# Presentation: 334071

## Section 9

***Spacecraft Technologies***

***Wideband Advanced Recorder / Processor (WARP)***
***X-Band Phased Array Antenna***
***Enhanced Formation Flying***
***Carbon-Carbon Radiator***
***Pulse Plasma Thruster***
***Lightweight Flexible Solar Array***

## Wideband Advanced Recorder Processor (WARP) 

***Technology Enabler***
***Description:***
- High Rate (up to 840Mbps capability), high density (48Gbit storage), low weight (less than 25.0 Kg) Solid State Recorder/Processor with X-band modulation capability.
- Utilizes advanced integrated integrated circuit  packaging (3D stacked memory devices) and “chip on board” bonding techniques to obtain extremely high density memory storage per board (24Gbits/memory card)
- Includes high capacity Mongoose 5 processor which can perform on-orbit data collection, compression and processing of land image scenes.
***Validation:***
- The WARP is required to store and transmit back science image files for the AC, ALI and Hyperion.
***Partners:***
- Litton Amecom

***Benefits to Future Missions:***
- The WARP will validate a number of high density electronic board advanced packaging techniques and will provide the highest rate solid state recorder NASA has ever flown.
- Its basic architecture and underlying technologies will be required for future earth imaging missions which need to collect, store and process high rate land imaging data.

***Wideband Advanced Recorder Processor (WARP)***** **

## Top-Level Specifications

***Data Storage:******	******	******48 Gbits ***
***Data Record Rate:******	****** > 1 Gbps Burst***
***	******	******	******	******900 Mbps Continuous (6 times faster than L7 SSR)***
***Data Playback Rate:******	******105 Mbps X-Band (with built-in RF modulator)***
***                 ******	******    ******	******2 Mbps S-Band***
***Data Processing:******	******Post-Record Data Processing Capability***
***Size: ******	******	******	******25 x 39 x 37 cm***
***Mass: ******	******	******22 kg***
***Power:******	******	******38 W Orbital Average., 87 W Peak***
***Thermal:******	******	******15 - 40 °C Minimum Operating Range***
***Mission Life:  ******	******	******1 Year Minimum, 1999 Launch***
***Radiation:******	******	******15 krad Minimum Total Dose, LET 35 MeV***

***Top-Level Specifications***

## WARP on Spacecraft, Bay 1

***WARP on Spacecraft, Bay 1***

## EO-1 Flight Data System Architecture

***EO-1 Flight Data System Architecture***

## WARP Flight Hardware Architecture

***WARP Flight Hardware Architecture***

## WARP Infusion Opportunities

***WARP Infusion Opportunities***

***NASA owns the WARP design***
***WARP was built in association with Litton Amecom***
***WARP is particularly applicable to missions with the following:***
***High ingest data rates ************ 1.0 Gigabit / second***
***Need for processing capability on board***
***Use of phased array antenna as primary downlink***
***WARP was single-string for EO-1 but reliability enhancements have already been designed***
***Technical support to facilitate infusion is negotiable***
***For further information, contact:***
*Terry Smith*
_*[Terrence.M.Smith.1@gsfc.nasa.gov](mailto:Terrence.M.Smith.1@gsfc.nasa.gov)*_
*301-286-0651*

## X-Band Phased Array Antenna (XPAA)

***Technology Need:***
- High rate, reliable RF communication subsystems
***Description:***
- The X-band phased array antenna is composed of a flat grid of many radiating elements whose transmitted signals combine spatially to produce desired antenna directivity (gain)
*Avoids problems of deployable structures and moving parts *
*Lightweight, compact, supports high downlink (100’s Mbps) rates.*
*Allows simultaneous instrument collection and data downlink.*
***Validation:***
- The XPAA will be validated through measurement of bit error rate performance and effective ground station EIRP during science data downlinks over the lifetime of the mission.
***Commercial Partners:***
- Boeing Phantom Works

***Benefits to Future Missions:***
- Future Earth Science missions will produce tera-bit daily data streams.  The Phase Array  antenna technology will enable:
*Lower cost, weight and higher performance science downlinks*
*Lower cost and size  ground stations*
*More flexible operations*

