Payload Verification

This page summarizes all completed payload verification activities.

V-PLD-0020

Description:Verify maximum sun vector angle in X,Y, and Z before samples are shaded by putting the EM payload module on a turnstyle in a dark room with a single bright light source at a known angle from the module. Slowly rotate the module until samples are shaded. Record this angle. R-PLD-0830, R-PLD-0070

Verification Evidence: Test was performed, as described here, and we found that the samples in the farthest four rows were shaded before 24 degrees. However, these tests showed that the CAD-based analysis is conservative and so the design was updated and re-analyzed. As the analysis proved conservative we determined that a new round of physical testing was not needed.

V-PLD-0070

Description: Confirm that Payload measures the average red reflectance intensities for each sample by taking an image of a known coloured image with the camera- R-PLD-0080, R-PLD-0200

V-PLD-0080

Description: Confirm that Payload measures the average green reflectance intensities for each sample by taking an image of a known coloured image with the camera-R-PLD-0090, R-PLD-210

V-PLD-0090

Description: Confirm that Payload measures the average blue reflectance intensities for each sample by taking an image of a known coloured image with the camera.-R-PLD-0100, R-PLD-0220

V-PLD-0640

Description: Perform random vibration test on the Payload sample plate assembly, including payload samples, prior to integration with the rest of the spacecraft-R-PLD-0750, R-PLD-0760

Verification Evidence: Two rounds of vibration testing were performed. During the first round, the thin anthracite coal samples were found to be unsuitable for launch and some of the graphite coating (applied during the sample vacuum sintering process) flaked off.

During the second round, after the graphite coating was fully removed, all samples tested successfully survived.

Review of Design

V-PLD-0016

Description: Verify maximum sun vector angle in X,Y, and Z before samples are shaded by reviewing the CAD model. R-PLD-0150

Verification Evidence: Analysis was performed and calculations are shown here.

Analysis shows that the rear sample row will be shadowed at 22.8 degrees in the Z-axis and at 21.3 degrees in the Y-axis. Will discuss with Naeimeh. The rear sample row is beyond the required ten and so this might be acceptable.

V-PLD-0040

Description: Verify that Payload sample plate does not not use adhesives to secure samples by reviewing the CAD files and payload BOM. R-PLD-0030

Verification Evidence: Parts List and CAD model reviewed. No adhesives present.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0041

Description: Verify that Payload sample plate does not not use adhesives to secure samples by reviewing the CAD files and payload BOM. R-PLD-0030

Verification Evidence: Parts List and CAD model reviewed. No adhesives present.

V-PLD-0050

Description: Verify if Payload contains at least 15 geological samples as specified by the science PI by reviewing the CAD design. G-PLD-0050

Verification Evidence: Verified by reviewing CAD model and Parts List. CAD has 24 samples.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0060

Description: Confirm that Payload samples are less than 14mm by 14mm in area by reviewing the CAD files and measuring the EM samples. R-PLD-0060

Verification Evidence: Verified by reviewing CAD model. Samples are nominally 10mm in diameter.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0140

Description: Verify that Payload measurement system includes two visible-wavelength cameras by reviewing the CAD model. R-PLD-0160, R-PLD-0165

Verification Evidence: BOM and CAD models include two MT9D111 ArduCam cameras.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0141

Description: Verify that Payload measurement system includes two Arducam MT9D111 visible-wavelength cameras by reviewing the CAD model. R-PLD-0160, R-PLD-0165

Verification Evidence: BOM and CAD models include two MT9D111 ArduCam cameras.

V-PLD-0160

Description: Verify that Payload cameras have pixel sizes are no larger than 100 micrometers per channel by reviewing the camera data sheet. R-PLD-0170

Verification Evidence: Pixel sizes are 2.8 x 2.8 μm as shown in Table 1 of the camera data sheet.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0161

Description: Verify that Payload cameras have pixel sizes are no larger than 100 micrometers per channel by reviewing the camera data sheet. R-PLD-0170

Verification Evidence: Pixel sizes are 2.8 x 2.8 μm as shown in Table 1 of the camera data sheet.

V-PLD-0190

Description: Verify that Payload cameras used for measuring sample reflectance have fields of view larger than the sample plate by taking an image of the sample plate with one of the cameras, mounted in the same position as the flight design, and confirming that all samples are sufficiently in view and in focus to achieve the required 59 red / 52 green / 45 blue pixels for each sample. R-PLD-0290

Verification Evidence: Test was performed and samples were sufficiently in view and in focus.

V-PLD-0220

Description: Verify that the gnomon has a matte surface finish. R-PLD-0320

V-PLD-0230

Description: Verify that the gnomon is be less than 28mm x 28mm by revewing the CAD design. R-PLD-0330

Activities performed: As shown on the gnomon ICD, the gnomon is 20 x 20 mm.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0231

Description: Verify that the gnomon is be less than 28mm x 28mm by revewing the CAD design. R-PLD-0330

Activities performed: As shown on the gnomon ICD, the gnomon is 20 x 20 mm.

