The Gandalf Staff is a mobile tool designed to be a flexible device supporting crewed and uncrewed operations on the lunar surface.The core of the device is a 24v battery with communications and data storage systems.Initial optional components supporting crewed Extra-Vehicular Activity (EVA) include a LiDAR and 360@ camera.These provide 3D mapping of the traverse for documentation, and to aid future planning.The mapping also creates outreach opportunities for the public to "stand beside" the astronaut in Virtual Reality (VR).The staff provides external lighting for field site illumination in the south polar region low sun angle environment.Navigation instruments for crew position determination with Lunar Search and Rescue (LunaSAR) are also included.The staff itself can be used as a walking aid or as a splint for Incapacitated Crew Rescue (ICR).As a stand-alone device, the staff operates as a long duration untended science platform collecting environmental data and sending it to a lunar base station.The stand-alone mode requires connection to an auxiliary power source (e.g.solar array) and energy storage system (e.g.battery), so it could become an electrical recharging station.To make rapid progress in the 1 st year, and also to demonstrate innovative project management techniques, NASA guided a private industry partner, T STAR, in leading Capstone Engineering student teams at Texas A&M University (TAMU) for proof-of-concept development and testing.These teams developed the power system and demonstrated successful integration of LiDAR, WiFi communications, and external lighting subsystems.Another industry team at Jacobs Technology prototyped a tripod to hold the staff upright.For the 2 nd year (FY'22), NASA will again collaborate with partners to prototype enhanced power and lighting concepts.Year 2 will also add new capability for LunaSAR and geophysical science instrumentation using a heat probe.The heat probe is based upon Apollo heritage but modified to measure subsurface volatile ice regimes at the Artemis landing site.Components of the Gandalf Staff can be developed, tested, and deployed independently, or on the integrated staff, rovers, or utility trailers.The project supports crew safety, lunar sample curation, mission science, and public outreach goals of NASA.

As the new decade begins, new programmatic strategies to conduct more frequent, lower cost missions are beginning to be applied to deep space robotic science missions, such as the Commercial Lunar Payload Services (CLPS) program. These new strategies include moving from cost-plus contracts towards fixed price contracts, commercial contractors increasingly sharing in development costs, finding launch opportunities through ride sharing and comanifesting payloads, and making use of smallsats and other spacecraft with off-the-shelf hardware. While these new practices are now being applied in many areas across NASA, they are not yet being widely implemented in the Mars exploration program, where large bespoke missions have become the dominant programmatic strategy. As the decadal survey for planetary science in the 2020’s begins its deliberations, it should consider how programmatic strategies that emphasize lower cost, more frequent missions to Mars can provide groundbreaking science return and enable the beginning of a new age in Martian exploration

Introduction: Gravimetry, the measurement of slight variations in gravitational acceleration, can be used to infer density distributions in a planet’s subsurface. While surface-based surveys are common on Earth, extraterrestrial surveys are typically confined to orbital platforms. This restricts the resolution of the data and inhibits the study of crustal structure at a finer scale, representing a need for data collected at the surface or near surface. Recently, the first surface gravity traverse on Mars was performed using the microelectromechanical systems (MEMS) engineering accelerometers on the Curiosity rover [1]. This study highlighted the potential of MEMS devices for planetary exploration. Additionally, such devices are more robust and have lower masses, costs, and power requirements than traditional gravimeters, adding to their suitability for planetary applications. NASA has developed an instrument that utilizes tri-axial MEMS accelerometers contained within an inertial measurement unit to conduct gravity measurements. Here, we discuss a project that aims to support wider efforts to develop MEMS gravimeters for planetary exploration [2,3].

Comets likely formed in the outer regions of the protosolar nebula where they incorporated and preserved primitive presolar materials, volatiles resident in the outer disk, and more refractory materials from throughout the disk. The return of a sample of volatiles (i.e., ices and entrained gases), along with other components of a cometary nucleus, will yield numerous major scientific opportunities. We are unaccustomed to thinking of ices through a mineralogical/petrological lens, but at cryogenic temperatures, ices can be regarded as mineral components of rocky material like any other. This is truly Terra Incognita, as a sample from a natural cryogenic (10s of K) environment is unprecedented in any setting; currently, we can only make educated guesses about the nature of these materials on a microscopic scale. Such samples will provide an unparalleled look at the primordial gases and ices present in the early solar nebula, enabling insights into the gas phase and gas-grain chemistry of the nebula. Understanding the nature of the ices in their microscopic, petrographic relationship to the refractory components of the cometary sample will allow for the study of those relationships and interactions and a study of evolutionary processes on small icy bodies. The previous 2013-2022 Planetary Decadal Survey included a study of a Flagship-class cryogenic comet nucleus sample return mission, given the scientific importance of such a mission. However, the mission was not recommended for flight in the last Decadal Survey, in part because of the immaturity of critical technologies. Now, a decade later, the scientific importance of the mission remains and relevant technological advances have been made in both cryo instrumentation for flight and laboratory applications. Such a mission should be undertaken in the next decade.

