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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 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.

Researchers and other technology developers require regolith simulants that accurately emulate the properties of lunar, Martian, and asteroid soils to ensure that the processes, devices, tools, and sensors being developed will be usable in an active mission environment. To move toward higher fidelity regolith simulants, NASA has developed a system that takes typical regolith simulants and implants ions of relevant elements to better simulate the conditions of extraterrestrial soils. The ion implantation device developed here is composed of three key elements as shown in the figure below: two hopper and rotary valve elements and the acceleration grid structure. To perform the ion implantation, the system is first placed within a vacuum chamber, pumped down, and gases of the elements of interest are pumped into the chamber. The system then first passes a mass of granulated lunar regolith simulant through two stages of hoppers and rotary valves to condition the material. Key to the system is a process for interstitial gas removal (a source of contamination) as shown in the figure on the right. After conditioning, the regolith simulant is passed between two parallel electrodes under a high voltage, accelerating ions of the process gas and implanting those ions within the regolith simulant at controllable depths. The related patent is now available to license. Please note that NASA does not manufacturer products itself for commercial sale.

This NASA-developed eVTOL UAS is a purpose-built, electric, reusable aircraft with rotor/propeller thrust only, designed to fly trajectories with high similarity to those flown by lunar landers. The vehicle has the unique capability to transition into wing borne flight to simulate the cross-range, horizontal approaches of lunar landers. During transition to wing borne flight, the initial transition favors a traditional airplane configuration with the propellers in the front and smaller surfaces in the rear, allowing the vehicle to reach high speeds. However, after achieving wing borne flight, the vehicle can transition to wing borne flight in the opposite (canard) direction. During this mode of operation, the vehicle is controllable, and the propellers can be powered or unpowered. This NASA invention also has the capability to decelerate rapidly during the descent phase (also to simulate lunar lander trajectories). Such rapid deceleration will be required to reduce vehicle velocity in order to turn propellers back on without stalling the blades or catching the propeller vortex. The UAS also has the option of using variable pitch blades which can contribute to the overall controllability of the aircraft and reduce the likelihood of stalling the blades during the deceleration phase. In addition to testing EDL sensors and precision landing payloads, NASA’s innovative eVTOL UAS could be used in applications where fast, precise, and stealthy delivery of payloads to specific ground locations is required, including military applications. This concept of operations could entail deploying the UAS from a larger aircraft.