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Hyper-X Stage Separation Trajectory Validation StudiesAn independent twelve degree-of-freedom simulation of the X-43A separation trajectory was created with the Program to Optimize Simulated trajectories (POST II). This simulation modeled the multi-body dynamics of the X-43A and its booster and included the effect of two pyrotechnically actuated pistons used to push the vehicles apart as well as aerodynamic interaction forces and moments between the two vehicles. The simulation was developed to validate trajectory studies conducted with a 14 degree-of-freedom simulation created early in the program using the Automatic Dynamic Analysis of Mechanics Systems (ADAMS) simulation software. The POST simulation was less detailed than the official ADAMS-based simulation used by the Project, but was simpler, more concise and ran faster, while providing similar results. The increase in speed provided by the POST simulation provided the Project with an alternate analysis tool. This tool was ideal for performing separation control logic trade studies that required the running of numerous Monte Carlo trajectories.
Document ID
20040031535
Acquisition Source
Headquarters
Document Type
Preprint (Draft being sent to journal)
Authors
Tartabini, Paul V.
(NASA Langley Research Center Hampton, VA, United States)
Bose, David M.
(Analytical Mechanics Associates, Inc. United States)
McMinn, John D.
(NASA Langley Research Center Hampton, VA, United States)
Martin, John G.
(NASA Langley Research Center Hampton, VA, United States)
Strovers, Brian K.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2003
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA Paper 2003-5819
Report Number: AIAA Paper 2003-5819
Meeting Information
Meeting: AIAA Modeling and Simulation Technologies Conference and Exhibit
Location: Austin, TX
Country: United States
Start Date: August 11, 2003
End Date: August 14, 2003
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
OTHER: 23-706-51-71
Distribution Limits
Public
Copyright
Public Use Permitted.
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