Rail Picosatellite Orbital Deployer (RailPOD) User … Picosatellite Orbital Deployer (RailPOD) User Guide for Payloads and Launch Vehicles ... Flexible CubeSat ... The origin of the

TK-RPUG-Rev2 December 2016

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Rail Picosatellite Orbital Deployer (RailPOD) User Guide for Payloads and Launch Vehicles

(TK-RPUG-Rev2)


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REVISION SUMMARY

REV NO.

RELEASE DATE

BRIEF DESCRIPTION/REASON FOR CHANGE

EFFECTIVE PAGES

00 November 2013 Draft Release All 01 July 2014 Initial Release All 02 December 2016 Updated for RailPOD Mk.II Release All


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TABLE OF CONTENTS

1.0 INTRODUCTION ................................................................................................................5 1.1 Background .......................................................................................................................5 1.2 RailPOD General Description and Coordinate System ....................................................6 1.3 RailPOD Quick Reference ................................................................................................7

2.0 PAYLOAD INFORMATION ..............................................................................................8 2.1 Mechanical Interfaces .......................................................................................................8 2.2 Deployment Switch, Access Port Interfaces, and Deployables ........................................9 2.3 Deployment Dynamics ...................................................................................................10 2.4 Integration Activities ......................................................................................................10

3.0 LAUNCH VEHICLE INFORMATION ...........................................................................11 3.1 Mechanical Interfaces .....................................................................................................11

3.1.1 Vertical and Horizontal Mounting Configurations ................................................11 3.1.2 Materials and Coatings ..........................................................................................11 3.1.3 Door Lock ..............................................................................................................11 3.1.4 Mass Properties ......................................................................................................12 3.1.5 Dynamic Properties ................................................................................................12

3.2 Electrical Interfaces ........................................................................................................13 3.3 Operational Limits ..........................................................................................................14 3.4 Safety and Mission Assurance ........................................................................................14

4.0 EXPANDABLE CAPABILITIES .....................................................................................15 4.1 Launch Integration Services ...........................................................................................15 4.2 Aggregated Missions ......................................................................................................15 4.3 Environment Isolation.....................................................................................................16 4.4 Sun Shade .......................................................................................................................16

5.0 CONTACT US ....................................................................................................................17 5.1 About Tyvak ...................................................................................................................17 5.2 U.S. Headquarters ...........................................................................................................17 5.3 Websites ..........................................................................................................................17

6.0 APPENDIX: HIGH RESOLUTION DRAWINGS .........................................................18


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List of Figures

Figure 1. Six CubeSats and their P-POD Deployment Systems (Top) and RailPOD (Bottom) ..... 5 Figure 2. RailPOD Generic Diagram and Coordinate System ....................................................... 6 Figure 3. Flexible CubeSat Configuration Options ........................................................................ 8 Figure 4. Cal Poly CubeSat Design Spec. (Gray) and Tyvak 3U XL Extra Volume (Green) ........ 8 Figure 5. RailPOD Pusher Plate Payload Interface ........................................................................ 9 Figure 6. Cal Poly Standard Access Port Location (Shown: Tyvak 3U XL) ................................. 9 Figure 7. Estimated Deployment Velocity for 3U Payloads ......................................................... 10 Figure 8. Typical Integration Flow ............................................................................................... 10 Figure 9. Horizontal and Vertical Mounting of the RailPOD ....................................................... 11 Figure 10. Deployed RailPOD ...................................................................................................... 11 Figure 11. RailPOD Coordinate System ....................................................................................... 12 Figure 12. RailPOD Circuit Diagram ........................................................................................... 13 Figure 13. Tyvak Spacecraft Processing Facility (Left) Tyvak Launch Integration (Right) ........ 14 Figure 14. Tyvak Launch Integration Services ............................................................................. 15 Figure 15. Aggregated Mission Concepts ..................................................................................... 15 Figure 16. Thermally Isolated RailPOD (Left) and Vibration Isolation Test Data (Right) .......... 16 Figure 17. RailPOD Without Sun Shade (Left) and With Sun Shade (Right) .............................. 16

List of Tables

Table 1. RailPOD Quick Reference ................................................................................................ 7 Table 2. Mass Properties ............................................................................................................... 12 Table 3. RailPOD Electrical Characteristics ................................................................................. 13 Table 4. RailPOD Operational Limits .......................................................................................... 14 Table 5. List of Drawings ............................................................................................................. 18


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1.0 INTRODUCTION 1.1 Background Started in 1999, the CubeSat Project began as a collaborative effort between Dr. Jordi Puig-Suari at California Polytechnic State University (Cal Poly), San Luis Obispo, and Prof. Bob Twiggs at Stanford University to develop a new class of picosatellites: The CubeSat standard. This standard is defined in the CubeSat Design Specification (CDS), located on the CubeSat website (http://www.cubesat.org). The CDS includes information regarding nominal dimensions of the standard, dimensional tolerances, acceptable materials, reference coordinate system, and other general information.

