Ibeos will be exhibiting at the times below:

Tuesday, April 27, 2021 @ 8AM-9:30AM PT  &  2PM-4PM PT 

Wednesday, April 28, 2021 @ 8AM-9:30AM PT &  2PM-4PM PT

Thursday, April 29, 2021 @ 8AM-9:30AM PT & 2PM – 4PM PT

Meet Our Cubesat Developers Workshop Conference Team

Abigail Davidson


Abigail has 15 years of experience designing, building, and leading the development of spacecraft and related hardware.  At Ibeos, Abigail is focused on company strategy and building external relationships with customers, vendors, and industry partners.



CtO/ Founder

John has over 15 years of experience designing electronics for satellites.  With an expertise in radiation hard electronics, John is focused on building a portfolio of products at Ibeos that combine reliability,  survivability, and low SWaPC to serve the Cubesat community.


Principal Mechanical Engineer

Joe has over 20 years of experience performing mechanical packaging designs for electronics, including spacecraft electronics.  

At Ibeos, Joe leads the design, fabrication, analysis, and test of various standard and custom electronics products.


Lead Mechanical Engineer

Grant has been with Ibeos since 2017.  At Ibeos Grant has led the development of many of our Cubesat product mechanical and packaging designs.  Grant is intimately familiar with the mechanical and thermal design of our Cubesat portfolio of products.


Lead Electrical Engineer

Hunter has been with Ibeos since 2018.  At Ibeos, Hunter specializes in the electrical design of boards and assemblies, with an emphasis on our computing product line.  Hunter’s specialty is in electrical design, firmware, and low-level software.

About Ibeos

Ibeos provides both standard and custom electronics to serve the Cubesat satellite market.

Ibeos is pioneering a new era where high quality subsystems are accessible to small satellite builders and operators at an affordable cost. With a background in electronics design for geosynchronous and long-life missions, Ibeos understands reliability. We apply this focus and expertise to smaller satellite subsystems through innovations in part selection, testing, and iterative design.  Ibeos provides economic subsystems with the quality and reliability required of operational commercial constellations, national security applications, and missions beyond LEO. 

Cubesat Standard Products

CubeSat Electric Power Subsystem (EPS)

Available in 14V or 28V Bus Voltage

  • Cubesat-compatible form-factor (96 mm x 90 mm x 14.5 mm)
  • 150 or 200-Watt S/A input peak power tracker, 3.3-Volt, 5-Volt and 12-Volt outputs, and power distribution functions
  • Radiation-tolerant by design
  • I2C and SPI command, control, and data handling interface
  • Analog under/over-voltage and over-current protection
  • Two-fault tolerant spacecraft inhibits
  • Spacecraft watchdog

Modular Smallsat Battery

Available in 45 or 90 Whr

  • 94.5 mm x 84.1 mm x 23.1 mm envelope
  • 45-Watt-hour modular lithium-ion battery; can be packaged in pairs to create 90 Watt-hour module
  • Radiation tolerant under/over-voltage and over-current protection
  • Low power inhibit interface allows long term storage and passivation for pre-deployment
  • ISS-compliant
  • Integrated heater and thermistor

28V / 135 Whr Battery

  • 94.5 mm x 87.5 mm x 50.6 mm
  • Provides 10A sustained discharge, 2.5A sustained charge currents in a Cubesat-compatible form factor
  • Radiation tolerant under/over-voltage and over-current protection
  • Low power inhibit interface allows long term storage and passivation for pre-deployment
  • Low power inhibit interface allows long term storage and passivation for pre-deployment

EDGE GPU - Based Payload Processor

  • Cubeast-compatible form-factor (1U envelope for primary processing assembly; 3U SpaceVPX envelope for expanded version)
  • Powerful processor with 300 GFLOPS* for mission data processing
  • 4 ARM cores with up to 2 GHz clock speed
  • 256 GPU cores
  • Radiation tolerant design with multi-core CPU and GPU cores for powerful and efficient parallel processing
  • Ideal for image processing, RF signal processing, SAR, and other high-throughput computationally intensive application

*Inquire directly for information regarding next generation version with increased processing capability, available in 2022.


Ibeos Featured In NASA's Annual Smallsat State of the Art Report

We’re honored to share that Ibeos was featured in NASA’s annual State of the Art of Small Spacecraft Technology Report!

Read the press release here:


Career Opportunities

We have opportunities for both new and experienced professionals who have technical backgrounds in electrical engineering, mechanical engineering, aerospace engineering, physics, and computer science. Ibeos also has opportunities for business professionals with experience in business development, accounting, and government program compliance/administration. If any of the aforementioned disciplines are of interest and you think that you are a good candidate for one of the listings below, send a copy of your resume to info@ibeos.com.

Available Positions

Senior Digital Architect

Ibeos is looking for an engineer with digital design experience. Desired skills include high-speed digital circuit design and high-speed PCB design. Knowledge of radiation effects is a plus

Senior Analog/Power Architect

Ibeos is looking for an engineer with experience in power electronics design. Desired skills include power converter design, PWB design, worst case analysis, and control loop design.  Knowledge of radiation effects is a plus.

Lead Electrical Engineer

Ibeos is looking for an engineer to support a wide range of analog and/or digital electronic designs. Desired skills include analog and/or digital eletrical design, PWB design, firmware design, electrical analysis, and circuit-level testing. Experience in any industry is welcome.

NASA Small Spacecraft Systems Virtual Institute

NASA Small Spacecraft Systems Virtual Institute (S3VI)

Virtual Exhibit Booth: https://calpoly.zoom.us/j/89020493339?

April 27: 8:00 AM – 9:30 AM PDT / 2:00 PM – 4:00 PM PDT

April 28: 8:00 AM – 9:30 AM PDT / 2:00 PM – 4:00 PM PDT

April 29: 8:00 AM – 9:30 AM PDT / 2:00 PM – 4:00 PM PDT

Bruce D. Yost


Small Spacecraft Systems Virtual Institute

Therese Moretto Jorgensen, Ph.D.

Chief Scientist

Small Spacecraft Systems Virtual Institute

Craig D. Burkhard, Ph.D.

Deputy Director

Small Spacecraft Systems Virtual Institute

About NASA’s Small Spacecraft Systems Virtual Institute

NASA’s Small Spacecraft Systems Virtual Institute (S3VI) endeavors to advance clear communications and coordination regarding small spacecraft activities across NASA; provide the US small spacecraft research community with access to mission enabling information; maintain engagement with small spacecraft stakeholders in industry, government and academia; and to support the overall small spacecraft community. The S3VI is a NASA-wide virtual institute managed at NASA Ames Research Center, with participation from multiple NASA centers and NASA Headquarters. The S3VI is jointly sponsored by NASA’s Space Technology Mission Directorate and the Science Mission Directorate.