The Flexible Lunar Architecture for Exploration (FLARE) is a concept to deliver four crew to the lunar surface for a minimum of seven days and then return them safely to Earth. FLARE can be implemented whenever the component vehicles are operational. FLARE was developed as an alternative to NASA's Human Landing System (HLS) reference architecture from the Design Analysis Cycle (DAC) #2 created in 2019. The DAC2 guidelines required utilization of the Gateway vehicle in a Near- Rectilinear Halo Orbit (NRHO). Instead, FLARE chooses a Low Lunar Frozen Polar Orbit (LLFPO) for lunar rendezvous of components, and an optional Gateway vehicle. The LLFPO provides a stable orbit that overflies the south pole every 2 h, ensuring easy access to the lunar surface for surface aborts with a much lower propellant requirement than NRHO. The minimum FLARE concept uses one Space Launch System (SLS) launch, one Orion, one European Service Module (ESM), and one human lander (launched on commercial vehicle(s)). FLARE adds the SpaceTug, based upon the mature and successful ULA "Common" Centaur Upper Stage vehicle, with modifications to create an Earth-Moon transfer vehicle. In the FLARE baseline mission, the SpaceTug provides propulsion needed to return the Orion + ESM from LLFPO to Earth. The SpaceTug also provides propulsion to deliver the separate human lander components - the Descent Element (DE) and the Ascent Element (AE) - from Low Earth Orbit (LEO) to LLFPO. The SLS Block 1 then launches the Orion + ESM and completes a rendezvous with the mated DE + AE components in LLFPO. FLARE offers optional phases beyond the baseline mission. The SpaceTug can deliver components of the planned Gateway, including the Power and Propulsion Element (PPE) and the Habitable and Logistics Outpost (HALO), to LLFPO. FLARE provides an option to deliver precursor equipment to the lunar surface to enhance and extend the human mission. With these components, including an inflatable habitation module and airlock, individual crew mobility vehicle(s), an In-Situ Resource Utilization (ISRU) demonstration, and science and technology experiments, the crew can explore and conduct science on the lunar surface for up to 14 days.

The Flexible Lunar Architecture for Exploration (FLARE) is a concept to deliver four crew to the lunar surface for 7 to 14 days and then return them safely to Earth by 2024. This meets NASA’s internal 2024 lunar landing deadline directed by President Trump (Trump, 2017) and the “5-year” goal set forth by Vice President Pence (Pence, 2019). FLARE is an alternative to NASA’s Human Landing System reference architecture from the Design Analysis Cycle (DAC) #2 (NASA, 2019b). The minimum FLARE concept uses one Space Launch System launch, one Orion, one European Service Module (ESM), and one human lander to deliver four crew to the Moon for a minimum surface duration of 7 days and return them to Earth. FLARE adds a new capability, called the SpaceTug, based upon the mature and successful United Launch Alliance “Common” Centaur Upper Stage vehicle, with modifications. In FLARE, the SpaceTug provides propulsion needed to return the Orion+ESM from the Moon to Earth. The SpaceTug also provides propulsion to deliver the human lander Descent Element (DE) and Ascent Element (AE) separately to lunar orbit. The Orion+ESM then completes a rendezvous with the mated DE+AE in lunar orbit. FLARE also offers optional phases to the Moon 2024 mission. The SpaceTug can also deliver components of the planned Gateway - including the Power and Propulsion Element and the Habitation and Logistics Outpost - to lunar orbit; however, the planned FLARE destination is a Low Lunar Frozen Polar Orbit unlike the NASA DAC2 plan for a Near Rectilinear Halo Orbit. FLARE also provides an option to deliver precursor equipment - including a habitation module, crew mobility devices and an In-Situ Resource Utilization demonstration - to the lunar surface for enhanced crew exploration and science with the extended 14-day surface mission.