***X-Band Phased Array Antenna (XPAA)***

## XPAA Performance Summary

***XPAA Performance Summary***

***Frequency - 8225 MHz***
***Bandwidth - 400 MHz***
***Scan Coverage - 60 deg half-angle cone***
***Radiating Elements - 64***
***RF Input - 14 dBm***
***EIRP - greater than 22 dBW at all commanded angles***
***Polarization - LHCP***
***Command Interface / Controller - 1773 / RSN***
***Input DC Power - <58 watts over 0 to 40 C***
***Mass - 5.5 kg***

## XPAA mounted on EO1, undergoing near-field scanning in the large clean room at GSFC.

***XPAA mounted on EO1, undergoing near-field scanning in the large clean room at GSFC.***

## Near Field Measurement Data for the XPAA when Mounted on EO1 

- Aperture Amplitude
- Far Field Cut
- Aperture Phase
- Far Field Contour

## XPAA Initial Validation Summary

***XPAA Initial Validation Summary***

***Early post-launch experience with the XPAA revealed intermittent data errors while NASA ground antennas were autotracking the X-band signal.  Currently, using S-band tracking and some additional passes, all science validation data is being successfully transmitted to ground using the XPAA.***
***A Tiger Team was established in December 2000 to find the cause:***
***Initial validation measurements and on-board telemetry indicate that the XPAA is operating well and as-designed***
***Alignment problems and other issues were found at the ground stations that are now being evaluated and rectified***
***This is the first X-band satellite with a Left-hand Circularly Polarized signal to be tracked by these stations***
***Several other commercial ground stations have had little or no difficulties in receiving the data.***
***All Tiger Team results will be included in the Technology Transfer Documentation***

## XPAA Technology Infusion Opportunities

***XPAA Technology Infusion Opportunities***

***Design is owned by Boeing Phantom Works in Seattle, WA.***
***Boeing is interested in the commercial sale of their phased array antennas similar to the EO-1 antenna***
***The phased array antenna is applicable to missions requiring:***
*Low mass antenna*
*High reliability with graceful degradation*
*Agile, accurate antenna pointing with no physical disturbance to the spacecraft*
***NASA support to facilitate infusion is negotiable***
***For further information contact:***
*Kenneth Perko*
_*[Kenneth.L.Perko.1@gsfc.nasa.gov](mailto:Kenneth.L.Perko.1@gsfc.nasa.gov)*_
*301-286-6375*

## Enhanced Formation Flying (EFF)

- The EFF technology enables small, inexpensive spacecraft to fly in formation and gather concurrent science data in a “virtual platform.”
- This “virtual platform” concept lowers total mission risk, increases science data collection and adds considerable flexibility to future Earth and space science missions.

***Technology Need:***
- Constellation Flying
***Description:***
- The enhanced formation flying (EFF) technology features flight software that is capable of autonomously planning, executing, and calibrating routine spacecraft maneuvers to maintain satellites in their respective constellations and formations.
***Validation:***
- Validation of EFF will include demonstrating on-board autonomous capability to fly over Landsat 7 ground track within a +/- 3km while maintaining a one minute separation while an image is collected.
***Partners:***
- JPL,GSFC, Hammers

***Enhanced Formation Flying (EFF)***

## Performance Required

***Mission Orbit Requirements***
***Paired scene comparison requires EO-1 to fly in formation with Landsat-7. ***
***Maintain EO-1 orbit with tolerances of:***
*One minute separation between spacecraft*
*Maintain separation so that EO-1 follows current Landsat-7 ground track to +/- 3 km *

*** ******EO-1 Formation Maneuver Frequency Is ***
***     ******Ballistic Dependent***

***Derived Orbit Requirements***
***Approximately six seconds along-track separation****** tolerance (maps to +/- 3km with respect to earth rotation)***
***Plan maneuver in 12 hours***
***Derived Software Constraints***
***Code Size approximately ************655Kbytes***
***CPU Utilization approximately <50% Average over 10 Hours during maneuver planning***
***Less than 12 hours per maneuver plan***

