# Presentation: 656492

## Deep Space 1

**Deep Space 1**
- Technology Space Flight Validation Status
- April 6, 1999

- These charts can be downloaded from URL: http://nmp.jpl.nasa.gov/ds1/NewsConference/
- High resolution images of DS1 can be viewed at URL:  http://www.jpl.nasa.gov/ds1news

## Deep Space 1•  System Level Validation of 12 Breakthrough Technologies

- Deep Space 1•**  System Level Validation of 12 Breakthrough Technologies**

**Remote Agent Architecture**

**Multifunctional**
**Structure**

**Advanced**
**Solar**
**Concentrator**
**Array**

**:  Industry Partner**

## Illustration of Benefits of DS1 Technologies

**•  ****Significant reduction in injected mass enables use of lower cost launch vehicle**
**•  ****Ion propulsion and miniaturization of spacecraft subsystems and instruments enabled by NMP technologies results in spacecraft mass reduction  **
**•  ****With standard technology, DS1 would be ~3 times heavier and would require a Delta III - class launch vehicle**
** ****Conceptualized DS1 using standard technology with similar functionality/trajectory:**
**N****2****O****4****/MMH bipropellant propulsion system**
**Mars ‘98 - class telecom**
**Cassini-type plasma instrument**
**Cassini-type visible / IR spectrometer**
**Scaled solar array**
**DS1 planned trajectory using total fuel**
** **
** ****DS1 ion propulsion and other technologies offer significant benefits to future missions**

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**Standard Tech**

**Injected Mass (kg)**

- 486

**DS1**
**Delta II**
**(7326)**
**Cost: ~$45M**

- ~1,300

**DS1**
**Delta III**
**class**
**Cost: ~$85M**

## Technology Validation Status

- March 31, 1999

## Ion Propulsion System

_**Ion Propulsion System**_

-  High-specific-impulse xenon ion propulsion system for deep space primary propulsion.
- Ion propulsion technology has been under development at NASA since the 1950s
- DS1 is the first use of ion propulsion for primary propulsion in deep space

-  Commercial sources and development partners
-  All flight ion propulsion equipment delivered by industry
-  Hughes Electron Dynamics Division
-  Spectrum Astro, Inc.
-  Additional development partners
-  Moog, Inc.
-  Physical Science, Inc.
-  NASA facilities involved
-  Glenn Research Center
-  Jet Propulsion Laboratory
-  Marshall Space Flight Center

## Ion Propulsion System Validation

- Flight Validation
- 100% complete on 01/99
- Performance validated over operating range of power levels
- Ion propulsion has increased the DS1 spacecraft velocity by 540 meters per second by April 6th.
-  By April 6, the ion engine will have 1300 hours of operation in space

**Flight Validation Rationale**
**• ****Perceived high risk was a barrier to use for science missions**
- Paradigm shift in propulsion approach from conventional periodic trajectory correction thrusting and cruise, to continuous thrusting
- Lack of relevant in-flight experience
-  **Validation **
** ****System level testing**
- Ion propulsion working with
-    other spacecraft subsystems
- Mission Operations team impact
**Measure interactions **
**  ****with spacecraft and **
**  ****space plasma environment**
- -  Determine compatibility of ion propulsion with
-    science observations

## Ion Propulsion Technology Benefits

- Using Small Launch Vehicles (Med-Lite)
- Based on Ion Propulsion

_**Ion Propulsion Technology Benefits**_

**Enables greater spacecraft mass to propellant mass ratio**
**Shortens flight time for a given mission**

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- Chemical Propulsion

- Ion Propulsion

- Ion Propulsion

- Chemical Propulsion

- Main Belt
- Asteroid
- Rendezvous

- Comet
- Rendezvous

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- Chemical Propulsion

- Ion Propulsion

- Ion Propulsion

- Chemical Propulsion

- Main Belt
- Asteroid
- Rendezvous

- Comet
- Rendezvous

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**Net Spacecraft Mass**

**Flight Time**

## Solar Concentrator Array Technology

- Ion engine requires high-power solar array - electric energy replaces chemical energy of conventional propulsion
- High power density (lower cost) of solar array achieved using high-efficiency solar cells and concentrator lenses
- Deployable Concentrator Elements - 7:1 concentration (1st system in space)
- Allows 1/7th as many solar cells, thus reducing array costs
- Multi-band gap solar cells - are active at multiple wavelengths
- Developed by AEC-Able Engineering, Inc., Entech Tecstar, under Ballistic Missile Defense Organization sponsorship and NASA Glenn Research Center

