Modelling cometary meteoroid stream traverses of the Martian Moons eXploration (MMX) spacecraft en route to Phobos

The Martian Moons Exploration (MMX) spacecraft is a JAXA mission to Mars and its moons Phobos and Deimos. MMX will carry the Circum-Martian Dust Monitor (CMDM) which is a newly developed light-weight ($\mathrm{650\,g}$) large area ($\mathrm{1\,m^2}$) dust impact detector. Cometary meteoroid streams (also referred to as trails) exist along the orbits of comets, forming fine structures of the interplanetary dust cloud. The streams consist predominantly of the largest cometary particles (with sizes of approximately $\mathrm{100\,\mu m}$ to 1~cm) which are ejected at low speeds and remain very close to the comet orbit for several revolutions around the Sun. The Interplanetary Meteoroid Environment for eXploration (IMEX) dust streams in space model is a new and recently published universal model for cometary meteoroid streams in the inner Solar System. We use IMEX to study the detection conditions of cometary dust stream particles with CMDM during the MMX mission in the time period 2024 to 2028. The model predicts traverses of 12 cometary meteoroid streams with fluxes of $\mathrm{100\,\mu m}$ and bigger particles of at least $\mathrm{10^{-3}\,m^{-2}\,day^{-1}}$ during a total time period of approximately 90~days. The highest flux of $\mathrm{0.15\,m^{-2}\,day^{-1}}$ is predicted for comet 114P/Wiseman-Skiff in October 2026. With its large detection area and high sensitivity CMDM will be able to detect cometary meteoroid streams en route to Phobos. Our simulation results for the Mars orbital phase of MMX also predict the occurrence of meteor showers in the Martian atmosphere which may be observable from the Martian surface with cameras on board landers or rovers. Finally, the IMEX model can be used to study the impact hazards imposed by meteoroid impacts on to large-area spacecraft structures that will be particularly necessary for crewed deep space missions.


Introduction
The Japanese Space Exploration Agency (JAXA) is planning to send the Martian Moons Exploration (MMX) spacecraft to the Martian moons Phobos and Deimos and to bring samples from Phobos to Earth (Kuramoto et al. 2018). The launch of MMX is planned for 2024, and Phobos sample arrival at Earth is scheduled for 2029.
MMX will be equipped with the large area Circum-Martian Dust Monitor (CMDM) which has a sensitive area of 1 m 2 (Kobayashi et al. 2018a). The primary goals of the CMDM dust investigations are to understand dust processes in the circum-Martian environment, including the search for a proposed but still undiscovered circum-Martian dust ring (Soter 1971;Hamilton 1996;Krivov and Hamilton 1997;Ishimoto et al. 1997;Showalter et al. 2006). A second goal is the measurement of interplanetary and interstellar dust (Kobayashi et al. 2018a) as well as cometary meteoroid streams.
The prominent dust tail of a comet predominantly consists of small submicrometer-sized particles that are blown out by the solar radiation pressure force. Larger dust particles with sizes of approximately 100 µm to 1 cm are ejected from the cometary nucleus at low speeds and remain very close to the comet orbit for several revolutions around the Sun (Agarwal et al. 2010). They slowly spread in the comet orbit as a result of small differences in orbital period, and they form a tubular structure along the orbit of the parent comet filled with dust, called a dust stream or trail. Particles in the intermediate size range from approximately 1 µm to 100 µm are still subject to radiation pressure, thus migrating away from the comet's orbital position, but they stay on trajectories similar to the orbit of their parent comet for some time.
Dust trails in the vicinity of comets were first observed by the Infrared Astronomical Satellite (IRAS; Sykes et al. 1986;Sykes and Walker 1992). In subsequent infrared observations, at least 80% of the observed Jupiter-family comets were associated with dust trails which can thus be considered one of their generic features (Reach et al. 2007). A recent review of the present knowledge on cometary dust, including dust trails, was given by Levasseur-Regourd et al. (2018).
