# Presentation: 041597

## Mission and Science Measurement Technology - 2004(MSMT-2004)

-  Advanced Measurement and Detection Technology
*Large Aperture Technology*
- Low Power Electronics

## Large Aperture NRA Overview

- The **Large Space Systems Project** develops concepts for large, ultra-lightweight space structures and apertures to expand mission capabilities, and to enable new visions of the Earth and the Universe.   Technology development includes advanced materials, deployable and inflatable structures, multifunctional and adaptive structures, and ultra-lightweight optical systems.
- The **Large Apertures Element** focuses on lightweight optics, adaptive optical, RF systems, wavefront correction, and concepts for deployment and assembly of large antennae and telescopes.* *

_*Large Optical Systems*_ - Large, lightweight scalable optical systems for imaging and monitoring celestial objects throughout the electromagnetic spectrum, but with an emphasis on visible through far-infrared. Also, moderate-sized optical systems for far-ultraviolet mirrors and lidar receiver applications.
_*Large Radiometer and Radar Systems*_ - Large antennas for space-based radio astronomy and remote sensing of the Earth and other planets with radar and radiometers.
_*Wavefront Control*_ - Active wavefront control to achieve and maintain the required surface precision/wavefront error of both telescope and antenna apertures in the presence of dynamic and quasi-static disturbances.

## Technology For Large Apertures 

- Lightweight & Space-Durable Materials

- Structural Deployment and Assembly

- Adaptive and Resilient Systems

**Technology For Large Apertures **

- _Metrics:_
-    - lower mass (X3)
-    - lower package volume (X10)
-    - lower cost:
- 	(reduced part count)
- 	(smaller launch vehicle)

- Antennas

- Telescopes

- Wavefront Control

*Actuation And Sensing *

## Table A.3.1:  Goals for future NASA Optical Systems

|  | X-ray mirrors | UV Mirrors | Visible | Scanning Lidar Telescope | NIR Earth Science Systems | Far infrared  to submm |
| --- | --- | --- | --- | --- | --- | --- |
| Wavelength / Energy Range | 0.05 -15 keV | 

100 – 400 nm | 400 -700 nm | 

355 – 2050 nm | 

0.7 - 4 
m | 20 – 800  
m |
| Size | 1 - 4 m | 

1 - 2 m | 6-10+ m | 

0.7 – 1.5 m | 

3m - 4 m | 10-25 m |
| Areal Density | <0.5 kg/m2/
grazing incident | 

< 10 kg/m2 | <5 kg/m2 | 

< 10 kg/m2 | 

< 5 kg/m2 | < 5 kg/m2 |
| Surface Figure | /150
at 
 =633 nm | 

 /300
at 
 =300 nm |  /150
at 
 =500 nm | 

 /10
at 
 = 633 nm | 

 /75 
at 
 =1  m |  /14
at 
 =20 m |

- T ~ 4oK

- _Optical Aperture Technology _
- _Deployment Technology _
- _System Distributed Cooling_

*Data is not met to be restrictive on novel ideas.*

## X-ray Mirrors

**X-ray Mirrors**

*Structure and Evolution of the Universe : Micro-Arcsecond X-ray Imaging Mission (MAXIM), MAXIM Pathfinder*

- Science Questions:
-  to probe the environment in the vicinity of black holes
-  to image a black hole
- Current Mission:  Con-X
-  Minimum effective area:  1,000 cm2 from 0.25 keV to 10 keV
- 		15,000 cm2 at 1.25 keV
- 		  6,000 cm2 at 6.0 keV
- 		  1,500 cm2 from 10 keV to 40 keV
- Mission Needs:
-  MAXIM Pathfinder
-  MAXIM
- Technology Required:
-  Large, lightweight X-ray mirror technology
-  Wavefront sensing and control technology
-  Reduced manufacturing time
**0.05-15keV, 1-4 m, <0.5 kg/m****2****/grazing incidence, **
******150 at ******** = 633nm **

## UV Mirrors

*Structure and Evolution of the Universe, Origins, Sun Earth Connection: Stellar Imager (SI)*

