SCALPSS 2 (SCALPSS 2)

Stereo imaging of Plume Surface Interactions (PSI) during and through CLPS lunar descent and landing. High frame-rate imaging is to begin at an altitude above where PSI onset is expected in order to capture the morphology of the disturbed terrain. This imaging continues through lander descent in order to capture PSI onset, measure morphology changes, and determine the extent of surface obscuration. High frame-rate imagines continues through landing and dust settling in order to capture the morphology of the disturbed terrain after PSI. Additional imaging during the surface mission will also be collected in order to improve post-landing morphology through changes in the ambient lighting, including shaddowing effects. Photogrammetry is used to measure the surface morphology and thus estimate the extent of PSI erosion and site alteration. The collected data in-situ flight data can then be used to validate and anchor PSI computational and engineering models currently being developed in support of various system (including lander, surface and orbital) and system architecture designs.  The SCALPSS 2.0 payload hopes to improve upon the successfull SCALPSS 1.1 payload which  was formally selected for development as part of the CLPS 19D mission awarded to Firefly Aerospace which launched in January 2025 and landed on 2 March 2025, and the SCALPSS 1.x payload which will be delivered to Blue Origin for integration to the first Mk1 test flight planned for mid-2025 as part of the CLPS CT-3 mission. The SCALPSS 2.0 payload will utilize new electronics to improve data management and higher resolution cameras for improved science data.

​​Lunar dust is a significant obstacle to achieving a sustainable human presence on the Moon, and lunar landers will be a major source of dust transport across the lunar surface. There is currently a lack of lunar flight data from plume-surface interaction (PSI) effects during descent and landing which leads to one of the greatest source of risks during the landing phase. Safety and operational risks due to lander-induced dust, erosion , and ejected material are significant drivers of dust mitigation technology development, lander designs, lunar surface element designs, lunar orbital element designs, and surface operations. As NASA and commercial companies prepare to land larger and larger payloads (growing to human scale) on the lunar (and eventually Mars) surface, these landers will be required to employ increased engine thrust resulting in plume interactions with the lunar surface to become more and more extensive, while at the same time, requiring even higher reliability than their predecessors.​

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