IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0721833
(2010-03-11)
|
등록번호 |
US-8196858
(2012-06-12)
|
발명자
/ 주소 |
- Croom, Mark A.
- Smith, Stephen C.
- Gelhausen, Paul A.
- Guynn, Mark D.
- Hunter, Craig A.
- Paddock, David A.
- Riddick, Steven E.
- Teter, Jr., John E.
|
출원인 / 주소 |
- The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
10 |
초록
▼
An aircraft is configured for flight in an atmosphere having a low density. The aircraft includes a fuselage, a pair of wings, and a rear stabilizer. The pair of wings extends from the fuselage in opposition to one another. The rear stabilizer extends from the fuselage in spaced relationship to the
An aircraft is configured for flight in an atmosphere having a low density. The aircraft includes a fuselage, a pair of wings, and a rear stabilizer. The pair of wings extends from the fuselage in opposition to one another. The rear stabilizer extends from the fuselage in spaced relationship to the pair of wings. The fuselage, the wings, and the rear stabilizer each present an upper surface opposing a lower surface. The upper and lower surfaces have X, Y, and Z coordinates that are configured for flight in an atmosphere having low density.
대표청구항
▼
1. An aircraft configured for flight in an atmosphere having a low density, the aircraft comprising: a fuselage;a pair of wings extending from the fuselage in opposition to one another;a rear stabilizer extending from the fuselage in spaced relationship to the pair of wings;wherein each of the fusel
1. An aircraft configured for flight in an atmosphere having a low density, the aircraft comprising: a fuselage;a pair of wings extending from the fuselage in opposition to one another;a rear stabilizer extending from the fuselage in spaced relationship to the pair of wings;wherein each of the fuselage, the pair of wings, and the rear stabilizer present an upper surface opposing a lower surface;wherein the upper and lower surfaces are defined at an X position along an X-axis in a 3-dimensional X, Y, Z configuration; andwherein the upper and lower surfaces are defined at Y and Z positions along respective Y and Z axes, corresponding substantially to the following table: YZ1005.68117.261037.25437.341049.79117.671081.35438.411093.90118.261125.46438.831138.00119.031169.57438.601182.11119.961213.67437.721226.20121.011257.75436.191270.30122.111301.81434.011314.40123.201345.83431.191358.50124.301389.81427.741402.59125.481433.73423.671446.68126.771477.59419.011490.77128.221521.39413.761534.85129.871565.12407.931578.92131.741608.77401.561622.98133.881652.34394.681667.02136.331695.83387.341711.05139.131739.27379.661755.04142.311782.65371.681799.01145.911825.98363.421842.93149.981869.25354.841886.80154.561912.45345.90191.27 193.721930.61159.671955.57336.63195.79 236.571974.36165.311998.63327.042018.04171.452041.63317.212061.66178.052084.61307.282105.22185.012127.58297.332148.72192.282170.47287.02217.43 159.252192.19199.792213.16275.912235.63207.48223.69 270.302255.58263.802279.04215.292297.80251.032321.20224.19257.36 140.96260.67 294.21300.44 131.64300.83 312.40342.35 327.29344.24 126.543744.64668.043758.76679.043765.49654.103778.09682.593784.17650.653797.57685.213803.05648.553817.10687.463822.01647.303836.67689.383840.99646.64384.41 340.583856.25691.103859.99646.443875.86692.613878.99646.57388.22 123.633895.47694.003897.98647.013915.08695.323916.97647.733934.71696.473935.94648.723954.35697.513954.91649.853973.87651.123973.98698.573992.81652.633993.61699.654011.73654.364013.25700.764030.63656.294032.88701.894049.51658.394052.51703.044068.38660.634072.14704.204087.23662.994091.77705.374106.07665.474111.39706.534124.89668.044131.02707.694143.70670.714150.65708.864162.50673.484166.85699.984181.28676.324181.67687.054198.83681.034200.06679.254218.82682.24426.85 352.58432.29 121.80469.58 363.51476.39 120.56512.54 373.55520.48 119.50555.68 382.76564.59 118.60598.98 391.18608.69 117.90642.42398.84652.80 117.40685.98405.76696.91117.05729.65411.98741.02116.83773.41417.53785.13116.70817.25422.43829.24116.66861.15426.68873.35116.71905.12430.30917.46116.82949.13433.28961.57117.00993.17435.63. 