DEFENSE TECHNOLOGY OBJECTIVES
SPACE PLATFORMS
SP0106FC Cryogenic Technologies. Develop advanced cryogenic cooling technologies
for space-based surveillance sensors requiring cooling between 10 K to 150 K that offer mass
savings, performance improvements, and long life potential over current dewars and radiators.
SWIR, MWIR, and LWIR detectors require cryocooling to reduce the thermal noise; thereby
providing higher signal to noise ratio and a greater acquisition range. The technical objectives
include: reduce mass by 15% by FY00 and 50% by FY05; reduce specific power (watts of input
power divided by watts of cooling) from 40 to 25 by FY05 and reduce it to 15 by FY10; increase
life expectancy from current 3 year level to 5 years in FY00 and to 10 years by FY10; improve
reliability from 95% to 98% by FY05; and eliminate significant induced vibration by FY10. The
technology challenges include: develop lighter weight cryogenic materials; optimize integration;
minimize friction and material stresses; eliminate contamination sources; minimize loss
mechanisms; and develop vibration isolation techniques. Cryogenic technologies are applicable
to sensors for space surveillance and missile warning and tracking missions, specifically the
SBIRS program, as well as NASA and NPOESS environmental sensors, and other agencies. The
technologies also support super conducting or cooled electronics which will be pervasive to all
DoD spacecraft, as well as AFSPC, NASA, and other agencies programs.
| Svc/Agency POC: |
SMC/XRT POC: |
Customer POC: |
LtCol David Lewis
SAF/AQRT
(703) 602-9200
|
Col Robert Preston
(310) 363-0840
|
Lt Charlie Light
SMC/MTAF
(310) 363-0020
|
Programmed DTO Funding ($M):
|
FY96 |
FY97 |
FY98 |
FY99 |
FY00 |
FY01 |
| Total |
4.8 |
12.6 |
12.5 |
13.5 |
13.6 |
7.6 |
SP0207F Thermal Management Technology. Develop technologies to improve the
performance and reliability while reducing the mass of spacecraft thermal management
subsystems. These technologies include: heat pipes, thermal energy storage devices, thermal
transfer devices, and radiators. The goals of these technology developments are: increase heat
flux from 10 W/cm2 (current) to 100 W/cm2 by FY10; increase heat transport by 25% by FY00
(75% by FY05, 120% by FY10); decrease thermal subsystem mass by 5% by FY00 (15% by
FY05, 30% by FY10); decrease electronic component temperature by 10°C by FY00; and
decrease spacecraft heater power by up to 75% by FY05. Technology challenges include: rapid,
reliable start-up and long term operation of capillary pumped loop systems and liquid metal heat
pipes; and development of (1) low cost, advanced composite materials and devices capable of
dissipating high heat fluxes from microelectronic devices, (2) sub-micron wicks (1 micron pore
size) for capillary pumped loop applications, and (3) flexible or rotatable joints that allow for the
efficient transportation of heat from the spacecraft bus outboard to a deployable radiator.
Thermal management is considered a pervasive technology area, applicable to all DoD, NASA,
and commercial spacecraft program offices as well as AFSPC, and other agencies. The
technologies are essential for those missions with either high power dissipation (SMC or SAF/SP
space based radar for surveillance/mapping) or concentrated power dissipation on reduced area
payloads (next generation military and commercial communication spacecraft such as MILSTAR
III, as well as the NPOESS program with a multitude of weather sensors).
