ADCS Verification Report

Verification Activities

V-ADC-0010

Check with the simulation and verify that ADCS provides attitude stabilization for the satellite.

Tags: Phase C

View Magnetometer Calibration Procedure.

V-ADC-0012

Verify that ADCS provide attitude stabilization in the magnetic environment the same as ISS orbit by testing via the ADCS simulator.

Tags: Phase C

View Gyroscope Calibration Procedure.

V-ADC-0013

Review the datasheet and verify that ADCS imported parts or services complies with import conditions imposed by the federal and provincial governments.

Tags: York U, Phase C

View ADCS datasheets. All components were found in digikey (https://www.digikey.ca/) and PCB was manufactured by Microart Services (https://microartservices.com/)

V-ADC-0050

Verify by review of design that ADCS communicates with CDH over SPI.

Tags: York U, Phase C

Figure 1 in the ADCS ICD shows connection with CDH: https://sites.google.com/site/manitobasat1/subsystems/aodcs/adcs-icd#h.p_4IeaWT5WRJ_l

V-ADC-0060

Review the data sheet to verify that ADCS is capable of withstanding a random vibrations environment as outlined by the NanoRacks Interface Document. There would be no individual vibration testing.

Tags: Phase C, Check

V-ADC-0070

Verify that the magnetometer on ADCS board is dual redundant, three axis, chip style with MMC5883MA part number.

LOTAD detailed schematic calls out the MMC5883MA chip on page 7, 4th row from the bottom, with a specified quantity of 2. https://drive.google.com/file/d/1xKW95KrB9WR5u-16WAxeTwhxWwqWsR8b/view. Verified by BoM: https://docs.google.com/spreadsheets/d/1DwguxR51N7s4ihyPEdjRZnMHKQeatchA

Tags: York U, Phase C

V-ADC-0080

Review the data sheets and verify that the gyroscope installed on the ADCS hardware is dual redundant, three axis, chip style with A3G4250D part number from STMicroelectronics.

Tags: York U, Phase C

Verified by BoM: https://docs.google.com/spreadsheets/d/1DwguxR51N7s4ihyPEdjRZnMHKQeatchA

V-ADC-0091

Check the interface between the sun sensors and the mounting pattern of the satellite structure to be on the +yside in CAD as per the Nanoracks coordinate system (+x on the internal coordinate system).

Tags: York U

Sun sensor designed with attachment to an arbitrary X or Y face in mind.

V-ADC-0110

Verify by review of design that the COTS gyros have a power input of 2.4-3.6 V.

Tags: Phase C, Check

Verified by the datasheet. View A3G4250D datasheet.

V-ADC-0120

Verify that ADCS provides solar illumination from +X face with a pointing accuracy of +/- 24 degree from the sun.

Tags: Check

https://docs.google.com/document/d/1YBmA3GzX0-YWuvSMHqm9FO-nlDMhmJ-E/edit?usp=sharing&ouid=106732546825246284245&rtpof=true&sd=true

The sun sensor is adapted from a previous CubeSat mission (DESCENT) which was designed to provide an accuracy of 0.5 degrees. It's expected that this sun sensor's accuracy will be lower due to the use of single-slit design, but should still provide adequate accuracy.

V-ADC-0130

Verify that ADCS has a capability of sampling Sun-vector angles at the rate of once/minute through ADCS simulator.

Tags: Phase C

V-ADC-0150

Test and verify that ADCS has a control accuracy of +/- 10 degrees outside eclipse times via ADCS simulator.

Tags: Phase C

V-ADC-0160

Review the ADCS design and datasheets to ensure it will not release or generate any foreign object debris (FOD) for all mission phases.

Tags: York U, Phase C

View ADCS datasheets. All designed components (Control board and sun sensors) are designed to be fixed. The control board will be fixed inside satellite through the mounting holes in the corners, while the sun sensor will be attached using screws going through the mask.

V-ADC-0170

Review ADCS component/material data sheets to confirm no hazardous materials(Beryllium, Cadmium, Mercury, Silver or any other material) are used regarding the NASA guidelines.

Tags: Phase C

View ADCS datasheets.

