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W OLTORIA DI UN USUO NON20180134382A1 MAN AT TAMAN ANTONIOLA D ( 19) United States (12 ) Patent Application Publication ( 10) Pub . No. : US 2018 /0134382 A1 Scholl et al. (43 ) Pub . Date : May 17 , 2018 ( 54 ) COMMERCIAL SUPERSONIC AIRCRAFT Publication Classification AND ASSOCIATED SYSTEMS AND (51 ) Int. Cl. METHODS B64C 30 / 00 (2006 .01 ) B64D 13 /08 ( 2006 . 01) ( 71) Applicant: Boom Technology, Inc. , Englewood , B64D 43 / 00 (2006 . 01 ) CO (US ) B64D 11 /06 ( 2006 .01 ) (72 ) Inventors : Nathaniel Blake Scholl, Englewood , (52 ) U . S . CI. CO (US ) ; Joe Wilding, Englewood , CO CPC . .. .. B64C 30 / 00 ( 2013 .01 ) ; B64D 13 / 08 (US ) ; Josh Krall, Englewood , CO (2013 .01 ) ; B64D 2013 /0618 (2013 .01 ) ; B64D (US ) ; Andy Berryann , Englewood , CO 11 / 064 (2014 . 12 ); B64D 43 / 00 ( 2013 .01 ) (US ) ; Michael Reid , Englewood , CO (US ) (57 ) ABSTRACT Commercial supersonic aircraft and associated systems and ( 21 ) Appl. No. : 15 /811 ,327 methods . A representative commercial supersonic aircraft includes a fuselage configured to carry a crew and between ( 22 ) Filed : Nov . 13 , 2017 20 and 60 passengers, a delta wing mounted to the fuselage , and a propulsion system carried by at least one of the wing Related U . S . Application Data and the fuselage , the propulsion system including a plurality (60 ) Provisional application No . 62 /421 , 870 , filed on Nov . of engines , at least one variable - geometry inlet , and at least 14 , 2016 . one variable - geometry nozzle . 101 103 100 102 51216 Chen 110 - - - - 000000 - - 161 - 00000000000- - - - 120 121a oooololo0000 131 0 162 124 151 160 Patent Application Publication May 17 , 2018 Sheet 1 of 12 US 2018 / 0134382 A1 162 100 104 www 124 a 160 110 Fig.1 150 151124 mewa 103 71317131 000000ogooo00000000000 newrew waswasn manw 101 - Do wok 121a 102102-TUE1276 sw 120 Patent Application Publication May 17 , 2018 Sheet 2 of 12 US 2018 / 0134382 A1 4 181 170 TITTI Fig.2 130 131 132 Patent Application Publication May 17 , 2018 Sheet 3 of 12 US 2018 /0134382 A1 -141 hitam 140 1356 Fig.3 135 LL 132 137X 138 135a6 -136 Patent Application Publication May 17 , 2018 Sheet 4 of 12 US 2018 /0134382 A1 134 179 176177 V 174 174 173 wwwwwwwww 1726 182TAKAR Fig.4 175 EEEEEEEEEEE wwwwwwwww TIet Patent Application Publication May 17 , 2018 Sheet 5 of 12 US 2018 /0134382 A1 DEGL wwwwwwwwwwwwwwwww GL GL 9992 NAME 9814 qEGILGLTCL189L LCGL 69L -99L wwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwe 94 tas ad OSL Patent Application Publication May 17 , 2018 Sheet 6 of 12 US 2018 /0134382 A1 150- 148 -154 23870 Fig.6 = 149 Patent Application Publication May 17 , 2018 Sheet 7 of 12 US 2018 / 0134382 A1 181 170 195a 7194 1197 180 198 122-17 19501950ee 1950- 121a 189 ??? -oche ?? wwwww ? 123 ? 189 Fig.7 L 1950-71950 64 189152 1216121b ? 1930 ?????? a as u wwwm 1956195e AAAAA 193b 189 44 191192 .199 152 187187 191 2 150 1938- 188 190190 193b Patent Application Publication May 17 , 2018 Sheet 8 of 12 US 2018 / 0134382 A1 156 --1635 166C 67 A 00 Fig.8 L 000 00 1000 PRIMAMMMMMMMMMMMMMMM 164 166b l 163a 166a 1567463a7 156 160 Patent Application Publication May 17 , 2018 Sheet 9 of 12 US 2018 / 0134382 A1 900 START RECEIVE PROPOSED START POINT 902 AND END POINT ITIA - 904 w RECEIVE INITIALIRL ROUTING ??????????????? RECEIVE WIND SPEED DATA AS - 906 WWWWWWWWW w FUNCTION OF TIME, ALTITUDE RECEIVE SPEED /NOISE BASED 1908 FLIGHT RESTRICTIONS 910 RECEIVE SPEED / FUEL USAGE DATA - 912 ADJUST/ DEVELOP PROPOSED RATING OUTPUT DATA TO MINIMIZEVIIVIIVIAN FLIGHT TIME WWWWWWWWWWWWWWWWWWWW - 914 913 NO < FLIGHT COMPLETE ? YES END Fig. 9 Patent Application Publication May 17, 2018 Sheet 10 of 12 US 2018 /0134382 A1 999 1070C-1070a-1 wyobootporu 1070a 1000 -10706 4020 S 22 1031 ameza 1031 wenn 10701-A4Let SANASSSSSSSSSSSSSS KEY WOOD w 10321031 Fig.10D 10201020 103110201024 Fig.10B k 1024 10101010 10041001 70c 2000 10001000 1070a 10101010 1031 10321032 -1020 1031 1030 10706410311032 -1001 1032 1032 Fig.10A Fig.10C 10241024 1032 ALLT1031 1010 1010 1000 1031 1000 Patent Application Publication May 17, 2018 Sheet 11 of 12 US 2018 /0134382 A1 1 * ** w * *** 1 1 wwww 1132 w 3 1 * * wie ** TO * wennm an * we or 1170a1 7 - - me waar * m . POLLL1 2 11706AA Fig. 11 Patent Application Publication May 17, 2018 Sheet 12 of 12 US 2018 /0134382 A1 1241 1231 1240 1242 Fig.12 * 1237 1235a 1236 12321232 US 2018 /0134382 A1 May 17 , 2018 COMMERCIAL SUPERSONIC AIRCRAFT [ 0014 ] FIG . 11 is a partially schematic illustration of a AND ASSOCIATED SYSTEMS AND supersonic inlet system configured in accordance with METHODS another embodiment of the present technology . [0015 ] FIG . 