| Svc/Agency POC: |
SMC/XRT POC: |
Customer POC: |
LtCol David Lewis
SAF/AQRT
(703) 602-9200
|
Col Robert Preston
(310) 363-0840
|
Lt Charlie Light
SMC/MTAF
(310) 363-0020
|
Programmed DTO Funding ($M):
|
FY96 |
FY97 |
FY98 |
FY99 |
FY00 |
FY01 |
| Total |
2.6 |
3.3 |
3.4 |
2.4 |
2.6 |
2.6 |
SP0306NF Space Structures and Control. Develop advanced space structural
component technology to reduce the weight and cost of spacecraft and launch vehicle structures
while improving their producibility and reliability. Also develop enabling structural sensing,
control and vibration damping technologies for space platforms, precision surveillance sensors,
space based radars, space based interceptors, missiles, and launch systems. This includes the
development of a new class of adaptive or smart structures, which contain sensors and actuators
to sense and suppress vibrations to meet mission requirements, the development of new
mechanism concepts, such as non-pyrotechnic release devices, and new structural response
sensors, such as advanced, multiplexable fiber optics sensors based on Bragg technology. In
addition, there is exploratory research into the development of new structural control algorithms
and into new approaches for determining the structural response characteristics of a space system
on orbit. Specifically, develop and demonstrate advanced structural control technology concepts,
techniques and production approaches to: reduce satellite structural mass by 40% and reduce cost
by more than 10% by FY01 (75% and 25% respectively by FY11); to reduce launch vehicle
structural subsystem mass by 40% and cost by 25% by FY01 (75% and a factor of 10,
respectively, by FY11); decrease satellite dynamic launch loads by a factor of 5 by FY01 (a
factor of 20 by FY11); reduce satellite pyrotechnic-shock by more than two orders of magnitude
by FY01; demonstrate flight qualified fiber optic sensors by FY00; and decrease on-orbit
disturbances experienced by payloads by a factor of 10 by FY01 (a factor of 100 by FY11).
Technical challenges/barriers include: rapid and less costly manufacturing techniques for large
launch vehicle structures; accounting for the synergistic effects of the combined aspects of the
space environment; developing high fidelity simulations; reducing the EMI effects and
increasing the reliability/durability of Multi-Functional Structures; satellite structural isolation
without constraints on rattle space (clearance), weight, power, and volume, as well as interaction
between the isolator control system and the launch vehicle control system; rapid non-pyrotechnic
release mechanisms; and integration of neural network technology into structural control systems
during its operation. The technical approaches are: new structural concepts and construction
methods to decrease the weight and cost, as well as improving the conductivity and radiation
shielding capability of, satellite bus and secondary structures; new techniques to better
understand and predict the effects of the space environment on spacecraft structures; and
integrating power, communication, and electrical paths into the structure thus eliminating the
need for wiring harnesses, connectors, and electronic boxes (Multi-Functional Structures).
Structural control and vibration damping technologies are pervasive and support a wide range of
commercial and military customers including all DoD spacecraft program offices as well as
AFSPC, NAVSPAWARS, NASA, and other agencies.
| Svc/Agency POC: |
SMC/XRT POC: |
Customer POC: |
USASSDC POC: |
LtCol David Lewis
SAF/AQRT
(703) 602-9200
|
Col Robert Preston
(301) 363-0840
|
Maj Jon Wicklund
AFSPC
(719) 554-5824
|
Mr. Ed Bird
(205) 955-4871
|
Dr. Lewis Sloter
ONR, Code 332
(703) 696-1453
|
|
|
|
Programmed DTO Funding ($M):
|
FY96 |
FY97 |
FY98 |
FY99 |
FY00 |
FY01 |
| Total |
7.2 |
7.0 |
7.8 |
8.8 |
10.1 |
10.9 |
SP0506F Large Precise Structures. Develop material applications, light weight
deployable structures and structural precision alignment technologies to provide stable, high
performance from poor quality structures. Applications include surveillance, e.g., 'space
AWACS,' communications and direct energy weapons, e.g., space based laser (WE0404CF).
Current systems are limited not only by the physical size of the spacecraft, but by the quality and
alignment of the system after incurring stresses induced by launch and exposure to space
environment. On orbit construction of erectible systems with alignment and compensation by
adaptive optical systems could provide a four-fold increase in resolution over today's system.