These meteoroid trails form fine structures superimposed on the interplanetary background dust cloud. When the Earth intercepts a cometary trail, the particles collide with the atmosphere and show up as meteors and fireballs with hourly rates significantly enhanced over the sporadic meteor background flux (Koschny et al. 2019, and references therein). Effects of meteoroid impacts were also observed on the Earth's Moon and on other planets (see Christou et al. 2019, for a comprehensive review). Meteor trails can impose safety risks for Earth orbiting and interplanetary spacecraft. Although the impact probability per spacecraft is small, spacecraft anomalies very likely related to meteoroid impacts were observed in the past (Caswell et al. 1995;Cameron et al. 2004). The risk is considered sufficiently high to occasionally affect crewed spaceflight operations (Beech et al. 1995).
In the past, the detection of meteoroid trails by spacecraft-based in situ dust detectors was hindered by the relatively small sensitive area of the instruments and low particle fluxes in the trails. Only recently could a small number of impacts of likely cometary meteoroid particles be identified in the data set collected by the in situ dust instruments onboard the Helios spacecraft in the inner Solar System in the 1970s (Altobelli et al. 2006;Krüger et al. 2020).
Interestingly, the identification of trail particles was only possible because Helios traversed the same region of space and thus, the same cometary trails, many times which significantly increased the chances to detect trail particles with these relatively small impact ionization dust sensors. MMX with its large area CMDM dust detector will be excellently equipped to make the first undisputable in situ detections of cometary meteoroid trails.
Cometary dust trails can be simulated with the Interplanetary Meteoroid Environment for eXploration (IMEX) dust streams in space model which was developed under contract by the European Space Agency (Soja et al. 2015b. IMEX is a new universal and physical model for dust dynamics and orbital evolution that simulates cometary dust trails in the inner Solar System. The model follows the trails of 420 comets and is ideal for studying meteor streams and cometary dust trails as measured by in situ detectors and observed in infrared images. A recent review of presently existing up to date models for dust in interplanetary space in the inner solar system can be found in Grün et al. (2019).
We use the IMEX model to study future cometary trail traverses by the MMX spacecraft during its interplanetary transfer to Mars and during its Martian orbital phase. After a brief description of the MMX mission and the CMDM instrument, we give an overview of the IMEX model. Next, we present and discuss the results of our IMEX simulations and, finally, we summarise our conclusions.

MMX Mission and Circum-Martian Dust Monitor
Building on the experience of the asteroid sample return spacecraft Hayabusa and Hayabusa 2, JAXA is planning to launch the Martian Moons eXploration (MMX) spacecraft to Phobos and Deimos (Kuramoto et al. 2018(Kuramoto et al. , 2019.
The mission will perform the first landing on one of the Martian moons, Phobos, collect samples from its surface, and return them to Earth. In addition to the returned samples, the mission will perform close-up remote sensing and in situ measurements at the two moons, and deploy a small rover on the Phobos surface. The launch of MMX is planned for 2024, the spacecraft will be in Mars orbit from 2025 to 2028, and the return module will arrive at Earth in 2029.
For its transfer to Mars MMX will use a low-energy transfer orbit, which takes about one year to reach the planet. This trajectory takes more time than a classical Hohmann transfer but significantly reduces the amount of fuel needed (Topputo and Belbruno 2015;Ogawa et al. 2019). After Mars orbit insertion, MMX will initially orbit the planet on a trajectory near Phobos' orbit. Subsequently the spacecraft will be injected into a quasi-satellite orbit around the moon with a minimum altitude above the Phobos surface of 20 km or less (Kuramoto et al. 2019).
MMX will be a 3-axis stabilised spacecraft throughout the entire mission.
