{"id":16177,"date":"2024-04-12T10:46:44","date_gmt":"2024-04-12T10:46:44","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=16177"},"modified":"2024-04-12T10:46:45","modified_gmt":"2024-04-12T10:46:45","slug":"advanced-low-cost-hypersonic-flight-test-platforms","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/04\/12\/advanced-low-cost-hypersonic-flight-test-platforms\/","title":{"rendered":"Advanced Low-Cost Hypersonic Flight Test Platforms"},"content":{"rendered":"\n<p><strong>F. Barato, D. Pavarin<\/strong><\/p>\n\n\n\n<p><strong>DOI Number XXX-YYY-ZZZ<\/strong><\/p>\n\n\n\n<p><strong>Conference Number HiSST-2022-201<\/strong><\/p>\n\n\n\n<p>Hybrid rockets are a specific type of propulsion system characterized by the use of a liquid oxidizer and<br>a solid fuel. This peculiarity provides very specific features respect to the other chemical propulsion<br>systems. Compared to solid rockets, hybrids are throttleable and restartable, they are environmentally<br>friendly and much safer to manufacture, store, manage and operate with a dramatic impact on costs.<br>Respect to liquid propulsion systems, hybrids are much simpler since the combustion chamber is not<br>regeneratively cooled and they need less than half of the liquid feed system. Thanks to these<br>peculiarities hybrid rocket propulsion systems are perfectly suited to be installed and operated on low<br>costs, partially reusable test platforms for hypersonic in-flight test. These affordable flight test platforms<br>can be used to provide otherwise not or only partially available real test data on components or<br>subsystems in the hypersonic regime, as, for example, thermal and mechanical loads, advanced<br>materials behavior, aerodynamics, air-breathing propulsion. University of Padua and T4i started doing<br>research in this field since 2006, acquiring a unique in the world expertise in the frame of paraffinbased hybrid rockets together with a wide expertise on nitrous oxide and hydrogen peroxide as<br>oxidizers. Different type of motors up to 25 kN of thrust have been designed, developed and tested.<br>Starting in 2019 a sounding rocket has been developed as a low-cost test platform for flight<br>demonstration of new technologies, including propulsion. The presentation provides an overview of the<br>work performed up to now and describes the new interesting opportunities made possible by advanced<br>hybrid rocket systems applied to hypersonic flight test platforms.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/HiSST-2022-201.pdf\" data-type=\"link\" data-id=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/HiSST-2022-201.pdf\">Read the full paper ><\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>F. Barato, D. Pavarin<\/b><\/p>\n<p>DOI Number XXX-YYY-ZZZ<\/p>\n<p>Conference Number HiSST-2022-201<\/p>\n","protected":false},"author":1,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[993,1006,1013],"tags":[1131,1129,440,1132,1130],"class_list":["post-16177","post","type-post","status-publish","format-standard","hentry","category-events","category-hisst-2022","category-propulsion-systems-and-components-hisst-2022","tag-flight","tag-hybrid","tag-hypersonic","tag-testing","tag-throttling","category-993","category-1006","category-1013","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16177","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=16177"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16177\/revisions"}],"predecessor-version":[{"id":16178,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16177\/revisions\/16178"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=16177"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=16177"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=16177"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}