V-PLD-0250

Description: Review the material selected for Gnomon and verify that it is on the NASA outgassing list with a TML < 1.0% and CVCM < 0.1%. R-PLD-0410, R-PLD-0350

Verification Evidence:

Gnomon to be machined from 6061 aluminum with an M2 Tool Steel pin and a target pattern etched with CerMark LMM6000. Both the gnomon body and pin are outgassing safe and the etching material has been flown successfully on a long duration NASA mission. No outgassing information is available on the LMM6000 etching material but the manufacturer has told us it is outgassing-safe and does not contain volatiles.

NEED TO find out what materials / compounds LMM6000 is made of before this can be considered "verified."

V-PLD-0255

Description: Review the Gnomon CAD model to ensure it allows for solar incidence angle measurements of up to 50 degrees. R-PLD-0360

Verification Evidence: Gnomon calculations as done by the Interlake School students uses angular measurements up to 50 degrees.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0265

Description: Review the gnomon CAD model to ensure it has a minimum solar incidence angle resolution of 5 degrees. R-PLD-0370

Activities performed: Gnomon calculations as done by the Interlake School students uses angular increments of 5 degrees.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0275

Description: Review the gnomon CAD model to ensure it has a minimum rotational resolution of 15 degrees. R-PLD-0380

Activities performed: Gnomon design has rotational resolution of 12 degrees as seen on the Gnomon ICD.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0290

Description: Verify that the gonomon is located on the geological sample plate by reviewing the CAD design. R-PLD-0390

Verification Evidence: As seen on the CAD model, the gnomon is mounted to the sample plate.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-300

Description: Review payload BOM and confirm that all materals have a Total Mass Loss (TML) of less than 1% and Collected Condensable Volatile Material (CVCM) of less than 0.1% on the NASA or ESA outgassing database. R-PLD-0350, R-PLD-410

Verification Evidence: BOM reviewed and no outgassing materials identified. Outgassing properties of the samples have not been determined but a waiver has been sent for them. The electronics shall be conformally coated to prevent potential outgassing.

V-PLD-320

Description: Verify that the payload cameras can measure each payload sample with no less than 59 pixels in the red frequency range by taking a picture with the camera, while the payload assembly is assembled, and counting the number of pixels for each sample. R-PLD-0420

Verification Evidence: Test was performed and samples had a sufficient number of red pixels, with a safety factor of 6.4 times.

V-PLD-330

Description: Verify that the payload cameras can measure each payload sample with no less than 52 pixels in the green frequency range by taking a picture with the camera, while the payload assembly is assembled, and counting the number of pixels for each sample. R-PLD-0430

Verification Evidence: Test was performed and samples had a sufficient number of green pixels, with a safety factor of 14.5 times.

V-PLD-340

Description: Verify that the payload cameras can measure each payload sample with no less than 45 pixels in the blue frequency range by taking a picture with the camera, while the payload assembly is assembled, and counting the number of pixels for each sample. R-PLD-0440

Verification Evidence: Test was performed and samples had a sufficient number of blue pixels, with a safety factor of 8.4 times.

V-PLD-350

Description: Take an image with both payload cameras and see if any portion of the image includes objects external to the payload module. R-PLD-0450

Verification Evidence: Test was performed and the camera was able to view objects external to the module.

V-PLD-0380

Description: Review payload design to ensure it complies with NASA guidelines for hazardous materials including Beryllium, cadmium, mercury, silver or other materials included in SSP-30233. R-PLD-0490

Verification Evidence: BOM reviewed and no prohibited materials identified. However, the Payload Control Board BOM must be reviewed still.

V-PLD-0390

Description: Perform analysis to ensure the payload is capable of withstanding the pressure extremes and depressurization / pressurization rate of the airlock as defined below. Airlock Pressure: 0 to 104.8 kPa Airlock pressure depressurization/re-pressurization rate: 1.0 kPa/sec. R-PLD-0500

Verification Evidence: BOM and design reviewed and no areas that may be affected by rapid de-pressurization have been identified.

V-PLD-0400

Description: Review design to ensure payload does not have detachable parts during launch or normal mission operations R-PLD-0510

Verification Evidence: No detachable parts included in payload design, BOM, or Payload Operations Plan.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0401

Description: Review design to ensure payload does not have detachable parts during launch or normal mission operations R-PLD-0510

Verification Evidence: No detachable parts included in payload design, BOM, or Payload Operations Plan.

V-PLD-0410

Description: Identify all Payload components on the spacecraft that are highly sensitive to shock via design review. G-PLD-0520

Verification Evidence: No shock sensitive components found.

