Centauri Dreams
Imagining and Planning Interstellar Exploration
New Horizons: A ‘Timing Flaw’ Scare Resolved
You get to expect the unexpected when writing about space probes, but somehow what New Horizons did to my weekend completely blind-sided me. Running a routine check of email before (I thought) sliding into the rest of a relaxing work break, I found messages about the glitch on the Pluto-bound spacecraft. Sunday turned into an all-screens-on exercise in checking multiple feeds and waiting for news.
The problem with New Horizons brought to mind a short story I wrote many years ago about an unmanned probe sent to Epsilon Indi on a 90-year journey. The probe is within a month of encounter when all goes silent and Earth controllers can only wait to see what happens.
The point of the story (it was called “Merchant Dying,” published in Charlie Ryan’s Aboriginal Science Fiction in the July/August 1987 issue) was that spacecraft going to another star are going to need autonomous repair capabilities we can only dream of today. New Horizons is a long way out, but we can still work with it through the Deep Space Network, and a check this morning shows DSN’s 70-meter Canberra dish working New Horizons as I write. But space is teaching us all about backup computers and autonomy one step at a time.
The ‘anomaly’ occurred on July 4 and led to a loss of communications with Earth. New Horizons’ autonomous systems were able to switch to the critical backup computer while placing the spacecraft in ‘safe mode’ and re-starting communications. Emily Lakdawalla reports here that the New Horizons Anomaly Review Board met at 1600 EDT yesterday to analyze the situation. The subsequent NASA statement was reassuring, and I’ll quote its latest update in its entirety:
NASA’s New Horizons mission is returning to normal science operations after a July 4 anomaly and remains on track for its July 14 flyby of Pluto.
The investigation into the anomaly that caused New Horizons to enter “safe mode” on July 4 has concluded that no hardware or software fault occurred on the spacecraft. The underlying cause of the incident was a hard-to-detect timing flaw in the spacecraft command sequence that occurred during an operation to prepare for the close flyby. No similar operations are planned for the remainder of the Pluto encounter.
“I’m pleased that our mission team quickly identified the problem and assured the health of the spacecraft,” said Jim Green, NASA’s Director of Planetary Science. “Now – with Pluto in our sights – we’re on the verge of returning to normal operations and going for the gold.”
Preparations are ongoing to resume the originally planned science operations on July 7 and to conduct the entire close flyby sequence as planned. The mission science team and principal investigator have concluded that the science observations lost during the anomaly recovery do not affect any primary objectives of the mission, with a minimal effect on lesser objectives. “In terms of science, it won’t change an A-plus even into an A,” said New Horizons Principal Investigator Alan Stern of the Southwest Research Institute, Boulder.
Adding to the challenge of recovery is the spacecraft’s extreme distance from Earth. New Horizons is almost 3 billion miles away, where radio signals, even traveling at light speed, need 4.5 hours to reach home. Two-way communication between the spacecraft and its operators requires a nine-hour round trip.
Status updates will be issued as new information is available.
So we’re less than ten days out from Pluto/Charon and a knuckle-whitening moment seems to have passed with little loss of data. With observations re-starting on Tuesday, here’s imagery from July 1, with the inset showing an enlarged Pluto. Features as small as 160 kilometers are visible at this point (credit: NASA/JHUAPL/SWRI). Onward and outward…
Update: More news this afternoon, as per NASA:
NASA will host a media teleconference at 3 p.m. EDT (19:00 UTC) today to discuss the New Horizons spacecraft returning to normal science operations after a July 4 anomaly. The mission remains on track to conduct the entire close flyby sequence as planned, including the July 14 flyby of Pluto…
Audio of the teleconference will be streamed live at http://www.nasa.gov/newsaudio
The Spacecoach Equation
My view is that the spacecoach, the subject of renewed discussion below by Brian McConnell and a design he and Alex Tolley have created, is the most innovative and downright practical idea for getting crews and large payloads to the planets that I’ve yet encountered. It’s low-cost and uses ordinary consumables as propellant, dramatically revising mission planning. Brian and Alex have continued refining the concept, as explained below in Brian’s essay on a modified version of the rocket equation. Have a look and you’ll see that planning long duration missions or missions with larger crews becomes a much more workable proposition because more consumables translate into more propellant. Could the spacecoach be our ticket to building a space-based infrastructure, with unmistakable implications for even deeper space?
