EXOLAUNCH Nova CubeSats And Microsatellites User Manual
- August 14, 2024
- EXOLAUNCH
Table of Contents
EXOLAUNCH Nova CubeSats And Microsatellites
Specifications
- Product Name: EXOpod Nova
- Type: Advanced Cubesat deployment system
- Revision: 1.2
- Release Date: June 2024
Product Information
The EXOpod Nova is an advanced Cubesat deployment system designed for
launching small satellites into space. It features components such as
redundant magnetic locks, door status indicators, set screws, an RBF pin for
the door, and a removable access window.
Components and Features
The main components of the EXOpod Nova include:
- Redundant Magnetic Locks
- Door Status Indicators
- Set Screws
- RBF Pin (Door)
- Removable Access Window
Purpose and Applicability
The EXOpod Nova is used for deploying Cubesats into space during dedicated rideshare missions. It is suitable for various launch vehicles and has been successfully used in missions like SpaceX Falcon 9 and Rocket Lab’s launches.
Quality Assurance
The product undergoes rigorous quality assurance testing to ensure reliability and performance during satellite deployment missions. It has a proven flight heritage and has been qualified through environmental testing.
Qualification and Flight Heritage
The EXOpod Nova has been tested for environmental qualifications and has a successful flight heritage, making it a reliable choice for Cubesat deployment missions. It has been used in various missions with multiple successful deployments.
FAQs
Q: What are the main components of the EXOpod Nova?
A: The main components include redundant magnetic locks, door status
indicators, set screws, RBF pin for the door, and a removable access window.
Q: In which missions has the EXOpod Nova been used?
A: The EXOpod Nova has been used in missions such as SpaceX Falcon 9,
SpaceX Transporter-5, Rocket Lab’s Four Of A Kind mission, and more.
EXOpod Nova User Manual Revision 1.2 / June 2024
EXOpod
NOVA
User Manual
Advanced Cubesat deployment system Revision 1.2 | June 2024
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EXOpod Nova User Manual Revision 1.2 / June 2024
Authors Name
Michael Tolstoj Till Siebert
Contact michael@exolaunch.com
till@exolaunch.com
Initials MT TS
Change Log
Version Author
Date
Changes
0.1
MT 18.10.2021 Pre-release version.
0.2
MT 07.02.2022 Pre-release version. Updated pinout table description, thermal qualification description
– Layout updated.
– Extended description in chapter 1.
– Updated Cubesat volume requirements in section 2.3.
– Updated allowable tolerance of Cubesat Z-axis length in Table 1.
– Moved mass properties to Appendix A and B.
1.0
MT
06.09.2022
– 12U S1 and S2 and 16U configurations added. – Added deployment energy values and deployment time calculation in section 2.4.
– Updated mounting torque of main interface in section 4.1.
– Updated description of lifting interface in section 4.1.4.
– Added Telemetry Toggler RBF description in section 5.2.
– Updated thermal interface description in chapter 6.
– Added information on transportation and satellite integration in chapter 7.
– Added 8U NOVA deployer in section 2.2 – Added 4U/8U NOVA Cubesat information in section 2.3 – Added new slot adapters in section 3.4 with mass properties in appendix 7.4D – Rework of the FEM modeling section in section 3.5 1.1 TS, MT 06.03.2024 – Added different mounting configurations in section 4.1 – Updated Nova 16U Bottom Plate Mounting interface in section 4.1.2 – Added different lifting configurations in section 4.1.3 – Added access window location for 16U Nova in section 4.2.5 – Added information about the Nova product ecosystem in section 7
– Added more detailed breakout of allowable Cubesat masses in Table 1
– Updated information on cubesat slot adapters in section 3.4
1.2
MT
17.06.2024
– Added information on vibration and shock loads experienced in Nova in section 3.5 – Updated lifting interface information in section 4.1.3
– Updated no-fire current and fixed typo (swapped Actuator 1 and 2) in Figure 36 in
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EXOpod Nova User Manual Revision 1.2 / June 2024
Introduction
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EXOpod Nova User Manual Revision 1.2 / June 2024
What is the EXOpod Nova?
Cubesats have been extremely successful in facilitating access to space. Since
California Polytechnic State University (Cal Poly) and Stanford University
introduced the Cubesat Design Specification in 1999, more than 1,500 Cubesats
have been launched into Low Earth Orbit. Their small size and low mass,
combined with standardized separation systems that are universally compatible
with any launch vehicle, have allowed Cubesats to become an increasingly
valuable asset to the New Space industry. Their design provides affordable
access to space, while enabling the development and use of fascinating new
technologies which would not be otherwise feasible.
Since 2017, Exolaunch has supported the conquest of space by Cubesats by successfully launching and deploying 270+ Cubesats between 0.25U and 16U using its market leading EXOpod Cubesat deployer family. However, Cubesat technology has come a long way since its initial inception, and the growing demands of the market are pushing the design of traditional deployer systems to their limits. Satellite developers are continuously pushing the boundaries of the Cubesat Design Specification by increasing mass, volume, and overall complexity in order to achieve performance improvements. At the same time, constellations comprising of hundreds of Cubesats are demonstrating new technologies and enabling new applications consequently, the number of Cubesats launched each year is steadily growing.
Exolaunch has developed its EXOpod Nova Advanced Cubesat Deployer within this
context. Nova is a state-of-theart separation system, built on years of
experience working with leading Cubesat developers and launch providers, and
is set to redefine the term “Cubesat”. Nova offers up to four times more space
for lateral protrusions, while also increasing the possible mass capacity by
up to 33% compared to other deployers on the market. Building on the
significant flight heritage and inheriting the best features of EXOpod, Nova
adds new capabilities, boosts performance, and further increases reliability.
Figure 1: Two EXOpod Nova deployers during launch vehicle integration on a
SpaceX Falcon 9.
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EXOpod Nova User Manual Revision 1.2 / June 2024
Figure 2: EXOpods as part of the SpaceX Transporter-1 dedicated rideshare mission.
Figure 3: EXOpod Nova deploying a Cubesat on the SpaceX Transporter-5 mission in May 2022.
Figure 5: Four EXOpod Nova flying on Rocket Lab’s “Four Of A Kind” mission in January 2024.
Figure 4: Fifteen Novas launched on SpaceX’s Transporter-9 mission in November 2023.
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EXOpod Nova User Manual Revision 1.2 / June 2024
Purpose and Applicability
This User Manual defines the interface requirements between EXOpod Nova and Cubesats for developers using Exolaunch launch services and products, as well as for launch providers. EXOpod Nova is designed as a standardized deployment system to launch and deploy any satellite that complies with the Cubesat Design Specification Rev. 14. Note that if there is any conflicting information between the CDS and the Nova User Manual, the Nova User Manual takes priority.
