CubeSat Interface Review (CIR)

Document Classification
X / Public Domain
ITAR Controlled
Internal Only
CSEP Proprietary

CubeSat Interface Review

(CIR)

Document Number:

Project:

Date:

CubeSat Name:

CubeSat Serial Number:

Location:

QA Engineer:

Support Engineers:

The CubeSat Developer agrees to keep CSEP informed

when items in this document change.

Please completereturn this form within 1 week of receiving it.

This form will be continuously updated.

For questions please contact the persons listed in Section 3.

CHANGE HISTORY LOG

Effective Date / Revision / Author / Description of Changes
4/25/10 / Revised Draft / Scott Williams / Created from CIR-1.5U version
2/25/11 / 1.0 / Bryan Klofas / Merged in ELaNa edits, added frequency and NOAA, updated format
3/9/11 / 1.1 / Bryan Klofas / Removed specific questions, added contact info
3/10/11 / 1.2 / Justin Foley / Modified contact info, minor wording changes
3/16/11 / 1.3 / Justin Foley / Added NOAA website for imager licensing
7/12/12 / 2.0 / Justin Foley, Mark Tinkle and Simon Lee / Incorporated lessons learned from OUTSat L-36 mission resulting in additional info requests related to pressure vessels, magnets, batteries, transmitters, etc…

1Introduction

The CubeSat Interface Review (CIR) is performed to determine if the CubeSat has anyinterface issues with the Poly Picosatellite Orbital Deployer (P-POD) or imposes any risks toco-manifested satellites. This review is recommended to be conducted in person with a prototype of their flight unit available. Measurements should be taken on the prototype during this process to confirm the findings.

1.1Objectives

The following are the objectives of this CIR:

  • Inspect CubeSat design, materials, and mission.
  • Review Qualification and Acceptance testing profiles and plans
  • Determine a timeline from Prototype construction to delivery of flight unit to CSEP
  • Provide inputs to CSEP team for inclusion into MSPSP
  • Describe any potential interface issues between satellites co-located in one P-POD
  • To capture interface requirements and updates from the CubeSat provider as it becomes available.

2Applicable Documents

The following documents form a part of this document to the extent specified herein. In the event of conflict between the documents referenced herein and the contents of this document, the contents of this document shall take precedence.

CubeSat Program Documents

P-POD Mk. III ICDP-POD Mk. III Interface Control Document

CDSCubesat Design Specification

3Contact Information

Please feel free to contact the persons below if you have any questions about this form.

Cal Poly State UniversityCal Poly State University

Ryan NugentJustin Foley

805-756-5087805-242-1274

4Cubesat Interface Review

Please use the following form to describe your satellite. Inputs from this form will be used to fill out associated ICDs and Range Safety documentation.

Note: All directions are referenced to the CDS coordinate system.

Please complete this form within 1 week of receiving it. If you need clarification, please contact the persons listed in Section 3.