The Poly Picosatellite Orbital Deployer (P-POD) is a standard deployment system that ensures all CubeSat developers conform to common physical requirements. The P-POD plays a critical role as the interface between the launch vehicle and CubeSats. The P-POD utilizes a tubular design and can hold up to 340.5mm x 100mm x 100mm of deployable hardware.

With the advent of nano-launch vehicles (NLV), Tyvak and Cal Poly together developed a lightweight deployer similar to the P-POD. The Rail Picosatellite Orbital Deployer (RailPOD) was designed to fly as a deployment system for any combination of CubeSats, totaling 3Us, as primary or secondary payloads. This User Guide is for the RailPOD, and contains information both Payloads and Launch Vehicles will find useful.

Figure 1. Six CubeSats and their P-POD Deployment Systems (Top) and RailPOD (Bottom)


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1.2 RailPOD General Description and Coordinate System The RailPOD is a rail type satellite dispenser capable of carrying up to 3U’s of CubeSat payload and serves as the interface between the CubeSats and Launch Vehicle (LV). The RailPOD is a rectangular truss structure, made out of high strength aluminum, with a door and a spring mechanism. Once the release mechanism of the RailPOD door is actuated, a set of torsion springs open the door and the CubeSats are deployed by the main spring gliding along the smooth flat rails. The origin of the RailPOD’s coordinate system is centered on the outer surface of the back panel (-Z face), as shown below. The RailPOD can be mounted to launch vehicles on its +X, -X, -Y, and –Z faces.

Figure 2. RailPOD Generic Diagram and Coordinate System

+Y

+X +Z

(Deploy Direction)

Door Telemetry

Release Mechanism

Deployment Spring

Door Hinge

Door

Truss Structure


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1.3 RailPOD Quick Reference Table 1. RailPOD Quick Reference

ID Description Unit Specification 01 Dispenser Mass

(Empty, Vertical) Kg [lb] 1.29 [2.78]

02 Dispenser Mass (Empty, Horizontal)

Kg [lb] 1.35 [2.98]

03 Payload Mass (Maximum)

Kg [lb] 6.0 [13.2]

04 Payload Capacity

- Up to 3U, Compatible with Cal Poly Spec. and Tyvak 3U XL Spec.

05 Payload Ejection Energy

J [ft-lbf] 6.38 [4.71]

06 Door Open Angle

Degree 110

07 Maximum Expected Tipoff Rates

Deg/sec/axis 10 (Dependent on CubeSat mass properties and deployable configuration)

08 Dispenser Temperature Limits

°C [°F] -50 to +100 [-122 to +212]

09 Dispenser Vibration Limits

- Meets or exceeds: MIL-STD-1540, GSFC-STD-7000

10 Dispenser Shock Limits - Meets or exceeds: MIL-STD-1540, GSFC-STD-7000

11 Door Release Function Time

ms 100 (At 3.5A Actuation Current)

12 Release Mechanism Resistance (Stowed)

Ohm 0.6-1.3 (Dependent on harness configuration)

13 Release Mechanism Resistance (Deployed)

Ohm Open Circuit

14 Actuation Current (Minimum)

A 2.0

15 Actuation Pulse Duration (Minimum)

ms 180

16 Resistance of Telemetry Switch (Closed)


17 Resistance of Telemetry Switch (Open)

Ohm Open Circuit

18 Current Capacity of Telemetry Switch (Maximum)

A 5.0

19 Voltage Capacity of Telemetry Switch (Maximum)

V 175

20 Dispenser Country of Origin - Designed, manufactured, and assembled in the United States


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2.0 PAYLOAD INFORMATION 2.1 Mechanical Interfaces The RailPOD is a rail type satellite dispenser capable of carrying up to 3U’s of CubeSat payload. The payload can be either a single 3U CubeSat or a 3U compliment of multiple discrete U-Class spacecraft. CubeSat rails may be discontinuous, with at least 75% of aggregated rail length being preserved. Larger aggregated discontinuities can be accommodated and are approved on a case-by-case basis. The RailPOD rail is constructed using Aluminum 7075-T73 and the CubeSat interface is hard anodized to MIL-A-8625F Type III Class 1.

Figure 3. Flexible CubeSat Configuration Options

The RailPOD accommodates CubeSats designed to the Cal Poly CubeSat Design Specification (CDS) as well as the Tyvak 3U XL Specification. For more information on the Cal Poly CDS, visit www.cubesat.org. Payloads which design to the Cal Poly CDS are compatible with Tyvak dispenser systems.