Small Spacecraft Systems Virtual Institute

The 2020 edition of NASA’s Small Spacecraft Technology State-of-the-Art report captures and distills the wealth of new information available on small spacecraft systems from NASA and other publicly available sources. This report is a survey of small spacecraft technologies sourced from open literature; it does not endeavor to be an original source, and only considers literature in the public domain to identify and classify devices. Commonly used sources for data include manufacturer datasheets, press releases, conference papers, journal papers, public filings with government agencies, news articles, presentations, and the Small Spacecraft Systems Virtual Institute Federated Search.

The S3VI hosts a public webinar series to share information with the community at large on work NASA, partner agencies, and other members of the community are performing in the area of small spacecraft. Speakers from NASA centers, partner agencies and NASA-funded universities present on a wide variety of small spacecraft topics including all phases of mission design, development, and operations; regulatory and process-oriented requirements; exploration and scientific strategies, and opportunities for the community.

Want to learn about advanced SmallSat technologies that could enable your future mission or be accessed for commercialization? Sign up to attend the SmallSat Technology Partnerships (STP) Technology Exposition being held Monday, May 24.

The virtual STP TechExpo will highlight advanced communications, navigation, constellation coordination, and other SmallSat technologies emerging from recent university-NASA partnerships funded under NASA’s Small Spacecraft Technology program’s STP initiative. STP teams in attendance will answer questions about technology transfer for your mission or product.

Visit the 2021 TechExpo webpage for more information.

NASA’s S3VI uses web technologies, databases, and virtual collaboration tools to collect, organize, and disseminate small spacecraft knowledge for the benefit of NASA and the community. S3VI has established this federated search capability that serves as an entry point to the SmallSat Parts On Orbit Now (SPOON) database and other NASA-internal and external databases to allow the public to search multiple databases for small spacecraft parts, technologies and conference proceedings. 

The Small Satellite Reliability Initiative (SSRI), in conjunction with NASA’s S3VI, has developed the SSRI Knowledge Base to improve mission confidence for small spacecraft. The SSRI Knowledge Base is a comprehensive online tool that consolidates and organizes resources, best practices, and lessons learned from previous small satellite missions. This free, publicly available tool is available to the entire SmallSat community at https://s3vi.ndc.nasa.gov/ssri-kb/

The S3VI publishes a quarterly digest of resources and activities occurring in the NASA and external small spacecraft communities. With the quickened pace of small spacecraft technology innovation, associated missions, and developments in launch capabilities, the amount of information available on the Internet is significant.

The S3VI newsletter offers a summary of links to our more popular web portal content to include mission design tools, recent NASA small spacecraft developments and accomplishments, events, solicitations, as well as other useful information.

If you are interested in receiving the newsletter, please subscribe to our mailing list.

Please visit the Small Spacecraft Systems Virtual Institute website for more information or email us.



Virtual Exhibit Booth: https://calpoly.zoom.us/j/89020493339?

April 27, 2021 @ 10AM-12PM PT | April 28, 2021 @ 2PM-4PM PT | April 29, 2021 @ 8:30 – 9:30 AM PT

Please contact me at kleidman@airphoton.com


Our leadership team has extensive experience designing and supporting satellite missions.  Our expertise extends from cubesats to full size payloads and mission design to delivering data products.

Vanderlei Martins AirPhoton CTO

Vanderlei Martins

Chief Technical Officer

Dr. Vanderlei Martins has developed and designed cubesat and full sized satellite instruments payloads.  His team at UMBC designed and built the Hyper Angle Rainbow Polarimeter (HARP) cubesat for studying aerosols and clouds.  The American Institute of Aeronautics and Astronautics (AIAA) named HARP the 2020 Small Satellite Mission of the Year.

Lorraine Remer

Chief Science Officer

Dr. Lorraine Remer has extensive experience in creating and implementing satellite data algorithms as well as calibration and validation activities.  She led the NASA Goddard Dark Target Aerosol Group from 2004 – 2012. She was a co-investigator on the HARP cubesat project.

She is an AGU fellow.

Oleg Dubovik

GRASP-SAS Chief Scientist

Dr. Oleg Dubovik is the lead developer of the  Generalized Retrieval of  Atmosphere and Surface Properties  (GRASP) and founder of GRASP – SAS.

GRASP  is the first unified algorithm and a software package developed for retrieving atmospheric properties from wide variety of remote sensing observations including satellite, ground-based and airborne data.

He is an AGU fellow.

Richard Kleidman

Chief Operating Officer

Rich Kleidman has been the COO of AirPhoton since its inception in 2012.  He has been (and continues to) be a support scientist for the MODIS Dark Target Aerosol Group at NASA GSFC as an SSAI employee.

He helped to develop the NASA ARSET training program during the first four years of its inception.

About AirPhoton

AirPhoton is a small Maryland based company. We design and manufacture instruments to measure airborne particulates.  We also offer support and data services for satellite instruments.  We are partnering with GRASP-SAS to offer end to end services and will be launching our own cubesat instruments in conjunction with GRASP.

AirPhoton and GRASP-SAS Projects and Services

Satellite Payloads

Payload Designs

Although our primary focus is on particulate monitoring and air quality we also have payload designs for:

  • Weather and clouds
  • Fire monitoring
  • Land cover
  • Snow & Ice monitoring


In-situ data can provide important information for cal-val activities and or other supporting data for satellite payloads.  AirPhoton produces a line of ground based instruments for particulate monitoring. We use both filter based and optical systems. These instruments can also be modified for aircraft use.

Filter Based Sampling Systems

The AeroExplorer is a filter based system that allows for completely programmable collection of particulates on filters.  Several of these instruments can be modified for aircraft use.

See the web page for a more complete explanation of the AeroExplorer and its capabilities.

The AeroExplorer is being used by NASA JPL to support its MAIA satellite program.

Optical Based Sampling Systems

Nephelometers – AirPhoton has several models of nephelometers from simple to complex.  The more advanced models can provide a full size distribution. Please see our Nephelometer web page for more information


GRASP  is the first unified algorithm and a software package developed for retrieving atmospheric properties from wide variety of remote sensing observations including satellite, ground-based and airborne data.

It infers nearly 50 aerosol and surface parameters including particle size distribution, the spectral index of refraction, the degree of sphericity and absorption. The algorithm is designed for the enhanced characterization of aerosol properties from spectral, multiangular polarimetric remote sensing observations. GRASP works under different conditions, including bright surfaces such as deserts, where the reflectance overwhelms the signal of aerosols. GRASP is highly versatile and allows input from a wide variety of satellite and surface measurements.

GRASP Services

  • Data processing
  • Software customization
  • Production system development from raw data to results, including user interface and all the tools needed to optimize code
  • Consulting

Level 1 Data Processing

We provide level 1 data processing services.

Raw data from a satellite needs a lot of processing before it can be used.  This includes calibration, georeferencing, and translating into engineering units. AirPhoton has extensive experience in this kind of processing including working with polarized data.


Sensor performance will vary over time as various components age and/or flaws are discovered. AirPhoton and GRASP-SAS have extensive experience in using ground and airborne instruments as well as data systems to calibrate and validate sensor performance and level I and Level II products.