Key technologies to be developed and demonstrated are extremely lightweight, large apertures
including dilute and inflatable optical and RF antennas, space erectible structures. Consideration
will be given to space apertures using silicon carbine subapertures and inflatable mirrors. Brute
force structural alignment and surface quality and configurations can be traded off with
wavefront correction of structural imperfections leading to major reductions in overall system
weight and consequently lower cost to place in orbit. In 1998, the technologies will be integrated
in the New World Vistas initiated Compensated, Large Lightweight Space Optics program, a
laboratory evaluation of integrated system performance which will begin in 1998. This program
will demonstrate in 2010 the performance of a revolutionary approach to a large aperture, high
resolution, space deployable imaging system implementation which will reduce optics payload
weight by at least 50% and launch cost proportionally. It will demonstrate space sensor
technologies required for very large aperture long dwell systems used for Global Awareness.
| Svc/Agency POC: |
SMC/XRT POC: |
Customer POC: |
LtCol David Lewis
SAF/AQRT
(703) 602-9200
|
Col Robert Preston
(310) 363-0840
|
AFSPC/DR, 21st Space Wing USSPC,
and other agencies
|
Programmed DTO Funding ($M):
|
FY96 |
FY97 |
FY98 |
FY99 |
FY00 |
FY01 |
| Total |
3.5 |
3.8 |
8.0 |
6.4 |
9.2 |
10.5 |
SP0606NFH Space Systems Survivability. Develop hardware and software techniques
required for space systems to survive and operate during flight without performance degradation
from the myriad of possible natural and manmade threats. Natural stresses arise from radiation,
debris, and chemical activity which can degrade spacecraft electronic and mechanical systems.
Beyond addressing the natural rigors of space, additional efforts are also needed to mitigate the
various hostile environments that might be created by an adversary. The most pervasive
challenge is assuring that spacecraft electronic systems have both total dose and Single Event
Effect (SEE) radiation tolerance. Future operations in moderate dose orbits (up to 50 krad total
dose over mission life; see SE2601AH DTO for radiation hardening used in high dose orbits) are
supported by two Navy projects nearing on-orbit operation. The prime experimental task of the
Microelectronics and Photonics Test Bed (MPTB) program is the measurement of radiation
effects, both on the ground and in orbit, with concurrent radiation dose and spectra measurements
for a number of primarily Commercial Off The Self (COTS) microelectronic and photonic
devices and subsystems. The space System Program Offices (SPOs), which provided the
prioritization to the MPTB program, will gain a near-term payoff in FY97 with the space
qualification of devices with a factor of 10 gain in capability for their space systems. Once the
space flight data has been reduced, the program's predictions and models will provide the broader
payoff of improved understanding of SEE processes, especially for reduced feature size devices,
and the radiation environment with initial availability by FY98. The Advanced Spacecraft
Computing and Autonomy Testbed (ASCAT) project will operate an advanced testbed of
computers aboard the DoD Space Test Program's ARGOS spacecraft to: (a) evaluate
performance and obtain comparisons among the Harris RH3000, TRW RH32, and Honeywell
RH32 processor designs operating in a DMSP type orbit, (b) evaluate fault-tolerant software
methodologies, (c) perform fault logging and statistical analysis, (d) and carry out on-orbit
processing of sensor inputs for autonomous operations. The payoffs for the ASCAT project will
be the technical basis for major satellite programs to select future computer and software designs
with system-level radiation tolerance and proven techniques for autonomous operation. Multiple
transitions of ASCAT test results to SPOs will begin in Sep 1997 and continue through Sep
2000. Air Force efforts on other natural sources of spacecraft degradation mainly address earth
orbiting debris and solar orbiting micrometeoroids. A predictive computer model of the debris
environment will become available by FY97 and a more general spacecraft predictive hazard
model has an expected release in FY99. Hostile environments include but are not limited to
directed/kinetic energy weapons (laser, microwaves, and kinetic projectiles) and collateral
nuclear effects. Tasks to address this threat include: threat susceptibility/ vulnerability
assessments of critical components, subsystems and systems; development of countermeasures to
mitigate vulnerabilities; and demonstration of technology options to support balanced strategies
to detect, avoid and operate in threat environments. Current technology efforts involve:
development of miniaturized radar and laser detectors for threat warning; sensor jamming
protection techniques for critical sensor optical components; front-end RF protection devices;
and predictive debris hazard models. These efforts will culminate in a space flight demonstration
in FY2000 which will support anticipated satellite block changes for SBIRS, MILSATCOM and
GPS. Current typical objectives for operating through a threat are: 10 E-4 SMATH Level 1 for
laser; 10 E-4 JCS for enhanced radiation; and the values are subsystem specific for RF. Current
typical survival objectives are: 1 SMATH Level 1 for laser; 1 JCS for enhanced radiation; and
140 dbW (EIRP) ground source for RF.
