NASA is studying a possible starshade flying in formation with the Nancy Grace Roman Space Telescope (Roman). The starshade would perform weeks-long translational retargeting maneuvers between target stars. A retargeting architecture that is based on chemical propulsion and does not require ground tracking or interactions with the telescope during the retargeting cruise is introduced. Feasibility is demonstrated through a covariance analysis of the starshade-telescope relative position over several weeks using realistic sensor and actuator assumptions. Performance is sufficient for Roman to reacquire the starshade after retargeting, and the architecture is shown to be applicable to other mission concepts such as the Habitable Exoplanet Observatory (HabEx). Results are verified through high-fidelity simulations, and driving sources of uncertainty are identified to confirm the robustness of the approach.
KEYWORDS: Telescopes, Error analysis, Sensors, Space operations, Monte Carlo methods, Sun, Control systems, Stars, Infrared telescopes, Filtering (signal processing)
Several starshade concepts for imaging exo-Earths would operate at the second Earth–Sun Lagrange point (L2) and consist of a starshade flying in formation tens to hundreds of thousands of kilometers from a telescope. The starshade would need to maintain meter-level lateral alignment with the line of sight from telescope to target star. A companion paper describes an optical sensing scheme using a pupil imaging camera in the telescope that can sense the relative lateral position to a few centimeters. A full flight-traceable formation flying framework that leverages this sensor is presented. In particular, a two-dimensional “disk deadbanding” algorithm is introduced for lateral control. The framework also maximizes the drift time between thruster burns to reduce interruption to scientific observations. The main sources of uncertainty affecting the control performance are compared, and it is found that spacecraft mass uncertainty is a driving factor. The formation flying environment is also analyzed to identify conditions that lead to worst-case differential gravity and solar radiation pressure disturbances. Finally, for a representative observation scenario with the Wide Field Infrared Space Telescope, this control system is tested through Monte Carlo simulations. The results show robust meter-level control with essentially optimal drift time between thruster burns.
A key challenge for starshades is formation flying. To successfully image exoplanets, the telescope boresight and starshade must be aligned to ∼1 m at separations of tens of thousands of kilometers. This challenge has two parts: first, the relative position of the starshade with respect to the telescope must be sensed; second, sensor measurements must be combined with a control law to keep the two spacecraft aligned in the presence of gravitational and other disturbances. In this work, we present an optical sensing approach using a pupil imaging camera in a 2.4-m telescope that can measure the relative spacecraft bearing to a few centimeters in 1 s, much faster than any relevant dynamical disturbances. A companion paper will describe how this sensor can be combined with a control law to keep the two spacecraft aligned with minimal interruptions to science observations.
This paper provides an overview of technology development for the Terrestrial Planet Finder Interferometer (TPF-I). TPF-I is a mid-infrared space interferometer being designed with the capability of detecting Earth-like planets in the habitable zones around nearby stars.
Exo-S is a direct imaging space-based mission to discover and characterize exoplanets. With its modest size, Exo-S bridges the gap between census missions like Kepler and a future space-based flagship direct imaging exoplanet mission. With the ability to reach down to Earth-size planets in the habitable zones of nearly two dozen nearby stars, Exo-S is a powerful first step in the search for and identification of Earth-like planets. Compelling science can be returned at the same time as the technological and scientific framework is developed for a larger flagship mission. The Exo-S Science and Technology Definition Team studied two viable starshade-telescope missions for exoplanet direct imaging, targeted to the $1B cost guideline. The first Exo-S mission concept is a starshade and telescope system dedicated to each other for the sole purpose of direct imaging for exoplanets (The "Starshade Dedicated Mission"). The starshade and commercial, 1.1-m diameter telescope co-launch, sharing the same low-cost launch vehicle, conserving cost. The Dedicated mission orbits in a heliocentric, Earth leading, Earth-drift away orbit. The telescope has a conventional instrument package that includes the planet camera, a basic spectrometer, and a guide camera. The second Exo-S mission concept is a starshade that launches separately to rendezvous with an existing on-orbit space telescope (the "Starshade Rendezvous Mission"). The existing telescope adopted for the study is the WFIRST-AFTA (Wide-Field Infrared Survey Telescope Astrophysics Focused Telescope Asset). The WFIRST-AFTA 2.4-m telescope is assumed to have previously launched to a Halo orbit about the Earth-Sun L2 point, away from the gravity gradient of Earth orbit which is unsuitable for formation flying of the starshade and telescope. The impact on WFIRST-AFTA for starshade readiness is minimized; the existing coronagraph instrument performs as the starshade science instrument, while formation guidance is handled by the existing coronagraph focal planes with minimal modification and an added transceiver.
In conjunction with a space telescope of modest size, a starshade enables observation of small exoplanets close to the parent star by blocking the direct starlight while the planet light remains unobscured. The starshade is flown some tens of thousands of kilometers ahead of the telescope. Science instruments may include a wide field camera for imaging the target exoplanetary system as well as an integral field spectrometer for characterization of exoplanet atmospheres. We show the preliminary designs of the optical instruments for observatories such as Exo-S, discuss formation flying and control, retargeting maneuvers and other aspects of a starshade mission. The implementation of a starshade-ready WFIRST-AFTA is discussed and we show how a compact, standalone instrument package could be developed as an add-on to future space telescopes, requiring only minor additions to the telescope spacecraft.
