System Requirements - cubesat-project/CubeSat GitHub Wiki
Must: Denotes an externally imposed requirement.
Shall: Denotes an internally imposed requirement, subject to internal changed.
May: Denotes a goal requirement
| System Requirements | |||
|---|---|---|---|
| Space Segment Requirements | |||
| Requirement Number | Requirement | Parent Req ID | Verification Strategy |
| SY-SS01 | The CubeSat shall be a 2U form factor | MR-OP06 | By design, by inspection |
| SY-SS02 | The CubeSat must comply with Nanoracks deployment specifications | MR-OP06, MR-PR07, MR-PR08 | By design, by inspection |
| SY-SS03 | The CubeSat must have a remove before flight pin | MR-OP06 | By design, by inspection |
| SY-SS04 | The CubeSat must have deployment switches | MR-OP06 | By design, by inspection |
| SY-SS05 | The CubeSat must have a 30-minute timer circuit | MR-OP06 | By design, by inspection |
| SY-SS06 | The CubeSat must provide a bill-of-materials to Nanoracks | MR-OP06 | By design, by inspection |
| SY-SS07 | The CubeSat must comply with outgassing specifications | MR-OP06 | By design, by inspection |
| SY-SS08 | The CubeSat shall receive and execute time-tagged telecommands | MR-OP03 | By design, by inspection |
| SY-SS09 | The CubeSat shall transmit time-tagged telemetry | MR-OP13, MR-OP14, MR-OP09 | By design, by inspection |
| SY-SS10 | The CubeSat shall determine its pose | MR-OP01 | By design, by inspection |
| SY-SS11 | The CubeSat shall control its pose | MR-OP01 | By design, by inspection |
| SY-SS12 | The CubeSat shall determine its orbital position | MR-OP01, MR-OP11 | By design, by inspection |
| SY-SS13 | The CubeSat shall provide enough power to operate all mission modes throughout its mission life | MR-OP04, MR-OP05 | By design, by inspection |
| SY-SS14 | The CubeSat shall survive the test environment | MR-OP04, MR-OP05 | By design, by inspection |
| SY-SS15 | The CubeSat shall survive the integration environment | MR-OP04, MR-OP05 | By design, by inspection |
| SY-SS16 | The CubeSat shall survive the launch environment | MR-OP04, MR-OP05 | By design, by inspection |
| SY-SS17 | The CubeSat shall survive the low earth orbit thermal environment | MR-OP04, MR-OP05 | By design, by inspection |
| SY-SS18 | The CubeSat shall survive the low earth orbit radiation environment | MR-OP04, MR-OP05 | By design, by inspection |
| SY-SS19 | The CubeSat shall facilitate integration of two Canadensys nano VR cameras | MR-SC01 | By design, by inspection |
| SY-SS20 | The CubeSat shall facilitate transmission of images from the camera to the ground | MR-SC03 | By design, by inspection |
| SY-SS21 | The CubeSat shall safely re-enter atmosphere and burn up | MR-OP08 | By design, by inspection |
| SY-SS22 | The CubeSat must have a launch mass less that 3.6kg | MR-PR07 | By design, by inspection |
| SY-SS23 | The CubeSat shall be operated in a LEOP & Checkout phase and a nominal phase | MR-PR07, MR-OP06 | By design, by inspection |
| SY-SS24 | The CubeSat and its components shall be designed and manufactured to meet system requirements for a minimum operational lifespace of 6 months | MR-OP04 | By design, by inspection |
| SY-SS25 | The CubeSat components shall be designed or selected to prevent undesired electromagnetic effects | MR-OP04 | By design, by inspection |
| SY-SS26 | The CubeSat shall always be in one of the following operations: Launch Mode; Deployment Mode; Detumble Mode; Safe Mode; Eclipse Mode; Communications Mode; Imaging Mode; and Nominal Mode | MR-OP06 | By design, by inspection |
| SY-SS27 | The CubeSat shall be delivered to the launch provider in Launch Mode | MR-PR07, MR-OP06 | By design, by inspection |
| SY-SS28 | The CubeSat shall exit Launch Mode into Deployment mode upon deployment from ISS | MR-PR07, MR-OP06 | By design, by inspection |
| SY-SS29 | The CubeSat transition to Deployment Mode shall trigger a 30 minute timer. | MR-PR07, MR-OP06 | By design, by inspection |
| SY-SS30 | The VR cameras may switch on to begin imagining during Deployment Mode as a goal | MR-OP07 | By design, by inspection |
| SY-SS31 | The CubeSat shall deploy its antenna following the 30 minute delay | MR-PR07, MR-OP06 | By design, by inspection |
| SY-SS32 | The CubeSat shall bootup the OBC during Deployment Mode | MR-OP02, MR-OP04 | By design, by inspection |
| SY-SS33 | The CubeSat shall exist Deployment Mode into Detumble Mode following the antenna deployment | MR-OP04 | By design, by inspection |
| SY-SS34 | The CubeSat shall minimize its initial rotation rates during Detumble Mode | MR-OP04 | By design, by inspection |
| SY-SS35 | The CubeSat shall control its pose to face its solar panels towards the sun during Detumble Mode | MR-OP04 | By design, by inspection |
| SY-SS36 | The CubeSat shall respond to TC with TM during Detumble Mode | MR-OP02, MR-OP04 | By design, by inspection |
| SY-SS37 | The CubeSat shall exit Detumble Mode into Nominal Mode through TC | MR-OP02, MR-OP04 | By design, by inspection |
| SY-SS38 | The CubeSat shall enter Safe Mode either through TC or through detection of an onboard anamoly | MR-OP02, MR-OP04 | By design, by inspection |