V-ADC-0180

Verify that ADCS complies with NASA guidelines for selecting all non-metallic materials based on available outgassing data.

Tags: York U, Phase C

https://outgassing.nasa.gov/

V-ADC-0190

Check with data sheets and verify that ADCS subsystem is capable of withstanding the pressure extremes and depressurization / pressurization rate of the airlock as defined below. Airlock Pressure: 0 to 104.8 kPa.

Tags: Phase C, Check

View ADCS datasheets.

V-ADC-0200

Review the design and verify that there are no detachable parts in the subsystem.

Tags: York U, Phase C

All designed components (Control board and sun sensors) are designed to be fixed. The control board will be fixed inside satellite through the mounting holes in the corners, while the sun sensor will be attached using screws going through the mask.

V-ADC-0201

Verify by visual inspection that no part of ADCS board is detachable.

Tags: Isolated Subsystem

V-ADC-0210

Check with data sheets and verify that subsystem does not use any pyrotechnics.

Tags: York U, Phase C

View ADCS datasheets. Magnetorquers are the only source of actuation, and no thrusters are included.

V-ADC-0230

Review the component data sheets and verify that ADCS is 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.

Tags: York U, Phase C

View ADCS datasheets.

V-ADC-0240

Check the design, to verify that ADCS does not pose any hazards to personnel or equipment at the ISS.

Tags: Phase C

View ADCS datasheets.

V-ADC-0250

Review the design to verify that the subsystem has the secondary locking feature for all components mounted to the structure.

Tags: Phase C, Mechanical

V-ADC-0270

Review the design and confirm that the ADCS has no propulsion system.

Tags: Phase C, Check

Magnetorquers are the only source of actuation, and no thrusters are included.

V-ADC-0290

Review the data sheets and verify that Maximum Effective Vent Ratio (MEVR) of the CubeSat structure and any enclosed containers internal to the CubeSat shall not exceed 5080cm.

Tags: Phase C, Check

View ADCS datasheets.

V-ADC-0310

Test and verify that ADCS have frame of reference w.r.t Sun vector for attitude determination with ADCS simulator.

Tags: Phase C

V-ADC-0351

Verify by review of design that the torque rods can provide 0.15 A.m^2 magnetic moment.

Tags:York U, Phase C, Check

Design-wise, the torque rods should be able to provide the stated magnetic moment.

https://docs.google.com/document/d/1YBmA3GzX0-YWuvSMHqm9FO-nlDMhmJ-E/edit?usp=sharing&ouid=106732546825246284245&rtpof=true&sd=true

V-ADC-0390

Review the data sheets and verify that the magnetometers detect the local magnetic field vector within accuracy of 1-2 degrees.

Tags: York U, Phase C

View ADCS datasheets.

V-ADC-0400

Verify that ADCS is going have an acceptable residual detumbling rate of 0.5 degrees/second.

Tags: Analysis

V-ADC-0450

Review the design and verify that ADCS hardware mounts to the structure.

Tags: York U, Phase C, Mechanical

The control board will be fixed inside satellite through the mounting holes in the corners, while the sun sensor will be attached using screws going through the mask.

V-ADC-0460

Review the data sheets and verify that ADCS shall operate in temperature ranges of -15 C to +50 C.

Tags: Phase C

View ADCS datasheets. Components chosen have operating temperature ranges of at least -40 C to +85 C.

V-ADC-0490

Review the data sheets and verify that ADCS components shall be electrically bonded per SSP 30245 Rev.E to ensure the spacecraft is free from electrical shock and static discharge hazards.

Tags: Phase C

View ADCS datasheets.

V-ADC-0520

Review the design to verify that the microcontoller have an SPI interface with the sun-sensors.

Tags: Phase C, Check

View ADCS datasheets. The chosen microcontroller, ATmega328PB, has SPI interface available.

V-ADC-0530

Review the design and Verify that the sun-sensors shall have a ground connection tied to the common ground bus through schematics.

Tags: Phase C, Check

The 10-pin connector used in the MOLTRES sun sensor has ground pins that are used to connect to the ground plane.

V-ADC-0540

Review the design and verify that ADCS has two digital sun-sensors.

