Low Thrust Electric Propulsion Mission Concepts For a 3-Meter Class Space Telescope

Abhi Tripathi; Buell T. Jannuzi; Dillon O'Reilly; Drew Latta; Ewan S. Douglas; Isaac Saedi-Marghmaleki; Jeffrey Kingsley; Justin Hom; Mohamed Nassif; Neel Kunjur

arxiv: 2606.26282 · v1 · pith:JNN6NWPFnew · submitted 2026-06-24 · 🌌 astro-ph.IM

Low Thrust Electric Propulsion Mission Concepts For a 3-Meter Class Space Telescope

Yael M. Brynjegard-Bialik , Mohamed Nassif , Drew Latta , Neel Kunjur , Nicholas Rahaim , Paul DeTrempe , Abhi Tripathi , Isaac Saedi-Marghmaleki

show 7 more authors

Dillon O'Reilly Justin Hom Patrick Ingraham Jeffrey Kingsley Buell T. Jannuzi S. Pete Worden Ewan S. Douglas

This is my paper

Pith reviewed 2026-06-26 01:07 UTC · model grok-4.3

classification 🌌 astro-ph.IM

keywords low thrust propulsionspace telescopelunar resonant orbitSun-Earth L2 haloexoplanet imagingmission designradiation environmentorbital transfer

0 comments

The pith

A 3-meter space telescope can reach stable 2:1 lunar resonant or Sun-Earth L2 halo orbits using low-thrust electric propulsion for exoplanet observations.

A machine-rendered reading of the paper's core claim, the machinery that carries it, and where it could break.

The paper assesses mission designs for a 3-meter telescope on a spacecraft with low thrust propulsion. It examines transfer paths to a 2:1 lunar resonant orbit and a Sun-Earth L2 halo orbit, along with the radiation conditions during those transfers. These orbits offer stable conditions with less radiation and thermal variation, which helps maintain the precision needed for exoplanet direct imaging and transit measurements. The analysis aims to maximize scientific return by selecting orbits that support long, high-quality observations while keeping costs down through the use of electric propulsion.

Core claim

The paper claims that the 2:1 lunar resonant orbit and Sun-Earth L2 halo orbit are viable science orbits for the telescope, with suitable low-thrust transfer trajectories that keep radiation exposure manageable.

What carries the argument

The analysis of low-thrust transfer trajectories to the 2:1 lunar resonant orbit and Sun-Earth L2 halo orbit, including radiation environment assessment.

If this is right

Transfer trajectories to the target orbits can be achieved with low thrust propulsion.
Radiation exposure remains manageable during the transfer phase.
The chosen orbits provide reduced radiation and thermal fluctuations for stable observations.
This setup supports high-precision exoplanet detection and characterization.

Where Pith is reading between the lines

These are editorial extensions of the paper, not claims the author makes directly.

Similar orbit choices might benefit other space telescope missions with electric propulsion.
Detailed propulsion system performance modeling could refine the transfer timelines.
Radiation data from these transfers could inform instrument shielding designs for future missions.

Load-bearing premise

The low thrust propulsion system can deliver the necessary delta-v for transfers to the target orbits without excessive radiation exposure to the spacecraft.

What would settle it

A detailed trajectory simulation demonstrating that no low-thrust path to either orbit keeps total radiation dose below instrument tolerance levels would disprove the mission feasibility.

read the original abstract

Space-based telescopes benefit from operating in stable orbital environments with reduced exposure to radiation and thermal fluctuations in order to minimize cost and maximize time for high-quality observations. Finding this ideal environment proves beneficial particularly for exoplanet discovery and characterization; direct imaging requires sub-nanometer wavefront stability and multi-hour observations, and transit detection requires parts-per-million photometric accuracy. Our team at University of Arizona's Steward Observatory and the Wyant College of Optical Sciences is evaluating various mission concepts for a 3-meter class telescope design, flying on a spacecraft bus equipped with a low thrust propulsion system. The presented mission analysis focuses on obtaining suitable transfer trajectories to the desired science orbit as well as understanding the radiation environment during the transfer, which is relevant for low thrust missions. The science analysis explores different operating orbits with the purpose of yielding maximum scientific return for detecting exoplanets. In this paper, we evaluate the use of a 2:1 lunar resonant orbit and a Sun-Earth L2 halo orbit for our mission.

Editorial analysis

A structured set of objections, weighed in public.

Desk editor's note, referee report, simulated authors' rebuttal, and a circularity audit. Tearing a paper down is the easy half of reading it; the pith above is the substance, this is the friction.

Desk Editor's Note private letter to a colleague

This is a targeted mission study applying known low-thrust trajectories and orbits to a 3 m telescope, with the main value in the radiation and transfer details rather than any new orbital mechanics.

read the letter

The paper evaluates transfer trajectories and radiation exposure for a 3 m class telescope on low-thrust electric propulsion, specifically to a Sun-Earth L2 halo orbit and a 2:1 lunar resonant orbit. That is the core of what they did.

The work applies established orbital concepts to one concrete telescope size and bus. The useful part is the attention to radiation during the longer coast times that low thrust creates. That matters for detector and electronics lifetime on an exoplanet imaging mission, and the authors flag it explicitly as relevant to their design.

Nothing in the orbital mechanics or propulsion modeling is new. Halo orbits and lunar resonant paths have been studied for decades. The paper does not derive new methods or present independent verification of the trajectory tools.