KEYWORDS: Nulling interferometry, Planets, Interferometers, Space operations, Mirrors, Robots, Control systems, Stars, Space telescopes, Interferometry
The last decade has seen great advances in interferometric nulling technology, propelled at first by the SIM and KECK
nulling programs and then by the Terrestrial Planet Finder Interferometer (TPF-I). In the infrared at N-band (using a CO2
laser at 10.6 micron wavelength) the first million to one nulls were reported on a KECK testbed in 2003. For TPF-I,
nulls needed to be both deep and broadband, and a suite of testbeds was designed and built to study all aspects of
achromatic nulling and system implementation, including formation flying technology. Also, observatory designs were
drawn up and studied against performance models. Modeling revealed that natural variations in the alignment and
control of the optical system produced an "instability noise" signal and this realization eventually led to a redesign of the
layout to a rectangular formation. The complexity of the early TPF-I spacecraft design was mitigated by the infusion of
ideas from Europe and produced the current X-Array design which utilizes simple reflectors to form the apertures
together with a stretched three dimensional formation geometry. This paper summarizes the main achievements of the
infrared nulling technology program including the development of adaptive nulling for broadband performance and the
demonstration of starlight suppression by 100 million to one.
This paper provides an overview of technology development for the Terrestrial Planet Finder Interferometer
(TPF-I). TPF-I is a mid-infrared space interferometer being designed with the capability of detecting Earth-like
planets in the habitable zones around nearby stars. The overall technology roadmap is presented and progress
with each of the testbeds is summarized.
Initial high-fidelity, flight-like ground demonstrations of precision formation flying spacecraft are presented. In
these demonstrations, maneuvers required for distributed spacecraft interferometry, such as for the Terrestrial
Planet Finder Interferometer, were performed to near-flight precision. Synchronized formation rotations for
"on-the-fly" observations require the highest precision. For this maneuver, ground demonstration performance
requirements are 5 cm in relative position and 6 arc minutes in attitude. These requirements have been met for
initial demonstrations of formation-keeping and synchronized formation rotations.
The maneuvers were demonstrated in the Formation Control Testbed (FCT). The FCT currently consists
of two, five degree-of-freedom, air bearing-levitated robots. The final sixth degree-of-freedom is being added in
August 2007. Each robot has a suite of flight-like avionics and actuators, including a star tracker, fiber-optic
gyroscopes, reaction wheels, cold-gas thrusters, inter-robot communication, and on-board computers that run
the Formation and Attitude Control System (FACS) software.
The FCT robots and testbed environment are described in detail. Then several initial demonstrations results
are presented, including (i) a sub-millimeter formation sensor, (ii) an algorithm for synchronizing control cycles
across multiple vehicles, (iii) formation keeping, (iv) reactive collision avoidance, and (iv) synchronized formation
rotations.
This paper provides an overview of technology development for the Terrestrial Planet Finder Interferometer
(TPF-I). TPF-I is a mid-infrared space interferometer being designed with the capability of detecting Earth-like
planets in the habitable zones around nearby stars. The overall technology roadmap is presented and progress
with each of the testbeds is summarized. The current interferometer architecture, design trades, and the viability
of possible reduced-scope mission concepts are also presented.
A novel space interferometer design originating in Europe has been studied. The interferometer uses the technique of
starlight nulling to enable detection of earth-like planets orbiting nearby stars. A set of four telescope spacecraft flying in
formation with a fifth, beam-combiner spacecraft forms the interferometer. This particular concept shows potential for
reducing the mission cost when compared with previous concepts by greatly reducing the complexity of the telescope
spacecraft. These spacecraft have no major deployable systems, have simplified propulsion and a more rugged
construction. The formation flying geometry provides for greater average separation between the spacecraft with
commensurate risk reduction. Key aspects of the design have been studied at the Jet Propulsion Laboratory with a view
to collaborations between NASA and the European Space Agency. An overview of the design study is presented with
some comparisons with the TPF-FFI concept.
This paper reviews recent progress with technology being developed for the Terrestrial Planet Finder Interferometer (TPF-I). TPF-I is a mid-infrared space interferometer being designed with the capability of detecting Earth-like planets in the habitable zones around nearby stars. TPF-I is in the early phase of its development. The science requirements of the mission are described along with the current design of the interferometer. The goals of the nulling and formation-flying testbeds are reviewed. Progress with TPF-I technology milestones are highlighted.
Distributed spacecraft flying in formation can overcome the
resolution limitations of monolithic, Earth-sensing systems.
However, formation spacecraft must now expend fuel to counteract
disturbances and the gravity gradients between spacecraft. We
consider three different formation architectures and determine the
delta-v required to maintain relative positions at accuracies
ranging from 0.1 to 10 m (1 sigma). The three architectures
considered are: (i) Leader/Follower, in which individual
spacecraft controllers track with respect to a passive, leader
spacecraft, (ii) Center of Formation, in which individual
spacecraft controllers track with respect to the geometric center
of the formation, and (iii) Iterated Virtual Structure, in which
a formation template is fit each timestep and individual
spacecraft controllers track with respect to the fitted template.
We show that in the presence of relative and inertial sensor noise
and disturbances (e.g., Earth oblateness and aerodynamic drag) relative positions can be maintained to the 10 m level for 4
mm/s/orbit.
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