COSATS is an international commercial spaceflight company, mainly engaged in the development of satellite platforms, subsystems, and services of space missions. The company’s core team has rich experience in space research and development. The subsystems and services have been widely used in satellites, drones, and airships. For more information, please contact us at xueguoliang@cosatspace.com or  visit our website:www.cosatspace.com 


COSTR CubeSat Str

COSTR CubeSat Structure is a kind of standard CubeSat structure based on modular concept design. COSTR CubeSat structure uses the standard U (the envelope of 1U is 10cm × 10cm × 10cm) as the unit and can provide 1U~16U structure at present. COSTR CubeSat structure is compatible with “CubeSat Design Specification” published by Cal Poly SLO. It could install various types of CubeSat subsystems and has strong adaptability to the platform.

COSTR CubeSat structure provides several built-in separation switches to ensure that the CubeSat structure is powered off before launch, as well as the ability to configure side panels according to the customer requirements.

  • The design of COSTR is based on the international standard of CubeSat
  • The structure uses high-strength aluminum alloy 7075/high-strength lightweight magnesium-lithium alloy
  • All screws are non-magnetic, high strength, corrosion-resistant titanium alloy screws
  • Hard anodizing is used in the surface treatment
  • Operation temperature:-40℃~+80℃
  • The subsystems that meet the standard of CubeSat could be directly mounted on the COSTR CubeSat Structure
  • The internal space can be flexibly adjusted to adapt to the installation of the subsystem
  • Cubesat subsystem and payload could be configured in horizontal/ vertical direction

COSAMU Attitude Measurement Unit

COSAMU Attitude Measurement Unit adopts SIP (System in Package) design method, which integrates sun sensor, three-axis gyroscope, three-axis magnetometer, temperature sensor and high-performance processor. It can be used to measure the three-axis attitude information of the spacecraft in real time, and provide high-performance and highly reliable data output.

  • Power consumption: <100mW
  • working voltage: 5V/3.3V  
  • Small size : outline size 40×40×10mm
  • The solar sensor, three-axis gyroscope and three-axis magnetometer are integrated in the interior
  • Light weight (weight<50g)
  • Fast data update rate (≥20Hz)
  • Communication interface: I2C/CAN/RS422

COSMTQ Three-axis Magnetorquers

The COSMTQ Three-axis Magnetorquers is used to control the attitude of the satellite and desaturation of the reaction wheel. It consists of two magnetorquer rods with metal cores and an air core torquer. Pulse Width Modulation(PWM) signals independently drive the magnetorquer rods/ magnetorquer coil. Besides, the temperature sensors and current sensors are embedded to monitor the operating condition. There are two kinds of magnetorquer board, COSMTQ-P uses 104pin connector and COSMTQ-S uses micro rectangular connectors.

  • The closed-loop control method is used to improve the magnetic moment precision
  • Operation voltage: 3.3V, 5V
  • Operation temperature: -20°C~50°C
  • Power consumption: <1.5W
  • Excellent EMC performance
  • Interfaces: I2C/ CAN

COSMAG High Precision Magnetometer

COSMAG High Precision Magnetometer is a high-precision three-axis vector sensor, used to measure the size and direction of the magnetic field at the location. This product has the characteristics of high resolution, low power consumption, strong anti-interference ability, and wide dynamic range. It can be widely used in aerospace, industry, agriculture, marine and meteorological fields.

  • The data output of triaxial magnetic field is calibrated
  • Devices can be screened according to customer needs
  • Standard I2C isolation interface, hot swappable
  • High precision temperature measurement at ±0.25 ℃ (- 40 ℃ ~ 125 ℃).
  • ≤ 5mW (3.3V) low power design
  • Working temperature: -20 ℃ to 50 ℃
  • Micro rectangular military connector, supporting customization
  • Titanium alloy screw
  • Vibration, shock and high and low temperature tests can be carried out according to customer needs

COSPOD CubeSat Deployer

COSPOD CubeSat Deployer

COSPOD CubeSat Deployer is used for in-orbit deployment. There are two kinds of CubeSat deployers.COSPOD-M series use frame structure with high strength Aluminum 7075. COSPOD-3D series use 3D printing frame structure with high strength aluminum alloy.The rear of COSPOD has a push plate. In the middle of the deployer, four rails are fitted four satellite ejection chutes. The memory alloy unlocking device controls the opening and closing of the front door. The mechanical and electrical interface of COSPOD is simple and reliable, the separation impact is small, and high separation attitude stability.

  • The design is based on the international standard of CubeSat
  • COSPOD-M uses high-performance aluminum 7075
  • COSPOD-3D uses 3D printing technology with aluminum alloy and it has 25% weight reduction and the tensile strength higher than 500Mpa
  • The COSPOD deployers can be used for the release of standard CubeSats, providing customized versions based on customer requirements for CubeSats applications with deployable solar panels or large antennas
  • Safe and reliable, No pyrotechnics and excess separators in the process of separation
  • The door opening experiment could be repeated many times by using the memory alloy unlocking system
  • Speed of separation is adjustable: 0.3~3 m/s
  • Electrical interface:
  • The resistance of the unlocking system: 1.1±0.15Ω
  • Current: ≥2A
  • Separation energy requirement: <21J
  • The required time of unlocking the door is according to the actual supply voltage and the power
  • Operation temperature: -40℃~58℃

COSSA Sun Sensor

COSSA Sun Sensor could measure the attitude information of the satellite relative to the sun. It has the advantages of compact size, low power consumption, and high reliability. There are two kinds of sun sensors, COSSA and COSSA pro. The COSSA is the standard version, and the COSSA pro is the high reliable version.

  • Operation voltage: 3.3V
  • Operation temperature: -25°C ~ 70°C
  • Power consumption: <10mA@3.3V
  • Interfaces: high reliable analog output
  • The COSSA Pro uses high strength, high performance titanium alloy housing and screws
  • Military-grade mini metal connector for COSSA to connected with other subsystems
  • Optional mounting bracket to adjust the installation angle of the sun sensor (can be customized according to customer requirements)
  • All components of COSSA Pro are screened
  • The calibration is carried out by using the class AAA solar simulator of COSAT Company and the high precision electric turntable

COSSD Sun Sensor

COSSD Sun Sensor with Digital Interface could measure the attitude information of the satellite relative to the sun, and determine the orientation of the sun vector in the satallite coordinate system by sensing the orientation of the sun vector, to obtain the attitude of the spacecraft relative to the sun orientation information. It has the characteristics of small size, low power consumption and high precision.

  • Operation voltage: 3.3V
  • Operation temperature: -25°C ~ 70°C
  • Power consumption: <150mW@3.3V
  • Interfaces: CAN / I2C

Three-axis Air Bearing Table

The Three-axis Air Bearing Table relies on compressed air to form an air film to float the platform, which realizes the relative motion condition without friction and simulates the mechanical environment in which the interference torque of the satellite is very small in space. By using the air floatation hemisphere, the three-axis air bearing table can not only simulate the attitude motion, which can simulate not only the attitude motion needed in the three-axis direction, but also the three-axis attitude coupling dynamics of the satellite, so as to verify the operation of the actual control law and control software in space. It is an indispensable experimental condition for satellite attitude control ground simulation.