## Subsystem Level

***Verify***
***EFF***
***AutoCon-F***
*GSFC*
*JPL*
*GPS Data Smoother*
***SCP***
***Algorithm Flight Code Uploads for JPL into RAM***

## Enhanced Formation FlyingTechnology Infusion Opportunities

***Enhanced Formation Flying****Technology Infusion Opportunities*

***Enhanced Formation Flying technology is owned by NASA***
***It is applicable to missions that require:***
***Constellations***
***“******Virtual” platforms that involve the coordinated use of instruments on different spacecraft***
***Autonomous operations***
***NASA support to facilitate infusion is negotiable***
***For further information contact:***
*Dave Folta*
_*[David.C.Folta.1@gsfc.nasa.gov](mailto:David.C.Folta.1@gsfc.nasa.gov)*_
*301-286-6082*

## Carbon-Carbon Radiator

- Increase instrument payload mass fraction.
***Description:***
- Carbon-Carbon is a special composite material that uses pure carbon for both the fiber and matrix. The NMP Earth Orbiter – 1 mission will be the first use of this material in a primary structure, serving as both an advanced thermal radiator and a load bearing structure  Advantages of Carbon-Carbon include:
*High thermal conductivity including through thickness*
*Good strength and weight characteristics*
***Validation: ***
- EO-1 will validate the Carbon-Carbon Radiator by replacing one of six aluminum 22” x27” panels with one constructed using the C-C composite materials. Mechanical and thermal properties of the panels will be measured and trended during environmental testing and on-orbit.

***Benefits to Future Missions:***
- This technology offers significant weight reductions over conventional aluminum structures allowing increased science payload mass fractions for Earth Science Missions.  Higher thermal conductivity of C-C allows for more space efficient radiator designs.*** ***
***Partners***
- CSRP (consortium)

***Carbon-Carbon Radiator***

## Design Overview

***Design Overview***

***Equipment panel (Bay #4) composed of carbon-carbon facesheets and an aluminum honeycomb core***
***Supports the LEISA and PSE***
***Measures 28.62 x 28.25 x 1.00 in***
***Mass of 3.12 kg***
***Flight unit and spare***
***Design stable since CDR***

## Performance Required

***Performance Required***

***Mass - Less than 2.5 kg***
***Stiffness - First mode frequency greater than 100 Hz when hard-mounted to the S/C***
***Strength - Inertial loading***
***Simultaneous quasi-static limit and S/C interface loads***
*15 g acceleration in any direction*
*Shear load of 16,100 N/m*
*Edge normal load of 19,500 N/m*
*Panel normal load of 1,850 N/m*
***Maximum fastener forces at the S/C attachment points***
*Maximum tension force of 25 N*
*Maximum shear force normal to panel edge of 135 N*
*Maximum shear force parallel to panel edge of 115 N*
***Strength - Thermal loading***
***On-orbit temperature variations ranging from -20°C to +60°C***

## Carbon-Carbon RadiatorTechnology Infusion Opportunity

***Carbon-Carbon Radiator****Technology Infusion Opportunity*

***Design is owned by Carbon-Carbon Spacecraft Radiator Partnership (CSRP)***
***This technology is applicable to missions requiring:***
***Lightweight, efficient radiators with favorable structural properties***
***Structural properties and thermal properties can be balanced in the manufacturing process***
***The CSRP is interested in providing these radiators to interested parties***
***NASA support to facilitate infusion is negotiable***
***For more information contact:***
*Dan Butler*
_*[Charles.D.Butler.1@gsfc.nasa.gov](mailto:Charles.D.Butler.1@gsfc.nasa.gov)*_
*301-286-3478*

## Pulse Plasma Thruster (PPT)

- The PPT offers new lower mass and cost options for fine precision attitude control for new space or earth science missions
***Partners***
***GRC, Primex, GSFC***

