Modular assembled space telescope

Lee D. FeinbergJason BudinoffHoward MacEwenGary MatthewsMarc Postman

Modular assembled space telescope

Lee D. FeinbergJason BudinoffNASA Goddard Space Flight CenterGreenbelt, Maryland 20771E-mail: Lee.D.Feinberg@nasa.gov

Howard MacEwenReviresco LLCAnnandale, Virginia 22003

Gary MatthewsITT Exelis Geospatial SystemsGreenbelt, Maryland 20771

Marc PostmanSpace Telescope Science InstituteBaltimore, Maryland 21218

Abstract. We present a new approach to building a modular segmentedspace telescope that greatly leverages the heritage of the Hubble SpaceTelescope and the JamesWebb Space Telescope. The modular design inwhich mirror segments are assembled into identical panels allows foreconomies of scale and for efficient space assembly that make a 20-maperture approach cost effective. This assembly approach can leverageNASA’s future capabilities and has the power to excite the public’s imagi-nation. We discuss the science drivers, basic architecture, technology,and leveraged NASA infrastructure, concluding with a proposed plan forgoing forward. © 2013 Society of Photo-Optical Instrumentation Engineers (SPIE) [DOI: 10.1117/1.OE.52.9.091802]

Subject terms: space telescope; James Webb Space Telescope, space assembly;deployment; robotics; human space operations; International Space Station; libra-tion points.

Paper 121848SS received Dec. 17, 2012; revised manuscript received Feb. 25,2013; accepted for publication Feb. 25, 2013; published online Apr. 25, 2013.

1 IntroductionSpace telescopes provide unique and important vantagepoints to study the universe free from the blur, thermal back-ground and absorption of the earth’s atmosphere. As with alltelescopes, larger space telescope apertures improve theresolution and sensitivity and thus are critical to enablingnew capabilities. An historic example of the power of spacetelescopes is provided by images from the Hubble SpaceTelescope (HST). HST’s resolution over a large field of viewwas a major step beyond ground capabilities and opened upa wealth of new scientific discoveries. Picking up fromHubble, the James Webb Space Telescope (JWST) will pro-vide a major increase in collecting area and sensitivity andextend the wavelength range into the near- and mid-infraredwhile maintaining HST’s resolution, thus laying the ground-work for a large array of new science. Deployment of JWSTat the Sun-Earth L2 libration point (SEL2) further enhancesits performance by minimizing the influences of the Earth-Moon system, particularly thermal effects and stray lightintrusion.

Looking beyond JWST, we propose an observatory incor-porating a new level of modularity that exploits economies ofscale in both mirrors and structure to enable a new class ofmuch larger space telescopes that can be cost effective andreadily assembled in space. Modularity can provide afoundation for 20-m and larger apertures, unleashing anothermajor step in scientific observation capabilities and furthercapitalizing upon the observational benefits of an SEL2orbital deployment.

This new approach leverages the knowledge and experi-ence gained in servicing HST, designing and building thesegmented and alignable JWST telescope, and in buildingand maintaining the International Space Station (ISS). Thelevel of modularity proposed is not only ideal for spaceassembly but also enables a more cost-effective solution

that utilizes economies of scale in the manufacturing, inte-gration, and testing of mirrors and structures. The modularityproposed complements and leverages NASA’s future capa-bilities, including human and robotic capabilities forassembly and servicing, and both the Space Launch System(SLS) and commercial launch vehicles. In addition, thearchitecture utilizes active on-orbit wavefront sensing andcontrol with updates every few minutes to greatly relax pas-sive stability requirements (14 days for JWST) that would bea major cost and performance driver for a large backplane. Itachieves this new active capability using the image-basedmethods proven for JWST without requiring complex on-board metrology systems. This modular and alignable archi-tecture also allows for incremental verification of mirrorpanels on the ground and not a full-up system test, whichwould not be feasible.