The main limitation is scope. The analysis stays inside one telescope diameter and one propulsion class, so the results do not generalize easily. The abstract gives no delta-v budgets, transfer durations, or dose numbers, which makes it hard to judge how tight the radiation margins actually are. If the full text has those numbers and error bars, the paper improves; if it stays qualitative, the claims about scientific return rest on weaker ground.

This is for groups already working on small space telescopes or low-thrust mission concepts at places like Steward Observatory. A reader planning a similar 2-4 m exoplanet imager could pull the orbit choices as a reference point.

It deserves peer review. The topic is practical, the authors have done the specific homework, and the radiation focus is a legitimate engineering question even if the orbital work itself is routine.

Referee Report

2 major / 0 minor

Summary. The manuscript evaluates low-thrust electric propulsion concepts for a 3 m class space telescope, with focus on obtaining transfer trajectories to a 2:1 lunar resonant orbit and a Sun-Earth L2 halo orbit while characterizing the radiation environment during transfer; the goal is to identify orbits that maximize scientific return for exoplanet detection and characterization by providing stable thermal and radiation conditions.

Significance. If the trajectory and radiation analyses prove robust, the work would supply concrete mission-design inputs for selecting stable orbits that reduce operational costs and improve observation quality for direct imaging and transit photometry; the emphasis on low-thrust transfers is timely given increasing interest in electric propulsion for deep-space astrophysics missions.

major comments (2)

[Abstract] Abstract and purpose statement: no quantitative outputs (transfer times, Δv budgets, radiation dose estimates, or comparison metrics between the two target orbits) are supplied to support the central claim that suitable transfers with manageable radiation exposure exist; without these data the feasibility evaluation cannot be assessed.
[Abstract] The weakest assumption identified (low-thrust system achieving transfers while keeping radiation manageable) is presented as the output of the work, yet no supporting calculations, trajectory models, or radiation-environment results appear in the provided material, leaving the central claim without load-bearing evidence.

Simulated Author's Rebuttal

2 responses · 0 unresolved

We thank the referee for the constructive comments on our manuscript. We agree that the abstract should be revised to include key quantitative results from the trajectory and radiation analyses already present in the full text, which will strengthen the presentation of our central claims.

read point-by-point responses

Referee: [Abstract] Abstract and purpose statement: no quantitative outputs (transfer times, Δv budgets, radiation dose estimates, or comparison metrics between the two target orbits) are supplied to support the central claim that suitable transfers with manageable radiation exposure exist; without these data the feasibility evaluation cannot be assessed.

Authors: We agree with this assessment of the abstract. The full manuscript contains the supporting trajectory optimization results, including specific transfer times, Δv budgets for the low-thrust system, radiation dose estimates along both paths, and direct comparisons of stability and exposure between the 2:1 lunar resonant orbit and Sun-Earth L2 halo orbit. We will revise the abstract to incorporate these quantitative outputs so that the feasibility evaluation is evident from the summary. revision: yes
Referee: [Abstract] The weakest assumption identified (low-thrust system achieving transfers while keeping radiation manageable) is presented as the output of the work, yet no supporting calculations, trajectory models, or radiation-environment results appear in the provided material, leaving the central claim without load-bearing evidence.

Authors: The full manuscript details the low-thrust trajectory models (including the specific electric propulsion assumptions and optimization approach), the computed transfer trajectories to each target orbit, and the radiation-environment results (dose accumulation during transfer). These form the load-bearing evidence for the claim. We acknowledge, however, that the abstract does not preview these results and will update it to summarize the key quantitative findings from the body of the paper. revision: yes

Circularity Check

0 steps flagged

No circularity; direct mission evaluation with no self-referential derivations

full rationale

The paper's core activity is an evaluation of transfer trajectories and radiation environments for low-thrust propulsion to 2:1 lunar resonant and Sun-Earth L2 halo orbits. This evaluation constitutes the output of the work rather than an unexamined premise. No equations, fitted parameters, self-citations, or ansatzes are described that reduce any claimed result to its own inputs by construction. The analysis is self-contained against external benchmarks such as orbital mechanics simulations.

Axiom & Free-Parameter Ledger

0 free parameters · 0 axioms · 0 invented entities

Abstract-only review yields no explicit free parameters, axioms, or invented entities; the evaluation relies on standard orbital mechanics assumptions not detailed here.

pith-pipeline@v0.9.1-grok · 5773 in / 920 out tokens · 23426 ms · 2026-06-26T01:07:44.072663+00:00 · methodology

discussion (0)

Reference graph

Works this paper leans on

42 extracted references · 13 canonical work pages · 1 internal anchor

[1]

Experience with the Hubble Space Telescope: 20 years of an archetype

Lallo, M., “Experience with the Hubble Space Telescope: 20 years of an archetype,”Optical Engineering, Vol. 51, No. 1, 2012, p. 011011. https://doi.org/10.1117/1.OE.51.1.011011, URL http://arxiv.org/abs/1203.0002

work page internal anchor Pith review Pith/arXiv arXiv doi:10.1117/1.oe.51.1.011011 2012
[2]

Requirements and design reference mission for the WFIRST/AFTA coronagraph instrument,

