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  • 1
    Publication Date: 2011-08-19
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 25; 19-23
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  • 2
    Publication Date: 2011-08-19
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 198-204
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  • 3
    Publication Date: 2019-06-28
    Description: The landing footprint of a conceptual high-lift transatmospheric vehicle is defined for aeromaneuvering entry from a typical low-earth orbit. The flight strategy for trajectory construction to maximize the landing area by extending downrange and crossrange as far as possible is developed in four phases by optimal programming of the vehicle's roll angle. Trajectories that reach any given landing site were calculated with the corresponding heating rates at three critical vehicle locations (stagnation point, wing leading edge, and body centerline). An optimization methodology was developed that demonstrates the trades between crossrange, peak heating and total heat loads as a function of three key flight parameters (altitude, flight-path angle, and vehicle roll angle). The maximum extent of the landing footprint was found to be 29,690 km downrange and 6560 km crossrange. Large variations in the ballistic coefficient had negligible effect on the extent of the footprint but could significantly affect heating. However, the footprint's longitude was displaced downstream or upstream with increasing or decreasing ballistic coefficient, respectively.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 88-0300
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  • 4
    Publication Date: 2019-06-28
    Description: The low-earth orbit rendezvous capability of a conceptual transatmospheric vehicle is analyzed for two endo-/exo-atmospheric ascent missions. Both cases involve coasting aerodynamic maneuvers starting from the burn-out conditions corresponding to air-breathing propulsion systems that achieve orbital velocity within the atmosphere. The powered phase of the ascent trajectories approximate constant dynamic pressure, fuel-efficient flightpaths typically flown by supersonic aircraft. The aeromaneuvering coast phases of the ascent include both coplanar (to determine altitude capability without plane-inclination changes) and aeroturning to LEO rendezvous at 400 km altitude (to assess plane-change capability). The coast-phase ascent maneuvers are correlated with G-load requirements and aerothermodynamic heating characteristics at two critical locations on the vehicle surface (i.e., the nose stagnation point and the body centerline). The results are correlated and recommendations are made concerning thermal protection and structural requirements.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 87-0513
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