We propose this architecture for a 20-m class ultraviolet(UV)-Optical (i.e., ultraviolet-visible) telescope enablingnew capabilities in the study of earth-like planets and otherexciting new capabilities due to high resolution and high sen-sitivity. A similar modular approach can also enable spacetelescopes in other spectral regions (e.g., a far-infrared tele-scope with angular separability that avoids target confusion).Moreover, it provides a natural basis for telescopes scaled toeven larger apertures. Through a combination of inter-national collaboration, leveraging both heritage telescopetechnologies and facilities and a wide range of futureNASA capabilities, we believe this can be accomplished atthe cost equivalent of a great observatory. We see this as alogical step in a long term space telescope strategy for NASAand its international collaborators.

2 Science DriversA 20-m class UV-optical space telescope will enable an eraof remarkable astrophysical discoveries. While the sciencecase for 8- to 10-m class space telescopes has been previ-ously contemplated (e.g., Green et al.1 and Postman et al.2,3),the sensitivity and angular resolution of a 20-m UV-optical0091-3286/2013/$25.00 © 2013 SPIE

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space telescope will allow us to enter a completely newregime of science. We briefly summarize three particularareas of investigation here. Note that these are just a fewof the many exciting investigations enabled by a 20-m classspace telescope, which of course will yield an even greaternumber of as-yet unimagined discoveries.

2.1 Habitable Exoplanets

The number of potentially habitable exoplanets that can bespectroscopically characterized scales as roughly the cube ofthe space telescope aperture. A 20-m space telescope withsensitivity across the 0.3- to 2.4-μm wavelength range willdefinitively answer the question “Is there life elsewhere inthe Galaxy?” It will be capable of obtaining R ¼ 100 spectrafor well over 1000 exoplanets (assuming an on-boardcoronagraph capable of a contrast ratio of 10−10 at 3λ∕D)out to a distance of 145 light years from the sun. Most impor-tantly, it can obtain a S∕N ¼ 10 spectrum at a spectral res-olution of R ¼ 100 for most of these systems in less than 3 hof integration time!

Broadband disc-averaged photometry with S∕N ¼ 20 canbe obtained in a mere 30 min of integration in most cases. Atsuch a pace, one can map the longitudinal distribution ofland-water-cloud cover ratios on hundreds of exoplanetsusing time-resolved imaging and spectroscopy. See Fig. 1for an example of such a reconstruction that was done byCowan et al.4 for Earth. A 20-m space telescope providessuch a potent observational capability that it will not onlyallow us to spectroscopically detect biomarkers on thesepotentially habitable worlds but will also enable the measure-ment of the land-to-water coverage ratios, potentially detectred edge absorption from vegetation, and measure seasonalvariations in these values, heralding a true era of remote sens-ing of exosolar planets.

2.2 Stellar Population Histories

A 20-m space telescope will, for the first time, enable thereconstruction of complete star formation histories (spanning10 Gyr) for ∼500 galaxies beyond the Local Group, openingthe full range of star formation environments to exploration.This would be a major leap in our observational capabilitiesthat would lead directly to a comprehensive and predictivetheory of galaxy formation and evolution. Our only directinsight into the stellar assembly process of modern-day

galaxies comes from sifting through their resolved stellarpopulations to reconstruct the star formation history, chemi-cal evolution, and kinematics of their various structures.5

Resolved stellar populations are cosmic clocks. Theirmost direct and accurate age diagnostic comes from obser-vations that can resolve the individual, older stars thatcomprise the main sequence turnoff. But the main sequenceturnoff rapidly becomes too faint to detect with any existingtelescope for any galaxy beyond the Local Group. Thisgreatly limits our ability to infer much about the details ofgalactic assembly because the galaxies in the Local Groupare not representative of the galaxy population at large. A20-m space telescope will allow us to reach well beyondthe Local Group.

HST cannot and JWST will not reach any large galaxiesbesides our Milky Way and M31 because they lack therequired angular resolution. A 20-m space telescope canreach 10-Gyr-old stars in ∼500 galaxies beyond the LocalGroup, including 68 giant spirals and 12 giant ellipticals,and can extend our reach even beyond the Coma SculptorCloud. Having such a range of environments and galaxytypes to study will finally allow us to truly test our under-standing of star formation and galaxy assembly.