  • Low friction loss
  • Multiple degrees of freedom
  • High stability
  • Large load-bearing capacity

CubeSat Education and Training Kit

CubeSat Education and Training Kit

CubeSat Education and Training Kit is mainly composed of three parts: CubeSat hardware、 interactive hardware and supporting courseware.

CubeSat hardware composition:Momentum wheel、 Camera module、 Power supply system Communication module、 On-board computer、 2U CubeSat Structure  torque Solar cell Sun sensor.

CubeSat hardware function introduction:

Attitude control simulation function: through the attitude control algorithm to simulate the flight of the CubeSat in orbit

Camera function: the interactive control platform controls the camera to take pictures, simulating the function of the CubeSat remote sensing camera

Communication function: the interactive control platform and the main body of CubeSat communicate through a wireless local area network to simulate the measurement and control function of CubeSat

Light source tracking function: use the sun-sensitive positioning light source, and then use the momentum wheel to drive the satellite to track the light source to simulate the function of CubeSat to orient the sun

Interactive control platform function introduction:

Simulation function: show the virtual running state of the CubeSat in space through the 3D interface

Virtual assembly function: virtual assembly of various parts of CubeSat through 3D

Control function: control CubeSat to take pictures, change attitude and track light source (sun orientation)

Data storage function: save and back up all the CubeSat data received

Supporting courseware

CubeSat orbit: introduce various orbit classifications, introduce orbit changes, orbital maneuvers, etc.

CubeSat overall design: how to design a CubeSat

CubeSat composition: introduce the knowledge of satellite load, structure, control, propulsion, power supply, and thermal control

CubeSat ground test: introduce the ground environment experimental knowledge of satellite mechanics, thermal cycle, etc.

CubeSat application: introduce the application of satellites in the fields of science, military, communications, geography, environment, meteorology, etc.

Star Tracker

Star Tracker of TY Space could measure the attitude information of the satellite relative to the star and output the information of attitude quaternion. It has the advantages of compact size, low power consumption, and high reliability. We could provide different kinds of space star trackers, which have been successfully launched into space and operating flawlessly on board of Lunar Exploration Program and High Resolution Remote Sensing Project, for over 100 satellites, such as Jilin-1, NS-1, NS-2, and ZhuHai1.

  • Operation voltage: 5V
  • Operation temperature: -30°C ~ 40°C
  • Exclusive Angle: <35°(Sun), <25°(Earth)
  • Update rate: 10Hz (20Hz option)
  • Power consumption: 500mW(average), 600mW(peak)
  • Interfaces: rs422/CAN
  • Lifetime: >3 years
  • TID:<10k rad(si)

COSGNSS Receiver

The COSGNSS Receiver is a high-dynamic and low-power consumption receiver, specially designed for microsatellites. It adopts BDS + GPS + GLONASS triple systems, three-band, and high-dynamic engine for location calculation. It offers superior dynamic performance with a high-precision engine and can adapt to a harsh space environment. Now, there are more than ten satellite missions have used the COSGNSS Receivers.

  • Support BDS B1/B2, GPS L1/L2, GLONASS L1
  • Support BDS/GPS/GLONASS single system independent location or BDS + GPS multi-system combined location
  • Support short, middle or long baseline, RTK work distance of 50km
  • Operation voltage: 3.3V~5.5V
  • Operation temperature: -40°C~75°C
  • Power consumption: <7W

Vincent Pereira


Freeport High School: Vincent Pereira, Victor Villatoro, Mia Sorrentino, Gilbert Rosario, Ethan Patterson, Yoendy Torres Almonte, Keyla Romero, June Cumento, David de la Llera, Lourdes Saunders, Jaileen Almonte, Melissa Bell, Jayden Easy, William Perry, Ryan Retzlaff, Cyler Witherspoon, Richard Johnson, Anthony Murray, Daniel Ciamaricone, Elodie Bourbon, Louis Inzerilli

Brookhaven National Laboratory: Dr. David Beirsach

Freeport High School is a finalist in the U.S. Department of Education’s CTE Mission: CubeSat, a national competition to bring space missions to high school students. Freeport received cash prizes, development kits and expert mentorship donated to the U. S. Department of Education by Arduino, Blue Origin, Chevron, EnduroSat, LEGO Education, Magnitude.io, MIT Media Lab Space Exploration Initiative, and XinaBox. Our CubeSat will contain an Arduino MKR WAN 1310 board, MKR GPS sensor, MKR MEM shield with a SD card, MKR IMU shield, and a lithium-polymer battery. The structure of the CubeSat was done by students in Industrial Drafting, CAD classes using AutoCAD, Sketchup, and a 3D printer. The CubeSat will be carried by a drone and its flight controlled by students in Video Media Production class. We will use this experience to teach a summer CubeSat class.

Team members will be available to speak with you on Wednesday, April 28th, and Thursday, April 29th, at 11 AM



To expand student interest in STEM fields, the U.S. Department of Education launched CTE Mission: CubeSat, a national challenge to inspire students to build technical skills for careers in space and beyond. High school students from across the country were invited to design and develop CubeSat prototypes, or satellites that aid in space research, bringing space missions out of the clouds and into the classroom [1]. The excitement and challenge of allowing students to do “real” things in space is a motivational experience that cannot be achieved by teaching in a classroom and represents education at its best [2]. Freeport High School was among the finalists chosen in this competition.


The primary mission of our CubeSat is to gather environmental observations to support authentic student research and create citizen scientists.  For the past few years, Freeport High School students have taken part in the Global Learning and Observations to Benefit the Environment (GLOBE) program. Students from nearly 40,000 schools located in approximately 120 countries participate in this program. In our CubeSat we will use two infrared imagers in specific bands to observe the surface temperature of Earth. Students will use this data in their ongoing effort to study the urban heat island effect. If successful, our CubeSat can be employed as a dedicated satellite to the GLOBE program giving it another educational dimension. Improvements on future launches may allow us to make measurements that can challenge large-scale satellite` cost-effectiveness by capturing comparable scientific data. 

Our mission will also use the CubeSat flight to study the principle of the conservation of mechanical energy. From the position and velocity of the CubeSat, students will be able to  calculate the total mechanical energy. The orbit of the CubeSat will be modified by perturbations resulting from air drag. We plan to use our data to determine the drag coefficient at the initial stages of changes in the CubeSat trajectory.  

Mentors provided by the U.S. Department of Education

Subject Matter Experts provided by the U.S. Department of Education

List of Webinars on Selected Space Topics

Professor Robert Twiggs                                              Space Environments

Robert Atkins                                                                 Space Innovation Course Lessons

Professor Robert Twiggs                                              Space Communications

Figure 1: Ted Tagami (Magnitude.io) engaging with Freeport Students

Figure 2: David Cuartielles (Arduino) engaging with Freeport Students

Science Payload

As a result of participation in the GLOBE program our students took temperatures of the concrete and grassy surfaces outside Freeport High School. These measurements were taken from the months of October to March. The maximum and minimum average temperature during these months of either surface are recorded in the Table below. We then used Planck’s blackbody radiation formula to convert these temperatures into wavelengths [3].