| Svc/Agency POC: |
SMC/XRT POC: |
Customer POC: |
LtCol David Lewis
SAF/AQRT
(703) 602-4200
|
Col Robert Preston
(310) 363-0840
|
Space SPOs, BMDO, DNA,
USSPACECOM, NAVSPAWAR,
DoD labs, NASA, other agencies,
commercial space assets
|
Ingham Meck
ONR
(703) 696-4825
|
|
|
Programmed DTO Funding ($M):
|
FY96 |
FY97 |
FY98 |
FY99 |
FY00 |
FY01 |
| Total |
7.5 |
8.0 |
7.4 |
7.4 |
7.4 |
7.5 |
SP0703FE Space-Based Guidance, Navigation, and Control (GN&C). The goal is
to develop new or improved GN&C hardware, software and techniques for use in
operational systems with a space component. This includes systems employed tactically in the
terrestrial environment as well as satellite and missile systems. Navigation techniques fusing
GPS data with local sensors and database information is an emerging core for much of the work.
There are presently two, albeit disparate, thrusts: (1) precision navigation on, or near, the earth's
surface and (2) the more classical space problems of satellite and missile Guidance, Navigation,
and Control (GN&C). The precision near-earth navigation problem has a focus on
providing the warfighter with a broad accurate digital representation of the operational theater
(consistent battlespace understanding). By FY98, the integration of data from GPS, local
navigation sensors, and Digital Terrain Database (DTD) source through advanced navigation
algorithms should demonstrate 1-3m positioning information. Beyond overcoming the data
fusion problem of generating useful information for situation awareness and path guidance,
anti-jam/anti-spoof GPS technology to mitigate active ECM, and GPS receiver satellite selection
algorithms appropriate cultural/natural terrain shadowing situation are technical challenges. In
the longer term, developing a concept that integrates the precision navigation with imaging
technology to support robust situation awareness, path guidance, and precision targeting
requirements should be completed by FY01. The precision guidance customers include
Silo-based ICBM SPO, AFSPC/DR and 20th Air Force. The foci for satellite and missile
GN&C are to develop and improve various sensor and system level technologies that (1)
increase accuracy and performance while reducing size, weight, and cost for both spacecraft and
missile navigation, attitude determination, orbit determination and propagation, and tracking; and
(2) improve understanding of nonlinear dynamical behavior and interaction with geomagnetic
field and long term orbital dynamics of artificial satellites. Recent tests have shown that orbit
determination algorithms under investigation are approximately 400% better than the fielded
AFSPC supplied state vector. Specific technology approaches are: (1) develop and improve
current accelerometer and gyroscope technology, to include ring laser gyros (RLGs) and
interferometric fiber optic gyros (IFOGs), and other solid state devices, performance by a factor
of 4 while reducing size, weight, and cost as compared to currently employed systems by FY02;
(2) increase GPS aided navigation system accuracy by a factor of 2 (goal 5-10 m absolute
positioning), reduce antenna weight and cost by a factor of 2, improve range metrics and tracking
while reducing range associated costs by FY04; (3) improve star tracker pointing accuracy by a
factor of 5 (goal 1 arcsecond), and decrease star tracker size, power, and weight requirements by
_33% by FY04; and (4) develop algorithms, computer software, and associated computer
hardware for autonomous navigation that will increase spacecraft navigation accuracy by a factor
of 3 (goal 30 m positioning accuracy) and attitude determination data by a factor of 2 (goal
<0.01 degrees) by FY04. The corresponding technical barriers are: (1) radiation hardening,
light sources, digital processors, coil selection and winding (IFOGs), mechanical dithering and
mirror durability (RLGs), gyro material, and micromachining processes; (2)The highly dynamic
space and missile environment, radiation exposure, robust software for real-time navigation data,
and the effects of plasma; (3) solid state detectors, digital processors, and optical alignment; and
(4) laser tracking and accurate ephemeris data. Satellite GN&C customers include, SMC,
AFSPC, Strategic Missile System Program Office, ONR, BMDO and others.
