Session
Science/Mission Payloads
Location
Salt Palace Convention Center, Salt Lake City, UT
Abstract
The 25 cm “V10” Monolithic Optical Payload has been developed through study phase design into a fully qualified system ready for on-orbit demonstration. This extends Lawrence Livermore National Laboratory’s monolithic telescope technology toward a rapidly fieldable, high performance space imaging system for small and medium spacecraft buses. Centered on the V10 monolithic Cassegrain optic in fused silica, the payload provides highly robust, diffraction limited performance with inherently maintained mirror alignment, eliminating complex on orbit alignment procedures and significantly reducing mechanical risk. The V10 optic is paired with a heritage focus mechanism and a panchromatic commercial off the shelf CMOS detectors, supporting imaging over a wavelength range of 450–1700 nm and enabling both near field and terrestrial imaging via an active focus mechanism. Our first on-orbit telescope will feature a 450-900nm visible band sensor.
The underlying monolithic optics technology is already demonstrated at scale, and this configuration preserves a credible path to Target Readiness Level (TRL) 9 and growth to apertures up to roughly 47 cm while maintaining the same basic architectural approach. At a nominal 500 km orbital altitude, the 25 cm system, coupled with a sensor with 2.4-micron pixels, is nominally designed to achieve NIIRS 4-5, providing tactically relevant spatial resolution for mission imaging, space domain awareness, and on-orbit characterization of resident space objects.
The optic is mechanically packaged in a carbon fiber housing with Hirth grooves and Viton containment to ensure stiffness, thermal stability, and robust environmental performance. The design targets a mass under 25 kg and a total payload volume below 27U (30 cm × 30 cm × 30 cm), making it compatible with a broad range of small satellite platforms. Standardized mechanical and electrical bus interfaces are complemented by an adaptable interface bracket that can be tailored to any specified bus geometry.
The mission concept emphasizes rapid integration and common bus compatibility. A proto qualification V10 payload, using the flight like 25 cm monolithic optic and housing, has been built and delivered for platform level integration and environmental test.
On orbit test planning is an integral part of the study. LLNL is collaborating with the bus integrator to support V10 payload assembly, test, and integration activities, including alignment verification, functional performance checks, and mission specific imaging modes. The on-orbit demonstration will validate optical performance, focus mechanism operation for near field and infinity focus, system jitter sensitivity, and the robustness of the standardized interfaces. Together, these activities are intended to mature the 25 cm Monolithic Optical Payload to a flight ready configuration that can be efficiently adapted to multiple missions and spacecraft platforms.
Document Type
Event
Scaling up Monolithic Optics Capabilities: 25cm Aperture and Beyond
Salt Palace Convention Center, Salt Lake City, UT
The 25 cm “V10” Monolithic Optical Payload has been developed through study phase design into a fully qualified system ready for on-orbit demonstration. This extends Lawrence Livermore National Laboratory’s monolithic telescope technology toward a rapidly fieldable, high performance space imaging system for small and medium spacecraft buses. Centered on the V10 monolithic Cassegrain optic in fused silica, the payload provides highly robust, diffraction limited performance with inherently maintained mirror alignment, eliminating complex on orbit alignment procedures and significantly reducing mechanical risk. The V10 optic is paired with a heritage focus mechanism and a panchromatic commercial off the shelf CMOS detectors, supporting imaging over a wavelength range of 450–1700 nm and enabling both near field and terrestrial imaging via an active focus mechanism. Our first on-orbit telescope will feature a 450-900nm visible band sensor.
The underlying monolithic optics technology is already demonstrated at scale, and this configuration preserves a credible path to Target Readiness Level (TRL) 9 and growth to apertures up to roughly 47 cm while maintaining the same basic architectural approach. At a nominal 500 km orbital altitude, the 25 cm system, coupled with a sensor with 2.4-micron pixels, is nominally designed to achieve NIIRS 4-5, providing tactically relevant spatial resolution for mission imaging, space domain awareness, and on-orbit characterization of resident space objects.
The optic is mechanically packaged in a carbon fiber housing with Hirth grooves and Viton containment to ensure stiffness, thermal stability, and robust environmental performance. The design targets a mass under 25 kg and a total payload volume below 27U (30 cm × 30 cm × 30 cm), making it compatible with a broad range of small satellite platforms. Standardized mechanical and electrical bus interfaces are complemented by an adaptable interface bracket that can be tailored to any specified bus geometry.
The mission concept emphasizes rapid integration and common bus compatibility. A proto qualification V10 payload, using the flight like 25 cm monolithic optic and housing, has been built and delivered for platform level integration and environmental test.
On orbit test planning is an integral part of the study. LLNL is collaborating with the bus integrator to support V10 payload assembly, test, and integration activities, including alignment verification, functional performance checks, and mission specific imaging modes. The on-orbit demonstration will validate optical performance, focus mechanism operation for near field and infinity focus, system jitter sensitivity, and the robustness of the standardized interfaces. Together, these activities are intended to mature the 25 cm Monolithic Optical Payload to a flight ready configuration that can be efficiently adapted to multiple missions and spacecraft platforms.