EXOpod Nova also allows for the deployment of Cubesats that exceed the limits of the Cubesat Design Specification in several key domains, which this User Manual in turn defines. The document also specifies the minimum requirements for compatibility with EXOpod Nova and the Launch Vehicle flight safety program when using Exolaunch services. This includes a description of all mechanical, thermal, and electrical interfaces, as well as their performance specifications. This document is valid until it is rescinded by Exolaunch or is superseded by a subsequent document version.
Quality Assurance
Quality assurance for the EXOpod Nova separation system is ensured at every
step of the production chain. The entire production line fulfils or exceeds
the highest quality assurance requirements. The facilities that manufacture
Exolaunch products are certified to ISO 9001:2015 standard, which requires
regular inspection of the manufacturing and assembly facilities and ensures a
consistently high quality of the final product. These exceptional quality
standards are also applied to the extensive qualification and acceptance
testing processes.
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EXOpod Nova User Manual Revision 1.2 / June 2024
Qualification and Flight Heritage
EXOpod Nova has flight heritage from the SpaceX Transporter Rideshare Program
as well as from Rocket Lab’s Electron and ISRO’s PSLV and is manifested for
launch on various other launch vehicles. Nova has been qualified to the launch
environments, including vibration, shock and thermal vacuum, of all of
Exolaunch’s launch partners, including Falcon 9 and Falcon Heavy, PSLV, Ariane
6, Vega-C, Electron, Spectrum and others. Regular delta qualifications ensure
that the system is compatible with new emerging launch vehicles on the market,
as well as with evolving customer requirements. In addition, the deployer has
inherited most of its features and mechanisms from the EXOpod deployer family
which has established flight heritage since 2017. To date, the EXOpod and
EXOpod Nova family of deployers has launched on 19 missions and has
successfully deployed over 270 Cubesats between 0.25U to 16U into orbit
without failure. In 2023, EXOpod was flight qualified for higher radiation
environments as it successfully delivered a commercial 16U satellite to GEO.
The flight trajectory featured a coast through the Van Allen belts.
Figure 6: EXOpod Nova during environmental qualification testing.
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EXOpod Nova User Manual Revision 1.2 / June 2024
EXOpod NOVA Advanced Cubesat Deployer
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EXOpod Nova User Manual Revision 1.2 / June 2024
2.1 Components and Features
The main components of the EXOpod Nova are shown in Figure 7. Each component
is described in detail later in the document.
Redundant Magnetic Locks
Door Status
Set Screws
RBF Pin (Door)
Removable Access Window
Door Latching Mechanism
Electrical Connector
Interface for Lifting Handles
Harness Guide with Zip Tie Holes
RBF Pin (Spring)
Deployment Wagon with Tuna Can Space and Isolated Spring
Compartment
Bottom Mounting Interface
Removable Access Window
RBF Pin (Deployment Wagon)
PEEK Zip Tie Mounts
Rear Mounting Interface
Figure 7: Main components of EXOpod Nova.
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EXOpod Nova User Manual Revision 1.2 / June 2024
2.2 EXOpod NOVA Configurations
The various configurations for EXOpod Nova are each identified with a
corresponding “S-code”, S1 S4, which specifies the number of slots
available. All EXOpod Nova configurations are shown in Figure 8 to Figure 12,
along with the associated S-code of each deployer configuration.
In deployer configurations with multiple slots, each slot is entirely
independent and is fully isolated from each other. Each slot also can be
modified to accommodate Cubesats that are of a smaller form factor than the
size of the slot by using non-deployable adapters. For example, a 3U slot can
be downsized to host 1U or 2U Cubesats, see section 3.4.
8U S2 2x4U Slot
8U S1 1x8U Slot
8U S2 2x4U Slot
Figure 8: Representation (Left) and 1x8U Slot and 2x4U Slot internal configuration (Right) of the 8U EXOpod Nova.
12U S1 1x12U Slot
16U S1 1x16U Slot
Figure 9: Representations (Left) and internal configuration (Right) of the 12U/16U EXOpod Nova S1.
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12U S2 2x6U Slots
16U S2 2x6UXL or 2x8U Slots
EXOpod Nova User Manual Revision 1.2 / June 2024
Figure 10: Representations (Left) and internal configuration (Right) of the 12U/16U EXOpod Nova S2.
12U S3 — 2x3U Slot and 1x6U Slot
16U S3 — 1x8U/6UXL and 2x3UXL/4U Slots
Figure 11: Representations (Left) and internal configuration (Right) of the 12U/16U EXOpod Nova S3.
12U S4 4x3U Slots
16U S4 4x3UXL or 4x4U Slots
Figure 12: Representations (Left) and internal configuration (Right) of the
12U/16U EXOpod Nova S4.
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copyright in this work, and no portion hereof is to be copied, reproduced, or
disseminated without the prior written consent of Exolaunch GmbH.
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EXOpod Nova User Manual Revision 1.2 / June 2024
Cubesat Allowable Volume
The general requirements of Cubesats are provided in the Cubesat Design
Specification (CDS) Standard Rev. 14. In the past, Cubesat deployers have been
developed to follow the CDS. However, EXOpod Nova has been designed to allow
Cubesats to exceed certain limitations of the Cubesat Design Specification in
terms of allowable mass and volume. Importantly, EXOpod Nova is also
backwards-compatible, and therefore is still able to accommodate any fully
CDS-compliant Cubesat even if it does not take advantage of Nova’s enhanced
performance envelope.
Notably, in the CubeSat Design Specification Rev 14, the specified Cubesat
rail length (Z) for both 6U and 12U configurations is indicated as 366mm, a
new definition compared to previous releases. Exolaunch introduces additional
distinctions between 6U/12Us and 6UXL/12UXLs. Specifically, Exolaunch
designates the Cubesat rail length (Z) for a standard 3U/6U/12U as 340.5mm,
while a 3UXL/6UXL/12UXL is defined as having a length of 365.9mm.
Comprehensive details on allowable CubeSat dimensions are provided in Table 1.
The maximum dimensions for 1U to 16U Cubesats that may be used with EXOpod Nova are provided in Table 1, and are further illustrated in Figure 13 and Figure 14. Here, the mint green areas mark the rails the primary interfaces with EXOpod Nova. The GREY and BLUE (the so-called “Tuna Can”) volumes may be used by the customer. The rails comply with the CDS and have a tolerance of ±0.1 mm, which must be adhered to if the Cubesat is to fit within the deployer. There is no defined tolerance for all other dimensions. Protruding features may be of any size within the usable volume envelope, but no part may extend beyond it. Custom Cubesat form factor may also be accommodated. Please contact Exolaunch.