2. An aircraft, as set forth in claim 1, wherein the X position corresponds substantially to 120.00. 3. An aircraft, as set forth in claim 2, wherein the upper and lower surfaces are defined at an X position along the X axis corresponding substantially to 240.00; and wherein the upper and lower surfaces are defined at Y and Z positions along the respective Y and Z axes, corresponding substantially to the following table: YZ1008.69127.061035.50427.371055.31127.701082.12428.341101.92128.521128.74428.601148.53129.521175.36428.161195.14130.671221.97427.011241.75131.901268.56425.161288.36133.131315.11422.621334.97134.311361.62419.401381.58135.491408.08415.511428.18136.761454.48410.961474.78138.171500.81405.741521.38139.781547.07399.921567.97141.551593.25393.541614.55143.521639.37386.671661.12145.731685.42379.371707.68148.241731.41371.731754.21151.101777.36363.821800.72154.391823.26355.651847.19158.141869.11347.171893.62162.361914.91338.471940.02166.931960.69329.651986.38171.862006.45320.692032.70177.222052.16311.532078.96181.862097.84302.182125.33176.992143.44292.472171.70172.122188.87281.992218.07 167.242229.98271.222264.44162.372274.71258.072310.80157.502319.28244.412348.36224.642357.32155.362394.98224.642403.94155.362441.61224.642450.53155.552487.43232.422494.11172.142533.33240.642537.23189.872579.49209.552579.59246.322617.72235.62375.12256.43375.38211.583785.74578.953812.53591.493818.72563.383844.17595.823850.44560.383875.93599.023882.31559.493907.76601.603914.19559.733939.60603.873946.06560.733971.45606.083977.89562.424003.30608.334009.70564.574035.15610.634041.47567.25404.71 291.984066.99612.964073.18570.54408.89180.024098.83615.304104.84574.314130.68617.664136.45578.444162.52620.024168.02582.894194.36622.414199.55587.614226.19624.814231.05592.574258.03627.254262.51597.734289.86629.734293.95603.024321.69632.264325.36608.454353.51634.854356.76614.014385.33637.504388.13619.684417.14640.234419.48625.46443.64317.504448.95643.044450.83631.304480.74645.954482.16637.194512.52649.004513.49643.11451.81162.044544.29652.244544.81649.044576.04655.48485.93337.08497.07150.97529.74353.01543.10143.56574.36 366.50589.41138.24619.51378.10635.87134.33665.05388.12682.41131.46710.86396.76728.98129.39756.89404.15775.58127.96803.09410.42822.20127.05849.42415.64868.82126.58895.85419.88915.44126.47942.36423.21962.07126.64988.91425.68. 4. An aircraft, as set forth in claim 1, wherein the upper and lower surfaces are defined at an X position along the X axis corresponding substantially to 360.00; and wherein the upper and lower surfaces are defined at Y and Z positions along the respective Y and Z axes, corresponding substantially to the following table: YZ1086.84190.931102.24349.391198.80193.201214.21348.271310.75195.911326.09343.421422.70198.871437.77335.261534.62202.551549.19324.111646.51207.091660.41311.041758.38212.211771.53297.171870.25217.191882.71283.671898.79281.751914.87279.801930.94277.821947.01275.811963.08273.771979.14271.691982.18220.411994.25220.571995.20269.582006.30220.732011.25267.452018.35220.892027.30265.292030.40221.062042.44221.232043.35263.112054.49221.412059.39260.892066.54221.592075.43258.652078.58221.782090.63221.972091.46256.382102.68222.162107.49254.082114.72222.362123.52251.742126.77222.572138.82222.792139.54249.352150.86223.012155.55246.932162.91223.252171.56244.472174.96223.492187.00223.732187.56 241.962199.05 223.962203.55 239.412211.10 224.172219.53 236.812223.14 224.352235.19 224.532235.51 234.152247.24 224.762251.48 231.442259.28 225.002267.43 228.682271.33 225.192283.38 225.343048.66 358.953081.81 392.983107.69 361.823136.06 416.993166.11 372.193191.42 438.323224.07 384.893247.35 458.103281.70 399.033303.68 476.743339.04 414.273360.32 494.403396.12 430.483417.24 511.153452.93 447.603474.42 526.973509.45 465.663531.88 541.763565.62 484.793589.64 555.293621.32 505.253647.80 