Structure Verification 0800-1130

Introduction

Continued verification activities for the Structure Subsection items 0800 through 1130

V-MEC-0800 - Intermodule electrical wire spacing - Verified

The Base shell which all modules are constructed from shown in this link to drawing, has a space set aside to allow for electrical pass through in zone C7 and D7, 14mm by 7mm. This space allows for at least 6 wires to connect between modules

V-MEC-0810 - Data line between Modules - Verified

Space for the data line has been met by verification activity V-MEC-0800. Ensuring that a single data line will be met by drawing of the intermodule wiring harnesses.

V-MEC-0820 - ADCS module power line space - Verified

This verification item will be illustrated in a machine drawing shown on the structure ICD page

V-MEC-0830 - ADCS module data line space - Verified

This verification item will be illustrated in a machine drawing shown on the structure ICD page

V-MEC-0840 - Power module Umbilical Access - Verified

This verification item will be illustrated in a machine drawing shown on the structure ICD page

V-MEC-0840 - Power module Umbilical Access - Verified

This verification item will be illustrated in a machine drawing shown on the structure ICD page

V-MEC-0850 - Power Module Umbilical access - Verified

This verification item will be illustrated in a machine drawing shown on the structure ICD page

V-MEC-0860 - Solar Panel wire space - Verified

This verification item will be illustrated in a machine drawing shown on the structure ICD page

V-MEC-0880 - Thermal coating possibility - Verified

External surface of the satellite has been Black anodized by price industries using the type 2 class 2 10-18 micron method which satisfies the requirement

V-MEC-0900 - Payload radiation windows - Verified

A window has been added to the payload module shells and is shown in the payload module drawings and working volume. Payload Working Volume

V-MEC-0910 - COMs UHF antenna - Verified

COMS utilizes one antenna. ICD drawings specify it deploys on the -X face of the satellite Coms ICD

V-MEC-0920 - Two Deployable Panels - Verified

Solar Panel ICD shows that there are 2 deployable panels. Solar Panel Assembly ICD

V-MEC-0930 - Solar panel deployment mechanism - Verified

The solar panel deployment mechanism described here: Link

V-MEC-0940 - Antenna deployment mechanism - Verified

The antenna deployment mechanism described here: Link

V-MEC-0950 - Antenna Test - Not Started

The antenna deployment system will be tested using parts designed and built to the final launch specifications and drawings as designed. Two types of tests will be performed. Release test and Hold test

Test 1: Release:

When controlled by a suitable stand-in for the power module the antenna system will deploy perpendicular to the side of the satellite. The test will be considered a pass if the antenna is deployed to +- 10 degrees to satellite side surface in the XY plane about the Z-axis. Electrical contact to the antenna must be maintained. This test will be performed 5 times and if the engineering model performs 5 successive tests without repairs to any component (aside from resetting the consumable release mechanism) the design will be considered acceptable for flight. If repairs are required to any components the deployment system will be disassembled completely and rebuilt to spec including any modifications to prevent failure. 5 successive deployments with no modification will be performed before the design is considered acceptable for use.

Test 2: Holding:

The antenna will be coiled, stowed and the burn-wire mechanism will be manually reset in the launch state. Once in the stowed position, the antenna 'door' will have a force gauge attached to the furthest point from the axis of rotation. The force gauge will then be used to pull against the door at a slow steady rate until the door opens. If the force required to break the holding mechanism and force the door open is more than the maximum force expected during launch then the test will be considered a pass. 5 separate tests are required with new, untested consumable burn wires for each test. If less than 5 tests pass, the mechanism/melt-wire will be reevaluated and the count will be reset to zero.