NOT Verification Evidence, but the U of W Lab Tech hit a couple of samples with a hammer and no damage was observed.

V-PLD-0420

Description: Review payload BOM to ensure all components are capable of withstanding the relative humidity environment for all mission phases leading up to deployment, which is between 25% to 75% relative humidity (RH) for ascent and on-orbit phases of flight. R-PLD-0530

Verification Evidence: Payload Samples are humidity sensitive and should not be exposed to high humidity for prolonged periods of time. As such, the spacecraft should be stored in a low humidity environment before integration with the resupply mission. They can be exposed to ambient humidity during integration, ascent, and on-orbit phases.

A sealed container with descants is sufficient for storage.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0421

Description: Review payload BOM to ensure all components are capable of withstanding the relative humidity environment for all mission phases leading up to deployment, which is between 25% to 75% relative humidity (RH) for ascent and on-orbit phases of flight. R-PLD-0530

Verification Evidence: Payload Samples are humidity sensitive and should not be exposed to high humidity for prolonged periods of time. As such, the spacecraft should be stored in a low humidity environment before integration with the resupply mission. They can be exposed to ambient humidity during integration, ascent, and on-orbit phases.

A sealed container with descants is sufficient for storage.

V-PLD-0430

Description: Review payload design to ensure it precludes or controls all hazards present, according to the Catastrophic Hazard Definition, via a risk analysis study. R-PLD-0540

Verification Evidence: Payload design has been reviewed via a failure mode analysis and no components present a catastrophic hazard risk.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0431

Description: Review payload design to ensure it precludes or controls all hazards present, according to the Catastrophic Hazard Definition, via a risk analysis study. R-PLD-0540

Verification Evidence: Payload design has been reviewed via a failure mode analysis and no components present a catastrophic hazard risk.

V-PLD-0450

Description: Confirm that those soldering payload controller components are certified to perform NASA-quality soldering by looking at their certifications. R-PLD-0560

Verification Evidence: Design reviewed and is compliant to SSP 30245 rev E.

V-PLD-0470

Description: Review the payload CAD model to verify that all Payload components have a mounting path to the structure. R-PLD-0580

Verification Evidence: Payload CAD model has been examined and all components have mounting paths to the structure.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0471

Description: Review the payload CAD model to verify that all Payload components have a mounting path to the structure. R-PLD-0580

Verification Evidence: Payload CAD model has been examined and all components have mounting paths to the structure.

V-PLD-0480

Description: Review the payload BOM to verify that all Payload components shall be capable of surviving in temperatures from -20C to +50C while non-operational R-PLD-0590

Verification Evidence: All components have operating temperature within our operational range.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0481

Description: Review the payload BOM to verify that all Payload components shall be capable of surviving in temperatures from -20C to +50C while non-operational R-PLD-0590

Verification Evidence: All components have operating temperature within our operational range.

V-PLD-0500

Description: Review the payload electrical design to verify that Payload can be powered using a single 6.4V (nominal) power line R-PLD-0610

Verification Evidence: Payload block diagram and ICDs include a buck converter to convert from VBAT to the required voltages.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0510

Description: Review the payload electrical design to verify that the Payload uses no more than 1.275W per orbit at peak power consumption. R-PLD-0620

V-PLD-0520

Description: Review the payload electrical design to verify that the payload design uses no more than 50 mW per orbit at peak power consumption. G-PLD-0630

V-PLD-0545

Review the payload controller design and confirm that it can take pictures with either camera. R-PLD-650

Verification Evidence: Payload controller design is capable of controlling and sending/receiving data from either camera.

V-PLD-0555

Review the payload controller design and confirm that it can turn the cameras off and on. R-PLD-660

Verification Evidence: Payload controller design is capable of turning both cameras on and off.

V-PLD-0570

Description: Review the camera documentation to verify that Payload is capable of transmitting sample images to CDH in a .raw format. G-PLD-0680

Verification Evidence: Payload Camera can transmit in 10-bit raw and 565RGB as per data sheet.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0585

Description: Review the payload controller design and confirm that it's able to communicate on CAN bus. G-PLD-0690

Verification Evidence: Payload controller design supports CAN communications.

V-PLD-0586

Description: Review payload controller design and confirm that it is capable of using the CubeSat Space Protocol (CSP) on CAN bus. R-PLD-0700, R-PLD-710

Verification Evidence: Payload controller design and processor support CAN communications. CSP is a software-level protocol and the hardware supports it.

V-PLD-0625

Description: Review payload controller design and confirm that the payload controller can reset either camera. R-PLD-730

Verification Evidence: Payload controller design is capable of resetting both of the cameras.

V-PLD-0630

Description: Verify that Payload has a non-structural mass less than 688 grams by reviewing the CAD model. R-PLD-740

Verification Evidence: Payload mass budget, based on the CAD model, is 384 g. This is far below the 688 maximum.

