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We describe the sensors, the sensor biasing and control, the signal-processing unit, and the operation of the Langmuir Probe and Waves (LPW) instrument on the Mars Atmosphere and Volatile EvolutioN (MAVEN) mission. The LPW instrument is designed to measure the electron density and temperature in the ionosphere of Mars and to measure spectral power density of waves (DC-2 MHz) in Mars’ ionosphere, including one component of the electric field. Low-frequency plasma waves can heat ions resulting in atmospheric loss. Higher-frequency waves are used to calibrate the density measurement and to study strong plasma processes. The LPW is part of the Particle and Fields (PF) suite on the MAVEN spacecraft. The LPW instrument utilizes two, 40 cm long by 0.635 cm diameter cylindrical sensors with preamplifiers, which can be configured to measure either plasma currents or plasma waves. The sensors are mounted on a pair of ∼ 7  meter long stacer booms. The sensors and nearby surfaces are controlled by a Boom Electronics Board (BEB). The Digital Fields Board (DFB) conditions the analog signals, converts the analog signals to digital, processes the digital signals including spectral analysis, and packetizes the data for transmission. The BEB and DFB are located inside of the Particle and Fields Digital Processing Unit (PFDPU).

The design, performance, and on-orbit operation of the three-axis electric field instrument (EFI) for the NASA THEMIS mission is described. The 20 radial wire boom and 10 axial stacer boom antenna systems making up the EFI sensors on the five THEMIS spacecraft, along with their supporting electronics have been deployed and are operating successfully on-orbit without any mechanical or electrical failures since early 2007. The EFI provides for waveform and spectral three-axis measurements of the ambient electric field from DC up to 8 kHz, with a single, integral broadband channel extending up to 400 kHz. Individual sensor potentials are also measured, providing for on-board and ground-based estimation of spacecraft floating potential and high-resolution plasma density measurements. Individual antenna baselines are 50- and 40-m in the spin plane, and 6.9-m along the spin axis. The EFI has provided for critical observations supporting a clear and definitive understanding of the electrodynamics of both the boundaries of the terrestrial magnetosphere, as well as internal processes, such as relativistic particle acceleration and substorm dynamics. Such multi-point electric field observations are key for pushing forward the understanding of electrodynamics in space, in that without high-quality estimates of the electric field, the underlying electromagnetic processes involved in current sheets, reconnection, and wave-particle interactions may only be inferred, rather than measured, quantified, and used to discriminate between competing hypotheses regarding those processes.

The Lunar Atmosphere and Dust Environment Explorer (LADEE) mission was designed to address long-standing scientific questions about the Moon’s environment, including the assessment of the composition of the lunar atmosphere, and characterization of the lunar dust environment at low orbital altitudes. LADEE was derived from the Modular Common Spacecraft Bus design that was developed at NASA Ames Research Center; it used modularized subassemblies and existing commercial spaceflight hardware to reduce cost. LADEE was launched on the very first Minotaur V, and was also the first deep space mission launched from Wallops Flight Facility in Virginia. LADEE was equipped with two in situ instruments and a remote sensing instrument to address the atmosphere and dust measurement requirements. LADEE also carried the first deep-space optical communications demonstration, the Lunar Laser Communications Demonstration. LADEE was launched in early September, 2013, took science data for over 140 days in low lunar orbit, and impacted the surface on April 18, 2014.

Shadowed locations near the lunar poles are almost certainly electrically complex regions. At these locations near the terminator, the local solar wind flows nearly tangential to the surface and interacts with large‐scale topographic features such as mountains and deep large craters. In this work, we study the solar wind orographic effects from topographic obstructions along a rough lunar surface. On the leeward side of large obstructions, plasma voids are formed in the solar wind because of the absorption of plasma on the upstream surface of these obstacles. Solar wind plasma expands into such voids, producing an ambipolar potential that diverts ion flow into the void region. A surface potential is established on these leeward surfaces in order to balance the currents from the expansion‐limited electron and ion populations. We find that there are regions near the leeward wall of the craters and leeward mountain faces where solar wind ions cannot access the surface, leaving an electron‐rich plasma previously identified as an “electron cloud.” In this case, some new current is required to complete the closure for current balance at the surface, and we propose herein that lofted negatively charged dust is one possible (nonunique) compensating current source. Given models for both ambipolar and surface plasma processes, we consider the electrical environment around the large topographic features of the south pole (including Shoemaker crater and the highly varied terrain near Nobile crater), as derived from Goldstone radar data. We also apply our model to moving and stationary objects of differing compositions located on the surface and consider the impact of the deflected ion flow on possible hydrogen resources within the craters.

ARTEMIS observes pickup ions around the Moon, at distances of up to 20,000 km from the surface. The observed ions form a plume with a narrow spatial and angular extent, generally seen in a single energy/angle bin of the ESA instrument. Though ARTEMIS has no mass resolution capability, we can utilize the analytically describable characteristics of pickup ion trajectories to constrain the possible ion masses that can reach the spacecraft at the observation location in the correct energy/angle bin. We find that most of the observations are consistent with a mass range of ∼20–45 amu, with a smaller fraction consistent with higher masses, and very few consistent with masses below ∼15 amu. With the assumption that the highest fluxes of pickup ions come from near the surface, the observations favor mass ranges of ∼20–24 and ∼36–40 amu. Although many of the observations have properties consistent with a surface or near‐surface release of ions, some do not, suggesting that at least some of the observed ions have an exospheric source. Of all the proposed sources for ions and neutrals about the Moon, the pickup ion flux measured by ARTEMIS correlates best with the solar wind proton flux, indicating that sputtering plays a key role in either directly producing ions from the surface, or producing neutrals that subsequently become ionized. Key Points ARTEMIS observes pickup ions from the lunar exosphere and/or surface Using ion trajectory information, we can constrain the mass of lunar ions Lunar pickup ion flux correlates with solar wind flux