The Tyvak 3U XL specification is a Tyvak specific accommodation which allows for additional payload volume. Payloads which design to the Tyvak 3U XL specification are compatible with Tyvak dispenser systems, but may not be compatible with 3rd party dispenser systems. High resolution mechanical interface drawings can be found in the Appendix.

CubeSats adjacent to the –Z RailPOD Pusher Plate interface may take advantage of the –Z Protrusion (3U+) payload volume. Typically, 3U sized CubeSats design for this accommodation, however smaller form factors may also make use the 3U+ volume. Payloads smaller than 3U should coordinate with Tyvak to ensure appropriate payload integration sequencing and compatibility.

Figure 4. Cal Poly CubeSat Design Spec. (Gray) and Tyvak 3U XL Extra Volume (Green)

One 2U and Two 0.5U Spacecraft

Three 1U Spacecraft

One 3U Spacecraft

*Section View*

-Z Protrusion Volume

http://www.cubesat.org/


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2.2 Deployment Switch, Access Port Interfaces, and Deployables The RailPOD can accommodate the Cal Poly standard CubeSat foot switch locations as well as non-standard foot switch locations such as rail switches and –Z perimeter switches. –Z perimeter switches can take advantage of surface area on the dispenser pusher plate outside of the Cal Poly standard CubeSat foot switch locations; rail switches utilize the smooth flat deployment rails to depress switches. Both rail and –Z perimeter switch designs can be accommodated and are approved on a case-by-case basis.

Figure 5. RailPOD Pusher Plate Payload Interface

To maintain compatibility with other dispenser systems, the RailPOD has been designed to support Cal Poly standard access port locations. The RailPOD, by virtue of the truss structure design, enables many points of un-obstructed payload access. If it is desired to access payloads outside the Cal Poly standard access port locations, contact Tyvak for additional details.

RailPOD payloads should constrain their deployables, to ensure smooth controlled deployment. The RailPOD can be configured to accommodate un-constrained deployables by means of inserts which provide smooth interior surfaces. If it is desired to implement un-constrained deployables, contact Tyvak for additional details.

Figure 6. Cal Poly Standard Access Port Location (Shown: Tyvak 3U XL)

Cal Poly Standard Switch Locations

(Red Areas)

-Z Perimeter Switch Locations

(Green Area)


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2.3 Deployment Dynamics Payloads are deployed by the main spring gliding along the smooth flat rails. The maximum expected tip off rate for payloads is 10 deg/axis/s, which is also dependent on CubeSat mass properties and deployable configuration. The spring is compressed when the payload is stowed, and allowed to extend once the door is commanded to open. The main spring can be designed to be more stiff or soft based on customer requirements, and payloads interested in main spring customization should contact Tyvak for more information.

Figure 7. Estimated Deployment Velocity for 3U Payloads

2.4 Integration Activities Integration of the CubeSat into the RailPOD dispenser is to be performed by trained personnel only. Integration typically takes place in class 100,000 clean room facilities, and requires one (1) payload technician to handle the spacecraft and two (2) RailPOD technicians to handle the RailPOD and perform quality assurance.

Prior to integration into the RailPOD, the CubeSats and RailPODs are inspected and measured to verify form and fit requirements. After integration, CubeSats are given the opportunity to perform pre-ship checkouts and/or charging. After delivery to the launch site, the hardware is handed over to the Launch Vehicle Provider.

Figure 8. Typical Integration Flow

1.2

1.4

1.6

1.8

2

2.2

2.5 3 3.5 4 4.5 5 5.5 6 6.5

Estim

ated�Deploym

ent�V

elocity

(m/s)

Payload�Mass(Kg)

𝒗, 𝒎/𝒔 = √𝟏𝟐. 𝟕𝟔

𝑴𝒂𝒔𝒔, 𝑲𝒈


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3.0 LAUNCH VEHICLE INFORMATION 3.1 Mechanical Interfaces 3.1.1 Vertical and Horizontal Mounting Configurations The RailPOD is designed to be mounted in either vertical or horizontal configurations. Interface and static envelope drawings are provided in the Appendix for both configurations.

Figure 9. Horizontal and Vertical Mounting of the RailPOD

3.1.2 Materials and Coatings The RailPOD is manufactured from Aluminum 7075-T73 and exhibits a truss-like structure. The RailPOD is Chemfilm Alodined to MIL-DTL-5541E, Class 3 and hard anodized to MIL-A-8625F Type III Class 1. Localized hard anodized coating provides a smooth low friction deployment surface for CubeSats that also prevents cold welding between working surfaces. Alodine is used at the Dispenser to Launch Vehicle interface, and provides a conductive interface to reliably ground the RailPOD.

3.1.3 Door Lock The RailPOD door, upon actuation, opens to 110° and locks into place using spring actuated locking elements. A 110° door open angle ensures adequate CubeSat deployment clearance, while minimizing deployed static envelope.

