Implementing Standard Microsatellites for Responsive Space

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Implementing Standard Microsatellites for
Responsive Space a presentation for the AIAA
Responsive Space Conference Redondo Beach,
CA April 2, 2003
Jeff Janicik, Director of Flight Systems
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Responsive Microsats

• Design Constraints
• Methods of Meeting Design Constraints
• CHIPSat Case Study
• Launch
• Applications

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What are Responsive Microsats?

• Small (10-100kg) satellites that provide
  immediate benefits to the end user
• Design Constraints
• Minimal Cost
• Minimal Weight
• Maximum Capability
• Aircraft-Like Operability
• More emphasis on operational utility in the
  design of a system than RD
• Negative Impacts of RD approach
• Reduced error margin
• Increased support requirements
• Increased DTE
• Increased operating costs

The Usual Suspects
But how do you meet these design constraints?
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Method 1 Modularity
Mission

• DEFINITION Decomposition of a system into
  modules
• Effective modularization minimizes
  interdependencies and most cleanly decentralizes
  the system

Bus System
Power Subsystem
C2 Software
Tiers of Modularity within a Microsat Design
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Method 2 Common Industry Interfaces and
Protocols

• Use of well-supported, widely-used interfaces and
  protocols eliminate the need for custom code
• TCP/IP, IEEE, 1394, Commercial RTOSs, etc.
• Promotes rapid responsiveness for the ground
  communications element
• Integrated with global network as opposed to
  being a bent-pipe to the global network

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Method 3 Standardization

• Experiment/Payload receives standard users guide
  from the microsat provider
• Build it, and they will come!
• I.e., RSDO (but much room for improvement)
• Development risk and modifications become the
  responsibility of the experiment
• PC plug-n-play Industry Model
• Standard hardware module plus software driver

CHIPsat Sept 01
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Method 4 Autonomy

• Minimal crew (one person, part-time) Mission
  Control with anywhere, anytime monitoring
• Modular intelligent flight software agents that
  actively monitor and react to situations
• Survivable, yet reduced complexity by limiting
  spacecraft modes
• Survive
• Orient
• Execute
• Commission within a few passes

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Case Study CHIPSat

• First-ever NASA UNEX microsat
• 30W OAV to payload, 300 MIPS / 6W
• 3-axis zero momentum bias
• 100 TCP/IP end-to-end comm architecture combined
  with modular bus architecture
• Custom code development was minimal at all levels
  (VxWorks, Linux, Windows NT)
• Internet tools open up wide range of operational
  capability
• Distributed IT and mission ops
• On-board and Ground Autonomy
• 100 survivable -- NO time-critical operations
• Rigorous test program to prove new miniature (3U
  PCI) COTS-based SpaceDev avionics

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Case Study CHIPSat (contd)
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Result

• Responsive Microsat
• COTS standard interface
• Low-cost, high-volume
• Single-string, miniature, but capable
• Blue-suit operations
• Fundamental change in how we design satellites
• Operational utility incorporated into payload
  design process before its even conceptualized
• Faster implementation of technology
• Reduced emphasis on reliability
• Need rapid, low-cost launch capability!

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Responsive Launch

• Chicken or egg syndrome
• Small Launch Vehicles of the Future
• SpaceDevs High-Performance Mass Fraction (HPMF)
  Hybrid SLV
• Pump-fed, high O/F and N2O density
• TNT equivalent of nearly zero
• SpaceXs Falcon
• DARPAs RASCAL
• Others

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Application Technology Testbed

• Developmental and/or Follow-on TE for
  acquisition space systems
• Standard microsat busses can provide the core for
  low-cost technology testbeds and reduce big
  ticket program risks

• Less reliability on modeling and simulation
  because empirical data can be achieved in a
  timely and affordable fashion (test like you fly)
• Existing model NASAs sounding rocket program
  provides suborbital technology testbed

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Application On-Orbit Maneuvering and Transfer

• 6 standard microsats with imaging payload from
  one ESPA launch stored in LEO waiting for tasking
  to survey area of interest
• SpaceDevs Maneuvering and Transfer Vehicle
  (MTV-3) is a standard microsat bus with hybrid
  propulsion capability
• Storable, non-toxic, and re-startable
• 800 m/s delta-V, bias
• Move into low-altitude position and return by
  command

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Application Launch on Demand

• Standard microsat bus combined with ISR payload
  launched into low orbit over theater with data to
  warfighter within hours
• Could be used for short-term coverage while
  larger, dedicated ISR spacecraft are maneuvered
  or placed in orbit for permanent coverage

In-Theater
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Application Educational Payloads

• Ideal place to institutionalize new set of
  rules with standard, modular, and autonomous
  microsats
• Students can build, launch, and operate payloads
  before graduating
• Microsat can be provided as heath-kit so
  students can learn satellite design through
  assembly and test
• Investigation of a capable
  3-axis stable bus at a recurring
  cost of 500K
• Predefined payload interface

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Summary

• Constrained by cost, size, capability, and the
  need for aircraft-like operability
• Responsive microsat design characteristics
• Modularity
• Common Protocols and Interfaces
• Standardization
• Autonomy
• Extensive range of applications for a standard
  microsat provided responsive launch exists
• Technology Testbed
• On-orbit Maneuvering and Transfer
• Launch On-Demand
• Educational Payloads