The CDS states that Aluminum 7075, 6061, 5005, and/or 5052 may be used for
both the main Cubesat structure and the rails.
Caution: The rails must additionally be hard anodized (Type III hard
anodization). Any deviation from the CDS, such as, but not limited to, the use
of a different material or surface finishes (e.g. other forms of anodizing or
a chromate conversion dual finish) must be approved by Exolaunch in written
form. Additional compatibility testing may be required. Furthermore, any holes
or edges on the Cubesat rail must be adequately chamfered. The rails must have
a surface roughness of Ra 1.6. These requirements also apply to satellite
engineering models using EXOpod Nova or Nova TestPods!
Figure 13: Maximum allowable dimensions for Cubesats launched in an EXOpod Nova. Contact areas with the deployer are marked in mint green.
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EXOpod Nova User Manual Revision 1.2 / June 2024
Figure 14: Maximum allowable tuna can dimensions for Cubesats launched in an EXOpod Nova.
Table 1: Maximum Cubesat dimensions
Description
Units Letter 1U, 2U, 3U, 4U 6U, 6UXL, 8U
12U, 12UXL
16U
Cubesat Rail Length (Z)
Cubesat Rail Width (X) Cubesat Rail Height (Y)
[±0.5 mm] [±0.1 mm] mm
[±0.1 mm]
1U: 113.5
2U: 227.0
6U: 340.5
A
3U: 340.5 6UXL: 365.9*
3U XL: 365.9* 8U: 454.0
4U: 454.0
B 100.0
C
226.3 100.0
12U: 340.5 12UXL: 365.9*
226.3
454.0
Max Space Between Rails (X) Max Space Between Rails (Y)
D 87.2
E
213.5 87.2
213.5
Max Protrusion from Rail (X) Max Protrusion from Rail (Y)
F 25.0
G
39.5 25.0
39.5
Number of Tuna Cans
–
–
1
2
4*
4*
Distance Between Tuna Cans
mm
–
–
126.3
Maximum Mass***
1U: 2.5
6U: 14.0
2U: 4.5
kg
–
6UXL: 16.0
12U: 26.0
36
3U: 7.0
8U: 18.0
4U: 9.0
Maximum Distance Between COG and Geometric Center
mm
–
See Table 2
The XL standard is defined differently by different standards. Exolaunch can provide adapters for any definition of “XL” but this must be coordinated in advance.
The 12U and 16U S1 Nova has an additional, fifth tuna located in the center
between the four larger tuna cans, see Figure 11. The usable height of this
tuna can is 67 mm with a 62 mm diameter.
Qualified masses are primarily based on SpaceX Falcon 9 launch environments
and differ slightly for other launchers or OTV missions. Please talk to
Exolaunch.
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EXOpod Nova User Manual Revision 1.2 / June 2024
The maximum recommended distance between the COG and the geometrical center is
outlined in Table 2. All values are based on the CDS [AD-1] and [AD-2] and
should be seen as a guideline rather than a firm limitation. For unique
Cubesat designs, the deviations can be higher, however, this can lead to
increased local loads on the satellite during testing and launch and can also
cause higher tip-off rates. For questions on custom designs and form factors,
please contact Exolaunch.
Table 2: Maximum recommended distance of the COG from the geometrical center
Description
X-axis (mm)
Y-axis (mm)
Z-axis (mm)
1U 2U 3U 4U 6U, 6UXL 8U 12U 16U
± 20 ± 20 ± 20 ± 20 ± 45 ± 45 ± 45 ± 45
± 20 ± 20 ± 20 ± 20 ± 20 ± 20 ± 45 ± 45
± 20 ± 45 ± 70 ± 90 ± 70 ± 90 ± 70 ± 90
2.3.1 Cubesat-to-Nova Fitcheck
To guarantee the compatibility of the Cubesat and Nova deployer, Exolaunch
requires performing:
A virtual fitcheck using a simplified CAD model of Nova and the satellite > The measurement of the rail dimensions on the assembled satellite > Preferably, a physical fitcheck with an Exolaunch Nova or Nova TestPod
Exolaunch will provide a rail measurement guide as well as a simplified 3D model of the applicable Nova configuration on request.
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EXOpod Nova User Manual Revision 1.2 / June 2024
2.4 Deployment Energy
Deployment velocities are calculated based on the physical properties of the
mechanical springs. Each 8U Nova has two springs and each 12U/16U Nova has 4
springs. The spring configuration is identical across all configurations. This
means that in a 1U-4U slot the deployment wagon is pushed by one out four
springs. Two springs are combined to push the deployment wagon in a 6U-8U slot
and four springs in a 12U-16U slot respectively. Typical Cubesat velocities
are illustrated in Figure 15. Satellite specific deployment velocities are
coordinated in the mission specific ICD. For more information reach out to
Exolaunch.
Figure 15: Deployment velocities for different Cubesat sizes and masses
Velocity [m/s]
2.40 2.20 2.00 1.80 1.60 1.40 1.20
0
10
20
30
Cubesat mass [kg]
1U 2U 3U 4U 6U 8U 12U 16U
40
2.5 Tip-Off Rates
Tip-off rates for all Cubesat types are expected to be below 10 deg/s in all
axes and are dependent on Cubesat mass properties. 3U long form factor types
tend to be more stable. The separation half cone angle is ±7.5 deg.
Figure 16: Successfully deployed Cubesat on SpaceX Transporter-5 mission
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EXOpod Nova User Manual Revision 1.2 / June 2024
Mechanical Properties
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EXOpod Nova User Manual Revision 1.2 / June 2024
3.1 Coordinate System
The coordinate system of EXOpod Nova is shown below. The coordinate system
origin is in the center of the rear plate mounting interface plane.
Figure 17: Coordinate System of the EXOpod Nova.
3.2 Mass Properties
Detailed mass properties for different EXOpod Nova configurations can be found
within Appendix A for the 8U (Table 10 through Table 11), Appendix B for the
12U (Table 12 through Table 15) and Appendix C (Table 16 through Table 19) for
the 16U. Configurations vary based on number of slots, and open/closed state.
The masses of each configuration are summarized in Table 4.
Nova configuration: 8U/12U/16U S1-S4, see Section 2.2 > Open and Closed state: see Table 3 > The masses do not include slot adapters or fasteners.