Figure 10. Deployed RailPOD

110°


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3.1.4 Mass Properties Mass, moment of inertia, and center of mass information for the RailPOD is provided below. These values are for reference only and the assumptions are as follows:

x The RailPOD is loaded with one 3U CubeSat with a uniformly distributed mass of 6 kg x The CubeSat’s center of mass is located at its geometric center. x The CubeSat is inertially axisymmetric about the RailPOD’s Z-axis. x A standard non-explosive actuator release mechanism is used on the RailPOD. x The RailPOD door is open 110° from the closed position for the post-deployment values. x Mass properties do not include harnessing, but do include the RailPOD’s door release

mechanism.

The RailPOD’s coordinate system is defined from the center of the outer surface of the back panel (-Z face), where the positive Y-axis comes out the top of the RailPOD; the positive Z-axis comes out the front (door) of the RailPOD, as shown in Figure 11.

Table 2. Mass Properties

Property Pre-Deployment(2) Post-Deployment(3)

Vertical Horizontal Vertical Horizontal Mass [Kg] 7.35 1.35 7.29 1.29

Center of Mass [cm]

Xg 0.0 0.0 0.0 0.0 Yg 0.1 -0.3 0.2 -0.1 Zg 22.8 24.8 22.9 25.5

Moment Of Inertia(1) [Kg-cm2]

Ixx 1116 375 1096 352 Iyy 1098 345 1079 322 Izz 201 86 197 82

(1) Moments of Inertia are calculated about the RailPOD’s Center of Mass (2) Values can vary significantly depending on CubeSat payload (3) Values can vary depending on harness configuration

Figure 11. RailPOD Coordinate System

3.1.5 Dynamic Properties The integrated RailPOD first natural frequency in the lateral directions (X, Y axis) is above 50 Hz. The integrated RailPOD first natural frequency in the axial direction (Z axis) is above 100 Hz.

+Y

+Z

+Y

+X


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3.2 Electrical Interfaces The RailPOD interfaces with the Launch Vehicle using three circuits: a primary release mechanism circuit, a secondary/redundant release mechanism circuit, and a door telemetry circuit. The circuits connect to the Launch Vehicle using a mutually agreed upon connector. Connectors typically are light weight, low outgassing, and thermally stable aerospace grade connectors. The following diagram is a general example of the electronic interface between the RailPOD and the launch vehicle. Contact Tyvak for more information about recommended connectors and capabilities. Deployment of CubeSats is initiated by an electric signal from the launch vehicle. The signal triggers the RailPOD door release mechanism, which in turn allows the door to open and deploy the satellites. In order to minimize shock to the CubeSats, the release mechanism does not utilize any pyrotechnics. One or two door state indication sensors installed on the RailPOD, near the door, are available to provide telemetry data to the launch vehicle. The switches are wired to create a closed circuit when the door is closed; and open circuit when the door is open.

Figure 12. RailPOD Circuit Diagram

Table 3. RailPOD Electrical Characteristics

Description Unit Specification Door Release Function Time

ms 100 (At 3.5A Actuation Current)

Release Mechanism Resistance (Stowed)


Release Mechanism Resistance (Deployed)

Ohm Open Circuit

Actuation Current (Minimum)

A 2.0

Actuation Pulse Duration (Minimum)

ms 180

Resistance of Telemetry Switch (Closed)


Resistance of Telemetry Switch (Open)

Ohm Open Circuit

Current Capacity of Telemetry Switch (Maximum)

A 5.0

Voltage Capacity of Telemetry Switch (Maximum)

V 175


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3.3 Operational Limits The RailPOD is designed for aerospace applications, and is suitable for use in space environments. The RailPOD is constructed using low outgassing components and materials. Space grade cabling, connectors, and coatings are used throughout.

Table 4. RailPOD Operational Limits

Description Unit Specification Dispenser Vibration Limits

- Meets or exceeds: MIL-STD-1540, GSFC-STD-7000

Dispenser Shock Limits - Meets or exceeds: MIL-STD-1540, GSFC-STD-7000

Dispenser Temperature Limits

°C [°F] -50 to +100 [-122 to +212]

3.4 Safety and Mission Assurance To ensure the safety of the Payload and reliability of the RailPOD, Tyvak employs quality control and traceable documentation processes during all stages of design, manufacture, assembly, test, and integration. Flight RailPODs are manufactured using certified materials, are precision verified, and assembled in class 100,000 cleanrooms. Tyvak technicians utilize calibrated tools and step-by-step procedures, creating traceable hardware history.

The RailPOD utilizes a Commercial Off The Shelf (COTS) release mechanism, designed for space applications. The COTS mechanism is factory tested and certified before qualified for use by Tyvak.

