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  • 1
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    Earth aerobraking strategies for manned return from Mars (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: ASTRODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 3, Ma; 297-304
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    NASA TECHNICAL REPORTS
  • 2
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    An Investigation of Aerogravity Assist at Titan and Triton for Capture into Orbit About Saturn and Neptune (2005)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: Previous work by our group has shown that an aerogravity assist maneuver at the moon Titan could be used to capture a spacecraft into a closed orbit about Saturn if a nominal atmospheric profile at Titan is assumed. The present study extends that work and examines the impact of atmospheric dispersions, variations in the final target orbit and low density aerodynamics on the aerocapture maneuver. Accounting for atmospheric dispersions substantially reduces the entry corridor width for a blunt configuration with a lift-to-drag ratio of 0.25. Moreover, the choice of the outbound hyperbolic excess speed (with respect to Titan) strongly influences the corridor width. Given the influence of these two parameters, certain mission scenarios may be feasible using a blunt aeroshell, while other mission designs would likely require a biconic vehicle with a higher lift-to-drag ratio. Preliminary simulations indicate that the same technique may be feasible for capture into orbit about Neptune using the tenuous atmosphere of Triton.
    Keywords: Space Sciences (General)
    Type: 2nd International Planetary Probe Workshop; 49-57; NASA/CP-2004-213456
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  • 3
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    Earth aerobraking strategies for manned return from Mars (1991)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The atmospheric flight environment of manned return from Mars is evaluated by analyzing the earth-return entry corridor. To identify and quantify the effects of various atmospheric exit conditions on the mission, the differences beween the capture to a specific orbit and the direct entry to a target splashdown site are investigated. The differences are quantified in terms of the airbrake lift-drag ratio requirements, the stagnation-point heating, and the significance of off-nominal atmospheric conditions. Results are presented on three different earth-return aerobraking scenarios: (1) the capture into a phasing orbit with a 24-hr period, (2) the capture into a 500-km circular orbit, and (3) the direct entry to splashdown.
    Keywords: ASTRODYNAMICS
    Type: AIAA PAPER 91-2873
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  • 4
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    Effect of parking orbit period on aerocapture for manned Mars missions (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: Aerocapture has previously been identified as a critical technology for manned Mars missions. A wide range of parking orbits is available into which an aerobraking vehicle could be captured, and earlier authors have advocated different target orbits for various reasons. The choice of the parking orbit impacts the amount of energy which must be dissipated during the atmospheric trajectory. The effect of this choice on the entry corridor width, the required vehicle L/D, and the aerothermal environment are explored in this paper.
    Keywords: ASTRODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 30; 4; p. 484-487.
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  • 5
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    Parametric study of manned aerocapture. II - Mars entry (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Keywords: ASTRODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 6; p. 814-819.
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  • 6
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    A Preliminary Investigation of Aerogravity Assist at Triton for Capture into Orbit About Neptune (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Previous work by our group has shown that an aerogravity assist maneuver at the moon Triton might be used to capture a spacecraft into a closed orbit about Neptune if a nominal atmospheric density profile at Triton is assumed. The present study extends that work and examines the impact of atmospheric dispersions, especially important in light of the very low density and large degree of uncertainty of Triton s atmosphere. Additional variables that are analyzed in the current study include ballute size and cut time and variations in the final target orbit. Results indicate that while blunt-body, rigid aeroshells penetrate too closely to the surface to be practical, ballutes of modest size show promise for this maneuver. Future studies will examine the application of inflatable aeroshells and rigid aeroshells with higher lift-to-drag ratios such as biconics and lifting bodies.
    Keywords: Space Sciences (General)
    Type: 3rd International Planetary Proe Workshop (IPPW-3); Jun 27, 2005 - Jul 01, 2005; Anavyssos; Greece
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  • 7
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    Earth return aerocapture for manned Mars missions (1991)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Lift to drag ratio (L/D) requirements and stagnation point heating have been examined for a variety of probable entry conditions and vehicle configurations. It is found that vehicles with an L/D of 0.5 or more provide a corridor width of at least 0.7 degrees while keeping the peak deceleration load below 5 g for approach velocities up to 14.5 km/s. It is shown that stagnation point peak heating rates and integrated heat load critically depend on both entry velocity and ballistic coefficient. For the most severe cases under consideration, peak heating and integrated heat load are five times greater than those encountered by Apollo but within the range of experience for unmanned vehicles.
    Keywords: ASTRODYNAMICS
    Type: AIAA PAPER 91-2874 , AIAA Atmospheric Flight Mechanics Conference; Aug 12, 1991 - Aug 14, 1991; New Orleans, LA; United States
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  • 8
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    A parametric study of manned aerocapture at Mars (1991)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The results of a parametric study of corridor width and stagnation point heating are presented for a range of a probable mission designs and vehicle configurations. Entry velocities were varied from 6 to 10 km/s, L/Ds from 0.1 to 1.0, and ballistic coefficients from 100 to 500 kg/sq m. It is found that vehicles with an L/D of 0.4 to 0.5 provide an entry corridor width of at least 1 deg for velocities up to 10 km/s. For entry velocities below approximately 7 km/s, radiative cooling may be possible for the thermal protection system. It is recommended that, at higher entry speeds, ablative heat shields be used. Maximum integrated stagnation point heat loads were equivalent to or less than those experienced by the Space Shuttle on a typical reentry.
    Keywords: ASTRODYNAMICS
    Type: AIAA PAPER 91-2871 , AIAA Atmospheric Flight Mechanics Conference; Aug 12, 1991 - Aug 14, 1991; New Orleans, LA; United States
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  • 9
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    Parametric study of manned aerocapture. I - Earth return from Mars (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: ASTRODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 6; p. 808-813.
    Format: text
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