- Science Questions:
-  to image surface features of other stars and measure their spatial/temporal variations
-  to enable improved forecasting of solar/stellar activity and its impact on planetary climates and life
- Current Mission:
- Mission Needs:
-  SI -  10-30 microsats with 1-2 meter apertures
- Technology Required:
-  Lightweight, high precision aperture technology
-  Reduced manufacturing time
**100-400 nm, 1-2 m, < 10 kg/m****2****, ********300 at ******** = 300nm**

## Visible Mirrors

*Astronomical Search for Origins: Space Ultraviolet Optical Telescope (SUVO) {Next Hubble Space Telescope (NHST), HST2}*

- Science Questions:
-  to study stellar populations and galaxy formation and evolution
-  to follow the chemical evolution of the universe
- Current Mission:  HST - 2.5m fixed aperture at 250 kg/m2, manufacturing time 1year/m2
- Mission Needs:
-  SUVO -  > 6 meter deployable aperture
- Technology Required:
-  Large lightweight deployable aperture technology
-  Wavefront sensing and control technology
-  Reduced manufacturing time
**400-700 nm, 6-10m, <5kg/m****2****, ********150 at ******** = 500nm**

## Scanning Lidar Telescopes

*Code Y : Follow-on to Vegetation Canopy Lidar (VCL) Follow-on to ESSP3, Follow-on to AIRS*
- Several lidar instruments envisioned for future launch require meter-class (0.7 – 1.5 m) scanning telescopes to achieve desirable coverage and accurate measurements. Lightweight optics combined with novel telescope designs may allow scanning the laser beam on a space platform without substantial penalty of momentum compensation. Such telescopes must maintain a high degree of optical quality and pointing accuracy in the thermal and vibration environment of space.
**Landcover characterization for**
- 		a. terrestrial ecosystem modeling,
- 		monitoring and prediction,
- 		b. climate modeling and prediction.
**Global reference data set of topographic spot **
**	****heights and transects**

**355-2050nm, 0.75-1.5m, <10kg/m****2****, ******** /10 at ******** = 633nm**

## Near IR Earth Science Systems

*Code Y :*
- NASA is also studying future missions for earth science observatories.  These observatories will enable studies that include vegetation, ocean "color" - the study of dissolved organic matter and atmospheric aerosols.  Wavelengths from the UV through the near infrared will be used.  The study of these physical systems at the 20-500-meter spatial resolutions illustrates the need for large optical systems.  Observations are planned from geosynchronous, near-geosynchronous orbits and Lagrange points. Large apertures are needed for 1 to 10 km spatial resolution from these orbits for full earth coverage.
*Atmospheric temperature measurement follow on to AIRS*

**0.7-4 microns, 3-4m, <5kg/m****2****, ********75 at ******** = 1microns**

## Far Infrared to Submm Systems

**Far Infrared to Submm Systems**

*Astronomical Search for Origins, Structure and Evolution of the Universe: Single Aperture Far Infrared (SAFIR) Observatory, Cosmic Microwave Background Polarization (CMBPOL), Submillimeter Probe of the Evolution of Cosmic Structure (SPECS)*

- Science Questions:
-  to study the birth and evolution of stars and planetary systems
-  to determine the connections between space, time and matter
- Current Mission:  JWST - 6m deployable aperture at < 50 K
- Mission Needs:
-  CMBPol -  > 5 meter apertures, < 10 K
-  SAFIR  - 10 meter primary mirror, < 10K
-  SPECS - 15-20 meter apertures, < 10K
- Technology Required:
-  Large lightweight deployable aperture technology
-  Cryogenic cooling and thermal management technology
-  Wavefront sensing and control technology
**20-800microns, 10-25m, <5kg/m****2****, 4K, ********14 at ******** = 20microns**

- SAFIR

- SPECS

## Table A.3.1:  Goals for future NASA Optical Systems

|  | X-ray mirrors | UV Mirrors | Visible | Scanning Lidar Telescope | NIR Earth Science Systems | Far infrared  to submm |
| --- | --- | --- | --- | --- | --- | --- |
| Wavelength / Energy Range | 0.05 -15 keV | 