Introduction: Gravitational data taken from a planetary body can be used to infer densities and structures within the planet’s crust. While orbital surveys have been able to explore subsurface stratification and densities, surveys from the surface, or near-surface could study these characteristics at greater depths and increase the resolution of the data. Inertial measurement units (IMUs) have been traditionally used for navigation and attitude determination. In 1995, the first study using an IMU for gravimetry was carried out over the Rocky Mountains [1]. The use of IMUs for terrestrial gravimetry has since become more common and has proven to be an effective, low-cost alternative to traditional gravimeters with the main drawback being poor long-term stability due to instrument drift [2]. More recently, IMUs on the Curiosity rover were used to conduct a gravity survey of the rover’s traverse at Gale Crater. This marked the first gravity survey conducted on the surface of Mars and proved the feasibility of using IMUs for surface and near surface gravimetry [3]. The objectives of this project are to: 1) test a proof-of concept instrument containing a microelectromechanical systems (MEMS) IMU, and 2) develop proper gravity data reduction methods for planetary inertial gravimetry. Instrument Background: The instrument, named HELIX, was developed by engineering students at Texas A&M University in College Station, Tx. HELIX is a balloon-mounted sensor package towed by a ground vehicle designed to collect airborne gravity data (see figure 1). The sensor package contains a low-drift IMU, GPS, rangefinder, and internal and external temperature sensors. The IMU is the tri-axial IMU-3030 manufactured by MEMSense. Data Processing: Fixed bias, scale factor, and cross-axis misalignment errors are determined by performing a six-position static test where the positive and negative axes in each direction are aligned with the vertical gravity vector. While flying, HELIX will experience turbulence and attitude instability. This can be compensated for by using a direction cosine matrix which rotates the IMU axes from the body reference frame into the inertial reference frame, where the gravity-sensitive z-axis is aligned with the gravity vector. Temperature variations are strongly correlated to bias in MEMS accelerometers [4]. The internal temperature of the IMU, and environmental temperature must be considered when modelling this relationship. Multiple regression will be used to determine a thermal correction and will include a linear drift term. Stochastic errors that occur during operation are highly nonlinear and must be estimated. The optimal system state estimator is the Kalman Filter [5]. An extended version called the Extended Kalman Filter (EKF) can be used to obtain estimates of gravity from a system containing stochastic errors. Gravity anomaly calculations can then be performed on the gravity estimates recovered from the EKF. Test Site: The initial test site for HELIX will be the Hastings Salt Dome located south of Houston, Texas. Salt domes are diapiric structures that migrate upward through the subsurface due to density differences with the surrounding rock. This difference should provide an apparent gravity anomaly. The data collected with HELIX will then be compared to data taken from a survey of the site conducted using a CG-5 Scintrex gravimeter, and data from the Pan American Center for Earth and Environmental Studies [6].

As Australia's population continues to grow so will the demand for affordable and liveable space. As liveable space becomes scarce the traditional construction standards will be pushed to the limits with high rise structures becoming more complex. As deep foundation design starts to get pushed to its limits, it is going to be important to understand the effects that ground water will have on the design and construction of such piles. To further investigate and analyse the effects of ground water on the axial and lateral bearing capacity of bored piles, a simulation was created using the Strand7 software package. The adopted soil properties for both drained (no ground water) and undrained soil (ground water present) conditions were determined through the literature review with the cohesion strength of the clay soils and the friction angle of the granular soils adjusted to help investigate the effects of ground water. When considering the undrained conditions of the clay soil two sce­narios were adopted, the first scenario was that the cohesion strength was not adjusted when the soil became undrained. The second scenario was that the cohesion strength was adjusted when the soil became undrained. Similarly when considering the undrained conditions of the granular soil two scenarios were adopted, the first scenario was that the friction angle was reduced to zero when the soil be­ came undrained. The second scenario was that the friction angle was halved when the soil became undrained. From the results it was found that the presence of ground water had a greater impact on granular soils than clay soils.

Introduction: Carbonate minerals of martian origin are present in several martian meteorites in trace concentrations (< 1%) and possess unique isotopic signatures that suggest that the martian environment and/or isotopic reservoirs are very different from the Earth’s [1–3]. Carbonates are most common in the older martian meteorites (Allan Hills 84001 and the nakhlites), however, there have been reports of carbonate in the younger shergottites including Elephant Moraine A79001 [1,4]. Acidification studies of Zagami and Shergotty have shown that CO2 is released suggesting that carbonate phases are present in these meteorites [4], but the origin of these phases is controversial. The young ages of the shergottites [5] makes them important samples for understanding the modern martian environment. The carbonates in EETA 79001 are the best-characterized secondary minerals in a shergottite, but their origin remains controversial. Gooding et al. [1] argued that two types of carbonate occur within the glassy parts of the meteorite. One type, nearly pure CaCO3 associated with Ca-sulfate shows textural evidence for being present in the rock prior to it being shocked, suggesting formation on Mars. The second was more abundant and consists of Ca-rich carbonate, possibly with finely intergrown Mg-phosphate, but does not possess any textural relationships indicative of a martian origin. Carbon and oxygen isotopic studies of this carbonate yielded oxygen isotopes that potentially suggest a martian origin as well [6, 7] (Fig 1). Are Elephant Moraine A79001 Carbonates Terrestrial? Many of the ordinary chondrites collected in Antarctica exhibit some form of weathering, and studies have shown that carbonates are a typical weathering product [8, 9]. Velbel et al. [9] suggest that at least 5% ordinary chondrites collected in Antarctica show visible white crusts, while spectroscopic measurements suggest that this weathering may be ubiquitous [10]. The most well studied example of Antarctic carbonate formation would be LEW 85320 which has been shown to contain hydrated Mg-carbonate with an isotopic composition consistent with formation from terrestrial reservoirs [11]. In addition, the C signature of this carbonate weathering product suggests formation in the past 40 years [11]. Indigenous carbonate is rare in ordinary chondrites of higher petrologic type (types 4-6) which therefore can serve as reliable witness plates for Antarctic weathering processes. A few studies have analyzed the isotopic composition of carbonates in Antarctic ordinary chondrites [12, 13]. The carbonate analyses have focused primarily on meteorites recovered from the Allan Hills region with a few exceptions. When compared with data from the martian meteorites (Fig. 1) a number of interesting observations can be made raising some unanswered questions.

