{"id":16254,"date":"2024-04-12T13:23:46","date_gmt":"2024-04-12T13:23:46","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=16254"},"modified":"2024-04-12T13:23:47","modified_gmt":"2024-04-12T13:23:47","slug":"rotational-detonation-engine-for-hypersonic-flight","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/04\/12\/rotational-detonation-engine-for-hypersonic-flight\/","title":{"rendered":"Rotational Detonation Engine for Hypersonic Flight"},"content":{"rendered":"\n<p><strong>Mr. Michael Paluszek*, Dr. Christopher Galea, Mr. Miles Simpkins, Dr. Yiguang Jub, and Dr.Mikhail Shneider<\/strong><\/p>\n\n\n\n<p><strong>DOI Number XXX-YYY-ZZZ<\/strong><\/p>\n\n\n\n<p><strong>Conference Number HiSST-2022-384<\/strong><\/p>\n\n\n\n<p>Hypersonic aircraft and missiles are of great interest. Potential applications include military reconnaissance and strike,<br>passenger aircraft, and the first stage for a two-stage to orbit launch vehicle. Numerous engines have been proposed for hypersonic vehicles including a wide variety of combined cycle engines, including those with integrated rockets and scramjets.<br>This paper presents the analysis, design, and simulation of a Rotating Detonation Engine (RDE) powered test vehicle that<br>can reach high Mach numbers. The paper covers the analysis of the engine with analytical studies. The aircraft, the size of a<br>hobbyist jet aircraft, that would be used to verify the flight performance of the engine is then presented. Non-linear dynamic<br>inversion techniques are used to design a guidance law. End-to-end simulations, including verification of the aircraft\u2019s overall<br>flight phases, are presented. Finally, the development plan for a cruise missile-sized test vehicle is discussed.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/HiSST-2022-384.pdf\" data-type=\"link\" data-id=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/HiSST-2022-384.pdf\">Read the full paper > <\/a><\/p>\n\n\n\n<p><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Mr. Michael Paluszek*, Dr. Christopher Galea, Mr. Miles Simpkins, Dr. Yiguang Jub, and Dr.Mikhail Shneider<\/b><\/p>\n<p>DOI Number XXX-YYY-ZZZ<\/p>\n<p>Conference Number HiSST-2022-384<\/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":[],"class_list":["post-16254","post","type-post","status-publish","format-standard","hentry","category-events","category-hisst-2022","category-propulsion-systems-and-components-hisst-2022","category-993","category-1006","category-1013","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16254","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=16254"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16254\/revisions"}],"predecessor-version":[{"id":16255,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16254\/revisions\/16255"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=16254"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=16254"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=16254"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}