Attachment A.3 12U Deployer_UserGuide_TYVAK-8005_November 2019_1.pdf

TYVAK-8005-Rev1 November 2019

Tyvak 12U Deployer

User Guide for Payloads and Launch Vehicles

(TYVAK-8005-Rev1)

COPYRIGHT © 2019 TYAVK NANO-SATELLITE SYSTEMS, INC. All rights reserved.

This User’s Guide provides a general overview of Tyvak’s 12U Deployer offered to customers. For detailed, mission-specific inquiries, please contact virag.shah@tyvak.com

CAPSTONE ATTACHMENT A.3, 12U DEPLOYER_USERGUIDE_TYVAK-8005_NOVEMBER2019 80KSC020R0003

TABLE OF CONTENTS

1.0 INTRODUCTION

1.1 Background

1.1 General Description, Payload Mass Capability, and Coordinate System

1.1.1 General Description

1.1.2 Mass Capabilities

1.1.3 Coordinate System

2.0 PAYLOAD INFORMATION

2.1 Mechanical Interfaces

2.2 Deployment Switch, Access Port Interfaces, and Deployables

2.2.1 Deployment Switch Locations

2.2.2 Access Port Interfaces

2.2.3 CubeSat Deployables

2.3 Deployment Dynamics

2.3.1 Tip-Off Rates

2.3.2 Deployment Velocity

2.4 Payload Environments

2.4.1 Payload Boundary Conditions

2.4.2 Payload Isolation

2.5 Deployer Options

2.5.1 Contamination-Sensitive Payloads

2.5.2 Optional Door Components

2.5.3 Test fixture

2.6 Integration Activities

3.0 LAUNCH VEHICLE INFORMATION

3.1 Mechanical Interfaces

3.1.1 Vertical and Horizontal Mounting Configurations

3.1.2 Materials and Coatings

3.1.3 Door Lock

3.1.4 Dynamic Properties

3.2 Mass Properties

3.3 Electrical Interfaces

3.4 Operational Limits

3.5 Safety and Mission Assurance

4.0 EXPANDABLE CAPABILITIES

4.1 Launch Integration Services

4.2 Aggregated Missions

5.0 CONTACT US

5.1 About Tyvak

5.2 U.S. Headquarters

5.3 Website

6.0 APPENDIX: HIGH RESOLUTION DRAWINGS

List of Figures

Figure 1. Generic 12U CubeSat with the 12U Deployer Figure 2. 12U Deployer Generic Diagram and Coordinate System Figure 3. Generic CubeSat meeting the Tyvak 12U Specification Figure 4. Access Port Locations Figure 5. Estimated Deployment Velocity for 12U Payloads Figure 6. Four Corner Payload Cradling in Stowed (L) and Deployed (R) Configurations Figure 7. Payload Boundary Conditions on Feet (L) and Rails (R) Figure 8. Payload Isolation Schematic, Full 3-axis Isolation is Achieved Figure 9 Effects of Internal Isolation System on Stowed CubeSat Figure 10. Optional Deployer Door On (L) and Off (R), with Extra Volume Example Figure 11. Payload Test Fixture Figure 12. Typical Integration Flow Figure 13. Horizontal (L) and Vertical (R) Mounting of the Tyvak 12U Deployer Figure 14. Deployed Tyvak 12U Deployer Figure 15. Tyvak 12U Deployer Circuit Diagram Figure 16. Tyvak 12U Deployer Undergoing Vibration Testing Figure 17. Tyvak Launch Integration Services Figure 18. Aggregated Mission Concepts ............................................................. Error! Bookmark not defined.

List of Tables

Table 1 Payload Mass Information Table 2 Separation Characteristics Table 3. Mass Properties Table 4 Tyvak 12 Disperser Electrical Characteristics Table 5 Tyvak 12U Deployer Operational Limits Table 6. List of Drawings

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. The CubeSat Design Specification, or CDS, includes information regarding spacecraft nominal dimensions, dimensional tolerances, acceptable materials, reference coordinate system, and other general information. The basic “1U” CubeSat measures 100mm x 100mm x 100mm.

The Poly Picosatellite Orbital Deployer (P-POD) was developed to provide a universal launch vehicle interface as well as deployment mechanism for CubeSats. The P-POD is a rail design and accommodates up to a “3U” CubeSat measuring 340.5mm x 100mm x 100mm. Deployers now also exist to launch “6U” CubeSats.