V-MEC-0960 - Solar Panel Deployment Test - Not Started

The solar panel deployment system will be tested using parts designed and built to the final launch specifications and drawings as designed. Two types of tests will be performed. Release test and Hold test

Test 1: Release:

When controlled by a suitable stand-in for the power module the solar panel system will deploy perpendicular to the side of the satellite. The test will be considered a pass if the antenna is deployed to +- 10 degrees to satellite side surface in the XY plane about the Z-axis. Electrical and data contact to the solar panels must be tested and maintained. This test will be performed 5 times and if the engineering model performs 5 successive tests without repairs to any component (aside from resetting the consumable release mechanism) the design will be considered acceptable for flight. If repairs are required to any components the deployment system will be disassembled completely and rebuilt to spec including any modifications to prevent failure. 5 successive deployments with no modification will be performed before the design is considered acceptable for use.

Test 2: Holding:

The solar panels will be stowed and the burn-wire mechanism will be manually reset in the launch state. Once in the stowed position, the solar panels will have a force gauge attached to the furthest point from the axis of rotation. The force gauge will then be used to pull against the door at a slow steady rate until the door opens. If the force required to break the holding mechanism and force the door open is more than the maximum force expected during launch then the test will be considered a pass. 5 separate tests are required with new, untested consumable burn wires for each test. If less than 5 tests pass, the mechanism/melt-wire will be reevaluated and the count will be reset to zero.

V-MEC-0965 - Melt Wire test to confirm it will survive - Verified

Test the melt wire candidates to identify and confirm the size will hold the solar panels and antenna in place

The Various candidates that passed the Creep test were subject to burn time testing. The spider wire performed the best at under 2 seconds to burn.

Link

V-MEC-0970 - Pressure Vessels - Verified

No pressure vessels are currently used in the structure subsystem.

After inspection of each module, there are no pressurized vessels present on the design.

V-MEC-0980 - Import Control - Verified

All hardware components can be purchased from local vendors and all machined parts can be conducted without requiring specialized companies to perform the task. Refer to the Parts list: link

V-MEC-1000 - Internal Power Storage - Verified

The only part of the satellite that has internal power storage is the PWR module. The batteries in the PWR module are stowed inside the PWR module as shown on the PWR module mechanical assembly drawing Link

V-MEC-1020 - Hazard Prevention - Verified.

All mechanical components with sharp edges that can be accessed from the outside once built will have callouts that round and blunt all edges and corners for the purpose of preventing a handler from injuring themselves.

Deployable systems are being sized and designed such that if an accidental pre-release occurs that no injury of a handler will happen. Solar Panel calculations.

The deployable mechanisms after testing do not deploy with enough force to injure a person.

V-MEC-1030 - Electrical Discharge Prevention - Verified

satellite electronics are grounded together to the satellite shell through a primary ground located on Power Module shell which connects to the power PCB.

V-MEC-1040 - Deployment Direction - Verified.

Final structure design was used to confirm this.

Separation switches face the -Z direction.

Antenna faces the -X direction

Solar Wings deploy to face the +Y direction.

All systems are capable of working as intended should the satellite be integrated first or second.

V-MEC-1050 - Deployable Hinge Direction - Verified

There are two deployable systems Solar Panels and the Antenna systems

Antenna hinge deploys to face +Y

Solar Wings go from facing +- X to +Y

see ICD for pictures: Solar ICD Coms ICD

V-MEC-1080 - Battery Enclosure Anodization - Verified

PWR Shell, Saddle and Mounting Brackets have been anodized to meet this requirement.

V-MEC-1110 - Satellite Destruction - Verified

The Satellite is not intended to purposely self destruct, and no components of the structure will enable purposeful destruction as illustrated in the Structure ICD Block diagram and the functional block diagram

V-MEC-1120 - Sharp Corners - WIP

All drawings of parts with sharp edges (that are accessible from the outside of the final build of the satellite) will contain a callout to remove and blunt any and all sharp corners during manufacturing.

After being manufactured, parts will be inspected to ensure no sharp regions remain on the components.

V-MEC-1130 - Battery Electrical Insulation - Verified

PWR module is anodized and non-conductive to prevent battery discharge through the structure.