Tyvak has extensive experience certifying hardware for flight from major U.S. and International launch ranges. Through many successful launch campaigns, Tyvak has been able to incorporate safety approved elements, designed to simplify Missile System Prelaunch Safety Package (MSPSP) and flight safety review processes.

Figure 13. Tyvak Spacecraft Processing Facility (Left) Tyvak Launch Integration (Right)


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4.0 EXPANDABLE CAPABILITIES 4.1 Launch Integration Services Tyvak is a U.S. owned turn-key nano-satellite solutions provider. In addition to offering spacecraft and dispenser services, Tyvak provides launch services. Tyvak principals have over a decade of experience integrating small spacecraft to launch vehicles. To date (Dec 2016) the Tyvak launch services team has successfully launched more than 140 satellites, enabling over 75 unique satellite programs to reach orbit and perform critical missions servicing educational, commercial, and government markets. Tyvak’s approach reduces cost and enables seamless mission integration. Those interested in Tyvak launch services should contact Tyvak for more information.

Figure 14. Tyvak Launch Integration Services

4.2 Aggregated Missions Aggregated missions improve packing efficiencies, and enable more payload mass per mission. The Tyvak RailPOD can be combined with either Tyvak aggregated launch adapters or with other launch vehicle aggregated accommodations. The RailPOD’s flexible mounting configurations simplify interface patterns and reduce overall adapter mass. Examples of aggregated missions are shown below. Those interested in aggregated missions should contact Tyvak for more information.

Figure 15. Aggregated Mission Concepts


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4.3 Environment Isolation To accommodate payloads that are sensitive to vibration loads, shock loads, or thermal loads; the Tyvak RailPOD is designed to be compatible with standard environmental isolation solutions. There are a wide array of compatible isolator options, which can be tailored to customer requirements. Those interested in isolation should contact Tyvak for more information.

Figure 16. Thermally Isolated RailPOD (Left) and Vibration Isolation Test Data (Right)

4.4 Sun Shade Some payloads may request to be completely shaded from the sun from launch vehicle integration up through deployment. Tyvak offers customizable sun shades for both horizontal and vertical mounting configurations. The sun shades are typically coated with a white thermal protection coating, but can be designed and manufactured for a range of optical properties. Those interested in sun shades should contact Tyvak for more information.

Figure 17. RailPOD Without Sun Shade (Left) and With Sun Shade (Right)


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5.0 CONTACT US 5.1 About Tyvak Tyvak Nano-Satellite Systems Inc., a U.S. owned private company, provides turnkey nano-satellite solutions for civil and commercial customers around the world. At Tyvak, we make space research and utilization more accessible today than it has ever been by leveraging unparalleled industry knowledge with state-of-the-art technology to develop small satellite solutions at a fraction of the cost of traditional spacecraft developers. Tyvak’s nano-satellite systems are adaptable, have low power consumption and are easily customizable to support multiple applications.

5.2 U.S. Headquarters 15265 Alton Parkway, Suite 200 Irvine, CA 92618 949.753.1020 [email protected]

5.3 Websites http://www.tyvak.com http://www.cubesat.org

Mission / Spacecraft Development and Analysis

Launch Services Operations

mailto:[email protected]

http://www.tyvak.com/

http://www.cubesat.org/


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6.0 APPENDIX: HIGH RESOLUTION DRAWINGS

Table 5. List of Drawings

Number Description Drawing Number

01 Tyvak 3U XL Payload Specification Drawing TK-3UXLDS-01

02 Tyvak 3U XL CubeSat Acceptance Checklist 3U XL CAC

03 RailPOD Mechanical Interface (Horizontal) TK-RPMK2-MIH

04 RailPOD Stowed Envelope (Horizontal) TK-RPMK2-SSEH

05 RailPOD Deployed Envelope (Horizontal) TK-RPMK2-SDEH

06 RailPOD Mechanical Interface (Vertical) TK-RPMK2-MIV

07 RailPOD Stowed Envelope (Vertical) TK-RPMK2-SSEV

08 RailPOD Deployed Envelope (Vertical) TK-RPMK2-SDEV

100.00

100.00

50.00

50.00

A 27.00 3X 86.50 2X 27.00

340.50 0.3

72.50

13.75

170.25

CUBESAT RAILS

5.90 MIN

5.90 MIN

DETAIL ASCALE 1 : 1

ADDITIONAL NOTES:

CUBESAT COORDINATE SYSTEM LOCATION IN 1.THE GEOMETRICS CENTER OF THE CUBESATAT LEAST ONE DEPLOYMENT SWITCH MUST BE 2.INCORPORATED ON ALL CUBESATS ON THE -Z RAIL INTERFACEACCESS PORTS ARE LOCATED ON BOTH +/-X 3.SIDES

