For 500 years transient light phenomena (TLP) have been observed on the lunar surface by ground-based observers. The actual physical reason for most of these events is today still unknown. Current plans of NASA and SpaceX to send astronauts back to the Moon and already successful deep-space CubeSat mission will allow in the future research nanosatellite missions to the cislunar space. This thesis presents a new hardware and software concept for a future payload on such a nanosatellite. The main task was to develop and implement a high-performance image processing algorithm which task is to detect short brightening flashes on the lunar surface. Based on a review of historic reported phenomena, possible explanation theories for these phenomena and currently active and planed ground- or space-based observatories possible reference scenarios were analyzed. From the presented scenarios one, the detection of brightening events was chosen and requirements for this scenario stated. Afterwards, possible detectors, processing computers and image processing algorithms were researched and compared regarding the specified requirements. This analysis of available algorithm was used to develop a new high-performance detection algorithm to detect transient brightening events on the Moon. The implementation of this algorithm running on the processor and the internal GPU of a MacMini achieved a framerate of 55 FPS by processing images with a resolution of 4.2 megapixel. Its functionality and performance was verified on the remote telescope operated by the Chair of Space Technology of the University of Würzburg. Furthermore, the developed algorithm was also successfully ported on the Nvidia Jetson Nano and its performance compared with a FPGA based image processing algorithm. The results were used to chose a FPGA as the main processing computer of the payload. This concept uses two backside illuminated CMOS image sensor connected to a single FPGA. On the FPGA the developed image processing algorithm should be implemented. Further work is required to realize the proposed concept in building the actual hardware and porting the developed algorithm onto this platform.

When developing products for space, including nanosatellites, the verification and validation process is a mandatory part of any project conducted within the European space industry. Within such a process, testing is a method for verification and validation. In this degree project, the appropriate tests for verification and validation of a nanosatellite were investigated. The project was conducted at the Royal Institute of Technology and the Polytechnic of Milan, as part of a larger research project under the name HERMES-SP. The research project was, at the time at which the degree project was taking place, in its first phase of the verification process. Therefore, tests for verification and validation of the Orbit Determination System (ODS) had not yet been defined. HERMES-SP is developing a nanosatellite platform with a very precise and reliable ODS, combining both Inertial Navigation System (INS) and Global Navigation Satellite System (GNSS). This degree project was thus conducted with HERMES-SP as an applicative case to investigate tests for a ’nanosatellites onboard ODS focusing on the GNSS. The ODS developed for the nanosatellite platform was studied, along with the underlying theory for ODS and GNSS. The plan for verification defined within HERMES-SP was also examined, and the presented methodology for test development was followed. To fully answer the project’s research question, the appropriate tests had to be identified and defined. This was done by first determining the requirements related to the ODS, and then identifying the tests that were needed to verify the requirements. Lastly, the tests were defined in test specifications and procedures. It was found that the relevant tests in the verification process were a handful of tests on the Equipment Test (ET), Software Test (SWT), and Subsystem Integration Test (SSIT) test levels. The tests were needed for verification of individual components in the system, as well as integrated components and their interfaces. The defined tests were considered appropriate for verification and validation for the first phase of the verification process. The project contributed to the identification and definition of tests for a restricted part of the verification process, related to the specified system of the HERMES-SP nanosatellite. The findings could be used in other nanosatellite projects with similar ODS by following the process and the methodology for test development documented in this report. / Vid utvecklandet av produkter ämnade för rymden, såsom satelliter, är processen för verifiering och validering en obligatorisk del av projekt utförda inom den Europeiska rymdindustrin. Under en sådan process är testning en metod för verfiering och validering. I detta examensarbete undersöktes de lämpliga testerna för verifiering och validering av en nanosatellit. Arbetet utfördes på Kungliga Tekniska Högskolan (KTH) och Politecnico di Milano, som en del av ett större foskningsprojekt under namnet HERMES-SP. När detta examensarbete tog plats var forskningsprojektet i sin första verifieringsfas. Därför hade inte tester för verifiering och validering av systemet för ombord banbestämning ännu definerats. Inom HERMES-SP utvecklas en platform för nanosatelliter med ett precist och tillförlitligt banbestämmnings system. Systemet kombinerar därför både tröghetsnavigeringssystem och satellitnavigering (GNSS). Systemet för ombord banbestäming utvecklat för nanosatelliten studerades, tillsammans med underliggande teori för banbestäming och GNSS. HERMES-SPs plan för verifiering och validering studerades, och den presenterade metodiken för testning adapterades. För att besvara arbetets forskningsfråga behövdes de lämpliga testerna identifieras och sedan defineras. Detta gjorder genom att först bestämma krav på systemet för banbestämning, och därefter identifiera de tester som behövdes för att verifiera kraven. Sist definerades testen i form av test specifikationer och test procedurer. Arbetet resulterade i att en handfull at tester relevanta för verifieringsprocessen identifierades. Dessa tester tillhörde olika nivåer av testing, nämligen testning av komponenter, mjukvara, och integrering av delsystem. Dessa tester var nödvändiga för att utvärdera individuella komponenter i systemet, samt integrerade komponenter och deras gränssnitt. De tester som definerades i arbetet ansågs nödvändiga för verifiering och validering under den första fasen av processen för verifiering. Examensarbetet bidrog till identifiering och definering av tester tillhörande en begränsad fas av verifieringsprocessen, relaterade till det specifiecerade systemet av HERMES-SPs nanosatellit. Upptäckterna skulle kunna användas i andra projekt för nanosatelliter med liknande system för banbestämning, genom att följa metodiken för utveckling av tester dokumenterade i denna rapport.