567.023676.23 527.693706.54 575.163728.99 554.713826.84489.853832.12496.493840.92499.083847.10535.943847.74526.803848.05545.043849.86517.903849.91500.873850.83553.763853.66509.573855.48561.643857.12475.493858.96502.363861.71568.343869.10573.753877.22577.983885.81581.183886.67472.773894.67583.543903.68585.183912.79586.243916.34472.113921.94586.793931.11586.903940.27586.643946.02472.463949.42586.053958.54585.163967.64584.003975.68473.523976.70582.603985.72580.973994.70579.144003.64577.124005.32475.084012.54574.924017.44517.034021.40572.554023.21516.814025.68521.054030.21570.024032.35517.484033.84525.224034.93477.154038.98567.344041.49518.144041.93529.534045.14562.474046.03553.344046.92544.224047.81535.094050.64518.814059.78519.474064.51479.524068.92520.144078.07520.804087.21521.464094.05482.414096.36522.124105.50522.794114.64523.464123.54485.794123.79524.124132.93524.794142.07525.474151.22526.144152.98489.554160.36526.824169.50527.514178.64528.194182.39493.624187.79528.874196.93529.564206.07530.254211.75497.964215.21530.944224.35531.634233.49532.324241.07502.554242.64533.024251.78533.714260.92534.414270.06535.124270.36507.334279.20535.834288.34536.544297.48537.264299.63512.264306.62537.984315.76538.714324.90539.454328.88517.334334.03540.194343.17540.934352.31541.684358.11522.514361.44542.444370.58543.204379.72543.974387.31527.804388.85544.754397.99545.534407.12546.324416.25547.114416.50533.194425.39547.924434.52548.734443.65549.554445.68538.634452.78550.384461.91551.214471.04552.064474.85544.104480.17552.914489.29553.774498.42554.654504.02549.594507.54555.544516.66556.504525.78557.424533.18555.154534.90558.354544.02559.304553.13560.294562.25561.12559.57 250.22639.33 201.09658.26 300.04750.95 192.40767.61 323.90862.89 189.60878.62 338.46974.87 189.52990.30 346.44. 5. An aircraft, as set forth in claim 2, wherein the upper and lower surfaces are defined at an X position along the X axis corresponding substantially to 480.00; and wherein the upper and lower surfaces are defined at Y and Z positions along the respective Y and Z axes, corresponding substantially to the following table: YZ1077.08199.891082.96322.951206.22199.561212.07325.391335.36200.251341.18322.851464.49201.921470.13315.911593.60204.671598.83305.331722.69208.381727.32292.361851.78211.951855.65277.991980.88214.941983.77261.742109.98218.442111.60 243.442239.06 222.403867.94 400.763871.64 405.983878.13 408.223884.81 409.803891.56 411.113895.51 387.563898.33 412.243905.13 413.233911.94 414.103918.76 414.913922.87 385.003925.59 415.683932.42 416.383939.25 417.043946.09 417.663950.34 384.383952.94 418.253959.78 418.833966.63 419.393973.47 419.943977.82 384.813980.32 420.493987.17 421.033994.01 421.574000.86 422.104005.28 385.914007.71 422.624014.56 423.154021.41 423.674028.25 424.194032.72 387.494035.10 424.714041.95 425.224048.80 425.724055.65426.224060.13 389.444062.50426.724069.35427.214076.20427.704083.05428.194087.52391.734089.91428.684096.76429.174103.61429.664110.46430.154114.89394.284117.31430.644124.16431.144131.01431.634137.86432.134142.21397.274144.71432.634151.56433.144158.41433.644165.26434.154169.48400.664172.11434.664178.96435.174185.81435.694192.65436.204196.72404.354199.50436.714206.35437.234213.20437.744220.05438.264223.91408.314226.90438.784233.75439.294240.60439.814247.44440.334251.07412.534254.29440.854261.14441.384267.99441.904274.84442.434278.20416.944281.69442.964288.53443.494295.38444.034302.23444.574305.30421.504309.07445.114315.92445.664322.77446.204329.61446.764332.38426.194336.46447.314343.30447.874350.15448.434356.99449.004359.44431.004363.84449.574370.68450.144377.53450.724384.37451.304386.48435.924391.21451.894398.06452.484404.90453.074411.74453.674413.51440.914418.58454.274425.43454.874432.27455.484439.11456.104440.53445.934445.95456.734452.79457.364459.62457.994466.46458.634467.54450.994473.30459.274480.14459.924486.98460.574493.81461.234494.55456.084500.65461.904507.48462.634514.31463.314521.14464.014521.54461.254527.98464.714534.81465.434541.64466.174548.47466.77690.16 215.29699.61 273.01818.87 205.28825.87 299.61947.95 201.53954.09 314.78. 