by Brian S McConnell
The spacecoach, first introduced here in Spaceward Ho! and A Stagecoach To The Stars and on spacecoach.org, is based on the idea of using consumables waste streams, such as water, CO2 and gasified waste, as propellant in solar powered electric engines. The idea is to turn what is normally dead weight (and a lot of dead weight on a long duration mission such as to Mars) into propellant. This in turn leads to dramatic reductions in mass, and thus mission cost, because a ship that uses waste from consumables as propellant no longer needs an external stage weighing several times as much to push it to its destination. (If you or your colleagues are working on electric propulsion systems and have test data and citations to share see below)
Image: The spacecoach. Credit: Rendering by Rüdiger Klaehn based on a design by Brian McConnell.
To understand the impact this has, we developed a modified version of the rocket equation that leads with the crew consumable requirements for a given mission, and then calculates the level of engine performance required to fly the mission using only consumables waste streams (mostly water and carbon dioxide) as propellant. This, in turn, yields a minimum mission cost, as no surplus propellant is required, so the mission cost is reduced to the cost to deliver the crew and consumables to the starting point (while the ship itself is reusable so its construction and launch cost can be amortized across many missions).
The rocket equation, shown below, predicts the ship’s delta-v (change in velocity), as a function of specific impulse (a measure of engine performance) and the ship’s mass ratio (starting mass divided by ending mass).
The spacecoach equation, shown below, predicts the minimum exhaust velocity (or specific impulse) required for a cost optimized mission as a function of its delta v and consumables budget.
For programmers, this can also be written in pseudocode as:
Let’s consider a ship that has a 40,000 kg hull mass when empty that is being resupplied for a trip to the Martian moons from EML-2 (Earth Moon Lagrange point 2). With low thrust propulsion this requires a delta-v of roughly 18 km/s roundtrip. The ship has a six person crew, with a 15 kg/person-day budget for water, food and oxygen. The mission is expected to last 600 days, so the consumables budget is 54,000kg.
According to the equation, the engines will need to achieve an exhaust velocity of 21 km/s, which equates to a specific impulse of about 2,100s, assuming 100% of the waste streams are reclaimed (if engines can be made to work with gasified waste, even solids such as trash should be usable as propellant). If we assume that some percentage of the consumables waste streams (e.g. solid waste) cannot be used, say 20%, the engines will need to operate at a specific impulse of 2,900s. This is within the performance envelope of Hall effect thrusters, as well as several other electric propulsion technologies. If the engine performance is not quite good enough, that’s ok, the ship would just be loaded with more water than the crew really needs to compensate for this, or could even support a larger crew. This will increase costs a bit above the minimum possible cost, but also provide safety reserves above what the crew is projected to need.
Next, let’s compare the mass budget for a similar ship using chemical propulsion (e.g. LOX + methane). This mission requires much less delta-v as the ship can exploit the Oberth effect (aka powered flyby) when departing Earth, and on arrival at Mars. To give the chemical ship a further advantage, we’ll assume it uses aerobraking for Mars capture and for Earth return. So the round trip delta-v in that scenario is roughly 8 km/s. The downside is the engine specific impulse is much lower, about 360s for oxygen + methane. Plugging this into the rocket equation results in a propellant mass budget of almost 820,000 kg, over twenty times the mass of the empty hull. This can be optimized by shedding mass, such as waste, spent stages, etc, but not by a great deal without making compromises in terms of consumables, payload, etc (and we’ve already given the chemical ship a big advantage by assuming it can use aerobraking extensively to minimize propulsive delta-v).
Compare this with the spacecoach, where the consumables are the propellant. It would require the delivery of only 54,000 kg of consumables. This is 1/15th what is required for the conventional mission, and should lead to comparable reductions in overall mission costs. Meanwhile the mission itself is much simpler and less risky (all low thrust propulsion, no chemical rockets with catastrophic failure modes, no high G maneuvers, no aerobraking, plus the option to add more crew and/or consumables with little penalty).
The savings come from two sources. Because the consumables are the propellant, there is no need for external propellant. This effect is amplified further because electric engines have much higher exhaust velocities than chemical rockets so even the relatively small consumables mass needed by the crew is sufficient to propel the ship (if electric engines operated at a specific impulse comparable to a chemical rocket, you’d need ten times more water than the crew would consume).