V-PLD-0680

Description: Review the payload design documentation to confirm that all visible payload structural components are to be black anodized. R-PLD-0790

Verification Evidence: All components that are to be anodized have been recorded on the payload Flight parts list.

V-PLD-0685

Description: Inspect the payload and confirm that all visible payload structural components are black anodized. R-PLD-0790

V-PLD-0690

Description: Review the payload BOM to confirm that all Payload components are capable of powering on at temperatures from -10C to +45C. R-PLD-0800

Verification Evidence: All components have power-on temperatures within our operational range.

V-PLD-0700

Description: Review the payload CAD model to verify that all Payload components internal to the spacecraft are no more than 92 mm in length along the Y axis. R-PLD-0810

Verification Evidence: Longest components are Controller PCB. Length and width of PCB is 90 mm.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0701

Description: Review the payload ECAD model to verify that all Payload components internal to the spacecraft are no more than 92 mm in length along the X axis. R-PLD-0810

Verification Evidence: The ECAD model shows the PCB to be 90 x 90 mm.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0710

Description: Review the payload CAD model to verify that all Payload components internal to the spacecraft are no more than 92 mm in length along the Y axis. R-PLD-0820

Verification Evidence: Longest components are Controller PCB. Length and width of PCB is 90 mm.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0715

Description: Measure the payload control board and confirm that the board is no more than 92 mm in length along the Y axis. R-PLD-0820

Verification Evidence: Payload EM board has been measured and is less than 92 mm in length in x and y axis.

V-PLD-0750

Description: Review the Payload control board design and confirm it can store no less than 0.8 KB of data. R-PLD-0130

Verification Evidence: As shown in the control board ICD, the control board has 1 GB of storage capacity.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0751

Description: Review the Payload control board design and confirm it can store no less than 0.8 KB of data. R-PLD-0130

Verification Evidence: As shown in the control board ICD, the control board has 1 GB of storage capacity.

V-PLD-0760

Description: Review the Payload control board design and confirm it can store no less than 4 KB of data. R-PLD-0140

Verification Evidence: As shown in the control board ICD, the control board has 1 GB of storage capacity.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0761

Description: Review the Payload control board design and confirm it can store no less than 4 KB of data. R-PLD-0140

Verification Evidence: As shown in the control board ICD, the control board has 1 GB of storage capacity.

V-PLD-0770

Description: Review the payload telemetry to confirm that payload telemetry shall include the sun vector at the time of sample measurements. R-PLD-0230

Verification Evidence: Pointing angle included in Payload Telemetry sheet.

V-PLD-0780

Description: Review the payload telemetry to confirm that the payload telemetry should include the pointing angle history since the previous payload measurements. R-PLD-0240

Verification Evidence: Pointing angle history included in Payload Telemetry sheet.

V-PLD-0790

Description: Review the payload telemetry to confirm that the payload telemetry shall include full images of the samples when requested by ground up to a maximum of two images per day. R-PLD-0250

Verification Evidence: Pointing angle history included in Payload Telemetry sheet.

V-PLD-0800

Description: Review the CONOPS to confirm that payload images are sent to ground at least once every 7 days. R-PLD-0260

Verification Evidence: Payload CONOPS plan has payload images sent to ground once every day for the first seven days of the mission and once every week afterwards.

V-PLD-0810

Description: Review the payload telemetry to confirm that payload telemetry shall include timestamps for each measurement. R-PLD-0270

Verification Evidence: Pointing angle history included in Payload Telemetry sheet.

V-PLD-0850

Description: Review the payload BOM to confirm that all components have been selected for a minimum on orbit lifetime of 3 months. R-PLD-850

Verification Evidence: All payload parts in the BOM have a minimum lifetime greater than 3 months and a review of the electrical components show that they should likely survive our expected radiation environment.

V-PLD-0860

Description: Review the payload CONOPS to confirm that the payload is designed to use the same orbit as the ISS. R-PLD-0860

Verification Evidence: Payload CONOPS plan has spacecraft being deployed from the ISS.

V-PLD-0870

Description: Review the payload design to ensure it will not release or generate any foreign object debris (FOD) for all mission phases. R-PLD-0870

Verification Evidence: Payload does not contain tethers, deployables, detachable parts, or other items which may create FOD.

V-PLD-0880

Description: Review the payload design and CONOPS to confirm that the payload will comply with NASA space debris mitigation guidelines as documented in NASA Technical Standard NASA-STD-8719.14A R-PLD-0880

Verification Evidence: Payload does not contain tethers, deployables which may create debris, pressure vessels, batteries, or propulsion systems and is not designed for atmospheric reentry. Deorbiting time is being performed by the Structure team.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0890

Description: Review the payload BOM to confirm that all components are capable of surviving in temperatures from -20C to +50C while non-operational. R-PLD-0890

Verification Evidence: All components have survival temperatures within our operational range.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0891

Description: Review the payload BOM to confirm that all components are capable of surviving in temperatures from -20C to +50C while non-operational. R-PLD-0890

Verification Evidence: All components have survival temperatures within our operational range.