Demers, R. T., Dekens, F., Calvet, R., Chang, Z., Effinger, R., Ek, E., Hovland, L., Jones, L., Loc, A., Nemati, B., Noecker, C., Neville, T., Pham, H., Rud, M., Tang, H., and Villalvazo, J., “Requirements and design reference mission for the WFIRST/AFTA coronagraph instrument,”Techniques and Instrumentation for Detection of Exoplanets VII, Vol. 9605, Int...

work page doi:10.1117/12.2191792 2015
[3]

On-orbit performance & operation of the attitude & pointing control subsystems on ASTERIA,

Pong, C., “On-orbit performance & operation of the attitude & pointing control subsystems on ASTERIA,” 2018

2018
[4]

Artemis: An Overview of NASA’s Activities to Re- turn Humans to the Moon,

Bartusek, L. M., Davis, J. L., and Vess, M. F., “Nancy Grace Roman Space Telescope Observatory Implementation and Challenges,”2022 IEEE Aerospace Conference (AERO), 2022, pp. 01–14. https://doi.org/10.1109/AERO53065.2022.9843415

work page doi:10.1109/aero53065.2022.9843415 2022
[5]

James Webb Space Telescope: L2 communications for science data processing,

Johns, A., Seaton, B., Gal-Edd, J., Jones, R., Fatig, C., and Wasiak, F., “James Webb Space Telescope: L2 communications for science data processing,”Observatory Operations: Strategies, Processes, and Systems II, Vol. 7016, SPIE, 2008, pp. 425–431

2008
[6]

A space imaging concept based on a 4m structured spun-cast borosilicate monolithic primary mirror,

West, S. C., Bailey, S. H., Bauman, S., Cuerden, B., Granger, Z., and Olbert, B. H., “A space imaging concept based on a 4m structured spun-cast borosilicate monolithic primary mirror,”SPIE Astronomical Telescopes + Instrumentation, edited by J. M. Oschmann, Jr., M. C. Clampin, and H. A. MacEwen, San Diego, California, USA, 2010, p. 77311O. https://doi.or...

work page doi:10.1117/12.857750 2010
[7]

S., Aldering, G., Allan, G

Douglas, E. S., Aldering, G., Allan, G. W., Anche, R., Angel, R., Ard, C. C., Chakrabarti, S., Close, L. M., Derby, K., Edelstein, J., Ford, J., Gersh-Range, J., Haffert, S. Y., Ingraham, P. J., Kang, H., Kelly, D. M., Kim, D., Lesser, M., Leisenring, J. M., Lin, Y.-C., Males, J. R., Martin, B., Payan, B. A., M, S. K. P., Rubin, D., Selznick, S., Gorkom, ...

work page doi:10.1117/12.2677843 2023
[8]

An Open-Source Python Pipeline for Optical Performances and Alignment Analysis Using Ray-Tracing Tools,

Nicolas, P., Ingraham, P., Choi, H., Douglas, E. S., Blomquist, S., Derby, K., and Kim, D., “An Open-Source Python Pipeline for Optical Performances and Alignment Analysis Using Ray-Tracing Tools,” 2026

2026
[9]

Design of the vacuum high contrast imaging testbed for CDEEP, the Coronagraphic Debris and Exoplanet Exploring Pioneer,

Maier, E. R., Douglas, E. S., Kim, D. W., Su, K., Ashcraft, J. N., Breckinridge, J. B., Choi, H., Choquet, E., Connors, T. E., Durney, O., Gonzales, K. L., Guthery, C. E., Haughwout, C. A., Heath, J. C., Hyatt, J., Lumbres, J., Males, J. R., Matthews, E. C., Milani, K., Montoya, O. M., N’Diaye, M., Noenickx, J., Pogorelyuk, L., Ruane, G., Schneider, G., S...

work page doi:10.1117/12.2560878 2020
[10]

Large etendue 3-meter unobscured three mirror anastigmat telescope for astrophysics,

Kim, D., Anche, R., Kang, H., Nicolas, P., Choi, H., Van Gorkom, K., Kim, Y.-S., Harrison, L., Ward, M., and Eiklenborg, M., “Large etendue 3-meter unobscured three mirror anastigmat telescope for astrophysics,”Optical Fabrication and Testing, Optica Publishing Group, 2025, pp. OW3B–2. URL https://opg.optica.org/abstract.cfm?uri=oft-2025-OW3B.2

2025
[11]

The Vector Vortex Coronagraph: Laboratory ResultsandFirstLightatPalomarObservatory,

Mawet, D., Serabyn, E., Liewer, K., Burruss, R., Hickey, J., and Shemo, D., “The Vector Vortex Coronagraph: Laboratory ResultsandFirstLightatPalomarObservatory,”ApJ,Vol.709,No.1,2010,p.53. https://doi.org/10.1088/0004-637X/709/1/53, URL http://iopscience.iop.org/0004-637X/709/1/53

work page doi:10.1088/0004-637x/709/1/53 2010
[12]

In: 2020 IEEE Aerospace Conference, pp

Philip Stahl, H., and Team, M. . J. D., “Habitable Exoplanet Observatory (HabEx) Telescope: Systems Engineering and STOP Modeling,”2020 IEEE Aerospace Conference, 2020, pp. 1–10. https://doi.org/10.1109/AERO47225.2020.9172550

work page doi:10.1109/aero47225.2020.9172550 2020
[13]

Launch window trade analysis for the james webb space telescope,

Yu, W. H., and Richon, K., “Launch window trade analysis for the james webb space telescope,”International Symposium on Space Flight Dynamics, 2014