Maximum/Minimum Average Temperature (0C)                 Peak Wavelength (Microns)

                                      22.6                                                                            9.8

                                       3.6                                                                            10.5

These wavelengths are in the infrared range and we will use infrared cameras to observe these surfaces from space. Therefore, if the infrared camera can measure the intensity of a perfect black body at a particular wavelength we can use Planck Blackbody formula to calculate its temperature [3].

There are two problems with this approach. The ground is not a perfect black body. A bigger problem is the fact that water vapor present in the atmosphere also absorbs infrared radiation. Therefore, we cannot used Planck’s formula to measure the temperature of the Earth’s surface. In the split window technique [4-6], we measure the radiation emitted at two wavelengths that are very near each other like 9.8 and 10.5 microns. We measure the temperature of the Earth’s surface using the following Split Window formula:

In the above formula, B is the Planck function, I1and I2 are the measured intensities at the two different wavelengths, and γ is a constant that depends on the water vapor content, viewing angle, transmittance and emissivity. The split window technique assumes that the correction due to water vapor is proportional to the difference in intensities of the two wavelengths.

Electronics and Computing

Figure 3 

Figure 3 displays the electronics in our prototype. At the top is the MKR IMU shield, followed by MKR GPS sensor, Arduino MKR WAN 1310 board, and MKR MEM shield with a SD (secure memory) card and an antenna. Arduino gave the sensor, boards, and antenna. A rechargeable 1200 mAH lithium-polymer battery supplies the power. We have included a square LED for demonstration purposes, which will light up if the pitch angle is less than 70 degrees and more than 110 degrees (Figure 3 and 4). To ensure that the required current goes to the LED we have included a 330-ohm resistor. 

Block Diagram of Computer Code in Arduino board inside Prototype [7]

The CubeSat will be launched by a Mavic Mini drone manufactured by DJI. There is also an Arduino MKR WAN 1310 board (also donated by Arduino) connected by USB cable to a laptop on the ground.


Figure 4: CubeSat Assembly


Launch Objectives

To obtain the GPS coordinates, altitude, latitude, and longitude at various time intervals. We also plan to test the accuracy of our GPS values by comparing them to the GPS values obtained by the sensors on the drone.

Determine the maximum distance digital data can be consistently transmitted via LoRa-based wireless communication links.  

We want to find out if Google Earth can use our GPS data, saved as NMEA 0183 sentences, to show the terrain (towns/roads) over which the drone passed by when in flight. This information is essential because we want to find the temperature differences between cities and urban areas. Google Earth will help us identify the towns and rural areas.

Introduction to attitude control. We have included an Inertial Measurement Unit (IMU) sensor that will give us the yaw, pitch and roll angles to measure the rotation of the CubeSat. This information is required to ensure that the camera is pointing towards the ground when taking photographs.

Educational Objectives of Launch

The GPS coordinates will enable us to calculate the satellite`s gravitational potential energy and kinetic energy. We will also introduce students to the sources of GPS errors and methods developed to reduce such errors.

Introduce students to Section 25.4.8 [2]. The additional resource includes Professor Twiggs`s presentation on CubeSat Communications.  

Generate excitement among the student body (including elementary students) by using VR headsets to see the Google Earth data in 3D.

Students will be introduced to rigid body rotation and their description using Euler angles. Euler angle convention of yaw, pitch, and roll will be explained to students. Students will also be introduced to the problem of gimbal lock that nearly occurred in NASA’S Apollo lunar missions.

CTE Connections

In the Drafting & Design program we have students working on the structure design component of the project. Students in Industrial Drafting and CAD classes have created detailed drawings of the CubeSat structure design using traditional drafting techniques and engineering software programs. These designs were then used to create working prototype models on a 3-D printer.

Students in our Electrical Engineering classes have worked to connect and test the computing, power, communication and data storage components required for the CubeSat structure to operate.

The Video Media Production class includes a Drone unit where students learn to fly a drone to record specialized video content. Students in this class are working on the launch component of the project and using the drone to fly and test the CubeSat prototype.

In the CTE Business Computer Applications program students are working to create a marketing plan to promote the CubeSat project. In the Web Page Design Class students are creating a CubeSat web page which will include details and updates related to the project

Future Work

One possible next step would be to use the IMU control code to trigger a cheap infrared camera to take a snapshot of the school’s exhaust stack when the attitude is right. This would teach students much of the thermal imaging basics.


[1] https://www.ed.gov/press-releases/U.S. Department of Education Launches Space Mission Challenge for High School Students, August 18, 2020.

[2] Space Operations and Ground Stations by Robert Twiggs and Benjamin Malphrus, Space Mission Engineering: The New SMAD, Wertz, J.R., Everett, D.F., Puschell, J.J., editors, Microcosm Press, Torrance, CA (2018).

[3] Physical Chemistry, Atkins, P, De Paula, J. Oxford University Press (2010).

[4] Price, J. C., 1984 Land surface temperature measurements from the split window channels of NOAA 7advanced very high-resolution radiometer. J. Geophyys. Res. Atmos. 89 (D5), 7231-7237.

[5] McMillin, L. M., 1975 Estimation of sea surface temperatures from two infrared window measurements with different absorption. J. Geophys. Res. 80 (36), 5113-5117.

[6]. Wang, M., He, G., Zhang, Z., Wang, G., Wang, Z., Yin, R., Cui, S., Wu, Z., Cao, X., 2019. A radiance-based split-window algorithm for land surface temperature retrieval: Theory and application to MODIS dat. Int. J. Appl. Earth Obs. Geoinformation 76, 204-217.

[7] https://github.com/dbiersach/CUBESAT/blob/main/Arduino/CUBESAT_GPS/CUBESAT_GPS.ino

CubeSat Laboratory

The Cal Poly CubeSat Laboratory

Home of the CubeSat Developers Workshop


Virtual Exhibit Booth: https://calpoly.zoom.us/j/89020493339?

April 27–29, 2021 @ 8AM-9:30AM PT | @ 2PM-4PM PT

The Cal Poly CubeSat Laboratory 2018–2019


For more details please click here



The Cal Poly CubeSat Laboratory (CPCL) is a multidisciplinary independent research lab. CPCL is the CubeSat development team of Cal Poly, an originator and leader for launches in the CubeSat community. The team consists of staff and students majoring in Mechanical, Electrical, Software, Aerospace, Materials, Industrial, and Manufacturing Engineering, as well as Physics, Business, Journalism and Graphic Design. CPCL has given Cal Poly students a robust learn-by-doing experience for almost two decades, supporting students to be day-one ready professionals.

Student involvement in CPCL projects is key to all activities. Cal Poly students have developed and launched twelve spacecraft since the start of the program, with multiple more in various stages of development.