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EXOpod Nova User Manual Revision 1.2 / June 2024
Table 3: Nova in stowed and deployed configuration. Closed State: Doors locked and spring in the stowed state
Open State: Doors open and spring in the relaxed state
Table 4: EXOpod Nova masses of different configurations. Configuration 8U S1 8U S2 12U S1 12U S2 12U S3 12U S4 16U S1 16U S2 16U S3 16U S4
Mass [kg] 7.70 8.83 9.77 11.31 12.32 13.32 10.75 12.85 14.05 15.27
Tolerance ±5%
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EXOpod Nova User Manual Revision 1.2 / June 2024
3.3 Outer Dimensions
The outer dimensions of the 8U, 12U, and 16U EXOpod Nova variants are shown in
Figure 18 through Figure 20 respectively.
Figure 18: 8U EXOpod Nova outer dimensions.
Figure 19: 12U EXOpod Nova outer dimensions.
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Figure 20: 16U EXOpod Nova outer dimensions.
EXOpod Nova User Manual Revision 1.2 / June 2024
3.4 Cubesat Adapters
To ensure that EXOpod Nova can accommodate non-standard Cubesat form factors,
a variety of adapters have been designed to fit in the slots of the deployer
and downsize it to the required form factor. Custom screws at the tip of the
guiding rails act as stoppers, preventing the adapters from exiting the EXOpod
Nova during deployment. Built-in switches provide a telemetry signal to the
launch vehicle indicating the status of the deployment. Figure 21 illustrates
some of the adapters offered by Exolaunch. Unique adapter types are available
on request. Detailed mass properties of standard Cubesat adapters can be found
in Table 20 of Appendix D.
Figure 21: Illustration of some available EXOpod Nova Cubesat adapters.
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EXOpod Nova User Manual Revision 1.2 / June 2024
All adapters are designed with maximum internal volume available for customer
use for external features and payloads. In addition to allowing a large
variety of Cubesat lengths, this slot adapter design enables the use of custom
and over-sized tuna can volumes. As an example, a 6U Cubesat with a large
external protrusion can be accommodated in an 8U Nova slot using an 8U-to-6U
slot adapter, see Figure 22. Contact Exolaunch for specific CAD file requests.
Figure 22: Example of 6U Cubesat with oversized Tuna Can launching in an 8U
slot using an 8U-to-6U Slot Adapter.
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EXOpod Nova User Manual Revision 1.2 / June 2024
3.5 Vibration and Shock Loads
Mechanical loads experienced by a Cubesat flying in a Cubesat deployer will
always be altered, i.e. amplified, damped or transformed, due dynamic
interaction with the deployer’s structure compared to loads specified at the
launcher interface.
This is understood and widely accepted across satellite, deployment system, and launch vehicle manufacturers, meaning that Cubesats are commonly designed and tested directly to loads specified in the launcher User Guide, rather than derived loads. In the same spirit, Cubesats are most often tested using test fixtures (such as the Nova TestPod), which are structurally not representative of the separation system used in flight. The general effect of the Nova structure on the vibration and shock loads seen by the Cubesat are illustrated in the following Figures. These loads have been measured in tests using monolithic aluminum body test dummies, which are structurally different from an actual Cubesat. See also section 3.6 for additional context.
Vibration loads, see Figure 23, generally see a local amplification at the first natural frequency (FNF) of Nova and are damped quite significantly in the entire frequency range thereafter. The exact location of the Nova’s FNF can shift depending on total mass, loads and deployer type, mounting configuration and Cubesat size, but the trend is the same.
Figure 23: Vibration loads (Random vibe transfer function) as seen by Cubesat flying in EXOpod Nova (Example for particular configuration).
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EXOpod Nova User Manual Revision 1.2 / June 2024
Shock loads, see Figure 24, are damped significantly across a wide portion of
the frequency spectrum, particularly in higher frequencies. Exact values
depend on input loads, deployer type, mounting configuration and Cubesat size,
but trends are consistent.
Figure 24: Shock loads (SRS) as experienced by Cubesat flying in EXOpod Nova (Example for particular configuration).
3.6 Loads and Finite Element Modeling
Modelling the dynamic behavior of a Cubesat-Deployer coupled system is
challenging and not recommended for most missions. The challenge of the task
stems from the fact that manufacturing tolerances which can’t be modelled in
FEM – have significant impact on the fit and the dynamic behavior of the
coupled system. The damping effect of the clamping mechanism adds to the
complexity of the behavior. Even small differences in the size of the Cubesat
rails (~0.1mm, within the standard rail tolerances) can have a significant
effect on the force applied by the rail clamps. Since the travel on the clamps
is so low, even small changes have a large effect; this explains the wide
range of forces provided in section
This effect has been verified in test.
Modelling effort can be justified if a particular risk with a sensitive
payload or subsystem has been identified. In such cases an FEA can be used as
a way to understand how launch environments may affect the satellite, however
there is inherent uncertainty which can’t be overcome outside of testing. The
best approach is to create the model using assumptions about how the satellite
is fixed in the deployer, then add margins on top to account for the
uncertainty. The only way to get an accurate understanding of the loads is to
perform a joint test in the Cubesat deployer, which Exolaunch can offer as a
special service in justified cases.
Detailed FE models of the EXOpod Nova for customer use are not available.
However, Exolaunch can provide transfer functions for specific Nova
configurations. Transfer functions are derived from tests with stiff Aluminum
Cubesat dummies.
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25 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
Mechanical Interfaces
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EXOpod Nova User Manual Revision 1.2 / June 2024
4.1 Launch Vehicle Interfaces
EXOpod Nova has mechanical interfaces on the bottom and rear faces for Bottom
Plate Mounting (BPM) and Rear Plate Mounting (RPM) respectively, which allows
for different mounting orientations on the launch vehicle adapter. These
interface properties are summarized in Table 5 and are shown in Figure 23.
High-strength stainless steel M8 screws (640 MPa yield strength or higher,
e.g. BUMAX 88) in combination with Nord-Lock NL8ss washers are required as
fasteners for all EXOpod Nova configurations. For alternative secondary
retention methods, please consult with Exolaunch.
Figure 25: Rear and Bottom Plate Mounting of the EXOpod Nova in horizontal and vertical orientation.
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EXOpod Nova User Manual Revision 1.2 / June 2024
Table 5: Mechanical interface specification.
Bottom Plate Mounting, BPM
Rear Plate Mounting, RPM
Deployment
Attachment points
Thread
Required fastener type
Required lock washer
Min. screw-in depth for mounting the Nova Max. screw-in depth for mounting the
Nova Tightening torque — Mounting Nova to launch vehicle interface
Surface finish
Overall Flatness
Parallel to mounting plane
Normal to mounting plane
8U: 8
12U: 6
16U: 8
8U: 4
12U/16U: 5
M8x12 Helicoil free- insert
M8, BUMAX 88 (800 MPa) or stronger
Nord-Lock NL8ss
13 mm
16 mm
22.0 Nm (15kN pre-load)
Ra 1.6 < 0.1 mm
The mounting feet of EXOpod Nova feature a free running threaded Helicoil insert for M8 fasteners. The mounting feet on the rear face are directly connected to the internal structure providing increased stiffness. A detailed view is shown in Figure 26.
