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Optimal Payload Trajectory Characteristics for Horizontally Launched Booster VehicleSome future rocket launch-vehicle concepts employ rigid wings to provide horizontal landing capability of individual stages for recovery and reuse. The use of wings for recovery may make it desirable to design such vehicles for launch horizontally rather than vertically. In this note the optimal weight-to-orbit capability of a selected rocket-engine booster system using the two different launch modes is compared, and the influence of wing size on the trajectory and weight-to-orbit capability of a horizontally launched vehicle is investigated.
Document ID
19680037547
Acquisition Source
Langley Research Center
Document Type
Reprint (Version printed in journal)
Authors
Jarrell R Elliott (Langley Research Center Hampton, United States)
Timothy R Rau (Langley Research Center Hampton, United States)
Date Acquired
August 4, 2013
Publication Date
March 1, 1968
Publication Information
Publication: Journal of Spacecraft and Rockets
Publisher: American Institute of Aeronautics and Astronautics
Volume: 5
Issue: 2
Issue Publication Date: March 1, 1968
ISSN: 0022-4650
e-ISSN: 1533-6794
DOI: 10.2514/3.29222
Subject Category
Launch Vehicles and Launch Operations
Report/Patent Number
AIAA-67-558
Meeting Information
Meeting: AIAA Guidance, Control, and Flight Dynamics Conference
Location: Huntsville, AL
Country: US
Start Date: August 14, 1967
End Date: August 16, 1967
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
68A18519
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
NASA Technical Management
Keywords
NASA Langley Research Center
Rocket Launch Vehicle
Turbulent Flow
Aerodynamic Coefficients
Angle of Attack
Structural Weight
Natural Convection
Cryogenic Propellant Tanks
Small Rocket
Chemical Rocket
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