6. An aircraft, as set forth in claim 1, wherein the upper and lower surfaces are defined at an X position along the X axis corresponding substantially to 600.00; and wherein the upper and lower surfaces are defined at Y and Z positions along the respective Y and Z axes, corresponding substantially to the following table: YZ1002.53196.571008.08303.001124.05195.411129.33310.961245.58195.461250.83313.531367.11196.431372.33311.411488.62198.301493.70305.161610.12201.161614.84295.481731.59204.881735.78283.561853.07208.451856.59270.311974.56211.451977.18255.292096.04214.922097.53238.352217.51218.793909.04311.663912.74316.213918.68318.323924.80319.873930.99321.123933.90299.623937.21322.153943.46323.043949.72323.863955.99324.613959.06297.153962.26325.293968.54325.933974.83326.543981.11327.123984.33296.483987.40327.693993.69328.253999.97328.804006.26329.344009.62296.894012.55329.864018.84330.384025.13330.894031.43331.394034.88297.894037.72331.894044.01332.384050.31332.864056.60333.334060.12299.454062.89333.804069.19334.254075.49334.704081.78335.154085.34301.394088.08335.594094.37336.044100.67336.484106.97336.924110.53303.614113.26337.364119.56337.814125.86338.254132.15338.704135.70306.064138.45339.164144.74339.614151.04340.074157.33340.534160.84308.724163.63341.004169.92341.464176.22341.934182.51342.404185.95311.754188.81342.874195.10343.344201.40343.824207.69344.294211.02315.084213.98344.764220.28345.234226.57345.714232.87346.184236.05318.674239.16346.664245.46347.134251.75347.614258.04348.094261.04322.504264.34348.574270.63349.054276.92349.534283.22350.024286.01326.544289.51350.514295.80351.004302.10351.494308.39351.994310.95330.734314.68352.494320.97352.994327.26353.494333.56354.004335.86335.064339.85354.514346.14355.024352.43355.544358.72356.064360.76339.504365.01356.594371.30357.124377.59357.654383.88358.184385.64344.034390.17358.724396.46359.264402.74359.814409.03360.364410.51348.614415.32360.924421.61361.484427.89362.044434.18362.604435.37353.224440.47363.184446.75363.764453.04364.354459.32364.954460.22357.884465.60365.544471.89366.144478.17366.744484.45367.344485.07362.584490.73 367.964497.02368.594503.29369.254509.57369.894509.91367.324515.85370.544522.13371.194528.40371.884534.68372.41759.89 208.82768.68 263.12881.04 199.75887.44 288.44. 7. An aircraft, as set forth in claim 1, wherein the upper and lower surfaces are defined at an X position along the X axis corresponding substantially to 720.00; and wherein the upper and lower surfaces are defined at Y and Z positions along the respective Y and Z axes, corresponding substantially to the following table: YZ1057.50189.571062.37288.341173.27190.721177.84296.681289.03192.651293.56299.841404.79194.981409.32298.431520.53197.721524.98293.141636.26200.951640.44284.671751.98204.551755.73274.071867.72207.661870.89262.151983.47209.901985.86248.542099.23212.162100.61233.122214.98214.623950.14222.573953.72226.603959.07228.713964.63230.203970.28231.293972.28211.683975.97232.223981.66233.043987.38233.763993.09234.433995.23209.253998.82235.054004.54235.654010.27236.234016.00236.804018.31208.504021.73237.354027.46237.884033.20238.384038.93238.884041.41208.724044.67239.374050.41239.844056.14240.314061.88240.754064.48209.634067.63241.194073.37241.614079.11242.024084.85242.434087.54210.974090.59242.834096.34243.224102.08243.624107.82244.014110.56212.814113.57244.414119.31244.804125.05245.204130.80245.614133.55214.984136.54246.014142.28246.424148.03246.834153.77247.244156.52217.394159.51247.664165.25248.084170.99248.514176.73248.934179.47219.984182.47249.364188.22249.794193.96250.224199.70250.654202.40222.744205.44251.084211.18251.514216.92251.944222.66252.374225.30225.754228.40252.804234.14253.234239.88253.674245.62254.104248.16229.014251.36254.534257.10254.974262.84255.404268.59255.844270.99232.474274.33256.284280.07256.724285.81257.164291.55257.614293.80236.144