Figure 26: Detailed view of the mounting feet.
Bottom Interface
M8x12 Threaded Insert 13 mm Thread
Engagement
Rear Interface
Nord-Lock NL8ss Washer
M8 Fastener
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28 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
4.1.1 Rear Plate Mounting Interface
The mounting hole pattern of the rear plate mounting (RPM) interface is shown
in Figure 25 and Figure 26.
Figure 27: Mounting hole pattern of the RPM interface on the 8U Nova variants.
Figure 28: Mounting hole pattern of the RPM interface on the 12U and 16U Nova
variants.
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29 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
4.1.2 Bottom Plate Mounting Interface
The mounting hole pattern of the bottom plate mounting (BPM) interface is
shown in Figure 27 for the 12U Nova and Figure 28 for the 8U and 16U Nova.
Figure 29: 12U Nova mounting hole pattern of the BPM interface.
Figure 30: 8U and 16U Nova mounting hole pattern of the BPM interface.
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30 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
Lifting Interface
EXOpod Nova provides a dedicated mounting interface for lifting handles on
four of the six faces (top, left, right and front), providing maximum
flexibility for handling and for different mounting orientations. The lifting
handles allow a loaded EXOpod to be lifted by crane or by hand safely and
conveniently. Each handle is attached to NOVA using two M4 thumb screws. While
the loaded mass of an EXOpod Nova is limited to 50kg, there is significant
safety margin built into the design of the handles, with each handle having a
Safe Working Load of 200kg. The use of a crane is strongly advised when moving
a loaded deployer. Lifting at an angle is to be avoided. Figure 29 shows
EXOpod Nova with lifting handles mounting locations. Additionally, EXOpod Nova
can also be lifted from the bottom interface by installing M8 eye bolts on the
mounting interface.
Figure 31: EXOpod Nova with lifting handles installed on the top face (left).
Additional mounting interfaces for the handles are located on the two
neighboring +X and -X and +Z faces (right).
4.1.4 Grounding
Cubesats are electrically isolated from the deployer when loaded inside.
Grounding through the EXOpod Nova is established through a conductive path
along the mounting interface screws.
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EXOpod Nova User Manual Revision 1.2 / June 2024
4.1.5 Remove Before Flight Elements
Three sets of Remove Before Flight (RBF) pins provide safety during ground
handling, satellite integration, and launch vehicle mating procedures, which
are illustrated in Figure 30:
Doors: Each door is secured by a threaded RBF pin. This is the last RBF element to be removed before
launch.
Spring: The deployment spring is retained by an innovative spring-loaded RBF pin, which is also used on
the CarboNIX microsatellite separation system. The pin is inserted when the deployment wagon is in a deployed state, with the spring-loaded element of the RBF pin snapping into place once the deployment wagon is pushed fully backwards into its stowed position. EXOpod Nova should always be transported in its stowed state.
Deployment wagon: A third set of pins, identical to the ones used on the doors, are used during Cubesat
integration to further secure the deployment wagon in a fully stowed position. This ensures the set screws can be optimally set.
Figure 32: EXOpod Nova with RBF pins installed (indicated in red).
Spring RBF
Spring not Secured
Spring Secured
Red Pin Visible
Red Pin Retracted
Door RBF
Deployment Wagon RBF
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EXOpod Nova User Manual Revision 1.2 / June 2024
4.2 Satellite Interfaces and Accessibility 4.2.1 Rails and Clamping Mechanism
The Cubesat rails are the primary interface between the satellite and EXOpod
Nova. Exolaunch has developed a unique clamping system which is highly
effective at constraining the satellite in the X and Y directions, thereby
preventing it from shaking and rattling during transportation and launch. This
clamping force is achieved by moving clamping surfaces on up to three guide
rails inwards towards the Cubesat. The mechanism engages as the door of the
slot is closed, and the force increases linearly with a decreasing opening
angle of the door. The total clamping force of the mechanism varies depending
on the size of the slot as well as on the size of the Cubesat within the
allowable tolerances. 3U slots have a clamping mechanism on a single rail.
6U/8U slots use two clamping rails and 12U/16U use three, although the second
and third active rail will only have a unidirectional force acting on the
Cubesat. The principle is illustrated in Figure 31. As an example, a 6U
Cubesat on the lower end of the allowable size or 99.9 mm x 226.2 mm will
experience a total clamping force of 1431 N, while the force will increase to
up to 4365 N as the rail dimensions approach 100.1 mm x 226.4 mm in size.
Figure 33: Clamping principle in 3U (left) and 6U (right) Cubesat slots.
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33 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
4.2.2 Deployment Wagon
The deployment wagon, shown in Figure 32, is situated in between the spring
and the Cubesat when the satellite is installed in the slot. It serves to keep
the spring in the correct orientation and ensures that the spring force is
correctly transmitted to the Cubesat. The deployment wagon is secured in the
slot by an independent restraint mechanism. This mechanism will not release
the wagon until the door has opened past 90 degrees, which prevents the
possibility of the Cubesat impacting the door during deployment. The
deployment wagon is stowed and secured with an RBF pin during integration.
Figure 34: Deployment wagon of a 3U/4U slot.
Satellite Interface Point
Deployment Wagon Rails
Tuna Can Space Isolated from Spring
4.2.3 Set Screws
Cubesats are secured inside the slot by means of a clamping mechanism, which
applies a clamping force in the X and Y directions. Cubesats are further
constrained in the Z-direction by the combination of the Deployment Wagon and
the adjustable set screws located on the doors (see Figure 33). Once a
satellite is placed inside EXOpod Nova, the door is closed, and the set screws
are then tightened. This eliminates any gap created by loose tolerances, thus
prohibiting any movement in the deployment direction. Each set screw is
prevented from loosening by means of a fixation ring. When the fixation ring
is engaged it acts like a wedge, increasing the running torque and preventing
the set screw from coming loose.
Figure 35: Set Screw detailed view
Fixation Ring
Set Screw
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Fixation Screw
34 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
4.2.4 Doors and Locking Mechanism
The doors of EXOpod Nova use a unique electromagnetic locking mechanism which
is used across all Exolaunch separation systems. These magnetic locks are
highly reliable, with years of impeccable flight heritage, more than 350
successful orbital deployments, and thousands of cycles in test to date. Each
door has two locks for redundancy, with each of them capable of triggering
deployment independently. The locks require a 28VDC/0.28A/130ms release signal
(see section 5.1). The high voltage and duration of the required pulse acts as
a safety barrier which cannot be overcome by coupled signals due to RF-
emission or static discharge. It also ensures universal compatibility with any
launch vehicle by means of the low current compared to motorized systems. The
lock design allows the mechanism to be released and reset within seconds. This
fast and simple process also allows functional checks to be easily performed
after transportation to the launch site as well as after the final integration
with the launch vehicle.