2.3 Dark Matter Dynamics

Dwarf spheroidal galaxies (dSph), the faintest galaxiesknown, are extraordinary sites to explore the properties ofnonbaryonic dark matter. A key reason for this is the discov-ery that all 19 dSph satellites of the Milky Way, coveringmore than four orders of magnitude in luminosity, inhabitdark matter halos with the same mass (∼107MSUN) withintheir central 300 pc.6 Owing to their small masses, dSphshave the highest average phase space densities of any galaxytype, and this implies that for a given dark matter model,phase-space limited cores will occupy a larger fraction ofthe virial radii. Hence, the mean density profile of dSph gal-axies is a fundamental constraint on the nature of dark matter.

Current facilities, including ground telescopes and HST,are unable to measure transverse proper motions to the accu-racy needed to determine the necessary phase space densityprofile slopes within dSph galaxies. A 20-m space telescope,however, can perform the essential astrometric measure-ments. The SEL2 halo orbit, the likely operating locale fora 20-m space telescope, is far more thermally stable than lowearth orbit (LEO), and the sensors and actuators put in placeto maintain the structure to the precision necessary for exo-planet science would allow the telescope to achieve one-sigma astrometric errors of 0.005 pixels. Depending on thefield of view of the imager, a 20-m space telescope will beable to measure transverse proper motions for at least 200stars per dwarf galaxy. This will make such a facility capableof providing some of the best constraints on the nature ofdark matter.

3 ArchitectureThe development of a large space telescope is driven byscience goals (which include outreach and education) andaffordability.7 Achieving the scientific goals described inSec. 2 requires a 20-m class UV-optical telescope diffractionlimited at a wavelength of 0.5 μm, the highest possiblethroughput, an orbital deployment with minimal exposureto illumination from Earth and the moon, and with adequateFig. 1 Aitoff projection of land coverage fraction on Earth.4

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stray light rejection to capitalize fully upon this orbitaldeployment. Although detailed analysis is still required,these considerations support an SEL2 deployment for thetelescope, which has added advantages in terms of longterm, highly precise pointing stability.

Affordability, of course, is of at least equal importancewith scientific merit, and much of the discussion in thispaper addresses cost effective solutions to the technology,design, and architecture of this space telescope. We havefollowed a few basic principles in our architecture develop-ment to achieve the most cost-effective space telescopesolution:

• Leverage JWST lessons and technological heritage inmirror systems, structures, pointing and control, andwavefront sensing and control to reduce technologicaluncertainty and risk. Start with robust system marginsbuilt into the architecture for mass, thermal manage-ment, and stability. This includes active control ofthe primary mirror system, easing structural require-ments on the backplane.

• Use economies of scale to reduce costs, especially forthe primary mirror. Leverage robotic and human spaceassembly capabilities to enable these economies.

The result of applying these cost savings principles is thearchitecture shown in Fig. 2. For maximum leverage, wehave chosen the mirror segment size (1.3 m flat-to-flat) andcontrol authority (6 degrees of freedom plus radius of cur-vature) to be directly traceable to JWST. Since this is a UV-optical system, the system will need to be diffraction limitedat 0.5 μm, which will drive the performance needed for indi-vidual mirrors and the primary mirror stability. To achievethe stability, we propose an active control using a hybridguider/wavefront sensor as proposed for the ATLAST 9.2 mconcept.8

Behind the primary mirror assembly itself is the largestructure that holds the mirrors. While there is a tradebetween active control of mirrors at high bandwidth, wehave baselined a stiff backplane that is dynamically isolatedfrom the spacecraft. The stiffness requires a deep structure,but since thermal stability is not a driver it can be made ofstandard composites (or even aluminum). In the configura-tion shown in Fig. 3, the entire backplane can be constructedfrom two panel types. This means that nonrecurring costs for

jigs, stands, and procedures is only required for twostructural designs. On JWST, the wings and center sectionrepresent two geometries but the backplane is made of avery sophisticated composite structure tailored for highthermal stability due to the passive design. The “panels”of structure we propose can also be built in assembly linefashion using integration techniques developed for JWST:

• The large robotics assembly system used on JWST canbe used to install individual mirrors on these panels.

• The interfaces between structural elements can utilizeheritage concepts from both HST servicing (e.g.,latches and connectors) and the microdynamicallystable hinges and joints used on JWST.