And it gets even better. This is counterintuitive, but it is actually easier to plan for long duration missions with larger crews and high delta v (Ceres, Venus and the Asteroid Belt for example). This is because more consumables = more propellant = higher delta-v given the same engine performance, whereas in a conventional ship you get into a vicious circle of mass incurring more mass. Running the numbers for a 6 person, 1000 day mission to Ceres (delta v : 26.5 km/s roundtrip from EML-2), the consumables budget is 90,000 kg, and the required engine specific impulse is again in the 2000s, which suggests that a ship capable of reaching Mars will be capable of reaching Ceres due to the larger consumables budget.
And speaking of Ceres, it is an enormous water reservoir. While early spacecoaches would be supplied entirely from the Earth, developing the ability to extract water from low gravity sites like Ceres, and possibly the Martian moons, will be a priority as it will reduce the need to launch water from Earth, and thus further reduce operating costs, but even without in situ resource utilization, spacecoaches will be an order of magnitude cheaper to operate, and will be capable of reaching destinations like Ceres that simply cannot be reached by humans using chemical propulsion.
While it takes people a while to see the implications of this (the thinking about how to design a spacecraft is pretty ingrained), the math is pretty straightforward and suggests that order of magnitude cost reductions for interplanetary missions, with greatly expanded range, will be possible with this approach.
If you are working on electric propulsion technology, we are compiling data about the relative performance of different technologies and propellants, especially as it relates to the use of water and waste gases, to provide the community with an easy to search repository of SEP test data and citations. This data will be made available at spacecoach.org as well as on github. If you’d like to submit test data and citations, you can use this form. Contact Brian McConnell at bsmcconnell@gmail.com for more information.
Thoughts on DE-STAR and Laser Sailing
Last week we looked at DE-STAR (Directed Energy Solar Targeting of Asteroids and Exploration), an ambitious program for developing modular phased arrays of kilowatt class lasers. The work of Philip Lubin (UC-Santa Barbara), DE-STAR is envisioned as a way to scale up a space-based system for asteroid mitigation. And in a new NIAC grant, Lubin will study an off-shoot called Directed Energy Propulsion for Interstellar Exploration (DEEP-IN) as a way of driving tiny ‘wafer’ probes on interstellar journeys. Reading about these ideas, Jim Benford responded with the comments below. A plasma physicist and president of Microwave Sciences (Lafayette, CA), Dr. Benford’s work on microwave beaming to sailcraft has included laboratory experiments at JPL with brother Greg that I’ve written about in these pages. Here are his thoughts on DE-STAR’s beaming methods and the issues they invoke.
by James Benford
The calculations presented by the DE-STAR group are basically a revisit of the work of Bob Forward, which was published over 30 years ago. Several other workers have formulated beam-driven sail scaling in the past, so this new group is revisiting that work.
From inspection of their papers, it appears that the DE-STAR group is producing concepts for very low mass, fast sailship probes using a method several others have explored previously: They get very small, light probes by putting all the effort into making them small, at the expense of having an enormous beaming aperture. The very large aperture is not emphasized in their papers, but the smallness of the sail is.
The “realistic” DE-STAR 4 design, for example, has an aperture of 10 km on a side. So the aperture is 330 times larger in linear dimension than the sail, 100,000 times larger in area.
Looking at it from the point of view of cost, such designs are far more expensive than alternatives where the aperture and sail are not so very different in size. (Beamer system cost scales inversely with the sail area.) So the choice of very large aperture drives the capital cost of the system very high; I estimate between 10 and 100 trillion dollars, depending on economies of scale. The operating cost is low because the required power is lower. I would recommend that the DE-STAR group look at cost-optimized methods, which are much more realistic and therefore much more likely to be built.
Image: Testing carbon sails at JPL. Here a carbon disk sail lifts off of a truncated rectangular waveguide under 10 kW microwave power (four frames, 30 ms interval, first at top). Credit: James and Gregory Benford.
Another problem with small sails is that if you do try to launch all of them simultaneously as a constellation, on a beam much larger than a single sail, the sails will not ride on the beam. They will drift off to the side due to perturbations. There are an extensive series of papers on the program I managed in sail acceleration, spin and stability from 1999 to 2005 (two of these are listed below). They describe beam-riding analytically, computationally and experimentally.