## Solar Concentrator Array Technology Validation

- Flight validation rationale
- Deployment and mechanical stability in space
- Verification of cell performance
- Technology validation 100% completed (11/98)
- Successful deployment
- Array performance verified
- Stable performance through first  5 months of mission
- Stable power supply during ion engine firings

## Examples of Future Users of Ion Propulsion & Solar Concentrator Array Technologies

_**Examples of Future Users of Ion Propulsion & **__**Solar Concentrator Array Technologies**_

## Small Deep Space Transponder(SDST)

**3 times mass reduction**
**Greater functionality (includes Ka-band) than conventional deep space transponders:**
**Ka-band exciter**
**Beacon tone generation for Beacon Monitor Operations Experiment**
**Advanced Radio Frequency integrated circuit and packaging technology enables the mass and size reduction**
**Developed by Motorola Corporation**

_**Small Deep Space Transponder**__**(SDST)**_

## Small Deep Space Transponder Validation To Date

**Flight validation rationale**
**End-to-end demonstration in space with ground tracking stations**
**Reduced risk for future science missions**
**Successful communications and radiometric measurements demonstrated at both X- and Ka-bands**
**Technology validation 100% completed (12/98)**

** ****One-way and two-way communications (X-band uplink and X- and Ka-band downlinks)**
** ****Ranging/Doppler (X-and Ka-bands)**
** ****Broad range of communication rates**
** ****X-band beacon tones transmission for the Beacon Monitor Operations Experiment**

## Small Deep Space Transponder Benefits

- 	1995 - Cassini Deep Space Transponder
- 11 kg, 22 watts,
- 11,500 cm3

- 1998 - DS1 - Small Deep Space Transponder
- 3 kg, 17 watts,
- 2000 cm3

**•  ****Significant reduction in mass, volume and cost with equivalent to greater performance to Deep Space Transponders used on Cassini, NEAR and Stardust missions**

## Examples of SDST Use in Future Science Missions

## Autonomous Navigation (AutoNav)

**CONVENTIONAL NAVIGATION**

**	**

**Radio Tracking**

**Images sent**
**and processed on**
**ground**

**Optical approach**

**AUTONOMOUS NAVIGATION**

*****

*****

**Optical Approach**

**Maneuver computed on spacecraft**

**Optical triangulation in cruise**

** ****Complete and integrated autonomous optical navigation and trajectory control system**
** ****Uses science-quality camera images of asteroids, stars and target bodies to estimate spacecraft position and compute control operations for trajectory maintenance and parameters for approach navigation and science observations**

**•  ****AutoNav developed by NASA Jet Propulsion Laboratory**

## DS1 AutoNav Validation

**Flight validation rationale**
- Verify interactions among spacecraft attitude control, command and data, image acquisition and propulsion functions in realistic flight operation scenario
**Validations complete to date:**
- Autonomous operation of the ion propulsion system
- Provides automation of the ion propulsion system engine start, shutdown, turn on and continuous operation cycles, per navigation plans stored aboard the spacecraft
- Autonomous picture planning and sequencing.
- Provides automation of navigation picture-taking-turns and onboard data processing.
- On-board ephemeris services
- Provides spacecraft positions in relation to the Sun, Earth and target asteroid in the inertial coordinate system
- Autonomous Image Processing:
- With onboard processed images, automatic determination of spacecraft position velocity
- Autonomous Maneuver Planning:
- Automatic planning of ion propulsion system thrusting
- Validation 75% complete
**Validations planned**
- Approach and encounter with the asteroid
- Confident of 100% complete validation by July 1999