Tags: York U, Phase C, Check

York University confirms that two sun sensors has been manufactured by Microart and sent to University of Manitoba.

See ADCS architecture.

V-ADC-0550

Review the design and verify that the torque rods have a ground connection tied to the H-bridges.

Tags: York U, Phase C, Check

See section 2.1 in Magnetorquer Calibration and Requirement Verification Procedure.

V-ADC-0560

Verify that ADCS has a micro-controller to collect data from magnetometers , gyros and torque rods.

Tags: York U, Phase C, Check

View ATmega328p full datasheet. Verified by BoM: https://docs.google.com/spreadsheets/d/1DwguxR51N7s4ihyPEdjRZnMHKQeatchA

V-ADC-0561

Review the design and confirm that the ADCS hardware contain a micro controller with a Atmega328p part number.

Tags: York U, Phase C

View ATmega328p full datasheet. Verified by BoM: https://docs.google.com/spreadsheets/d/1DwguxR51N7s4ihyPEdjRZnMHKQeatchA

V-ADC-0565

Review the design and confirm that the ADCS hardware contain no I2C connection.

Tags: York U, Phase C, Non-compliance submitted

V-ADC-0570

Review the design to confirm that no parts of the sun sensors are detachable.

Tags: York U, Phase C

Once the sun sensor masks are fixed to both the sun sensor and the spacecraft structure using long screws and nuts, they should not be detachable.

See Assembly Plan.

V-ADC-0571

Check by visual inspection in phase D and verify that no parts of sun sensors are detachable.

Tags: Isolated Subsystem

V-ADC-0590

Verify by checking with the simulation that ADCS avoids EMI from payload samples if they become magnetized. EMI should be included as magnetometer noise.

Tags: Simulink

V-ADC-0600

Review the data sheets and verify that ADCS hardware uses stress corrosion resistant materials.

Tags: Phase C

View ADCS datasheets. See Parts List.

V-ADC-0610

Check the design and verify that ADCS fits within the working volume for the ADCS subsystem.

Tags: Phase C, Check

base dimensions document: https://drive.google.com/file/d/1dg7GxBTKHzPUcRW2W5n9Xqt0wHR36d-b/view?usp=sharing

V-ADC-0630

Review the data sheets and verify that ADCS is going to use a peak power of 3W.

Tags: Phase C

View ADCS datasheets. All major components have peak power in the order of tens of mW.

V-ADC-0631

Verify by simulation that ADCS uses 62.08 Wmin per orbit.

Tags: Phase C

V-ADC-0640

Verify by measurement that the ADCS hardware has a maximum combined mass of 410 grams. (Performed by York).

Tags: York U, check

Three magnetorquers (Flight models) with their mounts have a combined weight of 82.7 grams (https://docs.google.com/document/d/19X43UtLNiIJJwRx6x9snYAbDyZLxGFSJ/)

Control board weight TBD

V-ADC-0650

Review the design and verify that the fasteners in ADCS hardware have a thread size of 2-56, 4-40, or 6-32.

Tags: Phase C, Check

Magnetorquer fastening screws are the following: https://www.mcmaster.com/92210A077/

The sun sensor mask screws seem to be metric? https://www.mcmaster.com/91430a151/

V-ADC-0651

Verify by inspection that the fasteners have a thread size of 2-56, 4-40, or 6-32.

Tags: Isolated Subsystem

V-ADC-0660

Verify by review of design that ADCS hardware has sensors for attitude determination.

Tags: Phase C

See Parts List.

V-ADC-0690

Review the design to verify that ADCS shall have two power connection between the controller and sun-sensors. (4X wires).

Tags: Phase C

See ADCS Hardware Block Diagram.

V-ADC-0700

Review the design to verify the power subsystem connects with the microcontroller interface with 2X wires.

Tags: Phase C

See ADCS Hardware Block Diagram.

V-ADC-0710

Review the design and the schematics to ensure that subsystem has a 3v3 voltage regulator with AZ1117EH-3.3TRG1DICT-ND part number.