297.29258.054303.02258.504308.76258.954314.50259.404316.57239.964320.24259.864325.98260.314331.72260.774337.46261.244339.32243.924343.20261.704348.93262.174354.67262.644360.41263.124362.06247.984366.15263.604371.88264.084377.62264.564383.36265.054384.78252.114389.09265.544394.83266.044400.56266.544406.30267.044407.50256.294412.03267.554417.77268.064423.50268.574429.23269.094430.20260.504434.97269.614440.70270.144446.43270.674452.16271.224452.90264.774457.89271.774463.62272.334469.35272.894475.08273.454475.59269.094480.81274.014486.54274.584492.27275.164497.99275.774498.28273.394503.72276.364509.45276.964515.17277.584520.90278.06826.19 197.36834.61 248.63941.73 190.57947.55 273.66. 8. An aircraft, as set forth in claim 1, wherein the upper and lower surfaces are defined at an X position along the X axis corresponding substantially to 840.00; and wherein the upper and lower surfaces are defined at Y and Z positions along the respective Y and Z axes, corresponding substantially to the following table: YZ1002.27180.871007.37258.371112.55182.291116.63273.281222.79186.011226.56282.081333.01190.031336.78285.901443.24193.861447.07285.241553.47197.561557.28280.961663.71201.201667.34273.741773.95204.661777.24264.501884.22207.251887.03253.941994.50208.611996.65241.752104.80209.512106.07227.882215.09210.384086.08149.584090.29149.874094.50150.164098.71150.454102.93150.744107.14151.024111.35151.304115.57151.594119.78151.874123.99152.154128.21152.444132.42152.734136.63153.024140.84153.314141.74124.324145.06153.614149.27153.904153.48154.204157.10125.804157.69154.504161.91154.814166.12155.124170.33155.424172.44127.464174.54155.734178.75156.054182.96156.364187.17156.674187.76129.274191.38156.994195.59157.304199.81157.624203.07131.184204.02157.934208.23158.254212.44158.574216.65158.884218.37133.204220.86159.204225.07159.514229.28159.834233.49160.144233.66135.304237.70160.464241.91160.784246.13161.094248.93137.504250.34161.414254.55161.734258.76162.054262.97162.364264.19139.784267.18162.684271.39163.004275.60163.334279.44142.154279.81163.654284.02163.974288.23164.294292.44164.624294.67144.594296.65164.944300.86165.274305.07165.604309.28165.924309.90147.114313.49166.254317.70166.594321.91166.924325.11149.694326.12167.254330.33167.594334.54167.924338.75168.264340.31152.344342.96168.604347.17168.944351.38169.294355.50155.034355.58169.634359.79169.984364.00170.334368.21170.684370.69157.764372.42171.034376.62171.394380.83171.744385.04172.104385.87160.524389.25172.464393.45172.834397.66173.194401.05163.314401.87173.564406.07173.934410.28174.304414.49174.674416.22166.134418.69175.054422.90175.434427.10175.814431.31176.194431.38168.994435.51176.584439.72176.974443.92177.364446.54171.874448.13177.764452.33178.164456.53178.584460.73179.004461.70174.744464.94179.434469.14179.854473.34180.274476.87177.584477.54180.694481.74181.124485.94181.554490.14182.004492.02180.514494.34182.454498.54182.904502.74183.354507.11183.71892.09185.17900.01 233.46. 9. An aircraft, as set forth in claim 1, wherein the upper and lower surfaces are defined at an X position along the X axis corresponding substantially to 960.00; and wherein the upper and lower surfaces are defined at Y and Z positions along the respective Y and Z axes, corresponding substantially to the following table: YZ1010.85170.951015.43232.321037.07170.841041.03237.971063.28171.161066.76242.991089.49171.721092.59247.471115.69172.601118.50251.451141.88173.691144.47255.001168.07175.001170.49258.181194.24176.481196.56260.991220.41178.071222.65263.471246.57179.691248.78265.621272.74181.301274.93267.461298.91182.891301.10269.011325.07184.451327.29270.281351.25185.951353.48271.261377.42187.411379.69271.961403.60188.821405.90272.371429.78190.181432.11272.521455.96191.491458.33272.391482.15192.761484.54272.061508.33193.981510.75271.531534.52195.171536.96270.801560.71196.311563.16269.881586.90197.421589.35268.791613.10198.491615.53267.531639.29199.521641.71266.101665.49200.511667.88264.521691.69201.471694.04262.831717.88202.391720.19261.021744.09203.251746.34259.091770.29204.061772.47257.091796.49204.791798.60254.961822.70205.451824.72252.751848.91206.021850.84250.491875.12206.491876.95248.171901.33206.841903.06245.751927.55207.081929.15243.221953.76207.251955.23240.581979.98207.321981.30237.832006.19207.322007.37234.992032.41207.262033.42232.082058.62207.162059.46229.082084.84207.032085.49225.952111.05206.872111.50222.652137.27206.752137.48219.152163.42215.402163.48206.592189.32211.372189.70206.372215.18206.84919.81192.98932.43 