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  • 1
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    The Flying Diamond: A joined aircraft configuration design project, volume 1 (1988)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results of the analysis conducted on the Joined Wing Configuration study are presented. The joined wing configuration employs a conventional fuselage and incorporates two wings joined together near their tips to form a diamond shape in both plan view and front view. The arrangement of the lifting surfaces uses the rear wing as a horizontal tail and as a forward wing strut. The rear wing has its root at the tip of the vertical stabilizer and is structurally attached to the trailing edge of the forward wing. This arrangement of the two wings forms a truss structure which is inherently resistant to the aerodynamic bending loads generated during flight. This allows for a considerable reduction in the weight of the lifting surfaces. With smaller internal wing structures needed, the Joined Wing may employ thinner wings which are more suitable for supersonic and hypersonic flight, having less induced drag than conventional cantilever winged aircraft. Inherent in the Joined Wing is the capability of the generation of direct lift and side force which enhance the performance parameters.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-CR-184699 , NAS 1.26:184699
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Dynamics and Stability and Control Characteristics of the X-37 (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents the stability and control analysis and the control design results for the Boeing/NASA/AFRL X-37. The X-37 is a flight demonstrator vehicle that will go into space and after its mission, autonomously reenter and land on a conventional runway. This paper studies the dynamics and control of the X-37 from atmospheric reentry through landing. A nominal trajectory that lands on the Edwards Air Force Base Lakebed is considered for all the analysis and design. The X-37's longitudinal and lateral/directional bare-airframe characteristics are presented. The level of maneuvering control power is assessed. Vehicle trim with multiple surfaces is discussed. Special challenges where the wings loose roll effectiveness are discussed and solutions are presented. Aerodynamic uncertainties and flexibility modeling issues are presented. Control design results and robustness analysis methods are presented. Results are provided for the Entry, Terminal Area Energy Management (TAEM), and Approach and Land phases.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA GN&C Conference; Aug 09, 2001; Montreal; Canada
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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