One of the scientific instruments on board MMX will be the Circum-Martian Dust Monitor (CMDM; Kobayashi et al. 2018a). It is a large area dust detector with 1 m 2 sensor area. For dust detection CMDM will use the outermost polyimide film of the spacecraft multi-layer insulation (MLI), which is a thermal blanket of the spacecraft. The sensor will use the MLI on one flat side of the spacecraft and have a field-of-view of 2π. Additional piezoelectric elements will be mounted on the MLI surface. A dust particle hitting or penetrating the MLI surface generates a stress wave that subsequently propagates through the MLI film. It can be detected by one or more of the piezoelectric sensors, and the position of the impact on the MLI can be derived from the differences between the arrival times of the signals measured on the multiple pick-up sensors. From the derived position of the crater or penetration location, it will be possible to distinguish whether it is a dust impact or noise event (Kobayashi et al. 2016). Information about the projectile's mass and impact speed can be derived from the waveform of the signal.
At 10 km s −1 impact speed the instrument can detect impacts of particles as small as approximately 3 µm in radius.

IMEX cometary trails model
In order to identify time intervals when the MMX spacecraft will traverse cometary meteoroid trails, we use the IMEX dust streams in space model (Soja et al. 2015b. The model generates trails for 362 Jupiter-family, 40 Halley-type, and 18 Encke-type comets available in the JPL Small Body Database (SBDB) as of 1 August 2013, which have perihelion distances q < 3 AU, semimajor axes a < 30 AU, and defined total visual magnitudes.
Particles are emitted when the comet is in the inner Solar System, taking into account perihelion passages between the years 1700 and 2080 for Encke-type comets, and between 1850 and 2080 for Jupiter-family and Halley-type comets, respectively. This reflects the fact that the most recently released dust is expected to be most important, and also the maximum size of the database that could be maintained at the time when the model was developed.
For each passage through the inner Solar System within 3 AU of the Sun of each comet (which we refer to as apparition in the following), particles are emitted from the sunlit hemisphere of the comet nucleus within the time ranges specified above. About 28,000 particles are ejected per comet per apparition for Halley-type comets; and about 14,000 for other comets.
The dust ejection is described by the comet emission model of Crifo and Rodionov (1997). The model assumes the dust emission to be driven by water gas production within 3 AU of the Sun. It estimates the water production rate using the visual magnitude, and a gas-to-dust ratio (Jorda et al. 2008). The JPL Small Body Database provides total and nuclear magnitudes.
Dust-to-gas mass ratios can be estimated for individual comets, and they mostly range from 0.1 to 3, though higher values are possible. They appear to be dependent on heliocentric distance (A'Hearn et al. 1995). Given the large uncertainties in dust-to-gas ratios, the model uses a value of 1. Deviations from this can be considered in the analysis of individual comets.
The IMEX model uses the mass distribution model of Divine and Newburn (1987) and Agarwal et al. (2007Agarwal et al. ( , 2010, with model parameters given by Soja et al. (2015b). The mass distribution covers the range from 10 −8 kg to 10 −2 kg, separated into eight mass bins (approximately corresponding to 100 µm to 1 cm particle radius; Soja et al. 2015b). The particle density is assumed to be ρ = 1, 000 kg m −3 . For comets with unknown radius a value of 1 km is assumed (Soja et al. 2015b).
The trajectory of each emitted particle is integrated individually including solar gravity, planetary perturbations, solar radiation pressure and Poynting-Robertson drag. The model calculates the impact velocity for each individual particle onto the spacecraft as well as dust number density and flux. A detailed model description including an application to the trail of comet 67P/Churyumov-Gerasimenko was given by Soja et al. (2015b). We use the IMEX For the Martian orbital phase of MMX we use Mars as the target for our simulations. We do not consider the interplanetary return to Earth in this work. CMDM will be mounted on the spacecraft module that will return to Earth and be able to collect data during this mission phase, however, we do not have a trajectory for this mission phase available at the present time. Given that IMEX is a time-dependent model, the use of the actual spacecraft trajectory is a prerequisite to make reliable predictions for the occurrence of trail traverses and the dust fluxes during such traverses. Figure 1 shows the simulated dust fluxes during cometary trail traverses of MMX along its interplanetary transfer to Mars. The MMX trajectory for this mission phase is shown in Figure 2, and details of these trail traverses are given in Table 1.  reference frame projected onto the ecliptic plane. The particle impact speeds for the above four comets are in the range 10 km s −1 |v imp | 20 km s −1 . Table 1 gives the impact speeds together with the impact directions of the particles. The latter are given as the upstream direction in the spacecraft frame of reference of the particle flow which corresponds to the radiant of a meteor stream in a planetary atmosphere.