175.87940.67 208.36958.47172.92964.97218.14984.65171.58990.03 225.84. 10. An aircraft, as set forth in claim 1, wherein the upper and lower surfaces are defined at an X position along the X axis corresponding substantially to 1680.00; and wherein the upper and lower surfaces are defined at Y and Z positions along the respective Y and Z axes, corresponding substantially to the following table: YZ1174.69159.391186.20146.971191.00172.351207.26145.971210.23180.991228.35146.211230.12187.991249.42147.011250.34194.001270.48148.211270.74199.361291.27204.161291.52149.711311.92208.501312.54151.441332.64212.421333.53153.481353.43215.981354.50155.731374.27219.231375.45158.201395.15222.161396.38160.851416.08224.821417.29163.561437.03227.211438.21166.271458.01229.361459.13168.921479.02231.271480.07171.501500.05232.931501.01174.011521.09234.371521.96176.421542.15235.551542.93178.731563.22236.471563.90180.951584.30237.161584.88183.081605.39237.591605.88185.101626.47237.901626.88187.041647.57238.061647.89188.891668.66238.071668.91190.661689.75237.941689.93192.341710.84237.701710.96193.941731.93237.331732.00195.461753.01236.841753.04196.881774.09198.221774.10236.241795.15199.471795.18235.551816.21200.641816.25234.751837.27201.691837.33233.861858.34202.681858.40232.961879.42203.551879.46231.891900.49204.311900.52230.751921.58204.931921.58229.561942.64228.311942.66205.401963.69226.981963.75205.741984.73225.551984.84205.932005.77 224.042005.93 206.002026.80 222.452027.02 205.962047.83 220.812048.12 205.782068.85 219.122069.20 205.472089.87 217.352090.29 205.062110.87 215.452111.38204.542131.86 213.372132.46 203.932152.83 211.062153.54 203.312173.76 208.472174.62 202.612194.64205.542195.70 201.792215.47 202.22. 11. An aircraft, as set forth in claim 1, wherein the upper and lower surfaces are defined at an X position along the X axis corresponding substantially to 2280.00; and wherein the upper and lower surfaces are defined at Y and Z positions along the respective Y and Z axes, corresponding substantially to the following table: YZ1312.16158.261322.08147.421326.23169.651340.37146.641342.83177.361358.69146.951360.03183.681376.99147.741377.51189.131395.16194.031395.27148.861412.94198.441413.54150.241430.81202.451431.79151.801448.76206.111450.02153.581466.77209.451468.23155.541484.83212.521486.43157.641502.94215.321504.61159.871521.07217.881522.79162.131539.24220.211540.97164.391557.44222.321559.15166.621575.66224.231577.34168.811593.90225.931595.53170.961612.15227.431613.73173.061630.43228.711631.93175.121648.71229.761650.14177.121667.01230.621668.35179.071685.32231.241686.57180.971703.63231.761704.79182.831721.94232.151723.02184.631740.26232.421741.26186.401758.58232.571759.49188.121776.89232.601777.73189.801795.21232.541795.98191.431813.53232.371814.23193.011831.85232.101832.48194.551850.16231.751850.74196.041868.47231.321869.00197.491886.78230.801887.26198.891905.09230.271905.53200.241923.40229.591923.81201.531941.70228.861942.08202.721960.01228.081960.37203.781978.30227.251978.67204.701996.60226.341996.97205.502014.89225.362015.27 206.182033.18 224.302033.58 206.762051.46 223.172051.89 207.232069.74 222.002070.21 207.582088.02 220.782088.52 207.822106.29 219.502106.84 207.962124.56 218.112125.16 208.002142.81 216.562143.48 207.952161.05 214.812161.80 207.842179.25 212.802180.11 207.582197.43 210.512198.43 207.212215.56 207.88. 