Analysis of the staging maneuver and booster glideback guidance for a two-stage, winged, fully reusable launch vehicle
- Author:
- Naftel, J. Christopher
- Published:
- Apr 1, 1993.
- Physical Description:
- 1 electronic document
- Additional Creators:
- Powell, Richard W.
- Access Online:
- hdl.handle.net
- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
- Summary:
- 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.
- Collection:
- NASA Technical Reports Server (NTRS) Collection.
- Note:
- Document ID: 19930017827.
Accession ID: 93N27016.
NASA-TP-3335.
L-17066.
NAS 1.60:3335. - Terms of Use and Reproduction:
- No Copyright.
- Access Online:
- hdl.handle.net
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