PowerPoint Presentation STP BRIEF to SACT 2000

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Space Test Program Briefing November 2001
LT Paula Hildebrand (USN) Mission Design
Branch Space Test Program Naval Liaison
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SecDef Direction on STP (6 Nov 95)
STP Management and Funding Policy directs . .
. that the Space Test Program will maintain a
highly technical, capable management organization
for providing payload integration, launch
support, and orbital support. and . . .
reaffirms STPs role as a multi-user space
program whose role is to be the primary provider
of spaceflight for the entire DoD space research
community.
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STP Contributions to Operational
SystemsSurveillance Satellites
POAM III (S96-2) Polar ozone and aerosol
measurements
NPOESS
STS-79 (tent) PLUMES MSX observation of Shuttle
plumes
SBIRS / SMTS
TSX-5 (P96-2) Mobile Target Detection Radiation
Sensing and Diagnosis
DMSP
ARGOS (P91-1) SSULI sensor demo
GPS NDS Package
FORTE (P94-1) RF detection and discrimination
system
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STP Contributions to Operational Systems
Communications Satellites
Communications Satellites and Classified Users
STEP M4 (P95-1) Electromagnetic Propagation
Experiment
REX II (P94-2) Trans-ionospheric radio signals
DSCS
Army RF Systems
ARGOS (P91-1) Ionospheric modeling and electric
propulsion
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STP Contributions to Operational Systems
Technology Advances
STS-87 COOLLAR Joule Thomson cryocooler
Classified Program
Cryocoolers
DMSP follow-on
TSX-5 (P96-2) STRV-2 CEASE
SMTS
Electronics and Processors
Spacecraft Materials, Radiation Hardening and
Shielding Design
ARGOS (P91-1) HTSSE II ESEX GIMI USA SPADUS HIRAAS
Sensors
Satellite Autonomy
Electric Propulsion
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Space Test Program Mission

• Fly the maximum number of DoD experiments
  consistent with priority, opportunity, and
  funding
• STP serves all of DoD-- reduces duplication ---
  saves money.
• STP works from a prioritized list of sanctioned
  experiments, uses available budget, and searches
  for the most cost effective means to reach space.
• STP funds small launch vehicle, spacecraft,
  payload integration, and orbital operations for 1
  year
• Originally chartered by OSD in 1965
• Revalidated by SecDef Perry in 1995

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(No Transcript)
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WHAT DOES THE SPACE TEST PROGRAM (STP) DO?

• STP Programmatic Objectives
• Evaluate early operational capabilities
• Demonstrate new space systems and technologies
• Characterize space environment or sensor physics
• Reduce risk by flight testing prototype systems
  and components

• Payload Services Provided to SERB and
  Reimbursable customers
• Mission Design Studies
• Spacecraft acquisition, Payload integration and
  test
• Launch on ELVs (via RP) or launch on shuttle (via
  STH)
• One year of on-orbit operations (via VO)

STP provides cost effective way to flight test
new space systems technologies, concepts, and
designs
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DoD Space Experiments Review Board (SERB)

• Preceded by Service and other agency boards
• Chaired by SAF/AQS as USAF executive agent for
  DOD
• Supports broad voting membership
• DOD OSD, BMDO, NRO
• Warfighters USSPACECOM
• Services SAF/AQ, OPNAV, HQDA
• MAJCOMs AFSPC, NAVSPACECOM, USA SMDC
• Acquirers SMC
• Labs AFRL, NRL
• USG NASA
• Approves and prioritizes which DOD-sponsored
  technologies should be funded and flown by STP
• Provides strong consideration of operational need
• Military relevance is 60 of score

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STP Process
Launch Options
STP assists PI in SERB GO/NO GO decision
Yes
No
Enough to execute?
STP Required?
No
SHUTTLE COMPATIBLE?
ELV Mission Design Process
No
Yes
Yes
Acquisition As Required
Service/Agency SERBs
Shuttle Mission Design Process
DOD SERB
Mission Execution
No
DOD SERB List
Yes
LAUNCH
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STP Modes of Space Flight

• Micro/Mini Spacecraft
• Microsat (lt200 lb tw) Missions
• Minisat (lt350 lb tw) Missions
• Commercial/DoD Secondary or STP Shared Launch
• Small Class Spacecraft
• Pegasus/Taurus Class Launch
• Larger Class Spacecraft
• Approximately one mission every 4 years per PMD
• Delta II / EELV Class
• Potential Multiple Spacecraft vice One Large
  Spacecraft
• Piggybacks
• STP Experiments Added to Non-STP Spacecraft
• Commercial and NASA/DoD Targets of Opportunity
• Space Shuttle Missions
• Shuttle Payload Bay and Middeck Lockers
• International Space Station

