBinders and Fuels
Component Development
AdvancedCombustion Devices
Advanced Materialsfor Solid Motor
Cases
Light Weight ThrustChamber Assemblies
Thrust CellTechnologies
AltitudeCompensating
Nozzles
Upperstage NozzleIntegration
High TemperatureTurbines for LH2
Demonstrators
LOX/LH2 Upper StageElectric OTV- 30 kW Arcjet
Advanced OTV- Solar ThermalIntegrated Power-Head Demonstration
Cryogenic Booster
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THRUST 2: SPACECRAFT AND TACTICAL PROPULSION TECHNOLOGY
USER NEEDSThe Air Force Policy of “Global Presence” cites
Situational Awareness, Strategic Agility and Lethal-ity as tenants needing “technological innovations” to“enhance US ability to exert presence.” The fol-lowing SMC/AFSPC, ACC and NASA DevelopmentPlans require propulsion improvements to fulfillcritical deficiencies:Missile Offense, Air to Surface, and Counterair:Motor Service Life Prediction and Extension, HighPerformance Environmentally Acceptable Propel-lants, Low Cost Environmentally Acceptable Manu-facturing ProcessesConventional Deterrence: Missile Propulsion Ma-terial Applications, Global Range and Survivability,Missile Propulsion Technology, Missile PropellantNon-Destructive Test Technology, Solid RocketMotor Manufacturing, ReliabilityReconnaissance/Surveillance: Cost and Surviv-ability, Prompt Response without Force Deployment, Long Range Strike CapabilityCounterspace, Missile Warning: SurvivabilityMissile Defense: Survivability, Propellant Devel-opmentNon-Space: Fast Reaction Tactical Missiles, LessTime to Target, Increased Range, Throttle on De-mand, Low Cost, Increased Environmental Compli-ance.Satellite: Advanced Propulsion/Power Conversionfor Electric Propulsion (for Stationkeep-ing/Maneuvering)Weather: Small Satellite TechnologyNavigation: Modernization of Current Systems,Upgraded Future Systems to Replace Current Sys-tems with Lower Power Consumption, ImprovedPower Conversion, Advanced Attitude Control, Ad-vanced Electric Propulsion and Solar Propulsion.
GOALSThe propulsion needs identified above will be ful-
filled by achieving the goals set forth in the Inte-grated High Payoff Rocket Propulsion Technology(IHPRPT) initiative. IHPRPT’s vision is to doublesolid rocket propulsion capability by 2010 throughthe development of advanced, innovative rocket pro-pulsion technologyBy 2000, satellite propulsion systems will:• extend their life in geosynchronous orbit (GEO)
by 25%• double repositioning capabilities (number of
repositioning maneuvers) or
• increase allowable satellite mass by 10% withpresent life span capabilities.
By 2010, satellite propulsion systems will:• extend their life in GEO by 45%• increase repositioning capability by 5 times or• increase allowable satellite mass by 30% with
present life span capabilities.By 2000, the IHPRPT tactical goals will:• increase either warhead payload or range by
10%.• The number of theater missile defense systems
to cover an area can be reduced by 26% for di-vert (steering control) propulsion systems.
By 2010, the IHPRPT tactical goals will:• double tactical warhead payload or range and,• reduce necessary theater missile defense systems
for divert propulsion by 60%.Solar electric and solar thermal spacecraft propul-
sion development is critical to achieve the satelliteimprovements for stationkeeping and maneuvering.PL develops spacecraft propulsion technology for:• pulsed plasma thrusters,• anode layer thrusters, and• solar thermal (laser thermal) systems.
To accomplish the tactical payoffs, solid propellantand motor component development is crucial. ThePL rocket propulsion directorate has the only pro-grams that develop solid rocket propulsion technol-ogy for all Air Force tactical missile systems. PLdevelops tactical propulsion technology for:• developing low signature, high performance
propellants to eliminate tactical missile vulner-ability caused by signature detection.
• developing lightweight, tactical components toallow for increased warhead carriage capabilityor increased range.
• developing longer life, stronger motor compo-nents.
• decreasing production time and costs by utiliz-ing our carbon densification techniques andlightweight coatings.
• decreasing nozzle erosion rates (which increasesreliability, performance, and range)
• increasing oxidation resistance (which also in-creases reliability).
MAJOR ACCOMPLISHMENTSPL researchers have discovered and characterized
one of the major sources of the low pulsed plasmathruster (PPT) thrust efficiency - severe propellantloss mechanisms. This new understanding has fueledthe design of advanced PPTs, presently being tested
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at the PL Electric Propulsion Laboratory, which areexpected to have thrust efficiencies over three timeshigher than present designs.
Two experimental PPTs, designed by PL research-ers and fabricated at the Propulsion Directorate, havepassed their initial functional tests. The PPT’s in-clude the smallest electric propulsion thruster everfabricated and tested.
PL, in cooperation with contractors, developed anew way to design and fabricate spray foam-rigidized solar concentrators. The foam materialand solvent are sprayed onto the back of the reflectorwithin a conical shield so they would not contribute
to the space debris problem. It would cure in UV,then the shield and front canopy could be strippedaway leaving the rigid shell that would only dimplearound areas of micrometeoroid or space debrispenetration.
CHANGES FROM LAST YEARThe goals for the spacecraft subthrust have been
refined. This does not impact any of the long termpayoffs for the subthrust.
Milestones Year Metrics
Design tactical hybrid rocket engine FY98 Demonstrate 5% increase in mass fraction and 7% increase indelivered energy
Develop and integrate hardware for advanced tactical propulsiondemonstrator
FY98 Demonstrate 10% increase in mass fraction and 7% increase indelivered energy
Fabricate high altitude balloon experiment for improved solarthruster
FY99 Demonstrate 10% increase in Isp and 15% increase in massfraction
Develop/test pulsed plasma thruster FY00 Increase MightSat flight capabilities by increasing Isp by 25%and increasing thruster efficiency by 25%
Develop anode layer thruster (ALT) FY00 Demonstrate 15% increase in mass fraction and 15% increasein thruster efficiency
1 9 9 7 1 9 9 8 1 9 9 9 2 0 0 0 2 0 0 1 2 0 0 2 2 0 0 3 2 0 0 4 2 0 0 4 +
Spacecra f t Propu l s ion
2 0 % I n c r e a s e i n I s p( C h e m i c a l / S o l a r T h e r m a l )
3 5 % I m p r o v e m e n t i n M a s sFrac t i on
5 0 % I m p r o v e m e n t i nT h r u s t e r E f f i c i e n c y(Elec t r i c )
4 5 % I n c r e a s e i n S a t e l l i t eL i f e ( a t G E O )
30% Inc rea se i n Sa t e l l i t eP a y l o a d
5 0 0 % I n c r e a s e i n S a t e l l i t eR e p o s i t i o n i n g
P u l s e d P l a s m aT h r u s t e r
D e v e l o p m e n t
A d v a n c e dSpacec ra f t
S t a t i o n k e e p i n gD e m o n s t r a t i o n
H a l l T h r u s t e rD e v e l o p m e n t
I n c r e a s e dP e r f o r m a n c e S o l a rE l ec t r i c P ropu l s ion
S o l a r T h e r m a lSpacec ra f t
D e m o n s t r a t i o n
S o l a r T h e r m a lC o m p o n e n t
D e v e l o p m e n t
2 0 k w H a l l T h r u s t e rD e v e l o p m e n t
Tact i ca l Propu l s ion
L o w S i g n a t u r ePrope l l an t
T a c t i c a l S i g n a t u r eC o n t r o l
H y b r i d P r o p u l s i o nC o n c e p t s
P o l y m e r I n j e c t i o nM o l d i n g
T a c t i c a l H y b r i dE n g i n e
D e v e l o p m e n t
L o w W e i g h t , L o wC o s t T a c t i c a l M o t o r
D e m o n s t r a t i o n
A d v a n c e d T a c t i c a lP r o p u l s i o n
D e m o n s t r a t i o n
1 5 % I m p r o v e m e n t i nD e l i v e r e d E n e r g y
I m p r o v e M a s s F r a c t i o nW i thou tT V C / T h r o t t l i n g 1 0 %W ithT V C / T h r o t t l i n g 3 0 %
1 0 0 % I n c r e a s e i n M i s s i l eP a y l o a d
5 0 % R e d u c t i o n i nN u m b e r o f I n t e r c e p t o r sR e q u i r e d / T h e a t e r
10
THRUST 3: SPACE VEHICLE TECHNOLOGIESThe Space Vehicles Technology Thrust supports the suc-
cessful accomplishment of satellite and launch vehicle mis-sions by conceptualizing, developing, and demonstratingpervasive technologies that enable the use of the most effec-tive payload packages, operating in the optimum environ-ment. This thrust encompasses a wide range of disciplinesincluding structures and controls, thermal management, andelectrical power systems. Whether future systems are large,high power communications or weapons platforms, or small,distributed surveillance packages, technologies are beingdeveloped to reduce weight, reduce costs, and increase thecapabilities of space systems. The ultimate aim is a mas-sless, rigid spacecraft bus with limitless power generationand energy transmission capabilities that provides the opti-mum structural and thermal environment and that costs nextto nothing. The Space Vehicle Technologies Thrust has threesubthrusts: Dynamic Systems, Structural Systems, andSpace Power.
The focus of the Dynamic Systems subthrust is pro-viding vibration control, precision mechanisms, andcryocoolers that enhance the performance of payloads.Key programs in this area include launch load vibrationand acoustic attenuation, 35/60K multistage cryocoolers,and high precision, low-shock deployment devices.
The primary objectives of the Structural Systems sub-thrust are reduced mass and manufacturing costs. Keyprograms include multifunctional structures, advancedcomposite structures, inflatable structures, and large ar-ray antennas. Additionally, the thermal bus focusedtechnology area seeks to provide large heat transport ca-pabilities utilizing loop heat pipes and integrated capil-lary pumped loop systems.
