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NASA’s LESSH BCM is a compact, high-performance, ruggedized system designed to support extended science operations in harsh lunar environments. With a mass of 9.4 kg and dimensions of 50 x 25 x 10 cm, the BCM is engineered for seamless integration with the interface bank on the HLS. A 1.5-meter flexible harness with an EVA-compatible connector and removable dust cover enables reliable operation in austere environments. Astronaut-operated controls, such as a guarded power switch and LED indicators, simplify usability and reduce the potential for errors during high-stakes lunar operations. The BCM is optimized for safety and efficiency, incorporating state-of-the-art power and charging capabilities. It supports charging of 28V astronaut-rated batteries with a power output rated at 215W and integrates a battery pre-heater to maintain optimal performance in extreme temperatures. The BCM features a 4-hour charge time with software adjustability for charging parameters such as current, voltage, overvoltage, and undervoltage setpoints. Battery longevity is ensured through passive rebalancing of cell voltages and advanced safety features. Its 2-fault tolerant hardware and adjustable safety setpoints safeguard against potential hazards. Additionally, the BCM supports 1000BASE-T Ethernet pass-through for high-speed data transfer. Originally designed to extend the length of lunar surface science experiments by enabling astronauts to recharge instrumentation, NASA’s LESSH BCM may be desired by companies seeking to operate sensors on the lunar or Martian lunar surface. The design may also be suitable for terrestrial applications involving harsh environments where interchangeable sealed sensors must operate on their own or with rovers, robotics, and drones. The BCM is at technology readiness level (TRL) 4 (component and/or breadboard validation in lab) and is available for patent licensing.

WaveRider is a form of EDS technology that uses wires or insulated metal rods held a few millimeters above a substrate that is laden with dust. The wires carry a high-voltage AC square-wave signal. As the wires are moved across the surface, the dust is repelled and moves away from the wires until the whole surface is cleaned. The benefit of WaveRider over traditional EDS is that it can work on any surface, whereas traditional EDS only works with an insulating top coat. This would be a concern to any spacecraft that uses a statically dissipative surface as it's exterior top coat, and would require something like WaveRider to remove dust. Additionally, It may be beneficial to have moving wires as opposed to just having stationary electrodes for optically reliant surfaces (such as mirrors, solar panels, and helmets), as stationary wires can affect visibility. Also, because it uses wires, it can conform to irregularly shaped surfaces such as astronaut helmets or curved radiator surfaces. Moving electrodes may also offer fewer integration complexities compared with embedding stationary electrodes above the surface, since it may save weight and is structurally less complex. Electrodes on top of a surface don't place any burden on integrating it within a system (e.g., traditional EDS needs to be embedded inside cover glass for solar panels, inside O-rings/gaskets, or beneath the surface of a thermal control coating for radiators). It won't affect the properties of a coating, and there are no issues with how well it adheres to a surface like there are with traditional EDSs. Due to the nature of the technology, WaveRider could be adapted into a handheld tool that would allow much more ease of use, which is a freedom that astronauts wouldn't have if the system was built into a spacesuit or built into a machine.

RUM's body provides a number of features designed to achieve effective performance in a number of tasks. These tools include a scoop, regolith storage compartment, a self-cleaning sieve, de-blinder mechanism, two shaker motors, a vibro-compactor surface, a grader blade, a rock removal pry bar, and a surface for geotechnical measurements. The top of the scoop body includes storage for sensors, and additional room for other features. RUM can also be outfitted with additional sensors, quick attachment mechanisms, and geotechnical testing tools. The bottom surface of RUM's excavator blade has a flat plate surface which is used primarily for compaction but can also be used to smooth surfaces. The capability to conduct compaction of in-situ soils up to and beyond 100% relative density is made possible by tunable, high-impact tamping and high-frequency vibrations (or any combination of the two).The sides of the scooping area are used when measuring bulk density and relative density, and allow for a smooth trench wall to be formed. RUM's blade edge can be used for rigorous tasks such as rock removal and prying. Size screened regolith is required for both construction and ISRU operations, RUM has the capability and sort regolith below 1mm particle size at 10-40 grams per second without clogging. In addition to sorting regolith. RUM can measure soil shear using an attached grader blade, conduct pressure sinkage testing of regolith bearing and trafficability properties, regolith angle of repose, and regolith density using photogrammetry and known volume samples.