Results
For the MMX Mars Orbital Phase the simulated dust fluxes are shown in Figure 3. For seven comets with a total of nine trail traverses the predicted fluxes exceed 10 −3 m −2 day −1 , see also Table 1. The time intervals with fluxes above this limit last between 2 and 15 days, adding up to a total of 70 days. The comet trail traverse with the highest predicted flux is the one of 114P/Wiseman-Skiff with a maximum of 1.5 · 10 −1 m −2 day −1 . However, this trail is rather collimated, leading to a short traverse which lasts only three days. The model finds 72 additional comets with fluxes below 10 −3 m −2 day −1 . As for the interplanetary transfer phase, we do not consider them relevant.

Figures 1 and 3 also show the flux of sporadic interplanetary particles predicted by the Interplanetary Meteoroid
Engineering Model (IMEM) developed by Dikarev et al. (2005). For the IMEM simulations we assumed a spinning flat plate sensor. Given that the actual CMDM orientation on board the 3-axis-stabilized MMX spacecraft during the mission is not known at the present time, this is a reasonable approximation. We adopted the same particle size range as for the IMEX meteoroid trail simulations (10 −8 kg to 10 −2 kg) so that the fluxes can be directly compared with the fluxes predicted for the meteoroid trail traverses (Due to artefacts in the predicted fluxes for a lower mass cutoff at 10 −8 kg caused by the parametrisation of the cometary particle populations in the IMEM model, we used a slightly lower boundary of 4 · 10 −9 kg for the simulations and scaled the curves shown in Figures 1 and 3 by a factor of 2.5 that we derived from the particle size distribution). The highest predicted trail fluxes typically exceed the flux of sporadic interplanetary particles of the same size by approximately one (during interplanetary transfer) to two orders of magnitude (during Mars orbital phase). We ignore interstellar dust because it does not make any significant contribution to the dust fluxes in this size range . Fluxes expected for smaller interplanetary and interstellar particles down to the detection limit of CMDM as predicted by IMEM are given by Kobayashi et al. (2018a).
As for the interplanetary transfer, the locations of trail traverses and impact directions of trail particles are shown in Figure 4. The particle impact speeds are in the range 10 km s −1 |v imp | 22 km s −1 . Again the impact directions and speeds are given in Table 1. Strictly speaking, impact speeds and directions refer to an observer on Mars because we have used Mars as the target for our simulations. The orbital elements of the identified comets are given in Table 2 in the Appendix. All comets identified in our analysis are Jupiter Family Comets with orbital periods between 5.2 and 13.8 years.
Column 6 in Table 1 lists the total number of expected particle detections with CMDM during the traverse of each comet's trail (fluence). All these numbers are below 1, with the highest values being the fluences of approximately 0.3 for comets 19P/Borrelly and 114P/Wiseman-Skiff. It has to be noted that these fluences refer to particle sizes of approximately 100 µm and bigger, while CMDM can detect particles at least one order of magnitude smaller.
These smaller particles are not covered by the IMEX model and, thus, the fluences detectable with CMDM are expected to be significantly higher. We will discuss this in the next Section.

