← Back to NASA Technology Projects
Oscillating Heat Pipe Thermal Hinge for Passive Thermal Management
Completed
TRL 2 (started at 2, targeting 3)
Description
This proposal seeks two years of PhD level NSTGRO23 funding under Special Condition 1, given that the author previously received two years of Master’s level funding under NSTGRO21. The objective of this research is to develop a passively actuated, deployable radiator hinge for use onboard CubeSats. Heat will be carried from the CubeSat body to radiator panels for rejection through an Oscillating Heat Pipe (OHP) hinge made of Nitinol tubing. To provide CubeSat thermal management, as the Nitinol hinge increases in temperature, it will passively deploy radiator panels via the Shape Memory Effect (SME) to cool onboard components and then retract to minimize unnecessary heat rejection and the use of survival heating. This system will provide satellites with a dynamic thermal control system that has a high turndown ratio, low weight and cost, increased reliability, and high maximum heat rejection, among other advantages. Based on previous work by the author, this system will have a turndown ratio greater than 6, meeting the goal for variable geometry radiators in TA 14.2.3 “Heat Rejection” of the NASA Technology Roadmap. Previous work with deployable radiator panels are used to inform and accelerate the proposed work herein. However, this work focuses primarily on the deployable thermal hinge as a critical thermal management component. Outcomes include a functional benchtop prototype which allows for simultaneous OHP and SMA operation, a tuned thermal simulation of the system, and the relationship between the temperature of the CubeSat body and the radiator panel deployment angle.
Benefits
Having access to a deployable radiator with a high turndown ratio and high maximum heat rejection potential will enable small satellites to perform a wider variety of missions in more diverse locations (such as lunar orbit) while carrying high heat output instruments. Additionally, because our thermal control systems passive, it will provide additional benefits to small satellites including: increased reliability due to the lack of electronic control; redundancy in four panels operating in parallel; lower weight and cost relative to onboard power for heating cold-biased systems; and reduced system complexity.
Details
| Technology area | Thermal Management Systems > Thermal Control Components and Systems > Heat Rejection and Storage |
| Program | Space Technology Research Grants (STRG) |
| Lead organization | Brigham Young University-Provo, Provo, UT |
| Start date | 2023-08-01 |
| End date | 2025-07-31 |
Project contacts
Listed on TechPort itself — the most direct way to ask about this specific project.
How to get involved
This is early/mid-stage (TRL 2) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.
None of these are guaranteed paths for this specific project — TechPort itself doesn't have an "apply" button. Reaching out to the contact(s) above with a specific question is usually the fastest way to find out what's actually open.