Session
Poster Session 1
Location
Salt Palace Convention Center, Salt Lake City, UT
Abstract
Small satellite thermal vacuum tests involve securely mounting a spacecraft in a chamber, providing a representative thermal environment in the absence of convection. This study investigates the design of mechanical ground support equipment for supporting a range of spacecraft masses, from cubesats to ESPA-Grande class satellites of up to 500 kg, inside an existing thermal vacuum chamber. A system of four pieces of equipment is proposed to facilitate thermal vacuum testing, while keeping in mind various considerations such as the laboratory cleanroom environment, available floor space, the load capacity of the chamber rails, the thermal vacuum environment and the human factors involved. Each of these considerations are outlined and their implications on the mechanical design are discussed.
This equipment increases the load capacity of the chamber rails without modifying them by means of external support. It also securely holds the spacecraft and its associated test equipment inside the chamber while accommodating relative dimensional changes due to thermal expansion and creates conductive thermal isolation between the spacecraft and the chamber. The study describes requirements, proposes two operation sequences for inserting a spacecraft into the thermal vacuum chamber, presents elements of the design and its major thermal and structural analyses. These analyses use a combination of first-principle calculations as well as the finite-element method to reveal positive margins throughout, verifying the feasibility of this design for thermal vacuum tests of small satellites.
The project is currently completing its detailed design phase and will be assembled, tested and fully functional in late-2025.
Document Type
Event
Development of Mechanical Ground Support Equipment for Small Satellite Thermal Vacuum Testing
Salt Palace Convention Center, Salt Lake City, UT
Small satellite thermal vacuum tests involve securely mounting a spacecraft in a chamber, providing a representative thermal environment in the absence of convection. This study investigates the design of mechanical ground support equipment for supporting a range of spacecraft masses, from cubesats to ESPA-Grande class satellites of up to 500 kg, inside an existing thermal vacuum chamber. A system of four pieces of equipment is proposed to facilitate thermal vacuum testing, while keeping in mind various considerations such as the laboratory cleanroom environment, available floor space, the load capacity of the chamber rails, the thermal vacuum environment and the human factors involved. Each of these considerations are outlined and their implications on the mechanical design are discussed.
This equipment increases the load capacity of the chamber rails without modifying them by means of external support. It also securely holds the spacecraft and its associated test equipment inside the chamber while accommodating relative dimensional changes due to thermal expansion and creates conductive thermal isolation between the spacecraft and the chamber. The study describes requirements, proposes two operation sequences for inserting a spacecraft into the thermal vacuum chamber, presents elements of the design and its major thermal and structural analyses. These analyses use a combination of first-principle calculations as well as the finite-element method to reveal positive margins throughout, verifying the feasibility of this design for thermal vacuum tests of small satellites.
The project is currently completing its detailed design phase and will be assembled, tested and fully functional in late-2025.
