{"id":16467,"date":"2024-04-26T14:29:45","date_gmt":"2024-04-26T14:29:45","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=16467"},"modified":"2024-04-26T14:29:46","modified_gmt":"2024-04-26T14:29:46","slug":"system-level-transient-model-of-a-propulsion-plant-for-a-mach-2-vehicle","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/04\/26\/system-level-transient-model-of-a-propulsion-plant-for-a-mach-2-vehicle\/","title":{"rendered":"System level transient model of a propulsion plant for a Mach 2 Vehicle"},"content":{"rendered":"\n<p><strong>K. Van den Borre, A. C. Ispir, B. H. Saracoglu<\/strong><\/p>\n\n\n\n<p><strong>DOI Number XXX-YYY-ZZZ<\/strong><\/p>\n\n\n\n<p><strong>Conference Number HiSST-2022-445<\/strong><\/p>\n\n\n\n<p>As a continuation of previous European efforts to develop high-speed civil air transportation, the<br>MORE&amp;LESS project aims to assess a broad spectrum of the supersonic flight regime, ranging from<br>Mach 2 to Mach 5. Within this scope, the present work builds a transient 1D propulsion model based on<br>the Olympus 593 engine, which powered the Concorde and operates at Mach 2. This model provides<br>new information on the transient engine behaviour, engine stability and control systems, which was<br>not possible using previously exploited steady 1D models. This approach also allows to simulate an<br>entire flight from take-off to landing in a computationally cost-efficient manner, allowing for efficient<br>optimisations taking all flight phases into account.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/HiSST-2022-445.pdf\" data-type=\"link\" data-id=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/HiSST-2022-445.pdf\">Read the full paper ><\/a> <\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>K. Van den Borre, A. C. Ispir, B. H. Saracoglu<\/b><\/p>\n<p>DOI Number XXX-YYY-ZZZ<\/p>\n<p>Conference Number HiSST-2022-445<\/p>\n","protected":false},"author":1,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[1006,1013],"tags":[1373,1372,1376,1375,1374],"class_list":["post-16467","post","type-post","status-publish","format-standard","hentry","category-hisst-2022","category-propulsion-systems-and-components-hisst-2022","tag-cycle-analysis","tag-dassl","tag-ecosimpro","tag-espss","tag-olympus-593","category-1006","category-1013","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16467","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\/1"}],"replies":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/comments?post=16467"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16467\/revisions"}],"predecessor-version":[{"id":16468,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16467\/revisions\/16468"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=16467"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=16467"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=16467"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}