Searched for: subject%3A%22thermal%255C+protection%255C+system%22
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Danny Tjokrosetio, Danny (author)
Advancements in the space sector have driven the democratization of planetary exploration. As a longstanding target of scientific interest, Mars will consequently witness an increasing demand for surface missions of various sizes. Its thin atmosphere, however, is a challenging environment for entry, descent, and landing (EDL). An incoming...
master thesis 2024
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Rønning, K.D. (author), Tang, Y. (author)
Due to good thermal conductivity and thermal shock resistance, ultra-high temperature ceramics such as zirconium diboride (ZrB2) have been investigated as promising materials to be used in reusable thermal protection systems TPSs are vital to the heat balance of a spacecraft during atmospheric reentry and subsequent operation in space. Hence,...
journal article 2024
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Rapisarda, Claudio (author)
Future Mars exploration missions require safe and controlled landing on the planet’s surface. Conventional entry, descent and landing (EDL) technologies, such as parachutes and rigid aeroshells, face limitations in meeting increasing demands for heavier payloads, harsher entry conditions, and desired landing locations due to their limited...
master thesis 2023
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ten Houte de Lange, Philip (author)
Dawn Aerospace is developing a horizontal take-off and landing two stage to orbit partially-reusable launcher concept. The re-usable first stage spaceplane operates on a return to launch site trajectory and integrates into the existing airspace, flying as an UAV. For any re-entry vehicle the design needs to account for aerothermodynamic...
master thesis 2022
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Vanhamel, J. (author), Eaton, Nicholas (author), Spreij, Roemer (author)
Currently, the amount of space debris is increasing rapidly due to the tremendous amount of satellite launches. Having an autonomous re-entry system aboard satellites at their end-of life, creates possibilities in the frame of lowering space debris, as well as for sample return from space. This paper aims at describing two possible deployment...
conference paper 2022
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Ahuja, Aditi (author)
The next step in spaceflight, among others, is the development of a reusable launch vehicle (RLV) suitable for manned missions. All existing designs of re-entry vehicles are either ballistic or low L/D vehicles. In the future, the aim is to develop a high L/D vehicle, because such vehicles experience lower g-loads, making the flight comfortable...
master thesis 2020
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Clar, Thibault (author)
With the global increase in passenger traffic and growing popularity of long-haul routes over the Asia Pacific region and Atlantic Ocean, the possibility for hypersonic transport could become an attractive option to reduce flight time over long distance from 16-20 hours down to around 4-5 hours. In this thesis, a Multi-Disciplinary Optimisation...
master thesis 2019
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Dubois, Wouter (author)
Current-day space vehicle are equipped with a passive Thermal Protection System (TPS), but these systems operate at the edge of their capabilities. The research into the next generation reusable space vehicle demands the use of active TPS, these systems are not limited to the capabilities of the used material but depend on the active cooling...
master thesis 2017
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Roorda, evelyne (author)
During its lifetime a space launcher is subjected to extreme heat loads. To protect space vehicles from these heat loads and their resulting temperatures they are equipped with a Thermal Protection System (TPS). Heat loads are typically the largest during flight through the atmosphere. The research question addressed in the thesis is: how robust...
master thesis 2017
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Buursink, J. (author)
To achieve a significant cost reduction for launch of payloads to space, it is essential that the launcher is reused to the largest possible extent, and that the maintenance and operations cost of this launcher are minimised. To achieve this, work is ongoing on metallic thermal protection systems (TPS) that hold the promise of much reduced...
doctoral thesis 2005
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