ACCESSPORT

ACCESSPORT

ACCESSPORT

+Y

+Z

ACCESSPORT

+Y

+X

RAIL AND ACCESS PORT DIMENSIONS

+Z +X

+Y

+Z +X

A

B

C

D

E

F

1 2 3 4 5 6 7

7654321

F

E

D

C

B

A

ALL DIMENSIONSIN MILLIMETERS

DRAWN BY:

DESIGNED BY:

CHECKED BY:

APPROVED BY:

DRAWING #: SCALE 1:4

SIZE

A

REVISION

TYVAK NANO-SATELLITE SYSTEMS 15265 ALTON PARKWAY, SUITE 200

IRVINE, CA [email protected]

ASSEMBLY

DATE: 1SHEET OF 3

PART NAME

1ROUND OR BREAK

EDGES AND CORNERS

J.CAR

A. KRU

CUBESAT SPECIFICATION

TOLERANCE:.XX 0.10

UNLESS NOTED

TK-3UXLDS-01

3U XL CUBESAT

21 NOV 2016

J.CAR

R.COE

10.00 MAX

10.00 MAX

10.00 MAX

B

HATCH AREAS REPRESENTALLOWABLE PROTRUSIONENVELOPES

DETAIL BSCALE 1 : 1

PROTRUSIONS SHALL BE BELOW THE RAILSURFACE ON THE +/-ZFACES

ACCESSPORT

ACCESSPORT

+Y+Y

+X

MAXIMUM ALLOWABLE PROTRUSIONS

ADDITIONAL NOTES:

NO EXTERNAL COMPONENTS OTHER THAN THE 4.RAILS SHALL TOUCH THE INSIDE OF THE DISPENSER. EXCEPTOINS CAN BE EVALUATED ON A CASE-BY-CASE BASIS.

ACCESSPORT+Z

A

B

C

D

E

F

1 2 3 4 5 6 7

7654321

F

E

D

C

B

A


DRAWN BY:

DESIGNED BY:

CHECKED BY:

APPROVED BY:


SIZE

A

REVISION



ASSEMBLY

DATE: 2SHEET OF 3

PART NAME

1J.CAR


TOLERANCE:.XX 0.10

UNLESS NOTED

TK-3UXLDS-01

3U XL CUBESAT

21 NOV 2016

ROUND OR BREAK EDGES AND

CORNERS

J.CAR

R.COE

A.KRU

50.00 MAX 88.00 MAX

50.00

50.00 ACCESS

PORTACCESS

PORT

+Y

+Z

"TUNA CAN" PROTRUSIONS

ADDITIONAL NOTES:

"TUNA CAN" EXTENSION DIMENSIONS INCLUDE 5.DYNAMIC CLEARANCE CONSIDERATIONS."TUNA CAN" EXTENSIONS ARE PROTECTED PAYLOAD 6.VOLUMES, HOUSED SEPARATELY FROM THE MAIN DEPLOYMENT SPRING.LARGER "TUNA CAN" EXTENSION VOLUMES CAN BE 7.EVALUATED ON A CASE-BY-CASE BASISSATELLITE DEPLOYS FROM DISPENSER IN THE +Z 8.DIRECTION.

ACCESSPORT

A

B

C

D

E

F

1 2 3 4 5 6 7

7654321

F

E

D

C

B

A


DRAWN BY:

DESIGNED BY:

CHECKED BY:

APPROVED BY:


SIZE

A

REVISION



ASSEMBLY

DATE: 3SHEET OF 3

PART NAME

1ROUND OR BREAK

EDGES AND CORNERS

J.CAR

A. KRU


TOLERANCE:.XX 0.10

UNLESS NOTED

TK-3UXLDS-01

3U XL CUBESAT

21 NOV 2016

J.CAR

R.COE

3U XL CubeSat Acceptance Checklist

(3U XL CAC) 08December2016

Version1Project/Mission: Date/Time: Engineers:Organization: Location:SatelliteName: SatelliteS/N: Mass(<6.0kg) ___________ RBFPin(≤10mm) ____________SpringPlungers(Depressed)

FunctionalY/N/NAFlushwithStandoff(Y/N/NA) RailsAnodized Y/N

DeploymentSwitches(Depressed)

FunctionalY/NFlushwithStandoff(Y/N)

DeployablesConstrained

Y/N/NA

MarkonthediagramthelocationsoftheRBFpin,connectors,deployables,andanyenvelopeviolations.

