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- W1638364423 abstract "A comparison of the approximate motion and heating of transatmospheric vehicles is presented for horizontal (lifting) and vertical (nonlifting) launch into low Earth orbit (about 218 km or 135 mi). The method of analysis is based on Chapman's Z-function transformation of the equations of motion with the assumption of an exponential atmosphere. These equations have been modified to include the effects of thrusting with mass loss. The modified transformed equations yield various analytic solutions including that for ascending lifting flight at constant drag-toweight ratio and that for ascending nonlifting flight while making a gravity turn. From these solutions estimates may be obtained of the payload capability (as fraction of launch weight) and of the relative aerodynamic heating loads to be encountered. Such estimates are presented for idealized single-stage-toorbit vehicles using typical values of specific impulse of thrust for air-breathing and rocket engines with JPIhydrocarbon and hydrogen fuel, respectively. In general, it is found that there is little advantage in payload capability of horizontal launch over vertical launch when JPIhydrocarbon fuel is used for the airbreathing-propulsion phase of lifting ascent (up to a Mach number of about 7.5). If liquid hydrogen is used instead of hydrocarbon fuel, there is only a small increase in payload fraction (about 13 percent). While aerodynamic heating is greater in the case of horizontal launch, it can be reduced to tolerable levels through use of steeper ascent flight paths in the upper atmosphere. *Member AIAA Formerly with NASA Ames Research Center, Moffett Field, California 94035 Nomenclature reference area speed of sound drag coefficient lift coefficient drag force acceleration of gravity atmosphere scale height altitude specific impulse of thrust lift force Mach number mass of vehicle total laminar convective heat absorbed per unit area laminar convective heating rate per unit area universal gas constant Reynolds number distance from center of Earth horizontal distance thrust force, also absolute temperature time circular orbital velocity, ,&i vehicle velocity dimensionless velocity ratio, V/uc weight of vehicle, mg dimensionless function of angle of attack atmosphere density-decay parameter flight-path angle, also ratio of specific heats for air operator denoting increment in quantity atmosphere density thrust angle relative to flight path Subscripts a value at apogee e value at atmosphere exit o value at sea level 1 value when V = 0.01 2 value when = 0.3 3 value when = Ve 4 value when = va Released to AIAA to publish in all forms." @default.
- W1638364423 created "2016-06-24" @default.
- W1638364423 creator A5091615411 @default.
- W1638364423 date "1987-08-17" @default.
- W1638364423 modified "2023-09-26" @default.
- W1638364423 title "Comparison of horizontal and vertical launch into orbit" @default.
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- W1638364423 doi "https://doi.org/10.2514/6.1987-2569" @default.
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