The manufacturing of optical components, such as lenses or mirrors, consists of numeroussteps that are essential to the performance of the fnished optical system, such as the specifcation ofthe optical surface. For a longer period, the main focus has been in identifying and restricting thenegative effects of the low and high spatial frequency content of the surface. However, as technologyand optical equipment has become more advanced, the effects of the mid-spatial frequencies havebeen studied more, and continue to be a topic of research. As of now, there is still a need for methodsthat accurately predict and analyse the regime of mid-spatial frequencies, such that they can becontrolled during the specifcation phase, successfully limiting the need of post-processing steps.This work introduces a software tool, specifcally designed to approach this problem, which wasto be developed in Python as a contribution to the existing Optical Scripting Library at OHB. Byspecifying an optical component in terms of a Power Spectral Density function, together with thecontributions from different spatial frequency domains and the application of a ripple patterns, thissoftware tool can generate pseudo-random optical surfaces, which maintains the input specifcations.Furthermore, a Dynamic Link Library fle was developed, sharing the same functionality as thePython implementation, allowing for simulations using Zemax OpticStudio. Using the software tool,it was found that the relative error between input and output measurements were approximately0.78%, in terms of the Power Spectral Density Function. In addition, the result of analysing one of thetwo test cases indicate that the software tool is effective in predicting the infuence of mid-spatialfrequency errors, fulflling a previously measured predicition. The second test case proved that thesoftware tool can be used for mimicing surfaces of real measurements, holding the same specifcations.

In the advent of Space 4.0 era with the commercialization and increased accessibility of space, a requirement analysis, trade-off options, development status and critical areas of a propulsion system for a Commercial Micro Moon Lander is carried out. An investigation of a suitable system for the current mission is examined in the frame of the ASTRI project of OHB System AG and Blue Horizon. Main trajectory strategies are being investigated and simulations are performed to extract the ∆V requirements. Top-level requirements are extracted which give the first input for the propulsion design. An evaluation of the propulsion requirements is implemented which outlines the factors that are more important and drive the propulsion design. The evaluation implements a dual comparison of the requirements where weighting factors are extracted, resulting the main drivers of the propulsion system design. A trade-off analysis is performed for various types of propulsion systems and a preliminary selection of a propulsion system suitable for the mission is described. A first-iteration architecture of the propulsion, ADCS and GNC subsystems are also presented as well as a component list. A first approach of the landing phase is described and an estimation of the required thrust is calculated. A unified Bipropellant propulsion system is proposed which fills out most of the mission requirements. However, the analysis shows that the total mass of the lander, including all the margins, exceeds a bit the mass limitations but no the volume limitations. The results shows that a decrease in payload capacity or the implementation of a different trajectory strategy can lower the mass below the limit. In addition, further iterations in the lander concept which will give a more detailed design, resulting to no extra margins, can drive the mass below the limit. Finally, a discussion on the results is done, addressing the limitations and the important factors that need to be considered for the mission. The viability of the mission due to its commercial aspect is being questioned and further investigation is suggested to be carried out on the ”micro” lander concept. / I tillkomsten av Space 4.0 era med kommersialisering och ökad tillgänglighet av rymden, en kravanalys, avvägningsalternativ, utvecklingsstatus och kritiska områden av ett framdrivningssystem för en kommersiell mikro månlandare bärs ut. En undersökning av ett lämpligt system för det aktuella uppdraget genomförs inom ramen för ASTRI-projektet för OHB System AG och Blue Horizon. Olika strategier för banor undersöks och simuleringar utförs för att extrahera ΔV-kraven. Topp-nivå krav definieras och ger den första inputen för designen av framdrivningssystemet. En utvärdering av framdrivningskraven implementeras och belyser de viktigaste faktorer som driver design av framdrivningssystemet. En avvägningsanalys utförs för olika typer av framdrivningssystem och ett preliminärt urval av ett framdrivningssystem som är lämpligt för uppdraget beskrivs. En arkitektur för framdrivningen, ADCS och GNC-delsystem presenteras såväl som en komponentlista. Ett första tillvägagångssätt av landningsfasen beskrivs och en uppskattning av den nödvändiga dragkraften beräknas. Ett enhetligt Bi-propellant framdrivningssystem föreslås som uppfyller ut de flesta uppdragskraven. Analysen visar dock att summan av månlandarens massa, inklusive alla marginaler, överstiger massbegränsningarna men inte de volymbegränsningarna uppsatta i projektet. Resultaten visar att en minskning av nyttolastkapaciteten eller genomförandet av en annan banstrategi kan minska den totala massan då den inom gränsvärdena. Dessutom, ytterligare iterationer i månlandarens koncept som kommer att ge en mer detaljerad design, vilket resulterar i inga extra marginaler, kan leda till att den uppskattade massan minskar ytterligare. Slutligen förs en diskussion om resultaten, med hänsyn till de begränsningarna och de viktigaste faktorerna som måste beaktas för uppdraget. Lönsamheten hos uppdraget på grund av sin kommersiella aspekt är ifrågasatt och vidare utredning föreslås utförs på ”mikro” månlandare konceptet.