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Modes of Space FlightData from 1965 - 2001
155 MISSIONS FLOWN
416 EXPERIMENTS FLOWN
Piggybacks
Piggybacks
Shuttle
Shuttle
Freeflyers
Freeflyers
The number of experiments flown is determined by
available dollars and available domestic/foreign
flight opportunities
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• 12 Weather/Space Weather (Including 1, 8, 9,
  10)
• 3 Micro Devices/Micro Satellite Technology
• 2 Communications
• 2 Space Force Protection/Force Enhancement
• 1 Power (Batteries, Solar Arrays)
• 2 Space Radiation (Radiation-Hardened
  Electronics)
• 13 Others
• Optics, Satellite Constellations/Formations,
  Navigation, X-Ray Imager, Human Physiology, Solar
  Sails, Spacecraft Thermal Control, Inflatable
  Antennas, etc.

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STP LAUNCH HISTORY 1965 - Mar 2001
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NASA/STP Kodiak StarPAYLOAD SUITE
NASA STARSHINE
SAPPHIRE
PCSAT
PICOSAT
PAYLOAD UPPER DECK
MODEL 38 PAYLOAD ADAPTER
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CORIOLIS Program Overview

• Program Objectives
• Coriolis spacecraft (S/C) will support the
  objectives of the WindSat and Solar Mass Ejection
  Imager (SMEI) experiments
• Mission Life - 3 Years Design, 5 Years Goal
• Initial Launch Capability (ILC) -- June 2002
• Program Cost Approximately 44M
• Includes spacecraft, LV fairing modification,
  1st year of on-orbit operations, launch range
  costs
• Does not include cost of experiment development
• Does not include funding for Titan II -- provided
  by SAF/AQS to Titan SPO

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ESPA
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MLV-05 Mission Description

• ESPA--EELV Secondary Payload Adapter--Space Test
  Program and Air Force Research Lab
• Better utilizes EELV margins and provides
  standard access to space for small satellites
• MLV-05 will be the first flight of ESPA

ESPA
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STPs MLV 05 Mission
GIFTS/IOMI/IMAGE
NPSAT
TBDSAT
TECHSAT 21 (3)
STPSAT
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MLV-05 Baseline Mission Profile(this data is for
LV planning!)

• IOMI is Prime given 2000kg mass budget
• Orbit GTO _at_ 27 inclination, desire 5
• ESPA Ring given 130kg mass budget
• TechSat 21 given 180kg x 3 spacecraft 540kg
  mass budget
• NPSat 1 given 70kg mass budget
• STPSat given 180kg mass budget
• 6thSat (margin) given 180kg mass budget
• Bottom Line
• 3100kg to LEO 2130kg from LEO to GTO
• Secondary orbit goal (all secondaries will deploy
  to same orbit)
• Altitude 550km, /- 10 km
• Inclination 35.3

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MLV-05 Mission Description

• IOMI--Indian Ocean METOC Imager--Office of Naval
  Research
• IOMI Sensor is GIFTS--Geosynchronous Imaging
  Fourier Transform Spectrometer (NASA EO-3 New
  Millennium Program)
• IMAGE rideshare--Ionospheric Mapping and
  Geocoronal Experiment--Naval Research Laboratory
• IOMI is 1 on the 2000 SERB, IMAGE is 5

IMAGE
GIFTS
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MLV-05 Mission Description

• NPSat1--Naval Postgraduate School Spacecraft
  Architecture and Technology Demonstration--Naval
  Postgraduate School (NPS)
• Microsat class spacecraft
• Provides hands-on education for officer students
  at NPS
• Demonstrate COTS technology in spacecraft
  architecture as a means of decreasing development
  time, and increasing reliability in software
  development
• NPSat1 is 29 on the 2000 SERB

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-MLV 2005-
Issues (Equipment/System/Financial/Management/Ope
rations)

• EELV Special Study with Boeing through SMC/MV--
  Phase II
• Critical step in determining mission profile,
  identifying unique issues
• Secondary deployment sequence being reviewed at
  SMC/VO
• Integrating Contractor-- RFP release under
  review
• Must expedite acquisition in order to meet
  mission requirements

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Schedule
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STP Summary