***Technology Need:***
*Increased payload mass fraction and precision attitude  control*
***Description:***
- The Pulse Plasma Thruster is a small, self contained electromagnetic propulsion system which uses solid Teflon propellant to deliver high specific impulses (900-1200sec), very low impulse bits (10-1000uN-s) at low  power.
- Advantages of this approach include:
*Ideal candidate for a low mass precision attitude control device. *
*Replacement of reaction control wheels and other momentum unloading devices.  Increase in science payload mass fraction.*
*Avoids safety and sloshing concerns for conventional liquid propellants*
***Validation:     ***
- The PPT will be substituted (in place of a reaction wheel) during the later phase of the mission (month 11).  Validation will include:
*Demonstration of the PPT to provide precision pointing accuracy, response and stability.*
*Confirmation of benign plume and EMI effects*

***Pulse Plasma Thruster (PPT)***

## PPT Design

- ACE IO

- PSE OPMI

- Main Cap & Plug Charge/Discharge
- Cap and Electronics Temp
- Main Cap & Plug Voltages
- Fuel Gauges

- +28 V Power

**Technology Principle**

**S/C Interface**

## Pulse Plasma ThrusterTechnology Infusion Opportunity

***Pulse Plasma Thruster****Technology Infusion Opportunity*

***Design is owned by Primex***
***Validation scheduled for October / November 2001***
***EO-1 unit developed at the Glenn Research Center***
***Applicable to missions requiring:***
***Low mass, precision attitude control***
***Highly reliable***
***Primex will provide similar units to interested parties***
***NASA support to facilitate infusion is negotiable***
***For more information contact:***
*Charles Zakrzwski*
- _[Charles.M.Zakrzwski.1@gsfc.nasa.gov](mailto:Charles.M.Zakrzwski.1@gsfc.nasa.gov)_
*301-286-3392*

## Lightweight Flexible Solar Array (LFSA)

- Increase payload mass fraction.
***Description:***
- The LFSA is a lightweight photovoltaic(PV) solar array which uses thin film CuInSe2 solar cells and shaped memory hinges for deployment. Chief advantages of this technology are:
*Greater than 100Watt/kg specific energies compared to conventional Si/GaAs array which average 20-40 Watts/kg.*
*Simple shockless deployment mechanism eliminates the need for more complex mechanical solar array deployment systems.  Avoids harsh shock to delicate instruments.*
***Validation:     ***
- The LFSA deployment mechanism and power output will measured on-orbit to determine its ability to withstand long term exposure to radiation, thermal environment and degradation due to exposure to Atomic Oxygen.
***Partners ***
- Phillips Lab, Lockheed Martin Corp

***Benefits to Future Missions:***
- This technology provides much higher power to weight ratios (specific energy) which will enable future missions to increase science payload mass fraction.*** ***

***Lightweight Flexible Solar Array (LFSA)***

## Description

***Description***

***Copper Indium Diselenide (CuInSe2 or CIS) Thin-Film Solar Cells ***
***Deposited on a Flexible Kapton Blanket suspended in a Composite Frame***
***Frame Deployed Using Shape Memory NiTi Alloys and a Launch Restraint Device***
***Advantage: Increase solar array w/kg (from typical 40 w/kg to >100 w/kg), increase science payload mass fraction ***
***Partners: AFRL (Kirtland AFB, NM), NASA/LaRC, Lockheed Martin (Denver, CO)***

## Description (continued)

_***LFSA FLIGHT UNIT***_

_***SMA - DEPLOYED***_

_***SMA - STOWED***_

***Description ****(continued)*

## Lightweight Flexible Solar ArrayTechnology Infusion Opportunities

***Lightweight Flexible Solar Array****Technology Infusion Opportunities*

***Design is owned by Lockheed Martin***
***Developed by Air Force Research Lab***
***Applicable to missions requiring low mass solar array***
***Shaped memory hinges provide simple, shockless deployment***
***Lockheed Martin will provide similar systems to interested parties***
***NASA support to facilitate infusion is negotiable***
***For more information contact:***
*John Lyons*
_*[John.W.Lyons.1@gsfc.nasa.gov](mailto:John.W.Lyons.1@gsfc.nasa.gov)*_* *
*301-286-3841*