Step # / Description
Deployables
1-1.Are there deployables on this spacecraft? Yes No, proceed to Step 2
1-2.If so, please provide the following information intoAppendix A:
-External mechanical drawing of the CubeSat in a stowed configuration (Use CDS Coordinate System).
-External mechanical drawing of the CubeSat in a fully-deployed, maximum dimension configuration (Use CDS Coordinate System).
1-3.Do all parts remain attached to the CubeSat, including hooks and tabs? Yes No
1-4.Are all deployable(s) constrained prior to integration into P-POD? Yes No
1-5.If so, please provide the following information into Appendix A:
-Provide a description and mechanical drawing of the different types of constraint mechanisms.
-Provide a description and mechanical drawing of the different types of release mechanism.
1-6.What are the times of deployment from initial to final configuration? (e.g. Antenna deployment takes approximately 1sec.) < 1 second for exo-structure to extend, ~ 1 sec for solar panels to extend from same triggering mechanism
1-7.What are the rates of deployment from initial to final configuration (e.g. Gravity gradient boom extends at 0.5in/sec? Exo-structure extends at a rate> 30 cm/s
1-8.Provide a descriptive summary of the deployment CONOPS sequence into Appendix A:
Satellite Internals
1-
2-
2-1.Provide an exploded view of the CubeSat with callouts to subsystems, see example below. Insert image into Appendix B.
2-2.Does the satellite contain stored chemical energy, not including batteries? Yes No
If so, please describe:
2-3.Does the satellite contain pressurized fluids? Yes No
If so, please describe the fluid and pressurizedcomponents
(for example: pressure vessel, lines and fittings, service and other valves,
pressure regulators, etc.):
External Dimensions
3-
Any protrusions in the stowed position must not exceed 6.5mm from the rails or between the stand-offs.
3-1.Are all protrusions less than 6.5mm? Yes No
(A proper measurement of protrusions shown below)
3-2.Please describe the location and dimensions of allprotrusions:
Deployable solar arrays and their mechanisms protrude 6.5mm off the +/- Y sides and protrude 6.5 mm out in the Z directions. On the +/- X sides, body-mounted solar arrays protrude 0.9mm and their fasteners protrude to 1.7mm off the side, and the arrays protrude 6.5mm out in the Z directions. On the +Z face a PCB panel and internal structure protrude 6.5mm (top of fasteners, PCB & structure ~ 1mm lower), on the –Z face, the THEIA payload internal structure protrudes 6.5mm, and the lens protrudes ~ 5.5mm
3-3.Provide an external view of the CubeSat with callouts to all protrusions with protrusion dimensions. Insert image into Appendix C.
Mass Properties
4-
4-1.Will the mass be less than 1.33 kg per U? Yes No
4-2.Is the center of mass within a 2cm sphere at the CubeSat geometric center? Yes No
4-3.Provide an image of the CubeSat with using Coordinates from the CDS, See example below.Insert image into Appendix D.
4-4.Total Projected Mass (kg): 3.97
4-5.Center of Mass: Xcg (mm): 53.1 Ycg(mm): 51.4 Zcg(mm): 149.1
4-6.Moments of Inertia: Ixx (kg*mm^2): 1.30*105 Iyy(kg*mm^2): 1.28*105 Izz(kg*mm^2): 2.75*104
4-7.Products of Inertia: Ixy (kg*mm^2): 9.70*103 Ixz(kg*mm^2): 2.70*104 Iyz(kg*mm^2): 2.76*104
4-8.Mass Properties Error Estimates:
-Mass:+.03/-0 kg
-Center of Mass: Z +20/-0%; X, Y +/- 5%
-(based on ratio of estimated to measured mass, and locations)
-Moments of Inertia: +/- 20% of stated values
-Products of Inertia: +/- 20% of stated values
-(based on ratio of modeled, distributed masses vs estimated, lumped masses, values should increase with higher fidelity model, as MOI data was for 3.77 kg of 3.97 kg)
Passive Magnets
5-
5-1.Do you have any passive magnets (e.g.magnets inreaction wheels, torque rods to stabilize orientation)? Yes No, proceed to Step 6
5-2.What is the worst-case field strength and direction at each side of the CubeSat? (e.g. 0.5gauss in the +Z direction on the +X side of the CubeSat)
5-3.What is the magnetic dipole moment of the magnet (A*m^2)?
Active Magnets
6-
6-1.Do you have any active magnets (e.g. magnetictorquers, motors, electromagnets, relay coils)? Yes No, proceed to Step 7
6-2.What is the worst-case field strength and direction at each side of the CubeSat? (e.g. 0.5gauss in the +Z direction on the +X side of the CubeSat) 9500 gauss normal to X and Y surfaces (switches depending on torque rod polarities)
6-3.What is the magnetic dipole moment of the magnet (A*m^2)? 0.13 A*m^2
6-4.Provide a description and circuit diagram of any inhibits that arepreventing the magnet from being active accidentally. Please see appendix J for transmitter inhibits in which power flows from the FSW power rail switches to the ACS controlled converters and power controller for each of 3 independent torque rods
Structure
7-
7-1.Is the structure and are the rails made from 6061 or 7075 aluminum? Yes No
7-2.If not, please describe the structure material and design?
THEIA contains an Invar structural piece used to maintain lens-sensor focal alignment over expected temperature range (see Appendix B). All other structural elements are 6061-T6 aluminum
Rails
8-
8-1.Are the rails hard anodized? Yes No
If not, please describe the surface coating: Rails also Teflon coated
8-2.Is the entire length of the rail surface free of obstructions and protrusions on the rail surface Yes No
If not, please describe the obstruction:
8-3.Are screws recessed into the rail? Yes No
If so, please measure the recession in mm: < 1 mm
8-4.If applicable, please mark the location of screws, protrusions, and obstructions on the rails by using the images on Appendix E.
CDS Required Components Location
9-
9-1.Please annotate thefigure intoAppendix F with the location of:
  • Spring plungers
  • Deployment switches
  • Data port
  • RBF pin