Discussion
Individual trail particles originating from comets 45P/H-M-P and 72P/Denning-Fujikawa were likely detected by the Helios dust instruments already in the 1970s (Altobelli et al. 2006;Krüger et al. 2020). IMEX predicts a flux of approximately 10 −2 m −2 day −1 for the traverses of these meteoroid trails by Helios. It has to be emphasised that the dust sensors on board Helios had a combined effective sensor area for trail particle detections of only about 30 cm 2 . However, Helios traversed the same region of space, and thus the same comet trail, ten times, which increased the detection probability also by a factor of ten. Considering that the sensor area of CMDM will be larger by a factor of more than 300 while the dust fluxes predicted by IMEX are similar within an order of magnitude, we conclude that CMDM has a very good chance to detect cometary trail particles as well.
Our analysis of the Helios dust data showed an offset by a few days for some dust particle detections as compared to the times predicted by the IMEX model (Krüger et al. 2020). Various reasons may be responsible for such an offset which include shortcomings of the IMEX model like, for example, the dust ejection model employed which may not fully cover all relevant aspects of dust ejection, or the particle trajectory computation which follows the particle motion only for up to 300 years. Furthermore, the model simulates particles with masses 10 −8 kg and bigger, corresponding to particle radii above approximately 100 µm while the masses of the particles detected Table 1. Results from the IMEX cometary dust trails simulations for MMX. The time interval of the trail traverse together with the predicted maximum flux (of 100 µm and bigger particles) are given in columns (2) to (5). Column (6) gives the fluence on to a 1 m 2 detector detectable during the time interval given in column (2). Columns (7) to (10) give the speed vector, while columns (11) and (12)  [m −2 (3) (8) by Helios as derived from the calibration of the Helios dust instruments were at least four orders of magnitude less massive, corresponding to particle radii of a few micrometers to about 10 µm (Note that the Helios dust instruments had a detection threshold for dust particles with masses of approximately 3 · 10 −16 kg at an impact speed of 10 km s −1 (Grün et al. 1980), corresponding to a particle radius of approximately 0.3 µm). Such smaller particles are more susceptible to radiation pressure and Poynting-Robertson drag than the larger ones which leads to an increased particle dispersion in space. From our analysis of the Helios data we concluded that the size (mass) of the impactors as derived from the instrument calibration may be significantly underestimated, even more so if cometary particles are fluffy aggregates as shown, for example, by the results from the Rosetta mission to comet 67P/Churymov-Gerasimenko (Güttler et al. 2019;Kimura et al. 2020b,a). A more detailed discussion is given by Krüger et al. (2020). To conclude, the time intervals for the trail traverses given in Table 1 may be too conservative when taking into account particles smaller than 100 µm.
The IMEX model simulates relatively large particle sizes r d ≥ 100 µm, much larger than the particles detectable by the CMDM dust detector (r d ≥ 3 µm). However, smaller particles are known to be present in the ejecta cloud of a comet, following a differential power law index of approximately −4 in their size distribution (Agarwal et al. 2010, and references therein), which corresponds to an index of approximately −3 for a cumulative size distribution. Their dynamical behaviour is not the same as for particles with r d 100µm due to the increasing effect of non-gravitational forces on the smaller particles. However, for sizes 10µm ≤ r d ≤ 100µm their orbital characteristics are sufficiently similar to the larger particles, but spatially offset due to perturbations, as preliminary tests have demonstrated. An updated version of the IMEX Streams model for smaller particle sizes is planned, but currently not available for predictions.
In order to get to a more realistic representation of the expected fluxes, we consider two cases with a lower cutoff of r cutoff,1 = 10 µm and r cutoff,2 = 30 µm, resprectively. We extrapolate from the IMEX model flux of particles with sizes r d ≥ 100 µm using a cumulative power law size distribution index of −3. This leads to an increase in total flux by a factor of 31.6 in the case of a cutoff at 30 µm, and a factor of 1 000 for the 10 µm cutoff. While it is unlikely that all particles in this size range remain in the stream, we consider a lower cutoff of 10 to 30 µm conservative, and therefore a reasonable estimate for the expected fluxes and fluences overall. Based on the fluences listed in Table 1 (column 6), on the order of approximately 10 to 100 trail particle impacts are expected during traverses of the densest trails predicted by the IMEX model. This is also supported by our Helios observations mentioned above.