Image: Carbon-carbon sail used in sail stability and spin experiments. SAIL diameter is 5 cm, height 2 cm, mass 0.056 gm. Experiments and simulations show that such conical sails can ride a microwave beam very stably. Credit: James Benford.
So it’s a pretty solid understanding, based on internal reflections on the underside of the sail, as follows:
- The sail must be non-flat, with a conical cone the best shape with the apex pointing away from the beam;
- The diameter of the sail must be of the same order as the transverse dimensions of the beam; and
- Spin helps stabilize beam-riding craft.
This cannot be avoided or all is lost — the sail tumbles. For more, see:
“Stability and Control of Microwave Propelled Sails in 1-D”, Chaouki T. Abdalla, Edl Schamiloglu, James Benford and Gregory Benford, Proc. Space Technology and Applications International Forum (STAIF-2001), Space Exploration Technology Conf, AIP Conf. Proc. 552, ISBN 1-56396-980-7STAIF, pg. 552, (2001).
“Experimental Tests Of Beam-Riding Sail Dynamics”, Gregory Benford, Olga Goronostavea and James Benford, Beamed Energy Propulsion, AIP Conf. Proc. 664, pg. 325, A. Pakhomov, ed., 2003.
Methane Detection as New Horizons Closes
As I write, we’re thirteen and a half days out from the Pluto/Charon encounter. New Horizons will make its closest approach to Pluto at 0749 EDT (1149 UTC) on July 14. All of which has had me reading Pluto-related science fiction that I missed along the way, including most recently Wilson Tucker’s “To the Tombaugh Station.” The story, which ran in the July, 1960 issue of Fantasy and Science Fiction, is a murder investigation that includes a journey to the station of the title, which had been established to investigate a ‘Planet X’ still further out in the system. Isaac Asimov has an essay on Pluto in this issue as well.
Image: The cover of the July, 1960 Fantasy and Science Fiction shows a generic moon landing scene by artist Mel Hunter. But if you look at it with our post-1978 (discovery of Charon) eyes, it could be seen as an imaginative take on a Pluto landing, with the Earth on the horizon being replaced by Charon. Given the prominence of “To the Tombaugh Station” on the cover, I found myself doing a double-take.
As to the real Pluto, we now learn that the infrared spectrometer on New Horizons has detected frozen methane on the surface, a compound first observed on the dwarf planet as early as 1976. What New Horizons will bring to the table is the chance to study differences in methane ice from one part of the surface to another. According to this NASA news release, Dale Cruikshank (NASA Ames, and a member of the New Horizons team) led the team of ground-based astronomers that made the original methane detection.
Image: The location of the New Horizons Ralph instrument, which detected methane on Pluto, is shown. The inset is a false color image of Pluto and Charon in infrared light; pink indicates methane on Pluto’s surface. Credit: NASA/Johns Hopkins Applied Physics Laboratory/Southwest Research Institute.
I hope you’re taking advantage of the fact that the raw images from New Horizons are being made available on the JHU/APL website. There you can see images from the spacecraft’s Long Range Reconnaissance Imager (LORRI) displayed without special processing. They’re posted within about 48 hours after coming in to the New Horizons Science Operations Center.
And below is the latest time-lapse movie, this one showing changes in the apparent size of Pluto and Charon as the spacecraft moves from 56 million kilometers to 22 million kilometers. The images involved in this time-lapse approach movie were taken between May 28 and June 25. Pluto continues to show a surface marked by a bright northern hemisphere, with darker material in a discontinuous band along the equator. It’s exciting to see differences emerging on Charon as well, along with the previously noted dark polar region.
The short video below is an annotated version of the above in which Pluto’s prime meridian (the region of the planet that faces Charon) is shown in yellow and the equator is shown in pink.
New Horizons’ Alice ultraviolet imaging spectrograph performed a test observation of the Sun on June 16 (this from a distance of 5 billion kilometers) to use in the interpretation of atmospheric observations to be taken on July 14. On that day, not long after the Pluto flyby, the spacecraft will study sunlight as it passes through Pluto’s atmosphere. New Horizons scientist Randy Gladstone (SwRI) puts it well: “It will be as if Pluto were illuminated from behind by a trillion-watt light bulb.” That backlight will tell us much about the atmosphere’s composition.