Dust is common close to the martian surface, but no known process can lift appreciable concentrations of particles to altitudes above ~150 kilometers. We present observations of dust at altitudes ranging from 150 to above 1000 kilometers by the Langmuir Probe and Wave instrument on the Mars Atmosphere and Volatile Evolution spacecraft. Based on its distribution, we interpret this dust to be interplanetary in origin. A comparison with laboratory measurements indicates that the dust grain size ranges from 1 to 12 micrometers, assuming a typical grain velocity of ~18 kilometers per second. These direct observations of dust entering the martian atmosphere improve our understanding of the sources, sinks, and transport of interplanetary dust throughout the inner solar system and the associated impacts on Mars’s atmosphere.

We report observations by the twin‐probe mission ARTEMIS of pick‐up ions of lunar origin obtained during times when the Moon was within the terrestrial magnetotail lobes. These ions were detected as two separate focused beams above the dayside lunar surface. Analysis of these beams has shown that they possess both field‐aligned and field‐perpendicular velocities, implying the presence of electric fields both parallel and perpendicular to the magnetotail lobe magnetic field. We suggest that the sources of these two electric fields are (a) the near‐surface electric field due to the lunar photoelectron sheath and (b) the electric field generated by the magnetotail lobe convection velocity. We use the energy and pitch angle spectra to constrain the source locations and compositions of these ions, and conclude that exospheric ionization of the neutral exosphere is the dominant lunar pick‐up ion production mechanism in the tail lobes. Key Points ARTEMIS observes pickup ions in the terrestrial magnetotail lobes Photoelectric and convection electric fields affect these ions These ions originate from the neutral exosphere and possibly a geologic vent

The two ARTEMIS probes observe significant precursor activity upstream from the Moon, when magnetically connected to the dayside lunar surface. The most common signature consists of high levels of whistler wave activity near half of the electron cyclotron frequency. This precursor activity extends to distances of many thousands of km, in both the solar wind and terrestrial magnetosphere. In the magnetosphere, electrons reflect from a combination of magnetic and electrostatic fields above the lunar surface, forming loss cone distributions. In the solar wind they generally form conics, as a result of reflection from an obstacle moving with respect to the plasma frame (just as at a shock). The anisotropy associated with these reflected electrons provides the free energy source for the whistlers, with cyclotron resonance conditions met between the reflected source population and Moonward-propagating waves. These waves can in turn affect incoming plasma, and we observe significant perpendicular electron heating and plasma density depletions in some cases. In the magnetosphere, we also observe broadband electrostatic modes driven by beams of secondary electrons and/or photoelectrons accelerated outward from the surface. We also occasionally see waves near the ion cyclotron frequency in the magnetosphere. These lower frequency waves, which may result from the presence of ions of lunar origin, modulate the whistlers described above, as well as the electrons. Taken together, our observations suggest that the presence of the Moon leads to the formation of an upstream region analogous in many ways to the terrestrial electron foreshock.

We analyzed lunar surface charging during solar energetic particle (SEP) events, utilizing Lunar Prospector measurements of surface potentials and electron fluxes, and upstream energetic particle data. Outside of the magnetosphere, we find a nearly one‐to‐one correspondence between extreme negative lunar surface charging and large solar proton events. Using new techniques to correct for spacecraft potential, we present the first quantitative measurements of lunar charging during SEP events, during which we find that the nightside surface reaches potentials of up to −4.5 kV, with negative potentials of a kilovolt or larger often observed. These potentials are far higher than typical nightside potentials of a few hundred volts negative and may increase the risk of electrostatic discharge and/or dust effects, introducing an additional hazard to the already dangerous radiation environment. For eight of eleven event periods, surface potentials correlate with electron temperature and with the ratio of energetic electron flux to both energetic proton flux and total electron flux. For these eight events, charging models taking into account both thermal/suprathermal and energetic particle fluxes, as well as secondary emission, can successfully predict surface potentials. However, during the other three events, surface potentials do not correlate with the same measurable quantities, and charging models cannot reproduce measured potentials. In order to develop reliable and accurate models for lunar surface charging during SEP events, we will need better measurements of ion and energetic particle behavior in the lunar environment, secondary electron emission from lunar materials, and lunar surface potentials.

As an airless body in space with no global magnetic field, the Moon is exposed to both solar ultraviolet radiation and ambient plasmas. Photoemission from solar UV radiation and collection of ambient plasma are typically opposing charging currents and simple charging current balance predicts that the lunar dayside surface should charge positively; however, the two ARTEMIS probes have observed energy‐dependent loss cones and high‐energy, surface‐originating electron beams above the dayside lunar surface for extended periods in the magnetosphere, which are indicative of negative surface potentials. In this paper, we compare observations by the ARTEMIS P1 spacecraft with a one‐dimensional particle‐in‐cell simulation and show that the energy‐dependent loss cones and electron beams are due to the presence of stable, non‐monotonic, negative potentials above the lunar surface. The simulations also show that while the magnitude of the non‐monotonic potential is mainly driven by the incoming electron temperature, the incoming ion temperature can alter this magnitude, especially for periods in the plasma sheet when the ion temperature is more than twenty times the electron temperature. Finally, we note several other plasma phenomena associated with these non‐monotonic potentials, such as broadband electrostatic noise and electron cyclotron harmonic emissions, and offer possible generation mechanisms for these phenomena. Key Points ARTEMIS has observed the dayside lunar plasma environment in the magnetotail We observe non‐monotonic potentials and plasma waves Modeling shows a critical role for the ion distribution