To minimize the time and resources required for assemblyin space, we propose ground assembly of two mirror panelconfigurations; 12 and 16 mirrors, as illustrated in Fig. 3.This allows some of the most demanding tasks to be accom-plished on the ground: installing individual mirrors on thebackplane panels, checking their optical quality and func-tionality, and verifying that they can be phased to a masterprescription. Prelaunch acceptance testing would onlyrequire functional, vibration, acoustic, and thermal vacuumtesting. Although the panels are to be assembled together inspace, individual mirror attachments would be designed sothat each mirror could be removed, for example by using arobot normally stowed on the telescope but out of the lightpath that can span the front of the primary mirror for main-tenance and servicing.

In-space assembly of modules would greatly leverageservicing experience from HSTand the ISS, which combinedhuman intervention and telerobotics with advanced latchsystems. Latches connecting mirror panels would bepreloaded to assure dynamic stability similar to JWST.Since individual assembly tasks can be fully programmed,simulated, and practiced on the ground, robots could wellperform the majority of tasks. Direct human involvementwould be reserved for real-time anomaly resolution andtroubleshooting (avoiding the extended latency and ineffi-ciency of control from the ground).

The key aspect of this large, segmented, and paneledarchitecture is the economy of scale cost savings (seeFig. 4) that enable large-scale production of even high-technology items such as modern automobiles and iPods.Economy of scale is also key to the Thirty-Meter Telescope(TMT) ground observatory that leveraged the 10-m Kecksegmented methodology to implement a design with 492(or more) segments.9 As is shown in Fig. 4, comparisonof normalized data from the first 18 segments of bothJWST and a major large ground segmented telescope showsthat after 12 segments the cost per segment was reduced bynearly 40%. Discussions with experts in composite materialssuggest that similar savings could also be expected in othermaterials and that the biggest investment will be in nonrecur-ring engineering and facilitization. Note that much (not all)of the required facilitization for the 20-m UV-Optical spacetelescope has been accomplished by JWST.

The UV-optical application has the further cost savingadvantage over JWST of not requiring expensive cryogenictesting. Moreover, the candidate mirror materials, ULE®and silicon carbide/nanolaminate (Actuated Hybrid Mirrors,or AHMs), are highly compatible with assembly lineFig. 2 Notional 20-m telescope robot/astronaut installation of panels.

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processing. Experience has shown that the cost of the pri-mary mirror for JWST was ∼10% of the mission cost.10

This figure included the costs of expensive cryogenicprocessing, handling, and testing that is not required for aUV-optical mirror. While some improvements will be neededin the final metrology of mirrors to achieve 5 nm RMS UV-optical class quality, the number of extra polishing iterationsis minimal and therefore not a cost driver beyond the initialnonrecurring engineering. While a grassroots cost estimatebased on the mirror technology chosen will be required, webelieve that economy of scale advantages will enable a 20-mtelescope with a primary mirror that is no more than 10% ofthe overall observatory cost.

Unlike the 9.2-m ATLAST concept, we have selected anassembled light pipe sunshield (as shown in Fig. 2) to protectthe optical train from the sun, earth, and moon, both for straylight and thermal control. Since mass is not a major driver inthis modular architecture, particularly if we use the SLS forlaunch, we do not need the more complex deploymentrequired by the 9.2-m planar sunshield.

The modularity of this space telescope assembly concepthas a major added benefit: it makes the system serviceableand assures it an extended life.

• Like ground telescopes that last for decades withperiodic instrument upgrades, we believe this observa-tory could have a 50-year plus lifetime. In this sense,

the cost to build, service, and operate the telescope isamortized over an extended period and the cost/scienceratio is thereby improved.

• The actual assembly infrastructure in robots and humancapabilities will maximally leverage the NASA missionas a whole and will not be a direct cost to this mission.

• In addition, the modularity, scale, and scientific impor-tance of this mission can, like TMT and JWST, lead toan international collaboration that can distribute thecosts of development among many participants.