Magnet LOCKED
Locked State Open State
Magnet OPEN
Set Screw Cubesat Interface
Set Screw
RBF Hole
Access Window
Door Pin
Pin Retracted
Figure 36: EXOpod Nova door in open and closed state.
The door system is designed with a mechanism that inhibits the release of the
deployment spring and wagon until the door has reached an opening angle
greater than 90 deg. This system prevents the satellite from impacting the
door during deployment. A latching mechanism is built into the hinge of the
door, locking the door open and preventing it from rebounding once the door
has fully opened.
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EXOpod Nova User Manual Revision 1.2 / June 2024
4.2.5 Access Windows
Large access windows are located on three sides of EXOpod Nova, allowing quick
and easy access to the satellite at any point during and after the
integration. Convenient access can be useful for a variety of reasons,
including the removal of RBF elements, satellite charging, last minute
software updates, and functional checks. Small access windows are located on
the Z+ face of the EXOpod Nova. The dimensions and locations of the windows
are shown in Figure 35. Measurements in this figure are taken from the
deployment wagon interface (satellite contact plane). Note that the windows on
the top face adjacent to the electrical connector can be blocked by the launch
vehicle harness.
Satellite Contact Plane
Window on +Y Face partially blocked
Y Z
Figure 37: Position and dimensions of the access windows on the EXOpod Nova. The 8U is missing one row of windows whereas the 12U Nova has one fewer columns.
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36 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
Electrical Interfaces
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EXOpod Nova User Manual Revision 1.2 / June 2024
5.1 Electrical Connectors
Each slot of EXOpod Nova has two magnetic locks acting as fully redundant
actuators, as well as two reed switches for telemetry, indicating the state of
the door and spring. For electrical connectivity, EXOpod Nova is equipped with
a D-Sub 37-pin male connector (ITT Cannon DCMA37P), which is identical across
all EXOpod Nova variants and serves as the primary electrical interface (see
Figure 36). The connector pinout is shown in Table 6, and the corresponding
slot numbers are indicated in Figure 37. Exolaunch recommends a D-Sub 37-pin
female connector from CONEC (part number 164X11799X) to be used for the
electrical harness. For more detailed information contact Exolaunch.
EXOpod Nova features reverse polarity protection diodes on the actuator lines.
The telemetry switches are Normally Open (NO), meaning that the first switch
circuit closes when the deployer door has fully opened, and the second reed
switch closes when the deployment wagon reaches the front of the deployer
slot. The electrical signal characteristics for the actuators as well as
guidelines for continuity checks are summarized in Table 7.
Figure 38: Left: D-Sub 37-pin main connector on EXOpod Nova top side (+Y) with pinout and actuator diagram.
S1
S2
S3
S4
Figure 39: Slot numbers corresponding to the pinout in Table 8. Note that there is only an S1 and S2 option for the Nova 8U.
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38 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
Table 6: DSub 37 connector pinout. Green cells indicate that the pins for this slot are used in the respective NOVA configuration.
Pin Slot
1 2 3 4
Slot 1 5 6 7 8 9 10 11 12 13 14 15
Slot 2 16 17 18 19 20 21 22 23
Slot 3 24 25 26 27 28 29 30 31 32 33
Slot 4 34 35 36 37
Function
Actuator 1 VCC Actuator 1 GND Actuator 2 VCC Actuator 2 GND Door Status TM
Door Status TM Wagon Status TM Wagon Status TM
x x x Actuator 1 VCC Actuator 1 GND Actuator 2 VCC Actuator 2 GND Door Status
TM Door Status TM Wagon Status TM Wagon Status TM Actuator 1 VCC Actuator 1
GND Actuator 2 VCC Actuator 2 GND Door Status TM Door Status TM Wagon Status
TM Wagon Status TM x x Actuator 1 VCC Actuator 1 GND Actuator 2 VCC Actuator 2
GND Door Status TM Door Status TM Wagon Status TM Wagon Status TM
EXOpod NOVA Configuration
S1
S2
S3
S4
Remarks
Y
Y
Y
Y
Closed when door is fully opened.
Closed when spring is fully extended.
not connected not connected not connected
N
Y
Y
Y
Closed when door is fully opened.
Closed when spring is fully extended.
N
N
Y
Y
Closed when door is fully opened.
Closed when spring is fully extended.
not connected not connected
N
N
N
Y
Closed when door is fully opened.
Closed when spring is fully extended.
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39 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
Table 7: Characteristics of the electrical signal to actuate the permanent magnets.
Parameter
Value
Permanent Magnet
Actuating voltage
Nominal: 28±4 VDC Max: 50 VDC
Min: 0.130 s
Pulse duration
Nominal: 0.5 sec
Max: 3 sec every 30 sec
No-fire: 25 mA
Current
Nominal: 280 mA
Max: 500 mA
Voltage Drop Continuity checks
1.2V± 10%
Actuator lines: 1.2±10% V voltage drop Telemetry lines: Open Loop >1M (in
armed mode)
Measured in multimeter diode mode Measured in multimeter resistance mode
5.2 Telemetry Toggler RBF
Nova features special Remove Before Flight elements which can be attached to
the deployer from the outside to simulate actuation of the telemetry switches,
i.e. simulate an open door or a deployed spring. This allows performing a
checkout of the launch vehicle harness after final integration, see Figure 38.
Figure 40: Nova telemetry toggler RBFs.
Door Telemetry Toggler RBF
Spring Telemetry Toggler
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copyright in this work, and no portion hereof is to be copied, reproduced, or
disseminated without the prior written consent of Exolaunch GmbH.
40 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
5.3 Harness Routing
To facilitate harness routing along the chassis, harness routing points are
located on the top and rear faces of EXOpod Nova (see Figure 39). The cable
guides on the rear face are made from PEEK, a robust engineering plastic with
low outgassing properties.
Cable canal with zip tie holes
PEEK zip tie mounts
Figure 41: Left: Harness routing canal and fixation points. Right: Example of
harness route.
5.4 Umbilical Connection
An umbilical connection for satellite charging or remote access after
integration with the launch vehicle is not available as a standard option.
Access to the satellite after integration into Nova is only possible through
the access windows which requires direct access by personnel. Custom solutions
for umbilical access can be evaluated on a case-by-case basis, talk to
Exolaunch.