V-PLD-0900

Description: Review the payload design to confirm that any Payload failure shall not create detachable parts. R-PLD-0900

Verification Evidence: All components are designed to be fastened with secondary fastening and are unlikely to create detachable parts

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0901

Description: Review the payload design to confirm that any Payload failure shall not create detachable parts. R-PLD-0900

Verification Evidence: All components are designed to be fastened with secondary fastening and are unlikely to create detachable parts

V-PLD-0910

Description: Review the payload design to confirm that it does not contain pyrotechnics. R-PLD-0910

Verification Evidence: Design and BOM contain no pyrotechnics.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0911

Description: Review the payload design to confirm that it does not contain pyrotechnics. R-PLD-0910

Verification Evidence: Design and BOM contain no pyrotechnics.

V-PLD-0920

Description: Review the payload design to confirm that the payload shall not interface with the NRCSD in any axis (X, Y and Z axes). R-PLD-0920

Verification Evidence: Payload design does not interface or protrude outside of the 100 mm x 100 mm area.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0921

Description: Review the payload design to confirm that the payload shall not interface with the NRCSD in any axis (X, Y and Z axes). R-PLD-0920

Verification Evidence: Payload design does not interface or protrude outside of the 100 mm x 100 mm area.

V-PLD-0930

Description: Review the payload CONOPS to confirm that the payload shall not operate for a minimum of 30 minutes where hazard potential exists (IE after deployment). R-PLD-0930

Verification Evidence: Payload CONOPS plan and primary CONOPS plan have spacecraft waiting 30 minutes after deployment before powering on. Payload will not be on during this time.

V-PLD-0970

Description: Perform failures modes analysis to ensure that no single failure or single operator error can cause a non-disabling personnel injury or illness, loss of a major ISS element, loss of redundancy (i.e. with only a single hazard control remaining) for on-orbit life sustaining function, or loss of use of the Space Station Remote Manipulator System (SSRMS). R-PLD-0970

Verification Evidence: Failure modes analysis has identified no single failure or operator error which could cause a non-disabling personal injury, illness, loss of major ISS element, loss of redundancy for on-orbit life sustaining function, or loss of use of the Space Station Remote Manipulator System (SSRMS).

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0971

Description: Perform failures modes analysis to ensure that no single failure or single operator error can cause a non-disabling personnel injury or illness, loss of a major ISS element, loss of redundancy (i.e. with only a single hazard control remaining) for on-orbit life sustaining function, or loss of use of the Space Station Remote Manipulator System (SSRMS). R-PLD-0970

Verification Evidence: Failure modes analysis has identified no single failure or operator error which could cause a non-disabling personal injury, illness, loss of major ISS element, loss of redundancy for on-orbit life sustaining function, or loss of use of the Space Station Remote Manipulator System (SSRMS).

V-PLD-0980

Description: Review the payload design and identify any potential hazards. Review the payload design and confirm that it controls each hazard to a level that is appropriate for the hazard type and occurrence. R-PLD-0980

Verification Evidence: Failure modes analysis has identified potential hazards and confirmed that each hazard is controlled to a level that is appropriate for each hazard type and occurrence.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-0981

Description: Review the payload design and identify any potential hazards. Review the payload design and confirm that it controls each hazard to a level that is appropriate for the hazard type and occurrence. R-PLD-0980

Verification Evidence: Failure modes analysis has identified potential hazards and confirmed that each hazard is controlled to a level that is appropriate for each hazard type and occurrence.

V-PLD-0990

Description: Calculate the payload's Maximum Effective Vent Ratio (MEVR) and verify that it does not exceed 5080 cm. R-PLD-0990

Verification Evidence:

The payload window is 91x77 = 7007 mm^2

The internal Payload volume, neglecting fillets, other structural features, and the payload components themselves is 104x96x96 = 958,464 mm^3

This volume is larger than the actual volume and is therefore conservative.

MEVR = Internal Volume / Vent Area = 958,464 mm^3 / 7007 mm^2 = 136.8 mm = 13.68 cm

This is considerably under the maximum allowable vent ratio of 5080 cm and is in compliance. As the expected EVR is far under the MEVR, further analysis is not warranted.