The Space Power subthrust is investigating new waysto generate, store, and distribute power efficiently and inquantities required by future spacecraft subsystems. Keyprograms in this area are Alkali Metal Thermal ElectricConversion (AMTEC), the flywheel energy storage andattitude control cooperative effort with NASA/LeRC, andthe Multijunction Photovoltaic Array ManTech program.
USER NEEDSThe technologies developed in this thrust support many
SMC programs, AFSPC Mission Area Plan deficiencies,and other Air Force space requirements. These includethe following Mission and Functional Area Plans.Space Control: The space surveillance submission areaseeks to monitor activities in the near earth corridor. Tothis end, acquisition, tracking and pointing precisionstructures, very low temperature cryocoolers forbroadband IR sensors, and high efficiency power genera-tion are required. The national missile defense submis-
sion area has identified the need for beam generator iso-lation from expansion and pointing optics
APEX Spacecraft with Photovoltaic Array Solar Power(PASP) Plus Diagnostics Experiment
Space Force Enhancement: The surveillance and threatwarning submission requires the ability to loiter in lowearth orbit (LEO), monitor hostile activities on the earthsurface, and communicate a warning. Cryogenic Cool-ers for 60-150K IR sensors, lightweight structures andantennas, operable smart structures, and high cycle en-ergy storage systems are required to enable this mission.The navigation submission area has identified the needfor lightweight, low cost arrays, while the environmentalmonitoring submission area requires lightweight anten-nas and cryocoolers for the appropriate range of IR sen-sors. For the communications submission area, light-weight antennas, high efficiency power generation anddistribution, and an advanced thermal management busare being developed.
Composite Shroud Winding Tool
Precision Employment: The global prompt strike sub-mission area will employ weapon systems requiring largecapacity cryogenic coolers, high efficiency power gen-eration, and large, lightweight precise structures.
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Space Support: The launch operations submission areahas identified deficiencies for multi-use upper stage pri-mary batteries, effective launch vehicle isolation sys-tems, and strong, lightweight launch vehicle structures.
GOALSFor the three subthrusts which comprise the Space Ve-
hicle Technologies thrust, the near term goals for 2000include the following:• Develop cryocoolers capable of operating in the 10K-
180K range with a 5 year operational lifetime• Develop and demonstrate cryogenic thermal control
system integration technologies that eliminate sig-nificant induced vibration (0.1 Nrms)
• Produce Cryocoolers with reduced power consump-tion (50 W/WCOOLING) and specific mass (8kg/WCOOLING)
• Decrease dynamic launch loads to which a satellite issubjected by a factor of 5
• Reduce pyrotechnic shock to which satellites aresubjected by more than two orders of magnitude
• Decrease on-orbit disturbances experienced by pay-loads by a factor of 10
• Improve total system power performance to 8 W/kg• Reduce Power System Costs to $6,000/W• Improve Solar Cell Conversion Efficiency to 25%• Develop Advanced lightweight and concentrator
arrays with specific power of 100 W/kg• Reduce satellite structural mass by 40% and reduce cost
by more than 10%• Reduce launch vehicle structural subsystem cost by 25%The far term goals for 2010 include the following:• Develop cryocoolers capable of operating in the 10K-
180K range with a 10 year operational lifetime
1997 1998 1999 2000 2001 2002 2003 2004 2004+
Dynamic Systems
- Large PreciseSpace Structures
- PrecisionPayloads on Non-PrecisionPlatforms
- Solid State(LASER)Cryocoolers
- NeuralNetworkControlSystems
- AdvancedModular, Multi-function SatelliteBus
- ExtremelyLightweightLaunch VehicleStructures
- Mini Satellites
- Advanced NaSBatteries
- PASP II FlightExperiment
- Super Capacitors
- SuperconductingEnergy Storage
- Solar ThermalConcentrators
- Thin FilmPhotovoltaics
Structural Systems
Power Systems
35/60K Multi-stage Cryocooler
Composite ShroudFlight Demo
Vibration IsolationAnd Suppression System(VISS) Flight Demo
10KAdvancedCryocooler
Autonomous SystemIdentification
Launch VibrationIsolation System(LVIS)
LightweightSMART Gimbal
Deployable PrecisionStructures for Imaging
Radiation Protectionfrom Composite Structures
Multi-functionalLaunch VehicleStructures
Advanced CompositeInterstage
Filament WoundCryogenic PropellantTank
Large Array Antenna Structure
Advanced Thermal Structural SpacecraftSystem
AMTECGroundExperiment
NaS BatteryFlight Demo
Li Ion BatteryLEO Qualification
Advanced Solar Concentrator Array
Flywheel EnergyStorage and AttitudeControl Flight Experiment
35% EfficientSolar CellProduction
Flywheel EnergyStorage and AttitudeControl Ground Demo
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• Develop and demonstrate cryogenic thermal controlsystem integration technologies that eliminate sig-nificant induced vibration (0.001 Nrms)
• Produce Cryocoolers with reduced power consump-tion (30 W/WCOOLING) and specific mass (3kg/WCOOLING
• Decrease dynamic launch loads to which a is sub-jected by a factor of 20
• Decrease on-orbit disturbances experienced by payloads by a factor of 100• Improve total system power performance to 15
W/kg• Reduce Power System Costs to $ 3,000/W• Improve Solar Cell Conversion Efficiency to 35%• Develop Advanced lightweight and concentrator
arrays with specific power of 150 W/kg• Reduce satellite structural mass by 75% and reduce
cost by more than 25%• Reduce launch vehicle structural subsystem cost by a
factor of 10
Advanced Spacecraft Structures Research Experiment(ASSTREX)
MAJOR ACCOMPLISHMENTS• Completed sodium sulfur flight test safety reviews
successfully.• Provided key data to NASA/DOE that enabled them
to select AMTEC as the baseline converter for theiradvanced radioisotope power system. Successfullytested the first multi-tube AMTEC cells in vacuum.
• Initiated flywheel energy storage and attitude controlprogram in conjunction with NASA.
• Accepted delivery of 150 24% efficient multijunctionsolar cells.
• Delivered advanced lightweight composite busstructures for BMDO STRV-2 and PL MightySat-Ivehicles. Demonstrated 11% structural mass frac-tion and reduced fabrication time by 30%.
• Demonstrated applicability of electron-beam proc-essing for fabrication of composite space structures.
• Commenced characterization of 5 W Reverse Bray-ton Cycle Cryocooler
• Demonstrated feasibility of Multi-Stage Multi-Load35/60K cryocoolers for MLIR/LWIR Sensors.
• Successful flight Demo of highest ever operatingtemperature liquid metal heat pipe on STS-77.
• Accomplished 40% improvement in heat transportwith 1.45 micron metal wick capillary pumped loop.
• Proved feasibility of employing precision payloadpackages on non-precision satellites with active vi-bration isolation system (VISS).
• The structures and control technology area receiveda score of two with special mention from the SABReview Board.
CHANGES FROM LAST YEAR• Thrust 3 Structural Systems and Thrust 5 Power and
Thermal Management from the previous TAP havebeen combined into Thrust 3 Space Vehicle Tech-nologies of the current TAP. This combination oftechnologies creates a synergy that will acceleraterealization of a truly modular, multifunctional satel-lite bus.
• Flywheel energy storage and attitude control jointprogram with NASA initiated.
• Modified AMTEC program to support NASA/DOEadvanced radioisotope program.
• Thermal Management (Bus) focused technology areaintegrated with spacecraft structures technologiesbranch.
• Launch isolation technology has changed from a PLpush to an SMC/TE sponsored program.
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MILESTONES YEAR METRICSNext Generation Multifunction Structure S/C PDR FY98 Reduced mass by 4X; Fully integratedSTRV -2 launch with VISS on-orbit demo FY98 Demonstrate precision platform on noisy busFlight test AMTEC cells FY98 >30% efficient conversionQualify and flight test NaS battery FY98 Tech transition 100 Whr/kg NaS cells with 10 year life cycleBegin development of advanced concentrator arrays FY98 Demonstrate modular, integrated solar cell/battery/PMAD systemDevelop and breadboard high voltage PMAD technology FY98 Demonstrate 100v, 90% efficiency PMAD componentsDemonstrate large capacity Li Ion battery technology FY98 Light weight energy storage technology > 40 Ahr10 K cryocooler report FY98 Demonstrate feasibility of 10 K system35K/60K advanced Stirling cryocooler FY98 Multi stage, multi load protoflight cryocooler demonstratedGround test flywheel energy storage system FY99 Light weight, high cycle life energy storage technology > 40 AhrTransition multi-junction cell technology from ManTech to industry FY99 Mass produce cells with efficiencies 24-26%
Precision Structure Controls Experiment
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THRUST 4: ADVANCED SPACE TECHNOLOGY INTEGRATION ANDDEMONSTRATION
USER NEEDSIn order to continue to effectively control and exploit
space into the next millennium, the Air Force must con-tinue to field affordable, technologically superior systemsand effectively use cutting-edge technology to improveoperational tactics. Technologies focused on meetingUSAF operational needs and deficiencies are identifiedthrough the use of the Air Force Technology PlanningIntegrated Product Teams (TPIPTs); however, timelytransition of those technologies has often proven difficult.Orderly and routine demonstrations provide flight heri-tage for emerging technologies and are effective plat-forms for the development and demonstration of im-proved operational tactics. Within this thrust PL con-ducts regularly-scheduled space, near-space, re-entryfrom space, and ground demonstrations to facilitate riskreduction and technology maturation, and hasten tech-nology transition to the operational user. These demon-strations include combining new technologies into mis-sion oriented demonstrations to show advances in opera-tions and tactics. The synergistic effect of operations,tactics, and new technologies will maximize operationalsystem improvements in the areas of life cycle costs aswell as performance.
GOALSThe broad goals of the Advanced Space Technology
Integration and Demonstration Thrust are to transitiontechnology by:• Providing integrated space technology flight and
ground demonstrations to address AFSPC identifieddeficiencies and requirements, as well as DDR&EDefense Technology Objectives
• Reducing cost of developing, launching, and operatingspace systems;
• Minimizing risk associated with inserting advancedtechnology into operational satellites developed bySMC and operated by AFSPC.