Cost prediction for space systems is inherently subject touncertainty and error, but Stahl et al.11 provide a rationalethat suggests that the MAST system cost model could beapproximated in important aspects by models for groundtelescopes. These latter models are characterized by costreductions as a function of time (i.e., costs are a functionof year of development). The authors base this upon theobservation that a new ground telescope tends to be a “varia-tion upon a theme,”while “Most space telescopes are unique,one of a kind designs which require the invention of newtechnology just to exist.” MAST has elements of bothmodels, most notably because it will draw heavily uponthe technology, expertise, and facilities of JWST; however,it will still require innovative technology development, suchas achieving and maintaining the precision primary mirrorfigure and finish required for coronagraphy. In so doing,it will also become a “variation upon a theme,” while itslarger components (primary mirror, light pipe, structure) willmake use of economies of scale that minimize costs. We alsobelieve that size alone will not invalidate the conclusions ofStahl and his co-authors, and that these components willremain a minority percentage of the overall cost of thetelescope. Therefore, although an accurate cost predictionwill not be possible short of highly detailed system/costmodeling, we believe that the actual cost of a 20-m class UV-Optical Observatory can be in family with the great observa-tories and can enable equally great advances in science.

4 Telescope/Observatory TechnologiesDue to past technology advances, the vast majority of therequired technology is already available at TechnologyReadiness Level (TRL) 6 or above.12 However, there are sev-eral technologies in which development along alternate pathscould provide significant cost and risk reduction. Theseinclude mirrors and coatings, wavefront sensing and control(WFS&C), structures and dynamic control, and certain

Fig. 3 Primary mirror buildup.

Fig. 4 Economies of scale.

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scientific instruments. These represent the key developmentenhancements that help achieve the performance required ofa large UV space observatory. A short review of each of thesetechnologies is provided in the following discussion. In gen-eral, these technologies (in at least one form) have attained aflight-ready TRL for longer wavelengths and smaller sys-tems, but can be enhanced to provide margin on achievingthe required performance in the UV and in a very largetelescope.

4.1 Mirror and Coating Technologies

Any analysis of a large optical system must include theprimary mirror assembly (PMA) as a central topic of consid-eration. When a space telescope system is so large that a seg-mented PMA is required to enable launch, the increasedprecision needed for UV imaging brings the complicationto an entirely new level. Both glass mirrors13,14 and silicon-carbide based actuated hybrid mirrors (AHM)15 may meetthe stringent requirements with additional technologydevelopment, and have been developed to advanced statesthrough programs such as the Advanced Mirror SystemDemonstrator (AMSD) and JWST. A representative examplefrom AMSD is shown in Fig. 5.

At a high level, the mirror quality must be on the order of5 to 10 nm RMS at 5 Å smoothness out to the edge. It ishelpful to break mirror figure and surface requirementsdown by spatial frequency content in order to better under-stand the processing challenges of fabrication:

• Low spatial frequency errors: These address areasfrom the full mirror diameter down to dimensions of∼50 mm.

• Mid-spatial frequency errors: From 50 mm down to0.1 mm (100 μm), including management of edgeroll-off errors between segments.

• High spatial frequency errors: From 100 μm downto 1 μm.

For UV systems, protected aluminum is the preferredcoating. Although there are lithium-based coatings that per-form better in the far-UV, they tend to absorb water anddegrade quickly prior to launch. Potentially, some develop-ment work could enhance the UV performance over alumi-num without the negative impacts associated with the

lithium-based coatings. Figure 6 shows the reflectivity ofgold, silver, and aluminum over a broad wavelength band.

4.2 Wavefront Sensing and Control

Wavefront sensing and control (WFSC) for the 20-m tele-scope will follow the active approach proposed for theATLAST 9.2 m and patented by Feinberg et al.16 Theapproach involves a hybrid sensor in which the WFSC sen-sors and guiders are part of the same instrument using a beamsplitter so that WFSC is performed on a reflected portion ofthe guide star. The hybrid sensors are placed in the outsidecorners of the field, allowing field diversity for aligning thesecondary mirror and consistent with the approach used toalign JWST. The key technologies that need work to fullyenable this are on-orbit WFSC which requires implementa-tion on flight qualified digital signal processors (or equiva-lent) and slightly improves sensing performance which ismostly a function of the hybrid instrument calibration.Since high-contrast instruments like the Visible NullingCoronagraph (VNC) may require a stable secondary mirror,there is also a trade on how to sense secondary mirror motionwhich could involve using the coronagraph data itself orimplement a laser truss for the secondary mirror.

