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Optimal control theory determination of feasible return-to-launch-site aborts for the hl-20 personnel launch system vehicle
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Dutton, Kevin E. |
| Copyright Year | 1994 |
| Description | The personnel launch system (PLS) being studied by NASA is a system to complement the space shuttle and provide alternative access to space. The PLS consists of a manned spacecraft launched by an expendable launch vehicle (ELV). A candidate for the manned spacecraft is the HL-20 lifting body. In the event of an ELV malfunction during the initial portion of the ascent trajectory, the HL-20 will separate from the rocket and perform an unpowered return to launch site (RTLS) abort. This work details an investigation, using optimal control theory, of the RTLS abort scenario. The objective of the optimization was to maximize final altitude. With final altitude as the cost function, the feasibility of an RTLS abort at different times during the ascent was determined. The method of differential inclusions was used to determine the optimal state trajectories, and the optimal controls were then calculated from the optimal states and state rates. |
| File Size | 1236665 |
| Page Count | 28 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19940032752 |
| Archival Resource Key | ark:/13960/t7pp41c8j |
| Language | English |
| Publisher Date | 1994-07-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance Launch Vehicles Lifting Bodies Space Shuttles Optimal Control Flight Altitude Control Theory Aborted Missions Abort Trajectories Spacecraft Launching Trajectory Optimization Ascent Trajectories Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
