DSE Group S12: Missile Space-based Trackingand Relay [M-STAR]

At present, there is a shortage of central Intelligence, Surveillance and Reconnaissance (ISR)frameworks within Europe and NATO countries. As such, one of the recognized challenges isthe capability to detect intercontinental ballistic missiles through means of a reliable and timelysystem. The prevailing shifts in the global geopolitical setting have evidenced that the threatof ballistic missiles is not weakening. As a result of this highly dynamic and ever-changingpolitical climate, the self-sufficiency that would follow from such a reliable detection systemis of strategic importance to the Netherlands and its European partners. Thus, M-STAR wascommissioned to DSE group 12 by the Royal Netherlands Air Force (RNLAF).

Mission ObjectiveM-STAR provides a complete design of a technical demonstration mission, maximising effectiveuse of a nanosat constellation to perform Early Warning for the Netherlands and its EuropeanPartners against ICBM threats. The detection, tracking and relay must be complete within 90seconds after launch, as dictated by the RNLAF.

System Design

In order to design a reliable system that is ableto detect, track and relay early warning within90 seconds of missile launch, a nanosat constel-lation of 306 satellites in 9 polar orbital planesis used. This constellation provides continuousglobal coverage. The technical demonstrationmission is planned to have seven satellites, buthas been designed to accommodate additionalspacecraft.Each M-STAR satellite consists of an alu-minium 12U structure equipped with a dual-optic (FOCUS and COVERAGE) InSb in-frared camera, which utilizes a circular imagingtechnique through means of a rotating mirror.By adopting the Otsu Thresholding algorithmon H2O and CO2 filtered images, potential mis-sile threats are identified. Through the applica-tion of a probabilistic model, a secondary satel-lite will be alerted of the potential missile usingan omnidirectional antenna. The second satel-lite will process and slew towards the coordi-nates of the potential missile using a modularADCS that allows for large momentum wheelsand a precise star tracker.These two satellites will perform a stereo-imaging process through which the 3D co-ordinates of the ICBM are computed. Thisdata, as well as the necessary data to clas-sify the ICBM, will be continuously relayedto the nearest ground station through satel-lite interlinking, at a bit rate of approximately20kbits/s, through the UHF frequency.

The spacecraft utilizes triple junction GaAs so-lar panels mounted on a gimbal in order to pro-vide sufficient power to the system. The ther-mal subsystem employs a passive thermal con-trol consisting of aluminized kapton foil as anouter coating to keep all subsystems and theircomponents at their operational temperaturerange. Furthermore, the InSb camera requiresa cooler to reduce dark current and instrumentnoise, for which the proposed cooler is the 6510Pulse Tube cooler by Thales Cryogenics. Thepropulsion unit consists of IFM ion thrusters toperform collision avoidance, orbit maintenanceand end of life operations.Each M-STAR satellite has been designed tooperate for a life time of 7 years, after whichthe system shall perform a de-orbit burn tocomply with the sustainability standards of themission.

Delft University of Technology Design Synthesis Exercise 2020