Spring Plungers
10-
10-1.Spring plunger Model Number: N/A
10-2.Spring Plunger Part Number: N/A
10-3.Tip material of spring plunger: N/A
10-4.Is the installed spring plungers threaded body flush with the top surface of the stand-off. Yes NoN/A
Deployment Switches
11-
11-1.Please describe the deployment switch type SPST Whisker Switch
11-2.What is the manufacturer and part number? Cherry Electrical DG13-B1LA
11-3.What is the contact point material of the switch? Stainless Steel
11-4.Is the contact point centered on the CubeSat Standoff? Yes No
11-5.What is the total throw length of the switch? (From rest to full mechanical travel): 2.35mm
11-6.What is the electrical switch activation length? (From rest to electrical activation): 1.8mm
11-7.How many deployment switches are used? 2
11-8.Are the switches connected in series or parallel? Series
11-9.Does the deployment switch cutall power to the satellite when depressed? Yes No
If not, please describe: The deployment switch stops current flowing to part of the power inhibit logic which cuts all power to the satellite.
11-10.Provide an image of the rail standoff with the installed deployment switch into Appendix G.
Diagnostic Port
12-
12-1.Please annotate the figure in Appendix F with the location of the Diagnostic Connector. Does the connector fit within the allowable Access Port area described in the CubeSat Design Spec, leaving enough clearance for plugging in a connector and cable?
Yes No
12-2.Please document the manufacturer and part number of the connector:
TBD
12-3.Can satellite diagnostics be performed with the deployment switch depressed and the RBF pin removed?
Yes No
12-4.Can satellite diagnostics be performed with the deployment switch depressed and the RBF pin inserted?
Yes No
12-5.Can batteries be charged with the deployment switch depressed and the RBF pin removed?
Yes No
12-6.Can batteries be charged with the deployment switch depressed and the RBF pin inserted?
Yes No
12-7.Please provide a simple schematic of the circuitry involved in 12-3 – 12-6. Insert the schematic in Appendix H
RBF Pin
13-
13-1.Please annotate the figure in Appendix Fwith the location of RBF pin. Does the RBF pin fit within the allowable Access Port area described in the CubeSat Design Spec, leaving enough clearance for inserting and removing the RBF pin?
Yes No
13-2.Please describe the RBF pin material:
Brass
13-3.Is the height of the RBF pin less than 6.5 mm from the surface of the rails?
Yes No
Power
14-
14-1.What is the type of battery used (NiCd, MiMH, lithium ion, lithium ion polymer)? Lithium Ion
14-2.What is the manufacturer and model number of the batteries used? Tenergy 30006 (ICR 18650-2600)
14-3.What battery protection circuitry is used? Built in over charge, over discharge, over current, and short curcuit
14-4.What is the UL number for all batteries? MH48285
14-5.Provide certification or documentation from the manufacture for UL listing.
14-6.Have the cells been modified from the UL-tested configuration? Yes No If so, describe the modifications:
14-7.Do the cells use a Positive Temp Coefficient (PTC) fuse? Yes No
14-8.Do the cells use a Current Interrupt Device (CID)? Yes No
14-9.What is the EPA classification of these batteries? None
14-10.What is the DOT classification of these batteries? DOT38.3
14-11.How many batteries are contained in the satellite? 1 Pack
14-12.What is the number of cells? 4
14-13.How are the cells wired together (series, parallel or combination)? Combination, two series, two parallel
14-14.What is the total mass of lithium? 0.78 g
14-15.How many watt-hours of stored energy are contained in all batteries in the spacecraft? 38.48 Wh
14-16.Is charging done through the diagnostic port? Yes No
14-17.Can charging be performed with the deployment switches depressed? Yes No
14-18.How long can the satellite remain in storage without need for charging? 1 Year
14-19.Can the mission be completed if deployed with depleted batteries? Yes No
14-20.Does the spacecraft have a different battery system powering a Real Time Clock? Yes No
14-21.If so, what is the manufacturer and model number of the batteries used for the RTC?
14-22.If so, what is the oscillator frequency of the RTC?
Transceiver
15-
15-1.What is the manufacturer and model number of each transmitter and receiver? COSGC custom-made SDRs, full duplex on independent circuits
15-2.Please describe RF license process and status? Ground station fully licensed, in the process of submitting application for AMSAT
15-3.How long after deployment from the P-POD will the spacecraft start transmitting autonomously? > 45 min (confirmed deployment required by software before autonomous command to transmit)