Since the post-9/11 wars began in Afghanistan and Iraq, leading Western militaries have been plagued by suicide in their ranks. Australia has been no exception and, as a result, the Australian Defence Force (ADF) has poured substantial medical and pastoral resources into suicide prevention.

Titan is the largest moon of Saturn with a gravity approximately 1/7 of Earth and an average surface temperature of ~94°K (-180°C) near the triple point of methane [1]. Titan’s atmosphere is four times as dense as Earth’s atmosphere, is composed of ~95% nitrogen and ~5% methane, and has a surface atmospheric pressure one and a half times that of Earth [2]. Extensive dunes on the surface suggest winds (at least seasonally) with aeolian transport of sediments [3]. Fluvial systems and lakes/seas of liquid hydrocarbons with lower viscosity than liquid water exist [4]. Exploration of this environment requires technologies capable of surviving cryogenic temperatures and hydrocarbon liquids. Solar power is not feasible for Titan surface operations due to the persistent haze that blocks the faint sun. Nuclear powered systems generate waste heat that could envelop an instrument in a methane gas cloud, or sink a hulled vessel from reduction in buoyant force as the hydrocarbon liquid boils. The goal of this proposal is to develop long lived planetary exploration platforms that operate at extremely cold temperatures using in situ resources for power, thus eliminating the need for a surface nuclear power source. We propose exploration of the Titan surface by harvesting wind energy. This technology proposal has been submitted to the NASA Innovative Advanced Concepts (NIAC) Phase I Step B process in Nov. 2017 with the slogan “going green on an orange moon”. The concept is to develop a Mobile Science Platform (MSP) that captures wind energy and converts it to electricity that is stored in a cryogenic superconducting capacitor, then to use the electrical energy to power a suite of instruments, communications equipment, and a propulsion system for the MSP (see Figure 1). Alternate propulsion systems are proposed for 1) solid surfaces with a Ground Rover Base (GRB), 2) liquid surfaces with a Lake Vessel Base (LVB), or a combination of both with an Amphibious Base (AB). This proposal includes many novel and exciting technologies for exploring Titan, including:  Energy capture from the atmospheric winds  Cryogenic electrical energy storage using superconductive materials  Biology instruments to detect possible microbial life in liquid hydrocarbons, lakebed sediments or lakeshore regolith  Scientific instruments to measure liquid hydrocarbon lake profiles, meteorology and subsurface, geological structures

The nature of the political world is changing, and this requires shifts in how we think about the role of universities in fostering and developing a strong civic culture, said Dennis Altman when presenting the sixth annual NTEU Lecture in Sydney in December.

When we interviewed Jenny Smith for a campaign video in December, she had only recently found out that she had a job for 2017. A contract researcher at the University of Tasmania for the last 18 years, Jenny has had 12 different jobs in this time, and never on a contract of more than 12 months. Lately the contracts have been no more than four months.

The martian surface contains features of ancient fluvial systems. Stable isotope analysis of carbonates that form in aqueous systems can reveal their formation conditions. The Nakhlite meteorites originally formed on Mars 1.3 Ga and were later exposed to aqueous fluids that left behind carbonate minerals [1], thus analysis of these carbonates can provide data to understand Amazonian climate conditions on Mars. Carbonates found in the Nakhlite meteorites contain a range of delta(sup 13)C values, which may be either martian carbonates or terrestrial contamination. To better under-stand terrestrial weathering products and martian carbonate formation processes, we conducted a set of carbonate isotope analyses on Antarctic meteorites focusing on Miller Range (MIL) Nakhlites as well as Ordinary Chondrites (OCs) (Figure 1)[1-11] [12]. OCs of petrology type H, L, and LL 3-6 were selected since they are not expected to contain preterrestrial carbonates, yet they have visible evaporite minerals on the fusion crust indicating terrestrial alteration. These cryogenically formed terrestrial carbonates may also provide an analog for cryogenic carbonate formation on Mars.