• Developing technology advances to sustain and in-crease the key ICBM strategic and tactical capabilities,which include range instrumentation and safety, flightand terminal navigation accuracy, as well as loweringthe life cycle cost of the existing ICBM fleet.
Methods to Meet Goals:• Validate new satellite technologies using state-of-the-
art and standard satellite configurations;• Plan and execute advanced technology and integrated
space flight demonstrations with the user, includingdevelopment of new operational strategies based onadvanced technology;
• Leverage civil and commercial spare capabilities toexamine new space technologies while reducing bud-get/schedule requirements.
• Employ simplified command and control concepts;• Employ increased autonomous satellite operations;• Verify the maturity of technology, and transition them• Emphasize a streamlined concept of operations with
maximum use of experienced integrated product teamsincluding contractors, in-house expertise from the AFLaboratories, and other government agencies;
• Lead the improvement of the laboratory's integrationand system engineering capability;
• Provide actual experience in design, fabrication, inte-gration, systems engineering, and flight of spacecraftpayloads to laboratory personnel;
• Integrate and execute ground, near space, and spacedemonstrations for other DoD agencies leveragingtheir technologies to enhance AF capabilities;
• Demonstrate GPS Range Standardization/SafetyTech;
• Demonstrate new miniature GPS systems to lowerrange costs and enhance safety with greater accuracyand reliability;
• Demonstrate GPS accuracy enhancements and anti-jam antennas and systems;
• Increase cost effectiveness, missile navigation, andtesting accuracy with improved GPS/INS coupling;
• Fly the Missile Technology Demonstration III (MTDIII) during FY98 to gain data on a high speed instru-mented penetrator warhead and GPS/INS navigationsystem.
MAJOR ACCOMPLISHMENTS
MightySat I Satellite Integration
MightySat I was delivered to PL in November 1996.MightySat I has completed all experiment and payload
15
integration at the Phillips Laboratory’s Aerospace Engi-neering Facility (AEF) as well as having completed vi-bration, thermal-vacuum environmental, and missionsequence testing. The satellite will test a compositestructure, high efficiency solar cells, a microelectrome-chanical accelerometer, high density rad-resistant mi-croelectronics, a shape memory actuator device, and amicrometeor particle impact device. MightySat I This issignificant because this is the first PL satellite to havecompleted test and integration at the AEF.
ITSD Clark Van
The Integrated Space Technology Demonstration(ISTD) Clark project took delivery of their Mobile
Ground Station early in FY97. The Clark van was soonpressed into use for the Army’s Roving Sands exercise.The exercise covered territory in parts of New Mexicoand Texas, and involved the world’s largest demonstra-tion of military equipment and personnel. The Clark vanwas used to provide simulated space-based sensor data tofield commanders during the exercise. These sensor col-lections were used by the US Army to aid in intelligencepreparation of the battlefield. The Clark van’s participa-tion in the Roving Sands exercise was specifically tai-lored to the Army Air Missile Defense Command for theTheater Missile Defense (TMD) Tactical OperationsCenter (TOC). The NASA Clark satellite will launch inFY98 and downlink multispectral imagery data directlyto the Clark van.
The Missile Technology Demonstration 2 (MTD 2) testflight was conducted on 29 January 1997. The firstflight, MTD 1, on 16 August 1995 demonstrated the useof a commercially available, differential GPS/INS pack-age that gave extremely accurate range metrics and posi-tion information to within 3.2 m at impact and enabledthe impact point to be estimated continuously for an on-board autonomous range safety solution.
MTD 2 consisted of a modified Pershing II reentry ve-hicle on top of a SR-19 rocket motor booster. The SR-19is the second stage of the Minuteman II. The active on-board differential GPS/IMU provided the navigation forthe flight in addition to the range safety metrics demon-
1997 1998 1999 2000 2001 2002 2003 2004 2004+
Integrated Technology Demonstrations
ISTD Warfighter seriescontinues
MightySat programcontinues. AnticipatedPayloads:
• RF/HPM PropagationStudy
• Integrated CompositeStructure
• Modular Isogrid SolarArray Substrates
• Satellite Attack WarningAssessment FlightExperiment (SAWAFE)
• Pulsed Plasma Thruster(PPT)
• Emerging BatteryTechniques
• Multi-Junction SolarCells
• Advanced ElectronicPackaging Techniques
• Space Debris Sensor• Compact Environmental
Anomaly Sensor(CEASE)
• Multi-Junction SolarCells
• Global EarthquakeObservation/Prediction(GEO)
MTD demonstration seriescontinues
Integrated GroundDemonstration Program(IGDP) continues
MightySat I demo of L/WStructures &Power, Adv
Electronics, Protection Tech &Release Mechanism
Complete UltraLITEsparse optical array
Demo (IGDP)
Launch Clark/SSTIIntegrated Space
Tech Demo
MightySat II.2Demo
Launch Warfighter-1Integrated Space Tech
Demo
MightySat II.1 FourierTransform Hyperspectral
Imager Demo
M issile Navigation and Reentry Vehicles
Update ICBM INSwith Solid State
Navigation
MTD 4 demo ofmodified Mark 11Cand penetrator fuse
MTD 3 demo ofGPS/INS and
penetrator/accelerometers
Provide MTD 2 penetratordesign & Mark 11C data to
CBM ACTD
Demo prototypeMEMS accelerometer
and improved Gyro
MTD 5 demo of GPSsignal reacquisition for
terminal guidance & anti-jam, anti-spoof antenna
Technology Infrastructure
Integration, Test, and Operations Support ofAFRL Space Flight Experiments
Support for MightySat ProgramIntegration, Test, Operations
Warfighter-2Integrated Space Tech
Demo
MightySat II.3Demo
MTD 6 CommonAero Vehicle Demo
16
strated on the first flight. Three GPS/INS packages wereindependently demonstrated on the flight. The missilebecame unstable 26 seconds into the flight when all thehydraulic fluid used to control the rocket motor nozzlewas prematurely expended. The factors leading to thiscontrol instability have been determined and correctedfor any potential future flights using similar systems andhardware. The on-board systems using GPS completelydemonstrated their potential to monitor missile motionduring the erratic flight until the command destruct wasaccomplished. The 650 lb penetrator survived the free-fall back to earth and was recovered. This penetrator andits two surviving internal instrumentation packages willbe reflown on a future flight.
The Integrated Ground Demonstration Program hascompleted their first major design review for theUltraLITE ground experiment. UltraLITE will demon-strate at a system level, deployment repeatability andstructural stability of a full scale sparse optical array.This experiment incorporates optical wavefront measur-ing sensors that determine position error of a mirror masssimulator. Sparse arrays have several potential spacebased applications.
CHANGES FROM LAST YEAR
This year, flight demonstrations formerly listed underThrust 8, “Space Vehicle and Missile Dynamics Tech-nology, have been incorporated into this thrust withinSubThrust 4D, Missile Navigation and Reentry Vehicles.This includes the Missile Technology Demonstrator(MTD) series, of which MTD-2 was flown in January1997.
UltraLITE Sparse Optical Array Concept
MILESTONES YEAR METRICSISTDF #1 Integration Clark/SSTI Launch FY986 Launch Mission; Begin On-orbit Demo; Mission Objectives MetDesign,
Fabrication, Integration CompleteMightySat I mission FY987 Launch on Space Shuttle STS-881UltraLITE Experiment (IGDP #1) FY98 Complete integration, execution, and analysis of a bench top experiment
demonstrating capability to field a large aperture, sparse optical arrayMissile Technology Demonstration 2B (MTD 2B) FY98 Demonstrate GPS/INS for range safety, obtain penetrator dataISTDF #2 Initiation Warfighter-1 Launch FY998 Launch Mission; Begin on Orbit Demos; Mission Objectives Met Mission
Defined Miniature Sensor Technology Integration (MSTI) satel-litesIGDP #2 Initiation
FY99FY95
MSTI-3 Launch. All mission objectives met.Execute systems engineeringprocess to identify high payoff concept w/critical integration issues whichwill demonstrate emerging technologies
Missile Technology Demonstration 3 (MTD 3) FY99 Demonstrate modified GPS/INS navigation and penetrator fuseMissile Technology Demonstration 4 (MTD 4) FY99 Demonstrate modified Mark 11CMightySat II.1 mission FY0098 Launch on Space Shuttle or Orbital/Suborbital Program (OSP)Multi-
Service Launch SystemMightySat II.2 mission FY010 Launch on Space Shuttle or Orbital/Suborbital Program (OSP)Multi-
Service Launch SystemPlasma/antenna Interaction Demonstration FY01 Reacquisition of GPS signal for terminal guidanceAnti-Jam, Anti-Spoof Antenna FY01 Ground demonstration of antenna prototypeMicromechanical Accelerometers and Improved Gyro FY02 Demonstrate manufacturing prototypeMightySat II.3 Mission FY03 Launch on Space Shuttle or Orbital/Suborbital Program (OSP)Multi-
Service Launch SystemMissile Technology Demonstration 4 (MTD 4) FY03 Demonstrate Common Aero Vehicle (CAV)
THRUST 5: SPACE MISSION TECHNOLOGIES
USER NEEDSMission Technologies include those components that
perform the primary mission function of AF spacesystems. In most cases, those technologies are eitherelectronics or sensors. Electronic circuits are as perva-sive in space system payloads (and other parts of thesatellite) as they are in everyday life while sensors arethe eyes and ears of a spacecraft.
Mission Technologies play a critical role in enablingthe US to prevail in space. The AF long-range visiondocument, “Global Engagement” states that “Globalsituational awareness...” such as that provided by Mis-sion Technologies onboard surveillance and threatwarning satellites “... by its very existence, gives na-tional leaders unprecedented leverage, and thereforeadvantages.” The extraordinary importance of MissionTechnologies was recognized in a recent letter from theUndersecretary of Defense for Acquisition and Tech-nology where he cited advanced radiation hardened(i.e., space) electronics as crucial to the DoD and,therefore, deserving focused attention. Similarly, re-cent DUSD-level interest in hyperspectral sensorsdemonstrates how important sensor technology is toDoD warfighting plans.