Missions now require even larger CubeSat sizes. Tyvak provides the Tyvak 12U Deployer to accommodate the 12U CubeSat form factor (2U X 2U X 3U). This User Guide contains important information for both satellite developers and launch providers.

1.1 General Description, Payload Mass Capability, and Coordinate System

1.1.1 General Description

The Tyvak 12U Deployer (Figure 1) is a rail type satellite deployer capable of carrying a 12U CubeSat payload and serves as the interface between the CubeSat and Launch Vehicle (LV). The Deployer is a rectangular metallic structure made of high-strength aluminum, an ejection spring mechanism, an internal rail system that clamps and restrains the CubeSat, and an optional two-piece door. The panels can be made of aluminum or carbon fiber depending on mission requirements.

Figure 1. Generic 12U CubeSat with the 12U Deployer

Unlike other rail designed deployers, the CubeSat is not restrained by the door nor is the satellite free to “float” within the deployer rails. The Tyvak deployer has a unique design that “cradles” all four CubeSat rails. The deployer rails and swivel clamps restrain the satellite in all three axes and the door is not a structural

2.0 PAYLOAD INFORMATION

2.1 Mechanical Interfaces

The Tyvak 12U Deployer is a rail type satellite deployer capable of carrying a single 12U CubeSat payload. CubeSat rails may be discontinuous between the CubeSat standoffs, with at least 75% of aggregated rail length being preserved on each rail Figure 3. Larger aggregated discontinuities can be accommodated and are addressed on a case-by-case basis. The Tyvak 12U Deployer/CubeSat interface rails are constructed using aluminum and are hard anodized to MIL-A-8625F Type III to prevent cold welding of working surfaces.

Figure 3. Generic CubeSat meeting the Tyvak 12U Specification

The Tyvak 12U Deployer accommodates CubeSats designed to the Tyvak 12U Specification, TK-12UDS-03. This specification is provided in the Appendix. The CubeSat may take advantage of the four -Z Protrusion payload volumes each with a diameter up to 88 mm and a height up to 50 mm beyond the -Z rail feet.

2.2 Deployment Switch, Access Port Interfaces, and Deployables

2.2.1 Deployment Switch Locations

The Tyvak 12U Deployer accommodates the standard CubeSat foot switch locations on the -Z rail standoffs. In addition, rail and -Z perimeter switches can be approved on a case-by-case basis. Rail switches utilize the deployment rails to depress switches and –Z perimeter switches take advantage of surface area on the deployer pusher plate outside of the standard CubeSat foot switch locations. More information about the deployer contact zones can be found in Section 2.4.1.

2.2.2 Access Port Interfaces

The Tyvak 12U Deployer has been designed to support access port locations on the +/-X and +/-Y panels shown in Figure 4. Contact Tyvak for additional details if access to payloads outside of these standard access port locations is required.

2.3.2 Deployment Velocity

Figure 5 depicts deployment velocities for the two possible spring configurations and associated payload mass.

Figure 5. Estimated Deployment Velocity for 12U Payloads

2.4 Payload Environments

2.4.1 Payload Boundary Conditions

Previous users of rail-type deployers faced the challenge of modeling the dynamic response of their satellite due to the “floating” nonlinear boundary condition between it and the deployer. The Tyvak 12U deployer solves this problem by incorporating movable rails that cradle the payload and provide an analyzable boundary condition shown in Figure 6. This mechanized rail interface allows the analyst to accurately predict transmissibility to the satellite and reduce the uncertainty in mechanical loads.

The Tyvak 12U Deployer utilizes four corner payload cradling rails that provide a constant boundary condition in all 3-axis. When stowed, the deployer rails extend inward and contact the payload rails. When commanded to deploy, the payload rails retract to allow smooth deployment of the payload.

Figure 6. Four Corner Payload Cradling in Stowed (L) and Deployed (R) Configurations

To accurately model the spacecraft interface to the deployer, the following deployer contact areas should be modeled (Figure 7):

1. The feet maintain contact with the deployer across the entire +/-Z rail surface.

2. The rails maintain contact with the deployer along a line at 4.9 mm (0.193 in) from the rail edge. This rail contact should be applied to both sides of each rail corner, for a total of eight contact lines.

Figure 7. Payload Boundary Conditions on Feet (L) and Rails (R)

2.4.2 Payload Isolation

The Tyvak 12U Deployer incorporates a first-of-its-kind full 3-axis internal isolation, reducing vibration and shock environments for payloads that eliminates the need for costly and volume-consuming external isolation.

