Jul 2026· Journal of Spacecraft and Rockets· pp. 1-13· 0 citations· 27 references
Abstract
The Mars Reconnaissance Orbiter (MRO) is uniquely qualified to meet objectives required by human missions to Mars. Landing site characterization capabilities include imaging for boulders and other terrain difficult for landing and/or driving, understanding soil properties for future construction, and locating resources such as subsurface ice deposits and caves. During the entry, descent, and landing phase, the Ultra High Frequency (UHF) radio can provide real-time data return, while several instruments can provide weather and atmospheric density information. The high-resolution imager can capture photos of a vehicle mid-descent and after touchdown. These capabilities could prove vital for determining the root cause after an anomaly. Once human presence on Mars is established, the UHF radio can provide positioning information, relay data from equipment placed outside of direct communication with the landing site, and serve as a backup voice communication system during extravehicular activities. Other MRO capabilities include creating stereo maps for extravehicular route planning, dust storm prediction and monitoring, atmospheric density measurements for aerobraking, improvement of spacecraft ephemerides to assist with precisely targeted landings, and finding lost hardware in orbit and on the ground. MRO remains healthy and retains sufficient fuel to operate until 2038.
The International Mars Prospecting Ride-Share System (IMPRESS) is presented here as a scalable, democratized, and low-cost mission architecture for distributed measurements on the martian surface and in the shallow subsurface. IMPRESS is intended to prospect on Mars in advance of sample return and human exploration. Its primary objective is to survey Mars for extant life, but it also supports geophysical, soil chemistry, resource, and landing-site risk assessments. Instead of relying on soft landers and drilling systems, IMPRESS deploys swarms of planetary penetrators that use descent kinetic energy to emplace instruments 0.2-1 m below the surface. This architecture provides spatial coverage, measurement replication, and mission redundancy. This increases the chance of detecting unevenly distributed biosignatures and gives negative results stronger context. Small penetrator platforms with standardized design, power, and communication interfaces lower the cost per experiment. The probes operate as independent nodes within a network, which enables time-correlated atmospheric, seismic, and environmental measurements that support the broader Mars exploration campaign. Repeatable mission deployments can range from small rideshare implementations with tens of penetrators to larger dedicated campaigns with hundreds or more. We describe the IMPRESS mission architecture, penetrator platforms, compatible payload classes, and how distributed shallow-subsurface surveys reduce scientific and operational uncertainty before future Mars surface activities. Key Words: Planetary penetrators-Mars-Extant life-Planetary protection-Distributed exploration-Rideshare. Astrobiology, XX, XXX-XXX.
Jan Špaček, Holden Alpern, Thomas Dineen et al.· Astrobiology· 0 citations
Unexpectedly following launch, the Lunar Trailblazer mission experienced software anomalies that led it to orient solar panels away from the sun and lose communication with Earth. This paper describes efforts to determine the spacecraft state and attempt recovery of the mission's science at the Moon. First, ground observatories at optical and radar wavelengths were engaged to maintain custody of the spacecraft and knowledge of its trajectory. Second, viability of recovery of the mission science objectives was established via testbed work to understand system behavior in fault conditions and determination of trajectories and maneuvers that would enable lunar orbit insertion. Third, optical photometry and radar doppler broadening were employed to determine Lunar Trailblazer's spin and orientation, using approaches similar to those in asteroid studies, to establish when solar panels might again receive sufficient power to boot the spacecraft and initialize its radio. Fourth, X‐band‐capable groundstations in addition to the NASA Deep Space Network were engaged to monitor for the spacecraft's radio carrier signal nearly continually, including crowd‐sourced monitoring and tip‐and‐cue style commanding. Lunar Trailblazer left the Earth‐Moon system and is in a 14‐year Earth return, heliocentric orbit. As it moved further away from Earth prospects for recovery became formidable; ultimately, the ability of the telecom system to return telemetry to Earth would have been insufficient to enable actions to recover the spacecraft, and the recovery attempt ended 6 July 2025. Lunar Trailblazer's mission recovery efforts illuminate capabilities in characterizing a 1–3.5 m3 size non‐cooperative object in cis‐lunar space.