• STP is a multi-user space program whose role is
  to be the primary provider of spaceflight for the
  entire DoD Space Research Community
• STP provides access to space through various
  means
• Freeflyer Spacecraft
• Space Shuttle / Space Station
• Piggybacks
• These services are available at potentially no
  cost to DoD SERB endorsed experiments subject to
  STP level of effort funding (approx 45M/year
  LOE)
• These services are also available to other
  customers on a cost reimbursement basis
• STP continues to seek the most cost effective
  means of spaceflight possible
• Expect increased use of Micro and Mini Satellite
  approach

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BOTTOM LINE

• STP IS A GOOD DEAL FOR THE NAVY!!!
• Navy (mostly NRL and ONR) Leverages
• Millions of dollars annually
• Personnel (Air Force and Aerospace Corp.)
• Experience

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Experience Tour with STP

• MLV05 Studies
• Boeing Special Studies (Finite Element Model
  (FEM), etc)
• Mini Coupled Loads Analysis (Mini CLA)
• Deployment sequence of secondaries - TechSat 21,
  NPSat, STPSat
• Systems level review/study of current program
  (CORIOLIS)
• testing and evaluation, risk reduction analysis
• NPSat Studies
• triple junction solar cell study
• integration/impact on MLV05

Get exposure to acquisition programs and
Aerospace space systems engineering expertise,
and promote the NAVY within SMC/Det 12
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Navy Space Billets within SMC/Det 12
SMC Detachment 12 Kirtland AFB NM
NRL Naval Liaison (O-3) - Mission Design Chief,
Mission Design/ Deputy Program Director
(O-5) Tri-Service Spacecraft Division -
Engineering/Test and Integration (O-3) Space
Shuttle/ISS Mission Manager (O-3), Johnson
Space Center
RSC Operations Officer (O-3) - manage mission
planning through on-orbit operations
4 Additional Navy Space billets - leverage
off Air Force expertise - experience
cradle-to-grave space programs
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Back up Slides
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Coriolis Mission Overview
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Program Overview

• Program Objectives
• Coriolis spacecraft (S/C) will support the
  objectives of the WindSat and Solar Mass Ejection
  Imager (SMEI) experiments
• Mission Life - 3 Years Design, 5 Years Goal
• Initial Launch Capability (ILC) -- 15 December
  2001
• Program Cost Approximately 44M
• Includes spacecraft, LV fairing modification,
  1st year of on-orbit operations, launch range
  costs
• Does not include cost of experiment development
• Does not include funding for Titan II -- provided
  by SAF/AQS to Titan SPO

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Experiment Objectives

• WindSat - Sponsored by ONR - Ranked 2 on 97
  SERB
• Demonstrate capability of polarimetric microwave
  radiometer to measure ocean surface wind vector
  (speed and direction) from space
• 25km resolution of wind field with /-2m/s speed,
  /- 20º direction accuracy
• Demonstrate support to warfighter with real-time
  tactical downlink of radiometer products from
  spacecraft to the field
• Transfer technology to NPOESS for risk reduction
  on CMIS
• Solar Mass Ejection Imager (SMEI) - AFRL - 8 on
  97 SERB
• Using a multiple-CCD camera system, detect and
  track solar mass ejection's as they propagate
  through the interplanetary medium
• Develop algorithms that use data from these
  images to give 1-3 days advance warning of
  geomagnetic disturbances
• Predict Arrival Time of Disturbances at Earth
• Provide Data Inputs to Coupled Environmental
  Models
• Predict Ionospheric Impacts on Communications,
  Navigation and Surveillance
• Predict Space Particle Environment Hazards to
  Spacecraft Operations

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Passive Microwave Polarimetry A Scientific
Breakthrough

• Ocean Surface Emission Varies With Wind Speed and
  Direction
• A/C Measurements Have Shown That the Wind
  Direction Signal Is Measurable at Typical Wind
  Speeds
• Polarimetric Radiometry Measures the Stokes
  Vector Which Provide Information Needed to
  Retrieve the Ocean Wind Vector

Upwelling Microwave Emission
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SMEI Science
CME Electrically Charged Particle Clouds with
Entrapped Magnetic Field Solar Thunderstorms

• Effects at Earth
• Geomagnetic Storms
• Energetic Particles

Solar Sector Boundary

• Problems for Warfighter
• Geolocation Errors
• Satcom Disruption
• Spacecraft Anomalies
• Satellite Drag
• Power Grid Damage
• Radar False Targets

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Space Vehicle Configuration
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WindSat Components
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SMEI Components
Data Handling Unit
Door Actuator
Radiator
Bright Object Sensor
Baffle Door
Camera Baffle
Camera Strong Box