In recognition of the importance of Mission Tech-nologies, AF SPOs, BMDO, and other space systemdevelopers have identified affordable, high perform-ance, radiation hardened, space qualifiable, sensor andsignal/data processing subsystems as essential spacetechnologies for the late 1990s and beyond. For exam-ple, improved booster detection sensitivity and cover-age, and worldwide detection and tracking capabilityfor missiles and warheads are requirements identifiedin several AFSPC Mission Area Plans. To meet thebroad range of requirements defined by these users,technologies that extend the performance of today’sspace sensor and electronic components must be devel-oped and demonstrated. The focus is to support war-fighters and operational users by providing MissionTechnologies that are simultaneously more cost effec-tive and higher performance.
The following paragraphs contain specific examplesof the numerous technology needs identified in SMCTPIPT development plans:Space Surveillance requires adaptive optics for largemirrors (MEMS), improved radiation-hardened proces-sor, parallel processing, and decreased optical wave-front error for space-based E-O sensors.National Missile Defense requires survivable high-speed anti-jam electronics, multi-sensor fusion tech-
nologies, advanced mid- and long-wavelength focalplane arrays, and multicolor focal plane arrays.Surveillance and Threat Warning mission area re-quires high density electronics, radiation tolerant elec-tronics, phenomenology of radar targets and clutter,advanced low power electronics, phased array tech-niques, advanced space processors, survivable high-speed communications, RF sensor model/simulationtools, high performance passive sensors, improved E-Osensors, optical wavefront sensors and correctors, andhyperspectral sensors.Space Force Application mission area requires ad-vanced electronics, hardened electronics, processingand anti-jam electronics, thrust axis accelerometer,next generation guidance systems & technology,miniature subsystem packaging, and a low cost starsensor.Navigation requires high-speed, low-power applicationspecific integrated circuits (ASICs).Satellite Communication requires higher-throughputhardened processors, and lightweight bus technologies.Satellite Control Network requires distributed proc-essing, and satellite autonomy.Weather requires nanosatellite technologies.
Example of a Nanosatellite 10 - 15 cm in Diameter
GOALSActive Sensors: The goal is to develop Space BasedRadar (SBR) technologies to enable transitioning in-telligence, surveillance, and reconnaissance missionssuch as AWACS and JSTARS into space. This effortencompasses the antenna architectures, phenomenol-ogy, and signal processing required to develop a sensorsuite for SBR. This goal will be achieved by develop-ing:• A sensor-level model in the “virtual satellite” model
developed by the System Technologies Division.♦ Extend the outputs to estimate cost and perform-
ance, and integrate with SMC and SWC battle labmodels and simulations
18
• Sensor characterization modeling and simulationcapabilities, including a radar clutter database, forselecting sensor suites and components, and for pro-viding a system perspective for technology develop-ment
• Antenna deformation compensation and beamsteering algorithms and adaptive processing tech-niques based on RL STAP specific-function applica-tions
• Low cost characterization of SBR components tosupport antenna and other component development
• Advanced Onboard Processing & Control technolo-gies for data reduction; advanced signal processing,automatic target recognition, sensor fusion, andcross cueing to ensure timely delivery of reconnais-sance and surveillance products to the tactical war-fighter
• Large, lightweight, multi-mode/band antennas forspace based military reconnaissance and surveillancemissions and commercial dual-use applications
Passive Sensors: The goal is to reduce developmentcosts, weight, and power consumption; increase reli-
ability, sensitivity, and resolution; and enhance af-fordability. This goal will be achieved by developing:• Next generation, highly sensitive detectors to pro-
vide reliable missile warning by detection of dimtargets, increased detection range, and improvedclutter suppression
• Multicolor detectors that simplify sensor design re-sulting in significantly lower power requirementsand lower weight
• Low power infrared detector readout electronics toreduce sensor spacecraft power requirements bymore than half and radiator weight by hundreds ofpounds
Space Communication: The goals are to develop:• Advanced EHF communications components for
satellite communication subsystems and RFcrosslinks
• Ways to use commercial services to support the defi-ciency in mobile services
• Optical techniques for satellite communicationsSpace Electronics: The goals are to permit increasedspace system affordability, reliability, operability, andautonomy by developing high-performance low-cost
1997 1998 1999 2000 2001 2002 2003 2004 2004+
Space Electronics
Reduce PowerConsumption 50%,Reduce Weight 75%,Reduce Volume 80%,Reduce O&M Cost UpTo 50%, ImproveThroughput 100x,Improve Efficiency30%, ImproveCapability,Affordability, AndReliability.
• 1.0 volt, 0.1 µm radhard microelectronics
• 10 Ghz+ digitalmicroelectronics
• Malleable processorsfor space, faulttolerant selfcorrecting/repairingprocessors
• High power SolidState PowerAmplifiers capable ofmeetingMILSATCOMrequirements forsatellite comm
Ultra-lightweightPower Converter forSpace , MEMS Gyro
Rad Hard GaAsand InP mixed
signal processors
Rad Hard highperformance
Digital SignalProcessor
Radiation Hardened30MIP, 32 bit
computer
Rad Hard 1Gbit+ SolidState Recorder,
Conformable Electronics
High performanceRad Hard fullydepleted SOI
microelectronics
Radiation Hardened1GIP+ parallel system,
NanosatalliteTechnologies
Space Sensors
High DynamicRange Mixer
RoomTemperature
MWIR and LWIRFPAs
MWIR ANDLWIR FPAs
MWIR ANDLWIR Integrated
FPAs
Space BasedRadar
Space Communications
Finalize DoDstrategy for using
commericalSatCom systems
Demonstrate 60GHz 0.6 W InPMMICs
Laser CrosslinkTechnology
5W 60 GHzCrosslink
Technology
Optical Comm60GHz 1W GaAs
MMIC powermodule
demonstrated
Develop 60 GHz0.6 W InPMMICs
19
space electronics that satisfy customer requirements.These goals will be achieved by:• Developing and demonstrating essential DoD space
electronics (e.g., 32-bit processors, or memory) with“spin-off” use by NASA and commercial programs
• Improving direct information transmission to fieldcommanders by 100% and reduce integration time50% through advanced electronics (e.g., signal proc-essing systems)
Key developments to meet the above goals are to:• Providing at least a 10X improvement in AF space
electronic system capability in the next five years by:♦ Leveraging from the rapid progress being made in
the commercial electronics industry♦ Transitioning high-demand commercial compo-
nents into space qualifiable versions♦ Leveraging industry's huge investment in design,
software, and testability♦ Developing innovative hardening technologies and
transferring to industry♦ Building standardized space data acquisition and
signal processing modules by standardizing hard-ened implementations of selected commercialprocessors
♦ Demonstrating space qualifiable versions of com-mercial high speed data busses including the FDDIand the ATM
• Developing new computer architectures and stan-dards to reduce the customer’s cost to develop andtest systems by up to 50%
• Providing more affordable computing solutions byenabling scaleable processing architecture and dis-tributed computing
• Developing Microelectromechanical System(MEMS) components to reduce the weight, size,power requirements and heat load of satellites, ena-bling more functional, and autonomous large satel-lites, and also new classes of micro- and nano-satellites
MAJOR ACCOMPLISHMENTSActive Sensors: The Space Based Radar (SBR) tech-nology area was very effective this past year. Workingclosely with customers and partners, the Space Elec-tronically Agile Radar (SPEAR) X-band, space basedradar concept, designed to perform Ground MovingTarget Indication (GMTI) missions, Air Moving Tar-get Indication (AMTI) missions, and Synthetic Aper-ture Radar (SAR) imagery, was developed and sub-mitted to SMC. The Cooperative LEO ElectronicallyAgile Radar (CLEAR) concept, designed to provideenhanced high resolution 3-d radar coverage for si-multaneous moving target detection (AMTI & GMTI),high resolution imagery, and high resolution mappingwith inexpensive, mass produced satellites, was devel-oped and presented to AFSPC. The SBR program hasalso had a very effective and active integrated productteam comprised of members from AF Labs, DARPA,NASA, academia, and industry. SMC transferred re-sponsibility for the modeling and simulation of SBR toPL
Passive Sensors: In the area of passive (e.g., infraredor IR) sensors, a HgCdTe-based MWIR camera wasdeveloped. This camera will be used to provide data toBMDO's Advanced Sensor Technology Program(ASTP) and will be used as a testbed for experimentalelectronics packages and focal plane array designs. Aneffort to increase the operating temperature of focalplane arrays to greater than 140 degrees Kelvin wasalso initiated to lower the total weight of a spacecraftby reducing the need for radiative cooling. In worksupported by SBIRS-High, risk reduction analysis wasperformed. Another HgCdTe effort demonstrated theability to mass-produce large MWIR focal plane arrays.In the area of Quantum-Well Infrared Photodetector(QWIP) technology, a new category of dark currenteffects that manifest themselves at the low tempera-tures required for space applications were discovered,and the sources that are responsible for this noise wereexplained. A collaborative effort was initiated with JPLto develop a low-background QWIP Focal Plane Arrayand the associated electronics at Rockwell ScienceCenter and Hughes SBRC. Another collaborative ef-fort was initiated with the NRC of Canada to develop atwo-color QWIP/LED/CCD imaging array. A novelvoltage-tunable QWIP structure was developed througha contract with the University of Florida.