| Svc/Agency POC: |
SAF/AQQS: |
Customer POC: |
SMC/XRT: |
Mr. Ron Beard
NRL
|
Col Charles Pugsley
(703) 697-8123
|
Capt Tim Coy
(719) 554-3836
|
Col Robert Preston
(310) 363-0840
|
| |
USASSDC:
Mr. Ed Bird
(205) 955-4871
|
|
|
Programmed DTO Funding ($M):
|
FY96 |
FY97 |
FY98 |
FY99 |
FY00 |
FY01 |
| Total |
6.6 |
5.0 |
4.9 |
5.0 |
5.3 |
5.1 |
SP0806FCH Space Power Technology. Develop satellite power subsystems that will
enable a factor of two improvement for the total power system (8 W/kg at $6000/W) by FY00
and a factor of four improvement (15 W/kg at $4000/W) by FY05 over current system specific
power (~4 W/kg at $10000/W). In addition, establish the performance credibility of high
temperature, compact power sources by FY05 that should extend the availability of electrical
power for DoD satellites by at least a factor of five (into the 50-100 kW range). These increases
in system specific power will garner cost savings, increase power, and provide mass saving
which contribute to the use of smaller, lower cost launch vehicles at tremendous savings to the
government. To achieve these goals, significant technological advancements will be made in the
three space power areas: energy generation, energy storage, and power management and
distribution (PMAD). In energy generation, typical conversion values for solar cells are
nominally 18.5% today with arrays generating useable power at nominally 50 W/kg. By FY00,
the objective is to increase the conversion efficiency and specific array power to 28% and 100
W/kg, respectively, by developing higher efficiency photovoltaics, concentrator arrays, and
revolutionary solar thermal energy generation devices, as well as mitigating the space
environmental interaction effects on these technologies (especially for orbits in the radiation
belts). An increase to 35% efficiency and 120 W/kg is planned by FY05. To further extend the
range of available electrical power, technologies required for high-temperature, compact power
sources will be developed. Technical barriers include: compatibility and applicability of
advanced materials in the space environment; viability of manufacturing; and feasibility of solar
thermal conversion and limits on high-temperature power conversion efficiencies. In energy
storage, technology thrusts are aimed at raising the specific energy at the cell level from
nominally 50 Whr/kg (SOA) to 120 Whr/kg by FY00. It is planned to achieve 175 Whr/kg at the
cell level by FY05. More critical than specific energy is raising the cycle life limits to enable
spacecraft lifetimes competitive with aircraft systems. At the low altitude orbits of such systems
as a space-based JSTARS or AWACS storage elements should exceed 50,000 cycle lifetimes and
approach 100,000 cycles. The technical challenges to increase energy density are severe: highly
reactive chemicals (sodium, lithium, etc.); runaway electrochemical reactions; and general safety
concerns. An additional focus is the development of high voltage PMAD components that allow
electrical bus voltages of 70 V to 120 V resulting in a mass reduction of the electrical bus of
50-75%. Space power is considered a pervasive technology area, applicable to all spacecraft
program offices as well as AFSPC, NASA, and other government agencies, and to commercial
spacecraft.
| Svc/Agency POC: |
SMC/XRT POC: |
Customer POC: |
LtCol David Lewis
SAF/AQRT
(703) 602-9200
|
Col Robert Preston
(310) 363-0840
|
Maj John Wickland
AFSPC
(719) 554-5824
|
LTC Jyuji Hewitt
DNA
(703) 325-2251
|
|
|
Mr. Matt Holm
DNA
(703) 325-0818
|
|
|
Programmed DTO Funding ($M):
|
FY96 |
FY97 |
FY98 |
FY99 |
FY00 |
FY01 |
| Total |
13.0 |
14.7 |
15.6 |
18.0 |
10.2 |
10.2 |
SP0901F Satellite Control. Develop and integrate satellite control technologies for the
AF Satellite Control Network (AFSCN) to provide autonomous ground and space operations,
portable ground operations and data dissemination, and advanced operator environments for
satellite control. This effort emphasizes the development of systems with increased operational
capability and low acquisition and maintenance costs. Enhanced capability is achieved by
providing immediate information to the warfighter through portable systems and providing a
continuous upgrade process with flexibility so changing requirements can be easily satisfied.