12 is a partially schematic , cut -away isometric CROSS -REFERENCE TO RELATED view of an inlet having a three -dimensional geometry in APPLICATION accordance with an embodiment of the present technology . [0001 ] The present application claims priority to pending U . S . Provisional Application 62 /421 ,870 , filed Nov . 14 , DETAILED DESCRIPTION 2016 and incorporated herein by reference . 1 . 0 Overview TECHNICAL FIELD [0016 ] The present technology is generally directed to commercial supersonic aircraft, and associated systems and [0002 ] The present technology is directed generally to methods . In particular embodiments , the supersonic aircraft commercial supersonic aircraft, and associated systems and is configured to carry from 40 -60 , or from 45 -55 passengers methods. ( a smaller number of passengers than did the Concorde ) on transoceanic routes and /or overland routes . The size of the BACKGROUND aircraft, alone or in combination with technological [ 0003] Supersonic aircraft have been used primarily for improvements in one or more of several areas described military missions since the mid - 1900s . Then , in the 1970s , further below , are expected to provide a high speed option the United States and Europe each developed commercial for commercial passengers , at a ticket price that is competi supersonic aircraft : the supersonic transport, or “ SST ” in the tive with current and future business class ticket prices, even United States, and the Concorde in Europe. The Concorde if fuel prices fluctuate . went on to fly commercial passengers on transatlantic routes [0017 ] Specific details of several embodiments of the through the 1990s. The fleet was permanently retired in technology are described below with reference to selected 2003 , following a temporary grounding in 2000 resulting configurations to provide a thorough understanding of these from an accident. Despite the fact that the Concorde flew embodiments , with the understanding that the technology commercial passengers for several decades , it was not may be practiced in the context of other embodiments . generally considered a commercially successful program Several details describing structures or processes that are because high operating costs did not make it broadly viable . well -known and often associated with other types of super Accordingly , and in light of the Concorde’ s retirement, there sonic aircraft and / or associated systems and components , remains a need in the industry for a viable and profitable but that may unnecessarily obscure some of the significant supersonic commercial aircraft . aspects of the present disclosure , are not set forth in the following description for purposes of clarity. Moreover , BRIEF DESCRIPTION OF THE DRAWINGS although the following disclosure sets forth several embodi ments of different aspects of the technology , several other [0004 ] FIG . 1 is a partially schematic , isometric illustra embodiments of the technology can have configurations tion of a commercial supersonic aircraft configured in accor and/ or components that differ from those described in this dance with embodiments of the present technology . section . As such , the technology may have other embodi [0005 ] FIG . 2 is a partially schematic , cross -sectional ments with additional elements and / or without several of the illustration of a propulsion system suitable for use with the elements described below with reference to FIGS. 1 - 12 . supersonic commercial aircraft shown in FIG . 1 . [0018 ] Several embodiments of the technology described [0006 ] FIG . 3 is a partially schematic , cross -sectional below may take the form of computer - or controller -execut illustration of an inlet portion of the propulsion system able instructions, including routines executed by a program shown in FIG . 2 . mable computer or controller . Those skilled in the relevant [0007 ] FIG . 4 is a partially schematic , cross - sectional art will appreciate that the technology can be practiced on illustration of the engine and nozzle portion of the propul computer or controller systems other than those shown and sion system shown in FIG . 2 . described below . The technology can be embodied in a [0008 ] FIG . 5 is a partially schematic illustration of a special- purpose computer or data processor that is specifi portion of a supersonic aircraft cabin , configured in accor cally programmed , configured or constructed to perform one dance with an embodiment of the present technology. or more of the computer - executable instructions described 10009 ]. FIG . 6 is a partially schematic , enlarged isometric below . Accordingly , the terms " computer” and “ controller " view of a portion of the cabin shown in FIG . 5 . as generally used herein refer to any suitable data processor [ 0010 ] FIG . 7 is a partially schematic illustration of a and can include , depending upon the task , palm -top com cabin air system configured

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