Session
Poster Session 1
Location
Salt Palace Convention Center, Salt Lake City, UT
Abstract
Environmental testing for small satellites often relies on separate systems to simulate space conditions, resulting in inefficiencies, increased operating costs, and challenges in accurately modeling the complex environment. This paper presents the conceptual design of an integrated testing platform that combines thermal, vacuum, solar, magnetic, navigation, and attitude control simulations into a single piece of hardware to provide reliable mission assurance. The design emphasizes the modifications required to overcome unique interactions between subsystems, enabling simultaneous, realistic environmental qualification of small satellites while reducing cost and complexity.
The fully integrated environmental testing system incorporates a thermal vacuum chamber (TVAC) with an integrated rotational platform, supporting dynamic attitude testing for attitude determination and control systems (e.g., magnetorquers, magnetometers, reaction wheels, star trackers, horizon sensors, and sun sensors). A solar simulation system replicates the UV, visible, and IR radiation for testing solar panel performance and thermal interactions. A magnetic field generation system using Helmholtz coils simulates Earth’s magnetic environment, while a GNSS simulator provides dynamic orbital navigation signals. Additional features include a star field projector for attitude determination tests, a horizon modeling system to replicate Earth’s thermal emissions and curvature, and an Earth albedo simulation module using collimated light sources and reflective Earth models.
This paper focuses on the design modifications needed to integrate these traditionally independent systems into a single platform. Unique challenges are addressed, such as managing heat buildup in the Helmholtz coils operating under vacuum conditions, providing three degrees of rotational freedom in a vacuum environment, and ensuring a uniform solar simulation within the constraints of thermal and vacuum conditions. Additional considerations include the interaction of simulated Earth albedo with horizon sensor testing, the effects of rotational platform vibrations on sensor calibration, and the alignment of star field projections with other dynamic subsystems.
Preliminary trade studies and modeling explore the feasibility of these design modifications, quantifying their impact on system performance and system cost. Results demonstrate that the integrated platform can operate these subsystems concurrently without significant performance degradation. Example use cases, such as CubeSats designed for Earth observation or interplanetary navigation, illustrate how the platform can validate mission-critical satellite subsystems in realistic scenarios.
By addressing the inherent challenges of subsystem integration, this conceptual design represents a significant advancement in small satellite environmental and functional testing. The proposed platform offers a unified, adaptable, and efficient solution for comprehensive small satellite qualification, addressing the increasing need for streamlined testing and reliable mission assurance.
Document Type
Event
Conceptual Design of an Integrated Small Satellite Environmental Testing Platform: Addressing Subsystem Integration Challenges
Salt Palace Convention Center, Salt Lake City, UT
Environmental testing for small satellites often relies on separate systems to simulate space conditions, resulting in inefficiencies, increased operating costs, and challenges in accurately modeling the complex environment. This paper presents the conceptual design of an integrated testing platform that combines thermal, vacuum, solar, magnetic, navigation, and attitude control simulations into a single piece of hardware to provide reliable mission assurance. The design emphasizes the modifications required to overcome unique interactions between subsystems, enabling simultaneous, realistic environmental qualification of small satellites while reducing cost and complexity.
The fully integrated environmental testing system incorporates a thermal vacuum chamber (TVAC) with an integrated rotational platform, supporting dynamic attitude testing for attitude determination and control systems (e.g., magnetorquers, magnetometers, reaction wheels, star trackers, horizon sensors, and sun sensors). A solar simulation system replicates the UV, visible, and IR radiation for testing solar panel performance and thermal interactions. A magnetic field generation system using Helmholtz coils simulates Earth’s magnetic environment, while a GNSS simulator provides dynamic orbital navigation signals. Additional features include a star field projector for attitude determination tests, a horizon modeling system to replicate Earth’s thermal emissions and curvature, and an Earth albedo simulation module using collimated light sources and reflective Earth models.
This paper focuses on the design modifications needed to integrate these traditionally independent systems into a single platform. Unique challenges are addressed, such as managing heat buildup in the Helmholtz coils operating under vacuum conditions, providing three degrees of rotational freedom in a vacuum environment, and ensuring a uniform solar simulation within the constraints of thermal and vacuum conditions. Additional considerations include the interaction of simulated Earth albedo with horizon sensor testing, the effects of rotational platform vibrations on sensor calibration, and the alignment of star field projections with other dynamic subsystems.
Preliminary trade studies and modeling explore the feasibility of these design modifications, quantifying their impact on system performance and system cost. Results demonstrate that the integrated platform can operate these subsystems concurrently without significant performance degradation. Example use cases, such as CubeSats designed for Earth observation or interplanetary navigation, illustrate how the platform can validate mission-critical satellite subsystems in realistic scenarios.
By addressing the inherent challenges of subsystem integration, this conceptual design represents a significant advancement in small satellite environmental and functional testing. The proposed platform offers a unified, adaptable, and efficient solution for comprehensive small satellite qualification, addressing the increasing need for streamlined testing and reliable mission assurance.
