{"status":"ok","message-type":"work","message-version":"1.0.0","message":{"indexed":{"date-parts":[[2025,10,12]],"date-time":"2025-10-12T01:08:41Z","timestamp":1760231321979,"version":"build-2065373602"},"reference-count":36,"publisher":"MDPI AG","issue":"9","license":[{"start":{"date-parts":[[2022,9,6]],"date-time":"2022-09-06T00:00:00Z","timestamp":1662422400000},"content-version":"vor","delay-in-days":0,"URL":"https:\/\/creativecommons.org\/licenses\/by\/4.0\/"}],"content-domain":{"domain":[],"crossmark-restriction":false},"short-container-title":["Symmetry"],"abstract":"<jats:p>According to the symmetrical characteristics of a new type of Reusable Launch Vehicle (RLV) in the recovery phase, we studied the basic aerodynamic model data of Starship and the aerodynamic data with rudder deflection, and the causes of its aerodynamic coefficients are expounded. At the same time, we analyzed its stability and maneuverability. According to the flying quality requirements, the lateral-directional model of Starship in the return phase at a high angle of attack is analyzed. Finally, we analyzed the lateral heading stability and control deviation of Starship by using the criterion and nonlinear open-loop simulations. The results show that the Starship has pitching and rolling stability, but it only has heading stability in some ranges of angle of attack, and there is no heading stability at a conventional large angle of attack. At the same time, after modal analysis and comparison of flight quality, it can be seen that the longitudinal long-period model of the starship degenerates into a real root and it is stable and convergent. The lateral heading roll mode is at level 2 flight quality, the helical mode is at level 1 flight quality, and the Dutch roll mode diverges, which needs to be stabilized and controlled later.<\/jats:p>","DOI":"10.3390\/sym14091862","type":"journal-article","created":{"date-parts":[[2022,9,8]],"date-time":"2022-09-08T09:51:09Z","timestamp":1662630669000},"page":"1862","update-policy":"https:\/\/doi.org\/10.3390\/mdpi_crossmark_policy","source":"Crossref","is-referenced-by-count":2,"title":["Performance Analysis on the Small-Scale Reusable Launch Vehicle"],"prefix":"10.3390","volume":"14","author":[{"given":"Zheng","family":"Gong","sequence":"first","affiliation":[{"name":"Department of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China"}]},{"ORCID":"https:\/\/orcid.org\/0000-0003-3906-2180","authenticated-orcid":false,"given":"Zian","family":"Wang","sequence":"additional","affiliation":[{"name":"China Academy of Launch Vehicle Technology, Beijing 100076, China"}]},{"given":"Chengchuan","family":"Yang","sequence":"additional","affiliation":[{"name":"Department of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China"}]},{"given":"Zhengxue","family":"Li","sequence":"additional","affiliation":[{"name":"China Academy of Launch Vehicle Technology, Beijing 100076, China"}]},{"ORCID":"https:\/\/orcid.org\/0000-0002-3399-916X","authenticated-orcid":false,"given":"Mingzhe","family":"Dai","sequence":"additional","affiliation":[{"name":"School of Automation, Central South University, Changsha 410083, China"}]},{"ORCID":"https:\/\/orcid.org\/0000-0002-3130-6497","authenticated-orcid":false,"given":"Chengxi","family":"Zhang","sequence":"additional","affiliation":[{"name":"School of Electronic and Information Engineering, Harbin Institute of Technology, Harbin 150006, China"}]}],"member":"1968","published-online":{"date-parts":[[2022,9,6]]},"reference":[{"key":"ref_1","doi-asserted-by":"crossref","first-page":"745","DOI":"10.2514\/2.2674","article-title":"Aeroservoelastic analysis of the B-2 bomber","volume":"37","author":"Britt","year":"2000","journal-title":"J. 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