{"id":22800,"date":"2025-10-23T13:21:34","date_gmt":"2025-10-23T13:21:34","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=22800"},"modified":"2025-10-23T13:21:34","modified_gmt":"2025-10-23T13:21:34","slug":"niobium-alloy-c-103-for-high-performance-space-applications-first-results-with-using-cold-spay-additive-manufacturing-csam","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2025\/10\/23\/niobium-alloy-c-103-for-high-performance-space-applications-first-results-with-using-cold-spay-additive-manufacturing-csam\/","title":{"rendered":"Niobium alloy C-103 for high-performance space applications \u2013 first results with using Cold Spay Additive Manufacturing \u2013 CSAM\u00a0"},"content":{"rendered":"\n<p><strong>Leonhard HOLZGASSNER, J\u00e1n KOND\u00c0S, Reeti SINGH, Markus BROTSACK<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: N\/A<\/strong><\/p>\n\n\n\n<p><strong>Conference number: HiSST-2025-193<\/strong><\/p>\n\n\n\n<p>Space propulsion applications require lightweight materials that can withstand high stresses at elevated temperatures. Niobium has a very low density compared to other refractory metals but high strength, i.e. a high strength-to-weight ratio. The material also shows high thermal conductivity and a low ductileto-brittle transition temperature. This low transition temperature is advantageous for space applications because it shows excellent resistance to high-frequency vibrations at cryogenic temperatures. Furthermore, C-103, a niobium, hafnium, and titanium alloys used for space propulsion applications, have a high melting point at around 2.350\u00b0C and show strong stability at elevated temperatures, too. Currently, many investigations around C-103 material for in-space propulsion systems for satellites are happening in the space industry. This work shows the feasibility of Cold Spray Additive Manufacturing (CSAM) technology to produce a C-103 test part as a first step for future nozzle designs for different space applications. It is essential for the application to have as thin walls as possible to get down the take-off weight of the satellites. A tube of around 135 mm in length and 2 mm in wall thickness has been manufactured using CSAM. The manufacturing process will be presented in detail, in pictures. It has been proven that C-103 can be sprayed with high deposition efficiency using cold spray technology. Deposition efficiency of around 92% with a 4 kg\/h deposition rate was observed. Both properties make cold spray cost-effective for manufacturing in-space propulsion nozzles with C-103<br>niobium alloy. Furthermore, microstructural and mechanical properties of cold-sprayed C-103 have also been investigated.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2025\/10\/HISST2025_193_paper.pdf\">Read the full paper here<\/a><\/p>\n\n\n\n<p><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Leonhard HOLZGASSNER, J\u00e1n KOND\u00c0S, Reeti SINGH, Markus BROTSACK<\/b><\/p>\n<p>DOI Number: N\/A<\/p>\n<p>Conference number: HiSST-2025-193<\/p>\n","protected":false},"author":2,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[993,3361,3363],"tags":[2161,3578,3579,3580],"class_list":["post-22800","post","type-post","status-publish","format-standard","hentry","category-events","category-1-hisst-2025","category-propulsion-systems-components","tag-additive-manufacturing","tag-cold-spray","tag-csam","tag-niobium-c-103","category-993","category-3361","category-3363","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/22800","targetHints":{"allow":["GET"]}}],"collection":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts"}],"about":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/types\/post"}],"author":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/users\/2"}],"replies":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/comments?post=22800"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/22800\/revisions"}],"predecessor-version":[{"id":22802,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/22800\/revisions\/22802"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=22800"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=22800"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=22800"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}