## Benefits of Autonomous Optical Navigation

- Greatly Reduced Tracking Requirements
- Ground-based tracking in support of spacecraft navigation can be virtually eliminated
- Enhanced Mission Science
- 25 times more accurate than conventional navigation accuracy
- Allows for closer flybys and rendezvous with planets, comets and asteroids at low risk to the spacecraft
- Enhanced science data acquisition through autonomous camera pointing
- Preliminary case study performed to illustrate AutoNav benefits

*“**Flagship”*

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- AutoNav

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**Conventional vs. AutoNav for [total work years (wy)]**

- * 	Long duration (5-10 years)
- ** 	Short duration (1-2 years)

## AutoNav Future Users

- Missions requiring precise terminal targeting of spacecraft position and/or remote sensing instruments. For example, Europa Orbiter and Discovery missions

*Europa Orbiter: *Missions with very sensitive trajectory control requirements and/or extreme fuel constraints.

- Missions with autonomously delivered and/or guided penetrators.

**Discovery Projects**

## Miniature Integrated Camera-Spectrometer (MICAS)

_**Miniature Integrated Camera-Spectrometer (MICAS)**_

- MICAS is the first fully integrated camera-spectrometer operating from the ultraviolet through infrared wavelengths
- MICAS advantages for planetary and terrestrial remote sensing:
- Combines 4 separate instruments into single instrument with common optics, electronics and structure
- Combined functionality and small size enables new class of remote sensing science capability from small spacecraft:
- Planetary Exploration
- Terrestrial Remote Sensing
- Developed by SSG Inc., Rockwell International Science Center, University of Arizona, Boston University, U.S. Geological Survey, and NASA Jet Propulsion Laboratory

**	****MICAS Technologies**
** ****New system architecture, optical / thermal design**
** ****New material (SiC)**
** ****New detectors**
** ****No moving parts**

## Miniature Integrated Camera-Spectrometer Validation

***Validations to date***
- Successful launch & validation of integrated silicon carbide optics & optical bench
- Validation of integrated low-noise electronics
- Validation of electronically shuttered visible channel
- Provided optical navigation data
- Calibration of 3 of 4 channels
- Validation 75% complete** **
***	******	******	******	******Future Validation***
- Long-term stability of optics and optical bench.
- Validate ultraviolet channel and verify calibration
- 100% technology validation of MICAS planned for 07/99

- Flight Validation Rationale:
-   Perceived risk of highly integrated instrument

## Benefits of MICAS TechnologiesComparison to Cassini Remote Sensing Instruments

_**Benefits of MICAS Technologies**__**Comparison to Cassini Remote Sensing Instruments**_

- MICAS
- Mass:13 kg
- Power: 13 W

- Mass: 100 kg
- Power: 90 W

-  Enables multi-observable science measurements from small (low cost) spacecraft
-  Examples of future users of MICAS technologies
-  Europa mission
-  Pluto-Kuiper mission
-  Discovery Projects
-  Earth System Science Pathfinder

- Totals:

## Plasma Experiment for Planetary Exploration (PEPE)

- Plasma Experiment for Planetary Exploration

-  Instrument to determine ion and electron mass and energy distribution for solar wind and planetary environment analysis, as well as characterization of effluent from ion propulsion sources.
-  On DS1, PEPE is used to characterize effluent from the ion propulsion system and to monitor the spacecraft state-of-health.