A thruster burn beginning at 1101 EDT (1501 UTC) on June 29, stopping 23 seconds later, was used to make the smallest of the nine course corrections since the spacecraft’s launch in 2006. New Horizons changed velocity by 27 centimeters per second, making a slight adjustment to its arrival time and position at close approach and flyby. The difference upon arrival: The craft would have reached close approach 20 seconds late without the burn, and 184 kilometers off-target.
“This maneuver was perfectly performed by the spacecraft and its operations team,” added mission principal investigator Alan Stern, of Southwest Research Institute, Boulder, Colorado. “Now we’re set to fly right down the middle of the optimal approach corridor.”
A Disruptive Pathway for Planet Formation
Planet formation can be tricky business. Consider that our current models for core accretion show dust grains embedded in a protoplanetary disk around a young star. Mixing with rotating gas, the dust undergoes inevitable collisions, gradually bulking up to pebble size, then larger. As the scale increases, we move through to planetesimals, bodies of at least one kilometer in size, which are large enough to attract each other gravitationally. Some planetesimals break apart through subsequent collisions, but a few grow into protoplanets, then planets themselves.
It’s a reasonable theory that fits what we see around young stars as solar systems take hold. But what Alan Boss (Carnegie Institution for Science) has been working on is a question raised by the process: How do the dust grains and objects smaller than planetesimals keep from being drawn into the protostar before they can become large enough to attract the materials they need to grow? The pressure gradient of the gas in the disk should make smaller objects — particularly those between 1 and 10 meters in radius — spiral inward to inevitable destruction.
By modeling the interactions between protoplanetary disks and their stars, however, Boss has come up with a proposed solution. Stars like the Sun can undergo explosive bursts of a century or so in duration, accompanied by an increase in the luminosity of the star. An explosive phase like this, which Boss’s paper argues can be linked to a period of gravitational instability in the disk, can scatter objects in the 1 to 10-meter range outward from the infant star.
Image: An artist’s concept showing a young stellar object and the whirling accretion disk surrounding it. Credit: NASA/JPL-Caltech.
The paper refers to the disruptions of the disk under scrutiny as ‘marginally gravitationally unstable phases of evolution’ (MGU), but they’re more widely known as ‘FU Orionis events.’ The star FU Orionis is a pre-main sequence star showing just this range of fluctuation in magnitude. It has given its name to the entire class, with other examples being V1057 Cyg and V1647 Orionis. We’re apparently seeing mass from an accretion disk falling into the young star, creating a high-luminosity phase that can persist for lengthy periods.
It has been suggested that eruptions like these can occur from 10 to 20 times as a young star matures. The event is, in any case, striking when it occurs. When V1057 Cyg was first observed undergoing this behavior in 1970, it increased in brightness by 5.5 magnitudes (going from 17th magnitude to 12th) over a multi-year interval. But we have a lot to learn. No FU Orionis star has yet been seen shutting down from its high-luminosity phase. Mike Simonsen provides an excellent background discussion of FU Orionis stars in The Furor over FUORs.
Boss modeled protoplanetary disks undergoing FU Orionis events for disks at 1 to 10 AU containing a wide variety of solid particle sizes subject to gas drag and gravitational forces. Backing up this model of gravitational interaction, recent work has shown that young stars can form spiral arms in their disks like those thought to be involved in the disruptive events Boss has studied. The gravitational forces produced by these spiral arms may be the key to scattering boulder-sized bodies so that they can survive gas drag and grow into planetesimals.
Larger bodies, then, have a chance to survive. Boss’ models showed that over time scales of ~6 X 103 years or longer, about half the gaseous disk mass was accreted onto the protostar, but during this same period, few objects between 1 and 10 meters were lost through inward migration. A much greater fraction of particles between 1 and 10 centimeters were lost to the protostar during the same period, but even here, a significant fraction survive.
“This work,” Boss adds, “shows that boulder-sized particles could, indeed, be scattered around the disk by the formation of spiral arms and then avoid getting dragged into the protostar at the center of the developing system. Once these bodies are in the disk’s outer regions, they are safe and able to grow into planetesimals. While not every developing protostar may experience this kind of short-term gravitational disruption phase, it is looking increasingly likely that they may be much more important for the early phases of terrestrial planet formation than we thought.”
The paper is Boss, “Orbital Survival of Meter-size and Larger Bodies During Gravitationally Unstable Phases of Protoplanetary Disk Evolution,” Astrophysical Journal Vol. 807 (July 1, 2015), No. 1, 10 (abstract).