15-4.Can the satellite be commanded into a “No Transmit” mode?
Yes No
15-5.Provide a schematic of the transmission inhibit circuitry. Indicate all inhibits between each battery and each transmitter, indicating how each inhibit is controlled. The independence of the inhibits should be illustrated/addressed. Insert into Appendix J.
Transmitter/Receiver / Operating Frequency (MHz) / 3dB Bandwidth
(kHz) / 60 dB
Bandwidth
(kHz) / Transmit Power
(Watts) / Gain of Antenna (dBi) / Antenna Type
Tx 1 / 2400 / TBD / TBD / 2 / 6 / Spiral
Tx 2
Tx 3
Rx 1 / 437 / N/A / N/A / N/A / 2 / Dipole
Transmitter/Receiver / Antenna
Polariza-tion / AutoTx Beacon
(Yes/No) / Duty Cycle
Time On/Off
(sec/sec) / Transmit Inhibit 1 / Transmit Inhibit 2 / Transmit Inhibit 3
Tx 1 / Circular / Yes / TBD / Sep Switch / Sep Switch / CDH
Tx 2
Tx 3
Rx 1 / Linear / N/A / N/A / N/A / N/A / N/A
Hazardous Materials
16-
16-1.Are there any ionizing radiation sources in this spacecraft? Yes No
If so, please describe:
16-2.Are there any sources of hazardous materials in this spacecraft? Yes No
If so, please describe:
16-3.Are there any Electro Explosive devices (EEDs) in this spacecraft? Yes No
If so, please describe:
Earth Observation
17-
17-1.Does this satellite contain any earth observation sensors, such as an imager? Yes No
17-2.If so, the NOAA Commercial Remote Sensing Regulatory Affairs Office must be notified for licensing. The first step is submitting contact information via .
17-3.Has a license from the NOAA Commercial Remote Sensing Regulatory Affairs Office been applied for or obtained? Yes No
17-4.Status of license: Currently in process of application, contact made, requirement of license confirmed
Special Materials or Components (i.e. Optics, Imagers)
18-
18-1.Does this spacecraft contain any special materials or components that require special handling, transportation and/or storage environment? Yes No
18-2.If so, please describe the requirements in detail and affected subsystems, components, and how the mission could be affected if proper measures were not in place:
THEIA (imager) lens is exposed, must handle cubesat without contaminating lens with dust, oils, etc, or scratching with hard surfaces. Lens is BK7 glass.
Vibration Testing
Qualification / Acceptance testing or protoflight testing must be performed prior to integration into the P-POD. After Acceptance testing in the P-POD, the satellite will NOT be deintegrated and will be stored until launch.
19-
19-1.Qualification Testing Location: LMCO SSC, Littleton, CO
19-2.Will you test Qualification/Flight units or a single protoflight unit? Qual/Flight Protoflight
19-3.Please describe the random vibration test profile: Taurus XL (ElaNa I)
19-4.What is the duration of the random vibration test? 3min/oct
19-5.Will a sine sweep be used to determine satellite structure differences between before and after the random vibration test? Yes No
19-6.Will you provide test results to CSEP after Qualification and Acceptance testing is preformed?
Yes No Initial: CAZT
Thermal Vacuum Testing
20-
20-1.Location of testing facility: LMCO SSC, Littleton, CO
20-2.Please describe the thermal/vacuum test profile: TBD, likely flight unit proto-qualification cycle test and then qualification bake-out
20-3.What is the thermal test duration? TBD
Note: It is recommended that CubeSats remain at or above the bakeout temperature longer than required to ensure that the bakeout requirement is satisfied.
20-4.Will you provide thermal/vacuum test results to CSEP?
Yes No Initial: CAZT
Timeline to Completion
21-
21-1.We realize that for CubeSat Developers, planning months in advance is difficult. However, please try to estimate when these tasks will start and end (Format: MM/DD/YYYY to MM/DD/YYYY):
Responses to payload questionnaire 10/17/12
PDR: 7/9/10
CDR: 1/7/11
Engineering unit/bus buildup and test: 1/8/11 to 9/30/12
Flight hardware build: 7/1/12 to 11/4/12
Structure: 7/1/12 to 11/4/12
Power: 10/1/12 to 11/4/12
Radio: 10/1/12 to 11/4/12
C&DH: 10/1/12 to 11/4/12
Payload: 10/1/12 to 11/4/12
Side Panels: 10/1/12 to 11/4/12
Antenna: 10/1/12 to 11/4/12
Deployable restraint(s): 10/1/12 to 11/4/12
Flight hardware assembly and integration: 11/4/12 to 11/25/12
Flight software: 11/4/12 to 11/25/12
Full functional checkout: 11/26/12 to 3/17/13
End-to-end command via radio: 12/15/12 to 3/17/13
Deployment tests: 1/4/13 to 1/20/13
VibrationTest on FM: 3/18/13 to 3/22/13
Thermal bakeout on FM: 3/25/13 to 3/29/13
CubeSat Fit-check: 3/29/13
Mission Readiness Review: 4/1/13
Delivery of CubeSat FM: 4/8/13
Other Comments