Satellite Communication: In the area of SatelliteCommunications, working with the MILSATCOMoffice, efforts were initiated to evaluate crosslink tech-nologies for EHF payloads and satellite buses. To en-sure other AF technology developments were exploited,this effort was coordinated with ongoing communica-tion system developments at Rome Laboratory. TheSBIR program was exploited to advance space com-munication technology. During the past year, threePhase I SBIRs where all were selected for Phase II ef-
20
forts. The developments will include engineering andconstruction of a 5 Watt 60 GHz power combiner, a 28GHz 1 Gbps wireless link system, and a Code DivisionMultiple Access fiber optic network that can supportup to 1 Terabit/sec. Fabrication and testing of a 1-Watt60-GHz Solid State Power Amplifier was also initiated.Space Electronics: Many space electronics successwere obtained this past year. In collaboration with in-dustry a new analog-to-digital convertor (ADC) wasco-developed for the GPS MAGR anti-jam filter. It isboth a successful commercial product and a space-qualified component that outperforms any previouslyspace-qualified ADC. A collaborative was initiatedwith NASA JPL to develop a postage-stamp sized mi-crocontroller-based data acquisition system that offersa flexible solution for a variety of simple spacecraftprocessing tasks for both NASA and the AF. The con-troller will be used by NASA in two Mars surfaceprobes that are under development for the Mars 98program, and a hardened version is being evaluated forAF single-node and fault-tolerant applications. In an-other effort, a micro DC-DC power converter was de-veloped--the size was reduced from 1000 in3 to 2 in3
and weight from 80lb to 0.25lb. Finally, developmentand application of the “hardening by design” approachwas continued this year. “Hardening by design” wasused for a control application on the STRV-1d mission.In this application, components must withstand harshradiation in GEO-transfer environments. The ap-proach is now being applied to advanced commercialprocesses, and being extended to include analog cir-cuitry.
In the flagship, advanced space processor program, asingle-board 32-bit ASCM (computer) was demon-strated. This led to an “Outstanding” technical CDRon SBIRS-Low. In addition, ASCM technology wasselected for the GPS-IIF and SBIRS-High programs.The first light-weight, double-sided 32-bit data/signalprocessor was also developed using a reduced versionof
ATIM that decreased the weight and size by 10X. Ation hardened foundry was initiated. Considerablesavings will result from using commercial devices forprototyping and reuse of software. Finally, the Im-proved Space Computer Program was iniated to satisfyspace system developer needs in the FY01/03 timeframe with a scaleable, integrated computer architec-ture.
In advanced electronics packaging, advancementswere made in the state of the art in space multichipmodule (MCM) technologies. Twenty high-densityinterconnect (HDI) modules were developed for theBMDO Midcourse Sensor eXperiment (MSX) in May1996. This represents the first fielded demo of thisbreakthrough packaging technology. Furthermore,
PL’s advanced packaging expertise was key to suc-cessful development of the anti-jam filter for the GPSMiniature Advanced GPS Receiver (MAGR). Theconceptual packaging framework is being extendedfrom the 200X size and weight reduction reported lastyear to even more robust, paper-thin MCMs that canapproach 1000X reductions.
In the Microelectromechanical Systems (MEMS)technology area, an effort was initiated to develop ex-tremely small microrelays which require power onlywhen switching. Collaborations with two other PL di-rectorates, Space Experiments and Lasers and Imag-ing, to develop several micromirror systems for adap-tive optics and beam steering are in place. Two spaceexperiment payloads, referred to as Microsystems AndPackaging of Low-power Electronics (MAPLE), weredeveloped and delivered to the MightySat I and SpaceTest Research Vehicle programs. In MAPLE, com-mercial processors and MEMS devices are to be flownalongside space qualified advanced packaging and fieldprogrammable gate arrays. We have also proven thelong term reliability of thermal microactuators, a con-cept first conceived by PL and AFIT (patent submitted)and fabricated by Sandia National Laboratories. Ar-rays of these actuators provide some of the highestforce per area of any MEMS actuator. Initial radiationcharacterization on thermal actuators shows them to beimmune to normal levels of space radiation.
GPS Anti-Jam Filter
CHANGES FROM LAST YEAR• Most of the MEMS programs listed above are new
this year—exceptions: Phase 2 SBIR’s and some mi-cromirror work
• Space Comm budget cuts of approximately $1M foreach year in 98-03
• DIDERA modem project with Sandia National Labshas been put on hold due to funding limitations
Milestones Year MetricsComplete development of a neural-net controlled, micromirror-based
adaptive optics demonstration for test in the Apache Point telescope,part of the VT/SX/LI collaboration
FY98 Deliver working micromirrors for insertion in the SX SmartAdaptive Optics testbed, then into the actual telescope system,followed by insertion into multiple BMDO sensor systems
Deliver space-qualifed Advanced Instrument Controller (AIC) mod-ules to NASA for the Mars 98 surface probe
FY98 First space application of plastic form of HDI, which features 2Xweight reduction, 8X cost reduction, and can withstand 30,000Gimpacts and operate down to -130 deg C
Demonstrate three-dimensional micro-card cage under the Highly Inte-grated Packaging and Processing program
FY98 Demonstrate a generalized approach for packaging digital sys-tems as a dense collection of multichip modules (50X densityover competing implementations)
Develop beam steering mirror array for future optical sensors includingsatellite star, earth and sun trackers
FY98 Demo on space experiment and insert in one future space system
Develop, fabricate and test micromirror-based spatial light modulatorsfor atmospheric and optical system aberration correction
FY98 Ground test adaptive optics based on micromirror arrays in AFtelescope, and insert into one future space system, widely publishresults
Space sensor clutter model database completed FY98 Model radar clutter for comprehensive set of terrain typesTropical Rainfall Measuring Mission is launched containing 280 HDI
MCMsFY98 First demonstration of thin-film MCMs built identically from
three different vendors, 20X the capacity of modules flown onMSX
Develop usable MEMS-based IMU FY99 Insert into nanosatellite design or fly on a NASA New Millen-nium spacecraft as demo for use in military component replace-ment programs
22
THRUST 6: SPACE SYSTEM TECHNOLOGIES
USER NEEDSThe Air Force policy of “Global Virtual Presence
requires a broad base of technologies that efficientlyservice current and future satellite systems. SpaceSystem Technology programs are firmly rooted in theOperational Requirements Document AFSPC 00-94,Satellite Control, 4 Aug 95 and the Satellite OperationsMission Area Plan, 20 Nov 95. The focus is on sup-porting warfighters and operational users by providingcost effective, efficient satellite navigation, commandand control, onboard mission data prepara-tions/processing, precision orbit prediction, and mod-eling and simulation supporting technology trades andCONOPS evaluations.Space Information Dominance with the attendantSurveillance & Threat Warning and Battle Manage-ment, Command & Control: These areas require highspeed decision support systems, data fusion, high-speedon-board signal processing, fast target detection, iden-tification, and targeting. High fidelity simulators andmodeling of space environments are essential.Space Forces Support, Satellite Operations, and Sat-ellite Operator Training: Technical needs relate to thereduction of manpower to monitor remote trackingstations and satellite health and status.Space Intelligence, Surveillance & Reconnaissancemissions relevant to Space Control, Space Surveil-lance and Special Operations Forces: Ground controldecision aids, automated ground control monitoringand autonomous spacecraft functions, and enhancedsatellite navigation are required to accommodate futureoperations.
GOALSSpace System Technologies goals are:
• Develop reusable, affordable software architecturesfor on-board and ground station processing, preci-sion navigation, precision orbit prediction, andspace debris detection.
• Rely on others for basic software methods and tooldevelopment.
• Develop and apply software technology concepts toachieve an optimum level of satellite autonomy.
• Develop a flexible, object-oriented modeling andsimulation environment that is capable of includingall space assets.
MAJOR ACCOMPLISHMENTSMultimission Advanced Ground Intelligent Control
(MAGIC) system tracks all satellite passes at FalconAFB Space Operations Complex (SOC) 33. This pro-vides telemetry storage and analysis for the operationallife of satellites managed by SOC 33. MAGIC alsodemonstrated two autonomous anomaly detection sys-tems based on an expert and case based system. Aautomated pass-plan prototype and hypertext opera-tion/training manuals were demonstrated. A low costsatellite decommutation system was demonstrated. Asoftware architecture demonstrated the proof-of-concept that satellite software can be reused with con-fidence.
Achievements in FY97 for Modeling and Simulation
include contributing a Spacecraft Simulation Toolkit(SST)-based GPS simulation and a Virtual Cockpit tothe ACC’s Warrior Flag 97 wargame exercises. Thesesimulations bring realistic modeling of navigationalaids to the training and exercise community. Modelingand Simulation has also delivered: the SST baselinearchitecture; the Ultra-Lightweight Imaging Technol-ogy Experiment (Ultra-LITE) simulation; Space-BasedRadar systems simulations; and limited bus health &status simulations used for satellite operator displays,anomaly resolution, and autonomous satellite opera-tion.
23
Astrodynamics has set up and begun gathering dataand images from its Raven telescope. This telescope isthe first of its kind: a lightweight, low cost optical sys-tem designed for tracking satellites. The Debris Analy-sis Workstation (DAW) v. 1.0 was also delivered in4Q97. The DAW is a state-of-the-art software tool forcomplex space debris hazard assessment. Astrody-namics has also published a textbook called “Funda-mentals of Astrodynamics and Application.” The bookdocuments many of the fundamental routines used byastrodynamicists. A unique approach blends standardtheoretical derivations and explanations, realistic op-erational considerations, and high quality algorithms.This combination of classroom technique and actualpractice is lacking in virtually all other astrodynamicsengineering textbooks.
The Reusable Software Architecture for Spacecraft(RSAS) program has developed interactive softwarethat will generate components tailored to meet a satel-lite's unique on-board processing requirements. Thissoftware, referred to as the "Workbench," is currentlyundergoing beta testing at the Phillips Laboratory andat contractor facilities. The beta workbench tailorscomponents for a satellite's Orbit Determination (OD)subsystem. The final version will include all of Guid-ance, Navigation, and Control (GN&C), and parts ofElectrical Power (EPDS) and Communications(COMM). Tailored components are performance re-quirements, design information, Ada source code, andtest software. The Workbench demonstrates the con-cept of domain engineering. Early work in the RSASproject developed a generic model of satellite on-boardprocessing. The satellite engineer is guided through thegeneric model by graphical user interfaces (GUIs).The engineer's decisions and inputs are captured in arelational database. These decisions and inputs are
1997 1998 1999 2000 2001 2002 2003 2004 2004+
Satellite Control
Satellite dataprocessing workstationcompleted.