In addition to this, a comparison of the IMEX model to observations of cometary meteoroid streams by Soja et al. for recent reviews). Given that MMX will be orbiting Mars in an orbit similar to Phobos during a significant fraction of the mission time, the spacecraft will largely be immersed in these rings and the question arises how CMDM can effectively separate cometary trail particles from ring particles. Dust number densities predicted for the Martian rings are approximately 6 · 10 −6 m −3 for the Phobos ring for particles larger than 30 µm and approximately 10 −4 m −3 for the Deimos ring for particles larger than 15 µm (Krivov and Hamilton 1997;Krivov et al. 2006).
Smaller particles are not expected to exist in abundance in the rings because their orbits are unstable. The expected particle impact speeds are in the range 0.2 to 0.8 km s −1 (Kobayashi et al. 2018a). Assuming a typical value of 0.5 km s −1 , these number densities convert to dust fluxes of approximately 300 m −2 day −1 and 4000 m −2 day −1 , respectively. Number densities for 100 µm and bigger particles as simulated by IMEX are not given by Krivov and Hamilton (1997). However, from their results we estimate that the fluxes of such particles in the rings are likely more than one (in the case of Phobos) up to two (Deimos) orders of magnitude lower. Even these reduced numbers exceed the fluxes for cometary trail traverses predicted by our IMEX simulations by a few orders of magnitude.
This makes particle identifications solely by enhanced dust fluxes very unlikely and, hence, we will have to use other criteria to identify cometary trail traverses. The impact speeds of trail particles exceed 10 km s −1 (Table 1) and are thus more than one order of magnitude higher than those of the ring particles. Furthermore, the impact direction of the particles can be derived from the spacecraft orientation at the particle impact time. Thus, the measured impact speed together with the impact direction will be the crucial parameters to separate cometary trail particles from Martian ring particles in the CMDM data set.
Similarly, during the interplanetary cruise phase of MMX, trail particles will have to be separated from the background flux of sporadic interplanetary particle impacts. Given that the impact speed will not serve as a crucial parameter because both populations will have similar speeds, we will instead search for cometary trail particles in the data set by using statistical techniques. We will use a method employed by Oberst and Nakamura (1991) to identify temporal clustering of meteoroid impacts detected by the Apollo lunar seismic network. The application of this method to in-situ dust detector data was described by Grün (2001) and successfully applied for the identification of Jovian dust stream particles in the Ulysses dust detector data set (Baguhl et al. 1993;Krüger et al. 2006).
About 15 years ago there was the claim that a meteor originating from comet 114P/Wiseman-Skiff was photographed in the Martian sky by the Mars exploration rover Spirit (Bell et al. 2004). However, later work quantified the effects of cosmic ray hits on the Spirit Pancam as part of a dedicated meteor search and placed this detection in doubt (Domokos et al. 2007). We also simulated the trail traverse of 114P/Wiseman-Skiff in 2004 with IMEX and we did not find a significantly enhanced dust flux in that period, consistent with the interpretation that the feature seen in the image taken by the Mars rover was a likely false detection.
In 2014  Si and Ca; Benna et al. 2015). Intense ultraviolet emission due to magnesium and iron was attributed to dust trail particles approximately 1 to 100 µm in size (Schneider et al. 2015). These observations showed that the ablation of meteoroids can lead to significant temporal changes in the composition of planetary atmospheres and ionospheres.