V-PLD-1000

Description: Review the payload design and confirm that an approved secondary locking feature is to be used for all fasteners and subcomponents. R-PLD-1000

Verification Evidence: All components are designed to be fastened with secondary fastening except for sample mounts. Sample mounts are held by a clamping lid.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1001

Description: Review the payload assembly procedures and confirm that an approved secondary locking feature is to be used for all fasteners and sub-components. R-PLD-1000

Verification Evidence: Flight model assembly instructions include secondary locking for all fasteners.

V-PLD-1010

Description: Review the payload BOM to confirm that the payload has no sealed containers with an internal pressure greater than 100 psia (pounds per square inch absolute). R-PLD-1010

Verification Evidence: BOM and design contain no pressure vessels. Single sealed container (crystal oscillator) has internal pressure of 1 atmosphere or 14 PSIA.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1011

Description: Review the payload BOM to confirm that the payload has no sealed containers with an internal pressure greater than 100 psia (pounds per square inch absolute). R-PLD-1010

Verification Evidence: BOM and design contain no pressure vessels. Single sealed container (crystal oscillator) has internal pressure of 1 atmosphere or 14 PSIA.

V-PLD-1015

Description: The payload shall not have any sealed container with an internal pressure greater than 100 psia (pounds per square inch absolute). R-PLD-1011

Verification Evidence: Hardware BOM and Electronics parts list design contain no pressure vessels or sealed containers. Electronics parts list contains a hermetically sealed crystal (ECS-250-18-5PX-F-TR) and correspondence with the manufacturer indicates that it is vacuum sealed. This crystal is pressurized to one atmosphere.

V-PLD-1030

Description: Review the payload design and confirm that the payload has no batteries. R-PLD-1030

Verification Evidence: BOM and design contain no batteries.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1031

Description: Review the payload design and confirm that the payload has no batteries. R-PLD-1030

Verification Evidence: BOM and design contain no batteries.

V-PLD-1040

Description: Review the payload design and confirm that the payload uses the same three-axis orientation system as defined by NanoRacks provided in the figure. R-PLD-1040

Verification Evidence: Payload uses same coordinate system as NRCSD.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1041

Description: Review the payload design and confirm that the payload uses the same three-axis orientation system as defined by NanoRacks provided in the figure. R-PLD-1040

Verification Evidence: Payload uses same coordinate system as NRCSD.

V-PLD-1050

Description: Review the payload design and confirm that it does not have any sharp corners or edges in the chassis and or in any accessible areas. R-PLD-1050

Verification Evidence: Payload design reviewed and no objects have sharp edges in accessible areas. All part drawings have instructions to remove all sharp edges when sent for machining.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1060

Description: Review the payload CONOPS and confirm that the payload is able to support commissioning activities after successful detumbling from initial 30 minute hold. R-PLD-1060

Verification Evidence: Payload CONOPS plan and main CONOPS plan have payload performing commissioning activities after detumbling which itself is after the 30 minute hold period.

V-PLD-1070

Description: Review the payload design and confirm that all components are capable of withstanding a deployment velocity of 0.5 to 2.0 m/s at ejection from the NRCSD. R-PLD-1070

Verification Evidence: Payload design reviewed and no components were found that may be affected by a 2 m/s velocity. This velocity is very low and only very fragile components could be affected.

V-PLD-1080

Description: Review the payload design and confirm that all components are capable of withstanding up to five (5) deg/sec/axis tip-off rate. R-PLD-1080

Verification Evidence: Payload design reviewed and no components were found that may be affected by a 5 degree per second angular velocity.

V-PLD-1090

Description: Review the payload BOM and identify all permanent magnets and electro-magnets. R-PLD-1090

Verification Evidence: BOM and design do not contain permanent magnets.

V-PLD-1100

Description: Review the payload BOM and confirm that any permanent magnets have a strength less than 3 Gauss measured at a distance of 7 cm. R-PLD-1100

Verification Evidence: BOM and design do not contain permanent magnets.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1101

Description: Review the payload BOM and confirm that any permanent magnets have a strength less than 3 Gauss measured at a distance of 7 cm. R-PLD-1100

Verification Evidence: BOM and design do not contain permanent magnets.

V-PLD-1110

Description: Review BOM and identify any imported products or services that may have import conditions imposed by the federal and provincial governments. Check each BOM item (that has import conditions) to make sure we are in compliance with them. R-PLD-0460

Verification Evidence: BOM does not contain components with import conditions.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1111

Description: Review BOM and identify any imported products or services that may have import conditions imposed by the federal and provincial governments. Check each BOM item (that has import conditions) to make sure we are in compliance with them. R-PLD-0460

Verification Evidence: All components in the BOM can be purchased off of Digikey or other commercial resellers and do not contain components with import conditions.

