Embedded Files
Introduction
Introduction
Various tests and analysis will be performed on the structure and its constituent parts throughout the projects lifetime. A summary of the tests, their status, and their results once completed are found on this page. This page is still under active development as part of finishing the Phase D schedule and deliverables.
Full Assembly Vibration Test
Full Assembly Vibration Test
Purpose
Purpose
The purpose of the full assembly vibration test is to certify the satellite as ready for launch. following the vibration test, a reduced functional test will be conducted to ensure electronics function as intended. The satellite will also be visually inspected for any fasteners backing out, that the deployable systems are intact, and that cracks did not form on the solar arrays.
Test Apparatus
Test Apparatus
The test apparatus, as seen in the attached figures to the right consists of the satellite inside the mock deployer which is then soft mounted between layers of bubble wrap and foam to the vibration table at the Magellan facility.
Required Materials and Tools
Required Materials and Tools
The Satellite
Nanoracks Mock Deployer
Seco SafeCell Anti-Static Bubble Wrap
Zotefoam Plastazote Foam (LD45FR)
Husky Ratchet Tie-Down straps (FH0942)
Eye bolts
Magellan vibration table
Test Set-Up
Test Set-Up
The test system will consist of Magellan's Vibration Table set up to use the Nanoracks soft mount vibration profile. The Satellite will be soft mounted onto the vibration table. The satellite will be tested to a provided random vibration profile for 60 seconds on each axis.
For Each Vibration Axis:
Place satellite within mock deployer, ensuring the RBF face is facing the +Y axis.
Layer soft mount materials as shown in the images to the right. Layers are Foam, bubble wrap, deployer, bubble wrap, and then foam again.
Test Procedures
Test Procedures
For each Axis, subject the satellite to the vibration profile shown below.
Unpack the satellite from the deployer once it has been vibrated in each axis.
Inspect for damage to the deployment mechanisms and thermistors.
Inspect that the deployments have not deployed.
inspect for any loose external fasteners
Inspect for any visible cracks in the solar panels
Inspect for any other forms of breakage to the satellite
Should any of the inspections fail, the satellite must be torn down and reassembled with fresh components that address the failed inspection.
Conduct the reduced functional test if inspections are passed.
First setup Satellite within Fit Jig and place on bubble wrap and foam layers
Second, place top layer of bubble wrap and foam, tie down with straps.
Results
Results
TBD
Rail Dimensional Inspection
Rail Dimensional Inspection
Purpose
Purpose
The purpose of this test is to ensure the corner rail ends are co-planer with each other when the satellite is assembled.
Test Apparatus
Test Apparatus
The test apparatus consists of the assembled satellite being placed on the granite table at the Magellan clean room. A feeler gauge is used to determine if the satellite corner rail ends are co-planar with each other.
Required Hardware
Required Hardware
Calipers
Magellan Granite Table
Ruler
Feeler gauge
Fully Assembled Satellite
Test Setup and Procedures
Test Setup and Procedures
Place the satellite vertically on the granite table in both the minus and positive Z orientations.
For each Z orientation slide the feeler gauge under each rail and determine if the rail ends are co-planar within +- 0.1 mm.
Should the inspection pass, log the results in a table below.
Should the results show non-co-planarity; one must re-assemble the satellite to ensure the rail ends are co-planar.
Test Results
Test Results
TBD
Fit Check
Fit Check
Purpose
Purpose
To ensure compliance with Nanoracks requirements for fitting into the deployer. The satellite structure's maximum dimension in the x and y axis must be 100 +-0.1 mm along the rail contact points.
Test Apparatus
Test Apparatus
The test apparatus consists of the Nanoracks Fit jig. The assembled satellite is placed into the satellite to ensure that the rail tolerances are within specifications. The satellite should be able to smoothly slide in and out of the fit jig without significant friction.
Required Tools
Required Tools
Satellite
Nanoracks Fit jig
Calipers
Test Procedure
Test Procedure
Measure the marked locations in the figure below using a caliper across the front, rear, left, and right faces to ensure dimensional compliance (100 +- 0.1mm).
Log caliper results
Should the caliper inspection pass, proceed to place the satellite into the Nanoracks fit jig.
Log whether the satellite successfully slid through the fit jig.
Fit Check Caliper Locations
Results
Results
TBD
Antenna Functional Test
Antenna Functional Test
Purpose
Purpose
Test Apparatus
Test Apparatus
Required Tools
Required Tools
Test Procedure
Test Procedure
Results
Results
Solar Panel Functional Test
Solar Panel Functional Test
Purpose
Purpose
Test Apparatus
Test Apparatus
Required Tools
Required Tools
Test Procedure
Test Procedure
Results
Results
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