Create technologies toenable autonomousoperations with limitedoperator intervention.
Complete process formigrating autonomy fromground to spacecraft.
Modeling & Simulation
Complete advanced distributedsimulation visualization,interfaces, and bus systems.
Space Simulation Frameworkbaseline architecture delivered& documented.
Demo autonomoussatellite & information-on-demand simulations.
Demo prototype ofvariable-fidelity real-time system models.
Laser Clearinghousesoftware complete.
Publish update #3 of“Orbit AnalysisSoftware Survey.”
Solve operational problems thatcurrently limit system accuracy ofdetermining orbits for high-valuegeosynchronous U.S. satellite systems.
Publish update #5 of“Orbit AnalysisSoftware Survey.”
Debris HazardDesign Toolcomplete.
Debris Analysis Workstation:unique analysis technologiestransitioned to AF, DOD,NASA, and other programs.
De-orbit hazardstudy complete.
Design, implement, andencourage others to usevoluntary, practical, &cost effective measures tomitigate the problemsassociated with spacedebris.
Demo operator trainingsystem
Complete prototypeof softwarearchitecture foronboard autonomy.
Flight demonstrationcompleted.
“Satellite Data ConsoleSoftware” version 3.0delivered. Provide warfighter with
spaced-based mechanismfor obtaining informationwhen they need it, and inthe form that they need it.
Next-generation satellitesform a virtual network,operating cooperativelyto provide the warfighterwith needed information.
Develop the ability toperform real-time andfaster-than-real-time‘what if’ exercises,making missioneffectiveness quantifiable,and allowing commandersand space doctrinedevelopers to conductwargaming exercises anddevelop new concepts ofoperation.
Astrodynamics
24
eventually used to tailor generic components to meetspecific requirements.
CHANGES FROM LAST YEARA new effort is investigating autonomous satellite
functionality and control.The RSAS project will be completed at the end of
FY97.
Milestones Year MetricsDevelop Methods of Resolving Unknown Satellite Anomalies FY98 Customer on-site product acceptanceDevelop Debris Analysis Workstation FY99 Predict space debris collision riskFlight Demo of autonomous orbit control FY01 Maintain orbit more accurately and efficiently than manual
commanding
25
THRUST 7: BATTLESPACE COMMUICATIONS AND OPERATIONS
USER NEEDSControl and exploitation of space is an Air Force
mission. To achieve this goal, techniques (includingsensors and operational models) are developed to spec-ify and forecast the battlespace environment and itseffects on Air Force systems and operations. Opera-tional needs, deficiencies, operational concepts, andtechnology needs are defined in Mission and Func-tional Area Plans in several areas.Space-Based Weather and Environmental Monitoringreflects that weather and environmental monitoring arebackbone functions that cut across every command andmilitary activity. All commands include weather andenvironmental monitoring to some extent in a varietyof Mission and Functional Area Development Plans.Relevant extracts include:Navigation: The Navigation Systems ModernizationPlan requires increased accuracy through carrier phaseambiguity resolution, system and ionosphere rangeerror correction, and multipath reduction algorithmsfor user equipment as a near-term need applicable toall GPS users. GPS systems require increased robust-ness against signal fades due to scintillation, especiallyas solar activity increases.
Improved ionospheric modeling is needed to aug-ment GPS by using geosynchronous satellites such asAdvanced MILSATCOM. Like requirements for im-proved GPS are also described in the Satellite Controland Intelligence, Surveillance and Reconnaissance(ISR) plans.Military Satellite Communications: There is a needto extend communications coverage into the polar re-gion, with its intense ionospheric disturbances forwhich no useful model yet exists. There is a require-ment to combat scintillation effects associated withpolar and equatorial ionospheric disturbances.Force Application: There is a demand to characterize,predict, and in some cases mitigate the effects of theintense ionization that surrounds very high speed aero-space platforms. A related need is the ability for sys-tems to receive GPS signals during periods of intenseionization.Satellite Control: Critical RF communication links aresusceptible to interruption by environmental distur-bances triggered by anomalous solar or geomagneticspace conditions. These disturbances can increase sat-ellite drag, alter orbits, cause high frequency (HF)blackout at high latitudes, alter the frequencies for HFcommunication links, and create ionospheric scintilla-tions that disturb ultra-high frequency/extremely-highfrequency (UHF-EHF) communications.
Battle Management Command and Control (BM/C2):Includes improved Over-The-Horizon (OTH) radar forearly launch detection and assessment. ACC, NorthAmerica Air Defense Command and US SouthernCommand identify OTH radar as a solution for currentC3I deficiencies and state that OTH radar will be usefulfor counter-drug surveillance. Reliable use of OTHradar requires accurate specification and forecasting ofthe ionosphere, which controls OTH operational per-formance.
GOALSSpecify and model the hazardous charged particle
environment throughout near-earth space so designerscan maximize performance with minimum life-cyclecosts. Measure key solar and interplanetary parametersfor specification and forecast models to minimize spacesystem degradation or failure.
Obtain a global, real-time capability to accuratelyspecify and forecast the ionosphere, and provide timelywarning of when, and how severely, ionospheric dis-turbances will disrupt C3I systems. Assess the effect ofionospheric scintillations that degrade GPS accuracy oravailability. Specify and predict the neutral density ofthe upper atmosphere within tolerances to meet opera-tional requirements for satellite tracking, reentry pre-dictions, detection of orbital changes, determination ofsatellite lifetimes plus on-board fuel requirements, andspace debris hazard assessments.
Combine the energetic charged particle, ionospheric,and neutral density models into an Integrated SpaceEnvironment Model that monitors the environment inwhich space systems operate, and warns of hazards tospace-and ground-based systems, like power transmissiongrids.Characterize and predict the intense ionization aroundhypervelocity platforms, quantify their effects on GPSradio signals, and develop techniques to control ioni-zation to alleviate radio blackout and decrease flightdrag.
MAJOR ACCOMPLISHMENTSAssessed the over 150 million auroral electron spectra
obtained with DMSP instrumentation. In addition toproviding a clearer picture of particle distribution (lognormal-Gaussian, population behaviors) for auroraldisturbance models, the study will yield a better tool toascertain auroral boundaries, key indicators of atmos-pheric, ionospheric, and magnetospheric disturbancelevels.
26
Installed PL-GEOSPace version 1.30 at 55SWS inNovember. This version includes real-time monitoringof auroral boundaries and radiation belts.
CRRES data analysis led to a proton diffusion modelfor Earth's radiation belts to predict diffusion timesfrom a given initial condition. This model will allowfor a more accurate prediction for decay of storm-builtpopulations.Delivered the CRRES Heavy Ion Model of the Envi-ronment (CHIME) to the 55 SWS in January. Morerecently the code was provided to other DoD agenciesand contractors. For a specified orbit and level of solaractivity, the model predicts the cosmic ray spectra andsingle event upset (SEU) rate for memory devices onspacecraft.
A strong inverse correlation of solar wind speed withdistance from a solar coronal hole was found. This factwill help forecast when, and with what intensity, solardisturbances will strike earth and disturb the neutraland ionized upper atmosphere (ionosphere), includingthe magnetosphere.
Much progress was made concerning the interactionof the solar wind (and associated shocks) with theearth. Shocks disturb the earth's upper atmosphere,ionosphere and magnetosphere. Transioned the resultsto 55SWS, including a shock recognition algorithmdesigned for solar wind input data. Developed a data-driven solar wind model that predicts shock arrivaltime at Earth. The daily transmission of solar wind
data for operational use at the 50SWS was accom-plished.
Three sensors were launched with DMSP vehicleF14 on 4 April 97. The sensors measure (at 840 km)ionospheric plasma concentrations, magnetic fields,and the flux of precipitating auroral particles.
The Charge Control System (CCS) continues towork extremely well on the DSCS B-7 vehicle. Re-corded and eliminated over 100 charging events(>1500V) to date.Valuable information was gleaned from the Photo-voltaic Array and Space Power experiment plus diag-nostics (PASP Plus). Ascertained the degradation ofsolar cell power with time and radiation dose for sev-eral different cell arrays. Determined leakage currentsas functions of the positive plasma concentrations,ram/wake orientations, and vehicle potential. Determ-ined also was the rate of arcing versus negative voltagelevel, ion flux, plasma density, velocity, ram angle, andarray temperature.
A new theory for (combined) electron-proton aurorasprovides more accurate electron density profiles. Thisimprovement will be included into operational iono-spheric models like PRISM, which became operationalat 55SWS last year. This specification model uses real-time data to extrapolate ionospheric conditions and theglobal propagation environment. The 55SWS's Voiceof America Comm. Assessment Code (VOACAP) forHF propagation was modified to accept PRISM out-puts. Validation is in progress at 55SWS and the new
1997 1998 1999 2000 2001 2002 2003 2004 2004+
Space Effects on Satellite Systems
Space Sensors for NPOESS
On-Board IntelligentDetection, Evaluation,
and Mitigation of Hazardsin Space Environment
CEASE Launch onSTP TX-5 Satellite
IOC for IntegratedSpace EnvironmentModel at 55SWS
Space SensorsLaunched onDMSP F14.
Coronal MassEjection Disturbance
Model to 55SWS
Fully DynamicGeoSpace ModelIOC at 55SWS
Active Solar RegionEvolution Model for
Disturbance Forecasts
Ionospheric Effects on COMM/NAV Systems
Coupled IonosphericScintillation Model
COMM/NAVOutage Forecast
System
Expand SCINDA toGPS L-Band
SCINDA installedat 55SWS
Technology for Mitigationof COMM Blackout for
Military Spaceplane
StandaloneCapability forApplication of
Environmental Datafrom Space-BasedSystems To AdviseTheatre Commanderof Adverse Impacts
on OperationalSystems and
Outages
Modeling andSimulation ofOperational
Environments forAcquistion Planning
27
capability becomes operational late this FY. It willgreatly improve HF connectivity and reliability.
The Ionospheric Forecast Model (IFM) was given toHQ/AWS in January for transition to operationalstatus. The IFM should be operational in FY98, provid-ing global 12 hour forecasts of ionospheric parametersto all DoD customers.