ListItem AsMeasured Required

Width[X-Y] +Z(0/3rd) Middle(1/3rd) Middle(2/3rd) -Z(3/3rd)

Side1(-Y) ____________ ____________ ____________ ____________ 100.0+0.1/-0.5mm

Side2(-X) ____________ ____________ ____________ ____________ 100.0+0.1/-0.5mm

Side3(+Y) ____________ ____________ ____________ ____________ 100.0+0.1/-0.5mm

Side4(+X) ____________ ____________ ____________ ____________ 100.0+0.1/-0.5mm

Height[Z] Rail1(+X,-Y) Rail2(-X,-Y) Rail3(-X,+Y) Rail4(+X,+Y)

____________ ____________ ____________ ____________ 340.5±0.3mm

Rail1(+X,-Y) Rail2(-X,-Y) Rail3(-X,+Y) Rail4(+X,+Y) lengthxwidth lengthxwidth lengthxwidth lengthxwidth

+ZStandoffs _____x_____ _____x_____ _____x_____ _____x_____ ≥5.9mm

-ZStandoffs _____x_____ _____x_____ _____x_____ _____x_____ ≥5.9mm

Protrusions Side1(-Y) Side2(-X) Side3(+Y) Side4(+X) Side5(-Z) Side6(+Z)

_______ _______ _______ _______ _______ _______ ≤10mm

TunaCan Length _______ ≤50mm Approval IT#1: ________________

MaximumRadius

_______

≤44mm

FromCenter

IT#2: ________________

Fitcheck _______ Go/NoGo Passed? Yes/No

THIRD ANGLE PROJECTION

DEPLOYMENT DIRECTION

MOUNTING SURFACE

4.250107.950

6.245158.623

4.425112.395

6X #10-32 LOCKING STINITRONIC 60MAX FASTENER .345 [8.763]MIN FASTENER .220 [5.588]

SCALE 1 : 4

← ←↑+Y

+Z

+Z

+X

↑←

TK-RPMK2-MIHSHEET 1 OF 1SCALE: 1:2

REVDWG. NO.

BSIZE

TITLE:

NAME DATE

TYVAK NANO-SATELLITE SYSTEMS, INC.15265 ALTON PARKWAY, SUITE 200

IRVINE, CA 92618WWW.TYVAK.COM

APPROVAL

ENGINEER

CHECKED

DRAWNUNLESS OTHERWISE SPECIFIED:DIMENSIONS ARE IN INCHESBRACKETED DIMENSIONS IN MMDO NOT SCALE DRAWING

A

INTERFACE, MECHANICAL,HORIZONTAL MOUNT, RAILPOD MK. II

NOTES (UNLESS OTHERWISE SPECIFIED):

MOUNTING SURFACE IS CHEMFILMED ALUMINUM AND 1.ELECTRICALLY CONDUCTIVE.

SEE TK-RPMK2-SSEH AND TK-RPMK2-SDEH DRAWINGS 2.FOR STATIC STOWED AND DEPLOYED ENVELOPE DRAWINGS, RESPECTIVELY.

INTERPRET DRAWING PER ANSI Y14.5-2009

REVISION DATE COMMENTS

MAX

CAGE CODE

6J8J8

A. KRUGGEL

A. KRUGGEL

12/15/16

125

A 12/15/16 INITIAL RELEASE

V. KAUSHISH

A A

B B

4

4

3

3

2

2

1

1

J. CARNAHAN

12/15/16

12/15/16

12/15/16


12.789324.842

6.

726

170.

840

15.480393.192

8.

185

207.

899

0.

927

23.5

46

MOUNTING INTERFACE


0.85021.590

17.379441.423

0.

669

16.9

80

5.

762

146.

355

+Z

+Y

↑→

→↓+X

+Z

→

A A

B B

4

4

3

3

2

2

1

1

TK-RPMK2-SSEHSHEET 1 OF 1

12/14/16A.KRUGGEL

J.CARNAHAN

V.KAUSHISH

SCALE: 1:4

REVDWG. NO.

BSIZE

TITLE:

NAME DATE



APPROVAL

ENGINEER

CHECKED


A

RAILPOD MK. II HORIZONTAL STATIC STOWED ENVELOPE



R.COELHO

12/14/16

12/14/16

12/14/16


CAGE CODE6J8J8


DIMENSIONS REPORTED IN THIS DOCUMENT ARE 1.MAXIMUM ENVELOPE DIMENSIONSSEE TK-RPMK2-MIH DRAWING FOR RAILPOD MK. II 2.HORIZONTAL MECHANICAL INTERFACE DETAILS


12.789324.841

6.

726

170.

840

15.480393.192

11

.262

286.

046

0.

927

23.5

46


MOUNTINGINTERFACE

→

0.85021.590

23.548598.119

5.

762

146.

355

0.

669

16.9

80

→↑+Y

+Z

+Z

+X

↓→

A A

B B

4

4

3

3

2

2

1

1

TK-RPMK2-SDEHSHEET 1 OF 1

12/14/16A.KRUGGEL

J.CARNAHAN

V.KAUSHISH

SCALE: 1:4

REVDWG. NO.