CPCL was an early leader in the CubeSat industry and since then has strived to develop a diverse knowledge base in all aspects of the small satellite ecosystem. CPCL has used that know-how to develop future generations of engineers, while developing successful working partnerships with a variety of community contributors. We look forward to continuing this role in the industry and further expanding the boundaries of space education and exploration.

Cal Poly CubeSat Laboratory At a Glance: 

  • Laboratory created in 1999
  • CubeSat standard established in 2004
  • $25+ million in sponsored projects
  • 1,000+ students trained from all colleges
  • 12 in-house developed and launched CubeSats
  • 175+ CubeSat missions supported


Cal Poly is developing a program that will provide CubeSat developers with the knowledge and experience gained from the many missions Cal Poly has been a part of. The lessons learned from those missions will be used to develop educational materials that will help developers avoid common pitfalls that have sunk previous missions. The goal is to increase success rates for all CubeSat programs across the board. The Best Practices program will begin by creating a database of gathered knowledge as an easily searchable reference. Cal Poly is also putting together a training program that will teach developers all aspects of CubeSat design, testing, program organization, licensing, and more. Trainings can be geared for experience levels ranging from beginner to novice.


Contact Us

Have any questions? Contact us at cubesat@calpoly.edu or visit our websites cubesat.org and polysat.org 



Vibe Testing

The CubeSat Laboratory operates an electro-dynamic shaker table capable of producing the required G-forces felt during launch. The vibration table is capable of producing a total sine vector force rating of 6000 pounds as it operates between 5 and 3000 Hertz. All P-PODs and CubeSats are thoroughly tested to simulate extreme launch conditions. 


T-VAC Testing

The Cal Poly CubeSat team performs regular thermal vacuum testing on all flight hardware to simulate behavior of materials in different environments. Donated by Northrop Grumman, the vacuum chamber can be held at 10^-5 torr and the test articles are heated and cooled by a copper shroud.


Clean Room

Equipped with 224 sq ft – 100,000 class clean room, the Cal Poly CubeSat team is able to build and integrate CubeSats and P-PODs on campus. Quality Assurance is maintained during all clean room procedures to allow for a consistent and reliable product. All personnel are required to wear protective lab suits and hair nets while working in the clean room. 

Shock Testing

The CubeSat team uses a drop hammer impact table to simulate the extreme launch shock environment, which P-PODs and CubeSats may experience. This shock table allows for precise, calibrated impact testing to ensure the proper simulation of a launch environment.


Helmholtz Cage

Built and assembled last year as a part of a thesis, the Cal Poly CubeSat team now has access to a Helmholtz cage for testing hardware in electromagnetically controlled environment. The cage has a minimum field of 10 nanoTeslas.


Groundstation Network

The team commands and downlinks data autonomously through a Cal Poly developed ground station network which is capable of autonomous operation of several ground stations in multiple geographic locations. PolySat currently has three operational ground stations on campus at Cal Poly; Hertz is composed of a UHF Yagi antenna and VHF Vagi antenna; Marconi is a dual-phased UHF Yagi array; and Friis is a quad-phased UHF Yagi array.


Read more about the Cal Poly CubeSat Laboratory testing and facilities here.



FAUXSAT stands for the First At-Altitude Use of XCube and Sync Acquisition of Telemetry. This project is being developed as a proof of concept payload for the XCube platform with the goal being to fly FAUXSAT onboard XCube’s first flight with NASA’s ER-2 aircraft to demonstrate XCube’s functionalities.

Aerodynamic Deorbit Experiment

ADE (CP-14), Aerodynamic Deorbit Experiment, is a 1U CubeSat with a deployable drag sail payload that will be deployed into a geostationary transfer orbit (GTO). The primary mission objective for ADE is to provide flight qualification for the dragsail and determine its viability. The deployable drag sail is designed to take advantage of the aerodynamic drag forces experienced by the spacecraft near its orbital perigee.


PowerSat is a mission in partnership with Deployables Cubed GmbH, Germany. PowerSat aims at demonstrating the deployment of a large solar array capable of producing up to 100 W. The power generated will be handled by a Maximum Power Point Tracking (MPPT) based electrical power subsystem being developed in-house by the Cal Poly CubeSat Laboratory (CPCL). Following launch, the solar array stowed in a 1U volume will unfurl like origami to a 4 m² area and pictures will be taken from space to validate the solar array deployment. The PowerSat CubeSat has been selected for participation in NASA’s CubeSat Launch Initiative (CSLI).



In 2020, the CubeSat Laboratory initiated the development of a deep space communication system for small spacecraft using X-band. The project overall goal is to establish the design of a low power consuming and low cost deep space communication system that will enable small spacecraft to expand their on-orbit capabilities and enable a larger number of players access to spacebased deep space research.


GOOSE is a nano reaction control system for small satellites that will use resistojets to flash water propellant to steam. As CubeSats go further than low Earth orbit, reaction control systems are necessary to control the attitude of the spacecraft and perform orbital maneuvers. The CubeSat Laboratory is tasked with the development of the avionics that will control the valves and heaters of the system, accepting commands, and relaying telemetry and sensor readings back to the spacecraft’s onboard computer.


PESPI is a two-year project in collaboration with UCI, UCLA and NASA’s Jet Propulsion Laboratory. The final product of the mission is to have a design for an electrospray thruster module. The Cal Poly CubeSat Laboratory (CPCL) has two main tasks. The first task consists in the design of a CubeSat-class electrical power subsystem (EPS) for operation of the thrusters. There are different types of thrusters and the EPS must be able to switch between two power thrusters that have different operating characteristics. The EPS must also be able to individually control the different thrusters as well as control a solenoid valve that controls the flow of the propellant.


Spinnaker 3

The Spinnaker3 payload will deploy an 18 m² dragsail to provide deorbit capability for the Firefly Alpha launch vehicle upper stage. The payload is composed of an 8U dragsail device with a 1U avionics box and a 12U stilt system. The dragsail device consists of four 3 m carbon fiber booms wrapped around a single hub and four transparent sail quadrants. Tracking and mission operations will be conducted at Purdue University and Cal Poly San Luis Obispo.


CubeSat Kit

The CubeSat Kit project aims to develop an educational platform with modular subsystem components so individuals can learn more about CubeSat operations and systems. The Kit serves to enable external training capabilities and can contribute to capacity building efforts domestically and internationally.

Interplanetary Spacecraft Poly-Picosatellite Orbital Deployer

The Interplanetary Spacecraft Poly-Picosatellite Orbital Deployer, or ISP-POD was developed by the Cal Poly CubeSat Laboratory (CPCL) to expand the capabilities of CubeSats to travel beyond the orbit of Earth. This deployer functions as a carrier, supporting CubeSats on their interplanetary journeys and deploying them into space when the time comes.


Stickcube is an internal project intended to be both: a learning project to get members of the Cal Poly CubeSat Laboratory (CPCL) more familiar and comfortable designing control systems and filters for future missions involving Attitude Determination and Control Subsystem (ADCS); and a testing bed for ADCS algorithms and hardware. Stickcube’s intended design is an inverted pendulum with a microcontroller (Arduino UNO), Initial Measurement Unit (IMU), and reaction wheels atop a threaded metal shaft.


