Developing Responsive and Agile Space Systems - Space-Library

Agile launch is one component required
to support the goals of the
Operationally Responsive Space
(ORS) Office, whose mission is to rapidly
augment DOD space systems to support
the warfighter in near real time. For ORS,
“rapidly” is defined as mission call-up to
launch in a matter of days or weeks. The target
launch time for augmentation missions
is six days. Typical DOD missions currently
take years and even decades to become
operational on orbit, so the ORS goal is an
ambitious one. Agile space launch involves
planning, acquiring, and executing a launch
quickly, but more than that, it requires
flexibility in mission design, availability of
multiple spacelift options, and a readiness to
seize opportunities.
The Aerospace Corporation has provided
systems engineering support to the
ORS Office since its founding in May
2007. Aerospace has also provided systems
engineering and mission assurance support
to the DOD Space Test Program (STP)
since its inception in 1965. STP is the
primary provider of mission design, spacecraft
acquisition, integration, launch, and
on- orbit operations for DOD space experiments
and technology demonstrations. The
typical mission timeline is three years from
start to on-orbit operability, and for two
recent missions, the timeline was under 12
months from call-up to launch.
These two recent missions, Kodiak Star
and Nanosat-2, illustrate the successful
application of the principles of agile space
launch. For the Kodiak Star mission, STP
and NASA, in approximately 11 months,
identified and prepared a payload to fly
aboard the Athena I launch vehicle. The
Nanosat-2 spacecraft, in storage for a year,
was reconfigured in four months to fly on
the Delta IV heavy-lift vehicle demonstration
in 2004.
These two launches, as case studies, provide
valuable insights into how to reach the
ambitious launch goal of six days. For both
missions, Aerospace was a key member of
a small team that provided systems engineering
support directly to the Air Force
mission manager, and then supported the
readiness review process with a mission
risk assessment to the Air Force mission
director.
A survey of current launch vehicles that
endeavor to have a “rapid” launch capability
is also useful in understanding how far
the industry must come to meet the six-day
goal. For example, the Minotaur family of
vehicles, which use surplus ballistic missile
components, provides low-cost, reliable
space launch capability to meet U.S.
government small-satellite requirements.
The Falcon 1 and Raptor series launch vehicles
provide additional launch options for
small payloads from STP and other DOD
programs. Aerospace was a member of the
government team developing the payloads
that flew on the eight Minotaur missions to
date and is involved at varying levels in five
of the seven Minotaur missions next scheduled
for flight.
STP is also working to use the excess
capability—the additional launch vehicle
performance and volume margin not used
by the primary mission—on launches of
government Evolved Expendable Launch
Vehicles (EELV) to fly both research and
operational payloads. Aerospace was instrumental
in the design and development
of the EELV Secondary Payload Adapter
Enhanced fairings and accuracy available for each vehicle
ORS compatible due to Ground-based Midcourse Defense (GMD)
heritage components
Minotaur 1 Minotaur 2 Minotaur 3 Minotaur 4 Minotaur 5
S1
S2
S3
S4
S5
Application
M55A1 (GFE)
SR 19 (GFE)
Orion 50XL
Orion 38
HAPS (Optional)
Spacelift
M55A1 (GFE)
SR 19 (GFE)
M57 (GFE) (Orion 50XL optional)
(N/A)
(N/A)
Suborbital/target
SR-118 S1 (GFE)
SR-119 S2 (GFE)
SR-120 S3 (GFE)
Super HAPS
(N/A)
Suborbital/target
SR-118 S1 (GFE)
SR-119 S2 (GFE)
SR-120 S3 (GFE)
Orion 38 (Star 48BV optional)
HAPS (optional)
Spacelift
SR-118 S1 (GFE)
SR-119 S2 (GFE)
SR-120 S3 (GFE)
Star 48BV
Star 37FMV
MTO/GTO/Lunar
Performance
581 kg to LEO
Larger fairing optional
LEO=185 km, 28.5°
Ballistic=VAFB to RTS
441 kg ballistic
(524 kg w/ Orion 50XL)
Larger front end optional
3064 kg ballistic
Larger fairing optional
1636 kg to LEO
(1931 kg w/ Star 48BV)
700 kg to MTO (GPS)
584 kg to GTO
392 kg to TLI
Above: The Minotaur 1 through 5 vehicles with their corresponding application
and performance information. Aerospace was a member of the government team
developing the payloads that have flown on the eight Minotaur missions to date
and is involved at varying levels for flights of five more scheduled for launch.
Previous page: An Athena 1 launch vehicle lifts off the launchpad at Kodiak Launch
Complex with the Kodiak Star spacecraft onboard Sept. 29, 2001.
Crosslink Summer 2009 • 19