4.3 Structures and Dynamic Control Technologies

Like the tolerances required of the optics, the supportingstructures17 also must be highly stable over time.

Fig. 5 1.4-m ultralightweight mirror, passive surface figure of 8.2 nm RMS.

Fig. 6 Reflectivity data for gold, silver, and aluminum.

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Vibration contributions must be minimized, but the ability tolimit input disturbances is constrained. Future vibration mit-igation will most likely be required to further reduce thedynamic response using an active dynamic control system18

that is incorporated into the structure. These can be, forexample, piezoelectric based mounting systems [for exam-ple, the Active Isolation Mount System (AIMS)] or voicecoil proof masses. The performance shown in Fig. 7 isbased on the 2.5-m dynamic testbed at Exelis and demon-strates the ability of an active system to reduce the dynamicresponse of the system.

4.4 High-Contrast Coronagraphy

Enabling very exciting exoplanet science with a 20-m seg-mented telescope requires advanced coronagraphic technol-ogies already being pursued for smaller space telescopes.This technology enables high-contrast observations (1e-10),but compatibility with a segmented pupil is required for theproposed ∼20-m architecture. A key technology that enableshigh contrast with a segmented pupil is the VNC, which isideally suited for a segmented system since the pupil isalready composed of hexagonal elements. Work on this hasbeen progressing at a rapid pace, and Lyon et al.19 havereported significant progress in a laboratory testbed. Addi-tional work on the VNC approach and work on adaptingcompeting coronagraphy approaches to segmented aperturesare a top priority for enabling exoplanet science on the 20-mobservatory.

5 Infrastructure Technology and ConsiderationsThe observatory system will depend upon interaction withand support from multiple elements of an extensive infra-structure, ground- and space-based; scientific, operational,and commercial; and existing or newly developed. Many ofthe existing elements will be useable in their current form orwith relatively minor enhancements, and will not be dis-cussed here. Such elements include:

• Science tasking and data interpretation. These can beprovided by existing organizations, most notably theSpace Telescope Science Institute (STScI) and theinternational astronomical community. HST andJWST provide accurate guides and models.

• Communications and control. These functions will beprovided by the same or analogous systems as used forJWST, notably a ground station at the STScI and theNASA Deep Space Network (DSN) for the actual datatransmission and reception.

The observatory will place special demands upon otherelements of the infrastructure, and these are discussed inthe following subsections.

5.1 Launch Systems

Specific details of the launch systems required will dependupon the final flight architecture selected for the mission, asdiscussed in Sec. 3 above. Two principal cases can be iden-tified, each of which imposes particular requirements on thelaunch system:

• Direct launch of either a complete observatory or con-stituent subsystems for assembly in the final opera-tional orbit. Given the order of magnitude of theprobable system masses, launch of a complete observa-tory on a single vehicle will only be possible usingsome variant of the Space Launch System (SLS), pic-tured in Fig. 8.

• Launch of observatory components to an intermediateassembly point [e.g., the ISS or its neighborhood,Geostationary orbit, or the Earth-Moon L2 (EML2)libration point] followed by transfer of a (nearly) com-plete observatory to the final orbit.

Adequate launch vehicles (in terms of launch mass andvolume capability) already exist20 in some form now orare in varying stages of development. In many cases, launchwill be limited more by available volume than by availablemass capability.

5.2 Infrastructure Technologies for ObservatoryAssembly

There are several basic strategies for deploying the telescopeonce it is in space: unassisted component deployment withno assembly (i.e., JWST), human assisted assembly, roboti-cally assisted assembly, and a combination of these two.Since this paper assumes a telescope too large to be folded

Fig. 7 Effectiveness of 2.5-m dynamic testbed for control of dynamic disturbances.