Additionally, this provides a reduction in manpower requirements of 45% by FY98, and 66% by
FY02; a reduction in operations and maintenance (O&M) costs (with an increase in
capability) by 30% in FY00, and 50% by FY04. Decision support for anomalies will be added in
phases from FY96 through FY99, on-board autonomous satellite health and status capability will
be flight tested in FY02, machine learning systems will be added by FY04, and immersive
operator environments will be added by FY05. Technology challenges include: developing
reliable, verifiable self-learning computer systems, providing on-board autonomous satellite
control, and verifying correct performance of highly intelligent ground and space systems. Users
include AFSPC, USAF Space and Missile Systems Center SPOs, and select Civil, Navy, BMDO,
and other agency offices.
| Svc/Agency POC: |
USD(A&T) POC: |
Customer POC: |
LtCol David Lewis
SAF/AQRT
(703) 602-9200
|
Col Robert Preston
(310) 363-0840
|
BGen Marshall Ward
(719)554-9768
|
Programmed DTO Funding ($M):
|
FY96 |
FY97 |
FY98 |
FY99 |
FY00 |
FY01 |
| Total |
2.3 |
3.3 |
3.8 |
4.3 |
4.6 |
4.8 |
SP1006F Spacelift Propulsion. Develop and demonstrate advanced spacelift propulsion
technology for military and nonmilitary space launch systems. These systems (solid, liquid, or
hybrid) could be expendable vehicles or military multi-use vehicles. By FY00 the technology
will be developed to improve the payload capability by 9% and reduce the O&S (Operations
and Support) costs by 19% of expendable launch vehicles while improving the payload
capability by 71% and reducing the O&S costs by 34% for multi-use vehicles. By FY05 the
technology will be developed to improve the payload capability by 16% and reduce the
O&S costs by 21% of expendable launch vehicles while improving the payload capability
by 121% and reducing O&S costs by 65% for multi-use vehicles. By FY10 the technology
will be developed to improve the payload capability by 21% and reduce the O&S costs by
28% of expendable launch vehicles while improving the payload capability by 170% and
reducing the O&S costs by 79% for multi-use vehicles. All payoffs will be attained by
improving mass fraction (solid systems) or thrust to weight (liquid systems), specific impulse,
and reliability while decreasing hardware and support costs. Due to the chemicals involved in
solid propellant manufacturing, processing, and firing, solid propellants will be constrained by
many environmental regulations by the year 2000. Near term (within 5 years) solid propulsion
programs will work toward developing new chemicals and processes used in motor
manufacturing and created during solid rocket motor firing. These programs will be available for
the EELV Phase I (medium lift) program technology insertion date. Additional technical
challenges exist in developing low cost, environmentally clean solid propellants that maintain
current performance capabilities of current propellants, and new solid motor case materials for
low cost, low weight systems. Approaches like ultra high strength fibers (1000 ksi tensile
strength) and lower density resins will help decrease motor volume due to reduced case thickness
to overcome the technical challenges within the next ten years. Liquid engine improvement
programs will work toward higher operating speeds, smaller components, fewer parts, new
materials and manufacturing processes (like rapid prototyping), leak free connectors and
purgeless seals. Additional technical challenges exist in developing fluid film bearings, metallic
and non-metallic turbine materials, high temperature turbine materials, and low maintenance
(easy to replace) components for near term system advances. Other liquid system technical
challenges involve developing low cost LOX/RP-1 propellant additives to increase performance.