100 – 400 nm | 400 -700 nm | 

355 – 2050 nm | 

0.7 - 4 
m | 20 – 800  
m |
| Size | 1 - 4 m | 

1 - 2 m | 6-10+ m | 

0.7 – 1.5 m | 

3m - 4 m | 10-25 m |
| Areal Density | <0.5 kg/m2/
grazing incident | 

< 10 kg/m2 | <5 kg/m2 | 

< 10 kg/m2 | 

< 5 kg/m2 | < 5 kg/m2 |
| Surface Figure | /150
at 
 =633 nm | 

 /300
at 
 =300 nm |  /150
at 
 =500 nm | 

 /10
at 
 = 633 nm | 

 /75 
at 
 =1  m |  /14
at 
 =20 m |

- T ~ 4oK

- _Optical Aperture Technology _
- _Deployment Technology _
- _System Distributed Cooling_

*Data is not met to be restrictive on novel ideas.*

## Large Optical Systems

_** **__**Favorable technology system traits include:**_
- High packaging efficiency for small launch volume;
- Design traceable to space-durable materials;
- Robust system response to re-pointing of the aperture;
- High surface reflectivity after repeated deployment;
- Increase the collection area while maintaining or reducing costs and minimizing mass;
- Reduce the time required for precision mirror fabrication per unit area;
- The ability to perform metrology and test for such large aperture mirror technologies;
- Diffraction limited quality of mirrors.
_**Integration of two or more of the following are encouraged:**_
- scalable large apertures;
- metering structures;
- active/passive cryogenics (if applicable);
- deployment methods and mechanisms;
- modeling to show scalability of the proposed technology to larger apertures.

## Table A.3.2 Goals for NASA Radiometers and Radars

|  | Radiometers  |  | RADARs |  |  |
| --- | --- | --- | --- | --- | --- |
|  | Filled Aperture
Antenna | Distributed/Synthetic Aperture Radiometer | Filled Aperture | Synthetic
Aperture Radar (SAR) | Inter-
ferometric 
SAR |
| Wavelength Range | 1.4 –300 GHz | 1.4 GHz -
183 GHz | 1.2 - 94 GHz | 100 MHz – 18 GHz | 1.2  - 18 Ghz |
| Array Size | Rotationally symmetric
25-30 m diameter | 30-50 m x 30-50 m | Parabolic cylindrical
Apertures 6-25m
Planar
>100m  | Linear
50-100m x
3-5m | 50-100 m x 3-5 m |
| Array/Aperture Areal Density | Mesh or membrane
<2 kg/m2 | <2 kg/m2 | <3 kg/m2 | <3 kg/m2 | <3 kg/m2 |
| Boom Size  |  | 100 – 1000  times the wavelength |  | 30-50m | 10-50  m |

- _Deployable Antenna Technology   _
- _Integrated Electromagnetic and Structural Design_

*Data is not met to be restrictive on novel ideas.*

## Filled Aperture Antenna Radiometers

*Code Y: **	**Earth Science Technology Office (ESTO) *
*	**	**Earth Science Technology Integrated Planning System (ESTIPS)*
*Code S: Structure and Evolution of the Universe: ARISE*

- Science Questions:
- Soil Moiture
- Ocean Salinity
- Very Long Baseline Interferometry
- Current Mission: Mission Needs:
-  25-30+ m diameter filled aperture
- 20m+ Synthetic apertures
- Technology Required:
-  Stable lightweight deployable mesh/ membrane aperture technology
**1.4-300 GHz, rotationally symmetric 25-30m, <2kg/m****2**

## Filled Aperture Radar

*Code Y: Global Precipitation Mission (GPM)*

- Science Questions:
-  to study the water cycle and surface precipitation
-  to parametrize convection to determine latent heating profiles
- Current Mission: Airborne Rain Mapping Radar (ARMAR)
- Mission Needs:
-  GPM - 15-20 meter cylindrical apertures
- Technology Required:
-  Stable lightweight deployable aperture technology
**1.2-94 GHz, parabolic cylindrical 6-25m/**
**planar >100m, <3kg/m****2**