B. Ehlmann, J. Bellerose, G. Lantoine et al.· Earth and Space Science· 3 citations
Sustainable human presence on the Moon and Mars requires surface infrastructure capable of supporting landing, refueling, cargo handling, and ISRU. This paper presents a systems architecture for extraterrestrial spaceports, informed by terrestrial logistics analogs (
e.g.,
port operations, ICAO standards) and space mission data (Artemis, Perseverance, VIPER). Key components include regolith-mitigating landing pads, autonomous construction using robotic excavators (
e.g.,
RASSOR), ISRU-to-propulsion chains (
e.g.,
Mars Oxygen In-Situ Resource Utilization Experiment, Sabatier reactors), and modular habitats. The analysis identifies key gaps: limited validation of ISRU-derived materials under lunar/Martian stressors, absence of standardized interface protocols for cross-provider interoperability, and insufficient power solutions for 14-day lunar nights or Martian dust storms. A phased implementation strategy is proposed, from robotic site surveys (2030s) to crew-tended hubs (2040s), prioritizing risk reduction through Earth-based analog testing and international standardization. The framework supports the emergence of an Interplanetary Logistics Grid but does not prescribe governance models. Instead, it offers a technically grounded foundation for infrastructure development aligned with COSPAR planetary protection and sustainability principles.
Abstract. Global Navigation Satellite Systems (GNSS) are becoming key enablers for autonomous operations beyond Low Earth Orbit (LEO). The Galileo Space Service Volume (SSV) offers strong potential for Earth Orbit Rising (EOR) missions, where spacecraft ascend from LEO to higher orbits using electric propulsion. This paper evaluates navigation performance achievable within the Galileo SSV for next-generation EOR missions using the JRC Integrated SSV Test Bench, which integrates realistic signal modelling, antenna patterns, and receiver dynamics. Two representative scenarios are analysed: a LEO–MEO transfer for a Galileo Second Generation satellite and a LEO–GEO transfer for a SATCOM platform. Results demonstrate that autonomous orbit determination is feasible with single-antenna configurations and moderate receiver sensitivity, confirming Galileo’s readiness, either alone or in conjunction with GPS interoperability to support autonomous orbit raising and guide future receiver design.
A. Piccolo· Materials Research Proceedin...· 1 citation
Future missions to Mars will require long duration operation of Environmental Control and Life Support System (ECLSS) technologies in deep space without resupply from Earth. Development of an integrated ECLSS for this application thus necessitates a redesign of traditional life support approaches used for low Earth orbit and Lunar expeditions. Closing the loop to reduce consumables and recapture valuable resources is a much higher priority. Additionally, reliability and maintainability become much larger considerations for long-term human space flight due to the complexity and impracticality of regular or emergency resupply. To facilitate the down-selection of suitable technologies for the next-generation ECLSS, a survey of historical and newly developed systems for habitat air revitalization was carried out. This paper summarizes technology options to be considered for air revitalization subsystems including carbon dioxide removal and reduction, oxygen generation, nitrogen resupply, trace contaminant control and particulate filtration, and Mars atmospheric processing. Basic functionalities and operational details of each technology are outlined, along with considerations concerning their feasibility for deep space exploration. Up-to-date sizing and performance data is also provided where available.
Charlie Priebe, Madeleine C. Oliver, Lawrence W. Barrett et al.· 55th International Conferenc...· 0 citations
The gravity on Mars is 3/8th of Earth gravity. The latest exploration Extravehicular Mobility Unit (xEMU) designed for lunar exploration is just under 400 lbm. While it would be reasonable for a crewmember to operate the xEMU on Earth’s Moon with 1/6 gravity, related studies have demonstrated that this same suit would not be feasible to operate on the surface on Mars. Studies involving Martian offloading are limited and the few available have demonstrated difficulty in suit operation with current advanced suit prototypes. Furthermore, deconditioning due to a long-term journey to Mars is expected to affect the overall suit mass that a crewmember can operate. This initial study aims to provide an initial mass requirement to bound the Mars spacesuit design within a reasonable range. It is expected that detailed Mars-simulation testing will subsequently refine the estimate to support Martian mission timelines. Considerations such as crew deconditioning due to the long exposure to microgravity, pressure garment system (PGS) weight offloading, restricted mobility increasing metabolic rate, and human fitness and size are combined into an initial assessment. Based on preliminary considerations, 230 lbm is recommended as a starting maximum Mars suit mass, which will be split between the PGS and Portable Life Support System (PLSS) subsystems.
R. Ogilvie, Ben Swartout, Bradley Hoffmann et al.· 55th International Conferenc...· 0 citations
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