Our Payloads

Primary Payload

In-Orbit Space Debris Tracking Using Passive Bistatic Radar

STRATHcube’s Primary Payload will demonstrate an in-orbit debris detection method called passive bistatic radar (PBR) to show the potential to better track and detect debris from orbit compared to the current capabilities of ground-based facilities. This demonstration will test a signal processing algorithm developed by researchers at the University of Strathclyde to detect debris.

If this demonstration is successful, it will provide an alternative to conventional ground-based tracking that is cheaper and more available to the space community. This method would also demonstrate to the wider industry the potential applications and benefits of this approach, allowing it to then be implemented on a larger scale in the future.

Two different Primary Payload design options were explored concurrently throughout the year:

1.     A novel 3D phase array antenna.

2.     A commercially available off-the-shelf patch antenna.

A high-level design for both the 3D and patch antenna options was completed to evaluate their scientific capabilities on the size of trackable debris and to determine their mass, power and volume parameters.

The integration of the 3D phase antenna onto the CubeSat platform was challenging due to its size, high mass and power draw. Furthermore, the estimated minimum detectable size of debris of the 3D antenna was not much greater than that achievable by the patch antenna.

Therefore, as the scientific goal of this experiment is to demonstrate the capabilities of space based PBR technology, the commercially available off-the-shelf patch antenna has been chosen to facilitate the Primary Payload experiment.

Secondary Payload

Fragmentation Monitoring During Re-entry

STRATHcube’s secondary payload aims to monitor and record the conditions under which solar panel fragmentation occurs during re-entry. This novel experiment, which is the first of its kind will provide invaluable re-entry data to validate and develop re-entry analysis tools used in Design for Demise processes.

The key challenges of this re-entry experiment include:

• Ensuring the CubeSat remains aerodynamically stable throughout re-entry

• Maintaining communication via a satellite constellation to ensure re-entry data can be collected

The design of the secondary payload at this stage therefore consists of a passive aerodynamic stabilisation system which utilises the CubeSats solar panels for stability, as well as a communications platform to allow for data transmission via the Iridium constellation.

The Scientific Sensor Platform designed for the secondary payload to collect the required measurements includes: a thermal imaging camera and electromechanical break switches to monitor the solar panels throughout re-entry, and a heat flux sensor, thermocouples, pressure sensors and an IMU to record the conditions under which the solar panels break away from STRATHcube.

Further investigation into the integration and compatibility of the thermal camera and required communication package with CubeSat platform will be carried out by future groups.