2014
[14]

Euclid. I. Overview of the Euclid mission,

Mellier, Y., Abdurroúf, A., Barroso, J. A., Achúcarro, A., Adamek, J., Adam, R., Addison, G. E., Aghanim, N., Aguena, M., Ajani, V., et al., “Euclid. I. Overview of the Euclid mission,”Astronomy & Astrophysics, 2025

2025
[15]

Overview of the Gaia mission,

Perryman, M., “Overview of the Gaia mission,”Astrometry in the Age of the Next Generation of Large Telescopes, Vol. 338, 2005, p. 3. 19

2005
[16]

PLATO Mission Overview,

Rauer, H., Heras, A., Mas-Hesse, M., and Pagano, I., “PLATO Mission Overview,”European Planetary Science Congress, 2024, pp. EPSC2024–197

2024
[17]

ArielSpaceMission,

Lueftinger,T.,andTinetti,G.,“ArielSpaceMission,”EncyclopediaofAstrobiology,Springer,Berlin,Heidelberg,2023,pp.189–

2023
[18]

https://doi.org/10.1007/978-3-662-65093-6_5532, URL https://link.springer.com/rwe/10.1007/978-3-662-65093-6_5532

work page doi:10.1007/978-3-662-65093-6_5532
[19]

Trajectory design for the transiting exoplanet survey satellite,

Dichmann, D. J., Parker, J. J., Williams, T. W., and Mendelsohn, C. R., “Trajectory design for the transiting exoplanet survey satellite,”International Symposium on Space Flight Dynamics, 2014

2014
[20]

Trajectory design to mitigate risk for the Transiting Exoplanet Survey Satellite (TESS),

Dichmann, D. J., Parker, J. J., Nickel, C., and Lutz, S., “Trajectory design to mitigate risk for the Transiting Exoplanet Survey Satellite (TESS),”AIAA/AAS Astrodynamics Specialist Conference, 2016, p. 5664

2016
[21]

IBEX Revisited: Operational Results for Long-Term Cislunar Orbit Propagation,

Carrico, J., Policastri, L., and Lutz, S., “IBEX Revisited: Operational Results for Long-Term Cislunar Orbit Propagation,” AAS/AIAA Astrodynamics Specialist Conference 2018, 2018

2018
[22]

Electric propulsion methods for small satellites: A review,

O’Reilly, D., Herdrich, G., and Kavanagh, D. F., “Electric propulsion methods for small satellites: A review,”Aerospace, Vol. 8, No. 1, 2021, p. 22

2021
[23]

A study on simultaneous design of a Hall effect thruster and its low-thrust trajectory,

Kwon, K., Lantoine, G., Russell, R. P., and Mavris, D. N., “A study on simultaneous design of a Hall effect thruster and its low-thrust trajectory,”Acta Astronautica, Vol. 119, 2016, pp. 34–47

2016
[24]

Radiation Effects and COTS Parts in SmallSats,

Sinclair, D., and Dyer, J., “Radiation Effects and COTS Parts in SmallSats,”Small Satellite Conference, Logan, Utah, USA, 2013, p. 12. URL https://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=2934&context=smallsat

2013
[25]

RecommendationsonUseofCommercial-Off-The-Shelf (COTS) Electrical, Electronic, and Electromechanical (EEE) Parts for NASA Missions,

Hodson, R. F., Chen, Y., Pandolf, J. E., Ling, K., Boomer, K. T., Green, C. M., Leitner, J. A., Majewicz, P., Gore, S. H., Faller, C.S.,Denson,E.C.,Hodge,R.E.,Thoren,A.P.,andDefrancis,M.A.,“RecommendationsonUseofCommercial-Off-The-Shelf (COTS) Electrical, Electronic, and Electromechanical (EEE) Parts for NASA Missions,” Tech. Rep. NESC-RP-19-01490, Dec
[26]

URL https://ntrs.nasa.gov/citations/20205011579

arXiv
[27]

Decadal, S. o. A. a. A. . A., Space Studies Board, Board on Physics and Astronomy, Division on Engineering and Physical Sciences, and National Academies of Sciences, Engineering, and Medicine,Pathways to Discovery in Astronomy and Astrophysics for the 2020s, National Academies Press, Washington, D.C., 2021. https://doi.org/10.17226/26141, URL https://www....

work page doi:10.17226/26141 2021
[28]

Maximizing the ExoEarth candidate yield from a future direct imaging mission,

Stark, C. C., Roberge, A., Mandell, A., and Robinson, T. D., “Maximizing the ExoEarth candidate yield from a future direct imaging mission,”The Astrophysical Journal, Vol. 795, No. 2, 2014, p. 122

2014
[29]

How the Habitable Worlds Observatory’s field of regard will impact the use of precursor science,

Spohn, C., Stark, C., and Savransky, D., “How the Habitable Worlds Observatory’s field of regard will impact the use of precursor science,”Space Telescopes and Instrumentation 2024: Optical, Infrared, and Millimeter Wave, Vol. 13092, SPIE, 2024, pp. 1869–1881

2024
[30]

Transiting Exoplanet Survey Satellite (TESS) flight dynamics commissioning results and experiences,

