Structure Verification 0540-0780

Nanoracks requires surface hardness to be equal or greater to anodized aluminum which is stated to be Rockwell 65-70. The rails are composed of 6061 Aluminum which has been Black anodized by price industries using the type 2 class 2 10-18 micron method which satisfies the requirement. Price Anodizing Brochure

V-MEC-0590 - Corner Rail Surface Roughness - Verified

Roughness vs. Grit charts indicates polishing above 80 grit to achieve a surface roughness that is less than 1.6 microns. The anodized rails were polished with emery cloth with a grit value of 280, thus ensuring the surface roughness will satisfy the requirement.

V-MEC-0600 - 4 x Corner Rails - Verified

Four corner rails are shown in the Structure ICD ICD Link.

V-MEC-0610 - Deployables Held In Place - Verified

There are two deployable systems, Solar Panels and Antenna systems. These systems will both be held in place and launched using a burn-wire system. Spiderwire fishing line will be melted using a 2 amp resistor heated above the melt point of the fishing line. These components are independent of the Nanoracks deployer.

V-MEC-0620 - Passive Structure - Verified

No part of the structural subsystem has any powered components as illustrated in the ICD Block Diagram. Submodules themselves contain the powered components comprising the internals of the satellite. Structural Assembly ICD

V-MEC-0630 - Deployable Mechanism - Verified

There are two deployable mechanisms solar panels and antenna deployment, neither of which use the Nanoracks deployer as part of their deployment plan, at the highest level these are demonstrated in their Design Overview pages: Deployment Systems

Both systems utilize a burn wire system consisting of spiderwire fishing line in contact with a 2 amp resistor.

V-MEC-0640 - Antenna Prototype Test - Verified

Antenna prototype test results will be listed here on completion. link

This test will perform a minimum of 10 consecutive test launches of the antenna deployment system using 3D Printed EM models of the antenna deployment system, this does not include an aluminum shell of the satellite, only the mounting and hinging components. Parts will be built in-house at the UofM when possible.

Pass criteria will require that the Antenna deploys parallel to the front of the satellite +- 10 degrees.

V-MEC-0641 - Solar Panel Prototype Test - Verified

Solar Panel deployment prototype test results will be listed here on completion. link

This test will perform a minimum of 10 consecutive test launches of the solar panels deployment system using 3D printed EM Models for the Wing deployment system and dummy masses for solar cells, this does not include an aluminum shell of the satellite, only the mounting and hinging components. Parts will be built in-house at the UofM when possible.

Pass criteria will require that the solar panels deploy parallel to the front of the satellite +- 10 degrees.

V-MEC-0650 - Independent Firing - Verified

The two deployable systems are fired independently from the structure system, i.e. structure cannot control the firing. The firing is handled by the power subsystem and is specified in this link.

To make sure that the two systems are able to be fired independently two separate mechanical systems are being designed. The location and separation for the two are shown in the Solar Panel Burn Assembly ICD and the COMs module antenna assembly ICD .

V-MEC-0660 - Redundant Holding Systems - Verified

There are two deployable systems that will need to meet this verification action, Solar panel deployment and antenna deployment

Solar Panel Deployment:

As planned the solar panels will be held in place using two sets of melt wire and each will wrapped around a metal tube which will hold a resistor. If one melt wire snaps during launch, the second will continue to hold it in place.

Antenna Deployment:

As planned the antenna will be held in place using two sets of melt wire and each will wrapped around a vertical knob which will hold a resistor. If one melt wire snaps during launch, the second will continue to hold it in place.

V-MEC-0670 - Redundant Firing Systems - Verified - Non-Compliant

There are two deployable systems that will need to meet this verification action, Solar panel deployment, and antenna deployment. Both systems use a single burn resistor to melt fishing line and release the deployable system.

V-MEC-720 - Plunger switch location - Verified

No pusher/plunger style switches are used in the structure subsystem. However, due to the design of the deployment switch this verification is still considered relevant. The deployment switch design keeps all three deployment switches and the force balance switch on the -Z face of the satellite. ICD

V-MEC-730 - Switch Contact - Verified

We are using Switches in a plunger design, as such the requirement that switches stay compressed along 75% of Nanoracks deployer length does not apply.

V-MEC-740 - Foot Switch Type - Verified

The foot switch design uses lever style switches which is currently demonstrated in the partial PWR assembly shown on the Structure ICD. Link

V-MEC-750 - Switches Within X-Y faces - Verified

The 4 switches are assembled within the power shell module as shown on the ICD page and thus lie within the external X and Y faces of the satellite. Structural ICD Overview

V-MEC-760 - Captive Foot Switch - Verified

Lever switches in conjunction with plunger pins will not generate debris when engaged or disengaged.

V-MEC-770 - Max force per switch - Verified

Maximum force for one separation pin is 2.14N. Spring Datasheet

V-MEC-780 - Max force for all switches - Verified

Maximum force of all four separation pins is 8.56N. Spring Datasheet

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