Deployable Solar-Panel Hinge
- Role
- Independent project
- Dates
- Nov 2026 – present
- Status
- In progress
- Tools
- SolidWorks, ANSYS, MATLAB
- Project
- P03
Abstract
A torsion-spring hinge, latch and burn-wire release for a CubeSat solar panel, sized against NASA-STD-5017 to 173% torque margin at 30° preload.
The deployment runs in 0.20 s and arrives at the latch with a 206 N impact, with positive margin on every part across Monte Carlo runs on spring rate, friction and inertia. A lumped thermal model caught the release element early: the original 3 W heater needs 58 s to free the panel against a 10 s requirement, so it was re-specified to heat in about 0.5 s.
Deployment is filmed with high-speed video and compared frame by frame against the model, then put through a 50-cycle life test.
Take it apart
A torsion-spring hinge, a latch and a burn-wire release, shown stowed against the spacecraft wall. Scroll to take it apart.
- The assemblyWhat it is, put together.
- Taken apartKeep scrolling. Every part comes off along its own axis, the way it would on the bench.
- What each part doesClick any label, or any part, to see its name and why it is there.
Files
3 folders · 4 files · 1 open in the browser, nothing downloads. 3 files are not uploaded yet.
Analysis
P03 / 02_Analysis| Type | File | Rev | Date | Status | Open |
|---|---|---|---|---|---|
| P03_Gate1_Hand_Calcs.pdfWorked hand calculations | — | — | Planned |
CAD
P03 / 03_CAD| Type | File | Rev | Date | Status | Open |
|---|---|---|---|---|---|
| MD | P03_Hinge_Assembly.mdSolidWorks | — | — | Planned | |
| MD | Every part in the hinge, its spec and what it is for | A | Nov 2026 | Current |
Test
P03 / 07_Test| Type | File | Rev | Date | Status | Open |
|---|---|---|---|---|---|
| MD | P03_Deploy_Test.mdHigh-speed video | — | — | Planned |
| Item | Part | Spec | What it is for |
|---|---|---|---|
| 01 | Solar panel | — | The deployed blade. Its inertia sets the 0.20 s deployment and the energy the latch has to absorb at the end of the swing. |
| 02 | Torsion springs | — | Store the deployment energy. At 30° preload they give 173% torque margin against NASA-STD-5017. |
| 03 | Hinge pin | — | The single shaft the knuckles and the springs turn on. It comes out along its own axis, which is how the hinge is serviced. |
| 04 | Hinge knuckles | — | Carry the pin and fix the deployment axis. Friction here is one of the three variables the Monte Carlo runs sweep, alongside spring rate and inertia. |
| 05 | Latch | — | Catches the panel at full deployment. The arrival carries a 206 N impact load. |
| 06 | Burn-wire release | — | Holds the panel stowed until commanded. A lumped thermal model caught the original 3 W heater needing 58 s against a 10 s requirement, so the element was re-specified to heat in about 0.5 s. |
| 07 | Spacecraft wall | — | The face the hinge bolts to, and the datum the deployed angle is taken from. |
Item numbers match the numbered callouts on the exploded view. A dash means the part is on the model but carries no callout.
Not uploaded yet.