- Jointly developed by Southwest Research Institute and Los Alamos National Laboratory for DS1

## PEPE Validation

**Flight Validation Rationale **
- Validation of PEPE can only be done in space because the space particle environment can not be adequately simulated on Earth.
**Validation Status**
- PEPE has observed the spacecraft environment with the Ion Propulsion System in both operating and non-operating modes
- Collaborative observations of solar wind conducted with Cassini Plasma Spectrometer
- Demonstrated that despite significant reductions in mass, power and size resources, PEPE still provides acceptable performance
- Validation is 75% complete
**Validation Planned**
- Extended system performance assessment
- March - April during long-duration ion propulsion system thrusting
- 100% technology validation planned by July 1999

## PEPE Benefits & Future Users

- PEPE embodies many of the comparable advanced capabilities of the Cassini Plasma Spectrometer (CAPS) while using a fraction of the resources:
_*	*__*	*__*	*__*	*__*	*_*    *_*PEPE*__*	*__*	*_*    *_*CAPS*_
_*	*__*	*__***RESOURCES***_
- 		Mass (kg)		       5.5		      23.4
- 		Power (W)		       9.6		      21.0
- 		Size (cm3)		    7,000		   25,000
- 		Cost			~$4.0M		~$22.0M
- Planetary and magnetospheric scientists have expressed interest in replications of the PEPE instrument for future missions
- Currently planned for infusion into two Discovery Mission Proposals

## Ka-Band Solid State Power Amplifier (KAPA)

_**Ka-Band Solid State Power Amplifier **__**(KAPA)**_

**Highest power solid state Ka-band amplifier ever used for deep space communications - high power enables high rate Ka-band communications from deep space**
**Demonstration of operational use of **
**	****Ka-band in space**
**DS1 Ka-band signal is critical to validate**
**	****and optimize technology development to**
**	****upgrade the 70 meter antenna stations for **
**	****Ka-band operation**
**100% technology validation completed in Jan 1999**
**Developed for NASA Jet Propulsion Laboratory by Lockheed Martin**

## Ka-Band Solid State Power Amplifier Benefits

**Greater bandwidth for telemetry**
**Total frequency allocation is **
**	****10 times that of X-band**
**Enhanced performance**
**4 times better performance than X-Band**
**20% the size / mass of X band amplifier**
**Flight Validation rationale**
**End-to-end operation with the NASA **
**	****Deep Space Tracking Network (DSN)**
**Side-by-side comparison with X-Band**
**Provides space-based source for DSN upgrades**
**Examples of future uses**
**Pluto-Kuiper Express Mission**
**Discovery Projects**
**Europa Orbiter Mission**

_**Ka-Band Solid State Power Amplifier **__**Benefits**_

**Ka-band**
**Solid State Power Amplifier (KAPA)**

## Beacon Monitor Operations Experiment

- Makes the spacecraft smart enough to monitor itself for health and safety and let the ground know when it needs help
- Overall spacecraft health and status translated into one of four general states
- On-board software summarizes spacecraft conditions succinctly
- Beacon Monitor transmits one of four tones to Earth to notify ground controllers of spacecraft state
- Developed by NASA Jet Propulsion Laboratory

## Beacon Monitor Operations Experiment

- Flight Validation Rationale
- End-to-end demonstration of integrated system technology requiring:
- spacecraft telemetry system, telecommunications (spacecraft) and
- ground tracking station participation
- Validations complete to date:
- Beacon tone transmission and detection
- Engineering data summary generation and visualization
- Tone message handling and reporting
- Validation 75% complete
- Validations planned
- Demonstrate weak signal beacon tone detection using the Low Gain Antenna
- Obtain Ka-band beacon signal characteristics through a Ka-band beacon signal
- Verify full functionality of the summarization system
- Completion planned for 07/99

## Beacon Monitor Operations Experiment Benefits and Future Users

- Simplifies communication with spacecraft
- Beacon’s tones much simpler to receive and understand than traditional complex digital telemetry
- Tracking of spacecraft can be done with a 3-10 meter antenna, rather than with a 70 meter antenna, at beacon pass cost of $100-$300/ day versus $4000-$18,000/ day for conventional telemetry tracking
- Ground station can rapidly assess spacecraft states and move to the next spacecraft being tracked
- During cruise, spacecraft could go for weeks or months without the need for sending digital telemetry to Earth
- 30% - 60% reduction in deep space mission operations costs
- Future users of this technology include all missions where extended periods of time are spent in interplanetary cruise without science data being taken and transmitted to Earth
- Reduces risk for Europa Orbiter, Pluto-Kuiper, and Solar Probe missions which plan to use it
- Can enable MIDEX and Discovery-class missions with constrained operations budgets
- Reduces mission risk by monitoring mission status more frequently than currently provided through Deep Space Network scheduled telemetry tracking

