{"status":"ok","message-type":"work","message-version":"1.0.0","message":{"indexed":{"date-parts":[[2026,1,30]],"date-time":"2026-01-30T09:09:05Z","timestamp":1769764145739,"version":"3.49.0"},"reference-count":23,"publisher":"SAGE Publications","issue":"13","license":[{"start":{"date-parts":[[2017,10,25]],"date-time":"2017-10-25T00:00:00Z","timestamp":1508889600000},"content-version":"tdm","delay-in-days":0,"URL":"https:\/\/journals.sagepub.com\/page\/policies\/text-and-data-mining-license"}],"content-domain":{"domain":["journals.sagepub.com"],"crossmark-restriction":true},"short-container-title":["Transactions of the Institute of Measurement and Control"],"published-print":{"date-parts":[[2018,9]]},"abstract":"<jats:p> Re-entry guidance is one of the primary tasks of a global strike mission. Hypersonic and common aero vehicles are currently being investigated for missions like this. This paper proposes a guidance law considering not only the constraints of terminal status and flight process, but also the avoidance of no-fly zones, to meet the requirements of a global strike mission. An improved A* algorithm is proposed first to achieve a real-time trajectory planning process. Then a dynamic optimization guidance law based on the model of a hypersonic vehicle considering single and multiple no-fly zones is founded. Numerical simulations show the robustness and rapidity of this optimization method. <\/jats:p>","DOI":"10.1177\/0142331217735050","type":"journal-article","created":{"date-parts":[[2017,10,25]],"date-time":"2017-10-25T20:44:26Z","timestamp":1508964266000},"page":"3899-3908","update-policy":"https:\/\/doi.org\/10.1177\/sage-journals-update-policy","source":"Crossref","is-referenced-by-count":6,"title":["Re-entry guidance for hypersonic vehicle satisfying no-fly zone constraints"],"prefix":"10.1177","volume":"40","author":[{"given":"Qing","family":"Lu","sequence":"first","affiliation":[{"name":"Institute of Precision Guidance and Control, Northwestern Polytechnical University, Shaan Xi Xi\u2019an, China"}]},{"given":"Jun","family":"Zhou","sequence":"additional","affiliation":[{"name":"Institute of Precision Guidance and Control, Northwestern Polytechnical University, Shaan Xi Xi\u2019an, China"}]}],"member":"179","published-online":{"date-parts":[[2017,10,25]]},"reference":[{"issue":"6","key":"bibr1-0142331217735050","first-page":"2251","volume":"56","author":"Acton JM","year":"2016","journal-title":"Limnology & Oceanography"},{"key":"bibr2-0142331217735050","unstructured":"Boyer J, Auletto R, Baloche N (2016) Method of adapting a segment of an aircraft trajectory with constant ground gradient segment according to at least one performance criterion. 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