| SY-SS39 | The CubeSat shall exit Safe Mode into Detumble Mode through TC | MR-OP02, MR-OP04 | By design, by inspection |
| SY-SS40 | The CubeSat shall enter Imagining Mode through time-tagged TC | MR-OP02, MR-OP04 | By design, by inspection |
| SY-SS41 | The CubeSat shall exit Imaging Mode into Nominal Mode through time-tagged TC | MR-OP02, MR-OP04 | By design, by inspection |
| SY-SS42 | The CubeSat shall enter Communications Mode through time-tagged TC | MR-OP02, MR-OP04 | By design, by inspection |
| SY-SS43 | The CubeSat shall exit Communications Mode into Nominal Mode through time-tagged TC | MR-OP02, MR-OP04 | By design, by inspection |
| SY-SS44 | The CubeSat shall enter Eclipse Mode either automatically or through time-tagged TC | MR-OP02, MR-OP04 | By design, by inspection |
| SY-SS45 | The CubeSat shall exit Eclipse Mode into Nominal Mode either automatically or through time-tagged TC | MR-OP02, MR-OP04 | By design, by inspection |
| SY-SS46 | The CubeSat shall function autonomously for a maximum of 7 days without intervention from MC | MR-OP02, MR-OP04 | By design, by inspection |
| SY-SS47 | The CubeSat shall detect onbaord anamolies | MR-OP04 | By design, by inspection |
| SY-SS48 | The CubeSat shall provide pointing accuracy of 15 degrees for the solar panel aligned with the normal to the sun vector | MR-OP04 | By design, by inspection |
| SY-SS49 | The CubeSat shall have a centre of mass within 2cm of the of centre of volume | MR-PR07 | By design, by inspection |
| SY-SS50 | The CubeSat configuration shall be such that no unit be subjected to loading beyond the limits stated in its specification | MR-OP04 | By design, by inspection |
| SY-SS51 | The CubeSat shall store up to 10 days of housekeeping data as a minimum | MR-OP14 | By design, by inspection |
| SY-SS52 | The CubeSat flight software shall be reprogrammable in orbit | MR-OP04 | By design, by inspection |
| SY-SS53 | The CubeSat power system shall be sized for an expected EOL of 12 months | MR-OP05 | By design, by inspection |
| SY-SS54 | The CubeSat system shall be designed for ground-based testability | MR-PR03, MR-PR04, MR-PR05, MR-PR06 | By design, by inspection |
| SY-SS55 | The CubeSat system shall be designed with ease of assembly and integration in mind | MR-PR03, MR-PR04, MR-PR05, MR-PR06 | By design, by inspection |
| Payload Requirements | |||
| SY-PA01 | The VR cameras shall have a bill of materials to provide the launch provider | MR-OP01 | By review |
| SY-PA02 | The VR cameras may switch on upon deployment from ISS as a goal | MR-OP07, MR-OP10 | By design, by inspection |
| SY-PA03 | The VR cameras shall be operable on a time-tagged queue | MR-OP10 | By design |
| SY-PA04 | One image shall be two semi-spherical images stitched together on the ground | MR-SC05, MR-SC06, MR-SC07, MR-OP10 | By design |
| SY-PA05 | The CubeSat shall integrate an Inuit engraving | MR-PR09 | by design, by inspection, by review |
| Ground Segment | |||
| SY-GR01 | The Western-based ground station shall be capable of two-way communication with the CubeSat. | MR-OP02 | By design, by inspection |
| SY-GR02 | The ground station shall transmit at UHF frequencies as specified by licence | MR-OP12 | By design, by inspection |
| SY-GR03 | The ground station shall receive at UHF frequencies as specified by licence | MR-OP12 | By design, by inspection |
| SY-GR04 | The Western-based ground station shall survive nominal London Ontario weather | MR-OP02 | By design, by inspection |
| SY-GR05 | The Western-based ground station shall be compatible with other CCP CubeSats operating with similar communications license bands | MR-OP02 | By design, by inspection |
| SY-GR06 | The CubeSat shall be operated using a Mission Control software interface | MR-PR01 | By design, by inspection |
| SY-GR07 | The Mission Control software shall interface with the ground station | MR-PR01 | By design, by inspection |
| SY-GR08 | The Mission Control software shall allow an operator to generate a sequence of time-tagged telecommands | MR-PR01 | By design, by inspection |
| SY-GR09 | The Mission Control software shall display time-tagged telemetry | MR-OP14 | By design, by inspection |
| SY-GR10 | The Ground Segment shall plan, prepare, and execute the operations of the CubeSat during all mission phases and operating modes | MR-OP02, MR-OP03 | By design, by inspection |
| SY-GR11 | The Mission Control software shall transfer all TM and payload data to data storage | MR-SC08, MR-SC09, MR-SC10, MR-SC11, MR-SC12, MR-SC13 | By design, by inspection |
| SY-GR12 | The Ground Station shall have a tracking angle rate of up to 1°/sec (TBC) | MR-OP01 | By design, by inspection |
| SY-GR13 | The Ground Segment shall maintain an updated CubeSat orbit estimate | MR-OP01 | By design, by inspection |
| SY-GR14 | The Ground Segment shall coordinate with project management to implement the outreach plan | MR-SC04 | By design, by inspection |
| SY-GR15 | The Ground Segment shall coordinate with project management to implement the imaging plan | MR-SC08, MR-SC09, MR-SC10, MR-SC11, MR-SC12, MR-SC13, MR-OP10 | By design, by inspection |