V-PLD-1160

Description: Review the payload design and identify any protuberances or other characteristics that could cause the payload to become jammed or caught in the NRCSD. R-PLD-1150

Verification Evidence: Payload design is fully within the structural module and does not contain any protuberances that could cause the payload to become jammed.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1161

Description: Review the payload design and identify any protuberances or other characteristics that could cause the payload to become jammed or caught in the NRCSD. R-PLD-1150

Verification Evidence: Payload design is fully within the structural module and does not contain any protuberances that could cause the payload to become jammed.

V-PLD-1170

Description: Review the payload BOM and identify all components that are subject to ITAR control. R-PLD-1160

Verification Evidence: All components in the BOM and electrical parts list can be purchased off of Digikey or other commercial resellers and are not subject to ITAR control.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1171

Description: Review the payload BOM and identify all components that are subject to ITAR control. R-PLD-1160

Verification Evidence: All components in the BOM and electrical parts list can be purchased off of Digikey or other commercial resellers and are not subject to ITAR control.

V-PLD-1180

Description: Review the payload BOM and identify all payload mounting components. Confirm that these materials are on Table I of MSFC-SPEC-522(Revision 1987) and stress corrosion susceptible materials (Table II). If any materials used are on the stress corrosion susceptible materials table (Table II), they must be coordinated with NanoRacks and documented in the ICA. R-PLD-1170

Verification Evidence: No items from Table II or Table III in BOM, all fasteners are 18-8 stainless steel, which are made from 300 series stainless steel. 300 SS is on Table I of MSFC-SPEC-522.

Note: Payload EM model used nitronic 60 stainless steel Helicoils on Table II but these will not be used on the flight model.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1181

Description: Review the payload BOM and identify all payload mounting components. Confirm that these materials are on Table I of MSFC-SPEC-522(Revision 1987) and stress corrosion susceptible materials (Table II). If any materials used are on the stress corrosion susceptible materials table (Table II), they must be coordinated with NanoRacks and documented in the ICA. R-PLD-1170

Verification Evidence: No items from Table II or Table III in BOM, all fasteners are 18-8 stainless steel, which are made from 300 series stainless steel. 300 SS is on Table I of MSFC-SPEC-522.

Note: Payload EM model used nitronic 60 stainless steel Helicoils on Table II but these will not be used on the flight model.

V-PLD-1190

Description: Review the Payload BOM and make sure no materials are on Table III of MSFC-SPEC-522 (Revision 1987). R-PLD-1180

Verification Evidence: No materials in the payload BOM are on table III of MSFC-SPEC-522.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1191

Description: Review the Payload BOM and make sure no materials are on Table III of MSFC-SPEC-522 (Revision 1987). R-PLD-1180

Verification Evidence: No materials in the payload BOM are on table III of MSFC-SPEC-522.

V-PLD-1200

Description:

Review Payload BOM and ensure it contains no high-energy materials that are likely to detonate. R-PLD-1190

Verification Evidence: Payload BOM does not include any high-energy materials that are likely to detonate.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1201

Description:

Review Payload BOM and ensure it contains no high-energy materials that are likely to detonate. R-PLD-1190

Verification Evidence: Payload BOM does not include any high-energy materials that are likely to detonate.

V-PLD-1210

Description: Review the Payload design and ensure that it adhears to the dimensional specification outlined by Nanoracks for the rails and envelope. R-PLD-1200

Verification Evidence: Payload module is compliant, as shown by the mechanical payload structure ICD.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1211

Description: Review the Payload design and ensure that it adhears to the dimensional specification outlined by Nanoracks for the rails and envelope. R-PLD-1200

Verification Evidence: Payload module is compliant, as shown by the mechanical payload structure ICD.

V-PLD-1220

Description: Review the payload BOM and ensure it does not contain any batteries. R-PLD-1210, R-PLD-1440

Verification Evidence: Payload BOM contains no batteries.

V-PLD-1230

Description: Review the payload design and ensure it has no electrical or data interfaces between the payload and the NRCSD. R-PLD-1220

Verification Evidence: Payload design includes no electrical or data interfaces with the NRCSD.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1231

Description: Review the payload design and ensure it has no electrical or data interfaces between the payload and the NRCSD. R-PLD-1220

Verification Evidence: Payload design includes no electrical or data interfaces with the NRCSD.

V-PLD-1280

Description: Review the payload Playbook Game plan and confirm that all design, development, building, testing and deployment testing is planned to be led by students. R-PLD-1430

Verification Evidence: Payload Playbook Game Plan has all design, build, and testing activities performed by students. Some manufacturing items are being performed by non-students but they are being lead by students.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1281

Description: Review the payload Playbook Game plan and confirm that all design, development, building, testing and deployment testing is planned to be led by students. R-PLD-1430

Verification Evidence: Payload Playbook Game Plan has all design, build, and testing activities performed by students. Some manufacturing items are being performed by non-students but they are being lead by students.

V-PLD-1300

Description: Review the payload E-CAD model and confirm that all capactors are ceramic capacitors. R-PLD-1450

Verification Evidence: All capacitors in the ECAD model are ceramic.