BSIZE

TITLE:

NAME DATE



APPROVAL

ENGINEER

CHECKED

DRAWNUNLESS OTHERWISE SPECIFIED:DIMENSIONS ARE IN INCHESBRACKETED DIMENSIONS IN MM

DO NOT SCALE DRAWING

A

RAILPOD MK. II HORIZONTAL STATICDEPLOYED ENVELOPE



R.COELHO

12/14/16

12/14/16

12/14/16

A 12/14/2016 INITIAL RELEASENOTES (UNLESS OTHERWISE SPECIFIED):

DIMENSIONS REPORTED IN THIS DOCUMENT ARE 1.MAXIMUM ENVELOPE DIMENSIONSSEE TK-RPMK2-MIH DRAWING FOR RAILPOD MK. II 2.HORIZONTAL MECHANICAL INTERFACE DETAILS

6J8J8CAGE CODE


.205

.1955.2074.953

MOUNTING PLATETHICKNESS

MOUNTING SURFACE


.450 [11.430] MAX WASHER DIA4 PL

4.520114.808

4.520114.808

4X .206.200

5.2325.080 THRU

FOR #10 SIZE FASTENER

SCALE 1 : 4

←

←↑+Y

+X+Z

+Y

↑←

TK-RPMK2-MIVSHEET 1 OF 1SCALE: 1:2

REVDWG. NO.

BSIZE

TITLE:

NAME DATE



APPROVAL

ENGINEER

CHECKED


A

INTERFACE, MECHANICAL,VERTICAL MOUNT, RAILPOD MK. II


MOUNTING SURFACE IS CHEMFILMED ALUMINUM AND 1.ELECTRICALLY CONDUCTIVE.

SEE TK-RPMK2-SSEV AND TK-RPMK2-SDEV DRAWINGS 2.FOR STATIC STOWED AND DEPLOYED ENVELOPE DRAWINGS, RESPECTIVELY.



MAX

CAGE CODE

6J8J8

A. KRUGGEL

A. KRUGGEL

12/15/16

125


V. KAUSHISH

J. CARNAHAN

12/15/16

12/15/16

12/15/16

A A

B B

4

4

3

3

2

2

1

1


14.980380.492

8.

185

207.

899

6.

562

166.

675

0.

927

23.5

46

12.289312.137

DEPLOYMENTDIRECTION

5.

762

146.

355

16.879428.723

MOUNTING INTERFACE

0.62115.773

0.

621

15.7

73

+Z

+Y

↑→ →

↓+X

←+Y →↓+X

+Z

A A

B B

4

4

3

3

2

2

1

1

TK-RPMK2-SSEVSHEET 1 OF 1

12/16/16A.KRUGGEL

J.CARNAHAN

V.KAUSHISH

SCALE: 1:4

REVDWG. NO.

BSIZE

TITLE:

NAME DATE



APPROVAL

ENGINEER

CHECKED


A

RAILPOD MK. II VERTICAL STATIC STOWED ENVELOPE



R.COELHO

12/16/16

12/16/16

12/16/16


CAGE CODE6J8J8


DIMENSIONS REPORTED IN THIS DOCUMENT ARE 1.MAXIMUM ENVELOPE DIMENSIONSSEE TK-RPMK2-MIV DRAWING FOR RAILPOD MK. II 2.VERTICAL MECHANICAL INTERFACE DETAILS


14.980380.492

11

.362

288.

586

12.289312.141

0.

927

23.5

46

6.

562

166.

675


→

SCALE 1:8

+Z

+X

↓→

23.048585.419

5.

762

146.

355

MOUNTING INTERFACE

0.62115.773

0.

621

15.7

73

+Z

+Y

↑→

+Y←+X

↓

A A

B B

4

4

3

3

2

2

1

1

TK-RPMK2-SDEVSHEET 1 OF 1

12/16/16A.KRUGGEL

J.CARNAHAN

V.KAUSHISH

SCALE: 1:4

REVDWG. NO.

BSIZE

TITLE:

NAME DATE



APPROVAL

ENGINEER

CHECKED

DRAWNUNLESS OTHERWISE SPECIFIED:DIMENSIONS ARE IN INCHESBRACKETED DIMENSIONS IN MM

DO NOT SCALE DRAWING

A

RAILPOD MK. II VERTICAL STATICDEPLOYED ENVELOPE



R.COELHO

12/16/16

12/16/16

12/16/16

A 12/16/2016 INITIAL RELEASENOTES (UNLESS OTHERWISE SPECIFIED):

DIMENSIONS REPORTED IN THIS DOCUMENT ARE 1.MAXIMUM ENVELOPE DIMENSIONSSEE TK-RPMK2-MIV DRAWING FOR RAILPOD MK. II 2.VERTICAL MECHANICAL INTERFACE DETAILS

6J8J8CAGE CODE

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