12. An aircraft, as set forth in claim 1, wherein the upper and lower surfaces are defined at an X position along the X axis corresponding substantially to 3120.00; and wherein the upper and lower surfaces are defined at Y and Z positions along the respective Y and Z axes, corresponding substantially to the following table: YZ2068.1386.962068.7885.272070.9587.902071.7084.732073.8588.542074.6784.582076.7989.062077.6484.552079.7389.502080.6284.572082.6889.892083.5984.612085.6490.232086.5784.672088.6090.532089.5484.742091.5690.802092.5284.822094.5391.052095.4984.912097.5091.272098.4785.002100.4791.472101.4485.092103.4491.652104.4285.182106.4191.812107.3985.282109.3891.962110.3785.372112.3592.092113.3485.472115.3392.202116.3185.562118.3092.302119.2985.662121.2892.382122.2685.752124.2592.452125.2485.842127.2392.512128.2185.942130.2192.552131.1986.022133.1892.582134.1686.112136.1692.602137.1386.202139.1492.602140.1186.282142.1192.602143.0886.362145.0992.582146.0686.432148.0692.552149.0386.512151.0492.512152.0186.572154.0292.462154.9886.642156.9992.402157.9686.702159.9792.332160.9386.762162.9492.252163.9186.812165.9292.162166.8886.862168.8992.052169.8686.902171.8791.942172.8386.952174.8491.822175.8186.992177.8191.692178.7987.042180.7991.542181.7687.102183.7691.382184.7487.162186.7391.202187.7187.222189.7091.022190.6987.292192.6790.822193.6687.362195.6490.612196.6487.442198.6090.392199.6187.532201.5790.152202.5987.622204.5489.902205.5687.722207.5089.652208.5487.822210.4689.382211.5187.932213.4389.092214.48 88.04. 13. An aircraft, as set forth in claim 1, wherein at least one stabilizer bar operatively interconnects the fuselage and the rear stabilizer at an angle substantially equal to 16.4 degrees, relative to a plane proximate a bottom of the fuselage. 14. An aircraft, as set forth in claim 13, wherein the at least one stabilizer bar includes a stabilizer hinge such that the rear stabilizer is foldable about the hinge, relative to the fuselage. 15. An aircraft, as set forth in claim 14, wherein each of the wings includes a wing hinge such that each of the wings are foldable about the respective wing hinge, relative to the fuselage. 16. An aircraft, as set forth in claim 15, wherein each of the wing hinges extends along a hinge axis substantially equal to 23.5 degrees, relative to a centerline of the fuselage. 17. An aircraft, as set forth in claim 1, wherein each of the wings and the rear stabilizer are foldable relative to the fuselage to a foldable position. 18. An aircraft configured for flight in an atmosphere having low density, the aircraft comprising: a fuselage;a pair of wings extending from the fuselage in opposition to one another;a rear stabilizer extending from the fuselage in spaced relationship to the pair of wings;a stabilizer bar operatively interconnecting the rear stabilizer and the fuselage;wherein each of the fuselage, the pair of wings, and the rear stabilizer present an upper surface opposing a lower surface;wherein the upper and lower surfaces are defined at an X position along an X axis, in a 3-dimensional X, Y, Z configuration; andwherein the upper and lower surfaces are defined at Y and Z positions along a respective Y and Z axis, corresponding substantially to the following table: YZ1005.68117.261037.25437.341049.79117.671081.35438.411093.90118.261125.46438.831138.00119.031169.57438.601182.11119.961213.67437.721226.20121.011257.75436.191270.30122.111301.81434.011314.40123.201345.83431.191358.50124.301389.81427.741402.59125.481433.73423.671446.68126.771477.59419.011490.77128.221521.39413.761534.85129.871565.12407.931578.92131.741608.77401.561622.98133.881652.34394.681667.02136.331695.83387.341711.05139.131739.27379.661755.04142.311782.65371.681799.01145.911825.98363.421842.93149.981869.25354.841886.80154.561912.45345.90191.27193.721930.61159.671955.57336.63195.79236.571974.36165.311998.63327.042018.04171.452041.63317.212061.66178.052084.61307.282105.22185.012127.58297.332148.72192.282170.47287.02217.43159.252192.19199.792213.16275.912235.63207.48223.69 