The AMDROHP mission is a technology demonstration for an Additively Manufactured Deployable Radiator with Oscillating Heat Pipes (AMDROHP). This mission is a collaboration with Cal State LA (principal investigator), NASA’s Jet Propulsion Laboratory and the Cal Poly CubeSat Laboratory. In addition to performing radiator validating experiments, the AMDROHP mission will serve as the foundation of CubeSat capabilities at Cal State LA and an educational opportunity for several graduate and undergraduate students. The development of this radiator technology will aid addressing the thermal challenges presented by high powered CubeSats on future lunar missions.



XCube is a collaboration project between NASA’s Ames Research Center, NASA’s Armstrong Flight Research Center, and the University Space Research Association. NASA’s high-altitude ER-2 has unused space in its payload bay. XCube offers a standardized mounting solution, communication protocol set, and a wide variety of power options, allowing organizations to develop smaller payloads according to the CubeSat standard and piggyback on ER-2 flights, maximizing the payload bay usage.


Benchmark Space

Benchmark Space Systems

Booth Times: April 27th – 29th at 8:00 – 9:30AM and 2:00 – 4:00PM PST 

Watch Here: https://calpoly.zoom.us/j/89020493339?

About Benchmark Space Systems:

Our mission is to improve yours. Founded in 2017 and headed for multiple in-space missions in 2021, Benchmark Space Systems is positioned to be your in-space mobility partner. We are focused on improving accessibility to propulsion capability by providing the most cost-effective propulsion solutions for your Small Satellite mission needs: from simple orbit adjustments and regulatory compliance to high-agility maneuvers and RPO. Benchmark Space’s innovations have been specifically designed to improve safety and capability for spacecraft ranging from 1U through ESPA class. Our short lead times, ease of integration, and unpressurized launch enabled by our patented On-Demand Pressurization System have been important differentiators for our customers. Our team is eager to explore how one of our several best-in-class products may improve your next mission!


Integrated Propulsion Systems:


Starling Propulsion System

Benchmark Space Systems’ Starling system offering was developed to provide the benefits of reliable, high-precision positioning and control capability with unprecedented safety and affordability

This innovative system uses inert, non-toxic powdered fuel that is filled before shipping and remains inert until a pressurization command is triggered on-orbit. The ability to fill, ship, store, and inhibit an assembled & fueled Starling is “a game changer” for lowering launch manifest and operational costs, improving safety and reliability over alternatives, and providing a path to ISS compatibility.

Additive manufacturing on primary components delivers unbeatable lead time, making this the premier propulsion solution for your next CubeSat mission.


Halcyon Propulsion System

Benchmark Space Systems’ Halcyon delivers a non-toxic (‘green’), high thrust propulsion system to the small satellite market. Our innovations address challenges with alternative systems in this class:  lead time, launch safety, and power consumption.

Our proprietary on-demand pressurization technology and non-toxic propellants will ease your launch manifest and expand your on-orbit capabilities.

Halcyon is offered in monopropellant HTP or dual mode HTP + Butane creating the most innovative small satellite solution for your high thrust, or pulse-mode operational needs.

First mission is launching in 2021.


Peregrine Propulsion System

Benchmark Space Systems’ Peregrine delivers a non-toxic (‘green’), high thrust propulsion system to the small satellite market. Our innovations address challenges with alternative systems in this class:  lead time, launch safety, and power consumption.

Our proprietary on-demand pressurization technology and non-toxic propellants will ease your launch manifest and expand your on-orbit capabilities. Additionally, Benchmark Space’s patent pending micromixing technique eliminates the need for catalyst beds, a high cost, long-lead component used in other chemical propulsion systems.

With in-house components designed for additive manufacturing, Benchmark offers an industry-best performance and value.          





Mitsui Bussan Aerospace Co

Mitsui Bussan Aerospace Co., Ltd.

Virtual Exhibit Booth: https://calpoly.zoom.us/j/89020493339?

April 27 @ 8:00AM-9:30AM PST | 2:00PM-4:00PM PST

April 28 @ 8:00AM-9:30AM PST | 2:00PM-4:00PM PST

April 29 @ 8:00AM-9:30AM PST | 2:00PM-4:00PM PST


We are looking forward to talking with you!


Please feel free to contact us for further information.


E-mail : spacebiz@mb-aero.co.jp

Website : https://mba-space.com/en/

About Our Services

Mitsui Bussan Aerospace offers various types of services for CubeSat developers.

(1) CubeSat deployment service from ISS KIBO Module

We were selected by JAXA (Japan Aerospace Exploration Agency) as an official service provider for the CubeSat deployment service from KIBO the Japanese experiment module on ISS. This is the first ISS privatization project given by JAXA and we are working with JAXA very closely to execute our mission. We are able to provide satellite rideshare launch opportunities to the ISS and deployment service  from the ISS for up to 6U size CubeSat and 50kg class satellites.

(2) One Stop Service

We can provide all necessary services to the customers who want to use satellites for commercial purposes and scientific experiments. We also provide relevant support services such as design and development of satellites, launch and deployment, frequency registration and satellite operations.

(3) Rocket Rideshare Service as a Spaceflight’s Agency

Spaceflight, Inc., the leading global launch services provider, offers the most diverse portfolio of launch options and comprehensive mission management services have teamed to expand their business footprint. We and Spaceflight have reached to conclude an exclusive agency contract in order to make sure each role in the sales activities in the global market.

(4) ISS Experimental Opportunity

We can introduce experimental opportunities inside ISS, such as Japanese experimental module KIBO. KIBO is the science laboratory to conduct various experiments under micro-gravity environment. We will assist you to realize your plan in the ISS mission.

Our Corporate Information

Over 30 years since being founded in 1982, Mitsui Bussan Aerospace Co., Ltd. has acted as a dedicated aerospace and defense trading company to contribute to the development of Japan’s aviation industry and the improvement of national security through the import and sales of helicopters, aircraft and defense-related equipment.
The company now goes beyond import and sales, leveraging information, logistics, financial and other technologies to provide business solutions that meet the wide-ranging needs of customers in aviation, defense and space.

Mitsui Bussan Aerospace arranges/negotiates with vendors for price, contract term, export control and other process on behalf of customers.

Brief company profile:

  • Established in April, 1982
  • A 100% owned subsidiary of Mitsui & Co., specialized in sales and marketing in aviation and aerospace fields
  • Approx. 120 employees as of April, 2021
  • Sales amount approx. US$585M – as of March 2020
  • Overseas Offices

-US Subsidiary: Dallas, TX

-European Liaison Office: Milano, Italy

  • Space business department was established on July 1st, 2019


Tekko Bldg. 22F, 8-2, Marunouchi 1-chome, Chiyoda-ku, Tokyo, Japan



April 27, 2021 @ 8:00 AM – 9:30 AM|

April 28, 2021 @ 7:00 AM – 8:00 AM – EU/Asia | 8:00 AM – 9:30 AM

April 29, 2021 @ 7:00 AM – 8:00 AM – EU/Asia | 8:00 AM – 9:30 AM | 2:00 PM – 4:00 PM

Virtual Exhibit Booth: https://calpoly.zoom.us/j/89020493339?


