One of the promising launch concepts that could replace the current space shuttle launch system is a two-stage, winged, vertical-takeoff, fully reusable launch vehicle. During the boost phase of ascent, the booster provides propellant for the orbiter engines through a cross-feed system. When the vehicle reaches a Mach number of 3, the booster propellants are depleted and the booster is staged and glides unpowered to a horizontal landing at a launch site runway. Two major design issues for this class of vehicle are the staging maneuver and the booster glideback. For the staging maneuver analysis, a technique was developed that provides for a successful separation of the booster from the orbiter over a wide range of staging angles of attack. A longitudinal flight control system was developed for control of the booster during the staging maneuver. For the booster glide back analysis, a guidance algorithm was developed that successfully guides the booster from the completion of the staging maneuver to a launch site runway while encountering many off-nominal atmospheric, aerodynamic, and staging conditions.


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    Title :

    Analysis of the Staging Maneuver and Booster Glideback Guidance for a Two-Stage, Winged, Fully Reusable Launch Vehicle


    Contributors:
    J. C. Naftel (author) / R. W. Powell (author)

    Publication date :

    1993


    Size :

    25 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English







    Two-stage reusable launch system utilizing a winged core vehicle and glideback boosters

    Macconochie, Ian O. / Martin, James A. / Wood, James S. et al. | NTRS | 1989


    Two-Stage Reusable Launch System Utilizing a Winged Core Vehicle and Glideback Boosters

    I. O. Macconochie / J. A. Martin / J. S. Wood et al. | NTIS | 1989