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41 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
Thermal Interfaces
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EXOpod Nova User Manual Revision 1.2 / June 2024
6.1 Thermal Qualification
To guarantee flawless performance in space, the EXOpod Nova has been qualified
to the environments listed in Table 8.
Table 8: Nova thermal qualification environnent.
System level
Parameter
Conditions
Magnetic lock EXOpod Nova EXOpod Nova
Thermal Cycling
Operational
TMAX TMIN
Survival
TMAX TMIN
27 cycles alternating between -34°C and +71°C +71°C -34°C +120°C -54°C
6.2 Satellite Interfaces
Heat transfer between Cubesat and EXOpod Nova primarily takes place by means
of heat conduction through the guide rails, deployment wagon, and set screws.
6.3 Launcher Interfaces
EXOpod Nova is not actively thermally controlled. A conductive thermal path is
achieved through the mounting interface. The passive thermal properties are
summarized in Table 9. A thermal model of the EXOpod Nova for customer use is
not available.
Table 9: Thermal interface.
Description
Bottom Plate Mounting Interface
Rear Plate Mounting Interface
Contact Area
Radiating Area
8U: 637.9 mm2 12U: 478.4 mm2 16U: 637.9 mm2
8U: 239.1 mm2
12U/16U: 478.2 mm2
Rough estimate (Aluminum/Carbon): 8U: 0.25m²/0.2m², 12U: 0.5m²/0.25m²m 16U: 0.6m²/0.3m²
Surface Material
Al 5083 Black Anodized (Type II): Emissivity () 0.93, Absorption () 0.70 Al 5083 Green Anodized (Type II): () 0.85, Absorption () 0.58
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43 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
Integration and Nova Ecosystem
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copyright in this work, and no portion hereof is to be copied, reproduced, or
disseminated without the prior written consent of Exolaunch GmbH.
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EXOpod Nova User Manual Revision 1.2 / June 2024
Exolaunch has designed various support equipment to improve user experience,
facilitate integration and testing of Cubesats into Nova and ship a loaded
EXOpod Nova safely.
7.1 Cubesat Integration
The integration procedure for EXOpod Nova is described in detail in the Nova
Cubesat integration Guide. Please contact Exolaunch for further details.
7.2 Nova TestPod
The Nova TestPods are a family of containers which were designed for Cubesat
testing and transportation. The TestPods come in multiple sizes to support any
Cubesat for factor. They have a strong and robust structure with a removable
interface plate for shaker tables. TestPods don’t have springs or electrical
actuators, making them easy and safe to use for unfamiliar operators. The
mechanical interface for the Cubesat is identical to that of a Nova deployer,
including the clamping mechanism, meaning that a test in a TestPod serves a
fully reliable fitcheck for the satellite. More information is available in
the Nova TestPod User Manual in [AD-3}.
Figure 42: Overview of the 4U, 8U and 16U EXOpod Nova TestPods.
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disseminated without the prior written consent of Exolaunch GmbH.
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EXOpod Nova User Manual Revision 1.2 / June 2024
7.3 Transportation
To ensure safe storage and transportation, EXOpod Nova is stored and
transported inside a Pelican Case with a laser-cut foam shell. For the
shipment to the launch site, Nova is placed in an ESD bag with desiccant.
Shock sensors are attached to the case, and the case is then strapped onto a
pallet. For transportation without a satellite inside, the springs must be in
their stowed state and secured using the provided RBF elements. For storage,
the spring must be in its deployed state whenever possible. Before satellite
integration, Nova is cleaned inside a cleanroom to standard ISO class 8
cleanliness requirements.
Figure 43: EXOpod Nova placed in its custom Pelican case and secured for shipment (Shock sensors not shown)
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EXOpod Nova User Manual Revision 1.2 / June 2024
7.4 Integration MGSE
For easy, fast and safe integration of customer satellites into Nova or into a
Nova TestPod, Exolaunch has developed a set of integration MGSE. The
Integration Table, which is shown below, is configurable to support any Nova
or TestPod configuration and can be set up in minutes. This streamlines the
integration procedure for any Cubesat and reduces risk, especially for larger
satellites which cannot be lifted manually.
Figure 41: Nova Integration Table Overview
Appendix
Figure 42: Cubesats manufactured by Kongsberg NanoAvionics being integrated into Nova and Nova TestPod using the Integration Table.
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47 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
Nova 8U Mass Properties
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EXOpod Nova User Manual Revision 1.2 / June 2024
The following tables give an overview of the mass properties of the 8U EXOpod Nova system. All tables use the EXOpod Nova coordinate system from section 3.1.
Table 10: Mass Properties 8U S1 BPM and RPM
Description
Closed
Mass (±5%)
X
Center of Gravity
Y
Z
IXX
Moments of Inertia rel. to COG
IYY
IZZ
IXY
Product of Inertia rel. to COG
IXZ
IYZ
0.47 5.55 287.01 334805.33 411119.71 134069.20 4621.50 714.53 272.57
7.7 X Y Z IXX IYY IZZ IXY IXZ IYZ
Open
0.48 13.65 335.7 337661.06 409696.94 138400.24 20921.85 637.16 241.46
Unit kg mm
kgmm²
kgmm²
Table 11: Mass Properties 8U S2 BPM and RPM
Description
Closed
Mass (±5%)
X
Center of Gravity
Y
Z
IXX
Moments of Inertia rel. to COG
IYY
IZZ
IXY
Product of Inertia rel. to COG
IXZ
IYZ
0.35 4.06 296.20 388654.81 464487.99 140390.24 7050.94 660.50 274.41
8.93 X Y Z IXX IYY IZZ IXY IXZ IYZ
Open
0.36 13.75 341.25 392992.26 462483.20 146808.47 30213.90 606.13 245.87
Unit kg mm
kgmm²
kgmm²
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49 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
Nova 12U Mass Properties
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50 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
The following tables give an overview of the mass properties of the 12U EXOpod Nova system. All tables use the EXOpod Nova coordinate system from section 3.1.