Jeroen Rotteveel


One of the founders of ISISPACE and currently the CEO of the company. His responsibilities include:

  • Strategy
  • Business Development and Institutional Markets
  • Internal Technology Roadmapping
  • Company Finance

Abe Bonnema

Director of Marketing & Sales/Co-Founder

One of the founders of ISISPACE and Director of the company. His responsibilities include:
  • Marketing and Sales
  • ISILAUNCH Services
  • Strategy Development

Konark Goel

Business Development Engineer

Business Developer at ISISPACE, background in Space Systems Engineering. His responsibilities include:

  • R&D collaborations
  • Satellite Platform and Turn-key Space Mission Sales

Kevin Segura

Sales Manager

Experienced in technical sales and science missions, with background in Aerospace engineering. His responsibilities include:
  • Custom satellite buses
  • Turnkey satellite missions
  • Capacity building programs

ISISPACE Group is a vertically integrated small satellite company, focused on providing high value, cost effective space solutions by making use of the latest innovative technologies. The company specializes in satellites ranging from 1 to 30 kilograms, providing contract research, innovative small satellite parts, sub-systems, platforms and turnkey space solutions to a broad range of customers. Based in Delft, Netherlands – ISISPACE employs over 125 specialists and maintains a development branch office in Somerset West, South Africa.

The vertical integration of nanosatellite activities within ISISPACE Group ensures that customer specific requirements can be accommodated, and flight hardware delivered quickly when customers are faced with a short delivery schedule. A large multi-disciplinary team enables the company to provide hands-on training for its customers, often in cooperation with educational partners in small satellite engineering. Through ISILAUNCH, its launch services subsidiary, it launches all sizes of small satellites. More info here.


Would you like to know more about our solutions? Take a look at our brochures here!

3U CubeSat ISISPACE Group6U CubeSat ISISPACE Group12/16U CubeSat ISISPACE Group

The TANGO mission concept developed by a consortium including ISISPACE Group as mission prime, and partners Netherlands Organisation for Applied Scientific Research (TNO), Royal Netherlands Meteorological Institute (KNMI), Netherlands Institute for Space Research (SRON) and 3D PLUS. The pair of 16U spacecraft host complex atmospheric science instruments for the monitoring of CH4 and NO2 emission on an urban or industrial scale. The spacecraft bus features redundant avionics for fault tolerance. This is seen as a major step in improving the robustness of spacecraft that use CubeSat and COTS-based equipment.

CubeSim - Satellite Simulator

CubeSim is an ISISPACE tool aimed at empowering satellite flight software development and testing, as well as making it entirely hardware independent. Software development is unfortunately too often hindered by hardware late-deliveries or low-availability. In addition, debugging on embedded hardware does have limitations in terms of debugging features and backtracing. Hard faults on embedded systems are often hard to catch and analyze, especially during software long-duration testing.


In a satellite, flight software runs on the OBC (on-board flight computer). The OBC in turn brokers memory and communication interfaces so that software can interact with radios, payloads and data.
Most of the code composing flight software is actually portable, which means that it could run on any platform – OBC or PC – as opposed to the CPU peripherals which are very specific to the chip being used.
The philosophy of CubeSim is to take advantage of that portability and simply replace or wrap the portions that are not. The diagrams below shows general FSW architecture, where OBC platform-specific libraries are replaced by a completely API-compatible set of libraries made to run on a PC. This way, flight software can be compiled either for an OBC or a PC running Windows/Linux.


That way, our embedded software engineers become able to run and debug flight software from their PC, benefitting from best-in-class development tools for multi-threaded environments, memory analytics and code coverage.

In-place library replacement


Regarding the replacement of hardware-specific parts of the software – hence non-portable – several options are available and offer different advantages, mostly regarding serial drivers:

  • Using USB-to-UART or USB-to-I2C adapters enables the development of software drivers and connecting to real hardware, locally or remotely,
  • Simulating fully or partly a device for pure software simulation, or fault injection,
  • Using empty function calls,

Deep functional analysis

The most difficult part of software testing often relies in functional testing, since it cannot be carried by unit testing and relies on sensors / actuators in a closed-loop-system.
Complete satellite mocking can in this case become a very efficient way of testing the behavior of the system:

  • Physics of the space environment is simulated,
  • Sensors use a model accounting for the physics propagator state,
  • Actuators also use a model and provide inputs to the physics propagator,

In this scenario, any satellite parameter can easily be exposed to the user in a way that it can be deeply analyzed and understood, taking into account its past and its evolution.
Tabulated outputs are generated and allow using analysis software to verify a healthy behavior in any simulated start conditions (eclipse, high spin rates, etc.).

Vincent Gollé​

Embedded software developer specialized in complex systems. His responsibilities include:

  • Develop mission-critical software,
  • Design Cubesat on-board computers.



Virtual Exhibit Booth Link: https://calpoly.zoom.us/j/89818628354

April 27, 2021 @ 8:00AM–9:30AM PT | April 28, 2021 @ 8:00AM–9:30AM PT | April 29, 2021 @ 8:00AM–9:30AM PT

Hey – thanks for dropping by NanoAvionics virtual booth! With over 85 accomplished CubeSat missions and commercial projects, our team has definitely something to share what relates to hardware, software and satellite mission development. Meet our team attending CubeSat Developers Workshop: 

F. Brent Abbott

CEO, Nanoavionics us

Brent has more than 20 years of experience in the satellite industry, with senior roles at Honeywell, AAC/Clyde Space and Surrey Satellite Technologies US, where he started the hosted payload program with OTB-1

Casey Kelby

Business development manager

Casey is a business development manager at NanoAvionics US. Prior to joining NanoAvionics, Casey gathered 7 years of experience in supporting business development and marketing in the commercial sector.

Augustinas Lubys

business development manager

Augustinas is a business development specialist at NanoAvionics, building successful relationships with customers from Europe and the Middle East. 

Zilvinas Kvedaravicius

business development director

Žilvinas brings a successful track record of business development and sales from early commercialization stages of NanoAvionics.  He works with all main markets and supervises NanoAvionics distributors in key regions. 

About NanoAvionics

NanoAvionics is a smallsat bus manufacturer and mission integrator currently based in five locations across the US, UK, and Lithuania. The company’s efforts are focused on enabling critical satellite functions and optimising their hardware, launch, and satellite operation costs by providing end-to-end small satellite solutions – ranging from single missions to constellations. Its core engineering team has implemented over 85 successful satellite missions and commercial projects during the past several years. With modularity as the fundamental principle of NanoAvionics systems’ architecture, NanoAvionics provides economic viability to a wide range of small satellite constellation-based missions, businesses, and organizations worldwide.

Learn about our flagship CubeSat bus M6P and its subsystems:

Download Product Information