Tags: Phase C, Check

Verified by BoM: https://docs.google.com/spreadsheets/d/1DwguxR51N7s4ihyPEdjRZnMHKQeatchA as well as LOTAD (control board) detailed schematics: https://drive.google.com/file/d/1xKW95KrB9WR5u-16WAxeTwhxWwqWsR8b/view

V-ADC-0711

Review the design and the schematics to ensure that subsystem has a 5v voltage regulator with AZ1117EH-5.0TRG1DICT-ND part number.

Tags: Phase C

Verified by BoM: https://docs.google.com/spreadsheets/d/1DwguxR51N7s4ihyPEdjRZnMHKQeatchA as well as LOTAD (control board) detailed schematics: https://drive.google.com/file/d/1xKW95KrB9WR5u-16WAxeTwhxWwqWsR8b/view

V-ADC-0712

Review the design and the schematics to ensure that subsystem has 3 H-bridges with BD6212HFP-TR part number.

Tags: Phase C

Verified by BoM: https://docs.google.com/spreadsheets/d/1DwguxR51N7s4ihyPEdjRZnMHKQeatchA as well as LOTAD (control board) detailed schematics: https://drive.google.com/file/d/1xKW95KrB9WR5u-16WAxeTwhxWwqWsR8b/view

V-ADC-0720

Verify by review of design that ADCS components internal to the spacecraft shall be no more than 92 mm in length along the X and Y axis.

Tags: York U, Phase C

Verified by base dimensions document: https://drive.google.com/file/d/1dg7GxBTKHzPUcRW2W5n9Xqt0wHR36d-b/view?usp=sharing

V-ADC-0760

Verify that ADCS uses a PD controller to maintain adequate sun-pointing.

Tags: Simulink

See Iris Attitude Determination and Control Algorithms and ADCS control design.

V-ADC-0800

Review the design and verify that ADCS have a temperature sensor to monitor the magnetometer temperatures.

Tags: York U, Phase C

View ADCS datasheets. MMC5883MA magnetometer confirmed to have on-chip temperature sensor as per datasheet.

V-ADC-0810

Verify that ADCS can track the turning rate of the spacecraft in detumbling until the desired rate of 0.5 degrees is achieved.

Tags: Simulink (same requirement as V-ADC-0800?)

MMC5883MA magnetometer confirmed to have on-chip temperature sensor as per datasheet.

V-ADC-0830

Review the data sheets and Verify that ADCS shall comply with with NASA space debris mitigation guidelines.

Tags: York U, Phase C, Check

View ADCS datasheets.

V-ADC-0850

Verify that ADCS shall be capable of withstanding the depressurization / pressurization rate of 1.0 KPa/s.

Tags: York U, Phase C, Check

View ADCS datasheets.

V-ADC-0860

Review the data sheets by UoM team and verify that ADCS shall be capable of withstanding the loads inside of the NRCSD when exposed to the acceleration environment with Acceleration induced by JEMRMS(Japanese Experiment Module Remote Manipulator System).

View ADCS datasheets.

V-ADC-0931

Verify by review of design that ADCS have an in-orbit lifetime of at least 3 months.

Tags: Phase C, Check

V-ADC-0940

Review the design and check the simulator to verify the ADCS have the voltage by power subsystem when SOC>40%.

V-ADC-0950

Review the team registry to verify that the ADCS design, development, building and deployment shall be led by students.

V-ADC-0980

Review the ADCS parts list and identify all components are subject to ITAR control.

Tags: York U, Phase C

BoM: https://docs.google.com/spreadsheets/d/1DwguxR51N7s4ihyPEdjRZnMHKQeatchA

V-ADC-0990

Review the data sheets to verify the ADCS survive in the temperature ranges from -20 C to +50 C.

Tags: York U, Phase C, Check (V-ADC-0460 redundant?)

View ADCS datasheets. Components chosen have operating temperature ranges of at least -40 C to +85 C

Note that resistors see degradation in performance beyond +70 C

V-ADC-1000

Review the design and the data sheets to verify ADCS will not create any detachable parts during cubesat failure.

Tags: York U, Phase C

Failure of the subsystem shouldn't result in detachment of the sun sensor nor the control board due to fixture using screws and nuts.