A finite element model of the CubeSat MIST was created, in order to assess the stresses that occur in the satellite in response to loads during its launch. Due to size limits of thesoftware used, simplifications had to be made to the geometry of the model. The loads assessed were quasi-static accelerations, random vibrations, shock loads, as well as a combined quasi-static acceleration and random vibration case. The study assumed the worst possible loads from a list of different potential launch vehicles for the satellite. Non-linear boundary conditions could not be modelled, and instead different linear boundary condition combinations were assessed. The results showed that the satellite showed positive margins of safety for the quasi-static loads. The lowest natural frequency for the satellite was above 130 Hz. For the random vibration loads, positive margins of safety could be shown if adverse stresses attributed to the boundary conditions inthe worst case were ignored. The model proved too conservative to qualify the satellite for the shock loads. Shock testing is therefore recommended for future work, unless requirements for waiving the shock testing can be met. The random vibration and combined loads analysis showed that the −X shear panel experienced high stresses in the corners of its windows, and the part should be inspected once environmental tests are conducted. The −X shear panel only showed adverse stresses in the most extreme boundary condition case, where its deformation was deemed unrealistic. / En finit elementmodell av nanosatelliten MIST skapades for att undersöka dess respons till lasterna under uppskjutning. På grund av storleksbegränsningar i programvaran behövde modellens geometri förenklas. Lasterna som undersöktes var kvasistatiska accelerationer, stokastiska vibrationer, chocklaster samt ett kombinerat kvasistatiskt accelerations- och stokastiskt vibrationsfall. Studien använde de värsta tänkbara lasterna från en lista över olika potentiella bärraketer för satelliten. Icke-linjära gränsvillkor kunde inte modelleras och istället utvärderades olika kombinationer av linjära gränsvillkor. Resultaten visade positiva säkerhetsmarginaler för kvasistatiska belastningar. Den lägsta naturliga frekvensen för satelliten var över 130 Hz. För de stokastiska vibrationsbelastningarna kunde positiva säkerhetsmarginaler motiveras om hänsyn togs till oegentligheter orsakade av gränsvillkoren i det extremaste fallet. Chocklastanalysen visade på begränsningar i modellen. Mekaniska chocktester kommer därmed behövas för att undersöka chocklasterna, om inte kraven for att hoppa över chocktestning uppfylls. Analyserna av de stokastiska vibrationerna och det kombinerade lastfallet visade att skjuvpanelen på −X-sidan upplever höga spänningar i hörnen på sina fönster, och bör inspekteras när experimentella tester genomförs. Skjuvpanelen på −X-sidan upplevde enbart för höga spänningar i fallet med mest extrema gröäsvillkor, där deformationerna bedömdes vara orealistiska.

The Canadian Nanosatellite Advanced Propulsion System is a liquefied cold-gas thruster system that provides propulsive capabilities to CanX-4/-5, the Canadian Advanced Nanospace eXperiment 4 and 5. With a launch date of early 2014, CanX-4/-5's primary mission objective is to demonstrate precise autonomous formation flight of nanosatellites in low Earth orbit. The high-level CanX-4/-5 mission and system architecture is described. The final design and assembly of the propulsion system is presented along with the lessons learned. A high-level test plan provides a roadmap of the testing required to qualify the propulsion system for flight. The setup and execution of these tests, as well as the analyses of the results found therein, are discussed in detail.