SME-SAT

Fueled by mass market demand, terrestrial consumer electronics continue to drive technology advancement in the field of microelectronics devices. Many of these technologies are spearheaded by the contributions of small and medium enterprises (SME).

Overview

There is a clear opportunity to revolutionise space technologies by leveraging advancement in the commercial electronics market. However, despite the benefits to the space industry, it remains difficult for SMEs to get involved due to the significant cost, effort, time, and paper work to qualify parts for space applications.

The primary purpose of this spacecraft is as a technology demonstrator. Each SME in the consortium will be responsible for contributing a particular spacecraft subsystem. These systems/subsystems will be integrated into a nanosatellite forming SME-SAT and allow Small to Medium Enterprises to space qualify and characterise their technologies in the environment of space.

The SME-SAT will be implemented using a 3U commercially available off the shelf (COTS) structure. This standard consists of a structure that has an external envelope of 100mm x 100mm x 340.5mm, internal envelope of 98.4mm x 98.4mm x 295.2mm (L x W x H). On the outside of this structure will be mounted a number of solar arrays that will provide power to the bespoke power system. Inside the structure are a number of PC-104 standard boards that provide the functionality discussed in the following subsections.

The sensor payloads are all connected to a common PC-104 board that interfaces to the rest of the satellite bus. Many of the sensor payloads are internal to the satellite, however the accelerometers and gyros are placed on a deployable boom that will move them approximately 300mm away from the spacecraft.

    Objectives

    The primary objective of this project is to involve SMEs from the terrestrial sector on a space project and allow them to space qualify their technology. SME-SAT brings together one of the largest SME based consortiums ever to develop advanced space technologies based on terrestrial applications, which enables them to fully space qualify their technologies within three years of the project start date.

    This project represents a unique, unprecedented space mission, fostering a new alliance between SME’s, universities and a large scale space prime/integrator in which high risk technologies will be developed and fully tested in space using cubesats.

    The particular payloads that will be demonstrated in this project include:

    • High precision ADCS (Surrey)
    • Nano-Control Moment Gyros for agility (Surrey)
    • Gyros (Sensonor)
    • Accelerometers (Sensonor/Theon)
    • Star sensor (ISIS)
    • Failure Detection, Isolation and Recovery (HSS)
    • Power system (SystematIC design, NL)
    • Structures (MPB)
    • Magnetometer (LEMI)
    • GPS (SSBV).

    Outputs

    To date, the SME-SAT consortium partners and staff have “Design, build, integrate and test platform and payload subsystem hardware and software into a new technology demonstrator mission based on the 3U CubeSat standard.”

    As per the project goals, each subsystem has undergone new developments to raise the technology readiness level (TRL), and these results can be exploited for research and commercial purposes. Since 2013, the consortium partners have worked together to ensure that hardware and software interfaces allowed for a complete satellite model and minimal remedial work or loss of project time.

    Period 1 summary

    During this period the project was broadly on target, having produced the deliverables associated with our proposal for M6 and M12. This period continues into month 22 where the launch phase of the project begins. This period is focused on getting the satellite into its launch ready configuration. The next challenges in the next period were:

    • To finish the testing of engineering models of both the hardware and software for payloads and core satellite components
    • Complete assembly of solar panels
    • Finish testing and space qualification of satellite payloads and sub systems
    • Integrate payloads into satellite
    • Qualification of the satellite
    • Secure launch opportunity

    Period 2 summary

    In 2015, the CubeSat underwent major mechanical and electrical redesign and review to ensure that each payload could be successfully accommodated inside the volume, and typical interfacing control documentation was utilised effectively to drive forward the manufacture of parts and payloads.

    In the period between Jan – June 2016, the flight software was advanced in FreeRTOS and a new bootloader started in April given all subsystems were at Surrey. Ongoing issues were found however and the launch delays were exploited to reduce the risk in given failure modes. New solutions were underway to combine the push to break deployment switch with the EPS battery to prevent leakage in the event of long storage durations, and ISIS recently returned new solar panels with magnetic compensation loops to prevent satellite spin-up present in recent CubeSat missions.

    In November 2015, the soft-stack of the flight model was documented online at YouTube and also demonstrated the boom deployment and sensor readings from the LEMI payload to confirm completion of boom deployment.

    A summary of the hardware status and qualification is presented at project close. At the start of the project the qualification status of each subsystem was reviewed and a tailored qualification plan was generated. The intention of the development plan was to ensure that all hardware was at the same level of acceptance prior to launch. The tests conducted included inspection, functional testing, vibration, thermal testing.

    Subsystem Payload/platform Qualification status Outstanding qualification for flight Model on which test was performed
    ISIS Structure Platform Heritage on multiple missions, Vibration (Qual) None N/A
    Stellenbosch ADCS Platform Heritage on multiple missions None N/A
    SystematIC EPS  Platform Vibration (Qual), Thermal tests successful PFM Vacuum testing EM (main component analysed during Vibration & Thermal)
    ISIS Solar Panels Platform Heritage on multiple missions None  N/A
    ISIS TRXVU Platform Heritage on multiple missions None  N/A 
    ISIS ANT-S Platform Heritage on multiple missions None  N/A 
    ISIS Star Tracker Payload ISIS flight processes observed Full PFM testing EM – no mechanical representative
    Surrey CMG Payload Vibration (Qual), Thermal tests successful PFM Vacuum testing (Vacuum rate components used only on FM) EM (Vibration & Thermal)
    SensoNor STIM Payload  Independently qualified, Vibration (Qual), Thermal tests successful None EM (Vibration & Thermal)
    LEMI Magnetometer Payload  None Full PFM testing  PFM
    Theon Accelerometer Payload  None Full PFM testing PFM 
    MPB STDR Tiles Payload  Vibration (Qual) None EM (Vibration)