## Table A.3.2 Goals for NASA Radiometers and Radars

|  | Radiometers  |  | RADARs |  |  |
| --- | --- | --- | --- | --- | --- |
|  | Filled Aperture
Antenna | Distributed/Synthetic Aperture Radiometer | Filled Aperture | Synthetic
Aperture Radar (SAR) | Inter-
ferometric 
SAR |
| Wavelength Range | 1.4 –300 GHz | 1.4 GHz -
183 GHz | 1.2 - 94 GHz | 100 MHz – 18 GHz | 1.2  - 18 Ghz |
| Array Size | Rotationally symmetric
25-30 m diameter | 30-50 m x 30-50 m | Parabolic cylindrical
Apertures 6-25m
Planar
>100m x | Linear
50-100m x
3-5m | 50-100 m x 3-5 m |
| Array/Aperture Areal Density | Mesh or membrane
<2 kg/m2 | <2 kg/m2 | <3 kg/m2 | <3 kg/m2 | <3 kg/m2 |
| Boom Size  |  | 100 – 1000  times the wavelength |  | 30-50m | 10-50  m |

- _Deployable Antenna Technology   _
- _Integrated Electromagnetic and Structural Design_

*Data is not met to be restrictive on novel ideas.*

## Large Radiometer and Radar  Systems

_** **__**Favorable technology system traits include:**_
- High packaging efficiency for small launch volume;
- Design traceable to space-durable materials;
- Robust system response to re-pointing of aperture;
- Deployment risk mitigation;
- Scanning of large apertures;
- Control and stability of rotating antennas in orbit;
- Widest possible wavelength range with 1 antenna;
- Minimum beam side lobes;
- Maintaining high beam efficiency with single and multiple beams;
- Wide field of view (meaning scanning range) with single antenna.

## Wavefront Sensing and Control

-  Active and adaptive systems focused on high dynamic range correction  applicable to large, lightweight deployable apertures of dual or single curvature, including control of primary or other optical elements:
- achieve diffraction-limited performance for wavelengths from the sub-mm through the visible.
- proof-of-concept demonstration of correction of errors of >10  to  /15 at the focal plane
- stability >1hr in the presence of specified vibrations.
- Active and adaptive systems focused on high dynamic range correction of radar apertures:
- to  /20 from errors of 100 
- alignment of the ground plane and the array plane to  /2
- 	with errors <  /20.
- Reaction/support structure with integral actuation and metrology:
- provide the dynamic and quasi-static geometry control necessary for the precision wavefront control to be within the capture range.

## Wavefront Sensing and Control

_** **__**Favorable technology system traits include:**_
- Integral actuation with extreme precision (< 100 nm) and high range (> 1cm);
- Integrally designed electromagnetic/structural compensation systems;
- Low thermal load actuation of optical systems;
- Low reaction force actuation;
- Integrated metrology and actuation.

## Technology Readiness Level

**TRL 9**
**—**
**TRL 8**
**—**
**TRL 7**
**—**
**TRL 6**
**—**
**TRL 5**
**—**
**TRL 4**
**—**
**TRL 3**
**—**
**TRL 2**
**—**
**TRL 1**

**System Test, Launch**
**& Operations**
**System/Subsystem**
**Development**
**Technology**
**Demonstration**
**Technology**
**Development**
**Research to Prove**
**Feasibility**
**Basic Technology**
**Research**

**Technology Readiness Level**

** ****9 *****Actual system "flight proven" through successful mission operations***_ _**  **
**8 *****Actual system completed and "flight qualified" through test and demonstration (ground or space)***_ _
** ****7 *****System prototype demonstration in a space environment***_ _
** ****6 *****System/subsystem model or prototype demonstration in a relevant environment (ground or space)***_ _
** ****5 *****Component and/or breadboard validation in relevant environment***_ _
** ****4 *****Component and/or breadboard validation in laboratory environment***_ _
** ****3 *****Analytical and experimental critical function and/or characteristic proof-of-concept***_ _
** ****2 *****Technology concept and/or application formulated***_ _
**1  *****Basic principles observed and reported***_ _

- _[http://technologyplan.nasa.gov](http://technologyplan.nasa.gov/)__  (Appendix B)_

## Sources of Note

- _Code S (_http://spacescience.nasa.gov)
- Structure and Evolution of the Universe (SEU)
- Astronomical Search for Origins (ASO)
- Sun Earth Connection (SEC)
- _Code Y (__[http://esto.nasa.gov/estips](http://esto.nasa.gov/estips)__)_
- Solid Earth Science,
- Global Water and Energy Cycle,
- Oceans and Ice,
- Atmospheric Chemistry & Solar Radiation.
- _Code R_
- MSMT (_[http://www.aero-space.nasa.gov/](http://spacescience.nasa.gov/)__)_