Parker, J. J. K., Lebois, R. L., Lutz, S., Nickel, C., Ferrant, K., and Michaels, A., “Transiting Exoplanet Survey Satellite (TESS) flight dynamics commissioning results and experiences,”AAS GUIDANCE & CONTROL CONFERENCE, 2018. URL https://ntrs.nasa.gov/api/citations/20180006156/downloads/20180006156.pdf

arXiv 2018
[31]

James webb space telescope trajectory, communications, and instrumentation comprehensive analysis,

Llanos, P. J., and Matas, A., “James webb space telescope trajectory, communications, and instrumentation comprehensive analysis,”In 2022 AAS/AIAA Astrodynamics Specialist Conference. AAS/AIAA. AAS Paper 22–623, August 2022. Charlotte, NC, 2022

2022
[32]

Targeting cislunar near rectilinear halo orbits for human space exploration,

Williams, J., Lee, D. E., Whitley, R. J., Bokelmann, K. A., Davis, D. C., and Berry, C. F., “Targeting cislunar near rectilinear halo orbits for human space exploration,”AAS/AIAA Space Flight Mechanics Meeting, 2017

2017
[33]

Methodology,

Parker, J. S., and Anderson, R. L., “Methodology,”Low-Energy Lunar Trajectory Design, John Wiley & Sons, Ltd, 3 June 2014, 2014, pp. 27–115. https://doi.org/10.1002/9781118855065.ch2, URL https://onlinelibrary.wiley.com/doi/abs/10.1002/ 9781118855065.ch2

work page doi:10.1002/9781118855065.ch2 2014
[34]

Transfers to Lunar Libration Orbits,

Parker, J. S., and Anderson, R. L., “Transfers to Lunar Libration Orbits,”Low-Energy Lunar Trajectory Design, John Wiley & Sons, Ltd, 2014, Chap. 3, pp. 117–226. https://doi.org/https://doi.org/10.1002/9781118855065.ch3, URL https: //onlinelibrary.wiley.com/doi/abs/10.1002/9781118855065.ch3

work page doi:10.1002/9781118855065.ch3 2014
[35]

Representations of invariant manifolds for applications in three-body systems,

Howell, K., Beckman, M., Patterson, C., and Folta, D., “Representations of invariant manifolds for applications in three-body systems,”The Journal of the Astronautical Sciences, Vol. 54, No. 1, 2006, pp. 69–93

2006
[36]

JWST Data Volume and Data Excess - JWST User Documentation,

“JWST Data Volume and Data Excess - JWST User Documentation,” , ???? URL https://jwst-docs.stsci.edu/jwst-general- support/jwst-data-volume-and-data-excess#gsc.tab=0. 20
[37]

EXOSIMS: Exoplanet Open-Source Imaging Mission Simulator,

Savransky, D., Delacroix, C., and Garrett, D., “EXOSIMS: Exoplanet Open-Source Imaging Mission Simulator,” , 2017. Ascl:1706.010

2017
[38]

ExoPAG SAG13: Exoplanet Occurrence Rates and Distributions,

ExoPAG Study Analysis Group 13 (SAG13), “ExoPAG SAG13: Exoplanet Occurrence Rates and Distributions,” Tech. rep., NASA Exoplanet Exploration Program Analysis Group (ExoPAG), 2017. URL https://science.nasa.gov/wp-content/uploads/ 2023/04/SAG13_closeout.pdf

2017
[39]

JPL HORIZONS On-Line Ephemeris System,

Giorgini, J. D., “JPL HORIZONS On-Line Ephemeris System,” https://ssd.jpl.nasa.gov/horizons/, 2024. NASA Jet Propulsion Laboratory, Solar System Dynamics Group

2024
[40]

The calculation of proton penetration and dose rates - NASA Technical Reports Server (NTRS),

Burrell, M. O., “The calculation of proton penetration and dose rates - NASA Technical Reports Server (NTRS),” Technical Report 19650025029, NASA Marshall Space Flight Center, Huntsville, Alabama, Jan. 1965. URL https://ntrs.nasa.gov/ citations/19650025029

arXiv 1965
[41]

Average depths of electron penetration: use as characteristic depths of exposure,

Lazurik, V., Moskvin, V., and Tabata, T., “Average depths of electron penetration: use as characteristic depths of exposure,” IEEE Transactions on Nuclear Science, Vol. 45, No. 3, 1998, pp. 626–631

1998
[42]

The Roman coronagraph community participation program: observation planning,

Wolff, S. G., Wang, J., Stapelfeldt, K., Bailey, V. P., Savransky, D., Hom, J., Biller, B., Brandner, W., Anche, R., Blunt, S., Brinjikji, M., Girard, J. H., Krause, O., Li, Z., Livingston, J., Millar-Blanchaer, M. A., Noel, M., Pueyo, L., De Rosa, R. J., Samland, M., and Schragal, N., “The Roman coronagraph community participation program: observation pl...

work page doi:10.1117/12.3020205 2024

[1] [1]

Experience with the Hubble Space Telescope: 20 years of an archetype

Lallo, M., “Experience with the Hubble Space Telescope: 20 years of an archetype,”Optical Engineering, Vol. 51, No. 1, 2012, p. 011011. https://doi.org/10.1117/1.OE.51.1.011011, URL http://arxiv.org/abs/1203.0002

work page internal anchor Pith review Pith/arXiv arXiv doi:10.1117/1.oe.51.1.011011 2012

[2] [2]

