{"id":{"repo_id":"nps","oai_identifier":"oai:calhoun.nps.edu:10945/13049"},"canonical_url":"https://search.dev.ndltd.org/etd/nps/oai:calhoun.nps.edu:10945/13049","repository":{"repo_id":"nps","name":"Naval Postgraduate School","base_url":"https://calhoun.nps.edu/server/oai/request"},"display":{"title":"A simulator study of the horizontal landing characteristics and piloting techniques for manned re-entry gliders","abstract":"A fixed based simulator study of the approach and tangential landing of a class of manned re-entry gliders was conducted to determine the piloting techniques and vehicle parameters which best define the approach and landing problem. Tests were conducted on. 5 configurations typical of proposed vehicles with maximum lift to drag ratios of 3 to 5. The problem was Investigated from final approach to touchdown, In still and turbulent air, simulating longitudinal equations of motion only. A three phase landing consisting of a steady glide final approach, a nearly constant load factor flare maneuver, and a 15 to 20 second shallow angle, final glide was the preferred technique. The vehicle parameters found to be most Important were maximum lift to drag ratio and speed for minimum drag. A landing analysis based on fitted parabolic drag polars and a constant load factor flare was found to be valid for the vehicles tested.","abstract_html":"A fixed based simulator study of the approach and tangential landing of a class of manned re-entry gliders was conducted to determine the piloting techniques and vehicle parameters which best define the approach and landing problem. Tests were conducted on. 5 configurations typical of proposed vehicles with maximum lift to drag ratios of 3 to 5. The problem was Investigated from final approach to touchdown, In still and turbulent air, simulating longitudinal equations of motion only. A three phase landing consisting of a steady glide final approach, a nearly constant load factor flare maneuver, and a 15 to 20 second shallow angle, final glide was the preferred technique. The vehicle parameters found to be most Important were maximum lift to drag ratio and speed for minimum drag. A landing analysis based on fitted parabolic drag polars and a constant load factor flare was found to be valid for the vehicles tested.","abstract_has_math":false,"creators":["Weiland, Robert F."],"institution":"Princeton University","degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":"Aerospace and Mechanical Sciences","school":null,"contributors":[],"advisors":["Seckel, E."],"committee_chairs":[],"committee_members":[],"year":1965,"date_issued":"1965-05-01","date_published":"1965-05-01","updated_at":"2026-07-27T20:25:53Z","subjects":[],"languages":[],"rights":["This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States."],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://hdl.handle.net/10945/13049","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.advisor","label":"Advisor","values":["Seckel, E."]},{"key":"dc:contributor.department","label":"Department","values":["Aerospace and Mechanical Sciences"]},{"key":"dc:creator","label":"Author","values":["Weiland, Robert F."]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date.accessioned","label":"Dc Date Accessioned","values":["2012-08-29T23:35:34Z"]},{"key":"dc:date.available","label":"Dc Date Available","values":["2012-08-29T23:35:34Z"]},{"key":"dc:date.issued","label":"Date","values":["1965-05-01"]},{"key":"dc:publisher","label":"Institution","values":["Princeton University"]},{"key":"dc:type","label":"Dc Type","values":["Thesis"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:rights","label":"Dc Rights","values":["This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. 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A three phase landing consisting of a steady glide final approach, a nearly constant load factor flare maneuver, and a 15 to 20 second shallow angle, final glide was the preferred technique. The vehicle parameters found to be most Important were maximum lift to drag ratio and speed for minimum drag. A landing analysis based on fitted parabolic drag polars and a constant load factor flare was found to be valid for the vehicles tested."]},{"key":"dc:title","label":"Title","values":["A simulator study of the horizontal landing characteristics and piloting techniques for manned re-entry gliders"]}]}],"canonical_facts":{"dc:contributor.advisor":["Seckel, E."],"dc:contributor.department":["Aerospace and Mechanical Sciences"],"dc:creator":["Weiland, Robert F."],"dc:date.accessioned":["2012-08-29T23:35:34Z"],"dc:date.available":["2012-08-29T23:35:34Z"],"dc:date.issued":["1965-05-01"],"dc:description.abstract":["A fixed based simulator study of the approach and tangential landing of a class of manned re-entry gliders was conducted to determine the piloting techniques and vehicle parameters which best define the approach and landing problem. Tests were conducted on. 5 configurations typical of proposed vehicles with maximum lift to drag ratios of 3 to 5. The problem was Investigated from final approach to touchdown, In still and turbulent air, simulating longitudinal equations of motion only. A three phase landing consisting of a steady glide final approach, a nearly constant load factor flare maneuver, and a 15 to 20 second shallow angle, final glide was the preferred technique. The vehicle parameters found to be most Important were maximum lift to drag ratio and speed for minimum drag. A landing analysis based on fitted parabolic drag polars and a constant load factor flare was found to be valid for the vehicles tested."],"dc:identifier.uri":["https://hdl.handle.net/10945/13049"],"dc:publisher":["Princeton University"],"dc:rights":["This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States."],"dc:title":["A simulator study of the horizontal landing characteristics and piloting techniques for manned re-entry gliders"],"dc:type":["Thesis"]},"updated_at":"2026-07-27T20:25:53Z"}