Comets with close encounters to Mars were studied by various authors (Adolfsson et al. 1996)  Comet trails were the subject of sky surveys in the infrared (Sykes and Walker 1992;Reach et al. 2007;Arendt 2014) and recently also in the visible wavelength range (Ishiguro et al. 2007). Comet 103P/Hartley is the only comet identified in our analysis which is contained in any of these surveys but unfortunately its trail remained undetected (Reach et al. 2007).
We also performed IMEX simulations for the DESTINY + ( The fact that we performed our simulations for the MMX Martian orbital phase with Mars as a target may lead to deviations in the impact directions and speeds as compared to those given in Table 1 because the spacecraft will be in an orbit very similar to the one of Phobos. Considering Phobos' orbital speed of about 2 km s −1 , the uncertainty in the impact speed caused by this approximation should be below 20%. Furthermore, considering that CMDM is a flat sensor with 2π field-of-view, the error in the impact direction should not lead to a significant uncertainty in the dust flux, in particular when taking into account that the fluxes predicted by IMEX have an uncertainty of at least a factor of ten anyway. For a more detailed analysis of the impact directions and speeds, and in particular for planning the CMDM measurements at Mars, it will be worthwhile to use the actual MMX trajectory around Mars in the future. Cometary meteoroid impacts may pose significant risks for Earth orbiting satellites and crewed spaceflight as has been already mentioned in the Introduction. For crewed missions to other planets this will likely become an increasingly severe issue because the spacecraft will become increasingly larger and long flight times will be required which will increase the probability for hazardous meteoroid hits. Christou and Vaubaillon (2010) pointed out that in the future the impact hazard should already be considered during the analysis and design phase of interplanetary missions in order to optimize their trajectories and reduce hazardous cometary trail traverses as much as possible.

Conclusions
We used the IMEX dust streams in space model (Soja et al. 2015b) to predict cometary meteoroid trail traverses by the MMX spacecraft. The model simulates cometary trails in the inner Solar System formed by particles in the size range 10 −8 kg to 10 −2 kg, approximately corresponding to 100 µm to 1 cm particle radius.
Using the presently available nominal trajectory of MMX we found that during its interplanetary transfer to Mars and while being in Mars orbit the spacecraft will traverse several cometary meteoroid trails. The highest dust flux is predicted for October 2026 when MMX will be in Mars orbit traversing the trail of comet 114P/Wiseman-Skiff, with a maximum flux of 0.15 m −2 day −1 lasting for about three days. We find a total of 12 trail traverses during the entire mission, with fluxes of at least 10 −3 m −2 day −1 , covering a total time period of approximately 90 days.
Smaller particles -which are not covered by the present IMEX model -are expected to exist in the comet trails as well and may lead to a few orders of magnitude higher dust fluxes. We conclude that the large area CMDM dust sensor on board MMX with its detection threshold of approximately 3 µm particle radius will likely be able to detect trail particles during a few meteoroid trail traverses.
The in situ detection and analysis of cometary trail particles in space creates a new opportunity to remotely measure the composition of celestial bodies without the necessity to fly a spacecraft to or even land on the source objects.
Missions carrying dust instruments in the near future that may benefit from this approach include DESTINY + to the asteroid (3200) Phaethon, Europa Clipper to the Jupiter system and the Interstellar Mapping and Acceleration Probe (Kobayashi et al. 2018b;Kempf 2018;McComas et al. 2018). Successful measurements of meteoroid trails by spaceborne instruments may lead to improvements of cometary trail models. Forecasts of trail traverses by planets in connection with in situ or remote spacecraft investigations can also provide new insights into atmospheric and ionospheric processes. Last but not least, they can make essential predictions for spacecraft hazards for future crewed deep space missions.    Figure 1). Blue lines indicate the approach direction (speed vector) of trail particles onto the spacecraft in the spacecraft-centered reference frame projected onto the X-Y plane (cf. Table 1). The X-Y plane is the ecliptic plane with vernal equinox oriented towards the +X direction. The comet orbits are superimposed as thin lines.