STP BRIEF to SACT 2000

1
Space Test Program Briefing November 2001
LT Paula Hildebrand (USN) Mission Design Branch
Space Test Program Naval Liaison
2
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.
3
STP Contributions to Operational
SystemsSurveillance Satellites
POAM III (S96-2) Polar ozone and aerosol measure
ments
NPOESS
STS-79 (tent) PLUMES MSX observation of Shuttl
e 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 sy
stem
4
STP Contributions to Operational Systems
Communications Satellites
Communications Satellites and Classified Users
STEP M4 (P95-1) Electromagnetic Propagation Expe
riment
REX II (P94-2) Trans-ionospheric radio signals
DSCS
Army RF Systems
ARGOS (P91-1) Ionospheric modeling and electric
propulsion
5
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 Sh
ielding Design
ARGOS (P91-1) HTSSE II ESEX GIMI USA SPADUS
HIRAAS
Sensors
Satellite Autonomy
Electric Propulsion
6
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

7
(No Transcript)
8
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 de
signs
9
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

10

11
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
12
STP Modes of Space Flight

• Micro/Mini Spacecraft
• Microsat (
• Minisat (
• 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

13
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
14

• 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.

15
STP LAUNCH HISTORY 1965 - Mar 2001
16
NASA/STP Kodiak StarPAYLOAD SUITE
NASA STARSHINE
SAPPHIRE
PCSAT
PICOSAT
PAYLOAD UPPER DECK
MODEL 38 PAYLOAD ADAPTER
17
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

18
ESPA
19
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
20
STPs MLV 05 Mission
GIFTS/IOMI/IMAGE
NPSAT
TBDSAT
TECHSAT 21 (3)
STPSAT
21
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

22
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
23
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

24
-MLV 2005-
Issues (Equipment/System/Financial/Management/Op
erations)

• 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

25
Schedule
26
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

27
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

28
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, an
d promote the NAVY within SMC/Det 12
29
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 - Enginee
ring/Test and Integration (O-3) Space Shuttle/
ISS Mission Manager (O-3), Johnson Space Center
RSC Operations Officer (O-3) - manage mission p
lanning
through on-orbit operations
4 Additional Navy Space billets
- leverage off Air Force expertise
- experience cradle-to-grave space programs
30
Back up Slides
31
Coriolis Mission Overview
32
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

33
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
  

34
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
35
SMEI Science
CME Electrically Charged Particle Clouds with Ent
rapped 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

36
Space Vehicle Configuration
37
WindSat Components
38
SMEI Components
Data Handling Unit
Door Actuator
Radiator
Bright Object Sensor
Baffle Door
Camera Baffle
Camera Strong Box