## Multifunctional StructuresA Revolution in Spacecraft Design, Manufacturing and Test

**Retains ground testability**
**Hardware developed by Lockheed Martin Astronautics (LMA), Denver, CO under sponsorship of Air Force Research Laboratory, Albuquerque and LMA**
**Flight Validation Rationale**
**Demonstration of produceability and long-term flight worthiness during multi-year mission**
**Verify electrical interconnects and structural integrity in space launch and mission thermal environments**

_**Multifunctional Structures**__**A Revolution in Spacecraft Design, Manufacturing and Test**_

**Flight Validation**
**Performance consistent with preflight tests**
**No degradation in flex conductor performance**
**No degradation of signal in the flight multi-chip module socket system**
**No failures in the data collection / interfacing electronics**
**100% complete (03/99)**

**Conventional Assemblies**

## Multi-Functional Structures Benefits & Future Users

- Benefits
- Leads to 10x savings in spacecraft mass
- Significant reduction in cable mass thereby reducing complexity and risk of failure
- Integrates interconnects into load-bearing element
- Reduces risk and improves reliability through integration
- Examples of Future Users
- Next Generation Space Telescope
- Space Based Infrared System
- National Polar Orbiting Operational Environmental Satellite
- Mars missions

## Power Activation and Switching Module (PASM)

- A miniature semiconductor high-voltage, high-current switching module providing power to analog subsystems
- 4 times reduction in module mass and size over current state-of-the-art switches used in spacecraft-enables small satellite power systems
- Flight validation rationale - demonstrate smart switching and current monitoring in actual spacecraft power system
- Validation 100% complete (03/99)
- Life tests in process for the duration of the mission
- Examples of future users
- Europa Orbiter
- Pluto-Kuiper Express
- Solar Probe

- Developed by Lockheed Martin Missiles and Space Inc., Boeing Co. and NASA Jet Propulsion Laboratory

## Low Power Electronics (LPE)

- Very low operating voltage integrated circuits with very high circuit density
- 20 times reduction in power consumption relative to current state-of-the-art integrated circuits-allows for smaller spacecraft power systems
- More radiation tolerant than current integrated circuits, thereby reducing risk of circuit failures during flight
- Flight Validation Rationale - demonstration of very low power microcircuits in space radiation environment
- Validation 100% complete (03/99)
- Operational life tests in process for the duration of mission
- Developed by Massachusetts Institute of Technology Lincoln Laboratory and NASA Jet Propulsion Laboratory
- Many future users in NASA, DoD and civil aerospace

## Remote Agent (RA)

- An autonomous “remote agent” of mission controller plans and executes many onboard activities with only general direction from the ground

- Developed by Carnegie Mellon University, NASA Ames Research Center and NASA Jet Propulsion Laboratory

## Remote Agent (RA)

- Flight Validation Rationale
- System-level demonstration of Remote Agent technology requires real time interactions with all spacecraft functions
- Completely new flight and ground operations paradigm
- Validation Planned
- Phase 1	- Demonstrate ground-based artificial intelligence planning and scheduling
- Flight demonstration of high-level control of autonavigation, camera pointing, attitude control maneuvers and power switching
- Phase 2	- On-board plan generation and execution
- Control of ion propulsion engine thrusting
- Demonstrate handling of anomalous behavior including on-board replanning
- Validation to be completed 06/99

## Remote Agent (RA)

- Benefits
- Greatly reduces ground tracking requirements
- Significantly reduces operations costs
- Provides rapid response to in-flight anomalies without ground control intervention
- Extensive use of autonomous control enables new explorations
- Examples of future uses
- Automatic sequencing and real time control

**Europa**

- Interferometer instruments (Terrestrial Planet Finder and Laser Interferometer Space Antenna) and autonomous rovers