High c* (combustion efficiency), high specific impulse systems will require developing systems
with higher chamber pressures, and materials that can tolerate higher temperatures with high
thermal conductivity. These improvements will support upgrades to current vehicles, EELV
Phase II (heavy lift), EELV product improvement, and far term military reusable vehicles. This
technology will support the warfighter and overcome the AFSPC range, survivability, and rapid
response deficiencies by developing higher performing, lower cost engine systems while
extending the life, range, and reliability of our current launch vehicles. Development programs
will address Space Command's number one priority deficiency within the Space Lift Mission
Area Plan (MAP) of reducing launch costs. Since all space and launch vehicle systems have
propulsion sub-systems, advanced space propulsion technology supports a wide range of
commercial and military customers including all spacecraft program offices at SMC and space
missions within AFSPC. Specifically, technology developments in this area will support the AF
Space Command and Space and Missile System Center top priority concept of responsive, low
cost expendable launch vehicle development.
| Svc/Agency POC: |
SMC/XRT POC: |
Customer POC: |
Maj Jon Wicklund
(719) 554-5824
|
Col Robert Preston
(310) 363-0840
|
Dr. David Sayles
205-955-1585
|
LtCol David Lewis
(703) 602-9200
|
|
|
Programmed DTO Funding ($M):
|
FY96 |
FY97 |
FY98 |
FY99 |
FY00 |
FY01 |
| Total |
22.6 |
32.2 |
27.0 |
27.6 |
29.9 |
33.3 |
SP1106F Orbit Transfer Vehicle Propulsion. Develop and demonstrate upper
stage/spacecraft (chemical, solar electric, solar thermal) propulsion systems for reusable, or
expendable orbit transfer vehicles. This will support the warfighter by developing systems for
AFSPC with enhanced strategic agility for orbit transfer and insertion missions (movement from
LEO to GEO). The resulting systems will enable the United States to sustain its global presence
through timely and accurate placement of satellites for assured situational awareness.
Non-chemical systems (solar electric, solar thermal) do this through available long-life space
assets for orbit transfer or orbit insertion systems. Chemical systems do this through rapid
response orbit transfer or orbit insertion systems. Spacecraft operational capabilities will be
improved resulting in lower cost satellites that more effectively support the warfighter's critical
information gathering and global communications needs. Spacecraft capability could be
improved by using integral propulsion units, enabling orbital transfer, maneuvering, and
repositioning/stationkeeping functions being performed by a single propulsion system. By
FY00, the technology development for orbit transfer payload increases of 25% will be
demonstrated for high power solar electric/solar thermal systems. Spacecraft operational
capabilities will also be improved resulting in lower cost satellites that more effectively
support the warfighter's critical information gathering and global communications needs. By
FY05, the technology development for payload increases of 50% will be demonstrated for solar
electric/solar thermal systems. By FY10, the technology development for payload increases of
100% will be demonstrated for solar electric/solar thermal systems. Because chemical orbit
transfer systems work toward rapid response instead of long-life and are technically more mature
then solar electric/solar thermal systems, discreetly different potential payoffs exist. By FY00,
the technology development for payload increases of 5% will be demonstrated for chemical orbit
transfer systems. By FY05, the technology development for payload increases of 10% will be
demonstrated. By FY10, the technology development for payload increases of 15% will be
demonstrated. Attaining the cost and weight goals for propellant and pressurization tanks can be
achieved by overcoming the technical challenges of developing ultra-high strength graphite and
non-graphite fibers overwrapping a thin, metal, fluid compatible inner liner. The use of
advanced materials for highly flexible elastomeric bladders will meet the technical challenge of
improving compatibility with propellants over a longer duration and decreasing leakage rates.