Requirements and design reference mission for the WFIRST/AFTA coronagraph instrument,

Demers, R. T., Dekens, F., Calvet, R., Chang, Z., Effinger, R., Ek, E., Hovland, L., Jones, L., Loc, A., Nemati, B., Noecker, C., Neville, T., Pham, H., Rud, M., Tang, H., and Villalvazo, J., “Requirements and design reference mission for the WFIRST/AFTA coronagraph instrument,”Techniques and Instrumentation for Detection of Exoplanets VII, Vol. 9605, Int...

work page doi:10.1117/12.2191792 2015

[3] [3]

On-orbit performance & operation of the attitude & pointing control subsystems on ASTERIA,

Pong, C., “On-orbit performance & operation of the attitude & pointing control subsystems on ASTERIA,” 2018

2018

[4] [4]

Artemis: An Overview of NASA’s Activities to Re- turn Humans to the Moon,

Bartusek, L. M., Davis, J. L., and Vess, M. F., “Nancy Grace Roman Space Telescope Observatory Implementation and Challenges,”2022 IEEE Aerospace Conference (AERO), 2022, pp. 01–14. https://doi.org/10.1109/AERO53065.2022.9843415

work page doi:10.1109/aero53065.2022.9843415 2022

[5] [5]

James Webb Space Telescope: L2 communications for science data processing,

Johns, A., Seaton, B., Gal-Edd, J., Jones, R., Fatig, C., and Wasiak, F., “James Webb Space Telescope: L2 communications for science data processing,”Observatory Operations: Strategies, Processes, and Systems II, Vol. 7016, SPIE, 2008, pp. 425–431

2008

[6] [6]

A space imaging concept based on a 4m structured spun-cast borosilicate monolithic primary mirror,

West, S. C., Bailey, S. H., Bauman, S., Cuerden, B., Granger, Z., and Olbert, B. H., “A space imaging concept based on a 4m structured spun-cast borosilicate monolithic primary mirror,”SPIE Astronomical Telescopes + Instrumentation, edited by J. M. Oschmann, Jr., M. C. Clampin, and H. A. MacEwen, San Diego, California, USA, 2010, p. 77311O. https://doi.or...

work page doi:10.1117/12.857750 2010

[7] [7]

S., Aldering, G., Allan, G

Douglas, E. S., Aldering, G., Allan, G. W., Anche, R., Angel, R., Ard, C. C., Chakrabarti, S., Close, L. M., Derby, K., Edelstein, J., Ford, J., Gersh-Range, J., Haffert, S. Y., Ingraham, P. J., Kang, H., Kelly, D. M., Kim, D., Lesser, M., Leisenring, J. M., Lin, Y.-C., Males, J. R., Martin, B., Payan, B. A., M, S. K. P., Rubin, D., Selznick, S., Gorkom, ...

work page doi:10.1117/12.2677843 2023

[8] [8]

An Open-Source Python Pipeline for Optical Performances and Alignment Analysis Using Ray-Tracing Tools,

Nicolas, P., Ingraham, P., Choi, H., Douglas, E. S., Blomquist, S., Derby, K., and Kim, D., “An Open-Source Python Pipeline for Optical Performances and Alignment Analysis Using Ray-Tracing Tools,” 2026

2026

[9] [9]

Design of the vacuum high contrast imaging testbed for CDEEP, the Coronagraphic Debris and Exoplanet Exploring Pioneer,

Maier, E. R., Douglas, E. S., Kim, D. W., Su, K., Ashcraft, J. N., Breckinridge, J. B., Choi, H., Choquet, E., Connors, T. E., Durney, O., Gonzales, K. L., Guthery, C. E., Haughwout, C. A., Heath, J. C., Hyatt, J., Lumbres, J., Males, J. R., Matthews, E. C., Milani, K., Montoya, O. M., N’Diaye, M., Noenickx, J., Pogorelyuk, L., Ruane, G., Schneider, G., S...

work page doi:10.1117/12.2560878 2020

[10] [10]

Large etendue 3-meter unobscured three mirror anastigmat telescope for astrophysics,

Kim, D., Anche, R., Kang, H., Nicolas, P., Choi, H., Van Gorkom, K., Kim, Y.-S., Harrison, L., Ward, M., and Eiklenborg, M., “Large etendue 3-meter unobscured three mirror anastigmat telescope for astrophysics,”Optical Fabrication and Testing, Optica Publishing Group, 2025, pp. OW3B–2. URL https://opg.optica.org/abstract.cfm?uri=oft-2025-OW3B.2

2025

[11] [11]

The Vector Vortex Coronagraph: Laboratory ResultsandFirstLightatPalomarObservatory,

Mawet, D., Serabyn, E., Liewer, K., Burruss, R., Hickey, J., and Shemo, D., “The Vector Vortex Coronagraph: Laboratory ResultsandFirstLightatPalomarObservatory,”ApJ,Vol.709,No.1,2010,p.53. https://doi.org/10.1088/0004-637X/709/1/53, URL http://iopscience.iop.org/0004-637X/709/1/53

work page doi:10.1088/0004-637x/709/1/53 2010

[12] [12]

In: 2020 IEEE Aerospace Conference, pp

Philip Stahl, H., and Team, M. . J. D., “Habitable Exoplanet Observatory (HabEx) Telescope: Systems Engineering and STOP Modeling,”2020 IEEE Aerospace Conference, 2020, pp. 1–10. https://doi.org/10.1109/AERO47225.2020.9172550

work page doi:10.1109/aero47225.2020.9172550 2020

[13] [13]