V-PLD-1440

Description: Review the payload sample plate design and confirm that it has a designed location for one TE Connectivity thermistors P/N GA10K3A1iC to monitor payload sample plate temperature. R-PLD-1590

Verification Evidence:

The sample plate thermistor will be mounted to the centre of the sample plate's rear face (i.e. the non-sun-facing side) as described in the Payload ICD.

V-PLD-1441

Description: Review the payload design and confirm that it has one TE Connectivity thermistors P/N GA10K3A1iC to monitor payload sample plate temperature. R-PLD-1590

Verification Evidence: Payload Design includes one thermistor on the sample plate.

Reviewed on 17 Aug 2020. Still Compliant

V-PLD-1450

Description: Review the payload design and confirm that it includes one TE Connectivity thermistors P/N GA10K3A1iC on each camera (for two total) to monitor payload camera temperatures. R-PLD-1600

Verification Evidence: Payload Design includes one thermistor on each camera as described in the Payload ICD.

V-PLD-1470

Description: Review the payload E-CAD model and BOM and confirm that all electrical components can withstand a total ionizing radiation dose of 1.5k rad over the three year mission duration R-PLD-1620

Verification Evidence: A review of the electrical components show that they should likely survive our expected radiation environment.

V-PLD-1480

Description: Review the payload controller design and confirm that it can read no fewer than one GA10K3A1iC thermistor. R-PLD-1555

Verification Evidence: Payload Controller design supports one GA110K3A1iC thermistor.

V-PLD-1630

Description: Review Payload BOM and confirm that all fasteners use a hex drive. G-PLD-0605

Verification Evidence: Payload Flight parts list has mostly hex drive fasteners. However, two Phillips head fasteners are included too. Structure has confirmed that this is acceptable.

Reviewed on 17 Aug 2020. Still Compliant, including internal RFD for Philips fasteners.

V-PLD-1631

Description: Review Payload BOM and confirm that all fasteners use a hex drive. G-PLD-0605

Verification Evidence: Payload Flight parts list has mostly hex drive fasteners. However, two Phillips head fasteners are included too. Structure has confirmed that this is acceptable.

V-PLD-1650

Description: Review the payload BOM and ensure that no materials are prohibited by NASA guideline SSP-30233. G-PLD-0605

Verification Evidence: No components on the Payload Flight parts list has materials prohibited by SSP-30233. Payload Control Board components have been reviewed and are compliant as well.

Analysis

V-PLD-0960

Description: Review the payload design and identify any potential hazards. Ensure that the payload design precludes or controls all these hazards. R-PLD-0960

Verification Evidence: Payload Failure Mode Analysis Identified the payload samples as a possible marginal hazard. This risk is being controlled by factors of safety on the compression load applied to the samples (to keep them held rigidly) and via extensive testing of the samples and sample plate.

V-PLD-0970

Description: Review the payload design and potential modes of failure and operator error. Ensure that no single failure or single operator error can cause a non-disabling personnel injury or illness, loss of a major ISS element, loss of redundancy (i.e. with only a single hazard control remaining) for on-orbit life sustaining function, or loss of use of the Space Station Remote Manipulator System (SSRMS). R-PLD-0970

Verification Evidence: Payload Failure Mode Analysis did not identify any single modes of failure or error that may cause a non-disabling personnel injury or illness, loss of a major ISS element, loss of redundancy (i.e. with only a single hazard control remaining) for on-orbit life sustaining function, or loss of use of the Space Station Remote Manipulator System (SSRMS).

V-PLD-0980

Description: Review the payload design and identify any potential hazards. Review the payload design and confirm that it controls each hazard to a level that is appropriate for the hazard type and occurrence. R-PLD-0980

Verification Evidence: Payload Failure Mode Analysis Identified the payload samples as a possible marginal hazard. This risk is being controlled by factors of safety on the compression load applied to the samples (to keep them held rigidly) and via extensive testing of the samples and sample plate.

V-PLD-1240

Description: Perform failure mode analysis and identify any single failure (including operator error) modes that cause a non-disabling personnel injury or illness, loss of a major ISS element, loss of redundancy (i.e. with only a single hazard control remaining) for on-orbit life sustaining function, or loss of use of the Space Station Remote Manipulator System (SSRMS). R-PLD-1230

Verification Evidence: Payload Failure Mode Analysis Identified the payload samples as a possible marginal hazard. This risk is being controlled by factors of safety on the compression load applied to the samples (to keep them held rigidly) and via extensive testing of the samples and sample plate.

V-PLD-1780

Description: Review the payload CAD model and confirm that no single component has a mass greater than 250 grams. R-PLD-0745

Verification Evidence: The Payload mass budget shows that no component is greater than 250 grams.