Added the plasmaspheric populations of hydrogenand helium ions to the Global-Theoretical IonosphericModel (GTIM). This model is the theoretical founda-tion of the applied model PRISM and will eventuallyexpand the utility of PRISM to higher altitudes.
Measured the principal loss mechanisms for theionosphere, the reactions of atomic oxygen ions withmolecular oxygen and nitrogen, for the first time above900K. The reaction rates have been found to increaseat higher temperatures compared to a decrease withtemperature from 300 to 900K. (Ionospheric tem-perature can rise to 2000K.) This finding has im-proved model calculations of electron concentration by50%, thereby reducing radar range and position errors.
Installed a new algorithm at Master Control for GPSat Falcon AFB. This algorithm was based on im-provements in ionospheric modeling, meets the re-quirement for single frequency position, and will sig-nificantly improve GPS performance.
A prototype Scintillation Network Decision Aid(SCINDA) was installed at 55SWS to provide the war-fighter with SATCOM outage regions and help himplan for such outages and/or degradation of navigation.This aid also helps identify the source of the outage:equipment failure, jamming, or ionospheric effect.
The ACTD Comm/Nav Outage Forecasting System(CNOFS) was developed for severe C3I outages nearthe magnetic equator. Based on research, CNOFS will
employ satellite and ground-based sensors for real-timewarnings. This ACTD was ranked #1 by the AFROClast December.
The High-frequency Active Auroral Research Pro-gram (HAARP), while still under construction, wasused to create an ionospheric source of ULF/ELF/VLFsignals akin to those required for underground sur-veillance and submarine communications; studytransmagnetospheric radio propagation to help char-acterize the near-earth space environment in conjunc-tion with data from NASA's (solar) WIND satellite;and generate irregularities in local regions of the auro-ral ionosphere for coordinated studies of scintillationeffects on transionospheric paths, such as satellite toground links.
CHANGES FROM LAST YEARAll optical and infrared effects on Air Force Systems
work has been placed in thrust eight, where the optical andinfrared remote sensing work has been conducted.Research on the contribution of cosmic rays to radiationeffects on defense systems will be terminated in FY98.Research on the following programs will be scaled back:Magnetospheric Substorms, Ultraviolet Technology, andIonospheric C3 Technology.
The BMDO-funded Space Weather and TerrestrialHazards Program, an effort to study the sun and trackspace debris, was terminated. The coronagraph builtfor he program is available for use elsewhere.The Improved Solar Optical Observing Network pro-gram and its initial funding profile were established.The source of funds beyond FY97 is not yet clear.
Milestones Year MetricsScintillation network Decision Aid. FY98 Upgrade to include GPS L-Band.Inversion of GPS to satellite propagation to determine electron densityprofiles.
FY98 Evaluate suitability for input to Ionospheric Forecast Models.
Forecast tool for the onset of equatorial scintillation on a global scalebased on satellite data.
FY98 Provided to 55SWS.
Develop and test miniaturized Digital Ion Drift Meter (DIDM) spaceplasma sensors.
FY98 Launch on space Test Program’s (STP) Space Test ExperimentsPlatform (STEP)-4 satellite.
Compact Environmental Anomaly Sensor (CEASE) FY98 Launch on STP’s TSX-5 satellite.PL-GEOSPace Version 2.0 (full dynamic, data-driven models) FY98 Delivered to 55SWS.Quasi-dynamic radiation models FY98 Complete transition to SMC and industry.Coupled Ionosphere Thermosphere Forecast Model FY98 Initial Operational Capability (IOC) at 55SWS.Dynamic models for radiation belt electron variations during activeperiods
FY98 Completed.
FY99 Launch on German satellite.FY99 Launch on British Defense Agency, Space Technology Research
Vehicle (STRV-1 c/d.Solar Mass Ejection Imager (SMEI) FY99 Ready for launch.Integrated Space Environment Model. (PL-GEOSPace is a major com-ponent.
FY00 IOC at 55SWS.
Improved Operational Space Environment Models FY00 IOC for Advanced Coupled Magnetospheric Model and SolarPrediction Model at 55SWS. IOC for Coupled IonosphericScintillation Model for 55SWS.
28
THRUST 8: OPTICAL SURVEILLANCE EFFECTS AND BATTLESPACEOPERATIONS
USER NEEDSExploitation of space and combat environments is key
to Air Force mission success. Important to achieving thisgoal is the development of techniques to accuratelyspecify, forecast, and mitigate the battlespace environ-ment and its effects on Air Force systems and operations.The pervasive nature of space and combat environmenteffects is evident in all Commands in deficiencies identi-fied by Mission and Functional Area Plans. It is also rec-ognized by SMC, ESC, and ASC Technology PlanningIntegrated Product Teams (TPIPTs). Improved specifi-cation and forecasting of the battlespace environment fortheater and strategic missile detection and tracking andfor air and surface target acquisition in theater engage-ments are needs which impact all military operations:Surveillance and Threat Warning requires improveddefinition of target and background signatures to designnew systems for missile warning, tracking, and interceptfor theater and national missile defense. Technologyneeds for near and far term system concepts includebackground clutter and target data base measurementsand modeling as well as discrimination algorithm devel-opment for SBIRS Geosynchronous/High Earth Orbit(GEO/HEO) and SBIRS Low Earth Orbit (LEO), theSpaceBorne Laser (SBL), and more advanced active sur-veillance systems.Combat Operations require improved target acquisitiontechniques and tactical decision aids incorporating ad-vanced theater weather forecast models for mission plan-ning and operations support. Technology needs for air-to-surface targeting include data retrieval techniques andcloud cover models for data-denied areas in threat thea-ters. Improved characterization of atmospheric laserpropagation for target kill is needed by the AirBorne La-ser (ABL) system.
GOALSGoals for improved target-background discrimination
for surveillance and threat warning include:• Measure/characterize the infrared and optical
wavelength signatures of backgrounds and targets(including missile plumes) needed to discriminatetarget from their backgrounds.
• Develop/validate computer codes to simulate infraredand optical atmospheric transmissions andbackgrounds and celestial backgrounds to allowdesigners to optimize the performance of infraredand optical sensors for surveillance, tracking, andinterceptor systems at minimum cost.
Goals for improved target acquisition for combatoperations include:• Exploit space-based remote sensing technologies for
application to theater requirements.• Develop Weather Impact Decision Aids to allow
operational users to predict electro-optical sensorsystem performance for all-weather operation.
• Measure and model small-scale atmospheric effects(including optical turbulence) on high-energy laserpropagation for optimizing weapon system power,range, and time-on-target.
MAJOR ACCOMPLISHMENTSThe Midcourse Space Experiment (MSX) satellite
performed over 200 data collection events during the tenmonth cryogenic operations period to provide criticallyneeded data on spatial structure and variability in atmos-pheric, cloud, and terrain infrared backgrounds and keydata on celestial backgrounds. A key discovery is highclutter level in the narrow medium-wavelength infrared(MWIR) band due to atmospheric gravity waves. Themeasured MWIR and LWIR (long-wavelength infrared)atmospheric scenes are needed for background modelassessment to support SBIRS system engineering tradestudies. An infrared astrometric catalog containing themost extensive survey of IR stars was constructed to pro-vide stellar on-board pointing and calibration for ad-vanced space-based surveillance and tracking systems.
Under the SBIRS Phenomenology Exploitation Pro-gram (PEP), MWIR and LWIR measurements of atmos-pheric, cloud, and terrestrial backgrounds made by theMiniature Sensor Technology Integration-3 (MSTI-3)satellite were used to provide small and large mosaicscenes and global background clutter statistics to assessSBIRS design performance and to determine how oftenperformance may be degraded. MSTI-3 data is also be-ing used to validate background clutter models to providereliable synthetic background scenes for the full range ofSBIRS operational conditions and system design tradespace.
Beta versions of the Synthetic High Altitude Radiance(SHARC) and SHARC Image Generator (SIG) codes togenerate two-dimensional images of high altitude IRbackground clutter were developed to extrapolate meas-ured background data to the full design trade space andall operational conditions for SBIRS and BMDO Theaterand National Missile Defense target detection and track-ing concepts. The SBIRS Model Toolkit (SMT) for
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simulating cloud and terrain background scenes observedfrom space platforms was developed and released to theSBIRS SPO and contractors.
The SPIRITS Aircraft 2 Version (SPIRITS-AC2) wascompleted and released to the defense community by theJANNAF Signatures Panel. This version supports targetmodules for the F-52H, Air Launched Cruise Missile(ALCM), C-130H, and C-17.
The Infrared Target-Scene Simulation Software(IRTSS) was developed to provide IR scene visualizationcapabilities for air-to-air and air-to-ground targets, in-cluding weather effects. The software is being tested andevaluated in a series of experiments at Eglin AFB testranges. IRTSS will be delivered to ESC for incorpora-tion in the Air Force Mission Support System (AFMSS).
The Cloud Scene Simulation Model (CSSM) was sig-nificantly upgraded to provide data-driven predictions of4D scenes of cloud content. The new capability enablesthe use of geostationary satellite imagery and mesoscaleweather model data to initialize CSSM calculations forhigher fidelity simulations.
Successful field campaigns in Korea and the MiddleEast were conducted to measure and characterize opticalturbulence effects on laser propagation in theaters of in-terest to the ABL weapon system. The measured atmos-pheric profiles provide critically needed data to specifyand predict ABL performance degradation due to opticalturbulence and its dependence on meteorological and
orographic conditions. The campaigns are part of amulti-year program to characterize the variation of tur-bulence with season and meteorology in theaters of inter-
est.
CHANGES FROM LAST YEARA new program to characterize missile plume signatures
through clouds for early-report of theater ballistic missileswas initiated under the Emphasis Area Program sponsoredby AFOSR
A new BMDO-sponsored program of aircraftmeasurements and model calculations to predict MWIRcloud clutter statistics for theater ballistic missile detectionand tracking against stressing cloud backgrounds is beingconducted as part of the BMDO Russian-AmericanObservational Satellites (RAMOS) Program.