Launch window trade analysis for the james webb space telescope,

Yu, W. H., and Richon, K., “Launch window trade analysis for the james webb space telescope,”International Symposium on Space Flight Dynamics, 2014

2014

[14] [14]

Euclid. I. Overview of the Euclid mission,

Mellier, Y., Abdurroúf, A., Barroso, J. A., Achúcarro, A., Adamek, J., Adam, R., Addison, G. E., Aghanim, N., Aguena, M., Ajani, V., et al., “Euclid. I. Overview of the Euclid mission,”Astronomy & Astrophysics, 2025

2025

[15] [15]

Overview of the Gaia mission,

Perryman, M., “Overview of the Gaia mission,”Astrometry in the Age of the Next Generation of Large Telescopes, Vol. 338, 2005, p. 3. 19

2005

[16] [16]

PLATO Mission Overview,

Rauer, H., Heras, A., Mas-Hesse, M., and Pagano, I., “PLATO Mission Overview,”European Planetary Science Congress, 2024, pp. EPSC2024–197

2024

[17] [17]

ArielSpaceMission,

Lueftinger,T.,andTinetti,G.,“ArielSpaceMission,”EncyclopediaofAstrobiology,Springer,Berlin,Heidelberg,2023,pp.189–

2023

[18] [18]

https://doi.org/10.1007/978-3-662-65093-6_5532, URL https://link.springer.com/rwe/10.1007/978-3-662-65093-6_5532

work page doi:10.1007/978-3-662-65093-6_5532

[19] [19]

Trajectory design for the transiting exoplanet survey satellite,

Dichmann, D. J., Parker, J. J., Williams, T. W., and Mendelsohn, C. R., “Trajectory design for the transiting exoplanet survey satellite,”International Symposium on Space Flight Dynamics, 2014

2014

[20] [20]

Trajectory design to mitigate risk for the Transiting Exoplanet Survey Satellite (TESS),

Dichmann, D. J., Parker, J. J., Nickel, C., and Lutz, S., “Trajectory design to mitigate risk for the Transiting Exoplanet Survey Satellite (TESS),”AIAA/AAS Astrodynamics Specialist Conference, 2016, p. 5664

2016

[21] [21]

IBEX Revisited: Operational Results for Long-Term Cislunar Orbit Propagation,

Carrico, J., Policastri, L., and Lutz, S., “IBEX Revisited: Operational Results for Long-Term Cislunar Orbit Propagation,” AAS/AIAA Astrodynamics Specialist Conference 2018, 2018

2018

[22] [22]

Electric propulsion methods for small satellites: A review,

O’Reilly, D., Herdrich, G., and Kavanagh, D. F., “Electric propulsion methods for small satellites: A review,”Aerospace, Vol. 8, No. 1, 2021, p. 22

2021

[23] [23]

A study on simultaneous design of a Hall effect thruster and its low-thrust trajectory,

Kwon, K., Lantoine, G., Russell, R. P., and Mavris, D. N., “A study on simultaneous design of a Hall effect thruster and its low-thrust trajectory,”Acta Astronautica, Vol. 119, 2016, pp. 34–47

2016

[24] [24]

Radiation Effects and COTS Parts in SmallSats,

Sinclair, D., and Dyer, J., “Radiation Effects and COTS Parts in SmallSats,”Small Satellite Conference, Logan, Utah, USA, 2013, p. 12. URL https://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=2934&context=smallsat

2013

[25] [25]

RecommendationsonUseofCommercial-Off-The-Shelf (COTS) Electrical, Electronic, and Electromechanical (EEE) Parts for NASA Missions,

Hodson, R. F., Chen, Y., Pandolf, J. E., Ling, K., Boomer, K. T., Green, C. M., Leitner, J. A., Majewicz, P., Gore, S. H., Faller, C.S.,Denson,E.C.,Hodge,R.E.,Thoren,A.P.,andDefrancis,M.A.,“RecommendationsonUseofCommercial-Off-The-Shelf (COTS) Electrical, Electronic, and Electromechanical (EEE) Parts for NASA Missions,” Tech. Rep. NESC-RP-19-01490, Dec

[26] [26]

URL https://ntrs.nasa.gov/citations/20205011579

arXiv

[27] [27]

Decadal, S. o. A. a. A. . A., Space Studies Board, Board on Physics and Astronomy, Division on Engineering and Physical Sciences, and National Academies of Sciences, Engineering, and Medicine,Pathways to Discovery in Astronomy and Astrophysics for the 2020s, National Academies Press, Washington, D.C., 2021. https://doi.org/10.17226/26141, URL https://www....

work page doi:10.17226/26141 2021

[28] [28]

Maximizing the ExoEarth candidate yield from a future direct imaging mission,

Stark, C. C., Roberge, A., Mandell, A., and Robinson, T. D., “Maximizing the ExoEarth candidate yield from a future direct imaging mission,”The Astrophysical Journal, Vol. 795, No. 2, 2014, p. 122

2014

[29] [29]

How the Habitable Worlds Observatory’s field of regard will impact the use of precursor science,