V-ADC-1011

Verify by inspection to confirm that ADCS external components adhere to dimension requirement by Nanoracks.

Tags: Isolated Subsystem

V-ADC-1020

Review the design and confirm that ADCS do not contain any batteries.

Tags: York U, Phase C

Verified by BoM: https://docs.google.com/spreadsheets/d/1DwguxR51N7s4ihyPEdjRZnMHKQeatchA

V-ADC-1040

Verify by review of design that there is no Electric interface between ADCS and NRCSD.

V-ADC-1070

Verify by review of design that the ADCS do not contain any sealed pressure container with the pressure of 100 psia.

Tags: Check

V-ADC-2000

Verify by visual inspection that ADCS do not have any sharp corners or edge in the accessible parts.

Tags: Integration

V-ADC-2001

Verify with a glove test during Integration that ADCS doesn't have any sharp corners.

Tags: Integration

V-ADC-2041

Verify by review that the fasteners used in ADCS use a hex head.

Tags: Isolated Subsystem

The following hex-head fastener is used for the torque rods https://www.mcmaster.com/92210A077/

Note that the sun sensor fastener (the mask screws) use a flat-head https://www.mcmaster.com/91430a151/

V-ADC-2050

Check with the ADCS simulator and verify that the ADCS is capable of withstanding up to 5. deg/s/axis tip off rate.

Tags: Simulink

V-ADC-2070

Review the design and check if ADCS use a permanent magnet. If yes, the strength shouldn't be no more than 3 Gauss measured at a distance of 7 cm.

Tags: York U, Phase C

Magnetorquer design consists of a cylindrical permalloy wound with 36 awg copper wire. No permanent magnet is present.

V-ADC-2080

Review the component data sheets and confirm that ADCS use ceramic capacitors.

Tags: York U, Phase C

Verified by BoM: https://docs.google.com/spreadsheets/d/1DwguxR51N7s4ihyPEdjRZnMHKQeatchA

V-ADC-3020

Check with the ADCS simulator and verify that the ADCS shall be able to slow rotation to 0.5 degrees per second within 4 orbits in detumbling mode.

Tags: Simulink

V-ADC-3050

Confirm that ADCS board contains dual redundant magnetometers through visual inspection on the final PCB.

Tags: Simulink

V-ADC-3070

Confirm that gyroscope is installed on ADCS hardware by visual inspection. To be verified by visual inspection.

Tags: York U

Verified by the pre-shipping photos. (https://drive.google.com/drive/folders/1XWhoNbRBDuL-VWjiW6NRPmDcC83iqv5c?usp=sharing)

V-ADC-4070

Review the design and confirm if Sun sensors have a dedicated ground line which is isolated from sun sensors electronics.

Tags: York U, Phase C

Dedicated ground lines are available in the 10-pin connector used for the sun sensor.

V-ADC-4080

Review the design and verify that torque rods use a maximum of 0.2 w of power.

Tags: Phase C, Check

Need to double check this number. May be obsolete.

V-ADC-4083

Review of design to confirm the torque rods are less than 60 grams.

Tags: Phase C

Measurement of individual torque rods (flight model) are 27.6 grams, 27.6 grams, and 27.5 grams. https://docs.google.com/document/d/19X43UtLNiIJJwRx6x9snYAbDyZLxGFSJ

V-ADC-4084

Review the ADCS hardware design and confirm that no parts of the torque rods are detachable.

Tags: York U, Phase C

Screws are available that attach both the permalloy cylinder to the mounting brackets, and the mounting brackets to the LOTAD control board.

V-ADC-4085

Check by visual inspection and confirm that H-bridges are connected to ground bus.

Tags: Isolated Subsystem

View LOTAD schematics.

V-ADC-5020

Review the design and verify that ADCS has a switch to communicate with PCU and CDH(SN74CBTLV3257-EP Part number).

Tags: Phase C

View SN74CBTLV3257 datasheet.

V-ADC-5050

Fit check the ADCS module mounting to confirm the module assembly process.

V-ADC-40840

Review by visual inspection in phase D that no parts of torque rods are detachable.

Tags: Phase C