NASA’s reverse-ephemeris lunar navigation system is a concept for determining position on the lunar surface based on known orbits of satellites. In conventional GPS navigation systems, the GPS satellite transmits ephemeris data to a receiver on earth for determining position at the receiver location. Whereas for the reverse-ephemeris approach the receiver becomes the transmitter, and the satellite instead serves more as a fixed reference position with a known ephemeris. This simplifies the satellite requirements and also mitigates potential navigational disruptions that can otherwise arise in navigation systems that utilize satellite-based communications, for example from interference, jamming, etc. The design consists of lunar surface S-Band (2,400 – 2,450 MHz) 10 W transceivers ranging with analog translating transponders on a three-satellite constellation in frozen elliptical orbits to provide continuous coverage with service to 300 simultaneous users over 1.8 MHz of bandwidth at the transponder. Digital bases systems are possible too. As compared to GPS-based navigation requiring four or more satellites costing 100’s of millions of dollars, the new NASA concept is based on using only three smallsats.

NASA’s Universal Modular Interface Converter (UMIC) is a bidirectional, modular power electronics converter that transfers power between a 120 V DC space power bus, and a medium-to-high-voltage, three-phase AC power grid. The UMIC system contains multiple parallel AC/DC UMIC modules that convert between 120 V DC and low voltage AC, as well as one or more transformers that convert power from the low voltage AC bus to the grid voltage. The UMIC module consists of multiple subsystems, including the power stage, gate driver, Field Programmable Gate Array (FPGA)-based controller, output filter, signal conditioning and sensing circuits, and thermal management subsystems. An FPGA-based controller is included within each AC/DC module and is used to regulate desired power system variables; synchronize power switching events and share load current between modules; synchronize the modules with existing service on the grid; receive commands; and share telemetry. The FPGA-based controller subsystem includes the FPGA Integrated Circuit, associated flash memory, and a controller area network (CAN) transceiver. It is envisioned that future UMIC designs can support lunar grid expansions, a Mars surface grid, or large space stations. These applications may necessitate different grid voltages or frequencies, or different control logic and communication systems. However, the core UMIC architecture and functionality will remain the same. The related patent is now available to license. Please note that NASA does not manufacture products itself for commercial sale.

The SSS-Joint is an interlocking joint system for joining structure components such as struts, flat truss frames, and volumetric truss bays together to build bigger and more complex structure systems. The SSS-Joint interface can be applied to various connection scenarios commonly found in truss structure assembly, including but not limited to strut-to-strut connections, strut-to-node connections, and half-node-to-half-node connections. By incorporating half-node joints, the number of standalone components can be reduced by over 52%, and assembly steps can be decreased by over 65% compared to traditional truss tessellations without half-nodes. In the current design, a single screwdriver can assemble all connections. The interlocking geometry of the SSS-joint features built-in guiding elements to aid the alignment process. Once in place, the screwdriver can rotate and engage with the spring-loaded captive lock-screw on the joint. The screwdriver tip does not need to be perfectly aligned, as the spring-loaded lock-screw will automatically pop into place within half a rotation after contact. This design dramatically reduces the complexity of the assembly process and eliminates the need for loose fasteners or specialized tools. The SSS-joint offers a robust, lightweight, and scalable solution for modular structural assembly in space and terrestrial applications alike. The SSS-Joint has reached Technology Readiness Level (TRL) 5 (validated in a relevant environment) and is available for patent licensing.

NASA’s adaptive camera assembly possesses a variety of unique and novel features. These features can be divided into two main categories: (1) those that improve “human factors” (e.g., the ability for target users with limited hand, finger, and body mobility to operate the device), and (2) those that enable the camera to survive harsh environments such as that of the moon. Some key features are described below. Please see the design image on this page for more information. NASA’s adaptive camera assembly features an L-shaped handle that the Nikon Z9 camera mounts to via a quick connect T-slot, enabling tool-less install and removal. The handle contains a large tactile two-stage button for controlling the camera’s autofocus functionality as well as the shutter. The size and shape of the handle, as well as the location of the buttons, are optimized for use with a gloved hand (e.g., pressurized spacesuit gloves, large gloves for thermal protection, etc.). In addition, the assembly secures the rear LCD screen at an optimal angle for viewing when the camera is held at chest height. It also includes a button for cutting power – allowing for a hard power reset in the event of a radiation event. Two large button plungers are present, which can be used to press the picture review and "F4" buttons of the Nikon Z9 through an integrated blanket system that provides protection from dust and thermal environments. Overall, NASA’s adaptive camera assembly provides a system to render the Nikon Z9 camera (a) easy to use by individuals with limited mobility and finger dexterity / strength, and (b) resilient in extreme environments.