Spohn, C., Stark, C., and Savransky, D., “How the Habitable Worlds Observatory’s field of regard will impact the use of precursor science,”Space Telescopes and Instrumentation 2024: Optical, Infrared, and Millimeter Wave, Vol. 13092, SPIE, 2024, pp. 1869–1881

2024

[30] [30]

Transiting Exoplanet Survey Satellite (TESS) flight dynamics commissioning results and experiences,

Parker, J. J. K., Lebois, R. L., Lutz, S., Nickel, C., Ferrant, K., and Michaels, A., “Transiting Exoplanet Survey Satellite (TESS) flight dynamics commissioning results and experiences,”AAS GUIDANCE & CONTROL CONFERENCE, 2018. URL https://ntrs.nasa.gov/api/citations/20180006156/downloads/20180006156.pdf

arXiv 2018

[31] [31]

James webb space telescope trajectory, communications, and instrumentation comprehensive analysis,

Llanos, P. J., and Matas, A., “James webb space telescope trajectory, communications, and instrumentation comprehensive analysis,”In 2022 AAS/AIAA Astrodynamics Specialist Conference. AAS/AIAA. AAS Paper 22–623, August 2022. Charlotte, NC, 2022

2022

[32] [32]

Targeting cislunar near rectilinear halo orbits for human space exploration,

Williams, J., Lee, D. E., Whitley, R. J., Bokelmann, K. A., Davis, D. C., and Berry, C. F., “Targeting cislunar near rectilinear halo orbits for human space exploration,”AAS/AIAA Space Flight Mechanics Meeting, 2017

2017

[33] [33]

Methodology,

Parker, J. S., and Anderson, R. L., “Methodology,”Low-Energy Lunar Trajectory Design, John Wiley & Sons, Ltd, 3 June 2014, 2014, pp. 27–115. https://doi.org/10.1002/9781118855065.ch2, URL https://onlinelibrary.wiley.com/doi/abs/10.1002/ 9781118855065.ch2

work page doi:10.1002/9781118855065.ch2 2014

[34] [34]

Transfers to Lunar Libration Orbits,

Parker, J. S., and Anderson, R. L., “Transfers to Lunar Libration Orbits,”Low-Energy Lunar Trajectory Design, John Wiley & Sons, Ltd, 2014, Chap. 3, pp. 117–226. https://doi.org/https://doi.org/10.1002/9781118855065.ch3, URL https: //onlinelibrary.wiley.com/doi/abs/10.1002/9781118855065.ch3

work page doi:10.1002/9781118855065.ch3 2014

[35] [35]

Representations of invariant manifolds for applications in three-body systems,

Howell, K., Beckman, M., Patterson, C., and Folta, D., “Representations of invariant manifolds for applications in three-body systems,”The Journal of the Astronautical Sciences, Vol. 54, No. 1, 2006, pp. 69–93

2006

[36] [36]

JWST Data Volume and Data Excess - JWST User Documentation,

“JWST Data Volume and Data Excess - JWST User Documentation,” , ???? URL https://jwst-docs.stsci.edu/jwst-general- support/jwst-data-volume-and-data-excess#gsc.tab=0. 20

[37] [37]

EXOSIMS: Exoplanet Open-Source Imaging Mission Simulator,

Savransky, D., Delacroix, C., and Garrett, D., “EXOSIMS: Exoplanet Open-Source Imaging Mission Simulator,” , 2017. Ascl:1706.010

2017

[38] [38]

ExoPAG SAG13: Exoplanet Occurrence Rates and Distributions,

ExoPAG Study Analysis Group 13 (SAG13), “ExoPAG SAG13: Exoplanet Occurrence Rates and Distributions,” Tech. rep., NASA Exoplanet Exploration Program Analysis Group (ExoPAG), 2017. URL https://science.nasa.gov/wp-content/uploads/ 2023/04/SAG13_closeout.pdf

2017

[39] [39]

JPL HORIZONS On-Line Ephemeris System,

Giorgini, J. D., “JPL HORIZONS On-Line Ephemeris System,” https://ssd.jpl.nasa.gov/horizons/, 2024. NASA Jet Propulsion Laboratory, Solar System Dynamics Group

2024

[40] [40]

The calculation of proton penetration and dose rates - NASA Technical Reports Server (NTRS),

Burrell, M. O., “The calculation of proton penetration and dose rates - NASA Technical Reports Server (NTRS),” Technical Report 19650025029, NASA Marshall Space Flight Center, Huntsville, Alabama, Jan. 1965. URL https://ntrs.nasa.gov/ citations/19650025029

arXiv 1965

[41] [41]

Average depths of electron penetration: use as characteristic depths of exposure,

Lazurik, V., Moskvin, V., and Tabata, T., “Average depths of electron penetration: use as characteristic depths of exposure,” IEEE Transactions on Nuclear Science, Vol. 45, No. 3, 1998, pp. 626–631

1998

[42] [42]

The Roman coronagraph community participation program: observation planning,

Wolff, S. G., Wang, J., Stapelfeldt, K., Bailey, V. P., Savransky, D., Hom, J., Biller, B., Brandner, W., Anche, R., Blunt, S., Brinjikji, M., Girard, J. H., Krause, O., Li, Z., Livingston, J., Millar-Blanchaer, M. A., Noel, M., Pueyo, L., De Rosa, R. J., Samland, M., and Schragal, N., “The Roman coronagraph community participation program: observation pl...

work page doi:10.1117/12.3020205 2024