A Planet Reborn?
Objects that seem younger than they ought to be attract attention. Take the so-called ‘blue stragglers.’ Found in open or globular clusters, they’re more luminous than the cluster stars around them, defying our expectation that stars that formed at about the same time should develop consistent with their neighbors. Allan Sandage discovered the first blue stragglers back in 1953 while working on the globular cluster M3. Because blue stragglers are more common in the dense core regions of globular clusters, they may be binary stars that have merged, but a number of theories exist, most of them focusing on interactions within a given cluster.
Image: The center of globular cluster NGC 6397, in an image taken by the Hubble Space Telescope. Credit: Francesco Ferraro (Bologna Observatory), ESA, NASA.
Now we may have found a planet that seems to be younger than it ought to be. Michael Jura (UCLA) and team report on the results in the Astrophysical Journal Letters, making the case that a planet orbiting an aging red giant may feed off mass flowing outward from its dying primary. A red giant can lose half its mass or more as it makes the transition to white dwarf, with sheets of material flowing into the outer system where aging gas giants may lurk.
Thus the white dwarf PG 0010+280, noted for its unexpectedly bright infrared signature in data UCLA student Blake Pantoja examined from the WISE (Wide-field Infrared Survey Explorer) mission. Spitzer observations from 2006 confirmed the excess of infrared, which could come from a small companion star — conceivably a brown dwarf — or a planet that has been rejuvenated by the inflow. The paper is careful to examine a range of alternatives, but further work is definitely called for given that this might represent planetary survival after the red giant phase.
At this point, we don’t have a good understanding of how common planets are around white dwarfs. Direct imaging has turned up a large gas giant at about 2500 AU orbiting the white dwarf WD 0806-661, and we also have theoretical calculations showing that planets can survive a red giant phase and remain in orbit around a white dwarf if they’re more than several AU out. Systems like this look to be unstable, with surviving minor planets eventually accreting onto the white dwarf to produce an enriched stellar atmosphere or a disk around the star.
Image: This artist’s concept shows a hypothetical “rejuvenated” planet — a gas giant that has reclaimed its youthful infrared glow. NASA’s Spitzer Space Telescope found tentative evidence for one such planet around a dead star, or white dwarf, called PG 0010+280 (depicted as white dot in illustration). Credit: NASA/JPL-Caltech.
Digging around in the new paper, I learn that we find dust disks around about four percent of white dwarfs, with all of those so far studied also showing an atmosphere enriched with heavy elements like oxygen, magnesium, silicon and iron. These elements have been assumed to be leftover materials from asteroids pulled apart by gravitational forces. An excess at infrared wavelengths is one way researchers have looked for low-mass companions around white dwarfs, and the first assumption about PG 0010+280 surely went in the same direction.
But as we learn, this is one white dwarf that does not fit the model for asteroid disks well. PG 0010+280 shows an infrared excess but no sign of heavy elements. From the paper:
Its unique infrared color as well as the non-detection of heavy elements with high-resolution spectroscopic observations suggest a possible alternative origin than white dwarfs with infrared excess from a circumstellar disk. From fitting the SED [Spectral Energy Distribution], we can not exclude models of either an opaque dust disk within the tidal radius or a substellar object at 1300 K, from an irradiated object or a re-heated planet. Future observations, particularly with spectroscopic observations in the ultraviolet and near-infrared, could reveal the nature of the infrared excess.
To fit the data, a cool brown dwarf would need a radius too small to produce the observed infrared excess, while a hot brown dwarf (re-heated during the red giant phase) would be too hot. A re-heated giant planet remains a real possibility, and the paper adds that spectroscopy in the near-infrared might be able to detect the signature of such a world, whose rejuvenation would leave a huge amount of dust in its atmosphere. “Due to possible accretion of carbon-rich material, the composition of the object’s atmosphere could be substantially modified and display CH4 and CO.”
A gas giant like the one hypothesized here would be about ten times the size of its primary — white dwarfs are about the size of the Earth, and as this JPL news release notes, such a star would be small enough to easily fit inside the Great Red Spot on Jupiter.
The paper is Xu et al., “A Young White Dwarf with an Infrared Excess,” Astrophysical Journal Letters Vol. 806, No. 1 (abstract / preprint). Thanks to Ashley Baldwin for the pointer on this one.