For high power arcjets, the major technical challenge is cathode life. Technology needs to be
developed to extend the lifetime up to 2500 hours. This will be accomplished with either new
cathode materials or novel cathode designs. Since all space and launch vehicle systems have
propulsion sub-systems, advanced space propulsion technology supports a wide range of
commercial and military customers including all spacecraft program offices at SMC and space
missions within AFSPC. Specifically, technology developments in this area will support the AF
Space Command and AF Space and Missile System Center #2 priority concept of long-life, rapid
response solar orbit transfer vehicle propulsion systems.
| Svc/Agency POC: |
SMC/XRT POC: |
Customer POC: |
Maj Jon Wicklund
AFSPC
(719) 554-5824
(719) 554-5119 fax
jwicklun@spacecom.
af.mil
|
Col Robert Preston
(310) 363-0840
(310) 363-6442
|
|
LtCol David Lewis
SAF/AQRT
(703) 602-9200
(703) 602-9199
|
|
|
Programmed DTO Funding ($M):
|
FY96 |
FY97 |
FY98 |
FY99 |
FY00 |
FY01 |
| Total |
4.5 |
3.9 |
7.2 |
9.5 |
9.6 |
9.9 |
SP1206F Spacecraft/Satellite Propulsion (Solar Electric, Solar Thermal, Chemical).
Develop and demonstrate spacecraft/satellite (solar electric, solar thermal, chemical)
propulsion systems for long-life, responsive satellite vehicles. This will support the warfighter
by developing systems for AFSPC with enhanced strategic agility and highly reliable
reconnaissance/surveillance and communication capabilities. The resulting long-life systems
(solar electric, solar thermal) and rapid response systems (chemical) will enable the United States
to sustain its global presence through timely and accurate situational awareness. Spacecraft
operational capabilities will be improved resulting in low cost, lightweight satellites that more
effectively support the warfighter's critical information gathering and global communications
needs. Solar electric and solar thermal systems can achieve the following improvements: by
FY00, the technology development for on orbit life increases of up to 5% will be demonstrated in
addition to repositioning improvements of 200% for low power systems; by FY05, the
technology development for on-orbit life increases of 15% will be demonstrated in addition to
repositioning improvements of 350%; by FY10, the technology development for on-orbit life
increases of 45% with repositioning improvements of 500% will be demonstrated. Chemical
systems can achieve advancements as follows: by FY00, the technology development for a 5%
increase in either on-orbit life or repositioning will be demonstrated; by FY05, the technology
development for a 10% increase in either on-orbit or repositioning will be demonstrated; by
FY10, the technology development for a 15% increase in on-orbit life or repositioning will be
demonstrated. Spacecraft propulsion performance challenges (thruster efficiency and specific
impulse increases) work toward developing low power (200 watt) hall thrusters for micro and
nano satellite technology. Near term challenges are to create thrusters that can start-up and
continue operating efficiently at these low power levels. Approaches include developing several
types of cathodes (for start-up and operation) and increasing the magnetic field intensity (for
efficiency). Mid-term evaluation of this new system physics will enable far term increases in
thruster efficiency to further reduce costs and increase performance. Parallel efforts in micro
power processing unit technology (for this hall thruster) must be developed for the total system
viability. Goals to improve mass fraction and producibility, and to reduce hardware
(material/manufacturing) costs will be addressed by overcoming the technical challenges of
developing new expulsion device designs, materials and fabrication processes. Near term
hydrazine system mass fraction improvements reside in developing new propellant expulsion
diaphragm assembly fabrication techniques, including hydroforming and superplastic forming of
the diaphragm and outer shell pieces. These approaches will fulfill the technical challenges to
improve reliability, dramatically reduce component costs, and improve the repeatability in key
structural parameters such as diaphragm thickness. Since most space and launch vehicle systems
have propulsion sub-systems, advanced space propulsion technology supports a wide range of
commercial and military customers including all spacecraft program offices at SMC and space
missions within AFSPC. Specifically, technology developments in this area will support the AF
Space Command and Space and Missile System Center #2 priority concept of developing high
performance solar satellite propulsion systems.
| Svc/Agency POC: |
SMC/XRT POC: |
Customer POC: |
Maj Jon Wicklund
(719) 554-5824
|
Col Robert Preston
(310) 363-0840
|
|
LtCol David Lewis
(703) 602-9200
|
|
|
Programmed DTO Funding ($M):
|
FY96 |
FY97 |
FY98 |
FY99 |
FY00 |
FY01 |
| Total |
1.2 |
1.1 |
1.5 |
1.8 |
1.9 |
1.4 |