Please return this form within 1 week of receiving it. If you need clarification, please contact the persons listed in Section 3.

Please return this form to the contacts listed in Section 3 above.

Appendix A: Deployable Section

Step 1-2: External mechanical drawing of the CubeSat in a stowed configuration (Use CDS Coordinate System).

Assembly drawings forthcoming, technical issues with CAD.

Step 1-2: External mechanical drawing of the CubeSat in a fully-deployed, maximum dimension configuration (Use CDS Coordinate System).

Step 1-5: Provide a description and mechanical drawing of the different types of constraint mechanisms.

The deployable exo-structure is constrained from extending by a frangibolt, which anchors the exo-structure to the bus section structure. The deployable Rx antennas are constrained by the exo-structure until full extension. The deployable solar arrays are constrained on one end by fixed hooks, attached to the payload section structure, and spring-loaded claws, attached to the exo-structure. The spring-loaded claws are constrained from releasing by contact with the bus structure. When the frangibolt is severed (“burned”) the exo-structure is free to extend. As the exo-structure extends the stowed solar arrays slide off the fixed claws, while the spring-loaded claws simultaneously rotate off of the solar arrays. This occurs within the first 0.5 cm of extension. Once the exo-structure has extended past the tip of the Rx antennas, they are free to rotate (by spring force) into position.