The internal isolation is placed between inner and outer structures as shown in Figure 8. The inner structure rides on these isolators, providing a damped environment for payloads. The outer structure remains a more rigid interface for launch vehicles. Lower launch loads allow the developer to focus on the space application versus surviving the launch environment. A more benign launch environment also results in an increased likelihood of passing environmental testing and improved on-orbit performance. Figure 9 demonstrates isolation transmissibility test results characterizing the damping efficiency of the isolation system.

Thermal isolation solutions can also be applied to the deployer to reduce hot and cold extreme conditions for flight.

Figure 8. Payload Isolation Schematic, Full 3-axis Isolation is Achieved

Figure 9 Effects of Internal Isolation System on Stowed CubeSat

2.5 Deployer Options

2.5.1 Contamination-Sensitive Payloads

They Tyvak 12U Deployer is maintained at a Generally Clean (GC) level. Generally Clean is defined as free of particulate and non- particulate visible to the normal unaided eye (except for 20-20 corrected vision) when inspected from a distance of 6 to 18 inches with a surface illumination of 100- 125 ft-candles of light. Higher levels of cleanliness can be achieved by means of special handling and build of the Tyvak 12U deployer. Please contact Tyvak if a higher level of cleanliness is required.

2.5.2 Optional Door Components

The Tyvak 12U Deployer utilizes an optional door designed to enclose payloads. If desired, the door may be removed without affecting deployer function or payload deployment dynamics. With the door removed, payloads have additional volume as shown in Figure 10 to use on a mission specific basis. This option may be limited by launch configuration and available volume surrounding the 12U deployer. If payloads are interested in utilizing extra volume afforded by removing the optional door, please contact Tyvak to discuss launch configurations and other considerations.

Figure 10. Optional Deployer Door On (L) and Off (R), with Extra Volume Example

3.0 LAUNCH VEHICLE INFORMATION

3.1 Mechanical Interfaces

3.1.1 Vertical and Horizontal Mounting Configurations

The Tyvak 12U Deployer is designed to be mounted in either vertical or horizontal configurations as depicted in Figure 13.

Figure 13. Horizontal (L) and Vertical (R) Mounting of the Tyvak 12U Deployer

3.1.2 Materials and Coatings

The primary Tyvak 12U Deployer structure is manufactured from aluminum and carbon fiber composite. The Tyvak 12U Deployer structure is Chemfilm Alodined to MIL-DTL-5541E, Class 3 and/or hard anodized to MIL-A- 8625F Type III. Localized hard anodized coating on all rail surfaces provides a smooth low friction deployment surface for CubeSats that also prevents cold welding between working surfaces. All launch vehicle interface surfaces are Alodined to provide a conductive interface and reliable ground.

3.1.3 Door Lock

The Tyvak 12U Deployer doors open to 105° (Figure 14) upon actuation and lock into place using spring actuated locking elements. A 105° door open angle ensures adequate CubeSat deployment clearance, while minimizing deployed static envelope.

Figure 14. Deployed Tyvak 12U Deployer

3.5 Safety and Mission Assurance

To ensure the safety of the Payload and reliability of the Tyvak 12U Deployer, Tyvak employs quality control and traceable documentation processes during all stages of design, manufacture, assembly, test, and integration.

Tyvak 12U Deployers are manufactured using certified materials, are precision verified, and assembled in a clean environment. Tyvak technicians implement aerospace industry practices throughout the build process, from detailed purchase documentation, thorough oversight of vendor-procured hardware, mandatory use of calibrated tools, strict engineering drawing control, extensive training, and step-by-step procedures verified by QA at critical points that are documented electronically. This results in a traceable womb-to-tomb history of all Tyvak-built systems with complete build configuration verification and control. New part revisions are traced using a revision control process.

Tyvak has extensive experience certifying hardware for flight from major U.S. and International launch ranges.

We have successfully integrated missions on 13 different launch vehicles for both government and commercial customers. As a result of these 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 16. Tyvak 12U Deployer Undergoing Vibration Testing

5.0 CONTACT US

5.1 About Tyvak

Tyvak Nano-Satellite Systems, Inc., a U.S.-owned, private company, provides end-to-end small satellite solutions for civil, defense and commercial customers worldwide. 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 spacecraft systems are adaptable, have low power consumption and are easily customizable to support multiple applications.

5.2 U.S. Headquarters

15330 Barranca Pkwy Irvine, CA 92618 949.753.1020 info@tyvak.com

5.3 Website

http://www.tyvak.com

Mission / Spacecraft

Development and Analysis

Launch Services Operations