The new transparent EDS technology is lighter, easier to manufacture, and operates at a lower voltage than current transparent EDS technologies. The coating combines an optimized electrode pattern with a vapor deposited protective coating of SiO2 on top of the electrodes, which replaces either polymer layers or manually adhered cover glass (see figure on the right). The new technology has been shown to achieve similar performances (i.e., over 90% dust clearing efficiency) to previous technologies while being operated at half the voltage. The key improvement of the new EDS coating comes from an innovative method to successfully deposit a protective layer of SiO2 that is much thinner than typical cover glass. Using vapor deposition enables the new EDS to scale more successfully than other technologies that may require more manual manufacturing methods. The EDS here has been proven to reduce dust buildup well under vacuum and may be adapted for terrestrial uses where cleaning is done manually. The coatings could provide a significant improvement for dust removal of solar cells in regions (e.g., deserts) where dust buildup is inevitable, but water access is limited. The EDS may also be applicable for any transparent surface that must remain transparent in a harsh or dirty environment. The related patent is now available to license. Please note that NASA does not manufacturer products itself for commercial sale.

NASA’s Passive PCB-Mounted Thermal Switch uses a heat pipe that extends from the electronics enclosure wall to the center of the electronics board. The switch includes a wax actuator that extends when warm. The extending piston on the actuator pushes the heat pipe against the anvil of the mechanism, which then provides a low-resistance heat path to the wall of the enclosure. When the wax actuator drops below a certain temperature, the piston retracts. A spring then pushes the heat pipe away from the anvil, breaking thermal contact and conserving heat. A series of insulating materials is used to reduce unwanted heat transfer through the springs. The mechanism is mounted to the board with a thermal interface material and screws to provide high contact pressure and thermal conductivity between the board and the mechanism. Additional heat straps are used to carry heat directly from particularly hot components. A key advantage of this NASA invention is that it does not require any energy input for operations (i.e., it is completely passive). In spaceflight applications, this enables significant mass savings as heaters can represent up to 50% of electronics systems’ power consumption. Given that typical battery chemistries stop functioning at approximately 0C, additional power is required to keep the batteries themselves warm. Thus, reducing heater power requirements by 50% could reduce overall energy storage requirements by approximately 70% – leaving more capacity for sensors, fuel, or other priorities. NASA’s switch is particularly useful for spaceflight applications where electronics are exposed to long bouts of extreme heat and cold, such as on the Moon (where the day-night cycle lasts 14 days with nighttime lows near -173C and daytime highs near 127C), or in deep space. Lunar landers and lunar infrastructure developers might be ideal end-users of the invention. Other applications where electronics experience extreme temperatures may benefit from this NASA innovation.

The jointly developed interlocking paver design consists of a molded solid material with tapered interlocking features that interface with features of an opposite gender in three orthogonal directions. This establishes a toleranced connection between the pavers that locks down six degrees of freedom. More specifically, the system consists of two types of pavers: polygon and spacer pavers. Both are symmetrical about the longitudinal and transverse axes and are designed to interlock securely with one another in a checkerboard pattern. The polygon paver features an octagonal top level and a rectangular bottom level with protrusions and recessed notches. The spacer paver has an elongated center portion with isosceles trapezoid extensions on the top level and a rectangular bottom level with protrusions and notches. The interlocking design locks down six degrees of freedom, providing enhanced stability and preventing the flow of exhaust gases between the seams to mitigate erosion of the underlying regolith. The pavers could be constructed leveraging in-situ resource utilization (ISRU). Lunar regolith has been identified as a potential construction material. Additionally, the pavers could be installed via robotic assembly, reducing the need for human labor in harsh environments.