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into any planned launch shroud, unassisted componentdeployment will not be considered, and all deployment strat-egies include assembly of at least the primary mirror. Thus,there will be basic trades between human and roboticallyassisted assembly, complicated by multiple possible combi-nations and permutations. For example, robot assemblers can(conceivably) either be integral to the telescope itself orentirely separate space vehicles that perform functions forseveral scientific observatories. Much will clearly dependupon the development of both manned space capabilities andinfrastructures and those of robots (and telerobots) in thecoming few years.

Moreover, these trades will be significantly affected bythe location (or locations, since partial and final assemblymay occur in different orbits) in which assembly is accom-plished. Four possibilities are of possible interest: LEO,probably in the vicinity of the ISS; geostationary orbit(GEO); in the final halo orbit at SEL2 or enroute thereto;or in Earth-Moon L2 (EML2) halo orbit.

A thorough systems engineering analysis of all of the pos-sible combinations of these deployment strategies must awaita detailed mission concept study, but Table 1 is intended toidentify some of the relationships and considerations thatmust be included in the full analysis. Note that, if an Earth-Moon libration point is selected for observatory assembly,there could be increased opportunities for architectural flex-ibility, such as providing a remote servicing base for theobservatory and creating opportunities for international col-laborations. With the large light baffle and active control,lunar orbits not previously considered may also be viable

and we consider defining the orbit a key next step in archi-tecture planning.

6 Plan ForwardJWST experience clearly demonstrated that mission targetedtechnology investment is the most efficient strategy since itassures that technology requirements are founded directlyupon mission needs. This technology investment strategymust stand on three bases: top-level scientific requirements,technology roadmapping, and detailed assembly and opera-tions architecture studies.

6.1 Science Drivers

Identifying the key science drivers will help formulate detailsof the telescope requirements, in turn impacting the basicarchitecture. For example, precision pointing requires a verystable platform that may drive the stiffness of the assembledbackplane or the need for active control. In the same vein, adecision to prioritize exoplanet observations can drive theneed for an actively controlled secondary mirror and wouldrequire increased responsiveness in the control systemarchitecture.

6.2 Technology Roadmap

The proposed telescope architecture has no need for new,enabling technologies in any of its critical paths.However, the system performance would be significantlyenhanced and the return on investment increased from thesuccess of a small number of technology developments inparallel paths. A few key examples include finer resolutionactuators, vibration isolation systems, onboard digital signalprocessing, and replicated mirrors that fully meet UV-opticalrequirements. These all have established technology bases,so the requisite technology development lies mainly inreducing cost, improving margins, and minimizing risk.To manage these developments, a technology roadmap willbe needed that includes selection points and off-ramps attimes that phase with expected system evaluations anddecisions.

6.3 System Architecture

Since the observatory must be addressed in the context of thetotal NASA program, early system architecture studies toevaluate the assembly methods and best locations forassembly and operations are a critical step. For example,the NASA robotic and human roadmaps must be factoredin to assure maximum synergies. These studies can help

Fig. 8 Space Launch System (SLS). (a) Launch vehicle. (b) Panels innotional shroud.

Table 1 Candidate observatory deployment strategies.

LEO/ISS GEO SEL2/enroute EML2

Humanassembly

High legacy Not Legacy Difficult Possible

Robotassembly

Available Possible Possible Possible

Combinationsa Available Unlikely Unlikely High value

ae.g., a human operator directly within a near-real-time roboticcontrol loop.

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develop the servicing and robotic interface requirements thatwould allow for real demonstration of assembly techniqueson ISS. As another example, SLS is a highly attractivelaunch vehicle for the observatory, but it must not exceedcertain minimum levels of contamination and vibro-acousticloads. We believe these architecture studies could happenquickly and should target the highest-priority interfacesfirst, such as inter-panel connectivity.

7 ConclusionThe case has been made that development of a 20-m classspace observatory is well supported both from a scienceneeds perspective and from a technical feasibility perspec-tive. Moreover, it has also been shown that it is both feasibleand mutually beneficial to leverage this development withother programs: NASA Exploration, International, andCommercial. The approach, heavily drawn from the heritageof programs such as HST, ISS, and JWST, is modular andcan be adapted for several scientific requirements and at var-iable size scales.

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Biographies and photographs of the authors not available.

Optical Engineering 091802-8 September 2013/Vol. 52(9)

Feinberg et al.: Modular assembled space telescope