Table 12: Mass Properties 12U S1 BPM and RPM
Description
Closed
Mass (±5%)
X
-3.79
Center of Gravity
Y
4.91
Z
226.81
IXX
Moments of Inertia rel. to COG
IYY
IZZ
IXY
Product of Inertia rel. to COG
IXZ
IYZ
398624.98 392411.67 263382.90
7173.66 20.78
5223.35
9.77 X Y Z IXX IYY IZZ IXY IXZ IYZ
Open
-3.79 6.94 284.25 423267.35 392803.03 287764.62 9774.23 1842.17 5290.84
Unit kg mm
kgmm²
kgmm²
Table 13: Mass Properties 12U S2 BPM and RPM
Description
Closed
Mass (±5%)
X
0.25
Center of Gravity
Y
-1.49
Z
229.22
IXX
Moments of Inertia rel. to COG
IYY
IZZ
IXY
Product of Inertia rel. to COG
IXZ
IYZ
447231.16 447881.78 293501.67
549.94 520.08 478.38
11.31 X Y Z IXX IYY IZZ IXY IXZ IYZ
Open
0.25 -1.49 280.04 484487.51 454969.80 323777.45 1411.23 375.46 438.04
Unit kg mm
kgmm²
kgmm²
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51 / 57
Table 14: Mass Properties 12U S3 BPM and RPM
Description
Closed
Mass (±5%)
X
0.24
Center of Gravity
Y
4.47
Z
234.42
IXX
Moments of Inertia rel. to COG
IYY
IZZ
IXY
Product of Inertia rel. to COG
IXZ
IYZ
482412.06 477425.09 302000.92
6552.48 412.52 519.79
12.32 X Y Z IXX IYY IZZ IXY IXZ IYZ
Table 15: Mass Properties 12U S4 BPM and PRM
Description
Closed
Mass (±5%)
X
0.25
Center of Gravity
Y
-1.28
Z
238.77
IXX
Moments of Inertia rel. to COG
IYY
IZZ
IXY
Product of Inertia rel. to COG
IXZ
IYZ
518587.00 507300.00 311585.37
708.86 389.61 500.40
13.32 X Y Z IXX IYY IZZ IXY IXZ IYZ
EXOpod Nova User Manual Revision 1.2 / June 2024
Open
0.25 6.44 283.53 524767.17 483689.96 338236.94 11492.628 317.582 480.702
Open
0.26 -1.26 286.27 567016.05 513264.79 354233.56 1587.10 300.89 467.59
Unit kg mm
kgmm²
kgmm²
Unit kg mm
kgmm²
kgmm²
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52 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
Nova 16U Mass Properties
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EXOpod Nova User Manual Revision 1.2 / June 2024
The following tables give an overview of the mass properties of the 16U EXOpod Nova system. All tables use the EXOpod Nova coordinate system from section 3.1.
Table 16: Mass Properties 16U S1 BPM and RPM
Description
Closed
Mass (±5%)
X
Center of Gravity
Y
Z
IXX
Moments of Inertia rel. to COG
IYY
IZZ
IXY
Product of Inertia rel. to COG
IXZ
IYZ
-3.07 3.51 279.46 610058.36 603219.57 298320.11 8949.13 495.63 5042.54
10.75 X Y Z IXX IYY IZZ IXY IXZ IYZ
Open
-3.08 5.34 347.28 621710.98 590535.92 322778.37 12794.12 2389.06 5158.28
Unit kg mm
kgmm²
kgmm²
Table 17: Mass Properties 16U S2 BPM and RPM
Description
Closed
Mass (±5%)
X
Center of Gravity
Y
Z
IXX
Moments of Inertia rel. to COG
IYY
IZZ
IXY
Product of Inertia rel. to COG
IXZ
IYZ
0.22 -2.01 281.68 694132.85 697246.55 336341.31 768.96 693.79 564.26
12.85 X Y Z IXX IYY IZZ IXY IXZ IYZ
Open
0.22 -2.01 340.14 722132.23 695044.16 366652.94 2277.80 527.45 585.33
Unit kg mm
kgmm²
kgmm²
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Table 18: Mass Properties 16U S3 BPM and RPM
Description
Closed
Mass (±5%)
X
Center of Gravity
Y
Z
IXX
Moments of Inertia rel. to COG
IYY
IZZ
IXY
Product of Inertia rel. to COG
IXZ
IYZ
0.17 4.37 288.53 754393.93 750472.01 347910.56 10301.23 816.81 555.14
14.05 X Y Z IXX IYY IZZ IXY IXZ IYZ
Table 19: Mass Properties 16U S4 BPM and RPM
Description
Closed
Mass (±5%)
X
Center of Gravity
Y
Z
IXX
Moments of Inertia rel. to COG
IYY
IZZ
IXY
Product of Inertia rel. to COG
IXZ
IYZ
0.16 -1.84 294.28 814482.37 802792.82 360202.81 1290.68 760.07 548.60
15.27 X Y Z IXX IYY IZZ IXY IXZ IYZ
EXOpod Nova User Manual Revision 1.2 / June 2024
Open
0.16 6.08 343.84 785453.16 745477.39 384109.73 15774.01 539.24 558.11
Open
0.15 -1.73 347.00 849216.33 795190.95 402304.72 2770.94 463.22 553.32
Unit kg mm
kgmm²
kgmm²
Unit kg mm
kgmm²
kgmm²
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55 / 57
EXOpod Nova User Manual Revision 1.2 / June 2024
Cubesat Adapter Mass Properties
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copyright in this work, and no portion hereof is to be copied, reproduced, or
disseminated without the prior written consent of Exolaunch GmbH.
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Table 20: Mechanical Properties of Cubesat slot adapters with minimum volume
1U max
2U max
Adapter
EXOpod Nova User Manual Revision 1.2 / June 2024
6U XL max
Units
Mass
X
Center of Gravity
Y
Z
IXX
Moments of Inertia rel. to IYY
COG
IZZ
IXY
Product of Inertia rel. to IXZ
COG
IYZ
0.218 0.7 0.00
64.09 853 869.40 917.93 0.00 5.88 0.00
0.324
X
0.47
Y
0.00
Z
125.02
IXX
2792.78
IYY
2803.64
IZZ
1333.7
IXY
0.00
IXZ
13.90
IYZ
0.00
0.196
X
-1.61
Y
0.00
Z
66.95
IXX
613.76
IYY
2332.96
IZZ
2777.05
IXY
0.00
IXZ
-3.25
IYZ
0.00
kg mm kgmm² kgmm²
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EXOpod Nova User Manual Revision 1.2 / June 2024
Acronyms
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Acronym
BPM CAD CDS COG FEA FEM LV MOI MGSE RBF RPM VDC
Description
Bottom Plate Mounting Computer Aided Design Cubesat Design Specification
Standard Rev. 14 Center of Gravity Finite Element Analysis Finite Element
Modeling Launch Vehicle Moment of Inertia Mechanical Ground Support Equipment
Remove Before Flight Rear Plate Mounting Volt Direct Current
EXOpod Nova User Manual Revision 1.2 / June 2024
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EXOpod Nova User Manual Revision 1.2 / June 2024
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the copyright in this work, and no portion hereof is to be copied, reproduced, or
EXOLAUNCH.COM disseminated without the prior written consent of Exolaunch
GmbH.
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copyright in this work, and no portion hereof is to be copied,
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reproduced, or disseminated without the prior written consent of Exolaunch GmbH.