Structure Verification 1150-Upward

Introduction

Continued verification activities for the Structure Subsection items 1150 through 1400

V-MEC-1150 - Permanent Magnets - Verified

Parts lists will be reviewed. There are no magnets on the design. Refer to Bill of Materials

V-MEC-1170 - Inhibit Switch - Verified

Satellite inhibit switch is contained in the PWR module, drawings, location and part drawings are available in ICD page.

V-MEC-1180 - Deployable Batteries - Verified.

Deployment systems do not use batteries after review. Refer to Bill of Materials

V-MEC-1200 - Deployable Capacitors - Verified

Confirm that the deployable systems do not contain or use capacitors.

No capacitors used after review.

V-MEC-1220 - LIPO Batteries - Verified.

No batteries in the PWR module use LIPO Batteries. Refer to Bill of Materials

V-MEC-1240 - Battery Bridging - Verified

All electrical connectors to batteries are wrapped with Kapton tape to prevent accidental bridging

V-MEC-1250 - PWR module wire holding - Verified

All electrical connectors to batteries are mounted to structural components to prevent movement between wires and structure components.

V-MEC-1300 - UHF Antenna Position - Verified

The UHF antenna is on the +Z face of the satellite.

V-MEC-1310 - Antenna Position - Verified

The COMS module wall thickness is 2mm. As a result the antenna cannot be positioned any closer to the +Z face of the satellite. Refer to COMS ICD

V-MEC-1320 - Mounting of Thermal Sensors - Verified

Mounting of thermal sensors is shown in PWR ICDs

V-MEC-1330 - COMS U-LOOP - Verified

An access port to the COMS U-LOOP has been added to the COMS Module and is shown in the COMS ICD's

V-MEC-1340 - Solar Panel Mounting - Verified

Solar Panels are mounted to the +X face of the satellite and are shown on the ICD page.

V-MEC-1350 - SunSensor Mounting - Verified

SunSensors are mounted to the -X face of the satellite and are shown on the ICD page.

V-MEC-1360 - 1/2 U Shell design - Verified

Interconnecting 1/2 U shell models are used to make the major structural components. Drawings are shown in the ICD page.

V-MEC-1370 - 1/2 U Assembly - Verified

Corner features shown in 1/2 U SHELL drawings are symmetric about the X and Y faces which allows four different positions and orientations to be used in assembly

V-MEC-1380 - Antenna Functionality test - Verified

Test results for the antenna function test on the flight model. The main purpose of this test is to confirm that unmodeled components in the COMS module do not interfere with the function of the Antenna deployment, connectors, wires are not planned to be modeled and may add additional friction or resistance to the deployment

V-MEC-1390 - Solar Panel Secondary holding system - Verified

A double melt wire design is used for the solar panels.

V-MEC-1400 - Antenna Secondary holding system - Verified

A double melt wire design is used for the antennas panels.

V-MEC-1410 - Post Vibration Deployment Test on Solar Panels - Verified

After the satellite has completed the vibration test the solar panels will be commanded to deploy. Once successful deployment has been achieved the solar panels will be reset for the next stage of testing

V-MEC-1430 - Post Thermal Chamber Deployment Test on Solar Panel System - Not Started

After the satellite has completed the Thermal cycling test the solar panels will be commanded to deploy. Once successful deployment has been achieved the solar panels will be reset for the next stage of testing

V-MEC-1440 - Post Thermal Chamber Deployment Test on Antenna System - Not Started

After the satellite has completed the Thermal cycling test the Antenna system will be commanded to deploy. Once successful deployment has been achieved the antennas will be reset for the next stage of testing

V-MEC-1445 - Installation inspection - Not Started

Installation inspection of battery enclosure surfaces, wire insulation, accidental bridging, wire restraints, and external sharp corners

#TODO inspection document to be created for this that outlines all parts to be inspected and how to be inspected

V-MEC-1450 - Pre Vibration Deployment Test of the Solar Panel System - Not Started

After the satellite has been assembled, the Solar panel deployment system will be commanded to deploy. Once successful deployment has been achieved the Solar panels will be reset for the next state of testing.

V-MEC-1455 - Integration Solar Panel Functional Test - Not Started

The Solar Panel deployment system will be commanded to fire during integration testing to confirm that installation was performed correctly and that all components are functioning as intended

V-MEC-1460 - Pre Vibration Deployment Test of the Antenna System - Not Started

After the satellite has been assembled, the Antenna deployment system will be commanded to deploy. Once successful deployment has been achieved the antenna system will be reset for the next state of testing.

V-MEC-1465 - Integration Antenna Function Test - Not Started

The Antenna deployment system will be commanded to fire during integration testing to confirm that installation was performed correctly and that all components are functioning as intended

V-MEC-1470 - Foot Switch Max Force - Not Started

After the power module has been assembled, each foot switch will be measured to determine the maximum force that it produced using a force gauge (or scale). Each spring will be confirmed to not individually exceed 3N.

V-MEC-1480 - Foot Switch Total Force - Not Started

After the power module has been assembled, the power module will be compressed as a whole against a scale and the total force to compress all four springs will be confirmed to not exceed 9N total.

V-MEC-1490 - No Structure System Battery - Verified

Review of the structure subsystem design to confirm that no battery is used.

V-MEC-1500 - Measure the corner rail clearance - Not Verified

Corner rails will be measured to confirm they meet the 6mm clearance, rail-to-rail dimensions specified by nanoracks, ends are coplanar and the lengths are 340.5 mm and the ends remain bare.

V-MEC-1420 - Post Vibration Deployment Test on Antenna system - Not Started

After the satellite has completed the vibration test the deployable antennas will be commanded to deploy. Once successful deployment has been achieved the antennas will be reset for the next stage of testing

V-MEC-1501 - Final Fit Check - Not Verified

Flight model satelite will be assembled and fit checked against the nanoracks deployer prior to vibe test to confirm the sat will meet dimensional spec.