270.302255.58263.802279.04215.292297.80251.032321.20224.19257.36140.96260.67294.21300.44131.64300.83312.40342.35327.29344.24126.543744.64668.043758.76679.043765.49654.103778.09682.593784.17650.653797.57685.213803.05648.553817.10687.463822.01647.303836.67689.383840.99646.64384.41340.583856.25691.103859.99646.443875.86692.613878.99646.57388.22123.633895.47694.003897.98647.013915.08695.323916.97647.733934.71696.473935.94648.723954.35697.513954.91649.853973.87651.123973.98698.573992.81652.633993.61699.654011.73654.364013.25700.764030.63656.294032.88701.894049.51658.394052.51703.044068.38660.634072.14704.204087.23662.994091.77705.374106.07665.474111.39706.534124.89668.044131.02707.694143.70670.714150.65708.864162.50673.484166.85699.984181.28676.324181.67687.054198.83681.034200.06679.254218.82682.24426.85 352.58432.29 121.80469.58 363.51476.39 120.56512.54 373.55520.48119.50555.68 382.76564.59 118.60598.98 391.18608.69 117.90642.42 398.84652.80 117.40685.98 405.76696.91 117.05729.65 411.98741.02 116.83773.41 417.53785.13 116.70817.25422.43829.24116.66861.15426.68873.35116.71905.12430.30917.46116.82949.13433.28961.57117.00993.17 435.63. 19. An aircraft configured for moving from a folded position to an unfolded position for flight in an atmosphere having low density, the aircraft comprising: a fuselage;a pair of wings extending from the fuselage in opposition to one another;a rear stabilizer extending from the fuselage in spaced relationship to the pair of wings;wherein each of the pair of wings and the rear stabilizer is foldable relative to the fuselage along a respective fold line;wherein each of the fuselage, the pair of wings, and the rear stabilizer present an upper surface opposing a lower surface;wherein the upper and lower surfaces are defined at an X position along an X axis, in a 3-dimensional X, Y, Z configuration; andwherein the upper and lower surfaces are defined at Y and Z positions along a respective Y and Z axis, corresponding substantially to the following table: YZ1005.68117.261037.25437.341049.79117.671081.35438.411093.90118.261125.46438.831138.00119.031169.57438.601182.11119.961213.67437.721226.20121.011257.75436.191270.30122.111301.81434.011314.40123.201345.83431.191358.50124.301389.81427.741402.59125.481433.73423.671446.68126.771477.59419.011490.77128.221521.39413.761534.85129.871565.12407.931578.92131.741608.77401.561622.98133.881652.34394.681667.02136.331695.83387.341711.05139.131739.27379.661755.04142.311782.65371.681799.01145.911825.98363.421842.93149.981869.25354.841886.80154.561912.45345.90191.27193.721930.61159.671955.57336.63195.79 236.571974.36165.311998.63327.042018.04171.452041.63317.212061.66178.052084.61307.282105.22185.012127.58297.332148.72192.282170.47287.02217.43159.252192.19199.792213.16275.912235.63207.48223.69270.302255.58263.802279.04215.292297.80251.032321.20224.19257.36140.96260.67294.21300.44131.64300.83312.40342.35327.29344.24126.543744.64668.043758.76679.043765.49654.103778.09682.593784.17650.653797.57685.213803.05648.553817.10687.463822.01647.303836.67689.383840.99646.64384.41 340.583856.25691.103859.99646.443875.86692.613878.99646.57388.22123.633895.47 694.003897.98 647.013915.08 695.323916.97 647.733934.71 696.473935.94 648.723954.35 697.513954.91 649.853973.87 651.123973.98 698.573992.81 652.633993.61 699.654011.73 654.364013.25 700.764030.63 656.294032.88 701.894049.51 658.394052.51 703.044068.38 660.634072.14 704.204087.23 662.994091.77 705.374106.07 665.474111.39 706.534124.89 668.044131.02 707.694143.70 670.714150.65 708.864162.50 673.484166.85 699.984181.28 676.324181.67 687.054198.83 681.034200.06 679.254218.82 682.24426.85352.58432.29121.80469.58363.51476.39120.56512.54373.55520.48119.50555.68382.76564.59118.60598.98391.18608.69117.90642.42398.84652.80117.40685.98405.76696.91117.05729.65411.98741.02116.83773.41417.53785.13116.70817.25422.43829.24116.66861.15426.68873.35116.71905.12430.30917.46116.82949.13433.28961.57117.00993.17 435.63.
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