Budgets cuts in Program Elements 62601F and 63707Fhave resulted in the termination of programs in triggeredlightning, tactical weather systems techniques, and WSR-88D algorithms.
1997 1998 1999 2000 2001 2002 2003 2004 2004+
Target-Background Discrimination for Surveillance
Enhanced Target-BackgroundDiscrimination Algorithms
SignatureCharacterization of
CV22 Osprey
Testing of F-22 forCompliance with LowObservability Specs
MSX and MSTI-3 clutttermeasurements for SBIRS and
BMDO Systems Analysis
StealthCountermeasure
Algorithms
Clutter Suppressionfor Low Signature
Targets
Dynamic TargetDetectivity Algorithms
for Missile Defense
Target Acquistion for Combat Operations
Theatre WeatherForecasting Software
Synthetic Atmospheresfor Hardware-in-Loop
Simulations
Forecast ofContrails for
Stealth Air Ops
IR Target Softwareto AF Mission
Support System
Turbulence and LaserPerformance Models
Stoplight Weather ImpactMission Planning Software
Tactical DecisionAids for ABL
Optical TurbulenceStatistical Data for
ABL Auth. to Proceed
Standalone Capability forTheatre Commander toApply Environmental
Data from Space-BasedSystems To Operational
Needs of UnmannedCombat Air Vehicles andAir Expeditionary Forces
Modeling andSimulation ofOperational
Environments forAcquistion Planning
Theatre MissileDefense
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Milestones Year Metrics
MSX and MSTI-3 IR background scenes FY98 Background model assessment and global background clutter statistics
High-altitude background clutter code FY98 Validated synthetic IR background scenes
Theater weather forecasting software FY98 Transition to weather forecasting systems
Optical turbulence statistical data FY98 Criteria for ABL Authority to Proceed
Synthetic atmospheric and cloud background scenes for new system bands FY99 Band-dependent background clutter assessment
Cloud clutter forecasting model for new system bands FY99 Band-dependent background clutter assessment
Infrared Target-Scene Simulation Software for mission planning and support FY99 Operational test and evaluation
Clutter suppression methods for low signature targets FY00 Validated filter band selection criteria
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GLOSSARYABL - AirBorne LaserACESS - Advanced Composite Ex-
perimental Spacecraft StructureACTD - Advanced Concept Tech-
nology DemonstrationADC - Analog-to-Digital ConverterAEF - Aerospace Engineering Facil-
ityAFIT - Air Force Institute of Tech-
nologyAFMSS - Air Force Mission Support
SystemAFOSR - Air Force Office of Scien-
tific ResearchAL - Armstrong LaboratoryALCM - Air Launched Cruise Mis-
sileALT - Anode Layer ThrusterAMTEC - Alkali Metal Thermal
Electric ConversionARIES - Applied Research In Energy
StorageASIC - Application-Specific Inte-
grated CircuitsASTP - Advanced Sensor Technol-
ogy ProgramATM - Asynchronous Transfer ModeBMDO - Ballistic Missile Defense
OrganizationC3I - Command, Control, Communi-
cations, and IntelligenceCAV - Common Aero VehicleCCD - Charge Coupled DeviceCCS - Charge Control SystemCEASE - Compact Environmental
Anomaly SensorCEP - Circular Error ProbableCHIME - CRESS Heavy Ion Model
of the EnvironmentCLEAR - Cooperative LEO Electroni-
cally Agile RadarCNOFS - Communication/ Naviga-
tion Outage Forecasting SystemCPVCRRESCSSM - Cloud Scene Simulation
ModelDARPA - Defense Advanced Re-
search Projects AgencyDMSP - Defense Meteriological Sat-
ellite Program
EHF - Extremely-High FrequencyE-O - Electro-opticalESA - European Space AgencyFDDI - Fiber Optic Digital
Data InterfaceGaAs - Gallium ArsenideGEO - Geosynchronous Earth OrbitGPS - Global Positioning SatelliteGTIM - Global-Theoretical Iono-
spheric ModelHAARP - High-frequency Active
Auroral Research ProjectHAN - Hydroxyl Ammonium NitrateHDBTDC - Hardened and Deeply
Buried Targets Defeat CapabilityHDI - High-Density InterconnectHEDM - High Energy Density Mate-
rialHEO - High Earth OrbitHF - High FrequencyHgCdTe - Mercury Cadmium Tellu-
rideICBM - Inter-Continental Ballistic
MissileIFM - Ionospheric Forecast ModelIMU - Inertial Measurement UnitINS - Inertial Navigation SystemIPV - Inertial Penetrator VehicleIR - InfraredIHPRPT - Integrated High Payoff
Rocket Propulsion TechnologyIRTSS - Infrared Target-Scene
Simulation SoftwareISR - Intelligence, Surveillance, and
ReconnaissanceISTD - Integrated Space Technology
DemonstrationsJANNAF - Joint Army, Navy,
NASA, Air ForceLASRE - Linear Aerospike SR-71
ExperimentLED - Light Emitting DiodeLEO - Low-Earth OrbitLWIR - Long-Wave InfraredM&S - Modeling and SimulationMAGIC - Multimission Advanced
Ground Intelligent ControlMAGR - Miniature Advanced GPS
Receiver
MANTECH - Manufacturing Tech-nology
MAP - Mission Area PlanMAPLE - Microsystems And Pack-
aging of Low-Power ElectronicsMCM - Multichip ModuleMEMS - Microelectromechanical
SystemMSX - Mid-Course Sensor eXperi-
mentMTD - Missile Technology Demon-
strationMWIR - Mid-Wave InfraredNOAA - National Oceanic and At-
mospheric AdministrationOSP - Orbital/Suborbital ProgramOTH - Over The HorizonPEP - Phenomenology Exploitation
ProgramPL - Phillips LaboratoryPPT - Pulsed Plasma ThrusterPRISM - Parameterized Real Time
Ionospheric SpecificationQWIP - Quantum-Well Infrared
PhotodetectorRAMOS - Russian-American Obser-
vational SatellitesRF - Radio FrequencyRL - Rome LaboratoryS&T - Science and TechnologySBIR - Small Business Innovative
ResearchSBIRS - Space-Based InfraRed Sys-
temSBL - Space-Based LaserSBR - Space-Based RadarSCINDA - Scintillation Network
Decision AidSEU - Single Event UpsetSHARC - Synthetic High Altitude
RadianceSIG - SHARC Image GeneratorSMC - Space & Missile Systems
CenterSMEI - Solar Mass Ejection ImagerSMT - SBIRS Model ToolkitSOX - Solid OxygenSPEAR - Space Electronically Agile
RadarSPIRITS
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SPREE - Shuttle Potential and Re-turn Electron Experiment
STIG - Space Technology Inter-agency Group
STRV - Space Technology ResearchVehicle
TA - Technology Area
TAP - Technology Area PlanTMD - Theater Missile DefenseTOC - Tactical Operations CenterTPIPT - Technology Planning Inte-
grated Product TeamsTRAM - Transmitting/Receiving
Antenna Module
TSS - Tethered Satellite SystemUHF - Ultra-High FrequencyVOACAP - Voice of America Com-
munication Assessment CodeWL - Wright Laboratory
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INDEX
AAir Force Office of Scientific
Research (AFOSR), 2, 28, 29Air Force Space Command (AFSPC),
7, 9, 12, 15, 20Applied Research In Energy Storage
(ARIES), 2Armstrong Laboratory (AL),3Autonomous Satellite Operations,
14
Bballistic missile, 5Ballistic Missile Defense
Organization (BMDO), i, 2, 3, 10,15, 17, 18, 24, 27, 28, 29
CCommunications, 2,3,10,17,18,24,26
DDebris, ii, 9, 22, 23, 24, 25, 27Defense Advanced Research Projects
Agency (DARPA), 29deficiencies, 4, 5Demonstration, 12, 14Department of Defense (DoD), i, 12,
15, 16, 23, 24DoD, i
EElectronics, 2,17,18,19,20European Space Agency (ESA), 4
GGlobal Positioning Satellite (GPS),
2, 3, 4, 12, 13, 14, 17, 18, 22, 24,29
Global Virtual Presence, 20GPS, 3
HHigh Energy Density Matter
(HEDM), 2
IIHPRPT, 5Integrated High Payoff Rocket
Propulsion Technology (IHPRPT),4, 5, 6, 7
Integrated Space TechnologyDemonstrations (ISTD), 13, 14, 29
JJet Propulsion Lab (JPL), 3
MManufacturing Technology
(MANTECH), 3, 29materials, 2, 3, 5MightySat, 10, 13, 14, 18MILSATCOM, 3, 9, 17, 22Missile Technology Demonstration
(MTD), 2, 12, 13, 14, 29Mission Area Plan (MAP), i, 29Modeling and Simulation, 17,19,22
NNASA, i, 3, 4, 5, 7, 9, 10, 13, 16, 17,
19, 24
OOptical Surveillance Effects, 2,4,27
Ppower
i,ii,3,10,11,12,17,18,19,20,24,25,27
powerhead, 6Propulsion, 3, 4, 5, 7, 8Pulsed Plasma thruster (PPT), 7, 8,
29
Rrocket, 7Rome Laboratory (RL), 3,17
SScience and Technology (S&T), i, 29Sensors, 3, 4, 14, 15, 17, 18, 19, 22,
23, 24, 26SMC, 5, 7, 9, 11, 12, 16, 24, 26, 29Sodium Sulfur (NaS), 11Solar, 5, 11iSpace and Missile Systems Center
(SMC), 11, 12, 15, 18, 21Space and Missiles, i, 2, 4Space Systems, 4, 5, 9, 12, 15, 22Space Vehicles, 2, 5spacelift, 5structures, i,10,11,12
TTechnology Area Plan (TAP), i, 3, 4,
30Technology Planning Integrated
Product Teams (TPIPT), i, 15, 30thermal management, ii,10transition, 11
WWarfighter, 14, 16, 24Wright Laboratory (WL), 3